B737-800 Full Flight Simulator · ATA 27 - Flight Controls 84 ... 31.2 EFIS CONTROL PANEL POWER...

Standard Product Specification Addendum 1 List of Malfunctions PROPRIETARY NOTICE: The information contained herein is confidential and/or proprietary to CAE Inc., and shall not be reproduced or disclosed in whole or in part, or used for any purpose whatsoever unless authorized in writing by CAE Inc. 29 September 2005 TPD no.A1600-B737 ADD1 Rev 3.0

C.P. 1800 Saint-Laurent, Quebec, Canada H4L 4X4 Tel (514) 341-6780 Fax (514) 341-7699

B737-800 Full Flight Simulator

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Revision History

REV. LEVEL DATE COMMENTS

3.0 2.1 2.0 1.1 0.0

29-Sep-2005 02-May-2003 30-Jan-2003 09-Dec-2002 03-Dec-2001

Updated to Reflect Latest Boeing Tail Updated to Reflect Engineering Changes Updated to Reflect Engineering Changes Updated to Reflect Engineering Changes Preliminary Documentation

Created by: Malfunction Coordinator Approved by: Evaluation Pilot Approved by: Project Manager

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Index Page ATA 21 - Air Conditioning & Press 1

21.1 EQUIPMENT COOLING OFF - EXHAUST..................................1 21.2 RAPID DEPRESSURIZATION (DIGITAL CPC).............................3 21.3 AUTO FAIL - OUTFLOW VALVE OPENS..................................4 21.4 PACK TRIP OFF....................................................6 21.5 PACK TRIP OFF RESETTABLE.........................................7 21.6 CABIN LEAK VARY 0% TO 100%.......................................8

ATA 22 - AutoFlight 10 22.1 LOCALIZER OFFSET...............................................10 22.2 FCC FAILURE.....................................................11 22.3 FLARE MODE FAILURE..............................................13 22.4 AUTOPILOT ACTUATOR FAILURE......................................15 22.5 FD FAIL.........................................................16 22.6 RUNAWAY STABILIZER..............................................17 22.7 A/T COMPUTER FAILURE............................................18 22.8 AUTOPILOT DISENGAGE SWITCH FAILED...............................19 22.9 LNAV SWITCH FAILURE.............................................20 22.10 VNAV SWITCH FAILURE.............................................22 22.11 TAKEOFF/GO-AROUND SWITCH FAILURE................................24

ATA 23 - Communications 26 23.1 VHF COMM TRANSCEIVER FAIL.......................................26

ATA 24 - Electrics 28 24.1 GENERATOR DRIVE DISCONNECT FAIL.................................28 24.2 GENERATOR DRIVE LOW OIL PRESSURE................................29 24.3 GENERATOR DRIVE SHAFT SHEAR.....................................30 24.4 APU GENERATOR DRIVE FAIL (EXCITER FIELD)........................31 24.5 BTB FAIL IN OPEN POSITION.......................................32 24.6 BTB FAIL IN CLOSED POSITION.....................................33 24.7 GENERATOR DRIVE OVERVOLTAGE.....................................35 24.8 LOSS OF BOTH ENGINE DRIVEN GENERATORS...........................36 24.9 BATTERY BUS OFF.................................................37 24.10 TRANSFORMER RECTIFIER FAIL......................................38 24.11 STATIC INVERTER FAIL............................................40 24.12 BATTERY CHARGER FAIL............................................41 24.13 BATTERY DISCHARGED..............................................42 24.14 AC STBY POWER AUTO TRANSFER FAIL................................44 24.15 AC TRANSFER BUS OFF.............................................45 24.16 MAIN BUS OFF....................................................46 24.17 STBY BUS OFF....................................................47

ATA 26A - Fire Protection (No Smoke) 48 26A.1 WHEEL WELL FIRE - CONTROLLABLE..................................48 26A.2 ENGINE OVERHEAT.................................................49 26A.3 ENGINE FIRE - 1 BOTTLE..........................................50 26A.4 ENGINE FIRE - 2 BOTTLES.........................................52 26A.5 ENGINE FIRE - UNEXTINGUISHABLE..................................54 26A.6 APU FIRE - EXTINGUISHABLE.......................................56 26A.7 APU FIRE - UNEXTINGUISHABLE.....................................58 26A.8 ENG L(R) BOTTLE FAILS TO DISCH..................................59 26A.9 APU BOTTLE FAILS TO DISCH.......................................61 26A.10 CARGO FIRE......................................................62 26A.11 APU DETECTOR FAIL...............................................64

ATA 26B - Fire Protection (Smoke) 65 26B.1 WHEEL WELL FIRE - CONTROLLABLE..................................65 26B.2 ENGINE OVERHEAT.................................................66 26B.3 ENGINE FIRE - 1 BOTTLE..........................................67 26B.4 ENGINE FIRE - 2 BOTTLES.........................................69

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26B.5 ENGINE FIRE - UNEXTINGUISHABLE..................................71 26B.6 APU FIRE - EXTINGUISHABLE.......................................73 26B.7 APU FIRE - UNEXTINGUISHABLE.....................................75 26B.8 ENG L(R) BOTTLE FAILS TO DISCH..................................76 26B.9 APU BOTTLE FAILS TO DISCH.......................................78 26B.10 CARGO FIRE......................................................79 26B.11 APU DETECTOR FAIL...............................................81 26B.12 ELECTRICAL SMOKE (P6 CB PANEL)..................................82 26B.13 PACK SMOKE......................................................83

