SECTION 3A ABNORMAL PROCEDURES -...

Section 3A - Abnormal Procedures

FAA Approved Airplane Flight Manual

3A-1 P/N 401-590001-0078

TABLE OF CONTENTSSUBJECT PAGE

SECTION 3AABNORMAL PROCEDURES

ABNORMAL PROCEDURES INTRODUCTION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A0-1IMMEDIATE ACTION ITEMS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A0-1NORMAL CHECKLISTS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A0-1CREW ALERTING SYSTEMS (CAS) MESSAGES (MSG). . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A0-1COMPUTER RESET. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A0-1MULTIPLE CAS MESSAGES . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A0-2MASTER WARNING / CAUTION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A0-2MCDU MENU PATH . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A0-2

ABNORMAL PROCEDURES ALPHABETICAL CAS INDEX. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A0-3GENERAL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A1-3

A1.1 REDUCED FLAP APPROACH AND LANDING . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A1-3ENGINE / APU . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A2-3

A2.1 ABORTED ENGINE START . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A2-3A2.1.1 ABORTED GROUND START. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A2-3A2.1.2 ABORTED STARTER-ASSISTED AIRSTART. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A2-3A2.1.3 ABORTED WINDMILLING AIRSTART. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A2-3

A2.2 ENGINE AIRSTART . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A2-4 FIGURE 1 - AIRSTART ENVELOPE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A2-4

A2.2.1 STARTER-ASSISTED ENGINE AIRSTART. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A2-4A2.2.2 WINDMILLING ENGINE AIRSTART . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A2-5A2.2.3 AFTER SUCCESSFUL AIRSTART . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A2-6

A2.3 SINGLE ENGINE FLIGHT AND LANDING. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A2-7A2.4 FADEC FAIL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A2-10A2.5 FADEC FAULT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A2-11A2.6 START FAIL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A2-11A2.7 START VALVE FAIL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A2-13A2.8 SINGLE THRUST REVERSER UNLOCK . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A2-14A2.9 DUAL THRUST REVERSER UNLOCK . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A2-15A2.10 APU STARTER FAIL ON . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A2-15A2.11 VIBRATION HIGH OR VIBRATION PRESENT WITHOUT INDICATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A2-16A2.12 ENGINE OIL PRESSURE HIGH (>106 PSI) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A2-17

SMOKE / FIRE / BLEED AIR . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A3-3A3.1 BLEED TEMPERATURE HIGH . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A3-3A3.2 BLEED PRESSURE HIGH . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A3-4A3.3 HP BLEED VALVE NOT CLOSED . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A3-5A3.4 L-R HP BLEED VALVE NOT CLOSED . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A3-6

ENVIRONMENTAL / PRESSURIZATION / DOORS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A4-3A4.1 AUTO PRESSURIZE FAIL / MANUAL PRESSURIZATION CONTROL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A4-3A4.2 CABIN DUCT TEMP HIGH . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A4-4A4.3 COCKPIT DUCT TEMP HIGH . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A4-5A4.4 EXTERIOR DOOR OPEN . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A4-6A4.5 INT BAGGAGE DOOR OPEN . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A4-7

Original Issue: Aug 8, 2011


3A-2

P/N 401-590001-0078Section 3A - Abnormal Procedures

SECTION 3AABNORMAL PROCEDURESTABLE OF CONTENTS (CONT’D)

SUBJECT PAGE

A4.6 OXYGEN PRESSURE LOW . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A4-7 FIGURE 1 - OXYGEN DURATION CHART - STANDARD . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A4-8 FIGURE 2 - OXYGEN DURATION CHART - OPTIONAL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A4-9A4.7 PACK FAULT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A4-10A4.8 PACK TEMP / PRESSURE HIGH . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A4-10A4.9 CABIN AIR INFLOW LOW . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A4-11A4.10 PACK AUTO SHUTDOWN . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A4-11A4.11 BAGGAGE ALTITUDE HIGH . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A4-11

ELECTRICAL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A5-3

FIGURE 1 (SHEET 1 OF 4) - ELECTRICAL POWER DISTRIBUTION CHARTS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A5-3



FIGURE 1 (SHEET 4 OF 4) - ELECTRICAL POWER DISTRIBUTION CHARTS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A5-6A5.1 AC 1 BUS FAIL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A5-7A5.2 AC 2 BUS FAIL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A5-7A5.3 DUAL AC BUS FAIL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A5-8A5.4 APU GENERATOR OVERLOAD . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A5-11A5.5 BATTERY BUS FAULT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A5-12A5.6 BATTERY CHARGE RATE HIGH . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A5-12A5.7 DC 1 BUS FAIL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A5-13A5.8 DC 2 BUS FAIL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A5-15A5.9 DUAL DC BUS FAIL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A5-16A5.10 ELECTRICAL CONTROL 1 FAIL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A5-19A5.11 ELECTRICAL CONTROL 2 FAIL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A5-21A5.12 SINGLE GENERATOR FAIL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A5-22A5.13 DUAL GENERATOR FAIL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A5-23A5.14 GENERATOR OIL PRESSURE LOW . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A5-27A5.15 GENERATOR OVERHEAT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A5-27A5.16 GENERATOR OVERLOAD . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A5-27A5.17 SPDA 1 FAIL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A5-28A5.18 SPDA 2 FAIL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A5-31A5.19 TRU OVERHEAT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A5-34A5.20 TRU OVERLOAD . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A5-35A5.21 EMER LIGHTS DISARMED . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A5-35A5.22 CB TRIP . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A5-36

INSTRUMENTS / AVIONICS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A6-3A6.1 FLAGS ON PFD, MFD, EICAS AND MCDU . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A6-3A6.2 AVIONICS TEMPERATURE HIGH . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A6-9A6.3 SINGLE DISPLAY FAULT OR OVERHEAT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A6-9A6.4 DUAL DISPLAY FAULT OR OVERHEAT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A6-10A6.5 SINGLE ADC FAILURE - RED X ON PFD FOR AIRSPEED, ALTITUDE AND VERTICAL SPEED DISPLAYS. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A6-11



TABLE OF CONTENTS (CONT’D)SUBJECT PAGE


Section 3A - Abnormal Procedures3A-3

P/N 401-590001-0078

A6.6 DUAL ADC FAILURE - RED X ON BOTH PFDS FOR AIRSPEED, ALTITUDE AND VERTICAL SPEED DISPLAYS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A6-11A6.7 SINGLE IRS FAIL, ATT FAIL ON PFD AND HDG FAIL ON PFD AND MFD . . . . . . . . . . . . . . . . . . . . . . . . . . . . A6-12A6.8 DUAL IRS FAIL, ATT FAIL ON BOTH PFDS AND HDG FAIL ON BOTH PFDS AND MFDS . . . . . . . . . . . . . . . A6-12A6.9 IRS POSITION FAULT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A6-13A6.10 IRS NOT READY . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A6-13A6.11 MAU OVERHEAT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A6-13A6.12 MAU FAN FAIL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A6-14A6.13 MAU 1A FAILURE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A6-14A6.14 MAU 2A FAILURE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A6-16A6.15 MAU 1B FAILURE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A6-18A6.16 MAU 2B FAILURE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A6-19A6.17 MAU 1A - 1B FAILURES . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A6-20A6.18 MAU 1A - 2A FAILURES / MONITOR WARNING 1 AND 2 FAILED - RED X OVER CAS FIELD. . . . . . . . . . . A6-22A6.19 MAU 1A - 2B FAILURES . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A6-24A6.20 MAU 1B - 2A FAILURES . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A6-26A6.21 MAU 1B - 2B FAILURES . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A6-28A6.22 MAU 2A - 2B FAILURES . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A6-29A6.23 AVIONICS BUS (ASCB) FAILURES / ABNORMAL DISPLAYS AND / OR 2 PFDS DISPLAYED ON LEFT OR RIGHT SIDE. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A6-31A6.24 RAD FAILURE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A6-31A6.25 AVIONICS CONFIG FAIL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A6-32A6.26 CONFIG MGMT 1-2 FAIL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A6-32A6.27 HARDWARE MISMATCH . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A6-32A6.28 FMS 1 GPS MISCOMPARE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A6-32A6.29 FMS 2 GPS MISCOMPARE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A6-32A6.30 FMS 1-2 GPS MISCOMPARE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A6-32A6.31 FMS POSITION MISCOMP . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A6-33

LANDING GEAR / BRAKES . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A7-3

FIGURE 1 - EICAS LANDING GEAR INDICATIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A7-3A7.1 EMERGENCY LANDING GEAR EXTENSION. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A7-4A7.2 LANDING GEAR THREE GREEN NOT INDICATED. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A7-5A7.3 LANDING GEAR HANDLE LOCKED DOWN . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A7-5A7.4 GEAR SYSTEM FAIL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A7-6A7.5 BRAKE WARM . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A7-6A7.6 NOSEWHEEL STEER FAIL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A7-8A7.7 BRAKE DEGRADE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A7-9A7.8 BRAKE FAILURE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A7-10A7.9 BRAKE PEDAL FAILURE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A7-11A7.10 UNCOMMANDED BRAKE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A7-11A7.11 ANTISKID FAIL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A7-12A7.12 PARK BRAKE PRESSURE LOW . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A7-13A7.13 PARK BRAKE ON . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A7-13A7.14 WEIGHT-ON-WHEELS FAILURE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A7-13



3A-4

P/N 401-590001-0078Section 3A - Abnormal Procedures

SECTION 3AABNORMAL PROCEDURESTABLE OF CONTENTS (CONT’D)

SUBJECT PAGE

HYDRAULICS. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A8-3A8.1 HYDRAULIC PRESSURE LOW . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A8-3A8.2 FLIGHT WITH HYDRAULIC FAILURE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A8-4A8.3 HYDRAULIC OVERHEAT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A8-7A8.4 EMERGENCY RUDDER SYSTEM OVERHEAT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A8-8

FLIGHT CONTROLS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A9-3A9.1 FLAP FAILURE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A9-3A9.2 FLAP LEVER DISAGREE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A9-4A9.3 SPOILER FAIL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A9-4A9.4 GROUND SPOILER FAIL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A9-6A9.5 PITCH CONTROL DISCONNECT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A9-7A9.6 ROLL CONTROL DISCONNECT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A9-8A9.7 PUSHER FAIL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A9-8A9.8 L-R SHAKER FAIL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A9-9A9.9 RUDDER FAIL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A9-9A9.10 SPEEDBRAKE EXTENDED . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A9-10A9.11 STABILIZER TRIM FAILURE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A9-10A9.12 TAKEOFF CONFIGURATION FAIL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A9-11A9.13 ELEVATOR CONTROL LIMIT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A9-11A9.14 AILERON TRIM RUNAWAY . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A9-11A9.15 RUDDER TRIM RUNAWAY . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A9-12A9.16 PITCH TRIM RUNAWAY. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A9-12A9.17 STABILIZER JAM . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A9-13A9.18 MAINTENANCE SWITCH ON . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A9-14A9.19 RIGGING FAILED . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A9-14A9.20 RIGGING IN PROGRESS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A9-14

AUTOFLIGHT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A10-3A10.1 AUTOPILOT PITCH MISTRIM . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A10-3A10.2 AUTOPILOT ROLL MISTRIM . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A10-3A10.3 AUTOPILOT STABILIZER TRIM FAIL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A10-4A10.4 AUTOPILOT MODES OFF . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A10-4A10.5 MACH TRIM FAIL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A10-5A10.6 AFCS FAIL - IRS DATA MISCOMPARE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A10-5A10.7 AFCS FAIL - ADC DATA MISCOMPARE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A10-6A10.8 YAW DAMPER OFF . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A10-6A10.9 YAW DAMPER 1-2 FAIL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A10-7A10.10 AUTOTHROTTLE DISC AND AUTOTHROTTLE 1 OR 2 FAIL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A10-7A10.11 AUTOTHROTTLE DISC AND AUTOTHROTTLE 1-2 FAIL. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A10-8A10.12 AUTOTHROTTLE 1 OR 2 FAIL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A10-8A10.13 AUTOTHROTTLE 1-2 FAIL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A10-9A10.14 NO A/T HOLD MODE DURING AUTOTHROTTLE ON TAKEOFF. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A10-9



TABLE OF CONTENTS (CONT’D)SUBJECT PAGE


Section 3A - Abnormal Procedures3A-5

P/N 401-590001-0078

FUEL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A11-3A11.1 BOOST PUMP FAIL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A11-3A11.2 FUEL FILTER BYPASS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A11-4A11.3 FUEL IMBALANCE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A11-4A11.4 FUEL TEMPERATURE LOW . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A11-5A11.5 FUEL PRESSURE LOW . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A11-6A11.6 FUEL QUANTITY LOW OR LOW FUEL ON PFD . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A11-7A11.7 FUEL PRESSURE SWITCH FAIL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A11-8

ICE / RAIN . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A12-3A12.1 EMERGENCY WINDSHIELD HEAT FAIL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A12-3A12.2 ENGINE ANTI-ICE FAIL OFF . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A12-3A12.3 ENGINE ANTI-ICE OVERPRESSURE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A12-4A12.4 ICING . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A12-4A12.5 DUAL ICE DETECTOR FAILURE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A12-5A12.6 PITOT HEAT FAIL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A12-5A12.7 L AND R PITOT HEAT FAIL OR STATIC PORT HEAT FAIL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A12-6A12.8 STANDBY PITOT HEAT FAILURE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A12-6A12.9 TAIL DE-ICE FAIL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A12-7A12.10 WINDSHIELD HEAT FAIL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A12-8A12.11 WINDSHIELD OVERHEAT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A12-8A12.12 WING ANTI-ICE FAIL OFF . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A12-9A12.13 DUAL WING ANTI-ICE FAIL OFF . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A12-9A12.14 WING ANTI-ICE OVERPRESSURE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A12-9A12.15 WING ANTI-ICE FAIL ON . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A12-10A12.16 WING ANTI-ICE TEMPERATURE LOW . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A12-11A12.17 FLIGHT AND LANDING WITH ICE ACCUMULATION ON THE WINGS. . . . . . . . . . . . . . . . . . . . . . . . . . . . A12-12A12.18 INADVERTENT ICING ENCOUNTER . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A12-14



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3A-6

P/N 401-590001-0078Section 3A - Abnormal ProceduresOriginal Issue: Aug 8, 2011



A0-1 P/N 401-590001-0078

ABNORMAL PROCEDURES INTRODUCTIONThe procedures contained in this section have been developed and recommended by the manufacturer for use in the operationof this airplane. These procedures are for guidance only in identifying acceptable operating procedures for abnormal conditions.An abnormal condition, in this context, is defined as an unusual situation in which immediate and precise action will substantiallyreduce the risk of degradation to the airplane operation.

NOTEIn these Procedures it is assumed that the positions of the Pilot and Copilot are as follows:

Pilot - occupying the left crew seat.Copilot - occupying the right crew seat.

IMMEDIATE ACTION ITEMS Abnormal Procedures do not contain immediate action items.

NORMAL CHECKLISTSCertain procedures in this section have Normal Checklists included which have been modified to fit the failure condition of theairplane. The purpose is to reduce the workload during an Emergency or Abnormal condition. Those procedures are identifiedby the appropriate statement below their heading.

CREW ALERTING SYSTEMS (CAS) MESSAGES (MSG)Throughout the procedural sections of the Airplane Flight Manual, Crew Alerting System (CAS) MSGs are organized by color asshown below:

COMPUTER RESET CAS MSGs may be reset on the ground by the following procedure:

1. Allow adequate time for the system to complete its power up BIT (Built In Test).2. If CAS MSG(s) remains posted, shutdown the airplane and remove all electrical power.3. Repower the airplane. Refer to SECTION 4 - NORMAL PROCEDURES.4. If CAS MSG(s) recur, refer to the appropriate Dispatch column of the CAS Index in this Section to determine dispatch

capability.

EMERGENCY

ABNORMAL

ADVISORY

STATUS



Section 3A - Abnormal ProceduresA0-2 P/N 401-590001-0078

MULTIPLE CAS MESSAGESSome failure cases will result in the posting of numerous additional CAUTION and ADVISORY CAS MSGs which are notcollected by the root cause CAS MSG e.g., MAU 1A FAIL posts another 6 CAUTIONS and more than 10 ADVISORIES.

The multiple CAS MSGs list posted may vary depending on the airplane operating condition at the time of failure. In theseconditions, the CAS MSG list does not always represent the precise operational state of the airplane.

The CAS MSG for the root cause will not always be displayed on top. The crew has to be aware of this and scan the list ofCAUTIONS and ADVISORIES first to find the root cause CAS MSG and to apply the applicable procedure. The root cause CASMSG will normally be one of the following CAS MSGs; , , ,

, , or .

The Flight Crew needs to review the Significant Items Lost Table and follow the abnormal procedure rather than relying on theCAS MSGs only for these conditions. The abnormal procedure addresses the actual operational state of the airplane underthese failure conditions.

MASTER WARNING / CAUTIONThe Master Warning / Caution annunciators on the glareshield are not shown. It is expected that the crew is familiar with theneed to push the master annunciator switches to acknowledge a new indication.

MCDU MENU PATHThe MCDU menu path for operation of circuit breakers controlled by the MCDU is shown in this AFM as in the followingexample:

MCDU / CB / ELEC MENU / CB BY SYSTEM / FLT CTRL 1/4 / FLAP CONTROL………CYCLE OUT, IN

The electrical menu is displayed directly without pilot selection if all circuit breakers are IN. For completeness, ELEC MENU isshown in the menu path to cover the case where one or more circuit breakers are OUT or LOCK. If all circuit breakers are IN,this step in the menu path can be ignored.

AC # Bus Fail DC # Bus Fail L-R Generator Fail

SPDA # Fail MAU # Fail Elect Ctrl # Fail CB Trip




A0-3 P/N 401-590001-0078

ABNORMAL PROCEDURES ALPHABETICAL CAS INDEX

NOTE• CAS MSGs with designations for Left, Right, Left and Right, 1, 2 or 1 and 2, are replaced with a pound

sign (#), or (# - #), respectively. The pound signs are not considered in the alphabetical ordering of theCAS MSGs in this index.

• Dispatch column addresses No Go (dispatch not permitted) or MEL (dispatch permitted, after applyingMEL procedures) or N/A (Not Applicable for dispatch).

CAS MESSAGE REF CONDITION Dispatch

AC 1 Bus Fail A5.1 AC1 Bus is unpowered due to a fault on the bus. No Go

AC 1-2 Bus Fail A5.3 AC1 and 2 Bus is unpowered due to a fault on the bus. No Go

AC 2 Bus Fail A5.2 AC2 Bus is unpowered due to a fault on the bus. No Go

AFCS Fail - ADC Miscomp A10.7 An Air Data Computer (ADC) data miscompare within the AFCS. No Go

AFCS Fail - IRS Miscomp A10.6 IRS data miscompare within the AFCS. No Go

Antiskid Fail A7.11 Antiskid system failure. No Go

AP Pitch Mistrim A10.1 Flight Only CAS MSG. Elevator servo load is high. MEL

AP Roll Mistrim A10.2 Flight Only CAS MSG. Aileron servo current is high. MEL

AP Stab Trim Fail A10.3 AP pitch trim inoperative. MEL

APU Gen Overload A5.4 The Auxiliary Power Unit (APU) generator load exceeds 16.7 KVA for >6 seconds while restoring loads after an automatic load shed. New loads will shed again in 2 minutes.

No Go

APU Starter Fail On A2.10 Start Contactor is closed when APU not in start configuration or contactor has been closed in excess of 55 seconds.

MEL

Auto Pressurize Fail A4.1 Dual-channel CPCS Built In Test (BIT) fail or cabin pressure controller BIT fail. Lost auto control to outflow valve.

MEL

Autothrottle Disc A10.10 Single A/T channel fail. MEL

AndAutothrottle 1 FailOrAutothrottle 2 FailAutothrottle Disc A10.11 Dual channel failure or manual override. MEL

AndAutothrottle 1-2 FailAutothrottle 1 Fail A10.12 Single A/T channel fail. MEL

OrAutothrottle 2 FailAutothrottle 1-2 Fail A10.13 Dual channel failure or manual override. MEL

Avionics Bus # Fail A6.23 Avionic Bus (ASCB) Failures / Abnormal Display Presentations. No Go

Avionics Config Fail A6.25 Ground Only CAS MSG. CMS inoperative or APMs miscompare or 3 APMs failed.

No Go

Avionics Temp High A6.2 Avionics rack is over 70° C (158° F) for >5 seconds. No Go

Baggage Altitude High A4.11 Baggage altitude exceeds 14,500 FT. MEL

Batt # Bus Fault A5.5 Fault on Batt # Bus for >2 seconds. No Go

Batt Charge Rate High A5.6 Battery capacity low (charge rate >25 Amps for >5 minutes) for dispatch or internal battery failure.

No Go




# Bleed Press High A3.2 Left or Right Bleed Pressure is >85 PSI for >15 seconds. No Go

# Bleed Temp High A3.1 Left or Right ECS Manifold temperature >274° C (525° F) for >5 seconds. No Go

# Boost Pump Fail A11.1 Left or Right Boost Pump failed to turn on; low pressure (press <5 PSI for >4 seconds), overheat (temperature >135° C (275° F)), or UFI trip (if installed).

MEL

Brake Degrade A7.7 Loss of one normal brake or two normal brakes not on same side gear. No Go

# Brake Fail A7.8 Loss of both wheel normal brakes on same side gear due to a dual failure of the brake control valves. Foot pedal braking is asymmetric.

No Go

Brake Warm A7.5 One or more brakes above 177° C (350° F). See Procedure

A7.5

Cabin Air Inflow Low A4.9 CPCS cannot regulate cabin pressure due to insufficient inflow. MEL

Cabin Duct Temp High A4.2 Cabin Duct >102° C (215° F) (Left ECS). MEL

CB Trip A5.22 A trip of any monitored circuit breaker. No Go

Cockpit Duct Temp High A4.3 Cockpit Duct >102° C (215° F) (Right ECS). MEL

Config Mgmt 1-2 Fail A6.26 Ground Only CAS MSG. Both CMS have failed - unable to monitor hardware / software match.

No Go

Coplt Brake Pedal Fail A7.9 Loss of any copilot brake pedal LVDT. No Go

DC 1 Bus Fail A5.7 DC 1 Bus de-energized for >5 seconds. No Go

DC 1-2 Bus Fail A5.9 Both DC 1 and 2 busses de-energized for >5 seconds. No Go

DC 2 Bus Fail A5.8 DC 2 Bus de-energized for >5 seconds. No Go

Display # Fault A6.3 Single Display BIT monitor has detected a failure. MEL

Display # Ovht A6.3 Single Display Unit >85° C (185° F). MEL

Display #-# Fault A6.4 Dual Display BIT monitor has detected a failure. No Go

Display #-# Ovht A6.4 Dual Display Unit >85° C (185° F). No Go

Elect Ctrl 1 Fail A5.10 GCU 1 Failure for >1 second. Results in loss of COM from the GCU to MAU # and A / EPCU.

No Go

Elect Ctrl 2 Fail A5.11 GCU 1 Failure for >1 second. Results in loss of COM from the GCU to MAU # and A / EPCU.

No Go

Elevator Control Limit A9.13 Control columns or elevators are near forward stops or split, with elevator controls not disconnected (detects cable break).

No Go

Emer Lights Disarmed A5.21 EMERGENCY LIGHT switch is OFF. MEL

Emer Rudder Sys Ovht A8.4 EMER RUDDER system hydraulic fluid reservoir temperature is >110° C (230° F) or motor temperature >149° C (300° F) for >2 seconds.

No Go

Emer Wshld Heat Fail A12.1 Left Windshield heat is on and the Emergency Windshield section is <10° C (50° F) for >5 seconds.

No Go

# Eng A-Ice Fail Off A12.2 Left or Right, or Left and Right, Engine anti-ice valve(s) didn't open when commanded for >5 seconds.

MEL

Or#-# Eng A-Ice Fail Off# Eng A-Ice Ovpress A12.3 Left or Right Engine anti-ice pressure is excessive. MEL

Exterior Door Open A4.4 At least 1 door not closed (Passenger Door, Emergency Exit Hatch, Ext. baggage, APU bay doors, Aft equip bay).

MEL

# FADEC Fail A2.4 Left or Right Engine has a major control problem. No Go

# FADEC Fault A2.5 Left or Right, or Left and Right, Engine(s) is operating with a limited set of engine control parameters.

No Go

Or#-# FADEC Fault





1 of 4 401-590001-0078TC3


Jul 25, 2012

ts93910

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Section 3A - Abnormal Procedures 2 of 4 401-590001-0078TC3

Temporary Changeto the


P/N 401-590001-0078TC3

SECTION 3A - ABNORMAL PROCEDURES

ABNORMAL PROCEDURES ALPHABETICAL CAS INDEX

Read the following Amber “Flap Fail” CAS MSG in place of the current Amber “Flap Fail” CAS MSG:

by: ___________________________________________ Randolph Shields, ODA Lead administrator Hawker Beechcraft Corporation ODA-230339-CE

Approval Date:___________________________________

FAA Approved

Publication Affected FAA Approved Airplane Flight Manual, P/N 401-590001-0078, dated Aug 8, 2011, or later revision for Hawker Model 4000 Airplanes.

Airplane Serial Numbers Affected

RC-59 and After or Prior Airplane Serials with Kit 401-3007 or 401-3008 or 401-3027 or 401-3028 Installed for Block Point Upgrade A.

Description of Change Revised Amber “Flap Fail” CAS MSG from “No Go” to “MEL” and added 0 degree flap information to the SINGLE ENGINE FLIGHT AND LANDING table.

Filing Instructions Insert Page 2 of 4 to face page A0-5 in Section 3A - Abnormal Procedures.Insert Page 4 of 4 to face page A2-7 in Section 3A - Abnormal Procedures.


Flap Fail A9.1 FCEU failure, LVDT error, AC2 115 VAC lost, lever not in detent >30 seconds, flap asymm, flap motor over-current >3 seconds, flap position mismatch, flap position error 2 >30 seconds.

MEL

Jul 25, 2012

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A0-5 P/N 401-590001-0078

Flap Fail A9.1 FCEU failure, LVDT error, AC2 115 VAC lost, lever not in detent >30 seconds, flap asymm, flap motor over-current >3 seconds, flap position mismatch, flap position error 2° >30 seconds.

No Go

Flap Lever Disagree A9.2 Flap lever not in a detent for >5 seconds due to crew action or flap lever switch failure.

No Go

FMS 1 GPS Miscompare A6.28 Airplane location as recorded by FMS 1 is different than the position recorded by GPS.

MEL

FMS 2 GPS Miscompare A6.29 Airplane location as recorded by FMS 2 is different than the position recorded by GPS.

MEL

FMS 1-2 GPS Miscompare A6.30 Airplane location as recorded by FMS 1 and 2 is different than the position recorded by GPS.

MEL

FMS Position Miscomp A6.31 The airplane position as reported by FMS 1 does not agree with the position reported by FMS 2, while one of the FMS is the active Nav source.

MEL

# Fuel Filter Bypass A11.2 Differential pressure across Left or Right, or Left and Right engine(s) fuel filter >22 PSI for >20 seconds (impending filter bypass).

No Go

Or#-# Fuel Filter BypassFuel Imbalance A11.3 Fuel imbalance exceeds 500 LB (227 KG). No Go

# Fuel Press Low A11.5 Left or Right Engine inlet fuel pressure <6 PSI. No Go

# Fuel Press Sw Fail A11.7 Ground Only CAS MSG. Left or Right, or Left and Right, Engine(s) fuel pressure switch(es) has failed in the high pressure state.

MEL

Or#-# Fuel Press Sw Fail# Fuel Qty Low A11.6 Left or Right, or Left and Right, Fuel quantity is low. No Go

Or#-# Fuel Qty LowFuel Temp Low A11.4 Fuel temperature is low (less than -25° C / -13° F). No Go

Gear System Fail A7.4 Normal landing gear system may not extend or retract. No Go

# Gen Oil Press Low A5.14 Left or Right Generator has low oil press (<45 PSIG). No Go

# Generator Fail A5.12 Left or Right Generator has failed. No Go

#-# Generator Fail A5.13 Left and Right Generator has failed. No Go

# Generator Overheat A5.15 Left or Right Generator oil temperature >141° C (285° F) for >5 seconds. No Go

# Generator Overload A5.16 Left or Right Generator output is >30 KVA for >6 seconds due to restoring loads after an automatic load shed.

No Go

Ground Spoiler Fail A9.4 A Ground Spoiler failure has been detected by ECMM 1 or ECMM 2. No Go

Hardware Mismatch A6.27 Ground Only CAS MSG. Hardware list does not match software level. No Go

# HP Bld Not Closed A3.3 Left or Right High Pressure Bleed valve will not close when commanded for >5 seconds.

MEL

#-# HP Bld Not Closed A3.4 Left and Right High Pressure Bleed valve will not close when commanded. No Go

# Hyd Overheat A8.3 Left or Right Hydraulic reservoir fluid temperature >110° C (230° F) for >2 seconds.

No Go

# Hyd Press Low A8.1 Left or Right, or Left and Right, Hydraulic system pressure <1600 PSI for >2 seconds.

No Go

Or#-# Hyd Press LowIce Detector 1-2 Fail A12.5 Both Ice Detectors are inoperative. MEL

Icing A12.4 Ice detected with Engine Anti-ice, Wing Anti-ice, Tail De-ice or Windshield Heat selected OFF or failed.

No Go





Int Baggage Door Open A4.5 Flight Only CAS MSG. Interior baggage door not closed above 35,500 FT. MEL

IRS # Fail A6.7 IRS 1 or 2 has suffered an alignment fault. No Go

IRS #-# Fail A6.8 IRS 1 and 2 have suffered alignment fault. No Go

IRS Not Ready A6.10 Ground Only CAS MSG. Excessive motion (>.011 FPS) detected during IRS 1 or 2, or 1 and 2 alignment on power up.

No Go

IRS Position Fault A6.9 Ground Only CAS MSG. IRS 1 or 2 did not receive GPS data on power up. No Go

Lateral Mode Off A10.4 Lateral mode has automatically changed to a degraded mode. Message removed on selection of a different lateral mode or times out 5 seconds after caution acknowledged.

N/A

Mach Trim 1-2 Fail A10.5 Flight Only CAS MSG. Mach trim is failed above Mach 0.78M or above 300 KIAS or air data lost to AFCS.

No Go

Maintenance Switch On A9.18 Ground Only CAS MSG. May indicate in-work maintenance. No Go

MAU # Ovht A6.11 MAU 1 or 2, or 1 and 2 power supply temperature >120° C (248° F). No Go

OrMAU #-# OvhtMAU 1A Fail A6.13 Failure of MAU 1 Channel A. No Go

MAU 1A-1B Fail A6.17 Failure of 2 MAU Channels as indicated. No Go


MAU 1B Fail A6.15 Failure of MAU 1 Channel B. No Go

MAU 1B-2A Fail A6.20 Failure of 2 MAU Channels as indicated. No Go

MAU 1B-2B Fail A6.21 Failure of 2 MAU Channels as indicated. No Go

MAU 2A Fail A6.14 Failure of MAU 2 Channel A. No Go


MAU 2B Fail A6.16 Failure of MAU 2 Channel B. No Go

MAU Fan Fail A6.12 MAU 1 or 2 has lost 2 or more cooling fans. No Go

Nosewheel Steer Fail A7.6 Failed NWS pressure switch or RVDT(s) or hyd valve(s) or rig error or BIT fail.

No Go

Oxy Press Low A4.6 Oxygen Pressure is <600 PSIG. MEL

# Pack Auto Shutdown A4.10 Left or Right Pack auto shutdown due to overtemperature or overpressure. MEL

# Pack Fault A4.7 Left or Right Pack control system fault - failed temp sensors, controller BIT fault, or valve failure for >12 seconds.

MEL

# Pack Temp / Press Hi A4.8 Left or Right Pack is at overtemperature or overpressure condition for >15 seconds.

MEL

Park Brake On A7.13 Flight Only CAS MSG. Park Brake not fully down. N/A

Park Brake Press Low A7.12 #1 and #2 accumulator pressure <800 PSI with the Park Brake pulled with AC power or DC power cart on.

No Go

Pilot Brake Pedal Fail A7.9 Loss of any pilot brake pedal LVDT. No Go

Pitch Disconnect A9.5 Disconnected Left - Right elevator controls. No Go

# Pitot Heat Fail A12.6 Left or Right Pitot Heat is not on (≤0.65 Amps) when commanded. MEL

#-# Pitot Heat Fail A12.7 Left and Right Pitot Heat is not on (≤0.65 Amps) when commanded. MEL

Pusher 1-2 Fail A9.7 Stall protection is unavailable or degraded. No Go

Rigging Failed A9.19 Ground Only CAS MSG. The rigging process has failed. Maintenance action has not been completed.

No Go

Rigging In Progress A9.20 Ground Only CAS MSG. System is in a rigging mode. One or more rigging is in process for AOA, aileron, elevator, stabilizer, flaps or rudder.

No Go





A0-7 P/N 401-590001-0078

Roll Disconnect A9.6 Disconnected aileron controls. No Go

Rudder Fail A9.9 Rudder Control Systems 1 and 2 failed. No Go

#-# Shaker Fail A9.8 Left and Right Stall Warning inoperative. No Go

SPDA 1 Fail A5.17 Loss of communication from SPDA1 to MAU. No Go

SPDA 2 Fail A5.18 Loss of communication from SPDA2 to MAU. No Go

Speedbrake Extended A9.10 S / B extended with Flaps >23°, or during flight below 600 FT AGL, or with either TRA >15° (N1~ 70%).

No Go

Spoiler Fail A9.3 ECMM1 or 2 detect a spoiler failure and functionality is affected. No Go

Stab Trim Fail A9.11 Normal Pitch Trim inoperative. No Go

# Start Fail A2.6 Ground Only CAS MSG. Left or Right Engine failed to start. No Go

# Start Valve Fail A2.7 Left or Right Engine starter air valve is not in FADEC commanded position after 6 seconds.

MEL

Static Port Heat Fail A12.7 Static port heating current <1.4 Amps for >2 seconds. MEL

Stby Pitot Heat Fail A12.8 Standby Pitot Heat current not sensed for >2 seconds when commanded on. MEL

T/O Config Fail A9.12 Ground Only CAS MSG. Take-off Configuration Warning System signals invalid or miscompare.

No Go

Tail De-Ice Fail A12.9 System / Switch disagree or combination actuator failure or processor failure or power supply failure or incorrect timing / sequence or unacceptable actuator performance.

MEL

# Thrust Rvsr Unlock A2.8 Left or Right sensors indicate Thrust Reverser is not properly stowed and locked, hydraulic pressure is not isolated from Thrust Reverser or the Thrust Reverse Lever is raised in flight.

MEL

#-# Thrust Rvsr Unlock A2.9 Left and Right sensors indicate Thrust Reversers are not properly stowed and locked, hydraulic pressure is not isolated from Thrust Reversers or the Thrust Reverse Levers are raised in flight.

MEL

TRU # Overheat A5.19 TRU 1 or 2, or 1 and 2 has overheated (>130º C / 266º F). No Go

OrTRU #-# Overheat

TRU # Overload A5.20 TRU 1 or 2, or 1 and 2 is in overload condition (>100% for >6 seconds). No Go

OrTRU #-# Overload

Uncommanded Brake A7.10 One or more brakes are applied (press >175 PSI) without being commanded by pilots or system.

No Go

Vertical Mode Off A10.4 Vertical mode has automatically changed to a degraded mode. Message removed on selection of a different vertical mode or times out 5 seconds after caution acknowledged.

N/A

# Windshld Heat Fail A12.10 Forward Windshields only, Control fault or temp low for >5 minutes. No Go

# Windshld Overheat A12.11 Left or Right Windshield is overheating >71° C (160° F) in flight, >82° C(180° F) on ground.

No Go

#-# Wing A-I Fail Off A12.13 Left and Right Wing Anti-ice valves failed closed for >12 seconds. MEL

# Wing A-Ice Fail Off A12.12 Left or Right Wing Anti-ice valve failed closed for >12 seconds. MEL

# Wing A-Ice Fail On A12.15 Left or Right Wing Anti-ice valve commanded closed and valve is open for >10 seconds.

MEL

Wing A-Ice Ovpress A12.14 Wing Anti-ice pressure >32 PSI for >15 seconds. MEL

Wing A-Ice Temp Low A12.16 Wing Anti-ice temperature low when ON for >2 minutes (inboard <59° C (138° F), outboard 66° C (150° F)).

