Manual de Vuelo

Learjet 45 AFM Introduction

MODEL BD-100-1A10

CUSTOMER SUPPORT PUBLICATION No. 100-1

DOT APPROVED

AIRPLANE FLIGHT MANUAL

Challenger 300

Draft 2.8

Learjet 45 AFM Introduction

Airplane Flight Manual

CSP 100-1

FEDERAL AVIATION ADMINISTRATION

APPROVAL PAGE

AIRPLANE FLIGHT MANUAL

CHALLENGER 300 AirplaneMODEL BD-100-1A10

38 500 lb/17 464 kg MTOW

Registration Number: _________________________

Manufacturer’s Serial Number: _________________

Approved by Chief, Flight Test for Director,Aircraft Certification, Transport Canada.

Date of Approval: ____________________________

Challenger 300 INTRODUCTION

Draft 2.8

DOT Approved xx-XX-2003 Airplane Flight Manual

RECORD OF TEMPORARY REVISIONS

It is the responsibility of the aircraft owner and operator to maintain their basicAFM with the temporary revisions applicable to their aircraft.

TR #Dated

Sectionor Page Description Status

Draft 2.8 CSP 100-1 00-02-01

3/14/03

Challenger 300 INTRODUCTIONTABLE OF CONTENTS

Draft 2.8
DOT Approved xx-XXX-2003 Airplane Flight Manual 01-00-01Draft 2.8 CSP 100-1
GENERAL INFORMATION 01-01-01

The Manual .................................................................... 01-01-01Revising The Manual ...................................................... 01-01-02Temporary Revisions ..................................................... 01-01-02Numbered Revisions ...................................................... 01-01-02Performance Data .......................................................... 01-01-03Notes, Cautions, and Warnings ..................................... 01-01-03

3/14/03


Draft 2.8
GENERAL INFORMATION

THE MANUAL

The manual consists of this introduction and the following seven basic chap-ters (for expanded checklists refer to the Flight Crew OperatingManual Vol. 1):

NOTE: Boldfaced text is used for emphasis or to show priority.

Chapter 1 — INTRODUCTION, containing information on the use and thestatus of this manual.

Chapter 2 — LIMITATIONS, must be observed during operation of the air-craft, except where a deviation is specifically authorized.

Chapter 3 — EMERGENCY PROCEDURES, containing the operating proce-dures for use during critical conditions.

Chapter 4 — NORMAL PROCEDURES, containing the designated operatingprocedures for day-to-day operations.

Chapter 5 — NON-NORMAL PROCEDURES, containing the designated op-erating procedures for non-emergency failure conditions.

Chapter 6 — PERFORMANCE, defines the aircraft performance under stan-dard performance conditions.

Chapter 7 — SUPPLEMENTS. Supplements are for aircraft conducting spe-cial operations and/or equipped with specific equipment. The ContaminatedRunway Data assists the operator when operating on a contaminated runway.

Chapter 8 — APPENDICES. Appendices contain ancillary information whichmay or may not be required for the operation of the aircraft.

3/14/03

INTRODUCTION Challenger 300

01-01-02 Airplane Flight Manual DOT Approved xx-XXX-2003CSP 100-1 Draft 2.8

REVISING THE MANUAL

Temporary Revisions or Numbered Revisions must be incorporated in themanual as soon as they are received.

TEMPORARY REVISIONS

Temporary Revisions may be issued to facilitate quick transmission of data.Temporary Revisions must be retained in the Flight Manual until removed bysome other authority — usually a superseding Temporary Revision or a Num-bered Revision.

NUMBERED REVISIONS

Numbered Revisions issued against the Flight Manual differ from TemporaryRevisions in that the pages contained in the Numbered Revision supersede likepages in the Flight Manual.

A vertical bar in the margin indicates a change in content from the previousversion of the Flight Manual. The vertical bars may not appear on pages thatcontain changes to graphs or tables. Additionally, when a “changed” page isthe result of a rearrangement of material due to a change on a previous page,no vertical bar will appear.

3/14/03



FLIGHT MANUAL PERFORMANCE DATA

The performance data in Chapter 6 of this manual provides performance datafor all aircraft with the same model designation rather than performance datafor a specific serial number aircraft. Therefore, due to serial number changesor the incorporation of Service Bulletins, performance charts may be issuedagainst this Flight Manual which are not applicable to the specific aircraft as-signed to the Flight Manual. Charts not effective for a particular aircraft maybe removed from the Flight Manual for that aircraft and need not be retained.The airplane effectivity of each chart is listed on the page containing the chartand in the List of Effective Pages.

NOTES, CAUTIONS, AND WARNINGS

NOTE: Notes highlight specific operating conditions or steps of a proce-dure.

CAUTION: Cautions call attention to operating procedures which, if notstrictly observed, may result in damage to equipment.

WARNING: Warnings call attention to operating procedures which, if notstrictly adhered to, may result in personal injury or loss oflife.

3/14/03

Challenger 300 LIMITATIONSTABLE OF CONTENTS

Draft 2.8

BASIC LIMITATIONS 02-01-01

Kinds of Operation ......................................................... 02-01-01Operation In Icing Conditions.......................................... 02-01-01Minimum Flight Crew ..................................................... 02-01-02

WEIGHT AND C.G. LIMITATIONS 02-02-01

Maximum Ramp Weight.................................................. 02-02-01Maximum Certified Takeoff Weight ................................. 02-02-01Minimum Flight Weight.................................................... 02-02-01Maximum Zero Fuel Weight ............................................ 02-02-01Maximum Certified Landing Weight ................................ 02-02-01CENTER-OF-GRAVITY (Fig. 02-03-01) ......................... 02-02-02

AIRSPEED/MACH LIMITATIONS 02-03-01

Maximum Operating Speed VMO/MMO............................ 02-03-01Maneuvering Speed (VA)................................................. 02-03-01Rough Air Penetration Speed (VRA)................................ 02-03-01Maximum Landing Gear Operating

Speed Retraction (VLO RET) ......................................... 02-03-01Maximum Landing Gear Operating

Speed Extension (VLO EXT) .......................................... 02-03-01Maximum Landing Gear Extended Speed (VLE) ............. 02-03-01Maximum Flap Extended Speed (VFE) ........................... 02-03-01AIRSPEED/MACH LIMITATIONS (Fig. 02-03-01) .......... 02-03-02

OPERATIONAL LIMITATIONS 02-03-03

Takeoff and Landing ....................................................... 02-03-03En Route ........................................................................ 02-03-03Maneuvering Load Factors ............................................ 02-03-03Flaps .............................................................................. 02-03-03Autoflight ......................................................................... 02-03-03Gear ............................................................................... 02-03-04Maneuvers ...................................................................... 02-03-04Tire Speed ...................................................................... 02-03-04AMBIENT TEMPERATURE LIMITS (Fig. 02-03-02)....... 02-03-04


3/14/03

LIMITATIONS Challenger 300TABLE OF CONTENTS

SYSTEMS LIMITATIONS 02-04-01Air Conditioning and Pressurization ................................02-04-01Autoflight .........................................................................02-04-01Avionics ..........................................................................02-04-02Electrical .........................................................................02-04-06Flight Controls .................................................................02-04-06Landing Gear Wheels & Brakes ......................................02-04-06

FUEL LIMITATIONS 02-05-01

Minimum Takeoff Fuel .....................................................02-05-01Approved Fuels ..............................................................02-05-01Fueling ............................................................................02-05-01

POWERPLANT LIMITATIONS 02-06-01

Engine Type ...................................................................02-06-01Engine Operation ...........................................................02-06-01Engine Starter .................................................................02-06-01Oil ....................................................................................02-06-02Thrust Reversers.............................................................02-06-02

AUXILIARY POWER UNIT (APU) LIMITATIONS 02-06-03

APU Type ........................................................................02-06-03Maximum Altitude............................................................02-06-03APU Start ........................................................................02-06-03Approved Fuels/Oils ........................................................02-06-03


3/14/03

Challenger 300 LIMITATIONS

Draft 2.8
BASIC LIMITATIONS

Observance of the limitations contained in the LIMITATIONS chapter of thisAirplane Flight Manual is mandatory.

KINDS OF OPERATION

This airplane is certificated to the applicable regulations in the transport cate-gory and is eligible for the following kinds of operations when the appropriateinstruments and equipment required by the airworthiness and operating re-quirements are installed and approved and are operable.

This airplane is approved for:

- VMC (Visual Meteorological Conditions)- IMC (Instrument Meteorological Conditions)- Day- Night- Icing

OPERATION IN ICING CONDITIONS

Engine Anti-Ice Systems:

Ground operations. The engine anti-icing system must be ON when theoutside air temperature (OAT) on the ground and for takeoff is 10 °C (50 °F)or below and visible moisture in any form is present (such as clouds, fog withvisibility of one mile (1500 m) or less, rain, snow, sleet, or ice crystals).

The engine anti-icing system must also be ON when the OAT is 10 °C (50 °F)or below when operating on ramps, taxiways, or runways where surface snow,ice, standing water, or slush may be ingested by the engines, or freeze on en-gines, nacelles, or engine sensor probes.

Flight operations. Icing conditions exist when the static air temperature(SAT) in flight is 10 °C (50 °F) to -40 °C (-40 °F) and visible moisture in anyform is present (such as clouds, fog, rain, snow, sleet, or ice crystals), exceptwhen the SAT is -40 °C (-40 °F) or below.

The engine anti-icing system must be ON when the ICE DETECTED CASmessage is on, or in icing conditions.

3/14/03

LIMITATIONS Challenger 300


OPERATION IN ICING CONDITIONS (Cont)

Wing Anti-Ice Systems:

Ground operations. The wing anti-icing system must be ON for takeoff whenthe OAT is 5 °C (41 °F) or below and visible moisture in any form is present(such as clouds, fog with visibility of one mile (1500 m) or less, rain, snow,sleet, or ice crystals).

The wing anti-icing system must also be ON when the OAT is 5 °C (41 °F) orbelow when operating on ramps, taxiways, or runways where surface snow,ice, standing water, or slush is present.

Flight operations. Icing conditions exist when the (SAT) in flight is 10 °C(50 °F) to -40 °C (-40 °F) and visible moisture in any form is present (such asclouds, fog, rain, snow, sleet, or ice crystals), except when the SAT is -40 °C(-40 °F) or below.

The wing anti-icing system must be ON when the ICE DETECTED CAS mes-sage is on, or in icing conditions.

Super-Cooled Large Droplet Icing

Operation in areas where super-cooled large droplet icing (SLD) conditionsexist is prohibited.

SLD conditions are indicated by ice accretion on the flight compartment sidewindows.

Wing and engine anti-ice systems must be ON in SLD conditions.

Leave icing conditions when side window icing occurs.

DITCHING

This airplane is certified for ditching when the appropriate safety equipment isinstalled per applicable regulations.

MINIMUM FLIGHT CREW

The minimum flight crew shall consist of a pilot and a copilot.

3/14/03


Draft 2.8
WEIGHT AND C.G. LIMITATIONSMAXIMUM RAMP WEIGHT ................................................... 38 650 lb

17 531 kg

MAXIMUM CERTIFIED TAKEOFF WEIGHT ......................... 38 500 lb17 463 kg

MINIMUM FLIGHT WEIGHT .................................................. 23 100 lb10 478 kg

MAXIMUM ZERO FUEL WEIGHT ......................................... 26 100 lb11 838 kg

NOTE: All weights in excess of Maximum Zero Fuel Weight must consistof fuel.

MAXIMUM CERTIFIED LANDING WEIGHT ......................... 33 750 lb15 309 kg

NOTE: The Maximum Takeoff Weight (MTOW) and/or MaximumLanding Weight (MLW) may be further limited due to performanceconsiderations.

3/14/03



CENTER-OF-GRAVITYThe center of gravity of the airplane for all flight conditions must be maintained withinthe applicable CENTER-OF-GRAVITY ENVELOPE below.

Figure 02-02-01

10

11

12

13

14

15

16

1840

35

30

25

20

WE

IGH

T x

100

0 —

PO

UN

DS

WE

IGH

T x

100

— K

ILO

GR

AM

S

28 30 32 36 40 4224

CENTER-OF-GRAVITY — % MAC

383426

Max Ramp Weight38 650 lb (17 531 kg)

Max Zero Fuel Weight26 100 lb (11 838 kg)

Max Landing Weight33 750 lb (15 309 kg)

Max Takeoff Weight38 500 lb (17463 kg)

17

3/14/03


Draft 2.8
AIRSPEED/MACH LIMITATIONS

MAXIMUM OPERATING SPEED (VMO/MMO)

VMO (up to 8000 ft) ...................................................................................... 300 KIAS

VMO (8001 to 29 475 ft)............................................................... 320 KIAS

MMO (Above 29 475 ft) ....................................................................0.83 MI

VMO/MMO may not be deliberately exceeded in any regime of flight (climb,cruise, or descent) unless a higher speed is authorized for flight test or pilottraining.

MANEUVERING SPEED (VA)

VA is the highest speed that full roll and yaw control can be applied withoutoverstressing the aircraft, or the speed at which the aircraft will stall with a loadfactor of 2.6 g at maximum gross weight, whichever is less.

Refer to applicable figure entitled Airspeed/Mach Limits, this section, for VA.

ROUGH AIR PENETRATION SPEED (VRA)

VRA .................................................................................................. 265 KIAS/0.75 MI

MAXIMUM LANDING GEAR OPERATING SPEED — RETRACTION (VLO RET)

VLO RET...................................................................................... 200 KIAS

MAXIMUM LANDING GEAR OPERATING SPEED — EXTENSION (VLO EXT)

VLO EXT...................................................................................... 250 KIAS

MAXIMUM LANDING GEAR EXTENDED SPEED (VLE)

VLE ............................................................................................. 250 KIAS

MAXIMUM FLAP EXTENDED SPEED (VFE)

VFE

- Flaps 10 ................................................................................ 210 KIAS- Flaps 20 ................................................................................ 210 KIAS- Flaps 30 ................................................................................ 175 KIAS

3/14/03



AIRSPEED/MACH LIMITATIONS (Cont)

AIRSPEED/MACH LIMITATIONS(PRIMARY PITOT-STATIC SYSTEM)

Figure 02-03-01

SPDENV_BD100_31OCT02

100 125 150 175 200 225 250 275 300 325 35INDICATED AIRSPEED KNOTS

0

5

10

15

20

25

30

35

40

45

50

PR

ES

SU

RE

AL

TIT

UD

E

1000

FE

ET 24

000

2850

0

3375

0

3850

0

Mmo = 0.83

Vm

o

MAXIMUM ALTITUDE

V A F

OR

WE

IGH

T L

B

3/14/03



OPERATIONAL LIMITATIONS

TAKEOFF AND LANDING

Maximum takeoff and landing pressure altitude............................8000 ft.Maximum tailwind component ....................................................... 10 kts.

Takeoffs and Landings are limited to paved runways.

EN ROUTE

Maximum Pressure Altitude .......................................................45 000 ft.

MANEUVERING LOAD FACTORS

Flaps Up ............................................................................+2.6 g to -1.0 g.Flaps Extended ................................................................... +2.0 g to 0.0 g.

FLAPS

Do not extend the flaps above 18 000 ft.

AUTOFLIGHT

The use of the Flight Level Change (FLC) mode in an autopilot coupled de-scent is prohibited above 0.80 MI/300 kts.

3/14/03



OPERATIONAL LIMITATIONS (Cont)

GEAR

Do not extend the gear above 18 000 ft.

MANEUVERS

No aerobatic maneuvers, including spins, are permitted.

TIRE SPEED

Maximum tire speed (ground speed) ....................................................182 kts.

AMBIENT TEMPERATURE LIMITATIONS

Figure 02-03-02

ALTENV_BD100_30OCT02

80 70 60 50 40 30 20 10 0 10 20 30 40 50 60TEMPERATURE oC

5

0

5

10

15

20

25

30

35

40

45

50

PR

ES

SU

RE

AL

TIT

UD

E

1000

FE

ET

AWAIT

ING U

PDATE

3/14/03


Draft 2.8
SYSTEMS LIMITATIONS

AIR CONDITIONING AND PRESSURIZATION

AIR CONDITIONING

Do not select the AIR SOURCE switch to TRIM AIR ONLY while the aircraftis on the ground.

The pack must be operating (APU or engine running and AIR SOURCEswitch — NORM or PACK ONLY) when the aircraft electrical power ison (BATTs or EXT PWR — On) for more than 30 minutes and the OAT isabove 40 °C (104 °F).

OXYGEN

The following aircraft certification requirements are in addition to the require-ments of applicable operating rules. The most restrictive requirements (certifi-cation or operating) must be observed.

Crew and passenger oxygen masks are not approved for use above 40 000 feetcabin altitude. Prolonged operation of passenger masks above 25 000 feet cab-in altitude is not recommended.

PRESSURIZATION

The maximum differential pressure on the ground (during taxi) must not ex-ceed 0.1 psi.

The maximum differential pressure during landing must not exceed 1.0 psi.

AUTOFLIGHT

Do not intentionally overpower the autopilot.

Do not use the autopilot in Flight Level Change (FLC) mode above 300 KIAS/0.80 MI.

Autopilot Minimum Use Height:

Climb, En Route, or Descent..................................................... 400 feet AGL.Approach

Precision............................................................................... 80 feet AGL.Visual and non-precision.................................................... 400 feet AGL.

The autopilot and transponder must use the same ADC source for flight inRVSM airspace.

3/14/03



SYSTEMS LIMITATIONS (Cont)

AVIONICS

FLIGHT MANAGEMENT SYSTEM (FMS)

The Collins FMS-5000 Flight Management System Pilot’s Guide (Part number523-0778334-002117 dated xx-xxx-xx or later) must be immediately availableto the flight crew whenever navigation is predicated on the use of the FMS.

The FMS is approved for use with software version [FMC SCID #] or later ap-plicable revision. The software status in the FMS Pilot’s Guide must match thatdisplayed on the equipment.

The fuel display parameters are advisory only, and must not be used to replacethe primary fuel quantity or fuel flow gauges for fuel load and range planning.

Approval Status:

En Route and Terminal Navigation — The FMS installation with the GPShas been approved as a supplemental means of navigation source for en routeand terminal operations.

Lateral Navigation — Provided the FMS is receiving adequate usable sig-nals, it has been demonstrated capable of and has been shown to meet the ac-curacy specifications of:

VFR/IFR en route domestic, terminal, within the United States NationalAirspace System, and latitudes bounded by North 67° 00 and South 65° 00using WGS-84 (or NAD 83) coordinate reference datum.

NOTE: The above statements do not constitute an operational approval.

3/14/03




AVIONICS (Cont)FLIGHT MANAGEMENT SYSTEM (Cont)

Approval Status (Cont):

RNP-10 — The FMS installation with the GPS with RAIM has been demon-strated to meet the criteria of FAA Order 8400.12A “Required Navigation Per-formance 10 (RNP-10) Operational Approval” as a means of navigation forflights without time limitations when a second GPS is installed.

Vertical Navigation — The FMS installation has been found to meet the re-quirements for VFR/IFR en route, terminal area and VNAV operation withinthe conterminous United States and Alaska in accordance with the criteria ofFAA AC 20-129.

NOTE: The above statements do not constitute an operational approval.

3/14/03





FMS Limitations.

IFR enroute and terminal navigation is prohibited unless the pilot verifies thecurrency of the database or verifies the waypoints for accuracy by reference tocurrent publications.

FMS approaches are prohibited.

To be used for navigation, the FMS must be receiving suitable navigationinformation from the following sources:

- One VOR / DME, or- Two DMEs, or- GPS. If the GPS is the only available sensor, use of the FMS for

navigation is not approved unless the Collins predication program832-3443-005 has been run.

Multiple entries of the same pilot defined waypoint in a flight plan isprohibited.

When the altimeter is adjusted to show the Height Above Ground (QFE) ratherthan sea level, VNAV must not be used.

Use of VNAV vertical guidance for a V-MDA type approach between the finalapproach fix and the missed approach fix is prohibited.

FMS may not be used as a primary source of navigation without an alternatemeans of navigation displayed.

3/14/03





Vertical Navigation Limitations

When using VNAV, the altimeter on each pilot’s instrument panel must be usedas the primary altitude reference for all operations.

When the altimeter is adjusted to show the Height Above Ground (QFE) ratherthan sea level, VNAV must not be used.

The minimum altitude for autopilot coupled VNAV operation is XXX feet(AGL).

CAUTION: - Extra caution must be exercised when using VNAV guid-ance for descent, especially during IFR instrument opera-tions.

- Errors to VNAV defined paths may occur because of cod-ing errors in the navigation data base and because of altim-etry errors. The actual VNAV path may deviatesignificantly below the intended VNAV path in very coldtemperatures, unless an approved temperature compensa-tion function (if equipped) is used to correct for non-stan-dard temperatures.

- Database coding of VNAV altitudes for approachwaypoints may result in VNAV paths continuing belowMinimum Descent Altitude (MDA), Decision Altitude(DA), or Decision Height (DH), or ending at an altitude toohigh to continue a safe descent to landing. VNAV paths (of-ten called pseudo-glide paths) are not equivalent to an ILSglideslope.

- Position along an approach must be verified prior to com-mencement of VNAV descent as displayed by the FMS.The required visual reference must be obtained prior tocommencing descent below published MDAs, DAs orDHs.

3/14/03




AVIONICS (Cont)

STANDBY INSTRUMENT

Use of the standby instrument localizer deviation guidance is prohibited duringlocalizer backcourse approaches.

TERRAIN AWARENESS AND WARNING SYSTEM (TAWS)

TAWS WARN TERRAIN switch must be OFF.

TRAFFIC ALERT AND COLLISION AVOIDANCE SYSTEM (TCAS)

Pilots are authorized to deviate from their Air Traffic Control (ATC) clearancein order to comply with a resolution advisory (RA) command.

Maneuvers must not be based solely on information presented on the trafficmap overlay.

ELECTRICAL

Ground or Flight Operations

- Continuous:Two or three generators operating ................................... 400 amps.One generator operating .................................................. 500 amps.

- Transient (5 minutes)............................................................ 600 amps.

NOTE: Refer to APU LIMITATIONS for additional APU generator limits.

FLIGHT CONTROLS

SPOILERS

Do not select Flight Spoilers to EMER except during emergency conditions oras required by procedure.

LANDING GEAR WHEELS & BRAKES

Towbarless towing is prohibited.

3/14/03



3/14/03

FUEL LIMITATIONS

MINIMUM TAKEOFF FUEL

With wing bulk fuel temperature at 45 °C (113 °F) or above, the minimum fuelload for takeoff is 2800 lb (1270 kg).

APPROVED FUELS

The mixing of fuel types is allowed.

Jet A and Jet A-1 fuels are approved.

Refer to Addendum I — FUEL SERVICING for a listing of approved fuels.

FUELING

Single-point pressure refueling is limited to 55 psig (3792 hPa) and defuelingis limited to -8 psig (-552 hPa).

Draft 2.8


Draft 2.8
POWERPLANT LIMITATIONS

ENGINE TYPE

AS907-1-1A turbofan propulsion engines.

ENGINE OPERATION

The engine indicating system is designed to show system status with specifiedcolors. The limits are indicated in red.

Manual ignition must be ON for engine starts, and while in flight.

ENGINE STARTER

On the ground above 9000 ft, start the right engine first, then use crossbleed tostart the left engine.

ENGINE START:

Three consecutive engine start cycles may be conducted, followed by a coolingperiod of 15 minutes, prior to additional starts and motoring.

The engine must be motored for 30 seconds after an aborted start.

For engine ground starting altitude and temperature limits, refer to thefollowing chart:

Start Envelope

ENGINE CRANKING:

The engine can be motored (cranked) for up to 5 minutes, followed by a cool-ing period of 15 minutes prior to additional starts or motoring.

0

5000

10 000

-40 -30 -20 -10 0 20 30 40 50OAT (C)

PR

ES

SU

RE

AL

TIT

UD

E (

FT

.)

-2000

10

Ground Start Envelope

3/14/03



POWERPLANT LIMITATIONS (Cont)

OIL

Oils conforming to Honeywell specification EMS 53110, Type II are ap-proved. Refer to Addendum II — ENGINE OIL SERVICING for a listing ofapproved oils.

THRUST REVERSERS

Limit thrust reverser system use to ground operations on paved surfaces.

Do not attempt to deploy thrust reversers in flight.

Do not use thrust reversers to back up the aircraft.

Do not use thrust reversers for touch-and-go landings.

Maximum reverse thrust is usable at speeds down to 40 KIAS. Idle reversethrust is usable at any speed.

3/14/03



AUXILIARY POWER UNIT (APU) LIMITATIONS

APU TYPE

Honeywell 36-150BD auxiliary power unit.

The EICAS system is designed to show system status with specified colors.

The maximum and minimum limits are indicated in red.

MAXIMUM ALTITUDE

APU Operation ........................................... 37 000 ft.APU GEN ................................................... 30 000 ft.Bleed air with up to 400 amps load ............. 20 000 ft.

Do not use the APU to start the left engine on the ground above 9000 ft.

Operation of the APU during fluid de-icing/anti-icing is prohibited.

Do not take off with an APU SHUTDOWN (A) CAS displayed without con-ducting an inspection. If the APU automatically shuts down due to an APUfailure, a visual inspection of the unit must be conducted prior to flight.

APU START

Delay starting the APU for 5 minutes after application of anti-icing fluid nearthe APU area.

The APU may be started up to an altitude of 30 000 ft (10 000 ft on the ground).The APU starter is limited to 30 seconds continuous cranking time.

Do not start the APU above 300 KIAS.

Three start attempts may be made, each followed by a one-minute coolingperiod. After the third start attempt, there must be a 20-minute cooling period.Two more start attempts may then be made. No further attempts may be madefor at least 40 minutes.

Six successful starts may be made at 10 minute intervals with a one hour wait-ing period prior to additional start attempts.

APPROVED FUELS/OILS

Fuels approved for the main aircraft engines are also approved for the APU.

Type I (MIL-L-7808) and Type II (MIL-L-23699) are approved oils for the APU.

3/14/03

Challenger 300 EMERGENCY PROCEDURES

Draft 2.8

DOT Approved xx-XX-2003 Airplane Flight Manual 03-00-01Draft 2.8 CSP 100-1

INTRODUCTION

GENERAL 03-01-01

AIR CONDITIONING & PRESSURIZATION 03-12-01

CABIN ALTITUDE (W) .......................................................... 03-12-01

CABIN DELTA P (W)............................................................. 03-12-02

L (R) BLEED LEAK (W)......................................................... 03-12-03

PACK LEAK (W).................................................................... 03-12-03

L (R) PYLON BLEED LEAK (W)............................................ 03-12-03

TRIM AIR LEAK (W).............................................................. 03-12-04

AUXILIARY POWER UNIT 03-15-01

APU FIRE (W) ....................................................................... 03-15-01

APU OVERTEMP (W) ........................................................... 03-15-01

AVIONICS 03-17-01

Multi-Functional Display (MFD) Annunciations...................... 03-17-01

HDG....................................................................................... 03-17-01

Primary Flight display (PFD) Annunciations .......................... 03-17-01

ALT ........................................................................................ 03-17-01

AP.......................................................................................... 03-17-01

ATT........................................................................................ 03-17-01

FD.......................................................................................... 03-17-01

FMS 1 FMS 2

LOC 1 LOC 2

VOR 1 VOR 2 ........................................................................ 03-17-01

HDG....................................................................................... 03-17-02

IAS......................................................................................... 03-17-02

MACH .................................................................................... 03-17-02

RA.......................................................................................... 03-17-02

VNV ....................................................................................... 03-17-02

VS.......................................................................................... 03-17-02

Taws Aurals........................................................................... 03-17-03

3/14/03

EMERGENCY PROCEDURES Challenger 300

03-00-02 Airplane Flight Manual DOT Approved xx-XX-2003CSP 100-1 Draft 2.8

ELECTRICAL

BATTERY POWER ONLY (W) ..............................................03-19-01

L (R) BATT OVERHEAT (W) .................................................03-19-02

EVACUATION

Emergency Evacuation .........................................................03-20-01

FLIGHT CONTROLS

Overspeed ............................................................................03-23-01

Stall On PFD..........................................................................03-23-01

Pitch Axis Uncommanded Motion ..........................................03-23-02

Roll or Yaw Axis Uncommanded Motion................................03-23-03

Pitch Control Jam...................................................................03-23-04

Roll Control Jam ....................................................................03-23-05

Yaw Control Jam ...................................................................03-23-06

HYDRAULICS

HYD PRESS LOW (W) ..........................................................03-25-01

ICE & RAIN PROTECTION

WING ANTI-ICE LEAK (W)....................................................03-27-01

L (R) WING OVERHEAT (W).................................................03-27-01

LANDING GEAR, WHEEL & BRAKES

GEAR (W) ..............................................................................03-28-01

GEAR BAY OVHT (W)...........................................................03-28-01

NORM BRAKES FAIL (W) .....................................................03-28-01

LANDING PROCEDURES

Ditching .................................................................................03-29-01

Forced Landing — Both Engines Inoperative .............................................03-29-02

3/14/03


DOT Approved xx-XX-2003 Airplane Flight Manual 03-00-03Draft 2.8 CSP 100-1

POWERPLANT

L (R) ENGINE EXCEEDANCE (W) .......................................03-32-01

L (R) ENGINE FIRE (W) ........................................................03-32-02

L (R) OIL PRESSURE LOW (W) ...........................................03-32-04

L (R) REVERSER UNSAFE (W)............................................03-32-05

Thrust Reverser Deployed Landing .......................................03-32-06

Dual Engine Flameout ..........................................................03-32-08

Engine Failure .......................................................................03-32-10

REJECTED TAKEOFF

Rejected Takeoff....................................................................03-33-01

SMOKE OR FIRE

Cabin/Cockpit Fire, Smoke Or Fumes ...................................03-34-01

LAV SMOKE (W) ...................................................................03-34-07

CARGO SMOKE (W).............................................................03-34-07

TAKEOFF CONFIGURATION WARNINGS

CONFIGURATION WARNING .............................................................................03-35-01

CONFIG AILERON TRIM (W) .........................................03-35-01CONFIG AUTOPILOT (W) ..............................................03-35-01CONFIG FLAPS (W) .......................................................03-35-01CONFIG RUDDER TRIM (W) .........................................03-35-01CONFIG SPOILERS (W).................................................03-35-01CONFIG STAB TRIM (W) ...............................................03-35-01PARK/EMER BRAKE ON (W).........................................03-35-01

PITCH DISCONNECT (W) ....................................................03-35-02

ROLL DISCONNECT (W)......................................................03-35-02

3/14/03


Draft 2.8


GENERAL

Procedures emphasized by enclosure in a box and boldfaced should be accom-plished without reference to this manual (memorized).

Terminology

Land as soon as possible — A landing should be accomplished at the nearestsuitable airfield considering the severity of the emergency, weather conditions,field facilities, ambient lighting, and aircraft gross weight.

Land as soon as practical — Emergency conditions are less urgent, and land-ing at the nearest suitable airfield may not be necessary.

3/14/03

Challenger 300 EMERGENCY PROCEDURESAIR CONDITIONING & PRESSURIZATION

Draft 2.8


CABIN ALTITUDE (W) “CABIN ALTITUDE”

1. Crew Oxygen Masks .................................................................. Don.2. Thrust levers .............................................................................IDLE.3. Autopilot ...........................................................................Disconnect.4. FLIGHT SPOILERS lever ................................................... EMER.5. Descend at MMO/VMO, but not below minimum safe altitude.6. Pilot and Copilot

NORM/O2 MASK switches ............................................. O2 MASK.

WARNING: If structural failure is evident, limit speeds and maneuveringloads as much as possible in descent.

NOTE: Descent from 45 000 feet to 15 000 feet requires approximatelyX minutes XX seconds.

7. Pilot and Copilot INPH switches................................................ INPH.8. Passenger oxygen masks ........................................... Verify deployed.

If time and conditions permit:9. Controlling Agency .................................................................... Notify.

10. Transponder ............................................................... Emergency 7700.11. Passengers............................ Check condition and provide assistance.

END

3/14/03

EMERGENCY PROCEDURES Challenger 300AIR CONDITIONING & PRESSURIZATION


CABIN DELTA P (W)Cabin Delta P is 9.2 psid or greater:

1. MANUAL PRESSURIZATION switch..........................................ON. 2. MAN RATE control ......................................................................... UP,

as required to reduce differential pressure.

CABIN DELTA P Warning remains on:

a. One L or R BLEED switch.....................................................OFF.b. Adjust N1 on opposite engine to control cabin pressurization.

If still unable to regulate the over pressurization:(1) AIR SOURCE switch .....................................................OFF.(2) Descend, but not below minimum safe altitude.

Cabin Delta P is -0.3 psid or less:1. MANUAL PRESSURIZATION switch..........................................ON.2. MAN RATE control .......................................................................DN,

as required to increase differential pressure.

CABIN DELTA P Warning remains on:a. Decrease aircraft descent rate.

Yes

Yes

No

No

END

END

END

3/14/03

Challenger 300 EMERGENCY PROCEDURESAIR CONDITIONING & PRESSURIZATION


L (R) BLEED LEAK (W)1. XBLEED switch.......................................................................Closed.2. Affected BLEED switch ..............................................................OFF.

If R BLEED LEAK (W) is on:a. L BLEED switch .................................................................... On.b. APU BLEED switch.............................................................OFF.

PACK LEAK (W)

1. AIR SOURCE switch .......................................... TRIM AIR ONLY.

PACK LEAK (W) remains on after 40 seconds:

a. AIR SOURCE switch ............................................................ OFF.b. Altitude .............................................................8000 ft maximum.c. RAM AIR switch .....................................................................ON.

PACK LEAK extinguishes:a. Altitude ..........................................................35 000 ft maximum.b. Cockpit COLD-HOT knob (for cockpit & cabin) ...... As Desired.

L (R) PYLON BLEED LEAK (W)

Affected Engine:1. Thrust lever ...............................................................................IDLE.

If PYLON BLEED LEAK (W) remains on:2. Affected engine RUN switch......................................................... OFF.3. Refer to Engine Shutdown in Flight procedure, Non-Normal proce-

dures.

END

Yes

No

END

END

3/14/03

EMERGENCY PROCEDURES Challenger 300AIR CONDITIONING & PRESSURIZATION


TRIM AIR LEAK (W)

1. AIR SOURCE switch ...................................................PACK ONLY.

TRIM AIR LEAK (W) remains on after 40 seconds:

a. AIR SOURCE switch .............................................................OFF.b. Altitude............................................................. 8000 ft maximum.c. RAM AIR switch.....................................................................ON.

TRIM AIR LEAK extinguishes:a. Cockpit COLD-HOT knob (for cockpit & cabin) .......As Desired.

Yes

No

END

END

3/14/03

Challenger 300 EMERGENCY PROCEDURESAUXILLIARY POWER UNIT


APU FIRE (W) "APU FIRE"

1. APU FIRE switch ........................................ Lift guard, FIRE push.2. FIRE EXT 2 switch................................. Lift guard, ARMED push.

3. XBLEED switch ........................................................................ Closed.

4. L and R BLEED switches................................................................ON.

5. APU BLEED switch ...................................................................... OFF.

6. APU switch.................................................................................... OFF.7. Bleeds .............................................................................................SET.8. Land as soon as possible.

APU OVERTEMP (W)

1. APU switch ..................................................................................OFF.

END

END

3/14/03

Challenger 300 EMERGENCY PROCEDURESAVIONICS

Draft 2.8


MULTI-FUNCTION DISPLAY (MFD) ANNUNCIATIONS

HDG

If HDG is displayed on left MFD:1. ATT/HDG REVERSION switch ........................................................ 2.

If HDG is displayed on right MFD:1. ATT/HDG REVERSION switch ........................................................ 1.

PRIMARY FLIGHT DISPLAY (PFD) ANNUNCIATIONS

ALT

If ALT is displayed on left PFD:1. AIR DATA REVERSION switch ....................................................... 2.

If ALT is displayed on right PFD:1. AIR DATA REVERSION switch ....................................................... 1.

AP

1. Control wheel MSW switch ..................................Depress and release.

NOTE: - An autopilot monitored disconnect is not always accompaniedby a yaw damper failure/disconnect.

- Depressing the MSW will cancel the AP disconnect aural warn-ing.

ATT

1. Monitor standby instrument.

If ATT is displayed on the left PFD:2. ATT/HDG REVERSION switch ........................................................ 2.

If ATT is displayed on the right PFD: 2. ATT/HDG REVERSION switch ....................................................... 1.

FD

1. FGP XFR button....................................................Select opposite side.

FMS 1 FMS 2LOC 1 LOC 2VOR 1 VOR 2

1. NAVSRC button ............................................. Select cross-side source.

END

3/14/03

EMERGENCY PROCEDURES Challenger 300AVIONICS


Primary Flight Display (PFD) Annunciations (Cont)

HDG

If HDG is displayed on left PFD:1. ATT/HDG REVERSION switch.........................................................2.

If HDG is displayed on right PFD:1. ATT/HDG REVERSION switch.........................................................1.

IAS


If IAS is displayed on the left PFD:2. AIR DATA REVERSION switch........................................................2.

If IAS is displayed on the right PFD:2. AIR DATA REVERSION switch........................................................1.

MACH


If MACH is displayed on the left PFD:2. AIR DATA REVERSION switch........................................................2.

If MACH is displayed on the right PFD:2. AIR DATA REVERSION switch........................................................1.

RA

1. Cross check instruments to validate altitude. 2. Do not rely on radar altimeter(s).

NOTE: To ensure prompt ground spoiler deployment, conduct a firm land-ing.

VNV

1. Use alternate means of vertical navigation.

VS

If VS is displayed on the left PFD:1. AIR DATA REVERSION switch........................................................2.

If VS is displayed on the right PFD:1. AIR DATA REVERSION switch........................................................1.

3/14/03

Challenger 300 EMERGENCY PROCEDURESAVIONICS


TAWS AURALS TAWS AURALS

“PULL UP” or“TERRAIN, TERRAIN, PULL UP” or“OBSTACLE, OBSTACLE, PULL UP”

1. Autopilot ............................................................................. Disengage.2. Thrust levers .................................................................................TO.3. Climb at maximum practical rate.4. Flight spoilers levers ................................................................... RET.5. LANDING GEAR switch.............................................................. UP.

6. Maintain climb until the warning ceases.

“WINDSHEAR, WINDSHEAR”

1. Autopilot ............................................................................. Disengage.2. Thrust levers .................................................................................TO.3. Rotate smoothly to the takeoff/go around pitch attitude, allowing

airspeed to decrease if necessary. Maintain wings level. Do not retractflaps or landing gear.

4. If the aircraft continues to descend, increase pitch attitude smoothlyand in small increments, bleeding airspeed as necessary to stopdescent. Use stall warning onset (stick shaker) as the upper limit ofpitch attitude.

5. Maintain escape attitude and thrust and delay retracting flaps orlanding gear until safe climb out is assured.

3/14/03

Challenger 300 EMERGENCY PROCEDURESELECTRICAL


BATTERY POWER ONLY (W)1. L and R GEN switches ................................. One at a time, select ON.

If a generator comes online:

2. DOME light switch ...................................... BRT for night operations.3. LEFT DISPLAYS REVERSION switch ............................ MFD REV.4. TUNE REVERSION switch..............................................CDU ONLY.5. Use the standby instrument for airspeed, attitude, and altitude informa-

tion.6. STAB TRIM switch....................................................................... SEC.7. AUX HYDRAULIC PUMP switch............................................... OFF.8. EMER LTS switch ......................................................................... OFF.9. Avoid icing conditions.

10. L and R PROBES switches .................OFF, unless in icing conditions.11. L and R WSHLD/WINDOW switches.......................................... OFF.12. MAN TEMP switch........................................................................ ON.

NOTE: If a generator does not come online, battery duration (with two 44amp hour batteries) with the generators off is one hour.

(Continued)

Yes

NoEND

3/14/03

EMERGENCY PROCEDURES Challenger 300ELECTRICAL


BATTERY POWER ONLY (Cont)At 30 000 ft and below:

13. APU start: .......................................... APU switch START and release.

The APU starts:

a. APU GEN.....................................................................Verify ON.b. LEFT DISPLAYS REVERSION switch...........................NORM.c. TUNE REVERSION switch .............................................NORM.d. STAB TRIM switch.................................................................PRI.e. AUX HYDRAULIC PUMP switch ...................................AUTO.f. L and R PROBES switches ......................................................On.g. L and R WSHLD/WINDOW switches ...................................ON.h. MAN TEMP switch................................................................. Off.i. EMER LTS switch................................................................ARM.j. Land as soon as practical.

14. Land as soon as possible.

Descent checks:15. Pressurization .... LNDG ALT set (LNDG ALT display is available on

summary page using FRMT button on display control panel).16. Standby Altimeter ............................................................................Set.17. Passengers Briefed/Cabin Check.

Approach checks:18. Final approach speed ............................................................. VREF + 10

19. Normal Landing Distance..................................... .............Multiply by: 1.70 with Thrust Reversers 1.50 without Thrust Reversers.

20. L WSHLD/WINDOW switch .......As required (to defog left window).21. Approach setup and crew briefing ...................................... Complete.

Before landing checks:22. LANDING GEAR switch ...............................................................DN.23. FLAPS selector ........ ........................................................................30.24. EMER LTS switch...........................................................................ON.

L (R) BATT OVERHEAT (W)

1. Affected BATT switch................................................................. OFF.

2. Battery temperature ..................................................................Monitor.

If battery temperature increases: a. Land as soon as possible.

Yes

No

3/14/03

Challenger 300 EMERGENCY PROCEDURESEVACUATION


EMERGENCY EVACUATION

1. PARK/EMER BRAKE ................................................................. Set.2. EMER DEPRESS switch ............................................................. ON.3. L and R ENG, and APU FIRE switches................ Lift guard, push.4. L and R BATT switches .............................................................OFF.5. STBY INST switch ......................................................................OFF.

6. Evacuate the aircraft using the passenger door or the emergency exit.

3/14/03

Challenger 300 EMERGENCY PROCEDURESFLIGHT CONTROLS

Draft 2.8


OVERSPEED “OVERSPEED”

1. Thrust levers .............................................................................IDLE.2. Autopilot ...........................................................................Disconnect.3. FLIGHT SPOILERS lever .................................................... EMER.4. Level wings, then pitch up.

5. Stab Trim ................................................As required to raise the nose.

STALL on PFD “STALL”

1. Lower the pitch attitude to reduce angle-of-attack. 2. Thrust levers .................................................................................TO.3. Level the wings.

END

END

3/14/03

EMERGENCY PROCEDURES Challenger 300FLIGHT CONTROLS


PITCH AXIS UNCOMMANDED MOTION

1. Master disconnect switch (MSW) .............................Depress and hold.

NOTE: The following conditions will exist when the MSW switch is de-pressed:

- The autopilot will disengage.