MEL





WOW Fail A7.14 Two or more failed sensors and / or LGCIMs. No Go

Yaw Damper 1-2 Fail A10.9 Failure of both YD or both Air Data Systems (ADS) or both IRS or both rudder ECU.

No Go

Yaw Damper Off A10.8 YD OFF, not failed. No Go





A1-1 P/N 401-590001-0078



GENERAL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A1-3A1.1 REDUCED FLAP APPROACH AND LANDING . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A1-3




A1-2




A1-3 P/N 401-590001-0078

GENERAL

A1.1 REDUCED FLAP APPROACH AND LANDINGComplete checklists are included for DESCENT through LANDING.

1. Landing Speeds, Landing Distance and Brake Energy . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .SEE TABLE

Brake failure may occur when brake energy exceeds 46.2 MFP.

a. Verify corrected brake energy does not exceed 46.2 MFP.

NOTE• If flap position is indicated between two lever positions, use the higher of the two landing speeds.

• If yoke position is off-center for straight steady flight (possible flap asymmetry) land with minimumcrosswind. Preferred crosswind is from the side with most available yoke travel.

FOOT NOTE:

(A) Select runway with no tailwind.

DESCENT1. Anti-ice / De-ice . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . AS REQUIRED2. Seats, Seat Belts, and Rudder Pedals . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ADJUSTED / SET3. SEAT BELT / NO SMOKING. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . AS REQUIRED4. APU START / STOP (if available and if 34,000 FT or below) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON AS DESIRED5. Approach and Landing Briefing . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .CONSIDERED

APPROACH1. Altimeters. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . SET / CROSS CHECK2. EXTERNAL LIGHTS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . AS REQUIRED3. Avionics, FMS, and Flight Guidance . . . . . . . . . . . . . . . . . .SET, PROGRAMMED, SOURCE AND MODES SELECTED4. CAS MSGs . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . REVIEW5. VSPEEDS and Landing Distance. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . COMPUTED6. Approach and Landing Briefing . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . COMPLETED7. FLAP WARN . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . INHIBIT8. Nosewheel Steering. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . TILLER CLEAR

NOTEIf a touch-and-go is planned, GROUND SPOILER ARM switch must be selected OFF.

9. GROUND SPOILER . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .CONFIRM ARM10. SEAT BELT / NO SMOKING. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .AUTO, OR ON11. FLAPS (if available) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .AS DESIRED

Flap Position 0° (A) 12° 20°Landing Speed (KIAS) VREF + 25 VREF + 15 VREF + 10

Landing Distance Increase by 2600 FT (793 M) Increase by 1600 FT (488 M) Increase by 1600 FT (488 M)

Brake Energy Multiply by 2.0 Multiply by 1.7 Multiply by 1.5




BEFORE LANDING

NOTENight FLAPS UP / 0° Landing: Taxi and Landing lights may not illuminate the ground until just beforetouchdown. Ensure the approach is stable at the correct angle so that a minimum of flare is required forlanding.

1. LANDING GEAR Handle . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . DOWN / THREE GREEN2. Guidance Controller SPD Knob . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . MAN3. SPEEDBRAKE. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CONFIRM RETRACTED4. FLAPS and Landing Speed . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .SEE TABLE5. EXTERNAL LIGHTS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . AS REQUIRED

NOTEA/T Auto Retard is not available with Flaps less than 20°.

6. A/T . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .DISCONNECT AT 100 FT OR ABOVE7. AP . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . DISENGAGE AT 80 FT OR ABOVE

GO AROUND1. TO / GA . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . SELECT

NOTEIf A/T is engaged, thrust application may not be as rapid as desired. If this occurs, disconnect A/T andadvance Thrust Levers manually.

2. Thrust Levers . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . FORWARD STOP (VERIFY TAKE-OFF N1)3. Airplane Pitch Attitude . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .12° (FD PITCH COMMAND)4. FLAPS (if available) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .12°

5. LANDING GEAR Handle (positive rate of climb confirmed). . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . UP6. Climb Airspeed (minimum). . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . LANDING7. FLAPS (if available, at VREF + 25 KIAS) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .UP / 0°

8. Anti-ice / De-ice . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . AS REQUIRED

LANDING1. Airspeed. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . LANDING2. Thrust Levers . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . IDLE3. Brakes (after touchdown) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .APPLY4. SPEEDBRAKE. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . EXTEND5. Thrust Reversers (after nosewheel on ground) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . DEPLOY6. Reverse Thrust (when deployment confirmed) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . AS REQUIRED7. Nosewheel Steering (all gear firmly on ground) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . AS REQUIRED8. Reverse Thrust. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . IDLE BY 60 KIAS9. Thrust Reversers . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . STOW BY TAXI SPEED

Procedure Completed




A2-1 P/N 401-590001-0078



ENGINE / APU . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A2-3A2.1 ABORTED ENGINE START . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A2-3

A2.1.1 ABORTED GROUND START. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A2-3A2.1.2 ABORTED STARTER-ASSISTED AIRSTART. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A2-3A2.1.3 ABORTED WINDMILLING AIRSTART. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A2-3

A2.2 ENGINE AIRSTART . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A2-4 FIGURE 1 - AIRSTART ENVELOPE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A2-4

A2.2.1 STARTER-ASSISTED ENGINE AIRSTART. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A2-4A2.2.2 WINDMILLING ENGINE AIRSTART . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A2-5A2.2.3 AFTER SUCCESSFUL AIRSTART . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A2-6

A2.3 SINGLE ENGINE FLIGHT AND LANDING. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A2-7A2.4 FADEC FAIL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A2-10A2.5 FADEC FAULT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A2-11A2.6 START FAIL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A2-11A2.7 START VALVE FAIL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A2-13A2.8 SINGLE THRUST REVERSER UNLOCK . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A2-14A2.9 DUAL THRUST REVERSER UNLOCK . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A2-15A2.10 APU STARTER FAIL ON . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A2-15A2.11 VIBRATION HIGH OR VIBRATION PRESENT WITHOUT INDICATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A2-16A2.12 ENGINE OIL PRESSURE HIGH (>106 PSI) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A2-17




A2-2




A2-3 P/N 401-590001-0078

ENGINE / APU

A2.1 ABORTED ENGINE STARTA2.1.1 ABORTED GROUND START

NOTE CAS MSG may post during an aborted start. The CAS MSG will not clear if a dry spin is

conducted. It will clear when the START button is pushed for a subsequent start attempt, or if theairplane is completely powered down.

1. START (affected engine) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . PUSH TO ABORT2. FUEL / IGN (affected engine) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF

IF DRY SPIN IS REQUIRED:

NOTEStarter operation is limited to three cycles, with a minimum of 3.5 minutes off between each cycle. Afterthree cycles, 5 minutes OFF is required. A cycle is a start attempt, a wet spin, or a dry spin.

a. START (affected engine) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .PUSH AND HOLD FOR 30 SECONDS

Procedure Completed

IF DRY SPIN IS NOT REQUIRED:

Procedure Completed

A2.1.2 ABORTED STARTER-ASSISTED AIRSTART1. START (affected engine) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . PUSH TO ABORT2. FUEL / IGN (affected engine) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF3. A2.2.1 STARTER-ASSISTED ENGINE AIRSTART or

A2.2.2 WINDMILLING ENGINE AIRSTART or A2.3 SINGLE ENGINE FLIGHT AND LANDING . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .PERFORM

Procedure Completed

A2.1.3 ABORTED WINDMILLING AIRSTART1. FUEL / IGN (affected engine) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF2. CONT IGNITION (affected engine) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .AUTO3. A2.2.1 STARTER-ASSISTED ENGINE AIRSTART or

A2.2.2 WINDMILLING ENGINE AIRSTART or A2.3 SINGLE ENGINE FLIGHT AND LANDING . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .PERFORM

Procedure Completed

# Start Fail




A2.2 ENGINE AIRSTART1. Review Airstart Envelope.2. Select Starter Assist or Windmill and Starter Assist.

FIGURE 1AIRSTART ENVELOPE

A2.2.1 STARTER-ASSISTED ENGINE AIRSTART

• Do not manually engage starter until N2 has dropped below 20%.

• Although FADEC will control ITT during the start, it will not automatically terminate an airstart and itcannot ensure ITT start limits are not exceeded. The Pilot must monitor ITT during the start and ensureITT remains within start limits.

1. INFLIGHT ENGINE SHUT DOWN (E2.4) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . COMPLETE2. Icing Conditions . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . EXIT / AVOID3. Wing Anti-ice . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF4. FIRE Handle (affected engine). . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . PUSH IN5. Thrust Lever (affected engine) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CONFIRM IDLE6. FUEL / IGN (affected engine). . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . AUTO7. START (affected engine) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .PRESS, START TIMING8. ITT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . MONITOR INCREASE WITHIN 30 SECONDS AND WITHIN LIMITS9. N2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . MONITOR FOR STEADY INCREASE

RC03D 053248AB.AI

350300250150500

0

5

10

15

20

25

30

40

35

200240

100




A2-5 P/N 401-590001-0078

IF NO ITT RISE WITHIN 30 SECONDS:

a. ABORTED STARTER-ASSISTED AIRSTART (A2.1.2) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .PERFORMb. WINDMILLING ENGINE AIRSTART (A2.2.2) or SINGLE ENGINE FLIGHT AND LANDING (A2.3) . . . . .PERFORM

Procedure Completed

IF SUCCESSFUL START IS INDICATED BY STEADY RISE OF ITT AND N2 STABILIZES AT IDLE:

a. AFTER SUCCESSFUL AIRSTART (A2.2.3) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .PERFORM

Procedure Completed

A2.2.2 WINDMILLING ENGINE AIRSTART

• Although the FADEC will control ITT during the start, it will not automatically terminate an airstart and itcannot ensure ITT start limits are not exceeded. The Pilot must monitor ITT during the start and ensureITT remains within start limits.

• The minimum required N2 for attempting a Windmilling Airstart is 10% between 26,000 FT to 10,000 FTand 8% at 10,000 FT and below (refer to FIGURE 1 - AIRSTART ENVELOPE). The published airstartenvelope does not guarantee the minimum required N2 will be available at the minimum airspeeds.Increase airspeed as required to obtain the minimum required N2 prior to attempting a WindmillingAirstart. The airspeed shall be maintained throughout the start. Failure to obtain the minimum requiredN2 prior to initiating the start may result in an unsuccessful airstart, exceeding ITT start limits and / orengine damage.

NOTE• Windmilling airstarts may take as long as 2.5 minutes.

• FADEC fuel control may cause pulsing ITT near the start limits while N2 continues to increase.

1. INFLIGHT ENGINE SHUT DOWN (E2.4) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .PERFORM2. FIRE Handle (affected engine) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . PUSH IN3. Thrust Lever (affected engine). . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .CONFIRM IDLE4. CONT IGNITION (affected engine) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON5. FUEL / IGN (affected engine) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . AUTO, START TIMING6. ITT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . MONITOR INCREASE WITHIN 30 SECONDS AND WITHIN LIMITS7. N2. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . MONITOR FOR STEADY INCREASE

IF NO ITT RISE WITHIN 30 SECONDS:

a. ABORTED WINDMILLING AIRSTART (A2.1.3) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .PERFORMb. STARTER-ASSISTED ENGINE AIRSTART (A2.2.1) or

SINGLE ENGINE FLIGHT AND LANDING (A2.3). . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .PERFORM

Procedure Completed

IF SUCCESSFUL START IS INDICATED BY STEADY RISE OF ITT AND N2 STABILIZES AT IDLE:

a. AFTER SUCCESSFUL AIRSTART (A2.2.3) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .PERFORM

Procedure Completed




A2.2.3 AFTER SUCCESSFUL AIRSTART

Monitor Oil Temperature within limits before adding power, unless required for safety.

NOTEUnless required for safety, engine should be run in idle for 2 minutes before advancing thrust lever.

1. L and R GEN . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . AUTO2. L and R HYDRAULIC PUMP . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . AUTO3. L and R BLEED . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . AUTO4. L and R PACK . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . AS REQUIRED5. OIL TEMP and PRES. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .WITHIN LIMITS6. Anti-ice / De-ice . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . AS REQUIRED7. Thrust Levers . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . AS REQUIRED8. L and R CONT IGNITION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . AUTO9. APU START / STOP (if available and if 34,000 FT or below) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON AS DESIRED

Procedure Completed




3 of 4 401-590001-0078TC3


Jul 25, 2012

ts93910

Rectangle





P/N 401-590001-0078TC3

SECTION 3A- ABNORMAL PROCEDURES

A2.3 SINGLE ENGINE FLIGHT AND LANDING

ENROUTERead the following Step 8 and associated table to replace the existing Step 8 information:

8. Landing Speeds, Landing Distance and Brake Energy . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .SEE TABLE



FOOT NOTE:

(A) Select runway with no tailwind.




Description of Change Revised Amber “Flap Fail” CAS MSG from “No Go” to “MEL” and added 0 degree flap information to the SINGLE ENGINE FLIGHT AND LANDING table.

Filing Instructions Insert Page 2 of 4 to face page A0-5 in Section 3A - Abnormal Procedures.Insert Page 4 of 4 to face page A2-7 in Section 3A - Abnormal Procedures.

Flap Position 0° (Flaps Inoperative Only) (A) 20°Landing Speed (KIAS) VREF + 25 VREF + 10

Landing Distance Increase by 2600 FT (793 M) Increase by 1600 FT (488 M)

Brake Energy Multiply by 2.0 Multiply by 1.5

Jul 25, 2012

ts93910

Rectangle



A2-7 P/N 401-590001-0078

A2.3 SINGLE ENGINE FLIGHT AND LANDINGComplete checklists are included for ENROUTE through LANDING.

NOTEThis procedure is utilized when a single engine is operated at reduced thrust or shut down.

ENROUTE1. Thrust. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . MCT MAX2. Driftdown (if required) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .PERFORM

NOTESingle-engine service ceiling may be determined by reference to SECTION 5 - PERFORMANCE,SINGLE ENGINE ENROUTE NET CLIMB GRADIENT.

3. Driftdown Airspeed . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 180 KIAS4. CROSSFEED . . . . . . . . . . . . . . . . . . . . . . .AS REQUIRED TO MAINTAIN IMBALANCE LESS THAN 500 LB (227 KG)

NOTE• The A/T will disengage and will not re-engage in case of engine failure.

• AP can be engaged providing the airplane is laterally and directionally in trim. If CAS MSG is posted, disengage AP and re-trim. Then re-engage AP if desired.

• Apply appropriate RVSM contingency procedures.

5. TCAS / Transponder . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . TA / 7700, AS REQUIRED

NOTEIf both generators are not available and the APU is not running, the APU cannot be started. APU start islocked out unless at least one Engine Generator is operating.

6. APU START / STOP (at 34,000 FT or below) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON AS DESIRED7. Land. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . NEAREST SUITABLE AIRPORT8. Landing Speeds, Landing Distance and Brake Energy . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .SEE TABLE



Flap Position 20°Landing Speed (KIAS) VREF + 10

Landing Distance Increase by 1600 FT (488 M)

Brake Energy Multiply by 1.5

AP Roll Mistrim




DESCENT1. Anti-ice / Deice . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . AS REQUIRED2. Seats, Seat Belts, and Rudder Pedals. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ADJUSTED / SET3. SEAT BELT / NO SMOKING . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . AS REQUIRED4. APU START / STOP (if available and if 34,000 FT or below) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON AS DESIRED5. Approach and Landing Briefing . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CONSIDERED

APPROACH1. Altimeters . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . SET / CROSS CHECK2. EXTERNAL LIGHTS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . AS REQUIRED3. Avionics, FMS, and Flight Guidance . . . . . . . . . . . . . . . . . SET, PROGRAMMED, SOURCE AND MODES SELECTED4. CAS MSGs. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . REVIEW5. VSPEEDS and Landing Distance . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . COMPUTED6. Approach and Landing Briefing . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . COMPLETED

Failure to position the inoperative engine thrust lever to IDLE prior to landing will defeat the landing gearwarning system’s ability to detect a gear up condition during approach and landing.

7. Thrust Lever (inoperative engine) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . VERIFY IDLE8. FLAP WARN . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . INHIBIT9. Nosewheel Steering . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . TILLER CLEAR

10. GROUND SPOILER. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CONFIRM ARM11. SEAT BELT / NO SMOKING . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . AUTO, OR ON12. FLAPS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . AS DESIRED

BEFORE LANDING1. LANDING GEAR Handle . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . DOWN / THREE GREEN2. Guidance Controller SPD Knob . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . MAN3. SPEEDBRAKE. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CONFIRM RETRACTED4. Flaps and Landing Speed . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .SEE TABLE5. EXTERNAL LIGHTS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . AS REQUIRED6. AP . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . DISENGAGE AT 80 FT OR ABOVE

SINGLE ENGINE GO AROUND

NOTEThe FD pitch command should only be used as initial guidance. Pitch adjustments may be required inorder to maintain VAPP.

1. TO / GA . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . SELECT2. Thrust Lever (operating engine). . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . FORWARD STOP (VERIFY TAKE-OFF N1)3. FLAPS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .12°

4. LANDING GEAR Handle (positive rate of climb confirmed). . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . UP5. Climb Airspeed (until clear of obstacles) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . VAPP

6. FLAPS (VREF + 25 KIAS). . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .UP / 0°





A2-9 P/N 401-590001-0078

LANDING1. Airspeed. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . VREF + 10 KIAS2. Thrust Levers. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .IDLE3. Brakes (after touchdown). . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .APPLY4. SPEEDBRAKE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . EXTEND

Directional control will be adversely affected by use of asymmetric reverse thrust. Use caution whendeploying Thrust Reversers and applying asymmetric reverse thrust.

5. Thrust Reversers (after nosewheel on ground) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . DEPLOY6. Reverse Thrust (when deployment confirmed) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . AS REQUIRED7. Nosewheel Steering (all gear firmly on ground). . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . AS REQUIRED8. Reverse Thrust . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .IDLE BY 60 KIAS9. Thrust Reversers . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . STOW BY TAXI SPEED

NOTEThe following is applicable if one engine is shut down:

The PTU will shut down if the EMERGENCY / PARK BRAKE is set with the airplane on the ground. Thiswill cause loss of hydraulic pressure on the side of the failed engine while the EMERGENCY / PARKBRAKE is set. Nosewheel Steering will fail due to loss of right hydraulic pressure.

Procedure Completed




A2.4 FADEC FAIL

NOTE• Engine may not respond to thrust lever movements, may run only at idle thrust, may surge or flameout.

• A/T and Engine Sync will disconnect.

IN FLIGHT

IF ENGINE SURGES OR INSTABILITY IS EXPERIENCED:

1. Land . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . NEAREST SUITABLE AIRPORT2. INFLIGHT ENGINE SHUT DOWN (E2.4) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . PERFORM

Procedure Completed

IF ENGINE CONTINUES TO RUN NORMALLY:

1. L and R CONT IGNITION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .ON2. Engine Instruments . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . MONITOR3. A/T . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . VERIFY DISCONNECTED4. Thrust Lever (affected engine) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .AVOID RAPID MOVEMENTS5. Land . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .AS SOON AS PRACTICAL

Procedure Completed

ON GROUND1. EMER / PARKING BRAKE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . SET2. FUEL / IGN (affected engine). . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF3. NORMAL PROCEDURES - SHUT DOWN and SECURING. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . PERFORM

Procedure Completed

L FADEC FailOr

R FADEC Fail




A2-11 P/N 401-590001-0078

A2.5 FADEC FAULT

NOTE• Engine may surge or performance may be affected.

• A/T and Engine Sync will disconnect.

IN FLIGHT1. Engine Instruments . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . MONITOR2. Thrust Lever (affected engine(s)) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . AVOID RAPID MOVEMENTS

Procedure Completed

DURING ENGINE GROUND START1. FUEL / IGN (affected engine(s)) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF

Procedure Completed

A2.6 START FAIL

If starter has disengaged, do not press START until N2 has dropped below 20%.

NOTE CAS MSG may post during an aborted start. The CAS MSG will not clear if a dry spin is

conducted. It will clear when the START button is pushed for a subsequent start attempt, or if theairplane is completely powered down.

CAS MSG will post only during ground starts. FADEC will “Auto Abort” the engine start bycutting fuel / ignition if:

• ITT has increased by less than 15°, 20 seconds after initiating start;

• N2 is less than 5.2% for more than 15 seconds after the start is initiated;

• N1 speed is not detected before N2 reaches idle;

• Inlet Guide Vane not positioned correctly.

L FADEC FaultOr

R FADEC FaultOr

L-R FADEC Fault

L Start FailOr

R Start Fail

# Start Fail

# Start Fail




• If ITT exceeds the temperature threshold for the duration listed in the table below;

NOTEFADEC alternates between the two ignitors for every start. If one ignitor is inoperative, the 2nd startattempt will be successful on the operational ignitor. Refer to MEL for dispatch with single ignitor.

1. Engine Indications . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . MONITOR2. FUEL / IGN (affected engine). . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF

IF LIMITS WERE EXCEEDED:

a. No Dispatch.

Procedure Completed

IF NO LIMITS WERE EXCEEDED:

NOTEStarter operation is limited to three cycles, with a minimum of 3.5 minutes off between each cycle. Afterthree cycles, 5 minutes OFF is required. A cycle is a start attempt, a wet spin, or a dry spin.

a. START (affected engine, dry spin) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . PUSH AND HOLD FOR 30 SECONDSb. Normal Start (third cycle). . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . PERFORM

Procedure Completed

ITT Abort LimitTemperature Threshold

(Degrees C)

Maximum Time Above ITT Temperature Threshold

(Seconds)ITT >= 930 0

ITT >= 920 1

ITT >= 900 4

ITT >= 850 8

ITT >= 800 13

ITT >= 700 25

ITT >= 600 35




A2-13 P/N 401-590001-0078

A2.7 START VALVE FAIL

IN FLIGHT

APU Bleed Valve must remain OFF after landing if Left Start Valve is affected.

IF START VALVE FAILED OPEN:

1. BLEED (affected side) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF2. BLEED ISOLATE. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CLOSE3. Affected Side ITT. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . MONITOR4. Operative PACK . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . HIGH FLOW

(CABIN = LEFT PACK, FLIGHT DECK = RIGHT PACK)

Procedure Completed

IF START VALVE FAILED CLOSED:

1. FUEL / IGN (affected engine) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF2. Operative PACK . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . HIGH FLOW

(CABIN = LEFT PACK, FLIGHT DECK = RIGHT PACK)3. WINDMILLING ENGINE AIRSTART (A2.2.2) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .PERFORM4. Affected Side ITT. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . MONITOR

Procedure Completed

ON GROUND

IF ENGINE STARTED SUCCESSFULLY (START VALVE FAILED OPEN):

1. FUEL / IGN (affected engine) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF2. BLEED (affected side) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF3. APU BLEED. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF4. External Air (if used) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .DISCONNECT5. BLEED ISOLATE. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CLOSE6. Notify Maintenance before any further start attempt.

NOTE• The engine can be started by manually opening and closing the Start Valve. The Start Valve can be

accessed through an opening in the engine cowling. Refer to Airplane Maintenance Manual forprocedure.

• APU Bleed Valve must remain OFF if Left Start Valve is affected.

7. Dispatch via MEL.

Procedure Completed

L Start Valve FailOr

R Start Valve Fail




IF NO N2 ROTATION (START VALVE FAILED CLOSED):

1. FUEL / IGN (affected engine). . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF2. Bleed Pressure. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . VERIFY 38 PSI MINIMUM

IF BLEED PRESSURE <38 PSI:

a. Bleed Source. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . SELECTb. Bleed Pressure . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . VERIFY 38 PSI MINIMUMc. Normal Engine Start . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . PERFORM

Procedure Completed

IF BLEED PRESSURE >38 PSI:

a. Notify Maintenance before any further start attempt.

NOTEThe engine can be started by manually opening and closing the Start Valve. The Start Valve can beaccessed through an opening in the engine cowling. Refer to Airplane Maintenance Manual forprocedure.

b. Dispatch via MEL.

Procedure Completed

A2.8 SINGLE THRUST REVERSER UNLOCK

Multiple sensors indicate Thrust Reverser is not properly stowed and locked, hydraulic pressure is not isolated from ThrustReverser or the Thrust Reverse lever is raised in flight.

Do not raise Thrust Reverse lever in flight.

1. Thrust Reverse Lever (affected side). . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . VERIFY STOWED

IF CAS MSG IS STILL POSTED:

a. Thrust Lever (affected engine) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . IDLEb. Thrust Reverser Valves CB (affected engine). . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .OUT (A)c. Engine Thrust Rating. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . MCTd. APU START / STOP (if available and if 34,000 FT or below) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON AS DESIREDe. Land . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . NEAREST SUITABLE AIRPORTf. SINGLE ENGINE FLIGHT AND LANDING (A2.3) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . PERFORM

FOOT NOTE:

(A) MCDU / CB / ELEC MENU / CB BY SYSTEM / ENGINE / 3/5 L T/R VALVES or 5/5 R T/R VALVES.

Procedure Completed

IF AMBER “# Thrust Rvsr Unlock” CAS MSG IS CLEARED:

Procedure Completed

L Thrust Rvsr UnlockOr

R Thrust Rvsr Unlock

# Thrust Rvsr Unlock




A2-15 P/N 401-590001-0078

A2.9 DUAL THRUST REVERSER UNLOCK

Multiple sensors indicate Thrust Reversers are not properly stowed and locked, hydraulic pressure is not isolated from ThrustReversers or the Thrust Reverse levers are raised in flight.

Do not raise Thrust Reverse levers in flight.

1. Thrust Reverse Levers . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .VERIFY STOWED


a. Thrust Reverser Valves CBs. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . BOTH SIDES OUT (A)b. Land . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . NEAREST SUITABLE AIRPORT

FOOT NOTE:

(A) MCDU / CB / ELEC MENU / CB BY SYSTEM / ENGINE / 3/5 L T/R VALVES and 5/5 R T/R VALVE.

Procedure Completed

IF AMBER “L-R Thrust Rvsr Unlock” CAS MSG IS CLEARED:

Procedure Completed

A2.10 APU STARTER FAIL ON

IN FLIGHT1. APU START / STOP . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF


a. BATTERY 2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF

NOTEBackup power to ERS will be lost with BATTERY 2 OFF.

Procedure Completed

ON GROUND1. APU START / STOP . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF2. SECTION 4 - NORMAL PROCEDURES - SHUT DOWN . . . . . . . . . . . . . . . . . . . . . . . . . . . PERFORM, AS REQUIRED3. External Power . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .DISCONNECT4. Dispatch per MEL.

Procedure Completed

L-R Thrust Rvsr Unlock

L-R Thrust Rvsr Unlock

APU Starter Fail On

APU Starter Fail On




A2.11 VIBRATION HIGH OR VIBRATION PRESENT

WITHOUT INDICATION

NOTEVIB indication, EICAS Engine Display below N2 indication, is Red above 1.00, Amber 0.96 to 1.00, Whiteat or below 0.95. Vibration display is removed when levels for both engines are below 0.81 for 5 minutes.

IN FLIGHT1. Thrust Lever (affected engine) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . RETARD SLOWLY

IF VIB INDICATION REMAINS AT OR ABOVE 0.96 OR VIBRATION IS PRESENT OR OTHER INDICATIONS ARE OUT OF LIMITS:

a. INFLIGHT ENGINE SHUT DOWN (E2.4) (affected engine) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . PERFORMb. Vibration . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . MONITOR

IF VIBRATION REMAINS:

1) Airspeed . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . REDUCE AS REQUIRED TO MINIMIZE VIBRATION2) Maximum airspeed with vibration present . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 180 KIAS (ABOVE 25,000 FT)

225 KIAS (AT OR BELOW 25,000 FT)3) Land . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . NEAREST SUITABLE AIRPORT

Procedure Completed

IF VIBRATION STOPS:

1) Land . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . NEAREST SUITABLE AIRPORT

Procedure Completed

IF OTHER INDICATIONS ARE NORMAL AND VIB INDICATION RETURNS TO WHITE:

a. Engine Indications . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . MONITORb. Thrust Lever (affected engine) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . LIMIT TO KEEP VIB BELOW 0.96c. TCAS. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .TA ONLYd. Land . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .AS SOON AS PRACTICAL

Procedure Completed

ON GROUND1. Do not dispatch if Vibration Indication is 0.81 or above.

Procedure Completed

VIB[ENGINE DISPLAY]

0.96 TO 1.00




A2-17 P/N 401-590001-0078

A2.12 ENGINE OIL PRESSURE HIGH (>106 PSI)

IN FLIGHT 1. Thrust Lever (affected engine). . . . . . . . . . . . . . . . . . . . . . . . . . . . . REDUCE TO MAINTAIN OIL PRESSURE ≤106 PSI

IF OIL PRESSURE DOES NOT REDUCE ≤106 PSI:

a. Thrust Lever (affected engine) . . . . . . . . . . . . . . . . . . REDUCE TO KEEP OIL PRESSURE AS LOW AS POSSIBLEb. SINGLE ENGINE FLIGHT AND LANDING (A2.3). . . . . . . . . . . . . . . . . . . . . . . . . . . . . . PERFORM, AS REQUIRED

Procedure Completed

IF OIL PRESSURE IS REDUCED:

a. Thrust Lever (affected engine) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . MAINTAIN OIL PRESSURE ≤106 PSIb. SINGLE ENGINE FLIGHT AND LANDING (A2.3). . . . . . . . . . . . . . . . . . . . . . . . . . . . . . PERFORM, AS REQUIRED

Procedure Completed

ON GROUND

NOTEOil pressure above 106 PSI is permitted during an Engine Cold Start (oil temperature <0° C). MaximumOil pressure is 220 PSI until 10° C oil temperature is reached. Engine should run for an additional 3minutes after 10° C oil temperature is reached.

IF OIL PRESSURE DOES NOT REDUCE ≤106 PSI:

1. SECTION 4 - NORMAL PROCEDURES - SHUT DOWN and SECURING . . . . . . . . . . . . . . . . . . . . . . . . . . .PERFORM2. No Dispatch.

Procedure Completed

IF OIL PRESSURE IS REDUCED:

1. Normal dispatch.

Procedure Completed




A3-1 P/N 401-590001-0078



SMOKE / FIRE / BLEED AIR . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A3-3A3.1 BLEED TEMPERATURE HIGH . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A3-3A3.2 BLEED PRESSURE HIGH . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A3-4A3.3 HP BLEED VALVE NOT CLOSED . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A3-5A3.4 L-R HP BLEED VALVE NOT CLOSED . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A3-6




A3-2




A3-3 P/N 401-590001-0078

SMOKE / FIRE / BLEED AIR

A3.1 BLEED TEMPERATURE HIGH

NOTEOn Bleed Synoptic the Left or Right Bleed Temperature indication will show amber dashes for 5 secondspreceding the Bleed Temperature exceedance displayed in amber inverse video.

IN FLIGHT

IF CAS MSG IS POSTED AND R BLEED IS ON:

1. BLEED ISOLATE. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . VERIFY OPEN2. L BLEED . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF

Procedure Completed

IF CAS MSG IS POSTED AND R BLEED IS OFF:

1. Thrust Lever (left engine). . . . . . . . . . . . . . REDUCE SLOWLY UNTIL CAS MSG IS CLEARED

2. Cabin Altitude . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . MONITOR3. SINGLE ENGINE FLIGHT AND LANDING (A2.3) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .PERFORM

Procedure Completed

IF CAS MSG IS POSTED AND L BLEED IS ON:

1. BLEED ISOLATE. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . VERIFY OPEN2. R BLEED . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF

Procedure Completed

IF CAS MSG IS POSTED AND L BLEED IS OFF:

1. Thrust Lever (right engine) . . . . . . . . . . . REDUCE SLOWLY UNTIL CAS MSG IS CLEARED

2. Cabin Altitude . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . MONITOR3. SINGLE ENGINE FLIGHT AND LANDING (A2.3) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .PERFORM

Procedure Completed

ON GROUND1. BLEED (affected side) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF2. APU START/STOP . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF3. No Dispatch.

Procedure Completed

L Bleed Temp HighOr

R Bleed Temp High

L Bleed Temp High

L Bleed Temp High

L Bleed Temp High

R Bleed Temp High

R Bleed Temp High

R Bleed Temp High




A3.2 BLEED PRESSURE HIGH

IN FLIGHT

IF CAS MSG IS POSTED AND R BLEED IS ON:

1. BLEED ISOLATE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . VERIFY CLOSED2. L BLEED . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .OFF3. FLIGHT DECK HIGH FLOW . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . HIGH

Procedure Completed

IF CAS MSG IS POSTED AND R BLEED IS OFF:

1. BLEED ISOLATE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . VERIFY CLOSED

2. Thrust Lever (left engine) . . . . . . . . . . . . . REDUCE SLOWLY UNTIL CAS MSG IS CLEARED

3. CABIN HIGH FLOW. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . HIGH4. SINGLE ENGINE FLIGHT AND LANDING (A2.3) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . PERFORM

Procedure Completed

IF CAS MSG IS POSTED AND L BLEED IS ON:

1. BLEED ISOLATE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . VERIFY CLOSED2. R BLEED . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .OFF3. CABIN HIGH FLOW. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . HIGH

Procedure Completed

IF CAS MSG IS POSTED AND L BLEED IS OFF:

1. BLEED ISOLATE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . VERIFY CLOSED

2. Thrust Lever (right engine). . . . . . . . . . . . REDUCE SLOWLY UNTIL CAS MSG IS CLEARED

3. FLIGHT DECK HIGH FLOW . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . HIGH4. SINGLE ENGINE FLIGHT AND LANDING (A2.3) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . PERFORM

Procedure Completed

ON GROUND1. BLEED (affected side) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF2. BLEED ISOLATE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CLOSE3. No Dispatch.

Procedure Completed

L Bleed Press HighOr

R Bleed Press High

L Bleed Press High

L Bleed Press High

L Bleed Press High

R Bleed Press High

R Bleed Press High

R Bleed Press High




A3-5 P/N 401-590001-0078

A3.3 HP BLEED VALVE NOT CLOSED

NOTE• ITT on affected side will increase at higher thrust settings.

• Fuel planning is affected.

• Amber “# HP Bld Not Closed” CAS MSG will clear during rejected takeoff.

IF DURING TAKEOFF (BELOW 80 KIAS):

1. REJECTED TAKEOFF (E1.1). . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .PERFORM

Procedure Completed

IF ABOVE 400 FT:

1. Thrust Lever (affected engine). . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . REDUCE TO KEEP ITT IN LIMITS

NOTEBleed Temperature and Bleed Pressure on affected side may be abnormal.

2. Bleed Synoptic . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . MONITOR BLEED TEMPERATURE AND PRESSURE3. Fuel . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CALCULATE RANGE

NOTEAmber “# HP Bld Not Closed” CAS MSG may clear when Thrust Lever on affected side is reduced belowapproximately 84% N1 during descent.

Prior to Landing:4. BLEED (affected side) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF

Procedure Completed

L HP Bld Not ClosedOr

R HP Bld Not Closed




A3.4 L-R HP BLEED VALVE NOT CLOSED

NOTE• ITTs will increase at higher thrust settings.

• Fuel planning is affected.

• Amber “L-R HP Bld Not Closed” CAS MSG will clear during rejected takeoff.

IF DURING TAKEOFF (BELOW 80 KIAS):

1. REJECTED TAKEOFF (E1.1) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . PERFORM

Procedure Completed

IF ABOVE 400 FT:

1. Thrust Levers . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . REDUCE AS CONDITIONS PERMIT

NOTEBleed Temperatures and Bleed Pressures may be abnormal.

2. Bleed Synoptic . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . MONITOR BLEED TEMPERATURES AND PRESSURES3. Fuel . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CALCULATE RANGE

NOTEAmber “L-R HP Bld Not Closed” CAS MSG may clear when Thrust Levers are reduced belowapproximately 84% N1 during descent.