- Stabilizer, configuration, Mach, aileron, and rudder trims will beinoperative while the switch is depressed.

- The stall pusher is inoperative while the switch is depressed.

2. Airspeed .....................................................Reduce to 0.XX MI or below.

If control force is relieved with MSW depressed:

a. STALL PUSHER switch ........................................................OFF.b. Flight Guidance Panel AP/YD DISC bar .............. PULL DOWN.c. Master disconnect switch (MSW) .................................... Release.

If Control force continues with MSW depressed:The malfuction is most likely a trim malfunction.a. STAB TRIM switch............................................................... SEC.b. Master disconnect switch (MSW) .................................... Release.c. Control Wheel Trim switch .......................................As Required.

If control force continues while on SEC Stab Trim:

d. Refer to PRI STAB TRIM FAIL procedure, Non-normal section.

If control force is relieved on SEC Stab Trim:(1) Do not use PRI STAB Trim.(2) Do not use Autopilot.

Yes

NoEND

Yes

No

END

3/14/03



ROLL OR YAW AXIS UNCOMMANDED MOTION

1. Master disconnect switch (MSW) .............................Depress and hold.

NOTE: The following conditions will exist when the MSW switch is de-pressed:

- The autopilot will disengage.

- Stabilizer, configuration, Mach, aileron, and rudder trims will beinoperative while the switch is depressed.

- The stall pusher is inoperative while the switch is depressed.

2. Airspeed..................................................... Reduce to 0.XX MI or below.

If control force is relieved with MSW depressed:

a. Flight Guidance Panel AP/YD DISC bar ..............PULL DOWN.b. Master disconnect switch (MSW).....................................Release.

If Control force continues with MSW depressed:The malfuction is most likely a trim malfunction.a. AIL and RUD Trim indications .......................................CHECK.b. Affected AIL or RUD circuit breaker................................. PULL.c. Master disconnect switch (MSW).....................................Release.

Yes

No

END

3/14/03



PITCH CONTROL JAM

1. PITCH DISCONNECT handle ............................... Pull and rotate.[PITCH DISCONNECT (S)]. The pilot will control the left elevatorand the copilot will control the right elevator.

2. Determine elevator without the jam and transition flight controlto that pilot.

a. Do not apply additional control force to a jammed control. b. Do not reconnect.


Descent Checks:4. Pressurization ..............................................................LNDG ALT set.5. WING ANTI-ICE switch ................................................... As required.6. L and R ENG ANTI-ICE switches..................................... As required.

Transition Level (or FL 180) Checks:7. Altimeters ............................................................................... Set pilot,

copilot and standby, and cross-check. 8. L and R LANDING light switches...................................................On.9. Cabin Check ......................................................................... Complete.

10. SMKG/BELTS switch.................................................. SMKG/BELTS.11. Fuel quantities and balance ........................................................Check.

Approach Checks:12. APU and Bleeds ...............................................................................Set.13. Final approach speed ................................................................... VREF.14. Normal landing distance ....................................................Multiply by:

1.15 without thrust reversers1.10 with thrust reversers.

15. Approach setup and crew briefing ....................................... Complete.

Before Landing Checks:16. LANDING GEAR switch ..............................................................DN.17. L LDG, NOSE LDG/TAXI, and R LDG light switches ...................On.18. FLAPS ............................................................................................. 30.

3/14/03



ROLL CONTROL JAM

1. ROLL DISCONNECT lever ...................................................... Pull.2. Determine the side without the jam and transfer control to that

pilot.

The jam is on the copilot’s side:

a. Do not use the copilot’s controls.b. Do not use aileron trim.c. Do not reconnect.d. Go to step 3.

(The jam is on the pilot’s side)a. ROLL SPOILERS switch ...................................................... OFF.b. Do not reconnect.


NOTE: Landing on a wide runway of sufficient length with minimumturbulence and crosswind is recommended.

Descent Checks:4. Pressurization .............................................................. LNDG ALT set.5. WING ANTI-ICE switch....................................................As required.6. L and R ENG ANTI-ICE switches .....................................As required.

Transition Level (or FL 180) Checks:7. Altimeters ...............................................................................Set pilot,

copilot and standby, and cross-check. 8. L and R LANDING light switches .................................................. On.9. Cabin Check .........................................................................Complete.

10. SMKG/BELTS switch ..................................................SMKG/BELTS.11. Fuel quantities and balance ........................................................ Check.

Approach Checks:12. APU and Bleeds............................................................................... Set.13. Final approach speed ............................................................ VREF + 5.14. Normal landing distance ................................................... Multiply by:


15. FLAPS TAWS WARN................................................................... OFF.16. Approach setup and crew briefing ........................................Complete.

Before Landing Checks:17. LANDING GEAR switch................................................................DN. 18. L LDG, NOSE LDG/TAXI, and R LDG light switches .................. On.19. FLAPS ............................................................................................. 30.

Yes

No

3/14/03



YAW CONTROL JAM

1. Use asymmetric thrust if required to minimize sideslip.2. Airspeed .......................... Reduce as necessary to control the aircraft.3. Land as soon as possible.

NOTE: - Landing on a wide runway of sufficient length with minimumturbulence and crosswind is recommended.

- Use asymmetric power if required to minimize sideslip.

- Flying the approach with minimum control and throttle inputswill help maintain directional control.

Descent Checks:4. Pressurization ..............................................................LNDG ALT set.5. WING ANTI-ICE switch ................................................... As required.6. L and R ENG ANTI-ICE switches..................................... As required.


copilot and standby, and cross-check. 8. L and R LANDING light switches...................................................On.9. Cabin Check ......................................................................... Complete.

10. SMKG/BELTS switch.................................................. SMKG/BELTS.11. Fuel quantities and balance ........................................................Check.

Approach Checks:12. APU and Bleeds ...............................................................................Set.13. Final approach speed .............................................................VREF + 5.14. Normal landing distance ....................................................Multiply by:

1.20 without thrust reversers.1.15 with thrust reversers.

15. TAWS WARN FLAPS ...................................................................OFF.16. NWS switch....................................................................................OFF.17. Approach setup and crew briefing ....................................... Complete.

Before Landing Checks:18. LANDING GEAR switch ...............................................................DN. 19. L LDG, NOSE LDG/TAXI, and R LDG light switches ...................On.20. FLAPS ..............................................................................................30.21. EICAS ........................................................................................Check.22. Carry power down to touchdown to aid in directional control.

NOTE: Thrust reversers may be used. Stow the thrust reversers ifdirectional control is lost.

3/14/03

Challenger 300 EMERGENCY PROCEDURESHYDRAULICS


HYD PRESS LOW (W)1. L and R HYDRAULIC PUMP switches .........................................ON.

Hydraulic pressure is restored:

a. Land as soon as practical.

a. Autopilot ..................................................................... Disconnect.b. Airspeed ......................................... 250 KIAS/0.75 MI maximum.c. L and R HYDRAULIC PUMP switches .................................Off.d. L and R HYDRAULIC SOV switches .............................. Closed.

NOTE: The gear accumulator will retain pressure for 30 minutes after acomplete hydraulic failure. The landing gear must be down prior tothis time if the flaps are not at 0°.

e. Leave icing conditions as soon as possible.f. Land as soon as possible.

NOTE: Landing on a wide runway of sufficient length with minimum tur-bulence and crosswind is recommended.

Descent Checks:2. Pressurization .............................................................. LNDG ALT set.3. WING switch......................................................................As required.4. L and R ENG ANTI-ICE switches .....................................As required.


copilot and standby, and cross-check. 6. L and R LANDING light switches .................................................. On.7. Cabin Check ..........................................................................Complete.8. SMKG/BELTS switch ..................................................SMKG/BELTS.9. Fuel quantities and balance ........................................................ Check.

Approach Checks:10. APU and BLEEDS .......................................................................... Set.11. Final approach speed ................................. As listed for flaps attained:

Flaps 0 ........................................................................... VREF + 25Flaps 10......................................................................... VREF + 15Flaps 20......................................................................... VREF + 10Flaps 30.......................................................................... VREF + 5.

(Continued)

Yes

No

3/14/03

EMERGENCY PROCEDURES Challenger 300HYDRAULICS


HYD PRESS LOW (Cont)12. Normal landing distance.....................................................Multiply by:

Flaps 0......................................................................................2.55Flaps 10....................................................................................2.55Flaps 20....................................................................................2.35Flaps 30...................................................................................2.25.

13. FLAPS TAWS WARN ...................................................................OFF.14. Approach setup and crew briefing ....................................... Complete.

Before Landing Checks:15. LANDING GEAR switch ...............................................................DN. 16. LG PULL handle.........................................................................PULL.

NOTE: Performing a sideslip, to each side, may help achieve MLG down-lock. Increased airspeed may be required to ensure downlockduring sideslip.

17. LANDING GEAR indication..................................................... Check,for three green DN indications.

CAUTION: Do not stow handle until gear pins are installed.

18. L LDG, NOSE LDG/TAXI, and R LDG light switches ...................On.19. NWS switch....................................................................................OFF,

maintain directional control using differential braking.

After Touchdown:20. Normal brakes .............................................................Apply, using one

continuous application to a full stop.

3/14/03

Challenger 300 EMERGENCY PROCEDURESICE AND RAIN PROTECTION

Draft 2.8


WING ANTI-ICE LEAK (W)1. WING ANTI-ICE switch .............................................................Off.

2. Leave icing conditions as soon as possible.

If approach and landing must be made with any ice or suspected ice: a. Refer to Abnormal Landings, Wing Anti-Ice Failure Landing

procedure, Non-Normal procedures.

WARNING: Even small accumulations of ice on the wing leading edgecan cause an increase in stall speed, and possibly a degrada-tion in stall characteristics.

L (R) WING OVERHEAT (W)

1. WING ANTI-ICE switch .............................................................Off.

If L WING OVERHEAT:2. WING SOURCE switch ....................................................... FROM R.3. Go to step 4.

If R WING OVERHEAT:2. WING SOURCE switch ........................................................FROM L.3. AUTO SYNC switch ..................................................................... OFF.4. WING ANTI-ICE switch ................................................................ON.

If the message reappears:5. WING ANTI-ICE switch ................................................................Off.6. Leave icing conditions as soon as possible.

If approach and landing must be made with any ice or suspected ice: 7. Refer to Abnormal Landings, Wing Anti-Ice Failure Landing

procedure, Non-Normal procedures.

WARNING: Even small accumulations of ice on the wing leading edgecan cause an increase in stall speed, and possibly a degrada-tion in stall characteristics.

3/14/03

Challenger 300 EMERGENCY PROCEDURESLANDING GEAR, WHEEL AND BRAKES

Draft 2.8


GEAR (W) “GEAR”

NOTE: If the radio altimeter is inoperative, the “GEAR” aural may bemuted via the Master WARNING/CAUTION switch.

Is adequate time available to extend gear:

1. LANDING GEAR switch ...............................................................DN.

1. Execute a go-around.

GEAR BAY OVHT (W)1. AIRSPEED ....................................................... 250 KIAS maximum.2. LANDING GEAR switch..............................................................DN.

Wait 10 minutes:3. LANDING GEAR switch ................................................................UP.

If GEAR BAY OVHT occurs again:4. LANDING GEAR switch ...............................................................DN.5. Land as soon as possible.

NORM BRAKES FAIL (W) “NORMAL BRAKES FAIL”

1. Normal landing distance................................... ................. Multiply by: 1.50 without thrust reversers 1.35 with thrust reversers.

After landing:2. FLIGHT SPOILERS lever .................................................... EMER.3. PARK/EMER BRAKE handle ................................... Pull smoothly.

Yes

NoEND

END

END

3/14/03

Challenger 300 EMERGENCY PROCEDURESLANDING PROCEDURES


DITCHING

1. If time and conditions permit:a. Proceed to nearest land or vessel.b. Notify controlling agency.c. Transponder ....................................................... Emergency 7700.d. ELT switch ..............................................................................ON.e. Life Vests ................................................................................ On.

NOTE: Inform passengers not to inflate life vests while inside aircraft.

f. Shoulder harnesses ........................................................... Locked.g. Cabin .................................................................................. Check.h. SMKG/BELTS switch ..........................................SMKG/BELTS.

2. AURAL WARNING DCU A and DCU B switches ..................... OFF.3. TAWS circuit breaker (CB2 A6) ....................................................Pull.4. DITCHING switch ...................................................... Lift guard, ON.

NOTE: If DITCHING is selected above 15 000 ft, the switch ON legendand the DITCHING ON Status CAS message will not illuminate until the air-craft descends below 15 000 ft.

At approximately 2000 ft:Plan landing direction as follows:

a. Calm Sea .................................................................... Into winds.b. Moderate Swells ............................................... Parallel to swells.c. High Wind ...............................................Into wind, attempting to

land on upwind (far) side of swell.5. LANDING GEAR switch.................................................................UP.6. FLAPS ............................................................................................. 30.7. EMER LIGHTS switch ...................................................................ON.Just before contact:8. Plan to land slightly nose high. Perform normal power-on approach at

VREF and touchdown at the lowest possible airspeed with minimumsink rate. Do not decelerate below shaker speed.

9. Thrust levers .........................................................IDLE at touchdown.After contact:

10. L and R ENG, and APU FIRE switches .....................Lift guard, push.11. L and R BATT switches ................................................................ OFF.12. Emergency exit ........................................... Open after airplane comes

to a complete stop.

3/14/03

EMERGENCY PROCEDURES Challenger 300LANDING PROCEDURES


FORCED LANDING — BOTH ENGINES INOPERATIVE

1. If time and conditions permit:a. Notify the controlling agency.b. Transponder .......................................................Emergency 7700.c. ELT switch...............................................................................ON.d. APU and Bleeds .......................................................................Set.e. Cabin ..................................................................................Check.f. SMKG/BELTS switch .......................................... SMKG/BELTS.

2. TAWS circuit breaker (CB2 A6) .................................................... Pull.Before landing checks:3. LANDING GEAR switch .............................................................. DN.4. LG PULL handle.........................................................................PULL.5. FLAPS .............................................................................................30.6. EMER DEPRESS switch ...............................................................ON.7. Shoulder harnesses ...................................................................Locked.8. EMER LIGHTS switch ..................................................................ON.9. L and R ENG FIRE switches ........................... Lift guard, FIRE push.

10. Plan to land slightly nose high. Perform normal power-on approach atVREF and touchdown at the lowest possible airspeed with minimumsink rate. Do not decelerate below shaker speed.

After airplane comes to a complete stop:11. APU switch ....................................................................................OFF.12. PARK/EMER BRAKE ....................................................................Set.13. L and R ENG, and APU FIRE switches ...................... Lift guard, push.14. L and R BATT switches ................................................................OFF.15. STBY INST switch ........................................................................OFF.16. Evacuate the aircraft using the passenger door or the emergency exit.

3/14/03

Challenger 300 EMERGENCY PROCEDURESPOWERPLANT

Draft 2.8


L (R) ENGINE EXCEEDANCE (W)

Affected Engine:1. Thrust lever ........................................................................... Retard.

Engine responds:

a. Continue flight.

a. Affected ENGINE RUN switch ................................................ OFF.

Engine responds:

(1) Refer to Engine Shutdown in Flight procedure, Non-Normalprocedures.

(1) Affected ENG FIRE switch ....................... Lift guard, Push.(2) Refer to Engine Shutdown in Flight procedure, Non-Normal

procedures.

Yes

No

Yes

No

END

3/14/03

EMERGENCY PROCEDURES Challenger 300POWERPLANT


L (R) ENGINE FIRE (W) “LEFT (RIGHT) ENGINE FIRE”

DURING TAKEOFF

Below V1 Speed:

1. Thrust lever ............................................................................... IDLE.2. Brakes.......................................................Maximum, or as required.3. Thrust reversers ......................................................................Deploy.

After Stopping:4. Affected ENG FIRE switch ........................ Lift guard, FIRE push.5. FIRE EXT 1 switch .................................Lift guard, ARMED push.6. PARK/EMER BRAKE ................................................................. Set.7. EMER DEPRESS switch ..............................................................ON.8. Non-affected ENG and APU FIRE switches................... Lift guard,

ARMED push.9. L and R BATT switches .............................................................. OFF.

10. STBY INST switch ...................................................................... OFF.

11. Evacuate the aircraft using the passenger door or the emergency exit.

Above V1 Speed:

1. Rotate at VR.2. Pitch attitude................................ Adjust as required to achieve V2.

NOTE: Initially rotate toward the flight director pitch guidance command.Adjust pitch as required to maintain V2.

3. LANDING GEAR switch...................UP after positive rate of climb.4. Affected engine thrust lever ................. IDLE, unless a critical thrust

situation exists.5. ENG FIRE switch......................................... Lift guard, FIRE push.

After 10 seconds if L (R) ENGINE FIRE CAS persists or there areother indications of fire:a. FIRE EXT 1 switch .........................Lift guard, ARMED push.

b. Affected ENGINE RUN switch .............................................OFF.c. Affected FUEL PUMP switch.......................OFF, if not required.

After 30 seconds if L (R) ENGINE FIRE CAS persists or there are otherindications of fire:

(1) FIRE EXT 2 switch ......................Lift guard, ARMED push.

6. Climb at V2 until clear of obstacles, accelerate to V2 +10 (Flaps 10)[V2+15 (Flaps 20)], retract flaps, then climb at en route climb speed.

(Continued)

END

3/14/03



L (R) ENGINE FIRE (Cont)

7. Rudder trim.........................................................................As required.

8. Monitor fuel balance, transfer as required. FUEL PUMP may be used.


10. Refer to Single Engine Landing, Non-Normal procedures.

IN FLIGHT

Affected Engine:

1. Thrust lever ...............................................................................IDLE, unless a critical thrust situation exists.

2. ENG FIRE switch ........................................Lift guard, FIRE push.

After 10 seconds if L (R) ENGINE FIRE CAS persists or there areother indications of fire:a. FIRE EXT 1 switch......................... Lift guard, ARMED push.

b. Affected ENGINE RUN switch............................................. OFF.c. Affected FUEL PUMP switch ...................... OFF, if not required.

After 30 seconds if L (R) ENGINE FIRE CAS persists or thereare other indications of fire:(1) FIRE EXT 2 switch .............................................. Lift guard,

ARMED push.3. Rudder trim ........................................................................As required.4. Monitor fuel balance. Transfer as required. Fuel PUMP may be used.5. Land as soon as possible.6. Refer to Single Engine Landing, Non-Normal procedures.

3/14/03



L (R) ENG OIL PRESS LOW (W)ENG OIL PRESS LOW CAS is displayed and L (R) OIL PRESS digits arered:

1. Affected thrust lever........................................................................Idle.2. Affected ENGINE RUN switch .....................................................OFF.3. Refer to Engine Shutdown in Flight, Non-Normal procedures.

Only the L (R) OIL PRESS digits are red:1. Affected engine OIL TEMP........................................................Check.

OIL TEMP is high:

a. Affected thrust lever ................................................................Idle.b. Affected ENGINE RUN switch .............................................OFF.c. Refer to Engine Shutdown in Flight, Non-Normal procedures.

a. OIL PRESS and OIL TEMP ............................................Monitor.The most likely problem is a single pressure sensor failure.

Yes

No

Yes

No

END

3/14/03



L (R) REVERSER UNSAFE (W) REV EI During Takeoff

Below V1 Speed:

1. Thrust levers .............................................................................IDLE.2. Brakes .......................................................Maximum or as required.3. Thrust reversers.......................................................................Deploy.

Above V1 Speed:

1. Rotate at VR.2. Pitch attitude ................................ Adjust as required to achieve V2.


3. LANDING GEAR switch...................UP after positive rate of climb.4. Affected engine thrust lever..................IDLE, unless a critical thrust

situation exists.5. ENG FIRE switch .........................................Lift guard, FIRE push.

After 10 seconds if L (R) ENGINE FIRE CAS persists or there areother indications of fire:a. FIRE EXT 1 switch......................... Lift guard, ARMED push.

b. Affected ENGINE RUN switch............................................. OFF.c. Affected FUEL PUMP switch ...................... OFF, if not required.

After 30 seconds if L (R) ENGINE FIRE CAS persists or there are otherindications of fire:

(1) FIRE EXT 2 switch...................... Lift guard, ARMED push.

6. Climb at V2 until clear of obstacles, accelerate to V2 + 23 (Flaps 10)[V2 + 30 (Flaps 20)], retract flaps, then climb at en route climb speed.

Other indications of thrust reverser deployment are present (buffeting or excessive pitch, roll, or yaw):

a. ENGINE RUN switch (deployed engine).............................. OFF.b. Rudder Trim ...............................................................As required.c. Affected BLEED switch ....................................................... OFF.d. XBLEED switch ..................................................................Open.e. Affected ENG ANTI-ICE switch........................................... OFF.f. Monitor fuel balance. Transfer as required.g. Land as soon as possible.h. Go to Thrust Reverser Deployed Landing procedure.

a. Thrust levers .............................................................. As required.(Continued)

Yes

No

3/14/03



L (R) REVERSER UNSAFE (Cont)

In Flight

1. Thrust lever (deployed engine) ...................................................IDLE.2. Airspeed ...........................................................XXX KIAS maximum.

Other indications of thrust reverser deployment are present (buffeting or excessive pitch, roll, or yaw):

3. ENGINE RUN switch (deployed engine) ......................................OFF.4. Rudder Trim ...................................................................... As required.5. Affected BLEED switch ................................................................OFF.6. XBLEED switch .......................................................................... Open.7. Affected ENG ANTI-ICE switch ...................................................OFF.8. Monitor fuel balance. Transfer as required.9. Land as soon as possible.