Prior to Landing by 1500 FT AGL:1. L and R BLEED (if wing anti-ice is not in use) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF

Procedure Completed

L-R HP Bld Not Closed




A4-1 P/N 401-590001-0078



ENVIRONMENTAL / PRESSURIZATION / DOORS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A4-3A4.1 AUTO PRESSURIZE FAIL / MANUAL PRESSURIZATION CONTROL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A4-3A4.2 CABIN DUCT TEMP HIGH . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A4-4A4.3 COCKPIT DUCT TEMP HIGH . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A4-5A4.4 EXTERIOR DOOR OPEN . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A4-6A4.5 INT BAGGAGE DOOR OPEN . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A4-7A4.6 OXYGEN PRESSURE LOW . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A4-7 FIGURE 1 - OXYGEN DURATION CHART - STANDARD . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A4-8 FIGURE 2 - OXYGEN DURATION CHART - OPTIONAL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A4-9A4.7 PACK FAULT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A4-10A4.8 PACK TEMP / PRESSURE HIGH . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A4-10A4.9 CABIN AIR INFLOW LOW . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A4-11A4.10 PACK AUTO SHUTDOWN . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A4-11A4.11 BAGGAGE ALTITUDE HIGH . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A4-11




A4-2




A4-3 P/N 401-590001-0078

ENVIRONMENTAL / PRESSURIZATION / DOORS

A4.1 AUTO PRESSURIZE FAIL / MANUAL PRESSURIZATIONCONTROL

IN FLIGHT1. PRESSURIZATION MANUAL CONTROL. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .CYCLE

IF CABIN PRESSURE AUTO CONTROL CANNOT BE RESTORED:

a. MANUAL PRESSURIZATION CONTROL. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .PERFORM

IF CABIN PRESSURE AUTO CONTROL IS RESTORED:

Procedure Completed

MANUAL PRESSURIZATION CONTROL

1. PRESSURIZATION MANUAL CONTROL. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .MAN2. MANUAL CABIN ALT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ADJUST OUTFLOW VALVE AS REQUIRED

a. ΔP (EICAS) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . FOR CRUISE, DETERMINE TARGET VALUE PER TABLEb. CABIN RATE (EICAS) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . KEEP RATE BELOW 500 FT / MINUTEc. MANUAL CABIN ALT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . SET HOLD AT REQUIRED ΔP

NOTE• MANUAL CABIN ALT will need to be adjusted with changes in altitude and / or thrust.

• In cruise, an outflow valve setting of approximately 15% to 16% (on EICAS) will be required.

• Airplane must be manually depressurized before landing to ensure Cabin Door and Emergency ExitDoor will open on ground.

• To ensure electronic maximum ΔP relief, do not descend cabin altitude below -1000 FT.

Prior to Landing by 1500 FT AGL:3. ΔP . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .0.00 PSI4. CABIN DEPRESSURIZATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . DUMP

Procedure Completed

ON GROUND1. PRESSURIZATION MANUAL CONTROL. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .CYCLE

IF CABIN PRESSURE AUTO CONTROL CANNOT BE RESTORED:

a. Dispatch per MEL.

Procedure Completed

FLT LEVEL 180 200 220 240 260 280 290 310 330 350 370 380

CABIN ALT (FT) 1100 1300 1500 1700 2000 2300 2400 2800 3200 3500 3900 4200

TARGET ΔP (PSI) 6.8 7.3 7.7 8.1 8.5 8.8 8.9 9.1 9.3 9.5 9.64 9.64

Auto Pressurize Fail




IF CABIN PRESSURE AUTO CONTROL IS RESTORED:

a. Normal Dispatch

Procedure Completed

A4.2 CABIN DUCT TEMP HIGH 1. ECS Synoptic . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK DUCT TEMP2. CABIN TEMP SELECT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . COOL

IF ECS DUCT TEMP NOT REDUCING OR CAS MSG IS STILL POSTED AFTER 30 SECONDS:

a. CABIN MANUAL COOL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . MAN

IF MANUAL COOL INEFFECTIVE:

1) L PACK. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF2) R PACK . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . HIGH FLOW


Procedure Completed

IF MANUAL COOL EFFECTIVE:

Procedure Completed

IF AMBER “Cabin Duct Temp High” CAS MSG IS CLEARED:

Procedure Completed

Cabin Duct Temp High

Cabin Duct Temp High




A4-5 P/N 401-590001-0078

A4.3 COCKPIT DUCT TEMP HIGH 1. ECS Synoptic. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK DUCT TEMP2. FLIGHT DECK TEMP SELECT. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . COOL

IF ECS DUCT TEMP NOT REDUCING OR CAS MSG IS STILL POSTED AFTER 30 SECONDS:

a. FLIGHT DECK MANUAL COOL. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .MAN

IF MANUAL COOL INEFFECTIVE:

1) R PACK . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF2) L PACK . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . HIGH FLOW


Procedure Completed

IF MANUAL COOL EFFECTIVE:

Procedure Completed

IF AMBER “Cockpit Duct Temp High” CAS MSG IS CLEARED:

Procedure Completed

Cockpit Duct Temp High

Cockpit Duct Temp High




A4.4 EXTERIOR DOOR OPEN

IN FLIGHT1. SEAT BELT / NO SMOKING . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .ON2. ECS Synoptic . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . DETERMINE OPEN DOOR

IF PASSENGER DOOR INDICATES OPEN:

a. Interior Door Handle . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .VERIFY HANDLE IS FULLY DOWN


NOTE• Pilot’s and Copilot’s PFD Airspeed and Altitude may be unreliable.


1) Stby Inst . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . MONITOR ALTITUDE AND AIRSPEED2) AP and A/T . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . DISCONNECT3) Land . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . NEAREST SUITABLE AIRPORT

Procedure Completed

IF AMBER “Exterior Door Open” CAS MSG IS CLEARED:

Procedure Completed

IF EMERGENCY EXIT OR BAGGAGE DOOR INDICATES OPEN:

a. Emergency Exit or Baggage Door. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . VERIFY SECURE

IF NOT SECURE:

1) Land . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . NEAREST SUITABLE AIRPORT

Procedure Completed

IF SECURE:

Procedure Completed

IF APU BAY OR AFT BAY INDICATES OPEN:

IF VIBRATION OR BUFFET PRESENT:

1) Airspeed . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . REDUCE TO 250 KIAS OR BELOW2) Avoid high maneuvering loads.3) Land . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . NEAREST SUITABLE AIRPORT

Procedure Completed

IF NO VIBRATION OR BUFFET PRESENT:

1) Avoid high maneuvering loads.2) Land . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . NEAREST SUITABLE AIRPORT

Procedure Completed

Exterior Door Open

Exterior Door Open




A4-7 P/N 401-590001-0078

ON GROUND1. Doors . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .CHECK VISUALLY AND SECURE IF NOT CLOSED



Procedure Completed

IF AMBER “Exterior Door Open” CAS MSG IS CLEARED:

a. Normal Dispatch.

Procedure Completed

A4.5 INT BAGGAGE DOOR OPEN 1. Baggage Compartment . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . UNOCCUPIED2. Interior Baggage Door . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CLOSE (CONFIRM LATCHED)

IF CAS MSG IS STILL POSTED AND DOOR CANNOT BE CLOSED:

a. Altitude . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 35,000 FT OR BELOWb. Land . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . AS SOON AS PRACTICAL

Procedure Completed

IF CAS MSG IS STILL POSTED AND DOOR HAS BEEN CONFIRMED CLOSED:

a. Interior Baggage Door. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . KEEP CLOSED

Procedure Completed

IF AMBER “Int Baggage Door Open” CAS MSG CLEARED:

a. Interior Baggage Door. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . KEEP CLOSED

Procedure Completed

A4.6 OXYGEN PRESSURE LOW 1. ECS Synoptic. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . REVIEW OXYGEN PRESSURE2. Oxygen Duration . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .CALCULATE (REFER TO FIGURE 1 OR 2)

IF NO ECS SYNOPTIC AVAILABLE OR DURATION IS EXCEEDED OR PRESSURE DROPS RAPIDLY:

a. Altitude . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 25,000 FT MSL OR MINIMUM SAFE ALTITUDE IF HIGHER

Procedure Completed

IF DURATION IS SUFFICIENT:

a. ECS Synoptic . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . MONITOR

Procedure Completed

Exterior Door Open

Int Baggage Door Open



Oxy Press Low




FIGURE 1OXYGEN DURATION CHART - STANDARD

RC03D 073063AB.AI

0

500

1000

1500

2000

2500

0 10 20 30 40 50 60 70 80 90 100

10,000 15,000 20,000 25,000 30,000 35,000 40,000CREW (2) 100% 109 134 170 218 287 388 545PASSENGERS

1 101 120 146 176 215 2612 94 109 128 147 172 1973 89 100 114 127 143 1584 84 92 102 111 123 1325 79 85 93 99 107 1136 75 80 85 89 96 99

N O. O F USERSCABIN ALTITUDE (FEET)

7 71 75 79 82 88 908 68 71 74 76 81 829 65 67 69 70 73 74

10 62 63 64 64 66 66

40,000545CREW (2 NORMAL)

10,000 15,000 20,000 25,000 30,000 35,000610 682 602 253 291 388

PASSENGERS1 430 431 380 198 218 2612 332 315 278 162 174 1973 270 248 219 138 144 158

22 20 1 1 11 1 4 1319 17 15 1 6 1 8 1117 15 13 4 9 9160 139 122 87 88 90146 126 111 81 82

NO. OF USERSCABIN ALTITUDE (FEET)

4 8 5 8 9 2 25 7 4 4 0 0 36 4 2 4 9 6 978 80

132 113 99 73 749 73118 100 88 66 6610 67

__

__

____

__

__

__

____

__

For Interpolation Only





A4-9 P/N 401-590001-0078

FIGURE 2OXYGEN DURATION CHART - OPTIONAL

RC03D 073062AB.AI

0

500

1000

1 500

2 000

2 500

0 10 20 30 40 50 60 70 80 90 100

10,000 15,000 20,000 25,000 30,000 35,000 40,000CREW (2) 100% 158 195 246 316 416 564 792PASSENGERS

1 147 175 212 255 312 3792 137 159 185 214 250 2853 129 145 165 184 208 2294 121 134 149 161 178 1915 115 124 135 144 156 1646 109 115 124 129 139 144


7 104 109 116 120 128 1328 99 103 108 111 117 1209 94 97 100 102 106 108

10 90 91 93 93 96 96

40,000792

10,000 15,000 20,000 25,000 30,000 35,000CREW (2 NORMAL) 886 990 873 367 423 564

PASSENGERS1 624 625 552 287 316 3792 482 457 404 236 252 2853 393 360 318 200 210 2294 331 297 262 173 180 1915 286 253 223 153 157 1646 252 220 194 137 139 144


7 231 201 177 127 128 1328910

211191171

182 161 117 117 120163 144 107 106 108145 128 97 96 96

__

__

____

__

__

__

____

__






A4.7 PACK FAULT

1. PACK (affected side) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .OFF, THEN ON


a. PACK (affected side). . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFFb. Remaining PACK . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . HIGH FLOW


Procedure Completed

IF AMBER “# Pack Fault” CAS MSG IS CLEARED:

Procedure Completed

A4.8 PACK TEMP / PRESSURE HIGH

NOTEA High Pack Temperature or Pressure condition will normally result in an automatic pack shutdown if indual pack configuration.

1. PACK (affected side) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF2. ECS Synoptic . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . SELECT TO DETERMINE PACK STATUS

IF IN DUAL PACK CONFIGURATION (SHUTDOWN FAILED):

a. BLEED (affected side). . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFFb. APU START / STOP (for left pack only) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFFc. BLEED ISOLATE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CLOSEd. Remaining PACK . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . HIGH FLOW


Procedure Completed

IF IN SINGLE PACK CONFIGURATION (SHUTDOWN SUCCESSFUL):

a. Remaining PACK . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . HIGH FLOW(CABIN = LEFT PACK, FLIGHT DECK = RIGHT PACK)

Procedure Completed

L Pack FaultOr

R Pack Fault

# Pack Fault

L Pack Temp / Press HiOr

R Pack Temp / Press Hi




A4-11 P/N 401-590001-0078

A4.9 CABIN AIR INFLOW LOW

1. L and R BLEEDS. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CYCLE OFF, THEN AUTO2. L and R PACKS. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CYCLE OFF, THEN AUTO


a. FLIGHT DECK and CABIN HIGH FLOW . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . HIGHb. Thrust Levers . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . INCREASE AS CONDITIONS PERMITc. Cabin Altitude . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . MONITORd. Airplane Altitude (if cabin altitude is not controlled) . . DESCEND, NOT LOWER THAN MINIMUM SAFE ALTITUDE

Procedure Completed

IF AMBER “Cabin Air Inflow Low” CAS MSG IS CLEARED:

Procedure Completed

A4.10 PACK AUTO SHUTDOWN

NOTE CAS MSG will post when Wing Anti-Ice is selected ON with a single bleed

source. The following procedure is not applicable for this condition.

1. PACK (affected side) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CYCLE OFF, THEN AUTO


a. PACK (affected side) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFFb. Remaining PACK . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . HIGH FLOW


Procedure Completed

IF AMBER “# Pack Auto Shutdown” CAS MSG IS CLEARED:

Procedure Completed

A4.11 BAGGAGE ALTITUDE HIGH 1. SEAT BELT / NO SMOKING. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON2. Cabin Altitude . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . MONITOR3. Interior Baggage Door . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . KEEP CLOSED4. Land. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . AS SOON AS PRACTICAL

Procedure Completed

Cabin Air Inflow Low

Cabin Air Inflow Low

L Pack Auto ShutdownOr

R Pack Auto Shutdown

L Pack Auto Shutdown

# Pack Auto Shutdown

Baggage Altitude High




A5-1 P/N 401-590001-0078



ELECTRICAL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A5-3 FIGURE 1 (SHEET 1 OF 4) - ELECTRICAL POWER DISTRIBUTION CHARTS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A5-3 FIGURE 1 (SHEET 2 OF 4) - ELECTRICAL POWER DISTRIBUTION CHARTS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A5-4 FIGURE 1 (SHEET 3 OF 4) - ELECTRICAL POWER DISTRIBUTION CHARTS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A5-5 FIGURE 1 (SHEET 4 OF 4) - ELECTRICAL POWER DISTRIBUTION CHARTS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A5-6

A5.1 AC 1 BUS FAIL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A5-7A5.2 AC 2 BUS FAIL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A5-7A5.3 DUAL AC BUS FAIL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A5-8A5.4 APU GENERATOR OVERLOAD . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A5-11A5.5 BATTERY BUS FAULT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A5-12A5.6 BATTERY CHARGE RATE HIGH . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A5-12A5.7 DC 1 BUS FAIL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A5-13A5.8 DC 2 BUS FAIL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A5-15A5.9 DUAL DC BUS FAIL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A5-16A5.10 ELECTRICAL CONTROL 1 FAIL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A5-19A5.11 ELECTRICAL CONTROL 2 FAIL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A5-21A5.12 SINGLE GENERATOR FAIL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A5-22A5.13 DUAL GENERATOR FAIL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A5-23A5.14 GENERATOR OIL PRESSURE LOW . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A5-27A5.15 GENERATOR OVERHEAT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A5-27A5.16 GENERATOR OVERLOAD . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A5-27A5.17 SPDA 1 FAIL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A5-28A5.18 SPDA 2 FAIL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A5-31A5.19 TRU OVERHEAT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A5-34A5.20 TRU OVERLOAD . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A5-35A5.21 EMER LIGHTS DISARMED . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A5-35A5.22 CB TRIP . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A5-36




A5-2




A5-3 P/N 401-590001-0078

ELECTRICAL

FIGURE 1 (SHEET 1 OF 4)ELECTRICAL POWER DISTRIBUTION CHARTS

RC03D100628AA.AI

ANNUN LTS2 X

PTU SOV

APU FIRE EXT XR BLEED SOV1 X

APU/EXT PWR2R BLEED SOV2 XR BLEED VLV1 X

AURAL WARN 1 X R ECS CTRL XAV RACK FAN2 X R ENG AI VLV X

BLD ISOL VLVBAY FAN CTL

XX R ENG STRT X

BRAKE ACCUM XR FADEC A1 X

CBP 2 ESS2-1R FADEC A2 X

CBP 2 ESS2-2R FADEC B X

DCMP CONTROL* XR FIRE EXTGR X

EICAS XR FUEL LP SOV X

EMR GEN CTL2 XR FUEL HMU SOV X

EMR LT CTL2 XR HYD BP VLV X

ESS 2 XTIE X

XX

X

X

R HYD SOV X

FDR XR IGNITION A X

FLAP ECU XR IGNITION B X

GEN CTL2 ES2R OIL PRESS X

IRU 1B** XRIGHT AUDIO X

LDG GEAR 1 XROLL DISC X

MAU 2A XRUDDER CTRL2 X

NO SMOKE SGN XRWING AI VLV X

OUTBD BRAKESPDA2 ESS2-1

X

X

SPDA2 ESS2-2OXY DPLY VLV X XSPLR CTL 2

STAB TRIM X

XX

AP SERVO IO1 XANNUN LTS 1AIR DATA 1

XL FIRE EXTGR X

APU CONTROL X

L FUEL LP SOV X

APU DOOR CTL X

X

L FUEL HMU SOV X

APU/EXT PWR1 X

L HYD BP VLV X

AV RACK FAN1 X

L HYD SOV X

CBP 1 ESS1-1 X

L IGNITION A X

CBP 1 ESS1-2 X

L IGNITION B X

COM 1 X

L OIL PRESS X

CVR X

LEFT AUDIO XX

EMER LT CTL1 X

LEFT MCDU

EMER WS CTRL X

LWING AI VLV X

ERS CTL A X

MAU 1A X

ERS CTL B X

NAV 1 X

ESS BUS XTIE X

OUTFLOW CH 1 X

ESS XTIE CTL X

PITCH DISC X

FLT DECK LT1 X

RADIO 1 I/O X

FUEL XFD CL X

RUDDER CTRL1 X

FUEL XFD OP X

RUDDER TRIM X

GEN CTL1 ES1 X

SBY STAB TRM X

IRU 2B** X

SEAT BELT LT X

L AOA HT CTL XSPDA1 ESS1-1SMOKE DETECT

X

L BLEED SOV1 XSPDA1 ESS1-2 X

L BLEED SOV2 XL BLEED VLV1 X

SPDA1 ESS1-3 X

L CURSOR CTL X

SPLR CTRL 1 X

X

L ECS CTRL X

START PUMP* X

L ENG AI VLV X

STBY BUS X

L ENG START XL FADEC A1 XL FADEC A2 X STBY P/S CTL X

STBY P/S HT XTRANSPONDR 1 X

L FADEC B X

STBY COMPASS X

EMR GEN CTL1 XSTBY AIRDATA X

STBY INST X

Footnotes:

**IRU = IRS*START PUMP = DC FUEL PUMP

Footnotes:

**IRU = IRS*DCMP = AUX PUMP





RC03D100629AA.AI

ADF 1 X

L STICK SHKR X

AILRON SERVO XANTI-COL LT X

ECS XOVR CLS XECS XOVR OPN X

CABIN LIGHT2 XCABIN LIGHT5 XCABIN LIGHT7 XCBN SNSR FAN XCBP 3 DC1-1 XCBP 3 DC1-2 XCMS SYSTEM XCMS SEAT/LAV SWITCH XDME 1 X

X

GPWS

ELEV SERVO XEMER GEN RST XFLAP CONTROL XFLT DECK LT3 XFLT DECK LT5 XFLT DECK LT7 X

XGEN CTL2 DC1 X

L RFUEL VLV2 X

HF COM 1XHF COM 1 ANT

X

HMDG MAINT* XICE DET 1 XINBD BRAKE XINTERIOR 1 XINTERIOR 2 XINTERIOR 5 XIRU 1A*** X

L GUID CTLR XX

L LANDING LT

L BAY FAN

XL MCDU RFUEL XL PACK VALVE XL PFD CTLRL P0T0 HEAT1

XX

L PYL V VALV XL RFUEL VLV1 X

Footnotes:

DOOR IND****

***IRU = IRS**MAU 2C = MAU 2B*HMDG = EMER GEN

**** = IF INSTALLED

R P0T0 HEAT2

L T/R BALK XL T/R ISO XL T/R VALVES XL TAXI LT X

LDG GEAR 2 XLEFT PFD XMAU 1B X

PHONE XCVR XMID RACK FAN XMAU 2C** X

PITOT HT1 CT XX

R RFUEL VLV1 XR RFUEL VLV2 XR T/R ISO XRADIO ALT XRECOG PULSE XREFUEL CTL 1 XREFUEL CTL 2 XREFUEL CTL 3 XREFUEL CTRL XREFUEL PANEL XRIGHT MFD XSEC STAT HT2 XSELCAL XSPARE DC1-1 XSPDA1 DC1-4 XSPDA1 DC1-5 XSPDA1 DC1-6 XSPDA1 DC1-7 XSPDA1 DC1-8 XSPDA1 DC1-9 XSPDA1 DC1-10 XTAIL ICE CTL XTAT HEAT CTL XTBL/RD LTS FWD XTCAS XVIBR/L MAINT XWINDOW SHADES XWX RADAR XX-TIE 1 FUSE X

L UFI PWR**** X




A5-5 P/N 401-590001-0078


RC03D100630AA.AI

AC POWER CONTROL XAFT DNWASH LTS X

NW STEERING X

AFT UPWASH LTS XAILERON TRIM XAIR DATA 2 XAIRSHOW NETWORK XAP SERVO IO2 XAURAL WARN 2 XAUTOTHROTTLE XCABIN LIGHT1 XCABIN LIGHT3 XCABIN LIGHT4 XCABIN LIGHT6 XCBP 4 DC2-1 XCBP 4 DC2-2 XCKT SNSR FAN XCMS CNTRLS XCOM 2 XDATA MGMT UN XDME 2 X

XFLT DECK LT2FLT DECK LT4 XFLT DECK LT6 XFWD DNWASH LTS XFWD UPWASH LTS XGEN CTL1 DC2

ICE DET 2 XX

XX

INTERIOR 3 X

INTERIOR 6 XINTERIOR 4 X

IRU 2A**L P0T0 HEAT2

XX

L T/R SOV XLEFT MFD XMAU 1C* XMAU 2B XNAV 2 X

OUTFLOW CH 2 XPITOT HT2 CT XPRI STAT HT2 XPTU VALVE X

R BAY FAN XR AOA HT CTL X

R CURSOR CTL XR ENG MAINT XR GUID CTLR XR LANDING LT XR PACK VALVE XR PFD CTLR X

XR PYL V VALV XR STICK SHKR XR T/R BALK XR T/R SOV XR T/R VALVES XR TAXI LT X

RADIO 2 I/O XRIGHT MCDU X

R UFI PWR*** X

RIGHT PFD XSPARE DC2-2 XSPDA2 DC2-3 XSPDA2 DC2-4 XSPDA2 DC2-5 XSPDA2 DC2-6 XSPDA2 DC2-7 XSPDA2 DC2-8 XSPDA2 DC2-9 XSPDA2 DC2-10 XTOILET XTRANSPONDR 2 XWATER PUMP XWATER LVL SNSR &

WTR FLTR X

XXFER PUMP X

R P0T0 HEAT1

X-TIE 2 FUSE

Footnotes:

**IRU = IRS*MAU 1C = MAU 1B

HF COM 2HF COM 2 ANT

*** = IF INSTALLED





RC03D100631AA.AI

EMER WS FEED XEMER WS HEAT XHMDG CTL 1*

Footnote:*HMDG = EMER GEN

XICE DETECT 1 XPITOT 1 HEAT XSEC STAT HT1 XTAT HEAT X

AC 1B BUS XAC CMP BUS 1 XAPU GEN SENS X

HMDG HEAT* X

TRU 1 AC XPITCH TRIM X

L BOOST PUMP X

HYD PUMP TRU**

Footnotes:*HMDG = EMER GEN**HYD PUMP TRU = TRU3

XL AOA CS HT XL AOA HEAT X

WING INSP LT X

MICROWAVE OVEN X

COFFEE MAKER XCONVEC WARM OVEN X

WATER HEATER FWDXWATER HEATER AFTX

AC 2B BUS XAC CMP BUS 2 XAC EXT SENSE XCABIN AFT LH XCABIN AFT RH XCABIN FWD LH XCABIN FWD RH XCOCKPIT XDRAIN HEAT XFLAP MOTOR XGALLEY CLOSET XLAV X

LOGO LIGHT X

R BOOST PUMP XR AOA CS HT X

STROBE LIGHT XTAIL DE-ICE XTRU 2 AC XWNG RECON LT X

HMDG CTL 2*

Footnotes:*HMDG = EMER GEN

Footnote:*PANEL LOCATED IN NOSE OF AIRPLANE

XICE DETECT 2 XPITOT 2 HEAT XPRI STAT HT1 XR AOA HEAT XSPARE AC2B-1 XESS1 BUS

XBMS1 (RELAY) POWERX

HOT BATT 1 BUS X

XCBP 4 HB2 XCMC XELT XREFUEL DEPWR XREFUEL PWR X

AFT COMPT LT XXBATT MASTER1

BATT MASTER2

ENTR DR CTRL XENTRY DOOR PWR*FWD COMPT LT X

AFT NAV LT XAPU DOOR XAUDIO AMP XAUX PMP FUSE XERS FUSE XEXT FIRE BEL XL NAV LIGHT XR NAV LIGHT XRUDDER ECU X




A5-7 P/N 401-590001-0078

A5.1 AC 1 BUS FAIL 1. Flight Control and Thrust . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . FLY MANUALLY2. STABILIZER TRIM SELECT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . STBY3. Significant Items Lost. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . REVIEW

NOTEApply appropriate RVSM contingency procedures.

4. Airspeed. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . BELOW 0.78M / 300 KIAS5. Left PFD AIR DATA. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . REVERT TO ADC 26. Icing Conditions . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . EXIT / AVOID7. PUSHER FAIL (A9.7) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . REVIEW, AS REQUIRED8. APU START / STOP (if available and if 34,000 FT or below) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON AS DESIRED9. APU GEN. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .CONFIRM AUTO

10. Land. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . AS SOON AS PRACTICAL

Procedure Completed

A5.2 AC 2 BUS FAIL

1. Flight Control and Thrust . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . FLY MANUALLY2. Significant Items Lost. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . REVIEW


3. Right PFD AIR DATA. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . REVERT TO ADC 14. Icing Conditions . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . EXIT / AVOID5. PUSHER FAIL (A9.7) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . REVIEW, AS REQUIRED

Significant Items Lost_ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _AC 1 BUS Fail

Flight Controls Primary Pitch Trim, Mach Trim, Left Shaker, Pusher

Engine Autothrottle

Fuel Left Boost Pump

Avionics AP, CMF (Optional)

Electrical AC 1 Bus

Anti-ice Equipment Left Pitot Heat, TAT Probe Heat, Left AOA Heat, Left Windshield Heat, Emergency Windshield Heat

Lights Recog lights, Ice Detect lights

Cabin and Doors Cabin lighting (Emergency lighting will operate), Partial Cabin Equipment

Significant Items Lost_ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _AC 2 BUS Fail

Flight Controls Flaps, Right Shaker, Pusher

Fuel Right Boost Pump

Avionics AP

Electrical AC 2 Bus

Anti-ice Equipment Tail De-ice, Right Pitot Heat, Right AOA Heat, Right Windshield Heat

Lights Recog lights, Strobe lights

Cabin and Doors Partial Cabin Equipment

AC 1 Bus Fail

AC 2 Bus Fail




6. APU START / STOP (if available and if 34,000 FT or below) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON AS DESIRED7. APU GEN. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CONFIRM AUTO8. Land . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .AS SOON AS PRACTICAL

IF FLAP POSITION IS LESS THAN 35° AT TIME OF FAILURE:

a. REDUCED FLAP APPROACH AND LANDING (A1.1) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . PERFORM

Procedure Completed

IF FLAP POSITION WAS 35° AT TIME OF FAILURE:

a. Normal Landing . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . PERFORM

Procedure Completed

A5.3 DUAL AC BUS FAIL Complete checklists are included for DESCENT through AFTER LANDING AND SHUT DOWN.

Emergency Generator will engage and provide power to DC ESS 1 / 2.1. Flight Control and Thrust . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . FLY MANUALLY BY USING STBY INST2. Dutch Roll. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . SUPPRESS WITH LATERAL CONTROL INPUT, AS REQUIRED3. STABILIZER TRIM SELECT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .STBY4. Emergency Generator . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CONFIRM OPERATING5. Radio / Transponder . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . USE COM 1 AND TRANSPONDER 1 / 77006. Significant Items Lost . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . REVIEW

NOTE• A false CAS MSG may post.


Significant Items Lost_ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _AC 1-2 BUS Fail

Flight Controls Primary Pitch Trim, Mach Trim, Aileron Trim, Flaps, YD, Left and Right Shaker, Pusher

Engine Autothrottle, Left and Right Thrust Reverser, APU Start

FOPS Some Fire Annunciations, Smoke Detection and Bleed Leak Detection

Fuel Left and Total Fuel Quantity Indication, Fuel Transfer, Left and Right Boost Pump, Fuel Used Indication on EICAS

Radios Transponder 2, VHF 2, HF 1, HF 2, SELCAL

Avionics AP, Display Unit 1, 2, 4 and 5, FMS 1 and 2, TAWS, TCAS, ADF 1, NAV 2, DME 1 and 2, Rad Alt, GPS 1, Electronic Charts, CMF (Optional), Copilot’s: MCDU, CCD

Electrical AC 1-2 Bus, DC 1-2 Bus

Hydraulics PTU

Gear and Brakes Nosewheel Steering, Inboard Brakes

ECS Cabin and Cockpit Temp Control, Left and Right HP Bleed Valve Failed Closed, Left and Right Packs Failed On, ΔP Indication

Anti-ice Equipment Tail De-ice, Left and Right Pitot Heat, TAT Heat, Static Port Heat, AOA Heat,Left and Right Windshield Heat, Ice Detector 1-2

Lights Left and Right Landing lights, Left and Right Taxi lights, Recog lights, Beacon lights, Strobe lights, NAV lights, Ice Detect lights, Partial Cockpit lighting

Cabin and Doors Cabin PA, Cabin lighting (Emergency lighting will operate), Partial Cabin Equipment

AC 1-2 Bus Fail

Exterior Door Open




A5-9 P/N 401-590001-0078

7. Airspeed. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . BELOW 0.78M / 300 KIAS8. Altitude. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 35,000 FT OR BELOW

NOTEAutomatic Pressurization is operational, but FMS LDG ELEV data is lost.

9. MCDU / MENU / CABIN PRES . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ENTER MANUAL LDG ELEV10. Icing Conditions . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . EXIT / AVOID11. Autopilot Disconnect Tone. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . DISABLE, IF DESIRED

a. CBP 2, AVIONICS, AURAL WARN 1 CB . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . PULLb. MCDU / CB / ELEC MENU / CB BY SYSTEM / AVIONICS . . . . . . . . . . . . . . . . . . . . . . . . . . . AURAL WARN 2, OUT

12. NAVIGATION:a. GPS navigation is available on the left MCDU MENU / GPS NAV page.b. ILS and BC navigation are available on the standby instrument using the NAV button.

13. L-R SHAKER FAIL (A9.8). . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . REVIEW, AS REQUIRED

NOTE• Right Fuel Quantity Indication is available but degraded.

• Left and Right Fuel Quantity Low indications will be functional.

• Fuel quantity is degraded on affected side and CAS MSG will post. Subtract 700LB (318 KG) of fuel quantity reading per degraded tank for endurance and add 700 LB (318 KG) of fuelquantity per degraded tank for weight calculations.

14. Fuel . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . USE RIGHT FUEL QUANTITY INFORMATION X 215. Land. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . NEAREST SUITABLE AIRPORT16. Landing Considerations:

a. Select wide runway with minimum crosswind, no tailwind.

b. Normal Gear Operation is available even though CAS MSG may be posted.c. Nosewheel Steering will be inoperative even though the Amber “Nosewheel Steer Fail” CAS MSG does not post. Use

rudder for directional control. Add differential braking if required when rudder becomes ineffective.

d. Ground Spoilers will be operative, even though the CAS MSG is posted.

e. Flaps are inoperative.f. Thrust Reversers are inoperative.

g. Outboard Brakes and Emergency Brakes are operative.h. Landing, Taxi, Strobe and Beacon lights are inoperative.i. AURAL WARN CBs . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .RESET, AS DESIRED

17. Landing Airspeed, Landing Distance and Brake Energy . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .SEE TABLE



NOTEWith one pair of brakes inoperative, all the brake energy applied using the toe brakes will go into theoperational pair of brakes. The EMERGENCY / PARKING BRAKE applies pressure directly to all fourbrakes. If the landing is to be made at a heavy weight or on a limited length runway, consider addingEMERGENCY / PARKING BRAKE to distribute brake energy more evenly.

Fuel Qty Degrade

Gear System Fail

Spoiler Fail




DESCENT1. Seat, Seat Belts, Rudder Pedal . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ADJUST / SET

NOTESPEEDBRAKE will be available inflight with reduced deflection, even though the CASMSG is posted.

APPROACH1. Altimeter (Stby Inst) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . SET2. IFR Approach . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . STBY INST ILS OR BC (NAV 1)3. VSPEEDS and Landing Distance . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . COMPUTED4. Approach and Landing Briefing . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . COMPLETED5. Cabin . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . SECURE

BEFORE LANDING1. LANDING GEAR Handle . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . DOWN / THREE GREEN2. GROUND SPOILER. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CONFIRM ARM3. SPEEDBRAKE. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CONFIRM RETRACTED4. FLAPS Position . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CONFIRM

LANDING1. Airspeed. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . LANDING2. Thrust Levers . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . IDLE3. Brakes (after touchdown) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .APPLY4. SPEEDBRAKE. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . EXTEND5. Stop straight ahead on the runway using rudder control and differential braking for directional control.

AFTER LANDING AND SHUT DOWNShut down on runway as follows:

NOTEDifferential braking with only one pair of brakes operational is not adequate for taxi maneuvering.

1. SPEEDBRAKE. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . RETRACT2. EMERGENCY / PARKING BRAKE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . SET3. GUST LOCK . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .ENGAGE4. L and R WINDSHIELD HEAT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF5. EMERGENCY LIGHTS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . PULL TURN / OFF6. LEFT and RIGHT FUEL / IGN . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF7. OXYGEN . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .PULL / OFF8. EXTERNAL LIGHTS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF9. BATTERY 1 and 2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .OFF

Procedure Completed

Flap Position 0° 12° 20° 35°Landing Speed (KIAS) VREF + 25 VREF + 15 VREF + 10 VREF + 10

Landing Distance Multiply by 2.4 Multiply by 2.0 Multiply by 2.0 Multiply by 1.7

Brake Energy Increase by 12.0 MFP Increase by 9.1 MFP Increase by 6.5 MFP Increase by 2.1 MFP

Spoiler Fail




A5-11 P/N 401-590001-0078

A5.4 APU GENERATOR OVERLOAD

NOTE• The APU generator load exceeds 100%.

• Only occurs due to restoring loads after an automatic load shed.

• Auto load shed may take up to 5 minutes.

IF AUTO LOAD SHED HAS NOT REOCCURRED:

1. Elec Synoptic . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK APU GENERATOR STATUS AND LOAD2. MCDU / CB / ELEC MENU / ELEC SYS CONTROL / LOAD RESTORE . . . . . . . . . . . . . . . . . . . USE TO SHED ITEMS

TO REDUCE LOAD BELOW 95%

Procedure Completed

IF AUTO LOAD SHED HAS REOCCURRED:

1. Flight Control and Thrust . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . FLY MANUALLY2. Elec Synoptic . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK APU GENERATOR STATUS AND LOAD3. Significant Items Lost. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . REVIEW

NOTE• Pusher is unreliable.

• A false CAS MSG may post.


• Items that have been manually restored will be automatically re-shed during descent at 25,000 FT orduring climb at 26,000 FT. Loads can be restored as desired, see Step 4).