10. Go to Thrust Reverser Deployed Landing procedure below.

3. Thrust levers as required.

THRUST REVERSER DEPLOYED LANDING

WARNING: Go-around may not be possible with a deployed thrustreverser.


Descent Checks:1. Pressurization ..............................................................LNDG ALT set.2. WING switch...................................................................... As required.3. L and R ENG ANTI-ICE switches..................................... As required.

(Continued)

Yes

No

END

3/14/03



L (R) REVERSER UNSAFE (Cont)


copilot and standby, and cross-check. 5. L and R LANDING light switches .................................................. On.6. Cabin Check .........................................................................Complete.7. SMKG/BELTS switch ..................................................SMKG/BELTS.8. Fuel quantities and balance ........................................................ Check.

Approach Checks:9. APU and Bleeds............................................................................... Set.

10. Final approach speed ...................................................................VREF.11. Normal landing distance....................... ............................. Multiply by:

1.15 without thrust reversers 1.10 with thrust reversers.

12. Approach setup and crew briefing ........................................Complete.

Before Landing Checks:13. LANDING GEAR switch................................................................DN. 14. L LDG, NOSE LDG/TAXI, and R LDG light switches .................. On.15. FLAPS ............................................................................................. 30.

NOTE: After landing, use of the operative thrust reverser is allowable.

3/14/03



DUAL ENGINE FLAMEOUT

1. Crew Oxygen Masks (if above 14 000 ft)................................... Don.2. Best glide speed.................................................................... Establish.

3. Thrust levers ................................................................................IDLE.4. Engine RUN switches ....................................................................OFF.

Aircraft is above 20 000 ft:

5. Descend to below 30 000 ft.6. APU start:

a. APU switch ....................................................START and release.b. L and R BLEED switches ......................................................OFF.c. APU BLEED switch (above 20 000 ft) ..................................OFF.

7. Airspeed ............................................Increase to 250 KIAS or greater.8. FUEL panel:

a. XFER switch ......................................................................Closed.b. L and R PUMP switches ....................................................AUTO.

9. ENG ANTI-ICE switches................................................................ Off.10. ENGINE RUN switch (at 6% min N2) ...........................................ON.

Light off occurs within 20 seconds:

a. Other engine ......................................................................... Start.b. If only one engine is operating, refer to Engine Shutdown in

Flight, Non-Normal procedures.

a. ENGINE RUN switches .........................................................OFF.b. Attempt another windmill relight at a lower altitude or higher air-

speed, or establish best glide speed and descend below 20 000 ftfor starter assisted airstart (go to step 12).

Aircraft is below 20 000 ft:11. APU start:

a. APU switch ....................................................START and release.b. L and R BLEED switches ......................................................OFF.c. APU BLEED switch................................................................ON.d. XBLEED switch................................................................. OPEN.

(Continued)

Airplane Weight Best Glide SpeedXX 000 lbs XXX KIASXX 000 lbs XXX KIAS

Yes

Yes

No

No

3/14/03



DUAL ENGINE FLAMEOUT (Cont)

12. FUEL panel:a. XFER switch...................................................................... Closed.b. L and R PUMP switches .................................................... AUTO.

13. ENG ANTI-ICE switches ................................................................Off.14. ENGINE RUN switch .....................................................................ON.15. STARTER switch.......................................................................START.

Light off occurs within 20 seconds:

a. Other engine ..........................................................................Start.b. If only one engine is operating, refer to Engine Shutdown in

Flight, Non-Normal procedures.

a. ENGINE RUN switches ........................................................ OFF.b. Attempt another starter assisted airstart at a lower altitude or

higher airspeed, or refer to Ditching or Forced Landing — BothEngines Inoperative procedures, this chapter.

Yes

No

3/14/03



ENGINE FAILURE

During Takeoff

Below V1 Speed

1. Thrust levers ............................................................................. IDLE.2. Brakes .......................................................Maximum or as required.3. Thrust reversers .....................................................................Deploy.

Above V1 Speed

1. Rotate at VR.2. Pitch attitude ............................... Adjust as required to acheive V2.


3. LANDING GEAR switch...................UP after positive rate of climb.

4. Climb at V2 until clear of obstacles, accelerate to V2 + 23 (Flaps 10)[V2 + 30 (Flaps 20)], retract flaps, then climb at en route climb speed.

5. Refer to Engine Shutdown in Flight, Non-Normal procedures.

In Flight

1. Autopilot..............................................................................Disconnect.2. Thrust lever (operative engine) ............................Increase as required.3. Rudder Trim ...................................................................... As required.4. Refer to the following procedure as applicable:

a. Engine Shutdown in Flight, Non-Normal procedures.b. Single Engine Landing, Non-Normal procedures.c. Single Engine Go-Around, Non-Normal procedures.

3/14/03

Challenger 300 EMERGENCY PROCEDURESREJECTED TAKEOFF

Draft 2.8


REJECTED TAKEOFF

1. Thrust levers .............................................................................IDLE.2. Brakes .......................................................Maximum or as required.3. Thrust Reversers .....................................................................Deploy.

3/14/03

Challenger 300 EMERGENCY PROCEDURESSMOKE OR FIRE

Draft 2.8


CABIN/COCKPIT FIRE, SMOKE or FUMES

WARNING: In the event of smoke or fire, prepare to land without delaywhile completing fire suppression and/or smoke evacuation procedures.Whether or not smoke has dissipated, if it cannot be visibly verified that thefire has been extinguished following fire suppression and/or smoke evacua-tion procedures, land immediately at the nearest suitable airport.

1. Crew oxygen masks ..............................Don, select EMERGENCY.2. Smoke goggles ............................................................................. Don.3. Pilot and copilot MIC/MASK switches ...........................O2 MASK.

4. Pilot and copilot INPH switches ................................. INPH (enabled).5. PAX OXYGEN switch .................................................................. OFF.6. PAX OXYGEN THERAPEUTIC switch .......................................Off.7. EMER DEPRESS switch.............................................. Lift guard, ON.

If MANUAL PRESS is ON when EMER DEPRESS is selected, thecabin altitude may climb above 20 000 ft depending on aircraft alti-tude.

If cabin does not depressurize:a. MANUAL PRESS switch........................................................ON.b. MAN RATE control...........................................................Full up.

8. Descend as necessary but not below minimum safe altitude.9. Land as soon as possible.

Source is Known:

10. Extinguish fire using hand-held extinguisher or eliminate the source ofsmoke or fumes. If fire is extinguished and can visibly be verified, thepressurization and oxygen systems may be returned to normal.

(Continued)

Yes

No

END

3/14/03

EMERGENCY PROCEDURES Challenger 300SMOKE OR FIRE


CABIN/COCKPIT FIRE, SMOKE or FUMES (Cont)

Source is not known.

Electrical System Is Suspected Source

11. APU GEN switch ...........................................................................OFF.12. Autopilot.......................................................................DISCONNECT.13. EMER LTS switch..........................................................................OFF.14. R GEN switch.................................................................................OFF.15. R BATT switch...............................................................................OFF.16. BUS TIE switch ........................................................................... Open.

Smoke or fumes dissipate:

a. AIR SOURCE switch.............................................. PACK ONLY.b. WING SOURCE ANTI-ICE switch............................... FROM L.c. R BLEED switch ....................................................................OFF.d. TUNE REVERSION switch .....................................MFD ONLY.e. Transponder .............................................................. Select ATC1.f. Altitude......................................................... 25 000 ft maximum.g. Maintain airspeed at least XX knots above stall speed.

Descent Checks:h. Pressurization ......................................................LNDG ALT set.i. WING ANTI-ICE switch ...........................................As required.j. L and R ENG ANTI-ICE switches............................. As required.

Transition Level (or FL 180) Checks:k. Altimeters ........................Set pilot and standby, and cross-check.l. L and R LANDING light switches...........................................On.m. Cabin Check .................................................................. Complete.n. SMKG/BELTS switch .......................................... SMKG/BELTS.o. Fuel quantities and balance ................................................Check.

(Continued)

Smoke or fumes continue:

Bleed air system is suspected source

No

Yes

Yes

No

No

3/14/03





Smoke or fumes continue:

Smoke or fumes dissipate (Cont):Approach Checks:p. Final approach speed .......................................................... VREF .q. Normal landing distance ................................... Multiply by 1.65.r. Approach setup and crew briefing .................................Complete.

Before Landing Checks:s. LANDING GEAR switch........................................................DN.t. L LANDING light switch ........................................................ On.u. R HYDRAULIC PUMP switch...............................................ON.v. FLAPS ..................................................................................... 30.w. EMER LIGHTS switch............................................................ON.

Smoke or Fumes Continue:a. R BATT switch ........................................................................ON.b. R GEN switch ..........................................................................ON.

Transition to the standby instrument and magnetic compass untilthe AHRS realigns.

c. L GEN switch ........................................................................ OFF.d. L BATT switch....................................................................... OFF.e. STAB TRIM switch ............................................................... SEC.f. AIR SOURCE switch ...................................... TRIM AIR ONLY.g. WING SOURCE ANTI-ICE switch .............................. FROM R.h. Airspeed............ .............................. 185 KIAS/0.75 MI maximumi. TUNE REVERSION switch......... .............................MFD ONLY.j. Transponder.............................................................. .Select ATC2.k. Altitude ..........................................................25 000 ft maximum.l. Maintain airspeed at least XX knots above stall speed.m. Avoid excessive rudder inputs.

(Continued)

Bleed air system is suspected sourceNo

No

No

No

END

3/14/03





Smoke or Fumes Continue: (Cont)Descent Checks:n. Pressurization ......................................................LNDG ALT set.o. WING ANTI-ICE switch ...........................................As required.p. L and R ENG ANTI-ICE switches............................. As required.

Transition Level (or FL 180) Checks:q. Altimeters ..................... Set copilot and standby, and crosscheck. r. L and R LANDING light switches...........................................On.s. Cabin Check ................................................................. Complete.t. Fuel quantities and balance ................................................Check.

Approach Checks:u. Final approach speed ........................................................... VREF.v. Normal landing distance ....................................Multiply by 1.65.w. Approach setup and crew briefing ................................ Complete.

Before Landing Checks:x. LANDING GEAR switch .......................................................DN. y. NOSE LDG/TAXI, and R LDG light switches ........................On.z. L HYDRAULIC PUMP switch...............................................ON.aa. FLAPS ......................................................................................30.ab. EMER LIGHTS switch ...........................................................ON.


(Continued)

No

No

END

3/14/03





Bleed Air System Is Suspected Source

APU supplies bleed air:

a. XBLEED switch ................................................................ Closed.b. L BLEED switch......................................................................ON.c. APU BLEED switch .............................................................. OFF.d. R BLEED switch .....................................................................ON.

Smoke or fumes are eliminated:

(1) AIR SOURCE switch............................... TRIM AIR ONLY.


(a) AIR SOURCE switch...............................PACK ONLY.

Engines supply bleed air:a. R BLEED switch ................................................................... OFF. b. XBLEED switch ................................................................ Closed.


(1) R BLEED switch..............................................................ON.(2) L BLEED switch ............................................................ OFF.

(Continued)

No

Yes

Yes

No

No

Yes

No

END

Yes

No

END

END

END

3/14/03





(a) AIR SOURCE switch .......................TRIM AIR ONLY.


(i) AIR SOURCE switch........................ PACK ONLY.(ii) L BLEED switch ...............................................ON.

Yes

NoEND

Yes

NoEND

END

3/14/03



LAV SMOKE (W)WARNING: In the event of smoke or fire, prepare to land without delaywhile completing fire suppression and/or smoke evacuation procedures.Whether or not smoke has dissipated, if it cannot be visibly verified that thefire has been extinguished following fire suppression and/or smoke evacua-tion procedures, land immediately at the nearest suitable airport.

1. Crew oxygen masks................................... Don, select EMERGENCY.2. Smoke goggles............................................................................... Don.3. Pilot and copilot MIC/MASK switch .................................. O2 MASK.4. Pilot and copilot INPH switches.................................................. INPH.5. PAX OXYGEN switch .................................................................. OFF.6. PAX OXYGEN THERAPEUTIC switch ........................................Off.7. CABIN DC and AC POWER........................................................ OFF.8. EMER DEPRESS switch.............................................. Lift guard, ON.

Designated Crewmember:

9. Protective breathing equipment ..................................................... Don.10. Fire extinguisher ........................................................... Prepare for use.11. Fire or smoke source............................................................ Extinguish.12. Land as soon as possible.

CARGO SMOKE (W)

WARNING: In the event of smoke or fire, prepare to land without delaywhile completing fire suppression and/or smoke evacuation procedures.Whether or not smoke has dissipated, if it cannot be visibly verified that thefire has been extinguished following fire suppression and/or smoke evacua-tion procedures, land immediately at the nearest suitable airport.

1. Crew oxygen masks................................... Don, select EMERGENCY.2. Smoke goggles............................................................................... Don.3. Pilot and copilot MIC/MASK switch .................................. O2 MASK.4. Pilot and copilot INPH switches.................................................. INPH.5. PAX OXYGEN switch .................................................................. OFF.6. PAX OXYGEN THERAPEUTIC switch ........................................Off.7. CABIN DC and AC POWER........................................................ OFF.8. EMER DEPRESS switch.............................................. Lift guard, ON.

Designated Crewmember:

9. Protective breathing equipment ..................................................... Don.10. Fire extinguisher ........................................................... Prepare for use.11. Fire or smoke source............................................................ Extinguish.12. Land as soon as possible.

3/14/03

Challenger 300 EMERGENCY PROCEDURESTAKEOFF CONFIGURATION WARNINGS

Draft 2.8


CONFIGURATION WARNING “CONFIGURATION”

CONFIG AILERON TRIM (W)CONFIG AUTOPILOT (W)CONFIG FLAPS (W)CONFIG RUDDER TRIM (W)CONFIG SPOILERS (W)CONFIG STAB TRIM (W)

1. Thrust levers ................................................................................Idle.2. Brakes ........................................................Maximum or as required.3. Thrust reversers.......................................................................Deploy.

4. After stopping, takeoff configuration ......................................... Check.

PARK/EMER BRAKE ON (W) “CONFIGURATION”

1. Thrust levers .............................................................................IDLE.2. Brakes .......................................................Maximum or as required.3. Thrust reversers ......................................................................Deploy.

4. PARK/EMER BRAKE handle..................................................Release.

END

END

3/14/03

EMERGENCY PROCEDURES Challenger 300TAKEOFF CONFIGURATION WARNINGS


PITCH DISCONNECT (W)1. Thrust levers ................................................................................ Idle.2. Brakes........................................................Maximum or as required.3. Thrust reversers ......................................................................Deploy.

4. After stopping....................................................Align control columns.5. Pull and rotate PITCH DISC handle to release and push to full stow

position.6. Verify PITCH DISCONNECT CAS extinguishes. Slight movement of

the control columns may be required to reconnect the controls.

ROLL DISCONNECT (W)

1. Thrust levers ................................................................................ Idle.2. Brakes........................................................Maximum or as required.3. Thrust reversers ......................................................................Deploy.

4. After stopping...................................................... Align control wheels.5. Release the small locking lever and push the ROLL DISC lever for-

ward.6. Verify ROLL DISCONNECT CAS extinguishes. Slight movement of

the control wheels may be required to reconnect the controls.

END

END

3/14/03

Challenger 300 NORMALTABLE OF CONTENTS

Draft 2.8
GENERAL ............................................................................ 04-01-01

EXTERIOR PREFLIGHT ...................................................... 04-02-01

Exterior Safety Check/Walkaround ................................ 04-02-01CABIN PREFLIGHT ............................................................. 04-02-01

BEFORE STARTING ENGINES .......................................... 04-02-01

STARTING ENGINES .......................................................... 04-03-01

BEFORE TAXI ..................................................................... 04-03-01

TAXI AND BEFORE TAKEOFF ........................................... 04-03-02

RUNWAY LINEUP ............................................................... 04-03-02

AFTER TAKEOFF ................................................................ 04-04-01

CLIMB .................................................................................. 04-04-01

DESCENT ............................................................................ 04-04-01

APPROACH ......................................................................... 04-04-02

BEFORE LANDING ............................................................. 04-04-02

GO AROUND ....................................................................... 04-04-02

LANDING ............................................................................. 04-05-01

AFTER LANDING/CLEARING RUNWAY ........................... 04-05-01

SHUTDOWN ........................................................................ 04-05-01

3/14/03

Challenger 300 NORMAL PROCEDURESINTRODUCTION


3/14/03

GENERAL

This section contains those procedures which may be considered routine in

day-to-day operations.

Draft 2.8

Challenger 300 NORMAL PROCEDURES

Draft 2.8


EXTERIOR PREFLIGHT

EXTERIOR SAFETY CHECK/WALKAROUND

1. Exterior Safety Check/Walkaround ............Accomplish in accordance with FCOM Vol. 1.

CABIN PREFLIGHT

1. Cabin furnishings ...................................................................... Secure.2. Emergency exit ........................... Aisle clear and handle unobstructed.

Remove and stow aft emergency exit door security pin.

BEFORE STARTING ENGINES

1. Circuit breakers (CB1 and CB2) ..................................................... Set.2. Seats, safety harnesses .............................................................. Secure.3. Crew oxygen masks and smoke goggles ....................... Check oxygen

flow available. Masks and smoke goggles properly stowed.4. LANDING GEAR switch................................................................DN.5. L, R, and AUX HYDRAULIC PUMP switches ........................... OFF.6. AIR SOURCE switch .................................................................... OFF.7. Electrical panel ................................................................................ Set.8. L and R Cockpit lights .................................................................... Set.9. APU and Bleeds.............................................................................. Set.

10. SYSTEM TEST/RESET panel:a. ANNUN A ..............................................................................Test.b. ANNUN B ..............................................................................Test.c. PROBES .................................................................................Test.d. STALL/RUD LIM ..................................................................Test.

11. L and R rudder pedals ................................................................Adjust.12. L and R audio panels ...................................................................... Set.13. Fuel quantity ............................................................................... Check.14. Standby Instrument .................................................................... Check.15. Clock............................................................................ Zero flight time.16. TAWS WARN TERRAIN switch .................................................. OFF.17. NWS switch................................................................................... OFF.18. L and R FUEL PUMP switches................................................. AUTO.19. FMS ....................................................................................... Initialize.20. REVERSION panel ................................................................. NORM.21. AIR COND/BLEED panel ......................................................... Check.22. ANTI-ICE panel .............................................................................Test.23. PRESSURIZATION panel ......................................................... Check.

a. Landing altitude ....................................................................... Set.24. LIGHTING panel ................................................................ As desired.

3/14/03

NORMAL PROCEDURES Challenger 300


BEFORE STARTING ENGINES (Cont)

25. Gust lock ...................................................................................Stowed.26. Hydraulic panel .................................................................... Check/Set.27. Trim system.......................................................................... Check/Set.28. ELT...............................................................................................ARM.29. CABIN DC and AC PWR switches ................................................ON.30. PAX OXYGEN switch...............................................................AUTO.31. Altimeters .........................................................................................Set.32. Avionics ...........................................................................................Set.33. Takeoff data (V1, VR, V2, TO pitch and distance) .............. Computed

and speeds set (refer to Performance chapter).34. CAS messages .............................................................................Check.

3/14/03


Draft 2.8


STARTING ENGINES

Engine starts may be made by using the APU, an external air source, orcrossbleed from the other engine.

WARNING: Maintain a safe distance from the engine outlets at all timesduring engine operation. Airflow into the turbofan engine issufficient to draw personnel and equipment into the engineinlet.

NOTE: Ensuring ITT is below 350 °C (cranking if necessary) will reducethe possibility of a hot start.

1. Passenger door .......................................................................... Closed.2. PARK/EMER BRAKE handle........................................................ Set.3. Thrust levers ............................................................................... IDLE.4. STROBE switch .......................................................................... BCN.5. IGNITION switch ...........................................................................ON.6. Engine(s)........................................................................................Start.7. Generators....................................................................... Check on line.

BEFORE TAXI

1. FLAPS selector........................................................................ 10 or 20.2. Flight controls ............................................................................ Check.3. FLIGHT SPOILERS lever..........................................Check extension.4. GND SPOILERS ........................................................................ Check.5. Yaw damper .................................................................................... On.6. EICAS ........................................................................................ Check.7. ANTI-ICE panel ................................................ Checked/As required.8. Cabin check .......................................................................... Complete.9. Aircraft lighting ..................................................................As required.

10. SMKG/BELTS switch ..................................................SMKG/BELTS.11. NWS switch.....................................................................................ON.12. PARK/EMER BRAKE handle................................................. Release.

3/14/03



TAXI AND BEFORE TAKEOFF

1. Brakes and nose wheel steering .................................................Check.2. Flight instruments .......................................................................Check.3. Thrust reversers ..........................................................................Check.

NOTE: If thrust levers are moved during thrust reverser deployment orstow transitions, a REVERSER FAIL (C) message may be dis-played and the throttle may be locked at idle.

4. Engine instruments and N1 bugs .................................................Check,verify that the left and right bugs agree within 1%.

5. Takeoff data (V1, VR, V2, TO PITCH, Distance) .......................Check.6. Nav equipment ............................................................................Check.7. Crew takeoff briefing ............................................................ Complete.8. Radar/terrain....................................................................... As required.9. Transponder......................................................................................On.

10. ANTI-ICE panel ................................................................. As required.

NOTE: If WING ANTI-ICE is to be on for takeoff, it must be selected onat least 10 seconds prior to setting TO thrust.