4. MCDU / CB / ELEC MENU / ELEC SYS CONTROL / LOAD RESTORE . . . . . . . . . . . . . . . . . . . . . .USE TO RESTORESHED ITEMS (IF REQUIRED)DO NOT EXCEED 95% LOAD

5. Icing Conditions . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . EXIT / AVOID6. PUSHER FAIL (A9.7) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . REVIEW, AS REQUIRED7. Land. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . AS SOON AS PRACTICAL

Procedure Completed

Significant Items Lost_ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _APU Generator Overload

All Altitudes Above 26,000 FTFlight Controls Mach Trim, Right Shaker

Fuel Right Boost Pump Left Boost Pump

Radios HF 2

Avionics AP, ADC 2, Weather Radar, CMF (Optional)

Anti-ice Equipment Tail De-ice, Right Pitot Heat, Right AOA Heat, Left and Right Windshield Heat

Lights Left and Right Taxi lights, Recog lights, Strobe lights Left and Right Landing lights

Cabin and Doors Cabin lighting, Partial Cabin Equipment Additional Cabin lighting

APU Gen Overload

Exterior Door Open




A5.5 BATTERY BUS FAULT

1. Battery (affected bus). . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF

NOTE• With CAS MSG posted, the APU start is inoperative. The

CAS MSG may post and the right windshield heat will be lost. The NAV Lights and Audio for PA may beinoperative.

• With CAS MSG posted, the left windshield heat will be lost, except for theemergency windshield heat section.

Procedure Completed

A5.6 BATTERY CHARGE RATE HIGH

NOTEBattery charge rate is above 25 Amps.

IN FLIGHT 1. High Charge Battery. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . IDENTIFY

a. Elec Synoptic. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . NOTE BATTERY CHARGE CURRENTb. BATTERY (highest charge rate) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF

NOTE APU will not start if BATTERY 2 is OFF.

Procedure Completed

ON GROUND

1. Dispatch . . . . . . . . . . . . . . . . . . . . . . . . . . . . NO DISPATCH UNTIL CAS MSG IS CLEARED

IF CHARGE RATE REMAINS HIGH:

a. SECTION 4 - NORMAL PROCEDURES - SHUT DOWN. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . PERFORM

Procedure Completed

IF AMBER “Batt Charge Rate High” CAS MSG IS CLEARED:

a. Normal Dispatch.

Procedure Completed

Batt 1 Bus FaultOr

Batt 2 Bus Fault

Batt 2 Bus Fault Rudder Fault

Batt 1 Bus Fault

Batt Charge Rate High

Batt Charge Rate High




A5-13 P/N 401-590001-0078

A5.7 DC 1 BUS FAIL 1. Flight Control and Thrust . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . FLY MANUALLY2. Significant Items Lost. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . REVIEW

NOTE• Some CAS MSGs and Synoptic information may not be available.

• Some switch lights are inoperative.

NOTE• Spoilers functional, but with reduced deflection even though CAS MSG is posted.


3. Airspeed. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . BELOW 0.78M / 300 KIAS4. Left MFD . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . PFD OR MFD, AS REQUIRED5. Left FMS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . USE FMS 2, IF REQUIRED6. Icing Conditions . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . EXIT / AVOID7. PUSHER FAIL (A9.7) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . REVIEW, AS REQUIRED




8. Fuel . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . USE RIGHT FUEL QUANTITY INFORMATION X 29. Land. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . NEAREST SUITABLE AIRPORT

10. Landing Considerations:a. Select wide runway with minimum crosswind, no tailwind.

b. Normal Gear Operation is available even though CAS MSG may be posted.

c. Nosewheel Steering is inoperative, even though Amber “Nosewheel Steer Fail” CAS MSG is not posted. Use rudderfor directional control. Add differential braking if required when rudder becomes ineffective.

d. Ground Spoilers are operative.

Significant Items Lost_ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _DC 1 BUS Fail

Flight Controls Mach Trim, Flaps, Left Shaker, Pusher

Engine Autothrottle, Left and Right Thrust Reverser


Fuel Left and Total Fuel Quantity Indication

Radios HF 1, SELCAL

Avionics AP, Some FD Modes, FMS 1, Terrain Warning, TCAS, ADF 1, DME 1, Rad Alt, GPS 1, Weather Radar, Pilot’s: PFD, MCDU FMS Control, Copilot’s: MFD


ECS Left Pack Failed On

Anti-ice Equipment Tail De-ice, Left Pitot Heat, TAT Heat

Lights Left Landing light, Left Taxi light, Recog lights, Beacon lights

DC 1 Bus Fail

Spoiler Fail

Fuel Qty Degrade

Gear System Fail




e. Flaps are inoperative.f. Thrust Reversers are inoperative.

g. Outboard Brakes and Emergency Brakes are operative.h. Left Landing and Left Taxi lights are inoperative.





Procedure Completed

Flap Position 0° 12° 20° 35°Landing Speed (KIAS) VREF + 25 VREF + 15 VREF + 10 VREF






A5-15 P/N 401-590001-0078

A5.8 DC 2 BUS FAIL 1. Flight Control and Thrust . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . FLY MANUALLY2. Significant Items Lost. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . REVIEW




3. Airspeed. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . BELOW 0.78M / 300 KIAS

NOTECopilot can reselect MFD if required, but CCD is inoperative.

4. Right MFD . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . PFD OR MFD, AS REQUIRED5. Right PFD AIR DATA. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . REVERT TO ADC 16. Right FMS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . USE FMS 1, IF REQUIRED7. Icing Conditions . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . EXIT / AVOID8. PUSHER FAIL (A9.7) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . REVIEW, AS REQUIRED9. Land. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . NEAREST SUITABLE AIRPORT

10. Landing Considerations:a. Select wide runway with minimum crosswind, no tailwind.b. Nosewheel Steering is inoperative, even though Amber “Nosewheel Steer Fail” CAS MSG is not posted. Use rudder

for directional control. Add differential braking if required when rudder becomes ineffective.c. Flaps and Ground Spoilers are operative.d. Thrust Reversers will be inoperative.e. Normal Brakes are operative.f. Right Landing and Right Taxi lights are inoperative.

11. Landing Distance . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . MULTIPLY BY 1.2

Procedure Completed

Significant Items Lost_ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _DC 2 BUS Fail

Flight Controls Mach Trim, Aileron Trim, Right Shaker, Pusher



Fuel Fuel Transfer

Radios Transponder 2, VHF 2, HF 2

Avionics AP, FD, FMS 2, ADC 2, DME 2, NAV 2, Ground Proximity, Pilot’s: MFD, Copilot’s: PFD, MCDU, CCD

Gear and Brakes Nosewheel Steering

ECS Right Pack Failed On

Anti-ice Equipment Right Pitot Heat, Right AOA Heat

Lights Right Landing light, Right Taxi light

DC 2 Bus Fail




A5.9 DUAL DC BUS FAIL Complete checklists are included for DESCENT through AFTER LANDING AND SHUT DOWN.

Emergency Generator will engage and provide power to DC ESS 1 / 2.

1. Flight Control and Thrust . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . FLY MANUALLY BY USING STBY INST2. Dutch Roll. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . SUPPRESS WITH LATERAL CONTROL INPUT, AS REQUIRED3. STABILIZER TRIM SELECT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .STBY4. Emergency Generator . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CONFIRM OPERATING5. Radio / Transponder . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . USE COM 1 AND TRANSPONDER 1 / 77006. Significant Items Lost . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . REVIEW



7. Airspeed. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . BELOW 0.78M / 300 KIAS8. Altitude . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 35,000 FT OR BELOW


9. MCDU / MENU / CABIN PRES . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ENTER MANUAL LDG ELEV10. Icing Conditions . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . EXIT / AVOID11. Autopilot Disconnect Tone . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .DISABLE, IF DESIRED

a. CBP 2, AVIONICS, AURAL WARN 1 CB . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . PULLb. MCDU / CB / ELEC MENU / CB BY SYSTEM / AVIONICS . . . . . . . . . . . . . . . . . . . . . . . . . . . AURAL WARN 2, OUT

12. NAVIGATION:a. GPS navigation is available on the left MCDU MENU / GPS NAV page.b. ILS and BC navigation are available on the standby instrument using the NAV button.

Significant Items Lost_ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _DC 1-2 BUS Fail

Flight Controls Mach Trim, Aileron Trim, Flaps, YD, Left and Right Shaker, Pusher



Fuel Left and Total Fuel Quantity Indication, Fuel Transfer, Fuel Used Indication on EICAS and FMS


Avionics AP, FD, Display Unit 1, 2, 4 and 5, FMS 1 and 2, Terrain Warning, TCAS, ADF 1, DME 1 and 2, NAV 2, Rad Alt, GPS 1, Weather Radar, Electronic Charts, Copilot’s: MCDU, CCD

Electrical DC 1-2 Bus

Hydraulics PTU


ECS Left and Right Packs Failed On, ΔP Indication

Anti-ice Equipment Tail De-ice, Left and Right Pitot Heat, TAT Heat, Static Port Heat, Right AOA Heat, Ice Detector 1-2

Lights Left and Right Landing lights, Left and Right Taxi lights, Recog lights, Beacon lights,NAV lights, Partial Cockpit lighting


DC 1-2 Bus Fail

Exterior Door Open




A5-17 P/N 401-590001-0078

13. L-R SHAKER FAIL (A9.8). . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . REVIEW, AS REQUIRED




14. Fuel . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . USE RIGHT FUEL QUANTITY INFORMATION X 215. Land. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . NEAREST SUITABLE AIRPORT16. Landing Considerations:


b. Normal Gear Operation is available even though CAS MSG may be posted.c. Nosewheel Steering will be inoperative even though the Amber “Nosewheel Steer Fail” CAS MSG does not post. Use

rudder for directional control. Add differential braking if required when rudder becomes ineffective.

d. Ground Spoilers will be operative, even though the CAS MSG is posted.e. Flaps are inoperative.f. Thrust Reversers are inoperative.

g. Outboard Brakes and Emergency Brakes are operative.h. Landing, Taxi, Strobe and Beacon lights are inoperative.i. AURAL WARN CBs . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .RESET, AS DESIRED

17. Landing airspeed, landing distance and brake energy . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .SEE TABLE




DESCENT1. Seat, Seat Belts, Rudder Pedal . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .ADJUST / SET





Fuel Qty Degrade

Gear System Fail

Spoiler Fail

Spoiler Fail




APPROACH1. Altimeter (Stby Inst) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . SET2. IFR Approach . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . STBY INST ILS OR BC (NAV 1)3. VSPEEDS and Landing Distance . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . COMPUTED4. Approach and Landing Briefing . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . COMPLETED5. Cabin . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . SECURE

BEFORE LANDING1. LANDING GEAR Handle . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . DOWN / THREE GREEN2. GROUND SPOILER. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CONFIRM ARM3. SPEEDBRAKE. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CONFIRM RETRACTED4. FLAPS Position . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CONFIRM

LANDING1. Airspeed. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . LANDING2. Thrust Levers . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . IDLE3. Brakes (after touchdown) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .APPLY4. SPEEDBRAKE. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . EXTEND5. Stop straight ahead on the runway using rudder control and differential braking for directional control.



1. SPEEDBRAKE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . RETRACT2. EMERGENCY / PARKING BRAKE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . SET3. GUST LOCK . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .ENGAGE4. L and R WINDSHIELD HEAT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF5. EMERGENCY LIGHTS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . PULL TURN / OFF

NOTEEmergency Generator will drop off line when engine driven hydraulic pump pressure is lost and batterypower only will be available. In this condition, the VHF 1 radio frequency cannot be changed and radiotransmissions can only be received by selecting EMER operation on the audio panel.

6. LEFT and RIGHT FUEL / IGN . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF7. OXYGEN . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .PULL / OFF8. EXTERNAL LIGHTS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF9. BATTERY 1 and 2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .OFF

Procedure Completed




A5-19 P/N 401-590001-0078

A5.10 ELECTRICAL CONTROL 1 FAIL 1. Flight Control and Thrust . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . FLY MANUALLY2. STABILIZER TRIM SELECT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . STBY3. Significant Items Lost. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . REVIEW



NOTE• Spoilers functional, but with reduced deflection, even though CAS MSG is posted.


4. Airspeed. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . BELOW 0.78M / 300 KIAS5. Left MFD . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . PFD OR MFD, AS REQUIRED6. Left FMS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . USE FMS 2 (IF REQUIRED)7. Icing Conditions . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . EXIT / AVOID8. PUSHER FAIL (A9.7) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . REVIEW, AS REQUIRED9. APU START / STOP (if available and if 34,000 FT or below) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON AS DESIRED

10. APU GEN. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .CONFIRM AUTO




11. Fuel . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . USE RIGHT FUEL QUANTITY INFORMATION X 212. Land. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . NEAREST SUITABLE AIRPORT

Significant Items Lost_ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _Elect Ctrl 1 Fail

Flight Controls Primary Pitch Trim, Mach Trim, Flaps, Left Shaker, Pusher


FOPS Some Fire Annunciations, Smoke Detections and Bleed Leak Detection

Fuel Left and Total Fuel Quantity Indication, Left Boost Pump

Radios HF 1, SELCAL

Avionics AP, Some FD Modes, FMS 1, Terrain Warning, TCAS, ADF 1, DME 1, Rad Alt, GPS 1, Weather Radar, CMF (Optional), Pilot's: PFD, MCDU FMS Control, Copilot's: MFD

Electrical AC 1 Bus, DC 1 Bus


ECS Left Pack Failed On

Anti-ice Equipment Tail De-ice, Left Pitot Heat, TAT Heat, Left AOA Heat, Left Windshield Heat, Emergency Windshield Heat

Lights Left Landing light, Left Taxi light, Recog lights, Beacon lights, Ice Detect lights

Cabin and Doors Cabin lighting (Emergency lighting will operate), Partial Cabin Equipment

Elect Ctrl 1 Fail

Spoiler Fail

Fuel Qty Degrade




13. Landing Considerations:a. Select wide runway with minimum crosswind, no tailwind.

b. Normal Gear Operation is available even though CAS MSG may be posted.

c. Nosewheel Steering will be inoperative even though the Amber “Nosewheel Steer Fail” CAS MSG does not post. Userudder for directional control. Add differential braking if required when rudder becomes ineffective.

d. Ground Spoilers are operative.e. Flaps are inoperative.f. Thrust Reversers are inoperative.

g. Outboard Brakes and Emergency Brakes are operative.h. Left Landing and Left Taxi lights are inoperative.





Procedure Completed




Gear System Fail




A5-21 P/N 401-590001-0078

A5.11 ELECTRICAL CONTROL 2 FAIL 1. Flight Control and Thrust . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . FLY MANUALLY2. Significant Items Lost. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . REVIEW





NOTECopilot can select MFD if required, but CCD is inoperative.

4. Right MFD . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . PFD OR MFD, AS REQUIRED5. Right PFD AIR DATA. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . REVERT TO ADC 1, IF REQUIRED6. Right FMS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . USE FMS 1, IF REQUIRED7. Icing Conditions . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . EXIT / AVOID8. PUSHER FAIL (A9.7) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . REVIEW, AS REQUIRED9. APU START / STOP (if available and if 34,000 FT or below) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON AS DESIRED

10. APU GEN. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .CONFIRM AUTO11. Land. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . NEAREST SUITABLE AIRPORT12. Landing Considerations:

a. Select wide runway with minimum crosswind, no tailwind.b. Nosewheel Steering will be inoperative even though the Amber “Nosewheel Steer Fail” CAS MSG does not post. Use

rudder for directional control. Add differential braking if required when rudder becomes ineffective.c. Ground Spoilers are operative.d. Flaps are inoperative.e. Thrust Reversers are inoperative.f. Normal Brakes are operative.

g. Right Landing and Right Taxi lights are inoperative.

Significant Items Lost_ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _Elect Ctrl 2 Fail

Flight Controls Mach Trim, Aileron Trim, Flaps, Right Shaker, Pusher


FOPS Some Fire Annunciations, Smoke Detections and Bleed Leak Detection

Fuel Fuel Transfer, Right Boost Pump

Radios Transponder 2, VHF 2, HF 2

Avionics AP, FD, FMS 2, ADC 2, DME 2, NAV 2, Ground Proximity, Pilot's: MFD, Copilot's: PFD, MCDU, CCD

Electrical AC 2 Bus, DC 2 Bus


ECS Right HP Bleed Valve Failed Closed, Right Pack Failed On

Anti-ice Equipment Tail De-ice, Right Pitot Heat, Right AOA Heat, Right Windshield Heat

Lights Right Landing light, Right Taxi light, Recog lights, Strobe lights

Cabin and Doors Partial Cabin Equipment

Elect Ctrl 2 Fail







Procedure Completed

A5.12 SINGLE GENERATOR FAIL

1. Generator (affected side) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF, THEN AUTO

IF GENERATOR OPERATION IS NOT RESTORED:

a. Elec Synoptic. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .MONITOR GENERATOR LOAD

NOTE• If both generators fail and the APU is not running, the APU cannot be started. APU start is locked out

unless at least one Engine Generator is operating.

• At least one Engine Generator or the APU Generator must be operating for the electronic chartsfunction to operate.

IF APU OPERATION IS DESIRED:

1) Altitude . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 34,000 FT OR BELOW2) APU START / STOP. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .ON3) APU GEN . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CONFIRM AUTO

Procedure Completed

IF APU OPERATION IS NOT DESIRED:

1) Land . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .AS SOON AS PRACTICAL

Procedure Completed

IF GENERATOR OPERATION IS RESTORED:

Procedure Completed




L Generator FailOr

R Generator Fail




A5-23 P/N 401-590001-0078

A5.13 DUAL GENERATOR FAIL Complete checklists are included for DESCENT through AFTER LANDING AND SHUT DOWN.

1. Flight Control and Thrust . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . FLY MANUALLY2. Dutch Roll . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .SUPPRESS WITH LATERAL CONTROL INPUT, AS REQUIRED3. STABILIZER TRIM SELECT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . STBY, AS REQUIRED

NOTEThe APU cannot be started with both engine generators inoperative.

4. Each Generator in Turn . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .OFF, THEN AUTO

IF AT LEAST ONE GENERATOR RUNS:

a. SINGLE GENERATOR FAIL (A5.12). . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .PERFORM

Procedure Completed

IF CAS MSG IS STILL POSTED (OR SINGLE GENERATOR AND OPPOSITE ENGINEFAILED):

a. Land . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . NEAREST SUITABLE AIRPORT

IF APU RUNNING:

1) APU GEN. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .CONFIRM AUTO

NOTEItems that have been manually restored will be automatically re-shed during descent at 25,000 FT orduring climb at 26,000 FT. Loads can be restored as desired, see Step 4).

2) Elec Synoptic . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK APU GENERATOR STATUS AND LOAD3) Significant Items Lost . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . REVIEW

Significant Items Lost_ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _APU Running

All Altitudes Above 26,000 FTFlight Controls Mach Trim, Right Shaker

Fuel Right Boost Pump Left Boost Pump

Radios HF 2

Avionics AP, ADC 2, Weather Radar, CMF (Optional)

Anti-ice Equipment Tail De-ice, Right Pitot Heat, Right AOA Heat, Left and Right Windshield Heat

Lights Left and Right Taxi lights, Recog lights, Strobe lights Left and Right Landing lights

Cabin and Doors Cabin lighting, Partial Cabin Equipment Additional Cabin lighting

L-R Generator Fail

L-R Generator Fail




NOTE• Pusher is unreliable.

• A false CAS MSG may post.


• Items that have been manually restored will be automatically re-shed during descent at 25,000 FT orduring climb at 26,000 FT. Loads can be restored as desired, see Step 4).

4) MCDU / CB / ELEC MENU / ELEC SYS CONTROL / LOAD RESTORE . . . . . . . . . . . . . . . . USE TO RESTORESHED ITEMS (IF REQUIRED)DO NOT EXCEED 95% LOAD

5) Icing Conditions . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . EXIT / AVOID6) PUSHER FAIL (A9.7). . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . REVIEW, AS REQUIRED7) Land . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .AS SOON AS PRACTICAL

Procedure Completed

IF APU NOT RUNNING:

1) Emergency Generator . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CONFIRM OPERATING2) Radio / Transponder. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . USE COM 1 AND TRANSPONDER 1 / 77003) Significant Items Lost . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . REVIEW



4) Airspeed . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . BELOW 0.78M / 300 KIAS5) Altitude . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 35,000 FT OR BELOW

Significant Items Lost_ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _APU Not Running

Flight Controls Primary Pitch Trim, Mach Trim, Aileron Trim, Flaps, YD, Left and Right Shaker, Pusher



Fuel Left and Total Fuel Quantity Indication, Fuel Transfer, Left and Right Boost Pump, Fuel Used Indication on EICAS


Avionics AP, Display Unit 1, 2, 4 and 5, FMS 1 and 2, TAWS, TCAS, ADF 1, NAV 2, DME 1 and 2, Rad Alt, GPS 1, Electronic Charts, CMF (Optional), Copilot’s: MCDU, CCD

Electrical AC 1-2 Bus, DC 1-2 Bus

Hydraulics PTU


ECS Cabin and Cockpit Temp Control, Left and Right HP Bleed Valve Failed Closed, Left and Right Packs Failed On, ΔP Indication

Anti-ice Equipment Tail De-ice, Left and Right Pitot Heat, TAT Heat, Static Port Heat, AOA Heat, Left and Right Windshield Heat, Ice Detector 1-2

Lights Left and Right Landing lights, Left and Right Taxi lights, Recog lights, Beacon lights, Strobe lights, NAV lights, Ice Detect lights, Partial Cockpit lighting


Exterior Door Open

Exterior Door Open




A5-25 P/N 401-590001-0078


6) MCDU / MENU / CABIN PRES . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ENTER MANUAL LDG ELEV7) Icing Conditions . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . EXIT / AVOID8) Autopilot Disconnect Tone . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . DISABLE, IF DESIRED

a) CBP 2, AVIONICS, AURAL WARN 1 CB . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . PULLb) MCDU / CB / ELEC MENU / CB BY SYSTEM / AVIONICS . . . . . . . . . . . . . . . . . . . . . . AURAL WARN 2, OUT

9) NAVIGATION:a) GPS navigation is available on the left MCDU MENU / GPS NAV page.b) ILS and BC navigation are available on the standby instrument using the NAV button.

10) L-R SHAKER FAIL (A9.8) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . REVIEW, AS REQUIRED




11) Fuel . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . USE RIGHT FUEL QUANTITY INFORMATION X 212) Land . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . NEAREST SUITABLE AIRPORT13) Landing Considerations:

a) Select wide runway with minimum crosswind, no tailwind.

b) Normal Gear Operation is available even though CAS MSG may be posted.c) Nosewheel Steering will be inoperative even though the Amber “Nosewheel Steer Fail” CAS MSG does not

post. Use rudder for directional control. Add differential braking if required when rudder becomes ineffective.

d) Ground Spoilers will be operative, even though the CAS MSG is posted.e) Flaps are inoperative.f) Thrust Reversers are inoperative.

g) Outboard Brakes and Emergency Brakes are operative.h) Landing, Taxi, Strobe and Beacon lights are inoperative.i) AURAL WARN CBs. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .RESET, AS DESIRED

14) Landing Airspeed, Landing Distance and Brake Energy . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .SEE TABLE


a) Verify corrected brake energy does not exceed 28.3 MFP.


Fuel Qty Degrade

Gear System Fail

Spoiler Fail




DESCENT1) Seat, Seat Belts, Rudder Pedal . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ADJUST / SET


APPROACH1) Altimeter (Stby Inst) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . SET2) IFR Approach . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . STBY INST ILS OR BC (NAV 1)3) VSPEEDS and Landing Distance . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . COMPUTED4) Approach and Landing Briefing . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . COMPLETED5) Cabin . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . SECURE

BEFORE LANDING1) LANDING GEAR Handle . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . DOWN / THREE GREEN2) GROUND SPOILER. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CONFIRM ARM3) SPEEDBRAKE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CONFIRM RETRACTED4) FLAPS Position . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CONFIRM

LANDING1) Airspeed . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . LANDING2) Thrust Levers . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . IDLE3) Brakes (after touchdown) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .APPLY4) SPEEDBRAKE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . EXTEND5) Stop straight ahead on the runway using rudder control and differential braking for directional control.



1) SPEEDBRAKE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . RETRACT2) EMERGENCY / PARKING BRAKE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . SET3) GUST LOCK. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .ENGAGE4) L and R WINDSHIELD HEAT. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF5) EMERGENCY LIGHTS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . PULL TURN / OFF6) LEFT and RIGHT FUEL / IGN . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF7) OXYGEN . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .PULL / OFF8) EXTERNAL LIGHTS. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF9) BATTERY 1 and 2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF

Procedure Completed




Spoiler Fail




A5-27 P/N 401-590001-0078

A5.14 GENERATOR OIL PRESSURE LOW

1. Generator (affected side). . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF2. APU START / STOP (if available and if 34,000 FT or below) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON AS DESIRED3. APU GEN. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .CONFIRM AUTO

Procedure Completed

A5.15 GENERATOR OVERHEAT

1. Generator (affected side). . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF2. APU START / STOP (if available and if 34,000 FT or below) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON AS DESIRED3. APU GEN. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .CONFIRM AUTO

Procedure Complete

A5.16 GENERATOR OVERLOAD

1. Unnecessary Electrical Equipment . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . TURN OFF

NOTEAuto load shed may take up to 5 minutes.

2. Elec Synoptic . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK OPERATING GENERATOR STATUS AND LOAD

NOTELoads may be restored if the operating generator load is less than 95%.

3. MCDU / CB / ELEC MENU / ELEC SYS CONTROL / LOAD RESTORE . . . . . . . . . . . . . . . . . . . . . .USE TO RESTORESHED ITEMS (IF REQUIRED)DO NOT EXCEED 95% LOAD

Procedure Completed

L Gen Oil Press LowOr

R Gen Oil Press Low

L Generator OverheatOr

R Generator Overheat

L Generator OverloadOr

R Generator Overload




A5.17 SPDA 1 FAIL Indicates SPDA 1 COM Failure or SPDA 1 Internal Failure

1. L MCDU / CB / ELEC MENU / CB BY SYSTEM . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OPEN

IF CB PAGE OPENS:

a. SPDA 1 COM FAILURE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . PERFORM

IF CB PAGE DOES NOT OPEN:

a. SPDA 1 INTERNAL FAILURE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . PERFORM

SPDA 1 COM FAILUREa. Functions Affected. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . REVIEW

NOTE• Expect full control of all soft CBs by either MCDU.

• Some CAS MSGs and Synoptic information may not be available.

IF WING ANTI-ICE WAS OFF:

1) Icing Conditions . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . EXIT / AVOID

IF WING ANTI-ICE WAS ON AND IS NO LONGER REQUIRED (IF TAT ABOVE 10° C / 50° F):

1) WING ANTI-ICE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF2) L WING AI VLV CB (MCDU / CB / ELEC MENU / CB BY SYSTEM / ICE) . . . . . . . . . . . . . . . . . . . . . . . . . . . .OUT

AT SHUT DOWN

1. PITOT HT1 CT, SEC STAT HT2, and TAT HEAT CTL CBs (MCDU / CB / ELEC MENU / CB BY SYSTEM / ICE). .OUT

Procedure Completed

Functions Affected By SPDA 1 COM Failure

Flight Controls Rudder Trim indication inoperative - system works. Left Shaker inoperative.

Engine Left Thrust Reverser is inoperative.

ECS Left Bleed Valve will close, no control available.

Anti-ice Equipment Left Engine Anti-ice Valve opens.Left Wing Anti-ice Valve holds last commanded position.

Lights Left Landing and Left Taxi lights will hold last commanded state.

SPDA 1 Fail




A5-29 P/N 401-590001-0078

SPDA 1 INTERNAL FAILURELeft MCDU CB access will be inoperative. R MCDU CB IN / OUT of SPDA #1 CBs is lost (status of SPDA #1 breakers is lost,status will be unknown).

a. Functions Affected . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . REVIEW

NOTESome CAS MSGs and Synoptic information may not be available.

CROSSFEED OPERATION

IF CROSSFEEDING TO THE LEFT ENGINE AT THE TIME OF FAILURE:

Do not select CROSSFEED to R ENG.

1) Select CROSSFEED to OFF when desired fuel balance is achieved.

IF RIGHT WING HEAVY:

a) For subsequent balancing, select CROSSFEED to L ENG, then OFF when desired fuel balance is achieved.

IF LEFT WING HEAVY:

a) For subsequent balancing, use differential thrust.

IF CROSSFEEDING TO THE RIGHT ENGINE AT THE TIME OF FAILURE:

1) Select R BOOST PUMP ON.2) Balance fuel with differential thrust.

ANTI-ICE OPERATION

IF WING ANTI-ICE OR ENGINE ANTI-ICE WAS OFF:

1) Icing Conditions . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . EXIT / AVOID2) Land . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . AS SOON AS PRACTICAL


Left Wing Anti-ice Valve cannot be closed.

1) WING ANTI-ICE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF2) BLEED ISOLATE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . VERIFY CLOSED

Functions Affected By SPDA 1 Internal FailureEngines Left Thrust Reverser is inoperative.

Fuel Fuel Crossfeed will hold last commanded position.Left Boost Pump will hold last commanded state.

ECS Left Bleed Valve will hold last commanded position.

Anti-ice Equipment Left Engine Anti-ice Valve will hold last commanded position.Left Windshield Heat provides continuous unregulated heat.Left Wing Anti-ice Valve will hold last commanded position.

Lights Left Landing, Left Taxi and Beacon lights will hold last commanded state.

Cabin and Doors Seat Belt signs hold last commanded state.




IF CAS MSG IS POSTED:

a) Left Engine. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . REDUCE THRUSTb) Land. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . NEAREST SUITABLE AIRPORT

IF RED “Wing A-Ice Temp High” CAS MSG IS CLEARED:

a) Land. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .AS SOON AS PRACTICAL

AT SHUT DOWN

Pitot, Static, and TAT heating remain on until all AC electrical power is removed. Ground crew to stayclear of heated external elements.

L Windshield Heat remains on until all AC electrical power is removed.

Procedure Completed

Wing A-Ice Temp High




A5-31 P/N 401-590001-0078

A5.18 SPDA 2 FAIL Indicates SPDA 2 COM Failure or SPDA 2 Internal Failure

1. R MCDU / CB / ELEC MENU / CB BY SYSTEM. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OPEN

IF CB PAGE OPENS:

a. SPDA 2 COM FAILURE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .PERFORM

IF CB PAGE DOES NOT OPEN:

a. SPDA 2 INTERNAL FAILURE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .PERFORM

SPDA 2 COM FAILUREa. Functions Affected . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . REVIEW

NOTE• Expect full control of all soft CBs by either MCDU.

• Some CAS MSGs and Synoptic information may not be available.

b. BLEED ISOLATE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OPEN

IF WING ANTI-ICE WAS OFF:

1) Icing Conditions . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . EXIT / AVOID


1) WING ANTI-ICE. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF2) L WING AI VLV CB (L MCDU / CB / ELEC MENU / CB BY SYSTEM / ICE) . . . . . . . . . . . . . . . . . . . . . . . . . .OUT

AT SHUT DOWN

1. PITOT HT2 CT, PRI STAT HT2 and R AOA HT CTL CBs (MCDU / CB / ELEC MENU / CB BY SYSTEM / ICE) . . . OUT

Procedure Completed

Functions Affected By SPDA 2 COM Failure

Flight Controls Aileron Trim indication inoperative - system works.

Engine Right Thrust Reverser is inoperative.

ECS Right Bleed Valve will close, no control available.If Bleed Isolation Valve is in AUTO, the valve will not open and the Cyan “Bleed Isol Not Open” CAS MSG will not be posted. Manual control is available.

Anti-ice Equipment Left Wing Anti-ice Valve holds last commanded position.

Lights Right Landing and Right Taxi lights will hold last commanded state.

Cabin and Doors No Smoking sign fails ON - no control.

SPDA 2 Fail




SPDA 2 INTERNAL FAILURERight MCDU CB access will be inoperative. L MCDU CB IN / OUT of SPDA #2 CBs is lost (status of SPDA #2 breakers is lost,status will be unknown).

a. Functions Affected. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . REVIEW


CROSSFEED OPERATION

IF CROSSFEEDING TO THE LEFT ENGINE AT THE TIME OF FAILURE:



a) For subsequent fuel balancing, select CROSSFEED to L ENG.b) Select CROSSFEED to OFF when desired fuel balance is achieved.

IF LEFT WING HEAVY:

a) For subsequent fuel balancing, select CROSSFEED to R ENG.b) Retard Right Thrust Lever N1 and monitor fuel balance.c) Select CROSSFEED to OFF when desired fuel balance is achieved.d) Reset Right Thrust Lever as desired.

IF CROSSFEEDING TO THE RIGHT ENGINE AT THE TIME OF FAILURE:



a) For subsequent balancing, use differential thrust.

Do not select CROSSFEED to L ENG.

IF LEFT WING HEAVY:

a) For subsequent fuel balancing, select CROSSFEED to R ENG.b) Select CROSSFEED to OFF when desired fuel balance is achieved.

Functions Affected By SPDA 2 Internal Failure

Engines Right Thrust Reverser is inoperative.

Fuel Right Boost Pump will hold last commanded position.

ECS Right Bleed Valve will hold last commanded position.Bleed Isolation Valve will hold last commanded position.

Anti-ice Equipment Right Engine Anti-ice Valve will hold last commanded position.Right Windshield Heat provides continuous unregulated heat.Left Wing Anti-ice Valve holds last commanded position.

Lights Right Landing and Right Taxi lights will hold last commanded state.

Cabin and Doors No Smoking signs hold last commanded state.




A5-33 P/N 401-590001-0078

ANTI-ICE OPERATION

IF WING ANTI-ICE OR ENGINE ANTI-ICE OFF:

1) Icing Conditions . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . EXIT / AVOID2) Land . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . AS SOON AS PRACTICAL


1) L WING AI VLV CB (L MCDU / CB / ELEC MENU / CB BY SYSTEM / ICE) . . . . . . . . . . . . . . . . . . . . . . . . . .OUT2) BLEED ISOLATE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . VERIFY CLOSED

Right Wing Anti-ice Valve cannot be closed.


a) Right Engine . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . REDUCE THRUSTb) Land . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . NEAREST SUITABLE AIRPORT

IF RED “Wing A-Ice Temp High” CAS MSG IS CLEARED:

a) Land . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . AS SOON AS PRACTICAL

AT SHUT DOWN

Pitot, Static, and AOA heating remain on until all AC electrical power is removed. Ground crew to stayclear of heated external elements.

R Windshield Heat remains on until all AC electrical power is removed.

Procedure Completed

Wing A-Ice Temp High




A5.19 TRU OVERHEAT

NOTE• The CAS MSG will post due to either insufficient cooling for TRU 1 or TRU 2 or

excessive DC loads.

• The system may isolate affected TRU by tripping TRU 1 AC CB or TRU 2 AC CB, which will cause itsassociated DC 1 Bus or DC 2 Bus to fail.

IN FLIGHT1. Altitude . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 35,000 FT MAXIMUM

IF OR CAS MSG IS POSTED:

a. DC 1 BUS FAIL (A5.7) or DC 2 BUS FAIL (A5.8) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . PERFORM

Procedure Completed

IF AMBER “DC 1 Bus Fail” OR “DC 2 Bus Fail” CAS MSG IS NOT POSTED:

a. Land . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .AS SOON AS PRACTICAL

Procedure Completed

ON GROUND1. NORMAL PROCEDURES - SHUT DOWN and SECURING. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . PERFORM

Procedure Completed

TRU 1 OverheatOr

TRU 2 OverheatOr

TRU 1-2 Overheat

TRU # Overheat

DC 1 Bus Fail DC 2 Bus Fail




A5-35 P/N 401-590001-0078

A5.20 TRU OVERLOAD

1. Following items are lost due to Auto Load Shed:

2. Elec Synoptic . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .CHECK TRU LOAD

3. Additional items can be manually shed until CAS MSG is cleared:

• Left MFD, Right PFD, SELCAL, Weather Radar, Cockpit lighting

IF CAS MSG IS STILL POSTED, EXPECT POSSIBLE DC BUS FAILURE:

a. DC 1 BUS FAIL (A5.7) or DC 2 BUS FAIL (A5.8) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . PERFORM, IF APPLICABLE

Procedure Completed

IF AMBER “TRU # Overload” CAS MSG IS CLEARED:

a. Elec Synoptic . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . MONITOR TRU LOAD

Procedure Completed

A5.21 EMER LIGHTS DISARMED 1. EMERGENCY LIGHTS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ARMED OR ON, AS APPROPRIATE

Procedure Completed

Auto Load Shed

Cabin lighting Fax and Modem PA System Airshow

Water Heater Water Pump Additional Passenger and Lavatory items

Additional (Optional) Items ShedHF 2 CMF ADF 2 Flight Phone

TRU 1 OverloadOr

TRU 2 OverloadOr

TRU 1-2 Overload

TRU # Overload

TRU # Overload

Emer Lights Disarmed




A5.22 CB TRIP

IN FLIGHT1. Check MCDU / CB / CB OUT / LOCK and acknowledge white high-lighted CB tripped and amber NEW TRIP MSG at

LSK 6R if posted.2. Attempt one CB reset if practical.