RUNWAY LINEUP

1. L and R PROBES switches ..............................................................On.2. L LDG, N LDG-TAXI, and R LDG light switches .........................On.3. STROBE switch .................................................................... STROBE.4. CAS ..................................................................... Checked and cleared.

3/14/03


Draft 2.8


AFTER TAKEOFF

1. LANDING GEAR switch.....................UP after positive rate of climb.2. FLAPS ..................................0 at V2+23 (flaps 10); V2+30 (flaps 20).3. N LDG-TAXI light switch ............................................................ OFF.4. ANTI-ICE panel .................................................................As required.

CLIMB

1. Thrust levers ..................................................................................CLB.

10 000 ft Checks:2. SMKG/BELTS switch ........................................................As required.3. APU and Bleeds............................................................................... Set.4. Pressurization.............................................................................. Check.

Transition Altitude (or 18 000 ft) Checks:5. Altimeters ....................................................................................... Set. 6. L and R LANDING light switches ................................................ OFF.

DESCENT

1. Pressurization .............................................................. LNDG ALT set.2. ANTI-ICE panel .................................................................As required.


copilot and standby, and cross-check. 4. L and R LANDING light switches .................................................. On.5. Cabin Check ..........................................................................Complete.6. SMKG/BELTS switch ..................................................SMKG/BELTS.7. Fuel Quantities and Balance ...................................................... Check.

3/14/03



APPROACH

1. APU and Bleeds ...............................................................................Set.2. Landing data (VREF, VGA, Distance)................................................Set.3. Approach setup and crew briefing ........................................ Complete.

NOTE: When conducting a localizer backcourse approach, the TAWSWARN GS switch should be selected OFF to prevent nuisanceglideslope aural warnings.

BEFORE LANDING

1. LANDING GEAR switch ...............................................................DN.2. L LDG, N LDG -TAXI, and R LDG light switches ........................On.3. FLAPS.............................................................................................. 30.

GO-AROUND

1. Autopilot ......................................Disengaged with the TO/GA button.2. Thrust levers ................................................................................... TO.3. FLAPS...............................................................................................10.4. LANDING GEAR switch ............................................................... UP.5. Climb at VGA or above.6. When clear of obstacles, accelerate to VGA+ 23 and retract flaps.7. Pressurization ...............................................................LNDG ALT set.

3/14/03


Draft 2.8


LANDING

1. Brakes ................................................................................As required.2. Thrust reversers .................................................................. As desired.

AFTER LANDING/CLEARING RUNWAY

1. Transponder ................................................................................STBY.2. L and R PROBES switches .......................................................... OFF.3. ANTI-ICE panel .................................................................As required.4. Lighting .............................................................................. As desired.5. FLAPS ................................................................................. As desired.

SHUTDOWN

1. PARK/EMER BRAKE and chocks ................................................ Set.2. NWS switch................................................................................... OFF.3. L and R WSHLD/WINDOW switches ......................................... OFF.4. EMER LIGHTS switch ................................................................. OFF.5. IGNITION switch............................................................................Off.6. ENG RUN switches ...................................................................... OFF.7. STROBE light switch ................................................................... OFF.8. HYDRAULIC panel ...........................................................As required.9. Gust lock ......................................................................................... Set.

10. COCKPIT LIGHTS............................................................. As desired.11. APU BLEED switch ...................................................................... OFF.12. APU switch.................................................................................... OFF.13. NAV light switch ........................................................................... OFF.14. STBY INST switch........................................................................ OFF.15. L and R BATT switches ................................................................ OFF.

3/14/03

Challenger 300 NON-NORMAL PROCEDURESTABLE OF CONTENTS

Draft 2.8


CAUTION Table of Contents ................................................. 05-10-01

ADVISORY Table of Contents............................................... 05-40-01

3/14/03


Draft 2.8


AIR CONDITIONING & PRESSURIZATION 05-12-01

AIR COND TEMP FAIL (C) .................................................. 05-12-01

AIR COND TEMP HIGH (C) ................................................. 05-12-01

AUTO PRESS FAIL (C) ........................................................ 05-12-02

L (R) BLEED FAIL (C) .......................................................... 05-12-02

L (R) BLEED LOOP FAIL (C) ............................................... 05-12-03

CABIN ALTITUDE (C) .......................................................... 05-12-03

CABIN PRESS FAULT (C) .................................................... 05-12-03

DITCHING NOT AVAIL (C) ................................................... 05-12-04

EQPT RACK TEMP HIGH (C) .............................................. 05-12-04

OXYGEN QUANTITY LOW (C) ............................................ 05-12-04

OXYGEN VALVE CLOSED (C) ............................................ 05-12-04

PACK FAIL (C) ..................................................................... 05-12-05

PACK LOOP FAIL (C) .......................................................... 05-12-05

PACK TEMP HIGH (C) ......................................................... 05-12-05

PAX OXYGEN AUTO FAIL (C) ............................................ 05-12-06

L (R) PYLON LOOP FAIL (C) ............................................... 05-12-06

TRIM AIR FAIL (C) ............................................................... 05-12-06

TRIM AIR LOOP FAIL (C) .................................................... 05-12-07

XBLEED FAIL (C) ................................................................. 05-12-07

3/14/03

NON-NORMAL PROCEDURES Challenger 300TABLE OF CONTENTS


AUTO FLIGHT 05-14-01

AFCS MESSAGE FAIL (C) 05-14-01

AP HOLDING LWD (C)AP HOLDING RWD (C)AP HOLDING NOSE DOWN (C)AP HOLDING NOSE UP (C)..................................................05-14-01

AP STAB TRIM FAIL (C) .......................................................05-14-01

FD MODE CHANGE (C) ........................................................05-14-01

YAW DAMPER FAIL (C) .......................................................05-14-01

AUTOPILOT DISCONNECT aural.........................................05-14-02


APU BLEED ALT LIMIT (C) ..................................................05-15-01

APU FUEL SOV FAIL (C) .....................................................05-15-01

APU OVERSPEED (C) .........................................................05-15-01

APU OIL PRESS LOW (C) ...................................................05-15-02

APU OIL TEMP HIGH (C) .....................................................05-15-02

APU STARTER FAIL ON (C) ................................................05-15-02

AVIONICS 05-17-01

AIR DATA 1 (2) FAULT (C)....................................................05-17-01

EFIS COMPARATOR INOP (C) ...........................................05-17-01

EFIS MISCOMPARE (C) ......................................................05-17-01

L (R) IAPS FAIL (C) ..............................................................05-17-02

PFD X-TALK FAIL (C) ...........................................................05-17-02

AIR DATA COMPUTER (ADC) FAILURE — SINGLE...........05-17-02

AIR DATA COMPUTER (ADC) FAILURE — DUAL ..............05-17-02

ATTITUDE/HEADING COMPUTER (AHC) FAILURE ...........05-17-02

CDU FAILURE.......................................................................05-17-03

DCU A AND DCU B FAILURE...............................................05-17-03

ERRONEOUS PITOT-STATIC INDICATION ........................05-17-03

MFD FAILURE.......................................................................05-17-04

PFD FAILURE........................................................................05-17-04

RADIO ALTITUDE FAILURE.................................................05-17-04

RADIO TUNING FAILURE.....................................................05-17-04

TCAS AURALS......................................................................05-17-05

TAWS AURALS .....................................................................05-17-06

3/14/03



DOORS 05-18-01

AFT EQPT BAY DOOR (C) .................................................. 05-18-01

BATTERY BAY DOOR (C) ................................................... 05-18-01

CARGO DOOR (C) ............................................................... 05-18-01

EMERGENCY EXIT (C) ....................................................... 05-18-01

PASSENGER DOOR (C) ...................................................... 05-18-02

ELECTRICAL 05-19-01

APU GEN FAIL (C) ............................................................... 05-19-01

APU GEN OVERLOAD (C) .................................................. 05-19-01

L (R) BATT FAIL (C) ............................................................. 05-19-01

ELECTRICAL FAULT (C) ..................................................... 05-19-01

L (R) GEN FAIL (C) .............................................................. 05-19-01

L (R) ESS BUS FAIL (C) ...................................................... 05-19-02

L (R) GEN OVERLOAD (C) .................................................. 05-19-02

L (R) MAIN BUS FAIL (C) ..................................................... 05-19-03

FIRE PROTECTION 05-21-01

APU FIRE DET FAIL (C) ...................................................... 05-21-01

CARGO SMOKE DET FAIL (C) ............................................ 05-21-01

L (R) FIRE DET FAIL (C) ...................................................... 05-21-01

FIRE SYS FAULT (C) ........................................................... 05-21-01

FIREX APU SQUIB FAIL (C) ................................................ 05-21-02

GEAR BAY DET FAIL (C) .................................................... 05-21-02

3/14/03



FLIGHT CONTROLS 05-23-01

ELEVATOR SPLIT (C) ..........................................................05-23-01

FLAPS FAIL (C) ....................................................................05-23-01

FLAPS FAULT (C) ................................................................05-23-02

FLAPS NORM PRESS LOW (C) ..........................................05-23-03

FLT SPOILERS DEPLOY (C) ...............................................05-23-03

FLT SPOILERS FAIL (C) ......................................................05-23-03

FLT SPOILERS FAULT (C) ..................................................05-23-03

GND SPLRS NOT ARMED (C) .............................................05-23-03

GND SPOILERS FAIL (C) ....................................................05-23-04

MACH TRIM FAIL (C) ...........................................................05-23-04

PRI STAB TRIM FAIL (C) .....................................................05-23-05

ROLL SPOILERS FAIL (C) ...................................................05-23-07

ROLL SPOILERS FAULT (C) ...............................................05-23-07

ROLL SPOILERS OFF (C) ...................................................05-23-07

RUDDER LIMITER FAIL (C) .................................................05-23-07

SEC STAB TRIM FAIL (C) ....................................................05-23-08

SPOILERS FAIL (C) .............................................................05-23-08

SPOILERS FAULT (C) ..........................................................05-23-08

STALL PROTECT FAIL (C) ..................................................05-23-09

STALL PUSHER OFF (C) .....................................................05-23-09

FUEL 05-24-01

L (R) FUEL COLLECTOR LOW (C).......................................05-24-01

FUEL IMBALANCE (C) ..........................................................05-24-01

L (R) FUEL PRESS LOW (C) ...............................................05-24-02

L (R) FUEL PUMP FAIL (C) ..................................................05-24-03

FUEL QUANTITY FAIL (C) ...................................................05-24-03

FUEL QUANTITY LOW (C) ..................................................05-24-03

WING FUEL TEMP LOW (C) ................................................05-24-03

3/14/03



HYDRAULICS 05-25-01

AUX HYD TEMP HIGH (C) ................................................... 05-25-01

L (R) HYD PRESS LOW (C) ................................................. 05-25-01

HYD PTU FAIL (C) ............................................................... 05-25-03

L (R) HYD SOV FAIL (C) ...................................................... 05-25-03

L (R) HYD TEMP HIGH (C) .................................................. 05-25-04

ICE & RAIN PROTECTION 05-27-01

L (R) AOA VANE HEAT FAIL (C) ......................................... 05-27-01

ICE DETECTED (C) ............................................................. 05-27-01

ICE DETECTOR FAIL (C) .................................................... 05-27-01

L (R) ENG ANTI-ICE FAIL (C) .............................................. 05-27-01

L (R) PITOT HEAT FAIL (C) ................................................. 05-27-02

L (R) PROBE HEAT OFF (C) ............................................... 05-27-02

STBY PITOT HEAT FAIL (C) ............................................... 05-27-03

L (R) STBY STAT HT FAIL (C) ............................................. 05-27-03

L (R) WINDOW HEAT FAIL (C) ............................................ 05-27-03

L (R) WING A/I PRESS HI (C) .............................................. 05-27-04

WING A/ICE LOOP FAIL (C) ................................................ 05-27-04

L (R) WING A/ICE FAIL (C) .................................................. 05-27-05

WING ANTI-ICE FAULT (C) ................................................. 05-27-06

L (R) WSHLD HEAT FAIL (C) .............................................. 05-27-06

CRACKED, SHATTERED, DELAMINATED, OR ARCING WIND-SHIELD OR WINDOW...................................................... 05-27-06

ENGINE ICE INGESTION ..................................................... 05-27-07

3/14/03



LANDING GEAR, WHEEL & BRAKE SYSTEM 05-28-01

BRAKE FAULT (C) ...............................................................05-28-01

CPLT BRAKE FAULT (C) .....................................................05-28-01

GEAR DISAGREE (C) ..........................................................05-28-01

GEAR SYS FAIL (C) .............................................................05-28-01

L (R) INBD BRAKE FAIL (C) .................................................05-28-02

INBD BRAKE PRESS LO (C) ...............................................05-28-02

INBD BRAKES FAIL (C) .......................................................05-28-02

NOSE GEAR DOOR (C) .......................................................05-28-02

NWS FAIL (C) .......................................................................05-28-02

NWS LIMIT EXCEEDED (C) .................................................05-28-02

L (R) OUTBD BRAKE FAIL (C) .............................................05-28-03

OUTBD BRAKE PRESS LO (C) ...........................................05-28-03

OUTBD BRAKES FAIL (C) ...................................................05-28-03

PARK/EMER BRAKE ON (C) ...............................................05-28-03

PK/EMER BRK PRESS LO (C) ............................................05-28-04

PLT BRAKE FAULT (C) ........................................................05-28-04

WOW FAIL (C) ......................................................................05-28-04

LANDING GEAR MANUAL EXTENSION..............................05-28-04

LANDING PROCEDURES 05-29-01

SINGLE-ENGINE LANDING..................................................05-29-01

WING ANTI-ICE FAILURE LANDING....................................05-29-02

3/14/03



MISCELLANEOUS SYSTEMS 05-30-01

EMER LIGHTS OFF (C) ....................................................... 05-30-01

EMER LIGHTS ON (C) ......................................................... 05-30-01

POWER PLANT 05-30-01

L (R) ENGINE FLAMEOUT (C) ............................................ 05-32-01

ENGINES FUEL BYPASS (C) .............................................. 05-32-01

L (R) ENGINE VIBRATION (C) ............................................ 05-32-01

L (R) ENGINE FUEL SOV FAIL(C) ...................................... 05-32-01

L (R) ENG OIL PRESS HIGH (C) ......................................... 05-32-01

L (R) ENG OIL TEMP HIGH (C) ........................................... 05-32-02

L (R) FADEC FAIL (C) .......................................................... 05-32-03

L (R) REVERSER FAIL (C) .................................................. 05-32-03

L (R) START ABORTED (C) ................................................ 05-32-03

L (R) STARTER FAIL (C) ..................................................... 05-32-04

L (R) STARTER FAIL ON (C) ............................................... 05-32-04

ENGINE SHUTDOWN IN FLIGHT ........................................ 05-32-05

ENGINE AIRSTART ............................................................. 05-32-06

AUTO MODE AIRSTART ENVELOPE (FIG. 05-32-01)........ 05-32-07

SINGLE ENGINE GO AROUND ........................................... 05-32-08

3/14/03

Challenger 300 NON-NORMAL PROCEDURESAIR CONDITIONING & PRESSURIZATION

Draft 2.8


AIR COND TEMP FAIL (C)

1. MAN TEMP switch.........................................................................ON.2. COCKPIT and CABIN COLD-HOT knobs ........................ As desired.

AIR COND TEMP HIGH (C)

1. AIR SOURCE switch .....................................................PACK ONLY.

Airflow into Cockpit/Cabin stops:

2. AIR SOURCE switch .............................................. TRIM AIR ONLY.3. Altitude ..................................................................35 000 ft maximum.4. COCKPIT and CABIN COLD-HOT knobs ........................ As desired.

If AIR COND TEMP HIGH CAS remains displayed:5. Descend to an altitude that will safely allow unpressurized flight.6. AIR SOURCE switch ................................................................... OFF.7. RAM AIR switch.............................................................................ON.8. EMER DEPRESS switch.................................................................ON.

END

Yes

No

END

3/14/03

NON-NORMAL PROCEDURES Challenger 300AIR CONDITIONING & PRESSURIZATION


AUTO PRESS FAIL (C)

1. MANUAL PRESSURIZATION switch..........................................ON.2. MAN RATE control ........................................................... As required.

NOTE: The indicated cabin rate may be significantly higher than the com-manded rate when the cabin altitude is increased in manual mode.

L (R) BLEED FAIL (C)

1. Affected BLEED switch ................................................................OFF.2. XBLEED switch.........................................................................Closed.3. APU BLEED switch.......................................................................OFF.

1. Affected throttle ...................................................................... Increase.

BLEED FAIL (C) remains displayed:

2. Affected BLEED switch.................................................................OFF.3. XBLEED switch.................................................................... CLOSED.

If R BLEED FAIL is displayed:4. APU BLEED switch.......................................................................OFF.

END

END

Yes

No

END

END

3/14/03



L (R) BLEED LOOP FAIL (C)1. Affected BLEED switch ............................................................... OFF.

CABIN ALTITUDE (C)

1. Crew oxygen masks....................................................................... Don.2. AIR SOURCE switch ................................................... Check NORM.3. L and R BLEED switches .................................................... Check On.4. CABIN ALT .............................................................................. Check.

Cabin altitude continues to climb:

a. MANUAL PRESSURIZATION switch ..................................ON.b. MAN RATE control.................................................................DN,

as required to maintain satisfactory pressurization.c. Descend as necessary to control cabin altitude.

Cabin altitude stabilizes at a safe altitude:a. Continue flight.

CABIN PRESS FAULT (C)

1. Altitude ..................................................................25 000 ft maximum.

END

Yes

No

END

END

END

3/14/03



DITCHING NOT AVAIL (C)1. DITCHING switch ......................................................................... Off.

EQPT RACK TEMP HIGH (C)1. AIR SOURCE switch................................................................NORM.2. COCKPIT COLD/HOT control ......................................... Full COLD.3. Land as soon as practical.

OXYGEN QUANTITY LOW (C)

1. Altitude.................................................................. 25 000 ft maximum.

OXYGEN VALVE CLOSED (C)

1. Oxygen bottle valve ..................................................................... Open.

This CAS may occur in flight, with the OXYGEN QUANTITY LOW (C), ifthe bottle(s) are depleted. Refer to the OXYGEN QUANTITY LOWprocedure.

END

END

END

3/14/03



PACK FAIL (C)

On the ground:1. AIR SOURCE switch ................................................................... OFF.In flight:1. AIR SOURCE switch ............................................. TRIM AIR ONLY.

NOTE: Disregard andy AIR COND TEMP HIGH (C) CAS message thatilluminates for less than 30 seconds.

2. L BLEED switch .......................................................................... OFF.3. XBLEED switch ........................................................................ Closed.4. Altitude ..................................................................35 000 ft maximum.5. COCKPIT and CABIN COLD-HOT knobs ........................ As desired.

PACK LOOP FAIL (C)1. AIR SOURCE switch ............................................. TRIM AIR ONLY.

NOTE: Disregard andy AIR COND TEMP HIGH (C) CAS message thatilluminates for less than 30 seconds.

2. Altitude ..................................................................35 000 ft maximum.3. COCKPIT and CABIN COLD-HOT knobs ........................ As desired.

PACK TEMP HIGH (C)On the ground:1. AIR SOURCE switch ................................................................... OFF.In flight:1. AIR SOURCE switch ............................................. TRIM AIR ONLY.

NOTE: Disregard any AIR COND TEMP HIGH (C) CAS messagethat illuminates for less than 30 seconds.

2. Altitude ..................................................................35 000 ft maximum.3. COCKPIT and CABIN COLD-HOT knobs ........................ As desired.

PACK TEMP HIGH remains on:

4. Descend to an altitude that will safely allow unpressurized flight.5. AIR SOURCE switch ................................................................... OFF.6. RAM AIR switch.............................................................................ON.7. EMER DEPRESS switch.................................................................ON.

END

END

Yes

No

END

END

3/14/03



PAX OXYGEN AUTO FAIL (C)1. PAX OXYGEN switch ..........................................................DEPLOY.

L (R) PYLON LOOP FAIL (C)

Both bleed leak detection loops in the respective pylon have failed during thepower up self test.

TRIM AIR FAIL (C)

1. AIR SOURCE switch ..................................................... PACK ONLY.2. R BLEED switch ...........................................................................OFF.3. XBLEED switch.........................................................................Closed.4. COCKPIT and CABIN COLD-HOT knobs.........................As desired.

END

END

END

3/14/03



TRIM AIR LOOP FAIL (C)

1. AIR SOURCE switch .....................................................PACK ONLY.2. COCKPIT and CABIN COLD-HOT knobs ........................ As desired.

XBLEED FAIL (C)

1. XBLEED switch ..................................................................... CYCLE.

XBLEED valve is failed closed:

a. Crossbleed engine starts will not be possible. If necessary, con-duct a windmilling start on the left engine, and a windmilling orAPU assisted start on the right engine.

XBLEED valve is failed open:a. L or R BLEED switch ........................................................... OFF.

END

Yes

NoEND

END

3/14/03

Challenger 300 NON-NORMAL PROCEDURESAUTO FLIGHT

Draft 2.8


AFCS MESSAGES FAIL (C)

1. Autopilot ............................................................................ Disconnect.2. Autopilot ............................................................................. Do not use.

AP HOLDING LWD (C)AP HOLDING RWD (C)AP HOLDING NOSE DOWN (C)AP HOLDING NOSE UP (C)

1. Flight controls.....................................................................Hold firmly.2. Autopilot ...................... Use control wheel MSW switch to disconnect.3. Retrim aircraft if necessary.4. Autopilot .............................................................................. As desired.