IF CAS MSG REPOSTS OR CB RESET IS NOT PRACTICAL:

a. Perform the applicable ABNORMAL and/or ADVISORY / STATUS PROCEDURES for any posted CAS MSG(s).

Procedure Completed

IF AMBER “CB Trip” CAS MSG IS CLEARED:

Procedure Completed

ON GROUND1. Check MCDU / CB / CB OUT / LOCK and acknowledge white high-lighted CB tripped and amber NEW TRIP MSG at

LSK 6R if posted.2. Attempt one CB reset if practical.

IF CAS MSG REPOSTS OR CB RESET IS NOT PRACTICAL:

a. Refer to the applicable ABNORMAL and/or ADVISORY / STATUS PROCEDURES for any posted CAS MSG(s) orMEL for affected system.

Procedure Completed

IF AMBER “CB Trip” CAS MSG IS CLEARED:

Procedure Completed

CB Trip

CB Trip

CB Trip




A6-1 P/N 401-590001-0078



INSTRUMENTS / AVIONICS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A6-3A6.1 FLAGS ON PFD, MFD, EICAS AND MCDU. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A6-3A6.2 AVIONICS TEMPERATURE HIGH . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A6-9A6.3 SINGLE DISPLAY FAULT OR OVERHEAT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A6-9A6.4 DUAL DISPLAY FAULT OR OVERHEAT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A6-10A6.5 SINGLE ADC FAILURE - RED X ON PFD FOR AIRSPEED, ALTITUDE AND VERTICAL SPEED DISPLAYS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A6-11A6.6 DUAL ADC FAILURE - RED X ON BOTH PFDS FOR AIRSPEED, ALTITUDE AND VERTICAL SPEED DISPLAYS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A6-11A6.7 SINGLE IRS FAIL, ATT FAIL ON PFD AND HDG FAIL ON PFD AND MFD . . . . . . . . . . . . . . . . . . . . . . . . . . . . A6-12A6.8 DUAL IRS FAIL, ATT FAIL ON BOTH PFDS AND HDG FAIL ON BOTH PFDS AND MFDS . . . . . . . . . . . . . . . A6-12A6.9 IRS POSITION FAULT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A6-13A6.10 IRS NOT READY . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A6-13A6.11 MAU OVERHEAT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A6-13A6.12 MAU FAN FAIL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A6-14A6.13 MAU 1A FAILURE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A6-14A6.14 MAU 2A FAILURE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A6-16A6.15 MAU 1B FAILURE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A6-18A6.16 MAU 2B FAILURE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A6-19A6.17 MAU 1A - 1B FAILURES . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A6-20A6.18 MAU 1A - 2A FAILURES / MONITOR WARNING 1 AND 2 FAILED - RED X OVER CAS FIELD. . . . . . . . . . . A6-22A6.19 MAU 1A - 2B FAILURES . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A6-24A6.20 MAU 1B - 2A FAILURES . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A6-26A6.21 MAU 1B - 2B FAILURES . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A6-28A6.22 MAU 2A - 2B FAILURES . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A6-29A6.23 AVIONICS BUS (ASCB) FAILURES / ABNORMAL DISPLAYS AND / OR 2 PFDS DISPLAYED ON LEFT OR RIGHT SIDE. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A6-31A6.24 RAD FAILURE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A6-31A6.25 AVIONICS CONFIG FAIL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A6-32A6.26 CONFIG MGMT 1-2 FAIL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A6-32A6.27 HARDWARE MISMATCH . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A6-32A6.28 FMS 1 GPS MISCOMPARE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A6-32A6.29 FMS 2 GPS MISCOMPARE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A6-32A6.30 FMS 1-2 GPS MISCOMPARE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A6-32A6.31 FMS POSITION MISCOMP . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A6-33




A6-2




A6-3 P/N 401-590001-0078

INSTRUMENTS / AVIONICS

A6.1 FLAGS ON PFD, MFD, EICAS AND MCDU

Warnings And Flags Description Crew Action

A/T

Red A/T is displayed on top of PFD. A/T has disengaged due to a force override or an Autothrottle 1 or 2 Fail, or due to Pilot pushing the A/T Engage / Disengage or the A/T DISC switch.

Adjust thrust manually and select other channel. Perform AUTOTHROTTLE DISC AND AUTOTHROTTLE 1 OR 2 FAIL (A10.10) or AUTOTHROTTLE DISC AND AUTOTHROTTLE 1 - 2 FAIL (A10.11).Cancel the MSG via the A/T DISC switch.

AP

Red AP is displayed on top of PFD. AP disconnect warning with a cavalry charge. Abnormal disconnect is continuous and

accompanied by CAS MSG. In case of a pilot initiated disconnect, the Red “AP” warning times out after 2 seconds.

Fly manually. Pilot needs to cancel warning tone by the AP TRIM PUSHER switch.Refer to SECTION 3B - ADVISORY/STATUS PROCEDURES for AP 1-2 Fail CAS MSG.

ATTFAIL

ATT FAIL is displayed on ADI. Indicates IRS

failure accompanied by CAS MSG.

Refer to Stby Inst.Perform SINGLE IRS FAIL, ATT FAIL ON PFD AND HDG FAIL ON PFD AND MFD (A6.7) for single IRS failure. Perform DUAL IRS FAIL, ATT FAIL ON BOTH PFDs AND HDG FAIL ON BOTH PFDs AND MFDs (A6.8) for dual IRS failure.

HDGFAIL

HDG FAIL is displayed on PFD HSI and ARC and on MFD below heading indication. Indicates IRS failure accompanied by

CAS MSG.

Refer to Stby Inst.Perform SINGLE IRS FAIL, ATT FAIL ON PFD AND HDG FAIL ON PFD AND MFD (A6.7) for single IRS failure. Perform DUAL IRS FAIL, ATT FAIL ON BOTH PFDs AND HDG FAIL ON BOTH PFDs AND MFDs (A6.8) for dual IRS failure.

NOTAKEOFF

Take-off Configuration Warning on ADI in

connection with CAS MSG and continuous aural tone.Airplane is not in the proper take-off configuration as indicated by the appropriate CAS MSG.

Perform NO TAKEOFF (E1.4).

PULL UP

Ground proximity warning. Appears on the right inside of the ADI. TAWS warning is active.

1. Thrust Levers to forward stop (rapidly).

2. Rotate to approximately 15° (two engines) or 10° (single engine). Maintain wings level.

3. Speedbrakes - Retracted.

4. AP - Disengage.

5. Adjust pitch, as required, allowing airspeed to decrease to intermittent stick shaker, if required.

6. Maintain gear and flaps in current position until safe climbout is assured.

AP 1-2 Fail

IRS # Fail

IRS # Fail

No Takeoff




STALL

Displayed on Left and Right upper half of ADI. Airplane has identified a Stall and Pusher has fired.

1. Lower pitch attitude to reduce AOA.

2. Thrust Levers to TO.

3. Level wings.

4. Accelerate and fly out of stall conditions.

RADRAD on bottom half of ADI. Radar Altimeter failure.

Perform RAD FAILURE (A6.24).

WINDSHEAR

Displayed on the upper half of the ADI below the Roll Pointer. Windshear warning posts and aural alert sounds if a decreasing headwind (or increasing tailwind) and/or a severe downdraft exceeds the defined threshold. The warning remains until conditions have returned to normal, or a minimum of 8 seconds.

1. Thrust Levers to forward stop (rapidly).

2. Rotate to approximately 15° (two engines) or 10° (single engine). Maintain wings level.

3. Speedbrakes - Retracted.

4. AP - Disengage.

5. Adjust pitch, as required, allowing airspeed to decrease to intermittent stick shaker, if required.

6. Maintain gear and flaps in current position until safe climbout is assured.

X Large X is displayed over the CAS field.CAS information is not available for both Monitor Warning 1 and Monitor Warning 2.

Monitor airplane functionality. Perform MAU 1A - 2A FAILURES / MONITOR WARNING 1 AND 2 FAILED (A6.18).OVER CAS FIELD

X

Internal DU software or hardware problem caused by power transient. Can also occur during power up on ground.

NOTE:A “Configuration Not Ready” message may appear, in addition, over DU 3.

In Flight:Perform SINGLE DISPLAY FAULT OR OVERHEAT (A6.3).On Ground (after initial power up):Power down airplane completely (batteries OFF) and restore normal electric power.

OVER DU 1, 2, 3, 4, 5

X ADC 1 or ADC 2, or ADC 1 and ADC 2 failed. Refer to Stby Inst.Perform SINGLE ADC FAILURE (A6.5) or DUAL ADC FAILURE (A6.6) procedure as applicable.

OVER AIRSPEED, ALTITUDE AND VERTICAL SPEED

DISPLAYS ON PFD

X This indicates loss of data from selected NAV source.

Select opposite NAV source.Verify opposite LOC 1 / LOC 2 or VOR 1 / VOR 2 or FMS 1 / FMS 2 is displayed on both PFDs and in case of FMS on MFD.

OVER LATERAL DEVIATION DISPLAY ON PFD HSI AND / OR

OVER THE GLIDE SLOPE SCALE FOR ILS AND FMS

X Left or Right MCDU has failed. If display does not automatically resume normal function after approximately 1 minute, use the other MCDU.

OVER MCDU





1 of 2 401-590001-0078TC6


Aug 2, 2012

ts93910

Rectangle





P/N 401-590001-0078TC6

SECTION 3A - ABNORMAL PROCEDURES

INSTRUMENTS / AVIONICSA6.1 FLAGS ON PFD, MFD, EICAS AND MCDU

Read the following WINDSHEAR message in place of the current BLANK message, under Warnings And Flags:




Description of Change Under Warnings And Flags column, insert WINDSHEAR text inside blank amber cell.

Filing Instructions Insert Page 2 of 2 to face page A6-5 in Section 3A - Abnormal Procedures.


WINDSHEAR

Displayed on the upper half of the ADI below the Roll Pointer. Caution alert posts if an increasing headwind (or decreasing tailwind) and/or a severe updraft exceeds the defined threshold. The caution remains until conditions have returned to normal or a minimum of 8 seconds.

Crew Awareness:During approach, consider a go-around. If approach is continued, closely monitor airspeed and glidepath and avoid prolonged thrust reduction.

During Takeoff:Verify take-off thrust is set and maintain take-off path attitude.

Aug 2, 2012

ts93910

Rectangle



A6-5 P/N 401-590001-0078

WINDSHEAR

Displayed on the upper half of the ADI below the Roll Pointer. Caution alert posts if an increasing headwind (or decreasing tailwind) and/or a severe updraft exceeds the defined threshold. The caution remains until conditions have returned to normal or a minimum of 8 seconds.

Crew Awareness:During approach, consider a go-around. If approach is continued, closely monitor airspeed and glidepath and avoid prolonged thrust reduction.

During Takeoff:Verify take-off thrust is set and maintain take-off path attitude.

-------- System Information lost or invalid (No Data) Crew Awareness.

AMBER DASHES ONLY

ADC 1

Displayed in top of PFD and MFD. Pilot’s and Copilot’s PFD indicate the same Air Data source.

Monitor Stby Inst. AP cannot be re-engaged.Apply appropriate RVSM contingency procedures.

NOTEFor airplanes with Enhanced Mode S Transponder installed, the AFCS should remain coupled to the operative side ADC.

OrADC 2

On Both PFDs

ALT?

Displayed in Altitude tape on PFD. Monitor has detected more than 200 FT difference between Pilot’s and Copilot’s PFD altimeter indication.

Check and set Baro settings to agree.If ALT? flag does not clear compare altitude with Stby Inst.PFD AIR DATA: Select side that agrees with the Stby Inst.Confirm both sides indicate ADC 1 or ADC 2 as applicable.Apply appropriate RVSM contingency procedures.

DGRDDisplayed in right side of PFD. The FMS uses degraded mode.Some sensor inputs are missing.

Do not use FMS as primary NAV for terminal area navigation.

DR

Displayed in right side of PFD. The FMS has reverted to DR mode and lost major sensor inputs.

Check position sensor status on the FMS Position sensor page.Use other sensors if available for NAV. TERRAIN INHIBIT select.

DU #-#

Displayed in upper right corner of PFD. Display Unit failures indicated in addition to CAS MSG showing any combination of DU failures.

Perform SINGLE DISPLAY FAULT OR OVERHEAT (A6.3) or DUAL DISPLAY FAULT OR OVERHEAT (A6.4).

FD FAIL

Displayed in top of PFD. Flight Director fail. On either PFD Attitude Indication, loss of valid pitch and roll commands from the active AFCS.

Select other AFCS.

GND PROX Displayed in right side of ADI. TAWS caution advisory is active.

Recheck Terrain Clearance. Follow aural commands.

GS?Displayed in right side of ADI. Monitor has detected more than 2/3 dot Glideslope miscompare.

Go Around during CAT 2 Approach.Use side which agrees with Stby Inst for airplane control.

H

Displayed after VOR distance in PFD and MFD.DME is in HOLD mode on selected MCDU Radio page.

Crew Awareness.





HDG?

Displayed in actual heading on PFD and MFD. Monitor has detected Heading Miscompare of Pilot’s and Copilot’s compass of more than 10°.

Compare heading with Stby Inst.PFD ATT REF: Select side which agrees with Stby Inst.Confirm both sides indicate IRS 1 or IRS 2.

IAS?

Displayed in PFD Airspeed Tape. Monitor has detected more than 20 KIAS difference between Pilot’s and Copilot’s PFD Airspeed indication.

Compare Airspeed with Stby Inst.PFD AIR DATA: Select side that agrees with the Stby Inst.Confirm both sides indicate ADC 1 or ADC 2.

ICING Displayed in left side of PFD. Icing conditions are detected and ice protection is OFF or failed.

Perform ICING (A12.4)

IRS 1 Displayed in top of PFD. Both PFDs using same attitude and heading reference.

Pilots monitor Stby Inst.

OrIRS 2

On Both PFDs

LIM

A/T MSG displayed in the A/T mode field on the PFD.Autothrottle has reached limit to acquire and maintain its selected airspeed in descent, climb or cruise.Autothrottle reached limit for maximum or minimum speed.

Use Speedbrake as required in descent and monitor airspeed in climb and cruise.

LOC?Displayed in PFD, center of HSI. Monitor has detected more than 1/2 dot Localizer miscompare.

Go Around during CAT 2 Approach.Use side which agrees with Stby Inst for airplane control.

LOW FUEL Displayed in left side of PFD. Indicates fuel quantity is below 760 LB (345 KG) in either side.

Perform FUEL QUANTITY LOW (A11.6).

LPV

The PFD amber LPV annunciator indicates that the system is not capable of LPV operations. If inside the FAF, lateral and vertical deviation indications are removed from the PFD.

• LPV approach may be continued usingcross side LPV if indications are normal

• If outside the FAF, the approach may becontinued to LNAV / VNAV or LNAVminimums.

• Otherwise, go around.

MAX SPD Displayed in the lower left corner of the ADI. AFCS over speed protection mode is active.

Reduce airspeed as required.

MIN

Displayed in the upper left corner of the ADI. MSG indicates airplane has reached approximate Baro or RAD Alt minimum on a precision or non-precision approach.

Crew act as required by Approach Procedures and Approach Minimums.

MSG

Displayed in right side of the PFD. The PFD Annunciation indicates an FMS MSG on the MCDU scratch pad.

Check MCDU scratch pad for MSGs. Take appropriate action (if required).

NOTEAssociated Scratchpad MSGs will not be displayed if on a CB or Radio page.





A6-7 P/N 401-590001-0078

MW 1MW 1 or MW 2 displayed in EICAS status line. Miscompare detected between MW 1 and MW 2.

MCDU / MENU / DISP SETUP / CAS MSG SRC / MW 1 or MW 2, select opposite side. Compare CAS MSGs. Select side with higher number of CAS MSGs displayed.Note the additional MSGs and carry out Crew procedures as required.

OrMW 2

RA FAILDisplayed in lower right side of PFD.TCAS Resolution Advisory (RA) has failed and is not available.

MCDU / RADIO / TCAS / XPDR / TA SELECT. Crew Awareness.

RAD?

Displayed in center of bottom half of ADI. Radio Altitude indication on Pilot’s and Copilot’s PFD differ by more than10 FT below 200 FT,more than 22.5 FT between 200 and 1000 FT,more than 72.5 FT between 1000 FT and 2000 FT, and more than 135 FT above 2000 FT.

Perform RAD FAILURE (A6.24).Do not fly to CAT 2 minimums.

ROLL?

Displayed in top of ADI. Monitor has detected Attitude Miscompare of Pilot’s and Copilot’s attitude of more than 6° in roll.

Compare roll with Stby Inst. PFD ATT REF: Select side which agrees with Stby Inst.Confirm both sides indicate IRS 1 or IRS 2.

PITCH?

Displayed in top of ADI. Monitor has detected Attitude Miscompare of Pilot’s and Copilot’s attitude of more than 5° in pitch.Fuel quantity indication is degraded on side with faulty pitch display.

Compare pitch with Stby Inst. PFD ATT REF: Select side which agrees with Stby Inst.Confirm both sides indicate IRS 1 or IRS 2.Subtract 700 LB (318 KG) from fuel quantity reading on degraded side for endurance and add 700 LB (318 KG) of fuel quantity on degraded side for weight calculations.

NOTESelecting PFD ATT REF does not restore fuel quantity accuracy on affected side.

TCAS FAIL Displayed in lower right PFD.TCAS System is inoperative.

Increase vigilance for other traffic.

TCAS TEST Displayed in lower right PFD. TCAS is in Test mode.

Confirm TCAS Test passes.

VSPD Displayed below Airspeed Tape on PFD.Displays if any VSPD missing or invalid.

Review VSPEED entry and complete if necessary.

VTA

Displayed in top of Vertical Deviation Scale.Flashing indicates airplane is approaching an FMS vertical track profile requiring altitude change.

Pilot is to monitor AP FD modes appropriate to the altitude change.

WX FAIL

Displayed in PFD and MFD.Weather Radar has failed or GND MAP or WX mode was selected during Weather Radar warm up period.

Plan route as to avoid forecasted thunderstorms, or wait until warm up period is over (approximately 2 minutes).

XTKDisplayed in the right side of the PFD. Indicates that the airplane is on a temporary offset course.

Remember the OFFSET clearance limit and get back on track when required.





A red Low Speed Awareness bar may be displayed along the lower right side of the airspeed tape. The bar’s position is based on airspeed, airplane configuration and AOA. The shaker occurs at the top of the red range.

When the A/T is engaged in SPD mode, the amber bar appears. The A/T system is not allowed to fly the airplane at an airspeed below the top of the amber band.

Crew Awareness.

Airspeed Trend is illustrated by a white vertical bar positioned along the right side of the Airspeed Tape depicting the current acceleration / deceleration trend.The airspeed rolling digits turn AMBER INVERSE VIDEO when the Airspeed Trend vector is equal to or greater than the airplane’s current speed limit value.

Reduce thrust and extend Speedbrake as required or perform OVERSPEED RECOVERY (E1.5).


RC03D110682AB.AI

RC03D110673AA.AI




A6-9 P/N 401-590001-0078

A6.2 AVIONICS TEMPERATURE HIGH 1. L and R PACKS. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .AUTO2. FLIGHT DECK and CABIN HIGH FLOW. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . HIGH3. FLIGHT DECK and CABIN TEMP SELECT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . COOL

IF CAS MSG STILL IS POSTED:

a. Load Shed (MCDU / CB / ELEC MENU / CB BY SYSTEM / AVIONICS). . . . . . . . . . . COM 2, NAV 2, DME 2, ADF 1b. Land . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . AS SOON AS PRACTICAL

Procedure Completed

IF AMBER “Avionics Temp High” CAS MSG IS CLEARED:

Procedure Completed

A6.3 SINGLE DISPLAY FAULT OR OVERHEAT

1. Affected Display. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF LOAD AS FOLLOWS:

IF EICAS:

a. MFD DISPLAY REVERSION DU 4. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . EICAS

Procedure Completed

IF PFD:

a. MFD DISPLAY REVERSION (affected side) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . PFD

Procedure Completed

IF MFD:

a. MFD DISPLAY REVERSION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . PULL-OFF

Procedure Completed

Avionics Temp High

Avionics Temp High

Display # FaultOr

Display # Ovht




A6.4 DUAL DISPLAY FAULT OR OVERHEAT

1. Stby Inst . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . MONITOR (USE AS PRIMARY REFERENCE)2. PFD (if Display 1 and 5 Fail) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . RESTORE 13. EICAS Display (if Failed) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .RESTORE

Accomplish the above according to the following table:

FOOT NOTE:

(A) Momentary use of an MFD to monitor a Synoptic display is permissible, but the display must be returned toEICAS format as soon as practical.

4. For Overheat Only, De-power Affected Displays as Follows:

FOOT NOTE:

(A) MCDU / CB / ELEC MENU / CB BY SYSTEM / AVIONICS 7/12 LEFT PFD or 11/12 RIGHT PFD

Procedure Completed

FAILED DISPLAYS REVERSION ACTION AIRPLANE CONTROL MFD SCREEN1 and 2 None Right DU 4

1 and 3 Left MFD to EICAS Right DU 4

1 and 4 None Right DU 2

1 and 5 Left MFD to PFD Left DU 4

2 and 3 Right MFD to EICAS Left or Right DU 4 (A)2 and 4 None Left or Right None

2 and 5 None Left DU 4

3 and 4 Left MFD to EICAS Left or Right DU 2 (A)3 and 5 Right MFD to EICAS Left DU 2

4 and 5 None Left DU 2

AFFECTED DISPLAYS REVERSION ACTION AIRPLANE CONTROL DE-POWER ACTION1 and 2 None Right (A) L PFD-CB Out; L MFD Pull Off

1 and 3 Left MFD to EICAS Right (A) L PFD CB Out

1 and 4 None Right (A) L PFD CB Out; R MFD Pull Off

1 and 5 Left MFD to PFD Left (A) R PFD CB Out

2 and 3 Right MFD to EICAS Left or Right (A) L MFD Pull Off

2 and 4 None Left or Right (A) L MFD Pull Off; R MFD Pull Off

2 and 5 None Left (A) L MFD Pull Off; R PFD CB Out

3 and 4 Left MFD to EICAS Left or Right (A) R MFD Pull Off

3 and 5 Right MFD to EICAS Left (A) R PFD CB Out

4 and 5 None Left (A) R MFD Pull Off; R PFD CB Out

Display #-# FaultOr

Display #-# Ovht




A6-11 P/N 401-590001-0078

A6.5 SINGLE ADC FAILURE - RED X ON PFD FOR AIRSPEED, ALTITUDE AND VERTICALSPEED DISPLAYS

NOTE• AP will disengage and cannot be re-engaged.


• A/T may disconnect.

1. Flight Control and Thrust . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . FLY MANUALLY2. Stby Inst. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . MONITOR3. PFD AIR DATA (affected side) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .SELECT4. A/T . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ENGAGE, IF DESIRED5. AFCS (with optional Mode S Enhanced Surveillance Transponder installed) . . . . . . . . . . . . . . . . . . . VERIFY COUPLED

TO OPERATIVE SIDE ADC

Procedure Completed

A6.6 DUAL ADC FAILURE - RED X ON BOTH PFDs FOR AIRSPEED, ALTITUDE ANDVERTICAL SPEED DISPLAYS

1. Flight Control and Thrust . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . FLY MANUALLY USING STBY INST2. Significant Items Lost. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . REVIEW



NOTENormalized AOA Displays will not be functional on both PFDs.

4. Pressurization . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . SELECT MANUAL CONTROL5. MANUAL PRESSURIZATION CONTROL (A4.1). . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . REVIEW, AS REQUIRED6. Land. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . NEAREST SUITABLE AIRPORT7. Landing Airspeed, Landing Distance . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .SEE TABLE

a. Select runway with no tailwind.

Procedure Completed

Significant Items Lost

AP Autothrottle Mach Trim ΔP Display on EICAS

Automatic Pressurization Ground Proximity Terrain TCAS


Landing Distance Multiply by 1.2




A6.7 SINGLE IRS FAIL, ATT FAIL ON PFD AND HDG FAIL ON PFD AND MFD

NOTEDo not disengage YD as it will not re-engage.

1. Flight Control and Thrust . . . . . . . . . . . . . . . . . . . . . . . . . . FLY MANUALLY USING CROSS SIDE PFD OR STBY INST2. PFD ATT REF (affected side) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . SELECT3. AP and A/T. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . RE-ENGAGE, IF REQUIRED

NOTEFuel quantity is degraded on affected side and CAS MSG will post. Subtract 700LB (318 KG) of fuel quantity reading per degraded tank for endurance and add 700 LB (318 KG) of fuelquantity per degraded tank for weight calculations.

Procedure Completed

A6.8 DUAL IRS FAIL, ATT FAIL ON BOTH PFDs AND HDG FAIL ON BOTHPFDs AND MFDs

1. Flight Control and Thrust . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . FLY MANUALLY BY USING STBY INST2. Dutch Roll. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . SUPPRESS WITH LATERAL CONTROL INPUT, AS REQUIRED3. Significant Items Lost . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . REVIEW

NOTE• Stall protection system will not compensate for high entry rate stalls.



4. Altitude . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 35,000 FT OR BELOW5. Land . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .AS SOON AS PRACTICAL6. Landing FLAPS and Airspeed . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 20° / VREF + 10 KIAS7. REDUCED FLAP APPROACH AND LANDING (A1.1) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . PERFORM

Procedure Completed


AP YD Autothrottle Fuel Qty accuracy

Cat 2 Weather Radar stabilization

ATT and HDG Source on both PFDs

HDG Source on both MFDs

Ground Proximity Terrain

IRS 1 FailOr

IRS 2 Fail

Fuel Qty Degrade

IRS 1-2 Fail

Fuel Qty Degrade




A6-13 P/N 401-590001-0078

A6.9 IRS POSITION FAULT

NOTE• IRS did not receive position data on power up (ground only).

• Ensure airplane is at a position where GPS can be received.

1. Position Initialization (MCDU / NAV / POS INIT / LOAD) . . . . . . . . . . . . . . . . . LOAD CURRENT AIRPLANE POSITION2. IRS 1 AND 2 (MCDU / NAV / POS SENSOR / IRS# / STATUS). . . . . . . . . . . . . . . . . . . VERIFY ALIGNMENT STATUS

Procedure Completed

A6.10 IRS NOT READY

NOTEAbove 30 KT ground speed, the IRS will go to Align-In-Motion (AIM) mode. AIM provides attitude andheading, but not navigation data.

ON GROUNDStop the airplane and allow the Stationary Alignment process to complete. The “Time To NAV” information (MCDU / NAV / POSSENSOR / IRS# / STATUS) displays the time remaining until the alignment completes.

Procedure Completed

A6.11 MAU OVERHEAT

1. FLIGHT DECK and CABIN HIGH FLOW. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . HIGH2. FLIGHT DECK and CABIN TEMP SELECT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . COOL


NOTEBe prepared for reduced systems capability if MAU systems fail.


Procedure Completed

IF AMBER “MAU # Ovht” CAS MSG IS CLEARED:

Procedure Completed

IRS Position Fault

IRS Not Ready

MAU 1 OvhtOr

MAU 2 OvhtOr

MAU 1-2 Ovht

MAU # Ovht




A6.12 MAU FAN FAIL 1. FLIGHT DECK and CABIN HIGH FLOW. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . HIGH2. MAU OVERHEAT (A6.11) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . PERFORM, IF REQUIRED

Procedure Completed

A6.13 MAU 1A FAILURE

NOTE• Erroneous CAS MSG may post if both thrust levers are advanced.

• Erroneous CAS MSG and left oil pressure red inverse video may post. Monitorleft oil pressure value for normal readings (20 to 106 PSI).

1. Flight Control and Thrust . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . FLY MANUALLY2. Significant Items Lost . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . REVIEW



FOOT NOTE:

(A) Spoilers functional, but with reduced deflection even though CAS MSG is posted.


3. Airspeed. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . BELOW 0.78M / 300 KIAS4. Left PFD AIR DATA . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . REVERT TO ADC 25. FD . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ENGAGE, AS REQUIRED6. MCDU (for FMS and Radio control) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . USE RIGHT SIDE7. Pressurization . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . SELECT MANUAL CONTROL8. MANUAL PRESSURIZATION CONTROL (A4.1) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . REVIEW, AS REQUIRED9. Icing Conditions . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . EXIT / AVOID

10. PUSHER FAIL (A9.7) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . REVIEW, AS REQUIRED

Significant Items Lost_ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _MAU 1A Fail

Flight Controls (A) Mach Trim, Left Shaker, Pusher, Spoiler Indication on EICAS

Engine Autothrottle, Left Thrust Reverser


Fuel Left Fuel Quantity Indication, Left Fuel Flow Indication, Fuel Used Indication on EICAS and FMS (frozen at last value)

Radios HF 1, Pilot’s: MCDU Radio Control

Avionics AP, ADC 1, GPS 1, Standby Instrument ILS, Ground Proximity, Pilot’s: MCDU FMS Control


ECS Automatic Pressurization

Lights Ice Detect lights

MAU Fan Fail

MAU 1A Fail

No Takeoff

L Oil Press Low

Spoiler Fail




A6-15 P/N 401-590001-0078

NOTE• Right Fuel Quantity Indication is available, but degraded.



11. Fuel . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . USE RIGHT FUEL QUANTITY INFORMATION X 212. Land. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . NEAREST SUITABLE AIRPORT13. By 1500 FT AGL, CABIN DEPRESSURIZATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . DUMP14. Landing Considerations:


rudder for directional control. Add differential braking if required when rudder becomes ineffective.c. Ground Spoilers will be operative.d. Flaps are operative.e. Right Thrust Reverser will be available. Left Thrust Reverser is inoperative.


1) Multiply landing distance by 1.6 and increase brake energy by 0.2 MFP.




Procedure Completed

IF AMBER “Brake Degrade” CAS MSG IS CLEARED:

1) Multiply landing distance by 1.2.

Procedure Completed

Fuel Qty Degrade

Brake Degrade




A6.14 MAU 2A FAILURE


• Erroneous CAS MSG and right oil pressure red inverse video may post. Monitorright oil pressure value for normal readings (20 to 106 PSI).




FOOT NOTE:



3. Airspeed. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . BELOW 0.78M / 300 KIAS4. Right PFD AIR DATA. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . REVERT TO ADC 15. FD . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ENGAGE, AS REQUIRED6. MCDU (for FMS and Radio control) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . USE LEFT SIDE7. Pressurization . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . SELECT MANUAL CONTROL8. MANUAL PRESSURIZATION CONTROL (A4.1) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . REVIEW, AS REQUIRED9. Icing Conditions . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . EXIT / AVOID

NOTE• Left Fuel Quantity Indication is available, but degraded.



Significant Items Lost_ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _MAU 2A Fail

Flight Controls (A) Mach Trim, Right Shaker



Fuel Right Fuel Quantity Indication, Right Fuel Flow Indication, Fuel Used Indication on EICAS and FMS

Radios HF 2, Copilot’s: MCDU Radio Control

Avionics AP, ADC 2, GPS 2, Copilot’s: MCDU FMS Control

Gear and Brakes Nosewheel Steering, Gear Indication on EICAS and Synoptic, Gear Retraction


Anti-ice Equipment Left and Right Engine Anti-ice Control

Oxygen Oxygen Auto Deploy

MAU 2A Fail

No Takeoff

R Oil Press Low

Spoiler Fail

Fuel Qty Degrade




A6-17 P/N 401-590001-0078

10. Fuel . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . USE LEFT FUEL QUANTITY INFORMATION X 211. Land. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . NEAREST SUITABLE AIRPORT12. By 1500 FT AGL, CABIN DEPRESSURIZATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . DUMP 13. Landing Considerations:


b. Normal Gear Extension is available even though CAS MSG is posted.

c. Gear indication on EICAS and Flt Ctl Synoptic will be inoperative. Gear warning is still functional. After gear extension,select flaps 35 to verify no gear warning. Absence of the gear warning visual and aural cues with flaps 35 indicates allthree gear are down.

NOTEBelow 500 FT AGL, Ground Proximity “Too Low Gear” warning will sound with gear extended.

d. Nosewheel Steering will be inoperative even though the Amber “Nosewheel Steer Fail” CAS MSG does not post. Userudder for directional control. Add differential braking if required when rudder becomes ineffective.

e. Ground Spoilers will be operative.f. Flaps are operative.

g. Left and Right Thrust Reversers will be inoperative.






Procedure Completed



Procedure Completed

Gear System Fail

Brake Degrade




A6.15 MAU 1B FAILURE 1. Flight Control and Thrust . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . FLY MANUALLY2. Significant Items Lost . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . REVIEW

NOTE Some CAS MSGs and Synoptic information may not be available.


3. Airspeed. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . BELOW 0.78M / 300 KIAS4. FMS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . USE FMS 15. Landing Considerations:

a. Select wide runway with minimum crosswind, no tailwind.b. Nosewheel Steering is inoperative, even though Amber “Nosewheel Steer Fail” CAS MSG is not posted. Use rudder

for directional control. Add differential braking if required when rudder becomes ineffective.c. Ground Spoilers are operative.d. Flaps are operative.e. Left Thrust Reverser will be inoperative.f. Normal Brakes are operative.

g. Right Landing and Right Taxi lights are inoperative.6. Multiply landing distance by 1.2.

Procedure Completed

Significant Items Lost_ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _MAU 1B Fail

Flight Controls Mach Trim

Engine Autothrottle, Left Thrust Reverser


Avionics AP, Some FD Modes, FMS 2, Copilot’s: MCDU FMS Control


MAU 1B Fail




A6-19 P/N 401-590001-0078

A6.16 MAU 2B FAILURE 1. Flight Control and Thrust . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . FLY MANUALLY2. Significant Items Lost. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . REVIEW

NOTE Some CAS MSGs and Synoptic information may not be available.


3. Airspeed. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . BELOW 0.78M / 300 KIAS4. FMS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . USE FMS 25. Landing Considerations:

a. Nosewheel Steering will be operative.b. Flaps, Normal Brakes and Ground Spoilers will be operative.c. Right Thrust Reverser is inoperative. Left Thrust Reverser will be operative.

Procedure Completed

Significant Items Lost_ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _MAU 2B Fail


Engine Autothrottle, Right Thrust Reverser


Avionics AP, Some FD Modes, FMS 1, Pilot’s: MCDU FMS Control

MAU 2B Fail




A6.17 MAU 1A - 1B FAILURES

NOTEErroneous CAS MSG may post if both thrust levers are advanced.




FOOT NOTES:

(A) Spoilers functional, but with reduced deflection even though CAS MSG is posted.(B) Primary Pitch Trim will work only in slow rate.


3. Airspeed. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . BELOW 0.78M / 300 KIAS4. Left PFD AIR DATA . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . REVERT TO ADC 25. Left PFD ATT REF. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . REVERT TO IRS 26. FMS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . USE FMS 1

NOTENo changes can be made to the Flight Plan, but the data from FMS 1 will remain valid.