AP STAB TRIM FAIL (C)

1. Autopilot ..................... Use control wheel MSW switch to disconnect.2. Retrim aircraft if necessary.3. Autopilot ............................................................................. Do not use.

FD MODE CHANGE (C)

1. Flight director ................................................ Select the desired mode.

YAW DAMPER FAIL (C)

1. Yaw damper ......................................................................... Re-engage.

If YAW DAMPER FAIL remains on:2. Autopilot ............................................................................. Disconnect.3. Do not re-engage yaw damper.4. Altitude ..................................................................31 000 ft maximum.

END

END

END

END

3/14/03

NON-NORMAL PROCEDURES Challenger 300AUTO FLIGHT


AUTOPILOT DISCONNECT Cavalry Charge

1. Control wheel MSW switch ...........................Press to silence message.2. Autopilot...............................................................................Re-engage.

If condition recurs:3. Control wheel MSW switch ...........................Press to silence message.4. Do not re-engage autopilot.

END

3/14/03

Challenger 300 NON-NORMAL PROCEDURESAUXILIARY POWER UNIT

Draft 2.8


APU BLEED ALT LIMIT (C)

1. XBLEED switch ........................................................................ Closed.2. L BLEED switch ............................................................................ON.3. APU BLEED switch .......................................................................Off. 4. R BLEED switch .............................................................................ON.

APU FUEL SOV FAIL (C)

1. APU switch.................................................................................... OFF.2. XBLEED switch ........................................................................ Closed.3. L BLEED switch ............................................................................ON.4. APU BLEED switch .......................................................................Off. 5. R BLEED switch ............................................................................ON.

APU OVERSPEED (C)

1. XBLEED switch ........................................................................ Closed.2. L BLEED switch ............................................................................ON.3. APU BLEED switch .......................................................................Off. 4. R BLEED switch .............................................................................ON.5. APU switch.................................................................................... OFF.

END

END

END

3/14/03

NON-NORMAL PROCEDURES Challenger 300AUXILIARY POWER UNIT


APU OIL PRESS LOW (C)

1. XBLEED switch.........................................................................Closed.2. L BLEED switch ............................................................................ON.3. APU BLEED switch ....................................................................... Off. 4. R BLEED switch.............................................................................ON.5. APU switch ....................................................................................OFF.

APU OIL TEMP HIGH (C)1. XBLEED switch.........................................................................Closed.2. L BLEED switch ............................................................................ON.3. APU BLEED switch ....................................................................... Off. 4. R BLEED switch ............................................................................ON.5. APU switch ....................................................................................OFF.

APU STARTER FAIL ON (C)

1. APU switch ..................................................................................OFF.

END

END

END

3/14/03

Challenger 300 NON-NORMAL PROCEDURESAVIONICS

Draft 2.8


AIR DATA 1 (2) FAULT (C)The aircraft is above 29 000 ft.

1. AIR DATA REVERSION switch ........................ Select operative side.2. FGP XFR switch.......Select same side as air data reversion.

1. AIR DATA REVERSION switch ............................................. NORM.

EFIS COMPARATOR INOP (C)1. Instruments ........................................................................Cross check.

EFIS MISCOMPARE (C)If accompanied by ALT or IAS:

1. Altitude and airspeed .........................................................Cross check.2. AIR DATA REVERSION switch ........................ Select operative side.3. FGP XFR switch.......Select same side as air data reversion.

If accompanied by HDG, ROL or PIT:

1. Autopilot ............................................................................. Disconnect.2. Attitude and heading..........................................................Cross check.3. ATT/HDG REVERSION switch ......................... Select operative side.

If accompanied by LOC or GS:

1. Autopilot ............................................................................. Disconnect.2. Localizer and glideslope ....................................................Cross check.3. NAV SOURCE REVERSION switch ................. Select operative side.

If accompanied by RA:

1. Autopilot ............................................................................. Disconnect.2. Radio altitude........................... Cross check with barometric altimeter.3. Radio altimeter ...........................................................Use reliable side.

If accompanied by FD:

1. Autopilot ............................................................................. Disconnect.2. Flight directors...................................................................Cross check.3. FGP XFR switch.................................................. Select operative side.

Yes

No END

END

END

END

3/14/03

NON-NORMAL PROCEDURES Challenger 300AVIONICS


L (R) IAPS FAIL (C)L IAPS FAIL:

1. Autopilot..............................................................................Disconnect.2. FGP XFR switch .................................................................Select FD2.3. TUNE REVERSION switch ............................................. CDU ONLY.

R IAPS FAIL:1. FGP XFR switch .................................................................Select FD1.2. TUNE REVERSION switch ............................................. CDU ONLY.

PFD X-TALK FAIL (C)

1. Instruments ........................................................................ Cross check.2. Verify that the information is set (entered) on both display

control panels.

AIR DATA COMPUTER (ADC) FAILURE - SINGLE

1. AIR DATA REVERSION switch.........................Select operative side.

NOTE: FLAPS FAULT (A), STAB TRIM FAULT (A), and L and RFADEC FAULT (A) CAS messages will be displayed due to loss ofone ADC input.

2. FGP XFR switch.......Select same side as air data reversion.

AIR DATA COMPUTER (ADC) FAILURE - DUAL

1. Maintain aircraft control by reference to the standby airspeed/Machand altitude.

2. Operative flight director modes will be PITand ROL only.

ATTITUDE/HEADING COMPUTER (AHC) FAILURE

1. ATT/HDG REVERSION switch..........................Select operative side.

END

END

END

END

END

3/14/03



CDU FAILURE

1. TUNE REVERSION switch..............................................MFD ONLY.

DCU A and DCU B FAILURE

1. Autopilot ............................................................................. Disconnect.2. L and R HYDRAULIC PUMP switches .........................................ON.3. Land as soon as practical.

ERRONEOUS PITOT-STATIC INDICATION

1. Pilot’s, copilot’s, and standby instruments ................................. Check.

If the malfunction is suspected in the pilot’s or copilot’s pitot-static sys-tem:

a. ADC REVERSION switch .......................... Select operative side.

NOTE: FLAPS FAULT (A), STAB TRIM FAULT (A), and L and RFADEC FAULT (A) CAS messages will be displayed due to loss ofone ADC input.

b. FGP XFR switch.......................... Select same side as valid ADC.c. Land as soon as practical.

If the malfunction is suspected in both the pilot’s and copilot’spitot-static system:

a. Use standby instrument.b. Land as soon as possible.

If the malfunction is suspected in the standby pitot-static system:a. Use normal ADC displays.

END

END

END

3/14/03



MFD FAILURE

If an MFD fails (either L or R) any information entered on the opposite MFDcould be lost if the failed MFD comes back up.

1. Affected DISPLAYS REVERSION switch .......................... PFD REV.or

1. TUNE REVERSION switch ............................................. CDU ONLY.

PFD FAILURE

1. Affected DISPLAYS REVERSION switch .........................MFD REV.

RADIO ALTITUDE FAILURE

1. Normal landing distance.....................................................Multiply by:1.40 without thrust reversers1.35 with thrust reversers.

After Landing:2. FLIGHT SPOILERS lever .........................................................EMER.

RADIO TUNING FAILURE

1. TUNE REVERSION switch ............................................. CDU ONLY.

If unable to restore COM tuning on at least one side:2. TUNE REVERSION switch ........................................................121.5.

END

END

END

END

3/14/03



TCAS AURALS TCAS Aurals

“CLEAR OF CONFLICT”

Resume normal flight.

“CLIMB, CLIMB”

Change vertical speed to 1500 feet/min. climbing or as indicated on the VSI.

“CLIMB, CROSSING, CLIMB - CLIMB, CROSSING, CLIMB”

Change vertical speed to 1500 feet/min. climbing or as indicated on the VSI.The converging flight paths will cross at some altitude.

“DESCEND, DESCEND, DESCEND”

Change vertical speed to 1500 feet/min. descending or as indicated on the VSI.

“DESCEND, CROSSING, DESCEND - DESCEND, CROSSING, DESCEND”

Change vertical speed to 1500 feet/min. descending or as indicated on the VSI.The converging flight paths will cross at some altitude.

“ADJUST VERTICAL SPEED ADJUST”

Reduce climbing vertical speed to that shown on the VSI.

“INCREASE CLIMB - INCREASE CLIMB”

This follows a CLIMB advisory. The climb vertical speed should be increased,typically to 2500 feet/min., as shown on the VSI.

“INCREASE DESCENT - INCREASE DESCENT”

This follows a DESCEND advisory. The descent vertical speed should be in-creased, typically to 2500 feet/min., as shown on the VSI.

“CLIMB, CLIMB NOW”

This follows a DESCEND advisory. This advisory indicates that a reversal ofvertical speed from descent to climb is needed to provide adequate separation.

“DESCEND, DESCEND NOW”

This follows a CLIMB advisory. This advisory indicates that a reversal of ver-tical speed from climb to descent is needed to provide adequate separation.

3/14/03



TCAS AURALS (Cont)

“MAINTAIN VERTICAL SPEED MAINTAIN”

Maintain present vertical speed and direction.

“MAINTAIN VERTICAL SPEED, CROSSING, MAINTAIN”

A flight path crossing is predicted, but being monitored by TCAS. Maintainpresent vertical speed and direction.

“MONITOR VERTICAL SPEED”

Be alert for approaching traffic.

“TRAFFIC, TRAFFIC”

Gain visual contact with traffic. Check TCAS display for traffic bearing andrange if necessary.

TAWS AURALS TAWS Aurals

“SINK RATE, SINK RATE”

1. Descent rate ...............................................................................Reduce.

“TERRAIN, TERRAIN” or“DON’T SINK, DON’T SINK” or“TOO LOW, TERRAIN” or“CAUTION TERRAIN, CAUTION TERRAIN” or“CAUTION OBSTACLE, CAUTION OBSTACLE”

1. Establish a positive rate of climb.

“TOO LOW GEAR”

There is adequate time to extend gear:

1. GEAR switch ..................................................................................DN.

1. Execute a go-around.

END

Yes

No

END

END

3/14/03



TAWS AURALS (Cont)

“TOO LOW FLAPS”

1. FLAPS lever ..................................................................................... 30.

“GLIDESLOPE”

1. Fly aircraft up to glideslope.

“CAUTION WINDSHEAR”

During final approach:1. Add wind and gust allowances to the approach speed. Increase thrust

as necessary.2. Avoid getting low on the approach glidepath or letting the thrust levers

remain at idle for extended periods of time.

During takeoff:1. Thrust levers .................................................................................... TO.2. Airspeed.....................................V2+10, until safe climbout is assured.

3/14/03

Challenger 300 NON-NORMAL PROCEDURESDOORS

Draft 2.8


AFT EQPT BAY DOOR (C)

1. Avoid slips or skids that could open the door.

BATTERY BAY DOOR (C)

1. Avoid slips or skids that could open the door.

CARGO DOOR (C)

1. SMKG/BELTS switch .............................................................. BELTS.

WARNING: Do not approach door. Door failure may be indicated by aloud noise, pressurization leak, or rumble emanating from thehatch area.

EMERGENCY EXIT (C)

1. SMKG/BELTS switch .............................................................. BELTS.

WARNING: Do not approach exit. Exit failure may be indicated by aloud noise, pressurization leak, or rumble emanating from thehatch area.

END

END

END

END

3/14/03

NON-NORMAL PROCEDURES Challenger 300DOORS


PASSENGER DOOR (C)

WARNING: Do not approach door. Door failure may be indicated byloud noise, pressurization leak, or rumble emanating from thedoor area.

PASSENGER DOOR (C) is accompanied by evidence of door failure.

1. SMKG/BELTS switch.................................................. SMKG/BELTS.2. EMER DEPRESS switch ............................................ Lift guard, ON.

The cabin altitude will climb to approximately 15 000 feet andstabilize.

3. Airspeed ............................................................. 250 KIAS maximum.4. Establish descent to reduce cabin delta pressure, but not lower than the

minimum safe altitude.5. Land as soon as possible.

PASSENGER DOOR (C) is not accompanied by evidence of doorfailure1. SMKG/BELTS switch.................................................. SMKG/BELTS.2. Continue flight. The most probable cause is a proximity sensor

malfunction.

Yes

No

END

3/14/03

Challenger 300 NON-NORMAL PROCEDURESELECTRICAL

Draft 2.8


APU GEN FAIL (C)1. APU GEN switch.............................................................................ON.

If APU GEN FAIL CAS remains on:2. Do not attempt a second reset of the APU GEN switch.

APU GEN OVERLOAD (C)

1. Electrical load ........................................................................... Reduce.

L (R) BATT FAIL (C)

1. Affected BATT switch ........................................................ Verify OFF.2. Affected BATT temperature .................................................... Monitor.

If BATT TEMP decreases below 60 °C:3. Applicable BATT switch ................................................................. On.

ELECTRICAL FAULT (C)

1. Land as soon as practical.

L (R) GEN FAIL (C)

1. Affected L or R GEN switch ........................................................... On.

If GEN FAIL CAS remains on:2. Do not attempt a second reset of the GEN switch.

END

END

END

3/14/03

NON-NORMAL PROCEDURES Challenger 300ELECTRICAL


L (R) ESS BUS FAIL (C)1. Land as soon as practical.

If L ESS BUS FAIL CAS is displayed:

2. LEFT DISPLAYS REVERSION switch............................... PFD REV.3. ATT/HDG REVERSION switch.........................................................2.4. AIR DATA REVERSION switch........................................................2.5. Autopilot..............................................................................Disconnect.6. AIR SOURCE switch...............................................TRIM AIR ONLY.7. L BLEED switch ............................................................................OFF.8. XBLEED switch.........................................................................Closed.9. ANTI-ICE WING SOURCE switch ......................................FROM R.

NOTE: The STBY probe will not be anti-iced.

10. Altitude.................................................................. 25 000 ft maximum.11. Normal landing distance.............................................Multiply by 1.55.

R ESS BUS FAIL CAS is displayed:

1. ANTI-ICE WING SOURCE switch .........................................From L.2. Normal landing distance.............................................Multiply by 1.55.

L (R) GEN OVERLOAD (C)

1. Affected electrical load .............................................................Reduce.

Yes

No

END

END

END

3/14/03

Challenger 300 NON-NORMAL PROCEDURESELECTRICAL


L (R) MAIN BUS FAIL (C)1. Land as soon as practical.

If L MAIN BUS FAIL CAS is displayed:

2. LEFT DISPLAYS REVERSION switch ............................. MFD REV.

NOTE: MFD control panel will not control the MFD when reverted.Use display control panel.

3. AIR DATA REVERSION switch ....................................................... 2.4. Autopilot ............................................................................. Disconnect.5. Normal landing distance .................................................... Multiply by:


R MAIN BUS FAIL CAS is displayed:

6. AIR SOURCE switch ......................................................PACK ONLY.7. ANTI-ICE WING SOURCE switch.......................................... From L8. Normal landing distance .................................................... Multiply by:


Yes

NoEND

END

3/14/03

Challenger 300 NON-NORMAL PROCEDURESFIRE PROTECTION

Draft 2.8


APU FIRE DET FAIL (C)

1. APU Shutdown:a. XBLEED switch ................................................................ Closed.b. L BLEED switch......................................................................ON.c. APU BLEED switch ................................................................Off.d. R BLEED switch .....................................................................ON.e. APU switch ............................................................................ OFF.

CARGO SMOKE DET FAIL (C)

1. Doors between the cabin and the baggage compartment .............Open.

L (R) FIRE DET FAIL (C)

1. Affected engine indications ..................................................... Monitor.

FIRE SYS FAULT (C)

1. FIRE DET.................................................................................... TEST.

All of the following CAS messages should come on:L (R) ENG FIRE, APU FIRE, GEAR BAY OVHT, CARGO SMOKE

a. Continue flight.

One of the following CAS messages should come on:APU FIRE DET FAIL, CARGO SMOKE DET FAIL,L(R) FIRE DET FAIL, FIREX APU SQUIB FAIL,GEAR BAY DET FAIL, FIREX BTL 1 (2) FAULT.

a. Refer to the appropriate displayed CAS message.

END

END

END

Yes

No

END

END

3/14/03

NON-NORMAL PROCEDURES Challenger 300FIRE PROTECTION


FIREX APU SQUIB FAIL (C)

1. APU Shutdown:a. XBLEED switch.................................................................Closed.b. L BLEED switch .....................................................................ON.c. APU BLEED switch................................................................ Off.d. R BLEED switch .....................................................................ON.e. APU switch.............................................................................OFF.

GEAR BAY DET FAIL (C)

The CAS displays within 5 minutes of takeoff:

1. Airspeed .............................................................. 250 KIAS maximum.2. LANDING GEAR switch ...............................................................DN.

After 5 minutes:3. LANDING GEAR switch ................................................................ UP.

1. Continue flight.

END

Yes

NoEND

END

3/14/03

Challenger 300 NON-NORMAL PROCEDURESFLIGHT CONTROLS

Draft 2.8


ELEVATOR SPLIT (C)1. Airspeed............................................. Reduce until the message clears.

FLAPS FAIL (C)

Descent checks:1. Pressurization .............................................................. LNDG ALT set.2. WING ANTI-ICE switch....................................................As required.3. L and R ENG ANTI-ICE switches .....................................As required.


copilot, and standby, and cross-check. 5. L and R LANDING light switches .................................................. On.6. Cabin Check .........................................................................Complete.7. SMKG/BELTS switch ..................................................SMKG/BELTS.8. Fuel quantities and balance ........................................................ Check.

Approach checks:9. APU ................................................................................................ Set.

10. Final approach speed ................................. As listed for flaps attained:Flaps 0 ........................................................................... VREF + 20Flaps 10......................................................................... VREF + 15Flaps 20........................................................................... VREF + 5Flaps 30.................................................................................VREF.

NOTE: Use the lesser flap deflection VREF speed for flap settings betweenthe detent values.

11. Normal landing distance ................................................... Multiply by:

Without thrust reversers:Flaps 0 ..................................................................................... 1.45Flaps 10................................................................................... 1.40Flaps 20................................................................................... 1.25

With thrust reversers:Flaps 0 ..................................................................................... 1.40Flaps 10................................................................................... 1.30Flaps 20.................................................................................. 1.20.

12. FLAPS TAWS WARN................................................................... OFF.13. Approach setup and crew briefing.........................................Complete.14. L and R HYDRAULIC PUMP switches .........................................ON.

Before Landing checks:15. LANDING GEAR switch ...............................................................DN.16. L LDG, NOSE LDG/TAXI, and R LDG light switches ................. On.

END

3/14/03

NON-NORMAL PROCEDURES Challenger 300FLIGHT CONTROLS


FLAPS FAULT (C)

1. Airspeed ................................................................................. Decrease.2. FLAPS..........................................................Select the previous detent,

then select a detent to agree with the closest flap position.

NOTE: Trying to reset the flaps with the flap handle three times will resultin a FLAPS FAIL (C) if the condition has not cleared.

FLAPS FAULT (C) message clears:

3. ALTN FLAPS switch ....................................................Lift guard, ON, FLAPS RATE LOW (A) CAS will be on.

4. FLAPS selector ....................................................... Select the previous detent, then select a detent to agree with the closest flap position.

5. Refer to FLAPS FAIL (C) procedure, this section.

Yes

No

END

Yes

No END

3/14/03



FLAPS NORM PRESS LOW (C)

1. ALTN FLAPS switch.................................................... Lift guard, ON.2. FLAPS ................................................................................. As desired.

FLT SPOILERS DEPLOY (C)

1. FLIGHT SPOILERS lever.........................................................Retract.

FLT SPOILERS FAIL (C)

1. Altitude ...............................................................XX 000 ft maximum.2. Normal landing distance .............................................Multiply by X.X.

FLT SPOILERS FAULT (C)

1. Altitude ...............................................................XX 000 ft maximum.2. Normal landing distance ............................................Multiply by X.X.

GND SPLRS NOT ARMED (C)

1. GROUND SPOILERS switch ...................................MANUAL ARM.

If GND SPLRS NOT ARMED (C) remains on:2. Normal landing distance .................................................... Multiply by:


After touchdown:3. FLIGHT SPOILERS lever......................................................... EMER.

END

END

END

END

END

3/14/03



GND SPOILERS FAIL (C)1. GROUND SPOILERS switch........................................................OFF.2. Normal landing distance.....................................................Multiply by:


After touchdown:3. FLIGHT SPOILERS lever .........................................................EMER.

MACH TRIM FAIL (C)

1. Mach with AP engaged .......................................... 0.83 MI maximum.1. Mach with AP disengaged...................................... 0.75 MI maximum.

END

END

3/14/03



PRI STAB TRIM FAIL (C)1. STAB TRIM switch....................................................................... SEC.

NOTE: The autopilot, MACH trim, and configuration will be inoperativewith SEC STAB TRIM selected.

2. Control Wheel Trim switch .................................................. Operate as required to maintain trim.

3. Airspeed............................................................. 0.75 Mach maximum.

Stab trim is inoperative:

4. STAB TRIM switch....................................................................... OFF.

ELEVATOR PULL FORCE IS ENCOUNTERED(If the stabilizer jams during a high-speed condition):

a. Delay reducing airspeed as long as possible to minimize the timeout of trim.

b. Move C.G. aft if possible.

Descent checks:c. Pressurization ...................................................... LNDG ALT set.d. WING ANTI-ICE switch............................................As required.e. L and R ENG ANTI-ICE switches .............................As required.

Transition Level (or FL 180) Checks:f. Altimeters ........................................................................Set pilot,

copilot, and standby, and cross-check. g. L and R LANDING light switches .......................................... On.h. Cabin Check ..................................................................Complete.i. SMKG/BELTS switch ..........................................SMKG/BELTS.j. Fuel quantities and balance ................................................ Check.

Approach checks:k. APU ........................................................................................ Set.l. Final approach speed ...........................................................VREF.m. Normal landing distance ............................................ Multiply by:


n. Approach setup and crew briefing ................................Complete.

(Continued)

Yes

Yes

No

3/14/03



PRI STAB TRIM FAIL (Cont)SEC STAB TRIM FAIL is displayed (Cont):

o. FLAPS TAWS WARN............................................................OFF.

Before Landing Checks:p. LANDING GEAR switch ......................................................DN.q. L LDG, NOSE LDG/TAXI, and R LDG light switches ...........On.r. FLAPS ...................................................................................... 30.

ELEVATOR PUSH FORCE IS ENCOUNTERED:

a. Do not increase airspeed to minimize the out of trim conditions.b. Move C.G. forward if possible.c. Land as soon as possible to minimize aft C.G. movement.

Descent checks:d. Pressurization ......................................................LNDG ALT set.e. WING ANTI-ICE switch ...........................................As required.f. L and R ENG ANTI-ICE switches............................. As required.

Transition Level (or FL 180) Checks:g. Altimeters ....................................................................... Set pilot,

copilot, and standby, and cross-check. h. L and R LANDING light switches...........................................On.i. Cabin Check .................................................................. Complete.j. SMKG/BELTS switch .......................................... SMKG/BELTS.k. Fuel quantities and balance ................................................Check.Approach checks:l. APU ...................................................................................... Start.m. Final approach speed ............................................................ VREF.n. Normal landing distance.............................................Multiply by:


o. Approach setup and crew briefing ................................ Complete.

Before Landing Checks:p. LANDING GEAR switch .......................................................DN.q. L LDG, NOSE LDG/TAXI, and R LDG light switches ..........ON.r. FLAPS .......................................................................................30.

SEC STAB TRIM FAIL (C) is not displayed:

No

No

No

END

END

3/14/03



ROLL SPOILERS FAIL(C)

1. Normal landing distance ............................................Multiply by X.X.


ROLL SPOILERS FAULT (C)

2. Normal landing distance ............................................Multiply by X.X.

ROLL SPOILERS OFF (C)

1. ROLL SPOILER switch .................................................................. On.

RUDDER LIMITER FAIL (C)

1. Avoid excessive rudder inputs.2. Airspeed...............................................................185 KIAS maximum.


END

END

END

END

3/14/03



SEC STAB TRIM FAIL (C)PRI STAB TRIM FAIL is displayed:

1. Refer to PRI STAB TRIM FAIL procedure, this section.

1. STAB TRIM switch.........................................................................PRI.

SPOILERS FAIL (C)

1. FLIGHT SPOILERS lever ............................................................ RET.2. Altitude ............................................................... XX 000 ft maximum.3. Normal landing distance ............................................ Multiply by X.X.


SPOILERS FAULT (C)

1. Altitude ............................................................... XX 000 ft maximum.

Is any spoiler panel jammed in an extended position?

a. Autopilot......................................................................Disconnect.b. Aileron Trim.................................... As required to minimize roll.c. Land as soon as possible.d. Final Approach Speed ..................................................... Vref + 8.e. Normal landing distance.............................................Multiply by:



Yes

No

END

END

Yes

No

END

END

3/14/03



STALL PROTECT FAIL (C)1. STALL PUSHER switch ............................................................... OFF.2. Final approach speed ............................................................ VREF + 10.3. Normal landing distance .................................................... Multiply by:


STALL PUSHER OFF (C)

1. MSW disconnect button ...........................................................Release.

STALL PUSHER OFF remains on:

2. Final approach speed ............................................................ VREF + 10.3. Normal landing distance .................................................... Multiply by:


END

Yes

No

END

3/14/03

Challenger 300 NON-NORMAL PROCEDURESFUEL

Draft 2.8


L (R) FUEL COLLECTOR LOW (C)

1. Affected FUEL PUMP switch .........................................................ON.2. Sideslip ..................................................................................Minimize.3. Land as soon as possible.

FUEL IMBALANCE (C)

1. Fuel quantities ............................................................................ Check.

Correct fuel distribution, if required:2. FUEL XFER switch......................................................................Open.3. L or R FUEL PUMP switch (heavy wing) .....................................ON.4. Monitor wing fuel quantity.

When fuel balance is achieved:5. L or R FUEL PUMP switch ...........................................................Off.6. FUEL XFER switch..................................................................... Close.

L (R) FUEL PRESS LOW (C)

1. Affected FUEL PUMP switch .........................................................ON.

FUEL PRESS LOW CAS remains on:2. Affected thrust lever .................. Reduce to minimum practical setting.3. Maintain XX 000 feet or below to enable suction feed.

END

END

3/14/03

NON-NORMAL PROCEDURES Challenger 300FUEL


L (R) FUEL PUMP FAIL (C)

To balance fuel (if required):1. GRAVITY XFLOW switch.......................................................... Open.

NOTE: It may be necessary to use a sideslip to transfer fuel.

FUEL QUANTITY FAIL (C)

1. Monitor fuel quantity on the FMS.

FUEL QUANTITY LOW (C)

1. Fuel quantities ............................................................................Check. 2. L and R FUEL PUMP switches ......................................................ON.3. Land as soon as possible. A go-around is not recommended.

WING FUEL TEMP LOW (C)

1. Descend to a warmer ambient temperature.

END

END

END

3/14/03

Challenger 300 NON-NORMAL PROCEDURESHYDRAULICS

Draft 2.8


AUX HYD TEMP HIGH (C)

1. AUX HYDRAULIC PUMP switch .............................................. OFF.

If temperature continues to rise:2. AUX DC PUMP circuit breaker (CB1 D10) ..................................Pull.3. Land as soon as practical.

L (R) HYD PRESS LOW (C)

1. Affected HYDRAULIC PUMP switch ...........................................ON.2. HYDRAULIC pressure and quantity ...................................... Monitor.

If quantity is dropping rapidly:a. Autopilot ..................................................................... Disconnect.b. Affected HYDRAULIC PUMP switch.................................. OFF.c. Affected HYDRAULIC SOV switch.............................CLOSED.


Descent Checks:1. Pressurization .............................................................. LNDG ALT set.2. WING ANTI-ICE switch....................................................As required.3. L and R ENG ANTI-ICE switches .....................................As required.

Transition Level (or FL 180) Checks:4. Altimeters ....................................................................................... Set.5. L and R LANDING light switches .................................................. On.6. Cabin Check .........................................................................Complete.7. SMKG/BELTS switch ..................................................SMKG/BELTS.8. Fuel quantities and balance ........................................................ Check.


(Continued)

END

3/14/03

NON-NORMAL PROCEDURES Challenger 300HYDRAULICS


L (R) HYD PRESS LOW (Cont)L HYD PRESS LOW is displayed:

(1) Final approach speed .................................................... VREF.(2) Normal landing distance ....................................Multiply by:


(3) Approach setup and crew briefing ........................ Complete.

Before Landing Checks:(4) LANDING GEAR switch................................................DN.(5) LG PULL handle ............................................................ Pull.

NOTE: Performing a sideslip to each side may help achieveMLG downloack. Increased airspeed may be requiredto ensure downlock during sideslip.

(6) LANDING GEAR indication ................................ Check forthree green DN indications.

CAUTION: Do not stow the handle until the gear pins are in-stalled.

(7) L LDG, NOSE LDG/TAXI, and R LDG light switches ...On.(8) FLAPS ...............................................................................30.(9) NWS switch ....................................................................OFF,


After Touchdown:(10) Limit reverse thrust on the right side as required to maintain

directional control.

NOTE: Do not deploy the left thrust reverser.

R HYD PRESS LOW is displayed:(1) Final approach speed .................................................... VREF.(2) Normal landing distance ....................................Multiply by:


(3) ALTN FLAPS ..................................................................ON.(4) Approach setup and crew briefing ........................ Complete.

(Continued)

Yes

No

3/14/03



L (R) HYD PRESS LOW (Cont)Before Landing Checks:(5) LANDING GEAR switch ................................................DN.(6) L LDG, NOSE LDG/TAXI, and R LDG light switches... On.(7) FLAPS............................................................................... 30.

After Touchdown:(8) Limit reverse thrust on left side as required to maintain


NOTE: Do not deploy the right thrust reverser.

HYD PTU FAIL (C)1. Hydraulic quantity for both systems .......................................... Check.

Quantities are normal:

a. PTU switch...............................................................................ON.

Either quantity goes low or the message persists: a. PTU switch ............................................................................ OFF.

L (R) HYD SOV FAIL (C)

1. Affected SOV switch.........................................Check proper position.

END

Yes

No

END

END

3/14/03



L (R) HYD TEMP HIGH (C)

1. Affected HYDRAULIC PUMP switch .........................................OFF.2. Affected hydraulic temperature................................................Monitor.

Hydraulic temperature reaches 135 °C:

3. Autopilot .............................................................................Disconnect.4. Affected HYDRAULIC L (R) SOV...................................... CLOSED.

The affected L HYD PRESS LOW (C) is displayed.

NOTE: The hydraulic SOV should automatically close atapproximately 135 °C.


Hydraulic temperature reaches 155 °C:

a. Affected ENGINE RUN switch .............................................OFF.b. Rudder trim................................................................. As required.c. Electrical load ........................ Reduce, to within generator limits.d. Applicable BLEED switch .....................................................OFF.e. XBLEED switch................................................................. OPEN.f. Applicable ENGINE ANTI-ICE switch.................................OFF.g. Fuel balance......................................................................Monitor.h. Go to Descent Checks below.

Descent Checks:6. Pressurization ..............................................................LNDG ALT set.7. WING switch...................................................................... As required.8. L and R ENG ANTI-ICE switches..................................... As required.


copilot, and standby, and cross-check. 10. L and R LANDING light switches...................................................On.11. Cabin Check ......................................................................... Complete.12. SMKG/BELTS switch.................................................. SMKG/BELTS.13. Fuel quantities and balance ........................................................Check.

(Continued)

Yes

Yes

No

3/14/03



L (R) HYD TEMP HIGH (Cont)Approach Checks:

14. APU ..............................................................................................Start:

L HYD PRESS LOW is displayed:

(1) Final approach speed.....................................................VREF.(2) Normal landing distance .................................... Multiply by:


(3) Approach setup and crew briefing ........................Complete.

Before Landing Checks:(4) LANDING GEAR switch ................................................DN.(5) LG PULL handle.............................................................Pull.

NOTE: Performing a sideslip to each side may help achieveMLG downloack. Increased airspeed may be requiredto ensure downlock during sideslip.

(6) LANDING GEAR indication................................ Check forthree green DN indications.

CAUTION: Do not stow the handle until the gear pins are in-stalled and maintenance is obtained.

(7) L LDG, NOSE LDG/TAXI, and R LDG light switches... On.(8) FLAPS............................................................................... 30.(9) NWS switch ................................................................... OFF,


After Touchdown:(10) Limit reverse thrust on right side as required to maintain


NOTE: Do not deploy the left thrust reverser.

R HYD PRESS LOW is displayed:(1) Final approach speed.....................................................VREF.(2) Normal landing distance .................................... Multiply by:


(3) ALTN FLAPS ..................................................................ON.(4) Approach setup and crew briefing ........................Complete.

(Continued)

Yes

No

3/14/03



L (R) HYD TEMP HIGH (Cont)Before Landing Checks:(5) LANDING GEAR switch................................................DN.(6) L LDG, NOSE LDG/TAXI, and R LDG light switches ...On.(7) FLAPS ...............................................................................30.

After Touchdown:(8) Limit reverse thrust on left side as required to maintain


NOTE: Do not deploy the right thrust reverser.

END

3/14/03

Challenger 300 NON-NORMAL PROCEDURESICE & RAIN PROTECTION

Draft 2.8


L (R) AOA VANE HEAT FAIL (C)

1. Affected PROBES switch................................................OFF, then On.

AOA VANE HEAT FAIL remains displayed:a. Leave icing conditions as soon as possible.

If icing is encountered:b. STALL PUSHER switch........................................................ OFF.c. Final approach speed .................................................... VREF + 10.

d. Normal landing distance ............................................ Multiply by:1.25 without thrust reversers1.20 with thrust reversers.

ICE DETECTED (C)

1. WING ANTI-ICE switch.................................................................ON.2. L and R ENG ANTI-ICE switches .................................................ON.

ICE DETECTOR FAIL (C)

If in visible moisture or at night and SAT is +10 °C to -40 °C:1. WING ANTI-ICE switch.................................................................ON.2. L and R ENG ANTI-ICE switches .................................................ON.

L (R) ENG ANTI-ICE FAIL (C)

1. ANTI-ICE synoptic .................................................................... Check.

Affected engine anti-ice flow line is amber:

2. IGN switch.......................................................................................ON.3. Engine N1 ................................................ Increase to improve airflow.

If ENG ANTI-ICE FAIL remains on:a. Leave icing conditions as soon as possible.

An amber TT2 is displayed next to the engine graphic:2. Leave icing conditions as soon as possible.

END

END

END

Yes

No

END

END

3/14/03

NON-NORMAL PROCEDURES Challenger 300ICE & RAIN PROTECTION


L (R) PITOT HEAT FAIL (C)

1. Affected PROBES switch ............................................... OFF, then On.

PITOT HEAT FAIL remains displayed:

a. Cross-check the three pitot-static systems.

PITOT HEAT FAIL is accompanied by erroneous pitot-static indications:

If L PITOT HEAT FAIL:(1) AIR DATA reversion switch..................................... Select 2.

If R PITOT HEAT FAIL:(1) AIR DATA reversion switch..................................... Select 1.

L (R) PROBE HEAT OFF (C)

In flight:1. Affected PROBES switch ...............................................................ON.

Yes

Yes

No

END

3/14/03



STBY PITOT HEAT FAIL (C)

1. L PROBES switch ..........................................................OFF, then On.

STBY PITOT HEAT FAIL remains on:

a. Use the pilot’s and copilot’s airspeed/Mach indicators.Do not use the standby instrument.

L (R) STBY STAT HT FAIL (C)

1. Affected PROBES switch ...............................................OFF, then On.

If STBY STAT HT FAIL remains on:

a. Use the pilot’s and copilot’s airspeed/Mach indicators.Do not use the standby instrument.

L (R) WINDOW HEAT FAIL (C)

1. Affected WSHLD/WINDOW switch ..............................OFF, then On.a. Moving the COCKPIT and CABIN TEMPERATURE knobs to

HOT may help reduce fogging.

Yes

No

END

Yes

No

END

END

3/14/03



L (R) WING A/I PRESS HI (C)

1. WING SOURCE switch ..........................Select FROM L or FROM Ras required.

2. AUTO SYNC switch......................................................................OFF.

WING A/I PRESS HI remains displayed:

a. WING switch..........................................................................OFF.b. Leave icing conditions as soon as possible.

If approach and landing must be made with anyice or suspected ice:

(1) Refer to WING ANTI-ICE FAILURE LANDING proce-dure, Landing procedure section, this chapter.

WING A/ICE LOOP FAIL (C)

1. Do not takeoff.

Yes

NoEND

END

3/14/03



L (R) WING A/ICE FAIL (C)

1. Anti-Ice synoptic ........................................................................ Check.

Affected anti-ice flow line is amber:

a. Affected throttle ............................Increase to 74% N2 minimum.

WING A/ICE FAIL (C) extinguishes:

Both the L WING ANTI-ICE FAIL (C) and the R WING ANTI-ICEFAIL (C) are On:

1. WING ANTI-ICE switch .............................................................. OFF.2. Leave icing conditions as soon as possible.

If approach and landing must be made with any ice or suspectedice:a. Refer to WING ANTI-ICE FAILURE LANDING procedure,

Landing procedure section, this chapter.

a. WING SOURCE switch ................. Select FROM L or FROM Ras required.

b. AUTO SYNC switch ............................................................. OFF.

WING A/ICE FAIL (C) remains displayed:

(1) WING switch ................................................................. OFF.(2) Leave icing conditions as soon as possible.

If approach and landing must be made with any ice orsuspected ice:(3) Refer to WING ANTI-ICE FAILURE LANDING proce-

dure, Landing procedure section, this chapter.

Yes

No

END

Yes

No

Yes

No

END

3/14/03



WING ANTI-ICE FAULT (C)

1. Leave icing conditions as soon as possible.

When out of icing:2. WING ANTI-ICE switch ...............................................................OFF.

L (R) WSHLD HEAT FAIL (C)

1. Affected WSHLD/WINDOW switch.............................OFF, then On.

IF WSHLD HEAT FAIL (C) remains on:a. Leave icing conditions as soon as possible.b. Moving the COCKPIT and CABIN TEMPERATURE knobs to

HOT may help reduce fogging.

CRACKED, SHATTERED, DELAMINATED, OR ARCING WINDSHIELD OR WINDOW

1. Affected WSHLD/WINDOW switch.............................................OFF.2. Cabin differential pressure ............................ Reduce to 5.8 maximum.3. Altitude.................................................................. 15 000 ft maximum.4. Leave icing conditions as soon as possible.5. Moving the COCKPIT and CABIN COLD-HOT knobs to HOT may

help reduce fogging.

If core or inside plies are shattered:6. Airspeed .......................................205 KIAS maximum below 8000 ft.

END

END

END

3/14/03



ENGINE ICE INGESTION

1. IGNITION switch........................................................................... ON.Leave the switch ON for the duration of the flight.

2. Leave icing conditions as soon as possible.3. Avoid any abrupt changes in pitch, yaw, or roll.

To determine extent of engine damage due to ice ingestion, proceed asfollows:a. Thrust levers (one at a time) ....................................... Slowly and

cautiously retard to IDLE, then slowly and cautiously advanceand check for any vibration or abnormal noise on each engine.

CAUTION: If compressor stall is encountered, retard thrust lever untilsmooth operation is obtained. (If any of the fan blades havebeen damaged, the noise level and frequency will increasewith an increase of N1).

If ice damage has been experienced:(1) Engine N1 .......................................... Set as low as possible.

Maintain sufficient N1 for anti-icing heat and cabin pressure.(2) Land as soon as practical.

END

3/14/03

Challenger 300 NON-NORMAL PROCEDURESLANDING GEAR, WHEEL & BRAKE SYSTEM

Draft 2.8


BRAKE FAULT (C)

The brakes operate normally. No crew action required.

CPLT BRAKE FAULT (C)

1. Use the pilot’s brakes.

GEAR DISAGREE (C)

1. Airspeed ..............................................................250 KIAS maximum.2. LANDING GEAR switch................................................................DN.

If CAS remains with the landing gear selected down:3. Refer to the Landing Gear Manual Extension procedure, this section.

GEAR SYS FAIL (C)

1. Airspeed ..............................................................250 KIAS maximum.2. LANDING GEAR switch ...............................................................DN.3. LANDING GEAR indication .. Check for three green DN indications.

Three DN indications:

a. Land as soon as practical.

a. Refer to the Landing Gear Manual Extension procedure, thissection.

END

Yes

No

3/14/03

NON-NORMAL PROCEDURES Challenger 300LANDING GEAR, WHEEL & BRAKE SYSTEM


L (R) INBD BRAKE FAIL (C)

1. Operate with landing gear extended for 15 minutes prior to landing (toensure cool brakes).


NOTE: If heavy braking is used, the outboard brakes may lock up below 30knots.

INBD BRAKE PRESS LO (C)


INBD BRAKES FAIL (C)


NOSE GEAR DOOR (C)

1. Airspeed .............................................................. 250 KIAS maximum.2. Land as soon as practical.

NWS FAIL (C)

At Normal Taxi Speeds:1. Maintain directional control using differential braking on landing.2. NWS switch....................................................................................OFF.3. Thrust levers ................................................................................IDLE.4. Brake to a stop.

In flight:1. NWS switch....................................................................................OFF.2. Normal landing distance............................................. Multiply by X.X.3. Maintain directional control using differential braking on landing.

NWS LIMIT EXCEEDED (C)

1. Do not take off.

END

END

END

3/14/03



L (R) OUTBD BRAKE FAIL (C)1. Operate with landing gear extended for 15 minutes prior to landing (to

ensure cool brakes).2. Normal landing distance .................................................... Multiply by:


NOTE: If heavy braking is used, the inboard brakes may lock up below 30knots.

OUTBD BRAKE PRESS LO (C)

1. Normal landing distance .................................................... Multiply by:1.55 without thrust reversers1.40 with thrust reversers.

OUTBD BRAKES FAIL (C)

1. Normal landing distance .................................................... Multiply by:1.55 without thrust reversers1.40 with thrust reversers.

PARK/EMER BRAKE ON (C)

1. PARK/EMER BRAKE handle ..................................................... Stow.

If message remains:2. Normal landing distance .................................................... Multiply by:


CAUTION: All four brakes may be locked and landing control will be af-fected.

END

3/14/03



PK/EMER BRK PRESS LO (C)1. Normal brakes .............................................. Apply until chocks are in.

PLT BRAKE FAULT (C)

1. Use the copilot’s brakes.

WOW FAIL (C)


After touchdown:2. Flight spoilers.............................................................................EMER.

CAUTION: Normal brakes may be inoperative below 10 knots.

3. Directional control.......................... Maintain with differential braking.4. PARK/EMER BRAKE handle ......................... Apply below 10 knots.

LANDING GEAR MANUAL EXTENSION

1. Airspeed .............................................................. 250 KIAS maximum.2. LANDING GEAR switch ...............................................................DN.3. LG PULL handle............................................................................ Pull.