7. MCDU . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . USE RIGHT SIDE8. FD . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ENGAGE, AS REQUIRED9. Pressurization . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . SELECT MANUAL CONTROL

10. MANUAL PRESSURIZATION CONTROL (A4.1) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . REVIEW, AS REQUIRED11. Icing Conditions . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . EXIT / AVOID12. L-R SHAKER FAIL (A9.8) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . REVIEW, AS REQUIRED

Significant Items Lost_ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _MAU 1A - 1B Fail

Flight Controls (A) (B) Mach Trim, Left and Right Shaker, Pusher, Pitch Trim Indications, Aileron Trim Indications, Flap Indications, Spoiler Indications on EICAS

Engine Autothrottle, Left Thrust Reverser, Left Engine Displays


Fuel Left Fuel Quantity Indication, Left Fuel Flow Indication, Fuel Used Indication on EICAS and FMS


Avionics AP, Some FD Modes, FMS 2, ADC 1, IRS 1, GPS 1, Standby Instrument ILS, Pilot’s: MCDU FMS and Electrical Controls, Copilot’s: MCDU FMS Control, TCAS, Ground Proximity


ECS Automatic Pressurization, Pressurization Indication on EICAS, Bleed Isolate Auto Function

Anti-ice Equipment Tail De-ice, Right Engine Anti-ice

Lights Left Landing light, Left and Right Taxi lights, Beacon lights, Strobe lights, NAV lights, Ice Detect lights

Cabin and Doors No Smoking and Seat Belt Signs

MAU 1A-1B Fail

No Takeoff

Spoiler Fail




A6-21 P/N 401-590001-0078



• Fuel quantity is degraded on affected side and CAS MSG will post. Subtract 700LB of fuel quantity reading per degraded tank for endurance and add 700 LB of fuel quantity perdegraded tank for weight calculations.



b. Normal Gear operation is available even though CAS MSG is posted.

c. Nosewheel Steering will be inoperative even though the Amber “Nosewheel Steer Fail” CAS MSG does not post. Userudder for directional control. Add differential braking if required when rudder becomes ineffective.

d. Ground Spoilers will be operative.e. Flaps are operative.f. Left Thrust Reverser is inoperative.

g. Left Landing and both Taxi lights are inoperative.h. Select Flt Ctl Synoptic Display.

NOTEOne pair of brakes may have failed without posting the CAS MSG.

IF “BRAKE PRESS” SHOWS AMBER DASHES FOR ONE PAIR OF BRAKES:





Procedure Completed

IF “BRAKE PRESS” IS DISPLAYED FOR ALL FOUR BRAKES:


Procedure Completed

Fuel Qty Degrade

Gear System Fail

Brake Degrade




A6.18 MAU 1A - 2A FAILURES / MONITOR WARNING 1 AND 2 FAILED -

RED X OVER CAS FIELD

NOTE• Complete loss of MW 1 and 2.

• All aural and visual alerts are inoperative.


IF FUEL QUANTITY INDICATION VALID:

MW 1 and 2 have failed, all other systems are operational, monitor airplane system functionality.1. Land . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .AS SOON AS PRACTICAL

Procedure Completed

IF FUEL QUANTITY INDICATION IS INVALID:

MAU 1A and 2A have failed.1. Flight Control and Thrust . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . FLY MANUALLY USING STBY INST2. Dutch Roll. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . SUPPRESS WITH LATERAL CONTROL INPUT, AS REQUIRED3. Radio Tuning . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . PFD CCD TUNING4. Radio Transmissions . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .USE PILOT’S SIDE5. Significant Items Lost . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . REVIEW

NOTE• Complete loss of all CAS MSGs and Synoptic Information will occur.

• Erroneous left and right oil pressure red inverse video will be displayed. Monitor oil pressure for normalreadings (20 to 106 PSI).

FOOT NOTE:

(A) Primary Pitch Trim will work only in slow rate.

Significant Items Lost_ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _MAU 1A - 2A Fail

Flight Controls (A) Mach Trim, YD, Left and Right Shaker, Pusher

Engine Autothrottle, Left and Right Thrust Reverser, APU, Thrust Rating Indications

FOPS Fire Annunciations, Smoke Detection and Bleed Leak Detection

Fuel All Fuel Quantity Indications, Low Fuel Quantity Indication on EICAS and PFD, Left and Right Fuel Flow Indication, Fuel Used on EICAS and FMS

Radios HF 1, Pilot’s and Copilot’s: MCDU Radio Control, Copilot Transmit Inoperative

Avionics All CAS MSGs, Aural Warnings, Master Warning lights, Master Caution lights, AP, FD, FMS 1 and 2, Terrain, TCAS, ADC 1 and 2, NAV 1 and 2, IRS 1 and 2, Standby Instrument ILS, Ground Proximity, Pilot’s and Copilot’s: MCDU FMS Control

Gear and Brakes Nosewheel Steering, Normal Brakes, Gear Indication, Gear Retraction



Lights Recog lights, Strobe lights, Ice Detect lights




A6-23 P/N 401-590001-0078


6. Airspeed. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . BELOW 0.78M / 300 KIAS7. Altitude. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 35,000 FT OR BELOW8. Pressurization . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . SELECT MANUAL CONTROL9. MANUAL PRESSURIZATION CONTROL (A4.1). . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . REVIEW, AS REQUIRED

10. L and R BOOST PUMP . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON11. Icing Conditions . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . EXIT / AVOID12. L-R SHAKER FAIL (A9.8). . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . REVIEW, AS REQUIRED13. Fuel Used . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . TIME BASED ON FLIGHT PLAN14. Land. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . NEAREST SUITABLE AIRPORT

WITH VISUAL METEOROLOGICAL CONDITIONS15. By 1500 FT AGL, CABIN DEPRESSURIZATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . DUMP16. Landing FLAPS and Airspeed . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .20° / VREF + 10 KIAS17. Landing Considerations:

a. Select wide runway with crosswind not exceeding 10 KT, no tailwind.b. Gear will function with no gear indications or gear warning available. Tower fly by is recommended to verify gear

down.c. Nosewheel Steering will be inoperative. Use rudder for directional control.d. Ground Spoilers are operative.e. Flaps are operative.f. Left and Right Thrust Reversers are inoperative.

• EMERGENCY / PARKING BRAKE does not provide anti-skid protection.

• Take care not to extend the EMERGENCY / PARKING BRAKE into the PARK position while theairplane is in motion since excessive braking may result in locked wheels and possibly, burst tires.

g. EMERGENCY / PARKING BRAKE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . APPLY SMOOTHLY, AS REQUIREDh. Multiply landing distance by 2.0 and increase brake energy by 7.5 MFP.


1) Verify corrected brake energy does not exceed 46.2 MFP.

Procedure Completed






• Erroneous CAS MSG and left oil pressure red inverse video may post. Monitorleft oil pressure value for normal readings.




FOOT NOTE:



3. Airspeed. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . BELOW 0.78M / 300 KIAS4. Left PFD AIR DATA . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . REVERT TO ADC 25. FMS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . USE FMS 26. MCDU (for FMS and Radio control) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . USE RIGHT SIDE7. Pressurization . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . SELECT MANUAL CONTROL8. MANUAL PRESSURIZATION CONTROL (A4.1) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . REVIEW, AS REQUIRED9. Icing Conditions . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . EXIT / AVOID






Flight Controls (A) Mach Trim, Left Shaker, Pusher, Spoiler Indication on EICAS



Fuel Left Fuel Quantity Indication, Left Fuel Flow Indication, Fuel Used Indication on EICAS and FMS


Avionics AP, Some FD Modes, FMS 1, ADC 1, GPS 1, Standby Instrument ILS, Ground Proximity, Pilot’s: MCDU FMS Control



Lights Ice Detect lights

MAU 1A-2B Fail

No Takeoff

L Oil Press Low

Spoiler Fail

Fuel Qty Degrade




A6-25 P/N 401-590001-0078



rudder for directional control. Add differential braking if required when rudder becomes ineffective.c. Ground Spoilers are operative.d. Flaps are operative.e. Left and Right Thrust Reversers are inoperative.






Procedure Completed



Procedure Completed

Brake Degrade




A6.20 MAU 1B - 2A FAILURES


• Erroneous CAS MSG and right oil pressure red inverse video may post. Monitorright oil pressure value for normal readings.




FOOT NOTES:

(A) Spoilers functional, but with reduced deflection even though CAS MSG is posted.(B) Primary Pitch Trim will work only in normal rate.


3. Airspeed. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . BELOW 0.78M / 300 KIAS4. Right PFD AIR DATA. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . REVERT TO ADC 15. FMS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . USE FMS 16. MCDU (for FMS and Radio control) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . USE LEFT SIDE7. Pressurization . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . SELECT MANUAL CONTROL8. MANUAL PRESSURIZATION CONTROL (A4.1) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . REVIEW, AS REQUIRED9. Icing Conditions . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . EXIT / AVOID





Significant Items Lost_ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _MAU 1B - 2A Fail

Flight Controls (A) (B) Mach Trim, Pusher, Right Shaker





Avionics AP, Some FD Modes, FMS 2, ADC 2, GPS 2, Copilot’s: MCDU FMS Control





MAU 1B-2A Fail

No Takeoff

R Oil Press Low

Spoiler Fail

Fuel Qty Degrade




A6-27 P/N 401-590001-0078

11. Fuel . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . USE LEFT FUEL QUANTITY INFORMATION X 212. Land. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . NEAREST SUITABLE AIRPORT13. By 1500 FT AGL, CABIN DEPRESSURIZATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . DUMP14. Landing Considerations:


b. Normal Gear Operation is available even though CAS MSG is posted.c. Gear indication on EICAS and Flt Ctl Synoptic will be inoperative. Gear warning is still functional. After gear extension,

select flaps 35 to verify no gear warning. Absence of the gear warning visual and aural cues with flaps 35 indicates allthree gear are down.



e. Ground Spoilers are operative.f. Flaps are operative.

g. Left and Right Thrust Reversers are inoperative.






Procedure Completed



Procedure Completed

Gear System Fail

Brake Degrade




A6.21 MAU 1B - 2B FAILURES 1. Flight Control and Thrust . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . FLY MANUALLY2. Significant Items Lost . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . REVIEW



3. Airspeed. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . BELOW 0.78M / 300 KIAS4. Primary Navigation. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . USE SRN (SHORT RANGE NAV)5. MANUAL LDG ELEV (MCDU / MENU / CABIN PRES) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ENTER6. Landing Considerations:

a. Select wide runway with minimum crosswind, no tailwind.b. Nosewheel Steering is inoperative, even though Amber “Nosewheel Steer Fail” CAS MSG is not posted. Use rudder

for directional control. Add differential braking if required when rudder becomes ineffective.c. Ground Spoilers are operative.d. Flaps are operative.e. Left and Right Thrust Reversers are inoperative.f. Normal Brakes are operative.

7. Multiply landing distance by 1.2.

Procedure Completed

Significant Items Lost_ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _MAU 1B - 2B Fail




Avionics AP, Some FD Modes, FMS 1 and 2


MAU 1B-2B Fail




A6-29 P/N 401-590001-0078


NOTEErroneous CAS MSG may post if both thrust levers are advanced.

1. Flight Control and Thrust . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . FLY MANUALLY2. Significant Items Lost. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . REVIEW



FOOT NOTES:

(A) Spoilers functional, but with reduced deflection even though CAS MSG is posted.(B) Primary Pitch Trim will work in normal rate.


3. Airspeed. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . BELOW 0.78M / 300 KIAS4. Right PFD ATT REF . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . REVERT TO IRS 15. Right PFD AIR DATA. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . REVERT TO ADC 16. FMS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . USE FMS 27. MCDU (for FMS and Radio control). . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . USE LEFT SIDE8. FD . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ENGAGE, AS REQUIRED9. Pressurization . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . SELECT MANUAL CONTROL

10. MANUAL PRESSURIZATION CONTROL (A4.1). . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . REVIEW, AS REQUIRED11. Icing Conditions . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . EXIT / AVOID





Flight Controls (A) (B) Mach Trim, Right Shaker, Rudder Trim Indication, Spoiler Indication on EICAS

Engine Autothrottle, Left and Right Thrust Reverser, APU, Right Engine Displays




Avionics AP, Some FD Modes, FMS 1, ADC 2, IRS 2, GPS 2, Copilot’s: MCDU FMS Control





MAU 2A-2B Fail

No Takeoff

Spoiler Fail

Fuel Qty Degrade




12. Fuel . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . USE LEFT FUEL QUANTITY INFORMATION X 213. Land . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . NEAREST SUITABLE AIRPORT14. By 1500 FT AGL, CABIN DEPRESSURIZATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . DUMP15. Landing Considerations:


b. Normal Gear Extension is available even though CAS MSG is posted.

c. Gear indication on EICAS and Flt Ctl Synoptic will be inoperative. Gear warning is still functional. After gear extension,select flaps 35 to verify no gear warning. Absence of the gear warning visual and aural cues with flaps 35 indicates allthree gear are down.



e. Ground Spoilers are operative.f. Flaps are operative.

g. Left and Right Thrust Reversers are inoperative.






Procedure Completed



Procedure Completed

Gear System Fail

Brake Degrade




A6-31 P/N 401-590001-0078

A6.23 AVIONICS BUS (ASCB) FAILURES / ABNORMAL DISPLAYS AND /OR 2 PFDS DISPLAYED ON LEFT OR RIGHT SIDE

One or two primary avionics buses have detected a problem. The effects and indications will vary depending on the type andlocation of the failure. Monitor and crosscheck systems operation and indications and perform procedures for additional CASMSGs displayed.

1. The following systems may be affected:a. Cross side data may not be available to the PFD, MFD and/or MCDU.

b. Some CAS MSGs and Synoptic information may not be available. If is displayed in the CAS status line:

1) MCDU / MENU / DISP SETUP / CAS MSG SRC / MW 1 OR MW 2. . . . . . . . . . . . . . . SELECT OPPOSITE SIDE2) MW 1 AND MW 2 CAS MSGs . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . COMPARE3) MW WITH HIGHER NUMBER OF CAS MSGs . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .SELECT

c. Some switch lights may be inoperative.d. If two PFDs are displayed on the same side:

1) Left or Right MFD DISPLAY REVERSION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . PULL-OFFe. Left or Right CCD may not be available. Use opposite side CCD.f. Scrolling of CAS MSGs may not be available. MFD DISPLAY REVERSION to EICAS may regain function.

g. Autopilot and Flight Director operation may be affected. Selecting opposite side PFD with the CPL switch or theopposite AFCS from the MCDU DISP SETUP page may regain function.

h. Autothrottle operation may be affected. Selecting opposite A/T from the MCDU DISP SETUP page may regainfunction.

i. Gear indications may be inoperative. Gear warning is still functional. After gear extension, select FLAPS 35° to verifyno gear warning. Absence of the gear warning visual and aural cues with FLAPS 35° indicates all three gear aredown.

j. Below 500 FT AGL, Ground Proximity “Too Low Gear” warning may sound with gear extended.k. If Fuel Quantity indication is in degrade mode, subtract 700 LB (318 KG) of fuel quantity per degraded tank for

endurance and add 700 LB (318 KG) of fuel quantity per degraded tank for weight calculation.

Procedure Completed

A6.24 RAD FAILURERed RAD below attitude indicator indicates radio altimeter inop. Procedure valid also if RAD? is posted on both PFDs.

1. Significant Items Lost. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . REVIEW

2. A/T . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . DISENGAGE ON FINAL APPROACH3. SPEEDBRAKE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .CONFIRM STOWED BY 600 FT AGL

NOTELanding Gear Warning may appear below 14,000 FT and 170 KIAS with thrust reduced unless gear isdown and locked.

Procedure Completed


TCAS Ground Proximity CAS MSG Landing Inhibit Cat 2 Capability

A/T RETARD mode

Avionics Bus # Fail

MW #




A6.25 AVIONICS CONFIG FAIL Ground Only CAS MSG.

Configuration Management System is disabled or there is a miscompare between a personality module and the CMS masterconfiguration file.

Configuration of the installed equipment/software is unknown.1. No Dispatch.

Procedure Completed

A6.26 CONFIG MGMT 1-2 FAIL Ground Only CAS MSG.

Both CMSs have failed.

Avionics is unable to determine if software configuration matches installed hardware.1. No Dispatch.

Procedure Completed

A6.27 HARDWARE MISMATCH Ground Only CAS MSG.

CMS has detected a change in part number on installed equipment at airplane power up.

The newly installed hardware may not be compatible with current avionics software.1. No Dispatch.

Procedure Completed

A6.28 FMS 1 GPS MISCOMPARE Airplane location as recorded by FMS 1 is different than the position recorded by GPS.

1. Primary Navigation. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . DO NOT USE FMS 1

Procedure Completed

A6.29 FMS 2 GPS MISCOMPARE Airplane location as recorded by FMS 2 is different than the position recorded by GPS.

1. Primary Navigation. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . DO NOT USE FMS 2

Procedure Completed

A6.30 FMS 1-2 GPS MISCOMPARE Airplane location as recorded by FMS 1 and 2 is different than the position recorded by GPS.

1. Primary Navigation. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . USE SRN AND / OR VALID GPS POSITION IF AVAILABLE

Procedure Completed

Avionics Config Fail

Config Mgmt 1-2 Fail

Hardware Mismatch

FMS 1 GPS Miscompare

FMS 2 GPS Miscompare

FMS 1-2 GPS Miscompare




A6-33 P/N 401-590001-0078

A6.31 FMS POSITION MISCOMP The airplane position as reported by FMS 1 does not agree with the position reported by FMS 2, while one of the FMS is theactive Nav source.

1. Primary Navigation . . . . . . . . . . . . . . . . . . . . . . . . . . . . USE SRN AND / OR VALID FMS, IF IT CAN BE DETERMINED

Procedure Completed

FMS Position Miscomp




A7-1 P/N 401-590001-0078



LANDING GEAR / BRAKES . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A7-3 FIGURE 1 - EICAS LANDING GEAR INDICATIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A7-3

A7.1 EMERGENCY LANDING GEAR EXTENSION. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A7-4A7.2 LANDING GEAR THREE GREEN NOT INDICATED. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A7-5A7.3 LANDING GEAR HANDLE LOCKED DOWN . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A7-5A7.4 GEAR SYSTEM FAIL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A7-6A7.5 BRAKE WARM . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A7-6A7.6 NOSEWHEEL STEER FAIL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A7-8A7.7 BRAKE DEGRADE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A7-9A7.8 BRAKE FAILURE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A7-10A7.9 BRAKE PEDAL FAILURE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A7-11A7.10 UNCOMMANDED BRAKE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A7-11A7.11 ANTISKID FAIL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A7-12A7.12 PARK BRAKE PRESSURE LOW . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A7-13A7.13 PARK BRAKE ON . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A7-13A7.14 WEIGHT-ON-WHEELS FAILURE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A7-13




A7-2




A7-3 P/N 401-590001-0078

LANDING GEAR / BRAKES

FIGURE 1EICAS LANDING GEAR INDICATIONS

RC03D 062161AA.AI

N o r m a l

D o w n

C y c l e

N o r m a l

U p

C y c l e

A b n o r m a l

C y c l e

UPUP

UPDOOR

Gear Caution, Door Open

Gear in transit

Black and White

Red and White

Amber and Black = Gear Unsafe >17sec, Horn Not Active

= Gear Unsafe >17sec, Horn Active

Normal Gear In Transit <17 sec

Gear Up and Locked

Display blanked if

Gear and Doors up and locked for 5 sec AND No are True

Any Gear not up and lockedAny Door not closed and lockedGear Horn activeGear Handle Not Up

DOOR

DOORDN

DNDN

DOOR

DNDN

DOOR

UP UP UP

DNDN

DNDN

DN

DN DNDN

UPUPUP

Doors Open

Gear In Transit

Gear Down, LockedDoors OpenDOOR

Gear Down, Locked

Gear Up and Locked

Doors shut

Gear Unsafe, Door Open

Gear Locked Down,Door Open > 17sec

Any Door Open < 17sec

Any Door Open > 17sec

DOOR

DOOR

Gear not down/locked AND any of:WOW on groundFLAPS > 25RAD Alt below 600 ft with thrust reducedRAD Alt inop and

valid CAS < 170 andvalid PA below 14,500 ftand thrust reduced

Door in transit




A7.1 EMERGENCY LANDING GEAR EXTENSION

IF LANDING GEAR FAILS TO EXTEND:

1. Altitude . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . MAINTAIN 20,000 FT OR BELOW2. Airspeed. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .200 KIAS OR BELOW3. LANDING GEAR Handle . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .DOWN4. EMER GEAR Handle . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . PULL FULLY UP

IF ONE OR MORE LANDING GEAR IS NOT DOWN AND LOCKED:

a. LANDING WITH GEAR UP / PARTIALLY EXTENDED (E7.3) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . PERFORM

Procedure Completed

IF THREE GREEN AND IS POSTED ON EICAS:

EMER GEAR Handle must not be stowed after gear extension.

NOTE• Sufficient ground clearance will be available with main gear doors open.

• Nosewheel Steering is inoperative.

• Gear retraction will not be available during Go Around.

a. Runway . . . . . . . . . . . . . . . . . . . . . . . . . . SELECT WIDE RUNWAY WITH MINIMUM CROSSWIND, NO TAILWINDb. Directional Control. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . USE RUDDER AND DIFFERENTIAL BRAKINGc. Landing Distance. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .MULTIPLY BY 1.2

Procedure Completed


1. Altitude . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . MAINTAIN 20,000 FT OR BELOW2. Airspeed. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .200 KIAS OR BELOW3. LANDING GEAR Handle . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .DOWN4. EMER GEAR Handle . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . PULL FULLY UP


a. LANDING WITH GEAR UP / PARTIALLY EXTENDED (E7.3) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . PERFORM

Procedure Completed





a. HYDRAULIC PRESSURE LOW (A8.1) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . PERFORM

Procedure Completed

DOOR

R Hyd Press Low

DOOR




A7-5 P/N 401-590001-0078


1. FLAPS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . UP / 0°

2. Altitude. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . MAINTAIN 20,000 FT OR BELOW3. Airspeed. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 150 - 180 KIAS4. LANDING GEAR Handle . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . DOWN

NOTE• Yawing airplane up to 1/2 triangle deflection may assist the Main Gear to lock down.

• A yellow “X” on the Rudder may be seen briefly on the flight controls synoptic when yawing theairplane. Rudder function is not degraded.

5. EMER GEAR Handle. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . PULL FULLY UP


a. LANDING WITH GEAR UP / PARTIALLY EXTENDED (E7.3) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .PERFORM

Procedure Completed


a. FLAPS. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . AS REQUIRED




b. HYDRAULIC PRESSURE LOW (A8.1) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .PERFORM

Procedure Completed

A7.2 LANDING GEAR THREE GREEN NOT INDICATED1. EMERGENCY LANDING GEAR EXTENSION (A7.1) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .PERFORM

Procedure Completed

A7.3 LANDING GEAR HANDLE LOCKED DOWNPossible problem in the WOW system.

IF CLIMB PERFORMANCE IS ADEQUATE AND CAS MSG IS POSTED:

1. LANDING GEAR Handle . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .LEAVE DOWN2. GEAR SYSTEM FAIL (A7.4). . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .PERFORM

Procedure Completed

IF CLIMB PERFORMANCE IS NOT ADEQUATE OR AMBER “Gear System Fail” CAS MSG IS CLEARED:

1. LANDING GEAR Handle Down Lock MANUAL RELEASE. . . . . . . . . . . . . . . . . . . . . . . . . . PUSH TO RETRACT LOCK2. LANDING GEAR Handle . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . UP

Procedure Completed

L-R Hyd Press Low

DOOR

Gear System Fail




A7.4 GEAR SYSTEM FAIL

NOTEThis CAS MSG may be erroneous when displayed during DC BUS and MAU failures.

After Takeoff:

1. LANDING GEAR Handle . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . DOWN (DO NOT RETRACT)2. Airspeed. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .MAINTAIN BELOW 230 KIAS3. Altitude . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . MAINTAIN 20,000 FT OR BELOW4. Fuel . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CALCULATE RANGE5. Land . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . NEAREST SUITABLE AIRPORT

Procedure Completed

Prior to Landing:

NOTEGear retraction may not be available during Go Around.

1. Landing Gear Handle . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .DOWN

IF GEAR DOES NOT EXTEND:

a. EMERGENCY LANDING GEAR EXTENSION (A7.1) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . PERFORM

Procedure Completed

IF GEAR DOES EXTEND:

Procedure Completed

A7.5 BRAKE WARM

ON GROUND

IF DURING TAKEOFF:

1. REJECTED TAKEOFF (E1.1) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . PERFORM

Procedure Completed

IF BEFORE TAKEOFF (TAKEOFF INTENDED):

Brake failure may occur during a rejected takeoff if brake temperatures are greater than 177° C wheninitiating the takeoff. Adequate brake energy will be available for a rejected takeoff if the requirements ofStep 2 are met.

1. Flt Ctl Synoptic . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . MONITOR BRAKE TEMPERATURES

2. Takeoff with the CAS MSG posted is permitted if the following requirements are met:• BRAKE TEMP data must be available on the Flt Ctl Synoptic.• All four BRAKE TEMPs must have peaked and be decreasing.• Ambient temperature 35° C (95° F) or cooler.• No obstacles in flight path.• No Tailwind.• ECS - ON, HIGH FLOW - OFF, ANTI-ICE - OFF.• Take-off Performance Simplified Criteria MAY NOT be used.• The brake energy required for takeoff must be less than the value in the table below.

Gear System Fail

Brake Warm

Brake Warm




A7-7 P/N 401-590001-0078

NOTEWhen using the table below, the highest brake temperature must be used.

NOTEIn case of engine failure during takeoff, landing gear may be retracted to safely clear any obstacles.Landing gear should then be extended and a minimum speed of V2 maintained.

After Takeoff:3. LANDING GEAR Handle . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . DOWN (DO NOT RETRACT)4. Brakes . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . COOL IN AIRSTREAM5. Amber “Brake Warm” CAS MSG . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . VERIFY CLEARED

NOTEIt is recommended that the brake temperatures be reduced to less than 150° C, as brake temperaturesmay rise after retraction when the brakes are no longer in the airstream.

6. LANDING GEAR Handle (below 210 KIAS) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . UP

Procedure Completed

IF DURING TAXI (TAKEOFF NOT INTENDED):

1. Flt Ctl Synoptic. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . MONITOR BRAKE TEMPERATURES

NOTEThe CAS MSG may post following landing with light to moderate braking. It is safe totaxi the airplane providing no Red “Brake Hot” CAS MSG posts. At parking, the airplane should bechocked as soon as practical.

At Parking:

If brake temperatures are still increasing at shutdown, chock the airplane and remain clear of the mainlanding gear and the area directly inboard and outboard of the main landing gear wheels.

1. Parking Brake (after airplane has been chocked) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . RELEASE

Procedure Completed

IN FLIGHT1. LANDING GEAR Handle (below 230 KIAS) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . DOWN2. Brakes . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . COOL IN AIRSTREAM3. Amber “Brake Warm” CAS MSG . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . VERIFY CLEARED

NOTEIt is recommended that the brake temperatures be reduced to less than 150° C, as brake temperaturesmay rise after retraction when the brakes are no longer in the airstream.

4. LANDING GEAR Handle (below 210 KIAS) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . UP5. UNCOMMANDED BRAKE (A7.10). . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . PERFORM, IF REQUIRED

Procedure Completed

Highest Brake Temp - °C Maximum Takeoff Brake Energy - MFP350 33300 37250 42200 46.2

Brake Warm




A7.6 NOSEWHEEL STEER FAIL

NOTE• In cases where the Nosewheel Steering has failed due to electrical BUS or MAU channel failures, the

Amber “Nosewheel Steer Fail” CAS MSG will not post.

• Do not cycle the nosewheel circuit breaker if the Nosewheel Steering has failed due to an electricalBUS failure, MAU channel failure, or hydraulic system failure.

IN FLIGHT1. Nosewheel Steering . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . TILLER, CONFIRM CENTERED2. MCDU / CB / ELEC MENU / CB BY SYSTEM / LDGR / NW STEERING . . . . . . . . . . . . . . . . . . . . . . . . CYCLE OUT / IN


a. Runway . . . . . . . . . . . . . . . . . . . . . . . . . . SELECT WIDE RUNWAY WITH MINIMUM CROSSWIND, NO TAILWINDb. Directional Control. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . USE RUDDER AND DIFFERENTIAL BRAKINGc. Landing Distance. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .MULTIPLY BY 1.2

Procedure Completed

IF AMBER “Nosewheel Steer Fail” CAS MSG IS CLEARED:

Procedure Completed

ON GROUNDDuring Taxi:

1. Directional Control . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . USE DIFFERENTIAL BRAKING2. Airplane . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . BRING TO A COMPLETE STOP3. Nosewheel Steering . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . TILLER, CONFIRMED CENTERED4. MCDU / CB / ELEC MENU / CB BY SYSTEM / LDGR / NW STEERING . . . . . . . . . . . . . . . . . . . . . . . . CYCLE OUT / IN


Limited steering capability through use of differential braking has been demonstrated with NosewheelSteering inoperative. Due to limited steering capability, extreme care should be taken when taxiing withNosewheel Steering inoperative.

a. Directional Control. . . . . . . . . . . . . . . . . . . . . . . . . . USE DIFFERENTIAL BRAKING AND DIFFERENTIAL THRUST

Procedure Completed

IF AMBER “Nosewheel Steer Fail” CAS MSG IS CLEARED:

a. Nosewheel Steering . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . AS REQUIRED

Procedure Completed

Nosewheel Steer Fail






A7-9 P/N 401-590001-0078

A7.7 BRAKE DEGRADE Loss of inboard or outboard braking.

Takeoff:


Procedure Completed

Approach and Landing:

1. Landing Considerations:a. Select runway with no tailwind.b. Use rudder and Nosewheel Steering for directional control. Avoid asymmetric braking.c. Use Thrust Reversers (if operative).

2. Landing Distance . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . MULTIPLY BY 1.3


a. Verify brake energy does not exceed 28.3 MFP.


Procedure Completed

Brake Degrade




A7.8 BRAKE FAILURE

Complete LANDING checklist included.

• EMERGENCY / PARKING BRAKE does not provide anti-skid protection.

• Take care not to extend the EMERGENCY / PARKING BRAKE into the PARK position while theairplane is in motion since excessive braking may result in locked wheels and possibly, burst tires.

NOTESimultaneous operation of the EMERGENCY / PARKING BRAKE, Thrust Reversers and NosewheelSteering will require crew coordination.

Complete loss of normal brakes on affected side.

ON GROUND1. Thrust Levers . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . IDLE2. EMERGENCY / PARKING BRAKE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .APPLY SMOOTHLY, AS REQUIRED3. Thrust Reversers . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . AS REQUIRED4. Nosewheel Steering . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . AS REQUIRED

Procedure Completed

IN FLIGHT1. Landing Considerations:

a. Select runway with no tailwind.b. Use rudder and Nosewheel Steering for directional control. c. Use Thrust Reversers (if operative).d. Select Flt Ctl Synoptic Display to monitor brake pressure after landing.

2. Landing Distance . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .MULTIPLY BY 1.53. Airspeed. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .VREF (FLAPS 35°)

LANDING1. Thrust Levers . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . IDLE2. EMERGENCY / PARKING BRAKE (after nosewheel touchdown) . . . . . . . . . . . . .APPLY SMOOTHLY, AS REQUIRED3. Flt Ctl Synoptic . . . . . . . . . . . . . . . . . . . . . . . . . . . . .MONITOR BRAKE PRESSURE (APPROXIMATELY 900 PSI MAX)4. Thrust Reversers (after nosewheel is on ground) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . DEPLOY5. Reverse Thrust (when deployment confirmed) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . AS REQUIRED6. Nosewheel Steering (all gear firmly on ground) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . AS REQUIRED7. Reverse Thrust. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . IDLE BY 60 KIAS8. Thrust Reversers . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . STOW BY TAXI SPEED

Procedure Completed

L Brake FailOr

R Brake Fail




A7-11 P/N 401-590001-0078

A7.9 BRAKE PEDAL FAILURE

During Taxi:

IF BRAKES AFFECTED ON PILOT SIDE:

1. EMERGENCY / PARKING BRAKE . . . . . . . . . . . . . . . . . . . . . . APPLY SMOOTHLY, STOP AIRPLANE IF REQUIRED

Taxiing from the right seat is not recommended in congested areas.

2. Airplane taxi by Pilot using EMERGENCY / PARKING BRAKE or Copilot using differential braking.

Procedure Completed

IF BRAKES AFFECTED ON COPILOT SIDE:

1. Airplane taxi by Pilot.

Procedure Completed

Landing:

1. Landing and Braking . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . PERFORMED BY PILOT WITH OPERATING BRAKES

Procedure Completed

A7.10 UNCOMMANDED BRAKE

ON GROUNDDuring Takeoff:


Procedure Completed

IN FLIGHT


1. Brake Warm (A7.5). . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .PERFORM

Procedure Completed

IF AMBER “Brake Warm” CAS MSG IS CLEARED:

1. ANTI-SKID. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF2. Toe Brakes . . . . . . . . . . . . . . . PUMP SEVERAL TIMES TO EXTINGUISH AMBER “Uncommanded Brake” CAS MSG3. ANTI-SKID. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON


• Tire burst is likely when landing with uncommanded brake. Flt Ctl Synoptic page may be used todetermine affected wheel.

• Expect degraded directional control due to uncommanded braking and / or possible tire burst.

Pilot Brake Pedal FailOr

Coplt Brake Pedal Fail

Uncommanded Brake

Brake Warm

Uncommanded Brake




a. Runway . . . . . . . . . . . . . . . . . . . . . SELECT WIDE LONG RUNWAY WITH MINIMUM CROSSWIND, NO TAILWINDb. Landing / Touchdown point . . . . . . . . . . . . . . . . . . . . . . . . . . . PLAN OPPOSITE TO THE UNCOMMANDED BRAKEc. Directional Control. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . USE RUDDER AND NOSEWHEEL STEERING

Procedure Completed

IF AMBER “Uncommanded Brake” CAS MSG IS CLEARED:

Procedure Completed

After Landing / Taxi:

Do not continue taxiing with CAS MSG displayed and brake temperatures continuing toincrease.

1. Flt Ctl Synoptic . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . MONITOR BRAKE TEMPERATURES2. Taxi to ramp if brake temperatures permit.

Procedure Completed

A7.11 ANTISKID FAIL

• Tire burst possible when landing / taxiing with antiskid failure.

• Exercise caution when applying brakes with antiskid failure.

1. ANTI-SKID . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CYCLE OFF, THEN ARM

IN FLIGHT

IF CAS MSG STILL POSTED:

a. Landing Considerations:1) Monitor brake pressure on Flt Ctl Synoptic (approximately 900 to 1000 PSI).2) Apply brakes as required to avoid locking wheels.3) Use Thrust Reversers (if operative).

b. Landing Distance. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .MULTIPLY BY 1.4

Procedure Completed

IF AMBER “Antiskid Fail” CAS MSG IS CLEARED:

Procedure Completed

ON GROUND


a. No Dispatch.

Procedure Completed

IF AMBER “Antiskid Fail” CAS MSG IS CLEARED:

a. Normal Dispatch.

Procedure Completed

Brake Warm

Antiskid Fail

Antiskid Fail

Antiskid Fail




A7-13 P/N 401-590001-0078

A7.12 PARK BRAKE PRESSURE LOW

Do not start engines with this CAS MSG posted unless wheels are chocked.

1. AUX PUMP . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON2. Amber “Park Brake Press Low” CAS MSG . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . VERIFY CLEARED3. AUX PUMP . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .AUTO

Procedure Completed

A7.13 PARK BRAKE ON

NOTE CAS MSG will post only when airplane is airborne and EMERGENCY / PARKING

BRAKE is not stowed.

1. EMERGENCY / PARKING BRAKE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . STOW2. Amber “Park Brake On” CAS MSG . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . VERIFY CLEARED

Procedure Completed

A7.14 WEIGHT-ON-WHEELS FAILURE Complete checklists are included for AFTER LANDING and SHUT DOWN.

WOW system may be unable to define air / ground status correctly. Monitor systems operation and perform procedures for theadditional CAS MSGs displayed. Do not perform Touch-and-Go landings.

IN FLIGHT

NOTEThe following systems may be affected:

• Gear may not retract.• Pressurization may not be regulated in AUTO mode in air. Review MANUAL PRESSURIZATION

CONTROL (A4.1), as required.• Low speed awareness may not display on the PFD.• Weather Radar may be in the GROUND STBY mode. If Weather Radar is desired:

1. Select MFD Radar menu.

2. Select STBY OVRD.

3. Re-select STBY OVRD.

1. Landing Considerations:a. Select wide runway with minimum crosswind, no tailwind.b. Nosewheel Steering may be inoperative even if the Amber “Nosewheel Steer Fail” CAS MSG is not posted. Use

rudder for directional control. Add differential braking, if required, when rudder becomes ineffective.c. Brake touchdown protection may not function.d. Thrust Reversers may be inoperative.