NOTE: Performing a sideslip to each side may help achieve MLG down-lock. Increased airspeed may be required to ensure downlock dur-ing sideslip.

4. LANDING GEAR indication............. Check for three DN indications.

All landing gear are down (three DN indications):


CAUTION: Do not stow the handle until the gear pins are installed andmaintenance is obtained.

(Continued)

END

END

END

Yes

No

3/14/03



LANDING GEAR MANUAL EXTENSION (Cont)

All landing gear are not down:

NOTE: If a gear up landing must be made, select a long, wide runwaywith as little crosswind as possible. If time and conditions per-mit, plan the descent to ensure minimum fuel remaining on theaircraft. Ensure sufficient fuel for a controlled, power-on ap-proach.

5. Brief the passengers as required. a. Location and operation of emergency exits.b. All loose items .................................................................. Secure.c. Seat belts and shoulder harnesses ...................................... Secure.d. Emergency landing brace position.

Descent checks:6. Pressurization .............................................................. LNDG ALT set.7. WING switch......................................................................As required.8. L and R ENG ANTI-ICE switches .....................................As required.


copilot, and standby, and cross-check. 10. L and R LANDING light switches .................................................. On.11. Cabin Check .........................................................................Complete.12. SMKG/BELTS switch ..................................................SMKG/BELTS.13. Fuel quantities and balance ........................................................ Check.

Approach checks:14. APU and Bleeds............................................................................... Set.15. Approach setup and crew briefing ........................................Complete.

Before Landing Checks:16. L LDG, NOSE LDG/TAXI, and R LDG light switches .................. On.17. DCU A and DCU B AURAL WARNING .................................... OFF.

This will disable all aural warnings.18. FLAPS .............................................................................................. 30.

No landing gear is extended:

a. Plan to land slightly nose high. Perform normal power-onapproach at VREF and touchdown at the lowest possible airspeedwith minimum sink rate. Do not decelerate below shaker speed.

b. Go to At touchdown below.

Partial Gear extended:

(Continued)

No

Yes

No

3/14/03



LANDING GEAR MANUAL EXTENSION (Cont)

The nose gear fails to extend:

a. Relocate passengers aft to obtain aft C.G., if possible.b. Hold the nose off the runway as long as elevator control is avail-

able.c. Normal braking may be used and spoilers deployed. Use the rud-

der and/or the brakes for directional control.d. Go to At touchdown below.

One main gear fails to extend:a. Plan to land on the same side of the runway as the extended gear.b. Hold the applicable wing up as long as possible. Maintain direc-

tional control with the rudder and the nose wheel steering.

At touchdown:19. L and R ENGINE FIRE switches ...................Lift guard, FIRE PUSH.20. Normal braking may be used and spoilers deployed. Use the rudder

and/or the brakes for directional control.

After aircraft stops:21. PARK/EMER BRAKE ....................................................................Set.22. APU switch ....................................................................................OFF.23. L and R BATT switches .................................................................OFF.24. Evacuate the aircraft:

a. Passenger Door ....................................Open and the exit aircraft.b. Emergency Exit ..............Open and exit using the wing step area.

Yes

No

3/14/03

Challenger 300 NON-NORMAL PROCEDURESLANDING PROCEDURES

Draft 2.8

SINGLE ENGINE LANDING

Descent Checks:1. Pressurization .............................................................. LNDG ALT set.2. WING switch......................................................................As required.3. L or R ENG ANTI-ICE switches .......................................As required.


copilot, and standby, and cross-check. 5. L and R LANDING light switches .................................................. On.6. Cabin Check ..........................................................................Complete.7. SMKG/BELTS switch ..................................................SMKG/BELTS.8. Fuel quantities and balance ........................................................ Check.


10. Final approach speed ....................................................................VREF.11. Normal landing distance .................................................... Multiply by:


12. Approach setup and crew briefing ........................................Complete.

Before Landing Checks:13. LANDING GEAR switch ...............................................................DN.

If the right engine is shutdown: a. ALTN FLAPS switch.............................................................. ON.

14. FLAPS ............................................................................................. 30.15. LANDING GEAR indication .................................................... Check.16. L LDG, NOSE LDG/TAXI, and R LDG light switches .................. On.

After landing:17. Applicable thrust reverser...................................................As required,

limit to maintain directional control.

NOTE: Do not deploy the thrust reverser on the inoperative engine.


3/14/03

NON-NORMAL PROCEDURES Challenger 300LANDING PROCEDURES


WING ANTI-ICE FAILURE LANDING

WARNING: - Approach low speed flight with care so that detection of ab-normal flying qualities can be obtained. Increased buffetmay indicate ice formation on the wing leading edge.

- Even small accumulations of ice on the wing leading edgecan cause an increase in stall speed, and possibly a degrada-tion in stall characteristics.

- Visually inspect wing for ice accumulation if possible. UseWING INSP light at night.

Descent Checks:1. Pressurization ..............................................................LNDG ALT set.2. L and R ENG ANTI-ICE switches..................................... As required.


copilot and standby, and cross-check. 4. L and R LANDING light switches...................................................On.5. Cabin Check .......................................................................... Complete.6. SMKG/BELTS switch.................................................. SMKG/BELTS.7. Fuel quantities and balance ........................................................Check.8. Airspeed .................. Increase to VMO/MMO if possible to disperse ice.

Approach Checks:9. APU and Bleeds ...............................................................................Set.

10. Final approach speed ...........................................................VREF + 20.11. Normal landing distance ....................................................Multiply by:

1.55 without thrust reversers.1.45 with thrust reversers.

12. Approach setup and crew briefing ....................................... Complete.

Before Landing Checks:13. LANDING GEAR switch ..............................................................DN.14. L LDG, NOSE LDG/TAXI, and R LDG light switches ...................On.15. FLAPS ..............................................................................................20.

3/14/03

Challenger 300 NON-NORMAL PROCEDURESMISCELLANEOUS SYSTEMS

Draft 2.8


EMER LIGHTS OFF (C)1. EMER LTS switch ....................................................................... ARM.

EMER LIGHTS ON (C)

The cabin emergency lights are on.

3/14/03

Challenger 300 NON-NORMAL PROCEDURESPOWERPLANT

Draft 2.8


L (R) ENGINE FLAMEOUT (C)1. Affected engine thrust lever............................................................ Idle.

If engine does not auto restart:

2. Refer to Engine Shutdown In Flight procedure, this chapter.

ENGINES FUEL BYPASS (C)

1. L and R FUEL PUMP switches ......................................................ON.2. Land as soon as possible.

L (R) ENGINE VIBRATION (C)

During Icing Conditions:1. Affected thrust lever ..................... Increase above 70% N, then as desired.

2. If ENGINE VIBRATION (C) persists, go to During Non-Icing Condi-tions procedure below.

During Non-Icing Conditions:1. Engine Instruments .............................................................Monitor for

abnormal indications (oil temperature/pressure, N1, ITT and N2) orunusual sounds or vibrations.

If ENGINE VIBRATION CAS remains on for more than 30 secondsand if conditions permit:2. Respective Thrust lever ..............................................................Adjust.

NOTE: Engine shutdown is not recommended unless there are other indi-cations of severe engine abnormalities.

L (R) ENG FUEL SOV FAIL (C)

1. Respective ENG RUN switch........................................................ OFF.2. Refer to Engine Shutdown in Flight Procedure, this chapter.

L (R) ENG OIL PRESS HIGH (C)

1. Affected thrust lever ................................................................. Reduce.

END

END

END

END

END

3/14/03

NON-NORMAL PROCEDURES Challenger 300POWERPLANT


L (R) ENG OIL TEMP HIGH (C)

1. Affected thrust lever..................................................................Reduce.

NOTE: Upon reduction of engine power, the oil temperature may rise ini-tially due to a reduction in fuel flow through the Fuel Heater OilCooler.

2. OIL TEMP................................................................................Monitor.

OIL TEMP remains high:

a. Affected thrust lever ................................................................Idle.b. Land as soon as practical.

a. Continue flight.

Yes

No

END

3/14/03



L (R) FADEC FAIL (C)If engine shutdown:1. Refer to Engine Shutdown In Flight procedure this chapter.

If engine decelerates to idle:1. Affected engine thrust lever............................................................ Idle.2. Land as soon as practical. Refer to single engine landing procedure

this chapter.

If engine continues to operate:1. Avoid rapid throttle movements. Expect deteriorated engine response.2. Engine Instruments ................................................................. Monitor.

L (R) REVERSER FAIL (C)

1. Affected thrust reverser ....................................................... Do not use.

L (R) START ABORTED (C)

1. Affected engine RUN switch......................................................... OFF.2. If conditions warrant, another start may be initiated.

a. Respective STARTER switch .......CRANK, hold for 30 seconds.b. Respective engine RUN switch ...........................................RUN.c. Respective STARTER switch ....................... START and release.

END

END

END

3/14/03



L (R) STARTER FAIL (C)GROUND:If the message comes on during start:1. Affected engine RUN switch .........................................................OFF.

If the message comes on any other time:1. Continue.

IN FLIGHT:

If attempting an airstart:1. Refer to Engine Airstart — Windmill Airstart, this chapter.

If the message comes on any other time:1. Continue.

L (R) STARTER FAIL ON (C)

GROUND:1. Affected engine RUN switch .......................................................... Off.2. L, R, and APU BLEED switches ...................................................OFF.

IN FLIGHT:

L STARTER FAIL ON CAS is displayed.

1. XBLEED switch ..........................................................................Close.2. L BLEED switch ...........................................................................OFF.

R STARTER FAIL ON CAS is displayed.

1. XBLEED switch ..........................................................................Close.2. APU BLEED switch ......................................................................OFF.3. R BLEED switch ...........................................................................OFF.

END

END

Yes

No

END

END

3/14/03



ENGINE SHUTDOWN IN FLIGHT

Affected Engine:1. Thrust lever ................................................................................. IDLE.2. ENGINE RUN switch ................................................................... OFF.

NOTE: The ENG FIRE switch should not be pushed unless a fuel or hy-draulic leak is suspected.

3. Rudder trim ....................................................................... As required.4. Electrical load ....................................Reduce, within generator limits.5. Applicable BLEED switch ........................................................... OFF.6. XBLEED switch ..........................................................................Open.7. Applicable ENG ANTI-ICE switch............................................... OFF.8. Monitor fuel balance. Crossflow as required.9. Land as soon as practical.

10. Refer to Engine Airstart, if applicable. Refer to Single-Engine Land-ing procedure or Thrust Reverser Deployed Landing procedure, thissection, as appropriate.

3/14/03



ENGINE AIRSTART

WARNING: Do not attempt an airstart following an engine failure whichwas accompanied by indications of internal engine damage orfire.

CAUTION: Do not attempt an airstart without an indication of N1 rota-tion.

Figure 05-32-01

BEFORE START

Affected Engine:1. Make sure that the aircraft is within the appropriate Airstart Envelope

as shown in Figure 05-32-01, this section.2. FUEL panel:

a. XFER switch ........................................................Closed. (not on)b. PUMP switch......................................................................AUTO.

3. ENG ANTI-ICE switch................................................................... Off.4. BLEED switch................................................................................OFF.5. Thrust lever .................................................................................IDLE.6. Conduct the following windmill, crossbleed, or APU assisted airstart.

BD100/AS907 Windmill Start Envelope

-5000

0

5000

10 000

15 000

20 000

25 000

30 000

0

20

40

60

80

100

120

140

160

180

200

220

240

260

280

300

320

AIRSPEED (KIAS)

PR

ES

SU

RE

AL

TIT

UD

E (

FT

)

Sta

rte

r A

ssis

t,or

WM

Sta

rt

Starter Assist

3/14/03



ENGINE AIRSTART (Cont)

START

Crossbleed starter assisted airstart1. BLEED pressure ..............................................................32 minimum.

Affected Engine:2. ENG RUN switch ............................................................................ON.3. STARTER switch .................................................. START and release.4. IGN and FUEL FLOW .............................................................. Check.5. ITT ...................................................................................... Check rise.

NOTE: Start may be as long as 3 minutes to idle.

If no indication of light-off is obtained within 20 seconds afterSTARTER switch — START:

a. Affected ENG RUN switch .................................................. OFF.b. Repeat a starter assisted airstart or refer to Engine Shutdown in

Flight procedure, this chapter.c. Go to After Start.

APU bleed starter assisted airstart (Below 20 000 ft)1. L and R BLEED switches.............................................................. OFF.2. APU BLEED switch ........................................................................ On.

Affected Engine:3. ENG RUN switch ............................................................................ON.4. STARTER switch ......................................................................START.5. IGN and FUEL FLOW .............................................................. Check.6. ITT ...................................................................................... Check rise.


If no indication of light-off is obtained within 20 seconds afterSTARTER switch — START:

a. Affected ENG RUN switch .................................................. OFF.b. Repeat a starter assisted airstart or refer to Engine Shutdown in

Flight procedure, this chapter.c. Go to After Start.

3/14/03



ENGINE AIRSTART (Cont)

Windmill Airstart

Affected Engine:1. ENG RUN switch (at 6% min N2) ..................................................ON.2. IGN and FUEL FLOW ...............................................................Check.3. ITT .......................................................................................Check rise.


If no indication of light-off is obtained within 20 seconds after EngineRUN switch — ON:

a. Affected ENGINE RUN switch ............................................OFF.b. Repeat an airstart or refer to Engine Shutdown in Flight proce-

dure, this chapter.

AFTER START

Affected Engine:1. Engine instruments .....................................................................Check.2. GEN switch ...........................................................................Check On.3. ENG ANTI-ICE switch...................................................... As required.4. L and R, and APU BLEED switch(es)............................... As required.

SINGLE ENGINE GO-AROUND

1. Autopilot ............................................. Disengage with TO/GA button.2. Thrust lever ......................................................................................TO.3. Pitch attitude ..................................Adjust as required to achieve VGA.

NOTE: Initially rotate toward flight director pitch guidance command, ad-just pitch as required to maintain VGA.

4. FLAPS...............................................................................................10.5. LANDING GEAR switch ..............................UP, after positive rate of

climb is established.6. Climb at VGA.7. When clear of obstacles, accelerate to VGA +23 and retract flaps.8. Go to After Takeoff, Normal procedures.

END

3/14/03


Draft 2.8


INTRODUCTION 05-41-01

Introduction To Advisory Messages ...................................... 05-41-01

AUTO FLIGHT 05-44-01

FD 1 FAIL (A)FD 2 FAIL (A) ........................................................................ 05-44-01


APU FAULT (A) .................................................................... 05-45-01

APU SHUTDOWN (A) .......................................................... 05-45-01

AVIONICS 05-47-01

FDR FAULT (A) .................................................................... 05-47-01

MFD X-TALK FAIL (A) .......................................................... 05-47-01

FIRE PROTECTION 05-52-01

FIREX BTL 2 LOW (A) ......................................................... 05-52-01

FLIGHT CONTROLS 05-53-01

STALL WARN ADVANCED (A) ............................................ 05-53-01

FUEL 05-54-01

FUEL GRAV XFLOW FAIL (A) .............................................. 05-54-01

FUEL XFER FAIL (A) ........................................................... 05-54-01

HYDRAULICS 05-55-01

AUX HYD SYS FAIL (A) ....................................................... 05-55-01

AUX HYD PUMP FAIL ON (A) ............................................. 05-55-01

L (R) HYD DC PUMP FAIL (A) ............................................. 05-55-01

3/14/03



ICE & RAIN PROTECTION 05-57-01

ICE DETECTOR FAULT (A) .................................................05-57-01

L (R) ENG A/ICE FAIL ON (A) ..............................................05-57-01

L (R) ENG ANTI-ICE FAULT (A) ...........................................05-57-02

LANDING GEAR, WHEEL AND BRAKE SYSTEM 05-58-01

NWS FAULT (A) ....................................................................05-58-01

POWER PLANT 05-62-01

ENG SYNC/M-HOLD FAIL (A) ..............................................05-62-01

L (R) ENG FUEL TEMP LOW (A) ..........................................05-62-01

L (R) ENGINE FUEL BYPASS (A).........................................05-62-01

L (R) ENGINE OIL BYPASS (A) ............................................05-62-01

3/14/03

Challenger 300 NON-NORMAL PROCEDURESINTRODUCTION

Draft 2.8


ADVISORY MESSAGES

These sections (05-40-00 through 05-69-XX) of the Non-Normal chaptercontain the advisory CAS (cyan) messages that have a procedure associatedwith them.

3/14/03

Challenger 300 NON-NORMAL PROCEDURESAUTO FLIGHT

Draft 2.8


FD 1 FAIL (A)FD 2 FAIL (A)

1. Autopilot ............................................................................. Disconnect.2. FGP XFR button....................................................Select operative FD.3. Autopilot ............................................................................. As desired.

END

3/14/03

Challenger 300 NON-NORMAL PROCEDURESAUXILIARY POWER UNIT

Draft 2.8


APU FAULT (A)1. XBLEED switch ........................................................................ Closed.2. L BLEED switch ............................................................................ON.3. APU BLEED switch ........................................................................Off. 4. R BLEED switch .............................................................................ON.5. APU switch.................................................................................... OFF.

APU SHUTDOWN (A)

1. XBLEED switch ........................................................................ Closed.2. L BLEED switch ............................................................................ON.3. APU BLEED switch ........................................................................Off. 4. R BLEED switch .............................................................................ON.5. APU switch.................................................................................... OFF.

END

END

3/14/03


Draft 2.8


FDR FAULT (A)

1. With the PARK/EMER BRAKE set, push ENGINE EVENT buttonfor two seconds.

MFD X-TALK FAIL (A)If cross-side tuning is desired:1. TUNE REVERSION switch..............................................CDU ONLY.

END

3/14/03

Challenger 300 NON-NORMAL PROCEDURESFIRE PROTECTION

Draft 2.8


FIREX BTL 2 LOW (A)

1. APU Shutdown:a. XBLEED switch ................................................................ Closed.b. L BLEED switch .....................................................................ON.c. APU BLEED switch ...............................................................Off.d. R BLEED switch .....................................................................ON.e. APU switch ............................................................................ OFF.

3/14/03

Challenger 300 NON-NORMAL PROCEDURESFUEL

Draft 2.8


FUEL GRAV XFLOW FAIL (A)

1. Fuel Quantities ........................................................................... Check.2. GRAVITY XFLOW switch ......................................................... Cycle.

GRAVITY XFLOW valve fails to open:

If fuel is imbalanced:a. FUEL XFER switch............................................................. Open.b. L or R FUEL PUMP switch (heavy wing) ..............................ON.c. Wing fuel quantity ........................................................... Monitor.

When fuel is balanced:d. L or R FUEL PUMP switch .................................................. OFF.e. FUEL XFER switch............................................................ Close.

GRAVITY XFLOW valve fails to close:(1) Sideslip ..................................................................Minimize.

FUEL XFER FAIL (A)

1. Fuel quantities ............................................................................ Check.2. FUEL XFER switch .................................................................... Cycle.

FUEL XFER valve fails to open:

If fuel is imbalanced:a. GRAVITY XFLOW switch ................................................OPEN.

NOTE: It may be necessary to use a sideslip to transfer fuel.

FUEL XFER valve fails to close:a. L and R FUEL PUMPS ........ Both OFF or Both ON as required.

Yes

No

END

END

Yes

No

END

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Draft 2.8


AUX HYD SYS FAIL (A)

Fluid quantity digits are green:

1. AUX HYDRAULIC PUMP switch........................................... AUTO.

Message goes out:

2. AUX HYDRAULIC PUMP switch............................................... OFF.

AUX HYD PUMP FAIL ON (A)

1. AUX HYDRAULIC PUMP switch............................................... OFF.

L (R) HYD DC PUMP FAIL (A)

1. Affected HYDRAULIC PUMP switch ...........................................ON.

If L (R) HYD DC PUMP FAIL persists: 2. Affected HYDRAULIC PUMP switch ......................................... OFF.

The engine driven pump will provide sufficient pressure.

Yes

Yes

NoEND

END

END

END

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Challenger 300 NON-NORMAL PROCEDURESICE & RAIN PROCTECTION

Draft 2.8


ICE DETECTOR FAULT (A)

In visible moisture or night and SAT is between +10 °C and -40 °C:1. WING ANTI-ICE switch ................................................................ON.2. L and R ENG ANTI-ICE switches .................................................ON.

L (R) ENG A/ICE FAIL ON (A)

1. Use Engine Anti-Ice On performance data, Performance chapter.

END

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NON-NORMAL PROCEDURES Challenger 300ICE & RAIN PROCTECTION


L (R) ENG ANTI-ICE FAULT (A)

1. Use Engine Anti-Ice On performance data, Performance chapter.

3/14/03

Challenger 300 NON-NORMAL PROCEDURESLANDING GEAR, WHEEL AND BRAKE SYSTEM

Draft 2.8


NWS FAULT (A)1. NWS switch.............................................................. Do Not turn OFF.

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Draft 2.8


ENG SYNC/M-HOLD FAIL (A)

1. SYNC switch ................................................................................. OFF.2. MACH HOLD switch......................................................................Off.

L (R) ENG FUEL TEMP LOW (A)

1. Descend to a warmer altitude.2. Monitor the affected engine(s).

L (R) ENGINE FUEL BYPASS (A)

1. Affected FUEL PUMP switch ........................................................ON.2. Engine and fuel synoptic pages ............................................... Monitor.

L (R) ENGINE OIL BYPASS (A)

1. Affected engine indications .................................................... Monitor.

END

END

END

END

3/14/03

Manual de Vuelo

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Transcript of Manual de Vuelo