2. Landing Distance . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . MULTIPLY BY 1.2

Park Brake Press Low

Park Brake On

Park Brake On

WOW Fail




AFTER LANDING1. SPEEDBRAKE. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . RETRACT2. FLAPS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .UP / 0°

3. STABILIZER TRIM. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .SET TO TAKE-OFF RANGE4. Anti-ice / De-ice . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF, AS REQUIRED5. EXTERNAL LIGHTS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . AS REQUIRED6. Weather Radar. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .STBY7. CABIN DEPRESSURIZATION (if required) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . DUMP

• Pitot Probes, Static Plates, Angle Of Attack (AOA) vanes may still be heated after engine shutdown.

• L AOA vane will remain heated until AC power is removed from the airplane.

8. Depower Pitot Static, AOA, and TAT heat:a. STBY P / S HEAT (CBP 1) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .OUTb. MCDU / CB / ELEC MENU / CB BY SYSTEM / ICE:

1) PITOT HT1 CT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .OUT2) PITOT HT2 CT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .OUT3) PRI STAT HT2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .OUT4) R AOA HT CTL. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .OUT5) SEC STAT HT2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .OUT6) TAT HT CTL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .OUT

9. APU START / STOP . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON, AS DESIREDa. APU BLEED . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . AUTO

SHUT DOWN1. EMERGENCY / PARKING BRAKE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . SET2. GUST LOCK . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .ENGAGE3. L and R WINDSHIELD HEAT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF4. Anti-ice / De-ice . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF5. EMERGENCY LIGHTS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . PULL TURN / OFF6. EXTERNAL LIGHTS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . AS REQUIRED7. AC or DC External Power (if required) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CONNECT / ON

GROUND POWER UNIT IS NOT TO BE UTILIZED:

a. Continue with Step 8.

GROUND POWER UNIT IS TO BE UTILIZED:

IF AC OR DC EXTERNAL:

1) AC or DC External Power Source (ground crew) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CONNECTED AND ON

2) AC or DC EXT (switch out). . . . . . . . . . . . . . . . . . . . . . . . . .CONFIRM AC OR DC EXT ILLUMINATED

3) AC or DC EXT (switch in) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON, WHITE “AVAIL” EXTINGUISHED

EXTERNAL PNEUMATIC SOURCE TO BE UTILIZED FOR ENVIRONMENTAL:

1) External Pneumatic Source (ground crew). . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CONNECTED / ON

AVAIL




A7-15 P/N 401-590001-0078

8. LEFT and RIGHT FUEL / IGN . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF9. SEAT BELT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF

10. BEACON . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF11. OXYGEN . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . PULL / OFF12. APU START / STOP (if operating). . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF13. AC EXT OR DC EXT (if used) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . (SWITCH OUT) AVAIL14. AC or DC External Power (if used) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF15. EXTERNAL LIGHTS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF16. BATTERY 1 and 2 (5 seconds after EICAS APU display clears) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF

Procedure Completed

ON GROUND1. CABIN DEPRESSURIZATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .DUMP, IF REQUIRED

• Pitot Probes, Static Plates, Angle Of Attack (AOA) vanes may still be heated after engine shutdown.

• L AOA vane will remain heated until AC power is removed from the airplane.

2. Depower Pitot Static, AOA, and TAT heat:a. STBY P / S HEAT (CBP 1) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OUTb. MCDU / CB / ELEC MENU / CB BY SYSTEM / ICE:

1) PITOT HT1 CT. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OUT2) PITOT HT2 CT. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OUT3) PRI STAT HT2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OUT4) R AOA HT CTL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OUT5) SEC STAT HT2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OUT6) TAT HT CTL. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OUT

3. SECTION 4 - NORMAL PROCEDURES - SHUT DOWN and SECURING . . . . . . . . . . . . . . . . . . . . . . . . . . .PERFORM4. No Dispatch.

Procedure Completed




A8-1 P/N 401-590001-0078



HYDRAULICS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A8-3A8.1 HYDRAULIC PRESSURE LOW . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A8-3A8.2 FLIGHT WITH HYDRAULIC FAILURE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A8-4A8.3 HYDRAULIC OVERHEAT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A8-7A8.4 EMERGENCY RUDDER SYSTEM OVERHEAT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A8-8




A8-2




A8-3 P/N 401-590001-0078

HYDRAULICS

A8.1 HYDRAULIC PRESSURE LOW

1. Hyd Synoptic . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . MONITOR FOR HYDRAULIC SYSTEM STATUS


a. Land . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . AS SOON AS PRACTICAL

NOTEPTU is not available.

b. FLIGHT WITH HYDRAULIC FAILURE (A8.2) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .PERFORM

Procedure Completed

IF CYAN “# Hyd Fluid Low” CAS MSG IS NOT POSTED:

a. HYDRAULIC PUMP (affected side(s)) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CYCLE OFF, THEN AUTOb. POWER TRANSFER . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CYCLE OFF, THEN AUTO

IF CAS MSG DOES NOT CLEAR:

1) Land . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . AS SOON AS PRACTICAL2) FLIGHT WITH HYDRAULIC FAILURE (A8.2) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .PERFORM

Procedure Completed

IF AMBER “# Hyd Press Low” CAS MSG IS CLEARED:

1) Land . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . AS SOON AS PRACTICAL

Procedure Completed

L Hyd Press LowOr

R Hyd Press LowOr

L-R Hyd Press Low

# Hyd Fluid Low

# Hyd Press Low




A8.2 FLIGHT WITH HYDRAULIC FAILURE

LEFT HYDRAULIC SYSTEM FAILED:

1. Significant Items Lost . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . REVIEW

Approach and Landing:2. Landing Considerations:

a. Select long runway with minimum crosswind, no tailwind.b. Select FLAP WARN.




Procedure Completed

RIGHT HYDRAULIC SYSTEM FAILED:

1. Significant Items Lost . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . REVIEW

Approach and Landing:2. Emergency Landing Gear Extension . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . PERFORM

a. Altitude . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . MAINTAIN 20,000 FT OR BELOWb. Airspeed . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .200 KIAS OR BELOWc. LANDING GEAR Handle. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .DOWNd. EMER GEAR Handle . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . PULL FULLY UP


1) LANDING WITH GEAR UP / PARTIALLY EXTENDED (E7.3) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . PERFORM

Procedure Completed


Left Thrust Reverser Outboard Roll Spoilers and Speedbrake and Outboard Ground Spoilers

Inboard Brakes or Inboard Ground Spoilers may be lost.



Brake Energy Increase by 6.9 MFP


Right Thrust Reverser Midboard Roll Spoilers, Speedbrake and Midboard Ground Spoilers

Outboard Brakes may be lost.

Normal Landing Gear System Nosewheel Steering




A8-5 P/N 401-590001-0078




1) Landing Considerations:a) Switching AUX PUMP on after landing can recharge right accumulator provided there is no Cyan “R Hyd Fluid

Low” CAS MSG.b) Select wide runway with minimum crosswind, no tailwind.c) Select FLAP WARN.d) Directional Control. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . USE RUDDER AND DIFFERENTIAL BRAKING

NOTEDifferential braking with only one pair of brakes operational is not adequate for taxi and maneuvering.

e) Nosewheel Steering is inoperative even though the Amber “Nosewheel Steer Fail” CAS MSG is not posted.2) Landing Airspeed, Landing Distance and Brake Energy . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .SEE TABLE



Procedure Completed

LEFT AND RIGHT HYDRAULIC SYSTEMS FAILED:


2. EMER RUD . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON

Approach and Landing:3. Emergency Landing Gear Extension . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .PERFORM

a. FLAPS. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . UP / 0°

b. Altitude . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . MAINTAIN 20,000 FT OR BELOWc. Airspeed . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 150 - 180 KIAS d. LANDING GEAR Handle . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . DOWN





Left and Right Thrust Reversers Outboard and Midboard Roll Spoilers and Speedbrake, Outboard and Midboard Ground Spoilers

Normal Rudder function

Normal Landing Gear System Nosewheel Steering EMER GEN

DOOR




NOTE• Yawing airplane up to 1/2 triangle deflection may assist the Main Gear to lock down.

• A yellow “X” on the Rudder may be seen briefly on the flight controls synoptic when yawing theairplane. Rudder function is not degraded.

e. EMER GEAR Handle . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . PULL FULLY UP


1) LANDING WITH GEAR UP / PARTIALLY EXTENDED (E7.3) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . PERFORM

Procedure Completed


1) FLAPS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .20°



2) Landing Considerations:a) Switching AUX PUMP on after landing can recharge right accumulator provided there is no Cyan “R Hyd Fluid

Low” CAS MSG.b) Select wide runway with crosswind not exceeding 10 KT, no tailwind.c) Select FLAP WARN.d) Nosewheel Steering is inoperative even though the Amber “Nosewheel Steer Fail” CAS MSG is not posted. e) Use Rudder for directional control.f) Inboard Ground Spoilers are available.

g) Apply steady maximum continuous braking. Hydraulic pressure for braking is provided by accumulator only.

Accumulator pressures may not be sufficient to provide adequate braking for taxi maneuvering.

h) After airplane has come to a complete stop, shut down engines and chock wheels.3) Landing Airspeed, Landing Distance and Brake Energy . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .SEE TABLE



4) After Landing:a) NORMAL PROCEDURES - SHUT DOWN and SECURING . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . PERFORM

Procedure Completed




DOOR




A8-7 P/N 401-590001-0078

A8.3 HYDRAULIC OVERHEAT

1. HYDRAULIC PUMP (affected side). . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF2. Hyd Synoptic . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .MONITOR TEMP

IF TEMPERATURE DOES NOT REDUCE BELOW 110° C (230° F) OR CAS MSG REMAINS POSTED (NO HYD SYNOPTIC):

NOTEReducing engine thrust on affected side or descending to a lower altitude can help to reduce hydraulictemperature.


IF TEMPERATURE REACHES 135° C (275° F) OR CAS MSG IS STILL POSTED AFTER 30 MINUTES (NO HYD SYNOPTIC):

1) INFLIGHT ENGINE SHUT DOWN (E2.4) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .PERFORM

Procedure Completed

IF TEMPERATURE STAYS BELOW 135° C (275° F) OR AMBER “# Hyd Overheat” CAS MSG CLEARED WITHIN 30 MINUTES (NO HYD SYNOPTIC):

Procedure Completed

IF TEMPERATURE REDUCES BELOW 110° C (230° F) OR AMBER “# Hyd Overheat” CAS MSG IS CLEARED (NO HYD SYNOPTIC):

Procedure Completed

L Hyd OverheatOr

R Hyd Overheat

# Hyd Overheat

# Hyd Overheat




A8.4 EMERGENCY RUDDER SYSTEM OVERHEAT 1. EMER RUD (if not immediately required for safe flight). . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF

IF AUX PUMP IS NOT AVAILABLE:

a. EMER RUD . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .ON (FOR LANDING)

Procedure Completed

IF AUX PUMP IS AVAILABLE:

NOTEThe AUX PUMP will engage when EMER RUD is OFF, provided Cyan “R Hyd Fluid Low” CAS MSG isnot posted.

a. AUX PUMP . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .ON

Procedure Completed

Emer Rudder Sys Ovht




A9-1 P/N 401-590001-0078



FLIGHT CONTROLS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A9-3A9.1 FLAP FAILURE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A9-3A9.2 FLAP LEVER DISAGREE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A9-4A9.3 SPOILER FAIL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A9-4A9.4 GROUND SPOILER FAIL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A9-6A9.5 PITCH CONTROL DISCONNECT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A9-7A9.6 ROLL CONTROL DISCONNECT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A9-8A9.7 PUSHER FAIL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A9-8A9.8 L-R SHAKER FAIL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A9-9A9.9 RUDDER FAIL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A9-9A9.10 SPEEDBRAKE EXTENDED . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A9-10A9.11 STABILIZER TRIM FAILURE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A9-10A9.12 TAKEOFF CONFIGURATION FAIL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A9-11A9.13 ELEVATOR CONTROL LIMIT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A9-11A9.14 AILERON TRIM RUNAWAY . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A9-11A9.15 RUDDER TRIM RUNAWAY . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A9-12A9.16 PITCH TRIM RUNAWAY . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A9-12A9.17 STABILIZER JAM . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A9-13A9.18 MAINTENANCE SWITCH ON . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A9-14A9.19 RIGGING FAILED . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A9-14A9.20 RIGGING IN PROGRESS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A9-14




A9-2




A9-3 P/N 401-590001-0078

FLIGHT CONTROLS

A9.1 FLAP FAILURE

INCLUDING FLAP ASYMMETRY

NOTEFlaps will not move. Additional effects may be:

• Loss of flap position indication.• Flap asymmetry up to 5°.• Reduced Speedbrake and roll effectiveness (spoiler gearing low).• Shaker and Pusher are unavailable.

1. FLAPS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . POSITION NOTED2. Airspeed and Altitude. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OBSERVE FLAP LIMITATION3. FLAP Lever . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . MATCH TO FLAP POSITION / CONFIRM IN DETENT

NOTEIn case of flap asymmetry, up to 50% yoke deflection may be possible.

IF CAS MSG DOES NOT CLEAR AND YOKE DEFLECTED:

a. L-R SHAKER FAIL (A9.8) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . REVIEW, AS REQUIREDb. FUEL. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CALCULATE RANGE WITH FLAPS IN CURRENT POSITIONc. REDUCED FLAP APPROACH AND LANDING (A1.1) . . . . . . . . . . . . . . . . . . . . . . . . . . PERFORM, AS REQUIRED

Procedure Completed

IF CAS MSG DOES NOT CLEAR AND YOKE CENTERED:

a. Flap ECU and Control CBs. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CYCLE OUT / IN (A)

FOOT NOTE:

(A) MCDU / CB / ELEC MENU / CB BY SYSTEM / FLT CTRL / FLAP CONTROL & FLAP ECU


1) L-R SHAKER FAIL (A9.8) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . REVIEW, AS REQUIRED2) FUEL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CALCULATE RANGE WITH FLAPS IN CURRENT POSITION3) REDUCED FLAP APPROACH AND LANDING (A1.1) . . . . . . . . . . . . . . . . . . . . . . . PERFORM, AS REQUIRED

Procedure Completed

IF AMBER “Flap Fail” CAS MSG IS CLEARED:

Procedure Completed

IF AMBER “Flap Fail” CAS MSG IS CLEARED:

Procedure Completed

Flap Fail

Flap Fail

Flap Fail

Flap Fail




A9.2 FLAP LEVER DISAGREE

NOTE CAS MSG will post after 25 seconds if not corrected. In this case perform FLAP FAILURE

(A9.1).

1. FLAP Lever . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CONFIRM IN DETENT

Procedure Completed

A9.3 SPOILER FAIL

IN FLIGHT

NOTE• Spoiler panels shown with amber dashes on the Flt Ctl Synoptic should be assumed inoperative.

• Spoiler panels may not operate properly even if shown in green on the Flt Ctl Synoptic.

1. Flt Ctl Synoptic . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OBSERVE SPOILER PANELS2. SPEEDBRAKE. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .EXTEND / RETRACT TO OBSERVE SPOILER MOVEMENT

a. If the Midboard spoiler panels do not extend to any angle on the Flt Ctl Synoptic, one or both of the panels may beinoperative. Assume the Midboard Spoilers are inoperative for landing.

b. If the Outboard spoiler panels do not extend to any angle on the Flt Ctl Synoptic, one or both of the panels may beinoperative. Assume the Outboard and Inboard Spoilers are inoperative for landing.

c. If none of the spoiler panels extend to any angle on the Flt Ctl Synoptic, assume the Outboard, Midboard and InboardSpoilers are inoperative for landing.

NOTE• Aileron forces will be significantly higher at airspeeds greater than 300 KIAS.

• AP may be used, if available.

• Do not extend flaps beyond 20°.

• In the event of separation of a mechanical linkage, a free-floating panel will rise abruptly resulting in aroll upset during flap transition from 20° to 35°. The free-floating panel will stow abruptly during thetransition from FLAPS 35° to FLAPS 20°.

3. Landing Considerations with one or more spoiler panels inoperative:a. Select runway with minimum crosswind, no tailwind.b. Select FLAP WARN.c. Landing Configuration - FLAPS 20° (if flaps operative).d. Speedbrake and roll power will be reduced.e. A sudden roll asymmetry may occur upon ground spoiler deployment.

4. Landing Airspeed, Landing Distance and Brake Energy . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . SEE TABLESa. Verify corrected brake energy does not exceed brake failure value stated in the applicable Caution which follows.

Flap Lever Disagree

Flap Fail

Spoiler Fail




A9-5 P/N 401-590001-0078




FOOT NOTE:

(A) Landing weight not to exceed 38,750 LB (17,577 KG).

Procedure Completed



Procedure Completed

Flap Position 0° 12° 20°Landing Speed (KIAS) VREF + 25 VREF + 15 VREF + 10

Midboard Spoilers Inop

Landing Distance Multiply by 2.5 Multiply by 2.1 Multiply by 2.1

Brake Energy Increase by 12.8 MFP Increase by 9.9 MFP Increase by 7.0 MFP

Outboard and Inboard

Spoilers Inop



Outboard, Midboard and

Inboard Spoilers Inop

Landing Distance Multiply by 3.9 (A) Multiply by 3.1 Multiply by 3.1

Brake Energy Increase by 15.0 MFP (A) Increase by 12.2 MFP Increase by 9.8 MFP

Flap Position 0° 12° 20°Landing Speed (KIAS) VREF + 25 VREF + 15 VREF + 10

Midboard Spoilers Inop



Outboard and Inboard

Spoilers Inop



Outboard, Midboard and

Inboard Spoilers Inop



Brake Degrade




ON GROUND (BOTH ENGINES RUNNING)A complete power down with batteries OFF and subsequent restoring of normal electrical power may clear the Amber “SpoilerFail” CAS MSG.


1. No Dispatch.

Procedure Completed

IF AMBER “Spoiler Fail” CAS MSG IS CLEARED:

1. Normal Dispatch.

Procedure Completed

A9.4 GROUND SPOILER FAIL

IN FLIGHT

1. and CAS MSGs, if posted (A9.3) . . . . . . . . . . . . . . . . . . . . . . . . . PERFORM

2. Landing Considerations:a. Select runway with minimum crosswind, no tailwind.b. A sudden roll asymmetry may occur upon ground spoiler deployment.c. Expect increased sensitivity in roll control after touchdown.

3. Landing Distance . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .MULTIPLY BY 1.4

Procedure Completed

ON GROUND (BOTH ENGINES RUNNING)A complete power down with batteries OFF and subsequent restoring of normal electrical power may clear the Amber “GroundSpoiler Fail” CAS MSG.


1. No Dispatch.

Procedure Completed

IF AMBER “Ground Spoiler Fail” CAS MSG IS CLEARED:

1. Normal Dispatch.

Procedure Completed

Spoiler Fail

Ground Spoiler Fail

Ground Spoiler Fail Spoiler Fail

Ground Spoiler Fail




A9-7 P/N 401-590001-0078

A9.5 PITCH CONTROL DISCONNECT Indicates the connection between left and right pitch control circuits is open. Each column is connected to one elevator.

1. Pitch control . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .DETERMINE MOST EFFECTIVE COLUMN2. Flight Control and Thrust . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . FLY FROM PREFERRED SIDE

NOTEThe Stick Pusher is inoperative. The Amber “Pusher 1-2 Fail” CAS MSG will not post until the PusherAOA is reached.

3. Maximum Bank Angle . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . AVOID ABOVE 35°

4. Minimum Airspeed (above 20,000 FT) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 180 KIAS5. Minimum Airspeed (at or below 20,000 FT). . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .SEE TABLE


6. AP will disengage, do not re-engage.7. Landing Considerations:

a. Select runway with minimum crosswind, no tailwind.b. Normal (Primary) Pitch Trim is still available.c. Expect larger column movement and lighter forces.d. Expect some roll due to pitch inputs.e. Stick pusher is inoperative after a Pitch Control Disconnect (Amber “Pusher 1-2 Fail” CAS MSG not posted).

NOTEPitch Disconnect cannot be reconnected in flight by closing PITCH DISC switch. The pitch control circuitscan only be reconnected on the ground by maintenance personnel.

8. Landing Airspeed and Landing Distance . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .SEE TABLE

Procedure Completed

Flap Position 0° 12° 20° 35°MIN SPEED (KIAS) VREF + 25 VREF + 15 VREF + 10 VREF + 5



Pitch Disconnect




A9.6 ROLL CONTROL DISCONNECT Indicates the connection between left and right roll control circuits is open. Each yoke is connected to one aileron.

1. Roll Control . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . DETERMINE MOST EFFECTIVE YOKE2. Flight Control and Thrust . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . FLY FROM PREFERRED SIDE3. Side in Control . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CONFIRM4. ROLL SPOILER CONTROL. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . SELECT TO SIDE IN CONTROL5. Aileron Trim . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CONTINUE USE, AS REQUIRED6. AP will disengage, do not re-engage.


7. Landing Considerations:a. Select runway with minimum crosswind.b. Expect reduced aileron effectiveness and lighter aileron forces.c. Yokes may be displaced from center in wings level flight.

NOTERoll Disconnect cannot be reconnected in flight by closing ROLL DISC switch. The roll control circuitscan only be reconnected on the ground by maintenance personnel.

8. Landing FLAPS and Airspeed . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 20° / VREF + 10 KIAS9. REDUCED FLAP APPROACH AND LANDING (A1.1) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . PERFORM

Procedure Completed

A9.7 PUSHER FAIL

Do not perform intentional stalls.


2. Minimum Airspeed (above 20,000 FT). . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 180 KIAS3. Minimum Airspeed (at or below 20,000 FT) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .SEE TABLE

NOTELSA cue including A/T amber band and normalized AOA Displays may be inoperative on one or bothPFDs.

Procedure Completed

Flap Position 0° 12° 20° 35°MIN SPEED (KIAS) VREF + 25 VREF + 15 VREF + 10 VREF

Roll Disconnect

Pusher 1-2 Fail




A9-9 P/N 401-590001-0078

A9.8 L-R SHAKER FAIL

Do not perform intentional stalls.

NOTEDo not use AP and A/T below 160 KIAS.


2. Minimum Airspeed (above 20,000 FT) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 180 KIAS3. Minimum Airspeed (at or below 20,000 FT). . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .SEE TABLE

NOTELSA cue including A/T amber band and normalized AOA Displays may be inoperative on one or bothPFDs.

Procedure Completed

A9.9 RUDDER FAIL

NOTE• Rudder and YD are inoperative.

• CAS MSG will post.

DURING TAKEOFF (BELOW V1)1. REJECTED TAKEOFF (E1.1). . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .PERFORM

Procedure Completed

IN FLIGHT

NOTE• Rudder trim is ineffective.

• AP will disengage.


1. Flight Control and Thrust . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . FLY MANUALLY2. Dutch Roll . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .SUPPRESS WITH LATERAL CONTROL INPUT, AS REQUIRED3. Altitude. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 35,000 FT OR BELOW4. AP . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . MAY BE RE-ENGAGED

NOTEA persistent slip / skid indicator displacement indicates a jammed rudder.

5. Slip / Skid Indication . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ASSESS

Flap Position 0° 12° 20° 35°MIN SPEED (KIAS) VREF + 25 VREF + 15 VREF + 10 VREF

L-R Shaker Fail

Rudder Fail

Yaw Damper 1-2 Fail




IF RUDDER FAILED IN OFFSET POSITION:

a. JAMMED RUDDER CONTROL (E9.3) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . PERFORM

Procedure Completed

IF RUDDER FAILED IN NEUTRAL POSITION:

a. Land . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .AS SOON AS PRACTICALb. Landing Considerations

1) Select runway with minimum crosswind, no tailwind.2) Use differential braking for initial directional control. Add Nosewheel Steering below 80 KIAS.

c. Landing FLAPS and Airspeed. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 20° / VREF + 10 KIASd. REDUCED FLAP APPROACH AND LANDING (A1.1) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . PERFORM

Procedure Completed

A9.10 SPEEDBRAKE EXTENDED Speedbrake extended when below 600 FT AGL or FLAPS >23° or N1 >70%:

1. SPEEDBRAKE. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . RETRACT

Procedure Completed

A9.11 STABILIZER TRIM FAILURE Stabilizer Trim indication shows amber dashes and the pointer is removed from the Pitch Trim scale.

NOTE• AP will disengage.


• If a missed approach is required, do not reconfigure unless performance is critical.

• Maintain the speed at Go Around to minimize trim.

• Use thrust as required to ensure a safe climbout while avoiding a large speed increase.

1. STABILIZER TRIM SELECT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .STBY

IF STBY TRIM INOPERATIVE:

a. STABILIZER JAM (A9.17) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . PERFORM

Procedure Completed

IF STBY TRIM OPERATIVE:

NOTE• Stby Pitch Trim rate is slow and fixed. It does not vary above and below 0.5M like the Normal Pitch Trim

rate.

• AP, Mach Trim and Flap Trim compensation will be inoperative.

• The standby stabilizer trim limits differ from the Amber NU and Amber ND limit markings.

a. Flight Control and Thrust. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . FLY MANUALLYb. Airspeed . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . BELOW 0.78M / 300 KIASc. Approach. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .SET GEAR / FLAPS EARLYd. VREF . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . STABILIZE AND TRIM BY 1000 FT AGL

Procedure Completed

Speedbrake Extended

Stab Trim Fail




A9-11 P/N 401-590001-0078

A9.12 TAKEOFF CONFIGURATION FAIL

NOTETake-off Configuration Warning system may be inoperative.

Ground Only CAS MSG.1. REJECTED TAKEOFF (E1.1). . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .PERFORM2. No Dispatch.

Procedure Completed

A9.13 ELEVATOR CONTROL LIMIT Indicates possible elevator cable failure resulting in elevator asymmetry and an extreme forward column position.

1. Flight Control and Thrust . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . FLY MANUALLY

NOTE• Pitch control may be compromised by restricted forward column movement.

• Applying Nose Down Trim causes progressive out of trim pull force. Select a Stabilizer Trim positionthat results in mid range column position with a comfortable force.

2. Stabilizer Trim . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . TRIM NOSE DOWN, AS REQUIRED

NOTEPitch control inputs will be accompanied by small roll effects.

3. Control Column . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . MOVE AFT TO CONTROL PITCH4. Landing FLAPS and Airspeed . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . UP / 0°, VREF + 25 KIAS5. REDUCED FLAP APPROACH AND LANDING (A1.1) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .PERFORM

Procedure Completed

A9.14 AILERON TRIM RUNAWAY

NOTE• Increasing uncommanded roll force, possibly accompanied by CAS MSG and if

AP is engaged, CAS MSG may post. Verify no asymmetric thrust conditionexists and Rudder Trim is approximately neutral.


1. AP . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . DISENGAGE WHILE HOLDING YOKE FIRMLY, DO NOT RE-ENGAGE2. AILERON TRIM POWER. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF3. Rudder . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . APPLY TO RELIEVE AILERON FORCE4. Rudder Trim. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .SET, AS REQUIRED5. Airspeed. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .REDUCE TO RELIEVE AILERON FORCE

T / O Config Fail

Elevator Control Limit

Aileron Trim Fail

AP Roll Mistrim




• The CAS MSG and the indication on PFD may post during prolongeduncoordinated flight. In this case relieve rudder and reduce side slip to establish coordinated flight.Stay in coordinated flight for approximately 2 minutes after the Amber “# Fuel Qty Low” CAS MSG andthe Amber “Low Fuel” indication on PFD has cleared.

• Do Not CROSSFEED or perform FUEL IMBALANCE (A11.3) in uncoordinated flight while the

CAS MSG is posted. In order to correct fuel imbalance caused by prolongeduncoordinated flight, occasionally relieve rudder and reduce side slip.

6. Land . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .AS SOON AS PRACTICAL7. Landing Considerations:

a. Select runway with minimum crosswind.b. Select Rudder Trim to neutral before landing.

Procedure Completed

A9.15 RUDDER TRIM RUNAWAY Increasing uncommanded yaw and roll and rudder pedal movement.


1. AP . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . DISENGAGE WHILE HOLDING YOKE FIRMLY, DO NOT RE-ENGAGE2. RUDDER TRIM POWER . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF3. Rudder Force . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . APPLY TO MINIMIZE YAW4. A/T . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . DISCONNECT5. Asymmetric Thrust . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . SET, AS REQUIRED TO REDUCE YAW6. Bank . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ADJUST TO CONTROL HEADING7. Aileron Trim . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . SET AS REQUIRED8. Airspeed. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . AS REQUIRED9. Land . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .AS SOON AS PRACTICAL

10. Landing Considerations:a. Select runway with minimum crosswind.b. Remove Asymmetric Thrust before landing.c. Set Aileron Trim to neutral before landing.d. Rudder remains fully responsive to pedal inputs.e. Up to 45 LB (20 KG) may be required to center pedals.f. Up to 125 LB (57 KG) may be required for full opposing rudder.

g. Airspeed reduction will not significantly affect lateral acceleration (side force) or bank angle required for straight flight.

Procedure Completed

A9.16 PITCH TRIM RUNAWAY 1. AP TRIM PUSHER. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .PUSH AND HOLD2. STABILIZER TRIM SELECT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .STBY3. AP TRIM PUSHER. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . RELEASE4. STABILIZER TRIM FAILURE (A9.11). . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . PERFORM

Procedure Completed

# Fuel Qty Low Low Fuel

# Fuel Qty Low




A9-13 P/N 401-590001-0078

A9.17 STABILIZER JAM Complete checklists are included for BEFORE LANDING through LANDING.

NOTE• Mach Trim and Flap Trim will be inoperative.

• Pilot not flying may assist with Thrust Levers, Speedbrake Lever and with column forces.

• Use of A/T is recommended.

1. “JAMMED STABILIZER TRIM” . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ALERT CREW


2. AP . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .CONFIRM DISENGAGED3. Airspeed. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . MAINTAIN (OR ADJUST TO REDUCE FORCES)4. SPEEDBRAKE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . AS REQUIRED5. Land. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . AS SOON AS PRACTICAL

IF JAM OCCURS AT FLAPS 0°, 12° OR 20°:

a. Landing Considerations:1) Airspeed. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . REDUCE TO 230 KIAS AT APPROXIMATELY 15 NM OUT2) SPEEDBRAKE. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . AS REQUIRED3) LANDING GEAR Handle . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . DOWN AT APPROXIMATELY 10 NM OUT4) FLAPS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 20° AT APPROXIMATELY 5 NM OUT

b. Landing FLAPS and Airspeed. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .20° / VREF + 10 KIASc. REDUCED FLAP APPROACH AND LANDING (A1.1) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .PERFORM

Procedure Completed

IF JAM OCCURS AT FLAPS 35°:

a. FLAPS. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .MAINTAIN 35°

b. Landing Airspeed . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . VREF

BEFORE LANDINGa. LANDING GEAR Handle . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . DOWN / THREE GREENb. SPEEDBRAKE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .CONFIRM RETRACTEDc. FLAPS. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CONFIRM 35°

d. EXTERNAL LIGHTS. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . AS REQUIREDe. A/T . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . DISCONNECT AT 100 FT OR ABOVE




GO AROUNDNOTE

The FD pitch command should only be used as initial guidance. Pitch adjustments may be required inorder to maintain VREF.

a. TO / GA . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . SELECT

NOTEIf A/T is engaged, thrust application may not be as rapid as desired. If this occurs, disconnect A/T andadvance Thrust Levers manually.

b. Thrust Levers . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . FORWARD STOP (VERIFY TAKE-OFF N1)c. FLAPS. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .MAINTAIN 35°

d. LANDING GEAR Handle . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . LEAVE DOWNe. Climb Airspeed (minimum) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . VREF

f. Anti-ice / De-ice . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . AS REQUIRED

LANDINGa. Airspeed . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . VREF

b. Thrust Levers . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . IDLEc. Brakes (after touchdown) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .APPLYd. SPEEDBRAKE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . EXTENDe. Thrust Reversers (after Nosewheel is on ground). . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . DEPLOY, AS DESIREDf. Reverse Thrust (when deployment confirmed) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . AS REQUIRED

g. Nosewheel Steering (all gear firmly on ground) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . AS REQUIREDh. Reverse Thrust . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . IDLE BY 60 KIASi. Thrust Reversers. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . STOW BY TAXI SPEED

Procedure Completed

A9.18 MAINTENANCE SWITCH ON Ground Only maintenance CAS MSG.

Maintenance switch for ground rigging is not in the OFF position.

Airplane systems may be in calibrating mode.1. No Dispatch.

Procedure Completed

A9.19 RIGGING FAILED Ground Only maintenance CAS MSG.

The rigging process has failed. Maintenance action has not been completed.

System accuracy and operation is undetermined.1. No Dispatch.

Procedure Completed

A9.20 RIGGING IN PROGRESS Ground Only maintenance CAS MSG.

Rigging in progress and not complete. 1. No Dispatch.

Procedure Completed

Maintenance Switch On

Rigging Failed

Rigging In Progress




A10-1 P/N 401-590001-0078



AUTOFLIGHT. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A10-3A10.1 AUTOPILOT PITCH MISTRIM . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A10-3A10.2 AUTOPILOT ROLL MISTRIM . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A10-3A10.3 AUTOPILOT STABILIZER TRIM FAIL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A10-4A10.4 AUTOPILOT MODES OFF . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A10-4A10.5 MACH TRIM FAIL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A10-5A10.6 AFCS FAIL - IRS DATA MISCOMPARE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A10-5A10.7 AFCS FAIL - ADC DATA MISCOMPARE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A10-6A10.8 YAW DAMPER OFF . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A10-6A10.9 YAW DAMPER 1-2 FAIL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A10-7A10.10 AUTOTHROTTLE DISC AND AUTOTHROTTLE 1 OR 2 FAIL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A10-7A10.11 AUTOTHROTTLE DISC AND AUTOTHROTTLE 1-2 FAIL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A10-8A10.12 AUTOTHROTTLE 1 OR 2 FAIL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A10-8A10.13 AUTOTHROTTLE 1-2 FAIL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A10-9A10.14 NO A/T HOLD MODE DURING AUTOTHROTTLE ON TAKEOFF . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A10-9




A10-2




A10-3 P/N 401-590001-0078

AUTOFLIGHT

A10.1 AUTOPILOT PITCH MISTRIM

NOTEThe out of trim force at the time of autopilot disengagement can be as high as 30 LB (14 KG).

1. Yoke. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . HOLD FIRMLY2. AP . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . DISENGAGE

IF PRIMARY STAB TRIM IS NOT AVAILABLE:

a. STABILIZER TRIM FAILURE (A9.11) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .PERFORM

Procedure Completed

IF PRIMARY STAB TRIM IS AVAILABLE:

a. Pitch Trim . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ADJUST, AS REQUIRED

NOTE• Autopilot pitch mistrim is only monitored when AP is engaged. Should CAS MSG

return when AP is re-engaged, do not use AP.


b. AP . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . MAY BE RE-ENGAGED

Procedure Completed

A10.2 AUTOPILOT ROLL MISTRIM

NOTEThe out of trim force at the time of autopilot disengagement can be as high as 20 LB (9 KG).

1. Yoke. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . HOLD FIRMLY2. AP . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . DISENGAGE3. Roll Trim . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ADJUST, AS REQUIRED

NOTE• Autopilot roll mistrim is only monitored when AP is engaged. Should CAS MSG

return when AP is re-engaged, do not use AP.


4. AP . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . MAY BE RE-ENGAGED

Procedure Completed

AP Pitch Mistrim

AP Pitch Mistrim

AP Roll Mistrim

AP Roll Mistrim




A10.3 AUTOPILOT STABILIZER TRIM FAIL 1. Flight Control . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . FLY MANUALLY

NOTE• Primary Stab Trim, Flap Trim and Mach Trim may also be failed with separate annunciations. Standby

Trim is available. AP will disconnect.


2. Airspeed (if Mach Trim Failed) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . BELOW 0.78M / 300 KIAS

IF PRIMARY STAB TRIM IS NOT AVAILABLE:

a. STABILIZER TRIM FAILURE (A9.11) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . PERFORM

Procedure Completed

IF PRIMARY STAB TRIM IS AVAILABLE:

Procedure Completed

A10.4 AUTOPILOT MODES OFF

1. Flight Path . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . MONITOR2. AP and A/T. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK STATUS, SELECT APPROPRIATE MODES

IF UNABLE TO RESELECT APPROPRIATE MODES:

a. AP . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .DISENGAGEb. NAV Source, If Lost. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . TUNE AND COUPLE TO ALTERNATE

c. CAS MSG, if posted (A10.6) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . PERFORM

d. CAS MSG, if posted (A10.7) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . PERFORM


e. AP and A/T . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . RE-ENGAGE IF AVAILABLE

Procedure Completed

IF APPROPRIATE MODES CAN BE SELECTED:

a. AP and A/T . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . MAY BE RE-ENGAGED

Procedure Completed

AP Stab Trim Fail

Lateral Mode OffOr

Vertical Mode Off

AFCS Fail-IRS Miscomp

AFCS Fail-ADC Miscomp




A10-5 P/N 401-590001-0078

A10.5 MACH TRIM FAIL


Procedure Completed

A10.6 AFCS FAIL - IRS DATA MISCOMPARE

NOTECAS MSG will time out after approximately 5 seconds.




NOTECorrect attitude reference may be determined by comparison of Pilot’s / Copilot’s PFDs with the StbyInst.

3. Stby Inst. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . MONITOR ATTITUDE AND HEADING4. Affected IRS. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . DETERMINE

IF AFFECTED IRS CANNOT BE DETERMINED:

NOTEStall protection system will not compensate for high entry rate stalls.

a. Dutch Roll . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .SUPPRESS WITH LATERAL CONTROL INPUT, AS REQUIREDb. Altitude . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 35,000 FT OR BELOWc. Land . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . NEAREST SUITABLE AIRPORTd. Landing Flaps and Airspeed . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .20° / VREF + 10 KIASe. REDUCED FLAP APPROACH AND LANDING (A1.1) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .PERFORM

Procedure Completed

IF AFFECTED IRS IS DETERMINED:

a. PFD ATT REF (affected side) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .SELECT

NOTEStall protection system will not compensate for high entry rate stalls.

b. Dutch Roll . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .SUPPRESS WITH LATERAL CONTROL INPUT, AS REQUIREDc. Altitude . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 35,000 FT OR BELOWd. Land . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . NEAREST SUITABLE AIRPORTe. Landing Flaps and Airspeed . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .20° / VREF + 10 KIASf. REDUCED FLAP APPROACH AND LANDING (A1.1) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .PERFORM

Procedure Completed


AP YD Autothrottle

Cat 2 Capability

Mach Trim 1-2 Fail

AFCS Fail-IRS Miscomp




A10.7 AFCS FAIL - ADC DATA MISCOMPARE 1. Significant Items Lost . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . REVIEW



NOTECorrect speed reference may be determined by comparison of the Pilot’s / Copilot’s PFDs with the StbyInst.

3. Stby Inst . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . MONITOR SPEED AND ALTITUDE4. Affected ADC . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . DETERMINE

IF AFFECTED ADC CANNOT BE DETERMINED:

a. Airspeed . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . BELOW 0.78M / 300 KIASb. L-R SHAKER FAIL (A9.8) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . REVIEW, AS REQUIREDc. Land . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .AS SOON AS PRACTICAL

Procedure Completed

IF AFFECTED ADC CAN BE DETERMINED:

a. PFD AIR DATA (affected side) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . SELECTb. Amber ADC 1 or ADC 2 displayed on both PFDs . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CONFIRMc. Airspeed . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . BELOW 0.78M / 300 KIASd. L-R SHAKER FAIL (A9.8) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . REVIEW, AS REQUIREDe. Land . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .AS SOON AS PRACTICAL

Procedure Completed

A10.8 YAW DAMPER OFF 1. YD . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .ON

Procedure Completed


AP Autothrottle Mach Trim Flap Trim

Pusher Cat 2 Capability Left and Right Shaker

AFCS Fail-ADC Miscomp

Yaw Damper Off




A10-7 P/N 401-590001-0078

A10.9 YAW DAMPER 1-2 FAIL

NOTE• Apply appropriate RVSM contingency procedures.

• CAT 2 capability is lost.

• Deploying Speedbrake will increase stability with the Yaw Damper failed.

1. AP . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . DISENGAGE2. Flight Control and Thrust . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . FLY MANUALLY3. Dutch Roll . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .SUPPRESS WITH LATERAL CONTROL INPUT, AS REQUIRED4. Altitude. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 35,000 FT OR BELOW5. FLAPS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .20° OR LESS6. AP . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . MAY BE RE-ENGAGED7. Landing FLAPS and Airspeed . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .20° / VREF + 10 KIAS8. REDUCED FLAP APPROACH AND LANDING (A1.1) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .PERFORM

Procedure Completed

A10.10 AUTOTHROTTLE DISC AND AUTOTHROTTLE 1 OR 2 FAIL

Single A/T channel fail.1. Thrust. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . FLY MANUALLY2. A/T DISC . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . DEPRESS TO CLEAR AMBER “Autothrottle Disc” CAS MSG3. A/T . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . SELECT OPERATING CHANNEL (A)4. A/T . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . MAY BE RE-ENGAGED

FOOT NOTE:

(A) MCDU / MENU / DISP SETUP / AT 1 or AT 2

Procedure Completed

Yaw Damper 1-2 Fail

Autothrottle DiscAnd

Autothrottle 1 FailOr

Autothrottle 2 Fail




A10.11 AUTOTHROTTLE DISC AND AUTOTHROTTLE 1-2 FAIL

Dual A/T channel failure or manual override.1. Thrust . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . FLY MANUALLY2. A/T DISC . . . . . . . . DEPRESS TO CLEAR AMBER “Autothrottle Disc” AND AMBER “Autothrottle 1-2 Fail” CAS MSGS

IF CAS MSG IS STILL POSTED (DUAL CHANNEL FAILURE):

a. Use manual thrust.

Procedure Completed

IF AMBER “Autothrottle 1-2 Fail” CAS MSG IS CLEARED (MANUAL OVERRIDE):

a. A/T. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . MAY BE RE-ENGAGED

Procedure Completed

A10.12 AUTOTHROTTLE 1 OR 2 FAIL

Single A/T Channel Failure.

1. A/T . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . SELECT OPERATING CHANNEL (A)2. A/T . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . MAY BE RE-ENGAGED

FOOT NOTE:

(A) MCDU / MENU / DISP SETUP / AT 1 or AT 2

Procedure Completed

Autothrottle DiscAnd

Autothrottle 1-2 Fail


Autothrottle 1 FailOr

Autothrottle 2 Fail




A10-9 P/N 401-590001-0078

A10.13 AUTOTHROTTLE 1-2 FAIL Dual A/T channel failure.

IN FLIGHT1. Use manual thrust.

Procedure Completed

ON GROUND (BEFORE OR AFTER ENGINE START)1. Power down airplane completely (batteries off) before restoring normal electric power.



Procedure Completed

IF AMBER “Autothrottle 1-2 Fail” CAS MSG IS CLEARED:

a. Normal Dispatch.

Procedure Completed

A10.14 NO A/T HOLD MODE DURING AUTOTHROTTLE ON TAKEOFF1. Thrust Levers. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .GUARD TO PREVENT REDUCTION BELOW 400 FT AGL2. A/T . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CONFIRM OPERATION (ABOVE 400 FT)

Procedure Completed



HOLD




A11-1 P/N 401-590001-0078



FUEL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A11-3A11.1 BOOST PUMP FAIL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A11-3A11.2 FUEL FILTER BYPASS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A11-4A11.3 FUEL IMBALANCE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A11-4A11.4 FUEL TEMPERATURE LOW . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A11-5A11.5 FUEL PRESSURE LOW . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A11-6A11.6 FUEL QUANTITY LOW OR LOW FUEL ON PFD . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A11-7A11.7 FUEL PRESSURE SWITCH FAIL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A11-8




A11-2




A11-3 P/N 401-590001-0078

FUEL

A11.1 BOOST PUMP FAIL

Low pressure, overheat or UFI trip (if installed).

1. BOOST PUMP (affected side) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF2. CROSSFEED . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF

3. and CAS MSGs (same side), if posted, (A11.5) . . . . . . . . . . . . .PERFORM

IF CAS MSG IS STILL POSTED (OVERHEAT):

a. CAS MSG . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . MONITOR

IF AFTER 10 MINUTES CAS MSG IS STILL POSTED:

1) BOOST PUMP (affected side) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . VERIFY OFF

NOTEFuel transfer may be attempted. It may be required to cycle the fuel transfer switch several times for thefuel transfer system to operate.

2) Fuel Balance . . . . . . . . . . . . . . . . . . . . . . USE DIFFERENTIAL THRUST OR FUEL TRANSFER, AS REQUIRED3) Land . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . AS SOON AS PRACTICAL

Procedure Completed

IF AFTER 10 MINUTES AMBER “# Boost Pump Fail” CAS MSG IS CLEARED:

NOTEThe Boost Pump will operate once the overheat has cleared and the switch is placed in the AUTO or ONposition.

1) BOOST PUMP (affected side) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .AUTO

Procedure Completed

IF AMBER “# Boost Pump Fail” CAS MSG IS CLEARED (LOW PRESSURE OR UFI TRIP (IF INSTALLED)):

a. BOOST PUMP (affected side) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . VERIFY OFF

NOTEFuel transfer may be attempted. It may be required to cycle the fuel transfer switch several times for thefuel transfer system to operate.

b. Fuel Balance. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . USE DIFFERENTIAL THRUST OR TRANSFER, AS REQUIREDc. Land . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . AS SOON AS PRACTICAL

Procedure Completed

L Boost Pump FailOr

R Boost Pump Fail

# Boost Pump Fail # Fuel Press Low

# Boost Pump Fail

# Boost Pump Fail

# Boost Pump Fail




A11.2 FUEL FILTER BYPASS

Any Fuel Filter Bypass could be the result of general fuel contamination and could ultimately affect allengines.

1. TRANSFER . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . VERIFY OFF2. CROSSFEED. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF3. A/T . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . DISCONNECT4. CONT IGNITION (affected engine(s)) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .ON5. Thrust Lever (affected engine(s)). . . . . . . . . . . . . . . . . . . . . . . . . . . . . RETARD SLOWLY, CONDITIONS PERMITTING

IF CAS MSG IS STILL POSTED OR REAPPEARS:

a. Thrust Lever (affected engine(s)) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .AVOID ABRUPT CHANGES(Minimum thrust lever position as

required for safe flight and landing)b. Engine Indications . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . MONITORc. Land . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . NEAREST SUITABLE AIRPORT

Procedure Completed

IF AMBER “# Fuel Filter Bypass” CAS MSG IS CLEARED:

a. Thrust Lever (affected engine(s)) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . AS REQUIREDb. Land . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .AS SOON AS PRACTICAL

Procedure Completed

A11.3 FUEL IMBALANCE 1. Fuel Indication . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . REVIEW2. CROSSFEED. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . SELECT TO LOW QUANTITY SIDE

NOTE• Fuel transfer may be attempted. It may be required to cycle the fuel transfer switch several times for the

fuel transfer system to operate.

• If fuel crossfeed and fuel transfer are inoperative, use differential thrust to balance fuel.

3. TRANSFER . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . SELECT TO LOW QUANTITY SIDE4. Fuel Balance . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . MONITOR

IF FUEL CANNOT BE BALANCED WITHIN 500 LB (227 KG) BEFORE LANDING:

a. Disengage AP.b. Use Lateral Trim, as required.

L Fuel Filter BypassOr

R Fuel Filter BypassOr

L-R Fuel Filter Bypass

# Fuel Filter Bypass

Fuel Imbalance




A11-5 P/N 401-590001-0078

c. Land . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . NEAREST SUITABLE AIRPORT

NOTEMaximum recommended fuel imbalance following this procedure is 2000 LB (907 KG).

d. Landing Considerations:1) Select runway with minimum crosswind.

e. Landing FLAPS and Airspeed. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 20° / VREF + 10f. REDUCED FLAPS APPROACH AND LANDING (A1.1). . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .PERFORM

Procedure Completed

WHEN FUEL QUANTITY IS BALANCED:

a. Amber “Fuel Imbalance” CAS MSG . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . VERIFY CLEAREDb. CROSSFEED . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFFc. TRANSFER. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF

Procedure Completed

A11.4 FUEL TEMPERATURE LOW

IN FLIGHT

NOTE• Decrease altitude or increase airspeed as required to increase TAT to prevent further decrease in fuel

temperature.

• Fuel Synoptic display of fuel temperature will show amber dashes in case of sensor failure or when fuellevel in the left tank is below 3000 LB (1361 KG).

1. PFD TAT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK2. TAT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . INCREASE TO GREATER THAN -40° C3. Fuel . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CALCULATE RANGE

Procedure Completed

ON GROUND

• If Fuel Temperature is below -25° C (-13° F) do not dispatch.

• If Fuel Temperature is below -40° C (-40° F) do not start engines.

• Do not take-off without Fuel information on Fuel Synoptic.

NOTEIt is recommended to load warm fuel or warm up airplane in warm environment.

1. Fuel Synoptic . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK FUEL TEMPERATURE IN LIMITS

Procedure Completed

Fuel Temp Low




A11.5 FUEL PRESSURE LOW

1. Fuel Synoptic . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . MONITOR FOR FUEL SYSTEM STATUS

2. and CAS MSGs (same side), if posted . . . . . . . . . . . . . . . . BOOST PUMP(AFFECTED SIDE), OFF

FOR DURATION OF FLIGHT3. Amber “# Boost Pump Fail” CAS MSG (same side), if not posted. . . . . . . . . . . . BOOST PUMP (AFFECTED SIDE) ON



• Avoid load factors below 1.0 G.

• Engine fuel pump must be replaced before the next flight.

b. Thrust Lever (affected side) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .AVOID ABRUPT CHANGES

NOTEFuel leak is indicated by an increasing split between FMS computed fuel remaining and gaged fuel.

c. Fuel Quantity / Consumption. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .ASSESS FOR LEAKS

IF FUEL LEAK IS DETERMINED:

1) CROSSFEED . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF2) TRANSFER . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .VERIFY OFF3) BOOST PUMP (affected side) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF4) INFLIGHT ENGINE SHUT DOWN (E2.4) (affected engine) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . PERFORM

Procedure Completed

IF NO EVIDENCE OF FUEL LEAK:

1) CROSSFEED . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .SELECT TO AFFECTED SIDE


a) Thrust Lever (affected side). . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .AVOID ABRUPT CHANGESb) CROSSFEED . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFFc) Maximum Altitude . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . AT OR BELOW 26,000 FTd) Fuel . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CALCULATE RANGEe) Land. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . NEAREST SUITABLE AIRPORT

Procedure Completed

L Fuel Press LowOr

R Fuel Press Low

# Fuel Press Low # Boost Pump Fail

# Fuel Press Low

# Fuel Press Low




A11-7 P/N 401-590001-0078

IF AMBER “# Fuel Press Low” CAS MSG IS CLEARED:

a) Fuel Balance . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . MONITOR

NOTE• Fuel transfer may be attempted. It may be required to cycle the fuel transfer switch several times for the

fuel transfer system to operate.

• Fuel transfer should be used to offset the imbalance caused by crossfeeding. If fuel transfer staysinoperative, fuel crossfeed shall be selected OFF if required to maintain fuel balance within 500 LB(227 KG).

b) TRANSFER (if operative) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .SELECT TO LOW QUANTITY SIDEc) Land . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . NEAREST SUITABLE AIRPORT

Procedure Completed

IF AMBER “# Fuel Press Low” CAS MSG IS CLEARED:

a. Land . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . AS SOON AS PRACTICALb. Fuel Balance. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . USE DIFFERENTIAL THRUST OR TRANSFER, AS REQUIRED

Procedure Completed

A11.6 FUEL QUANTITY LOW OR LOW FUEL ON PFD

Indicates less than 760 LB (345 KG) in relevant fuel tank.

If jet pumps are inoperative and or CAS MSG is posted, thelast 400 LB (181 KG) of indicated fuel may not be usable under all flight conditions. Avoid sustained noseup pitch attitude.

1. Fuel Quantity . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . VERIFY2. Fuel Plan . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . REVIEW3. Fuel Balance . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . MONITOR, CROSSFEED AS REQUIRED4. Land. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . AS SOON AS PRACTICAL

Procedure Completed

L Fuel Qty LowOr

R Fuel Qty LowOr

L-R Fuel Qty Low

LOW FUEL

L Boost Pump On R Boost Pump On




A11.7 FUEL PRESSURE SWITCH FAIL

Ground Only CAS MSG.

Indicates false pressure signal when no pressure source is present. Amber “# Fuel Press Sw Fail” CAS MSG not available after

engine start. Boost pump AUTO functions will be inoperative if CAS MSG is posted.


Procedure Completed

L Fuel Press Sw FailOr

R Fuel Press Sw FailOr

L-R Fuel Press Sw Fail

# Fuel Press Sw Fail




A12-1 P/N 401-590001-0078



ICE / RAIN . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A12-3A12.1 EMERGENCY WINDSHIELD HEAT FAIL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A12-3A12.2 ENGINE ANTI-ICE FAIL OFF . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A12-3A12.3 ENGINE ANTI-ICE OVERPRESSURE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A12-4A12.4 ICING . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A12-4A12.5 DUAL ICE DETECTOR FAILURE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A12-5A12.6 PITOT HEAT FAIL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A12-5A12.7 L AND R PITOT HEAT FAIL OR STATIC PORT HEAT FAIL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A12-6A12.8 STANDBY PITOT HEAT FAILURE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A12-6A12.9 TAIL DE-ICE FAIL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A12-7A12.10 WINDSHIELD HEAT FAIL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A12-8A12.11 WINDSHIELD OVERHEAT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A12-8A12.12 WING ANTI-ICE FAIL OFF . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A12-9A12.13 DUAL WING ANTI-ICE FAIL OFF . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A12-9A12.14 WING ANTI-ICE OVERPRESSURE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A12-9A12.15 WING ANTI-ICE FAIL ON . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A12-10A12.16 WING ANTI-ICE TEMPERATURE LOW . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A12-11A12.17 FLIGHT AND LANDING WITH ICE ACCUMULATION ON THE WINGS. . . . . . . . . . . . . . . . . . . . . . . . . . . . A12-12A12.18 INADVERTENT ICING ENCOUNTER . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A12-14




A12-2




A12-3 P/N 401-590001-0078

ICE / RAIN

A12.1 EMERGENCY WINDSHIELD HEAT FAIL

NOTE• The Emergency Section of the Left Windshield has lost its source of power, but the remainder of the

Left Windshield sections may still be receiving heat.

• If reduced visibility occurs on the Pilot’s side, aircraft control may be transferred to the Copilot’s side.

IF THE LEFT SIDE WINDOW AND LEFT WINDSHIELD ARE COLD TO THE TOUCH:

1. Icing Conditions . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . EXIT / AVOID2. L WINDSHIELD HEAT. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF

Procedure Completed

IF THE LEFT SIDE WINDOW AND LEFT WINDSHIELD ARE WARM TO THE TOUCH (EXCEPT EMERGENCYSECTION):

1. L WINDSHIELD HEAT. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .VERIFY AUTO

Procedure Completed

A12.2 ENGINE ANTI-ICE FAIL OFF

1. ENGINE ANTI-ICE (affected engine(s)) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CYCLE OFF, THEN ON


a. Icing Conditions . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . EXIT / AVOIDb. CONT IGNITION (affected engine(s)). . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ONc. ENGINE ANTI-ICE (affected engine(s)) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF

Procedure Completed

IF AMBER “# Eng A-Ice Fail Off” CAS MSG IS CLEARED:

Procedure Completed

Emer Wshld Heat Fail

L Eng A-Ice Fail OffOr

R Eng A-Ice Fail OffOr

L-R Eng A-Ice Fail Off

# Eng A-Ice Fail Off




A12.3 ENGINE ANTI-ICE OVERPRESSURE

IN FLIGHT1. Thrust Lever (affected engine) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . MAINTAIN BELOW 80% N1

2. Icing Conditions . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . EXIT / AVOID

After Clear of Icing:3. ENGINE ANTI-ICE (affected engine) . . . . . . . . . . . . . . . . . . . OFF (AMBER “# Eng A-Ice Ovpress” CAS MSG CLEARS)4. Thrust Lever (affected engine) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . AS REQUIRED

Procedure Completed

ON GROUND1. Thrust Lever (affected engine) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . MAINTAIN BELOW 80% N1


Procedure Completed

A12.4 ICING

NOTEThe Amber CAS MSG and Amber indication on the PFD will post if ice detected withEngine Anti-ice, Wing Anti-ice, Tail De-ice or Windshield Heat selected OFF or failed.

IN FLIGHT

IF , , , OR CAS MSG IS ALSO POSTED:

1. Applicable Anti-ice / De-ice Procedure. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . PERFORM

Procedure Completed

IF AMBER “# Eng A-Ice Fail Off”, “Wing A-Ice Temp Low”, “Tail De-Ice Fail”, OR “# Windshld Heat Fail” CAS MSG NOT POSTED:

NOTE• The Amber CAS MSG and Amber indication on the PFD, should be replaced by a

White CAS MSG after Anti-ice / De-ice equipment is selected ON.

• CAS MSG may post if Wing Anti-ice system has failed or remains selectedOFF, with icing conditions detected.

L Eng A-Ice OvpressOr

R Eng A-Ice Ovpress

Icing

Icing ICING

# Eng A-Ice Fail Off Wing A-Ice Temp Low Tail De-Ice Fail # Windshld Heat Fail

Icing ICING

ICING

Stall Warn Advance




A12-5 P/N 401-590001-0078

1. Anti-ice / De-ice . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON


a. MCDU / MENU / STALL / STALL WARN ADVANCE . . . . . . . . . . . . . RESET, AFTER WING HAS BEEN VERIFIEDTO BE CLEAR OF ICE

Procedure Completed

IF CYAN “Stall Warn Advance” CAS MSG IS CLEARED:

Procedure Completed

ON GROUND

On ground, the absence of the Icing indicators does not reliably assure the airplane is free of ice.

1. Anti-ice / De-ice . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON

The airplane must have been properly de-iced and adequately cleaned of frost, ice, snow or slush.

2. NORMAL PROCEDURES - GROUND DE-ICING / ANTI-ICING OPERATIONS . . . . . . . . . . . .REVIEW AS REQUIRED

Procedure Completed

A12.5 DUAL ICE DETECTOR FAILURE

NOTEThe Amber and White CAS MSGs, and the Amber indication on the PFD,will not post during dual detector failures.

1. Flight Conditions . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . MONITOR FOR ICING CONDITIONS2. Anti-ice / De-ice . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON, IF ICING CONDITIONS EXIST

Procedure Completed

A12.6 PITOT HEAT FAIL

1. Icing Conditions . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . EXIT / AVOID


2. PFD AIR DATA (affected side) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . REVERT

Procedure Completed

Stall Warn Advance

Ice Detector 1-2 Fail

Icing Icing Icing

L Pitot Heat FailOr

R Pitot Heat Fail




A12.7 L AND R PITOT HEAT FAIL ORSTATIC PORT HEAT FAIL

Flight in visible moisture without pitot probe or static port heat may result in erratic or incorrect indicationsof airspeed, Mach No., and altitude on the primary displays.

1. Icing Conditions . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . EXIT / AVOID2. Airspeed and Altitude . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . COMPARE TO STBY INST

IF AIRSPEED OR ALTITUDE DOES NOT AGREE WITH STBY INST OR IF IN ICING CONDITIONS:

a. AP and A/T . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . DISCONNECT, DO NOT RE-ENGAGEb. Stby Inst . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . USE AS PRIMARY REFERENCEc. Airspeed . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . BELOW 0.78M / 300 KIASd. MCDU / CB / ELEC MENU / CB BY SYSTEM / AVIONICS 1/12 / AIR DATA 1 and AIR DATA 2 . . . . . SELECT OUTe. Dual ADC Failure (A6.6) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . PERFORM

Procedure Completed

IF AIRSPEED AND ALTITUDE AGREE WITH STBY INST AND NOT IN ICING CONDITIONS:

a. Stby Inst . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . MONITOR

Procedure Completed

A12.8 STANDBY PITOT HEAT FAILURE 1. Standby Airspeed and Altitude. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . DO NOT USE IF IN ICING CONDITIONS

Procedure Completed

L-R Pitot Heat FailStatic Port Heat Fail

Stby Pitot Heat Fail




A12-7 P/N 401-590001-0078

A12.9 TAIL DE-ICE FAIL

IN FLIGHT1. TAIL DE-ICE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .CYCLE (RETURN TO INITIAL POSITION)


a. Icing Conditions . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . EXIT / AVOID

With the Tail De-ice System failed ON, select FLAPS to 0° / UP within 10 minutes after landing to preventpossible damage due to an overheat of the system.

b. TAIL DE-ICE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF

IF LANDING IS TO BE MADE WITH KNOWN OR SUSPECTED ICE ON THE HORIZONTAL TAIL:

1) AP . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . DISENGAGE / DO NOT RE-ENGAGE2) Landing FLAPS and Airspeed . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .20° / VREF + 10 KIAS3) REDUCED FLAPS APPROACH AND LANDING (A1.1) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .PERFORM

Procedure Completed

IF LANDING IS TO BE MADE WITH NO ICE ON THE HORIZONTAL TAIL:

Procedure Completed

IF AMBER “Tail De-Ice Fail” CAS MSG IS CLEARED:

Procedure Completed

ON GROUND

NOTE CAS MSG may post with the Tail De-ice selected OFF as part of a BIT check and/or

as a result of an electrical power transient.

1. TAIL DE-ICE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CYCLE / OFF


a. Dispatch via MEL.

Procedure Completed

IF AMBER “Tail De-Ice Fail” CAS MSG IS CLEARED:

a. Continue with Normal Tail De-ice Operation as required.

Procedure Completed

Tail De-Ice Fail

Tail De-Ice Fail

Tail De-Ice Fail

Tail De-Ice Fail




A12.10 WINDSHIELD HEAT FAIL

IN FLIGHT1. WINDSHIELD HEAT (affected side) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CYCLE OFF, THEN ON

IF CAS MSG RE-POSTS AFTER APPROXIMATELY 5 MINUTES:

a. Icing Conditions. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . EXIT / AVOID

NOTEIf reduced visibility occurs on the affected side, aircraft control may be transferred to the unaffected side.

Procedure Completed

IF AMBER “# Windshld Heat Fail” CAS MSG IS STILL CLEARED AFTER APPROXIMATELY 5 MINUTES:

Procedure Completed

ON GROUND

With the CAS MSG posted, the Pilot’s emergency windshield heat may beoperating without temperature regulation. To avoid possible windshield damage, turn the LWINDSHIELD HEAT to OFF.

1. WINDSHIELD HEAT (affected side) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF2. Dispatch via MEL.

Procedure Completed

A12.11 WINDSHIELD OVERHEAT

IN FLIGHT

NOTEIf reduced visibility occurs on the affected side, aircraft control may be transferred to the unaffected side.

1. WINDSHIELD HEAT (affected side) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF2. Icing Conditions . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . EXIT / AVOID3. Airspeed. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . BELOW 280 KIAS

Procedure Completed

ON GROUND

If there are any visual impairments on the windshield such as bubbling or hazing, proceed to cool downthe windshield until the CAS MSG clears. Do not dispatch if any distortions or bubbles remain after theCAS MSG has cleared.

1. WINDSHIELD HEAT (affected side) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF2. Dispatch via MEL.

Procedure Completed

L Windshld Heat FailOr

R Windshld Heat Fail

# Windshld Heat Fail

L Windshld Heat Fail

L Windshld OverheatOr

R Windshld Overheat




A12-9 P/N 401-590001-0078

A12.12 WING ANTI-ICE FAIL OFF

1. BLEED ISOLATE. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OPEN

Procedure Completed

A12.13 DUAL WING ANTI-ICE FAIL OFF 1. Icing Conditions . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . EXIT / AVOID2. WING ANTI-ICE. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF3. FLIGHT AND LANDING WITH ICE ACCUMULATION ON THE WINGS (A12.17) . . . . . . . . . . . . . . . . . . . . .PERFORM

Procedure Completed

A12.14 WING ANTI-ICE OVERPRESSURE

IF ACCOMPANIED BY A CAS MSG:

1. WING ANTI-ICE FAIL ON (A12.15) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .PERFORM

Procedure Completed

IF NOT ACCOMPANIED BY AN AMBER “# Wing A-Ice Fail On” CAS MSG:

1. Icing Conditions . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . EXIT / AVOID2. WING ANTI-ICE. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF3. FLIGHT AND LANDING WITH ICE ACCUMULATION ON THE WINGS (A12.17) . . . . . . . . . . . . . . . . . . . . .PERFORM

Procedure Completed

L Wing A-Ice Fail OffOr

R Wing A-Ice Fail Off

L-R Wing A-I Fail Off

Wing A-Ice Ovpress

# Wing A-Ice Fail On




A12.15 WING ANTI-ICE FAIL ON

NOTE CAS MSG means that the indicated Wing Anti-ice Valve has not completely

closed when the Wing Anti-ice System is selected OFF or (in case of a Wing Anti-ice overpressurecondition) the automatic shutdown of the associated Wing Anti-ice Valve has failed.

IN FLIGHT

IF TAT IS GREATER THAN 10° C (50° F) OR IF CAS MSG IS POSTED:

1. Icing Conditions . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . EXIT / AVOID2. BLEED ISOLATE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CLOSE3. WING ANTI-ICE. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF4. BLEED (affected side) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF5. PACK (affected side) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF6. Remaining PACK . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . HIGH FLOW

(CABIN = LEFT PACK, FLIGHT DECK = RIGHT PACK)7. FLIGHT AND LANDING WITH ICE ACCUMULATION ON THE WINGS (A12.17) . . . . . . . . . . . . . . . . . . . . PERFORM

Procedure Completed

IF TAT IS LESS THAN 10° C (50° F) AND NO AMBER “Wing A-Ice Ovpress” CAS MSG IS POSTED:

1. WING ANTI-ICE. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .ON

Procedure Completed

ON GROUND1. BLEED ISOLATE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CLOSE2. WING ANTI-ICE. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF3. BLEED (affected side) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF4. APU BLEED (if left side affected). . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF5. PACK (affected side) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF6. Dispatch via MEL.

Procedure Completed

L Wing A-Ice Fail OnOr

R Wing A-Ice Fail On

# Wing A-Ice Fail On

Wing A-Ice Ovpress




A12-11 P/N 401-590001-0078

A12.16 WING ANTI-ICE TEMPERATURE LOW

IN FLIGHT

NOTEThe wing anti-ice system may not provide adequate wing anti-icing.

1. Thrust Levers. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . INCREASE AS CONDITIONS PERMIT


a. Icing Conditions . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . EXIT / AVOIDb. FLIGHT AND LANDING WITH ICE ACCUMULATION ON THE WINGS (A12.17) . . . . . . . . . . . . . . . . . .PERFORM

Procedure Completed

IF AMBER “Wing A-Ice Temp Low” CAS MSG IS CLEARED:

a. MCDU / MENU / STALL / STALL WARN ADVANCE . . . RESET IF CAS MSG IS POSTEDAFTER WING HAS BEEN VERIFIED TO BE CLEAR OF ICE

b. Cyan “Stall Warn Advance” CAS MSG. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . VERIFY CLEAREDc. Thrust Levers . . . . . . . . . . . . . . .AS REQUIRED (TO KEEP AMBER “Wing A-Ice Temp Low” CAS MSG CLEARED)

Procedure Completed

ON GROUNDPrior to Takeoff:


Procedure Completed

Wing A-Ice Temp Low

Wing A-Ice Temp Low

Stall Warn Advance




A12.17 FLIGHT AND LANDING WITH ICE ACCUMULATION ON THE WINGSComplete checklists are included for DESCENT through LANDING.

Due to distortion of the wing airfoil, ice formations on the wing leading edges can cause significant lossesin rate of climb, cruise speed, and range as well as increases in buffet and stall speeds. With largeaccumulations on the wing leading edges, aerodynamic wing and aileron buffet may be observed prior tostick shaker activation. Do not attempt flight at airspeeds below the onset of aerodynamic buffet.

IF TAT IS GREATER THAN 10° C (50° F) AND NO ICE ACCUMULATION IS OBSERVED ON THE WING LEADING EDGE:

NOTEFailure to reset the Stall Warn Advance may result in nuisance Stall Warning during Approach andLanding.

1. MCDU / MENU / STALL / STALL WARN ADVANCE . . . . . . RESET IF CAS MSG IS POSTED

2. Continue flight using SECTION 4 - NORMAL PROCEDURES Checklists.

Procedure Completed

IF TAT IS LESS THAN 10° C (50° F) OR ICE ACCUMULATION IS VISIBLE ON THE WING LEADING EDGES:

1. Icing Conditions . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . EXIT / AVOID2. Airspeed. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 200 KIAS OR GREATER3. FLAPS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .UP / 0°


4. AP and A/T. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . DISCONNECT, DO NOT RE-ENGAGE5. Landing Speeds, Landing Distance and Brake Energy . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .SEE TABLE

a. Select runway with no tailwind.


b. Verify corrected brake energy does not exceed 46.2 MFP.

DESCENT1. Anti-ice / De-ice . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . AS REQUIRED2. Seats, Seat Belts, and Rudder Pedals. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ADJUSTED / SET3. SEAT BELT / NO SMOKING . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . AS REQUIRED4. APU START / STOP (if available and if 34,000 FT or below) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON AS DESIRED5. Approach and Landing Briefing . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CONSIDERED


Landing Distance Increase by 2800 FT (853 M)


Stall Warn Advance




A12-13 P/N 401-590001-0078

APPROACH1. Altimeters. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . SET / CROSS CHECK2. Airspeed. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 200 KIAS3. EXTERNAL LIGHTS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . AS REQUIRED4. Avionics, FMS, and Flight Guidance . . . . . . . . . . . . . . . . . .SET, PROGRAMMED, SOURCE AND MODES SELECTED5. CAS MSGs . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . REVIEW6. VSPEEDS and Landing Distance. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . COMPUTED7. Approach and Landing Briefing . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . COMPLETED8. FLAP WARN and TERRAIN INHIBIT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . INHIBIT9. Nosewheel Steering. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . TILLER CLEAR

10. GROUND SPOILER . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .CONFIRM ARM11. SEAT BELT / NO SMOKING. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON12. FLAPS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . UP / 0°

BEFORE LANDING1. LANDING GEAR Handle . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . DOWN / THREE GREEN2. Guidance Controller SPD Knob. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .MAN3. SPEEDBRAKE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .CONFIRM RETRACTED4. FLAPS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 20°

5. Airspeed. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . VREF + 30 KIAS6. EXTERNAL LIGHTS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . AS REQUIRED

GO AROUND

NOTEThe FD pitch command should only be used as initial guidance. Pitch adjustments may be required inorder to maintain VREF + 30 KIAS.

1. TO / GA . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .SELECT2. Thrust Levers. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .FORWARD STOP (VERIFY TAKE-OFF N1)3. Airplane Pitch Attitude . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . AS REQUIRED TO MAINTAIN VREF + 30 KIAS4. FLAPS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 12°

5. LANDING GEAR Handle (positive rate of climb confirmed) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . UP6. Climb Airspeed (minimum) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . VREF + 30 KIAS7. Airspeed. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ACCELERATE TO 200 KIAS8. FLAPS (at 200 KIAS). . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . UP / 0°





LANDING1. Airspeed. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .VREF + 30 KIAS2. Thrust Levers . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . IDLE3. Brakes (after touchdown) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .APPLY4. SPEEDBRAKE. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . EXTEND5. Thrust Reversers (after nosewheel on ground) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . DEPLOY6. Reverse Thrust (when deployment confirmed) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . AS REQUIRED7. Nosewheel Steering (all gear firmly on ground) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . AS REQUIRED8. Reverse Thrust . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . IDLE BY 60 KIAS9. Thrust Reversers . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . STOW BY TAXI SPEED

Procedure Completed

A12.18 INADVERTENT ICING ENCOUNTER 1. L and R ENGINE ANTI-ICE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON, ONE AT A TIME2. WING ANTI-ICE and TAIL DE-ICE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .ON

NOTEInadvertent ice shapes may cause mild airframe buffet at airspeeds less than VREF but prior to stickshaker.

Procedure Completed


SECTION 3A ABNORMAL PROCEDURES -...

Documents

Transcript of SECTION 3A ABNORMAL PROCEDURES -...