ATA 27 - Flight Controls 84 27.1 YAW DAMPER HARDOVER.............................................84 27.2 AILERON SURFACE JAM.............................................85 27.3 ELEVATOR SURFACE JAM............................................87 27.4 ELEVATOR FEEL COMPUTER FAIL.....................................88 27.5 JAMMED STABILIZER...............................................90 27.6 STABILIZER RUNAWAY - MAIN ELECTRIC..............................91 27.7 STAB TRIM ACTUATOR CIRCUIT BREAKER TRIP.........................93 27.8 FLIGHT SPOILER PANEL JAM - LEFT WING............................94 27.9 FLIGHT SPOILER PANEL JAM - RIGHT WING...........................95 27.10 SPEED BRAKE DO NOT ARM LIGHT - ON...............................96 27.11 AUTO SPEEDBRAKE MODULE FAIL.....................................97 27.12 SPEEDBRAKE EXTENDED LIGHT ON....................................99 27.13 STANDBY RUD ON.................................................100

ATA 27F - Flaps/Slats 101 27F.1 FLAP POSITION IND FAIL.........................................101 27F.2 TE FLAP FAILS IN POSITION......................................102 27F.3 TE FLAP ASYM WING..............................................104 27F.4 LE FLAP FAILS IN POSITION......................................105 27F.5 AUTO SLAT FAIL.................................................107 27F.6 LE FLAP EXTENDED LIGHT FAIL....................................109 27F.7 LE FLAPS TRANSIT LIGHT ON......................................110 27F.8 FLAP LOAD LIMITER FAILS........................................111

ATA 28 - Fuel 113 28.1 TANK BOOST PUMP FAILS..........................................113 28.2 CENTER TANK BOOST PUMP FAILS...................................114 28.3 CROSSFEED VALVE FAIL IN POSITION...............................115 28.4 TANK LEAK......................................................116

ATA 29 - Hydraulics 118 29.1 HYDRAULIC PUMP LOW PRESSURE - ENGINE PUMP......................118 29.2 HYDRAULIC PUMP LOW PRESSURE - ELECTRIC PUMP....................119 29.3 ELECTRIC PUMP OVERHEAT.........................................121 29.4 SYS RSVR FLUID LOSS - EMDP LINE................................122 29.5 RESERVOIR LEAK - HI RATE.......................................124 29.6 SYS RSVR FLUID LOSS - EDP LINE.................................126

ATA 30 - Ice and Rain 128 30.1 ENGINE COWL VALVE - PRESSURE VALVE FAILS.......................128 30.2 WINDOW OVERHEAT - RESETTABLE...................................130 30.3 WING A/I VALVE FAILS IN POSITION...............................132

ATA 31 - Instruments & Displays 134 31.1 MAP FAILURE FOR DEUS...........................................134 31.2 EFIS CONTROL PANEL POWER FAIL..................................137 31.3 DISPLAY ELECTRONIC UNIT (DEU) FAIL.............................139 31.4 DU FAIL - INBOARD/OUTBOARD.....................................142 31.5 DU FAIL - UPPER/LOWER..........................................144

ATA 32 - Landing Gear/Brakes 146 32.1 AIR/GND SENSOR FAIL IN POSITION - NOSEGEAR.....................146 32.2 AIR/GND SENSOR FAIL IN POSITION - MAIN GEAR....................147 32.3 GEAR COLLAPSE..................................................148 32.4 GEAR LEVER FAIL IN POSITION....................................149 32.5 GEAR SELECTOR VALVE FAIL.......................................150 32.6 GEAR UP LOCK FAIL..............................................151 32.7 PARTIAL OR GEAR UP LANDING.....................................152 32.8 WHEEL BRAKE STUCK IN POSITION..................................153 32.9 WHEEL BRAKE INOP...............................................154

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32.10 BRAKE PRESS INDICATE ZERO PSI..................................155 32.11 ANTI-SKID INOPERATIVE..........................................156 32.12 AUTOBRAKE INOPERATIVE..........................................158 32.13 TIRE BURST - MAIN GEAR.........................................159 32.14 TIRE BURST - NOSE GEAR.........................................160 32.15 GEAR FAILS TO UNLOCK...........................................161 32.16 GEAR DN LK IND FAIL............................................162

ATA 34 - Navigation 163 34.1 ILS RECEIVER FAIL..............................................163 34.2 GLIDESLOPE RECEIVER FAIL.......................................165

ATA 34A - Flight Instruments 167 34A.1 PITOT PROBE HEAT FAIL..........................................167 34A.2 AOA PROBE HEAT FAIL............................................170 34A.3 TAT PROBE HEAT FAIL............................................172 34A.4 RADIO ALTIMETER FAIL...........................................174 34A.5 ISFD FAIL......................................................175 34A.6 ISFD ROLL/PITCH FAIL...........................................176

ATA 34E - EGPWS 178 34E.1 EGPWS FAIL.....................................................178 34E.2 EGPWS FALSE MODE 2 WARNING.....................................179

ATA 34F - FMS 181 34F.1 FMC FAIL.......................................................181 34F.2 MCDU FAIL......................................................186

ATA 34I - IRS 187 34I.1 ADIRU - IR FUNCTION FAIL.......................................187 34I.2 IR FAILS TO ALIGN..............................................189 34I.3 ADIRU - IR MOTION..............................................191 34I.4 ADIRU - IR POSITION DRIFT......................................193 34I.5 IR NON-CRITICAL FAULT..........................................195 34I.6 ADIRU ON DC....................................................198 34I.7 ADIRU DC FAIL..................................................201

ATA 34N - GPS 203 34N.1 GPS FAIL - BOTH SYSTEMS........................................203

ATA 34W - Weather Radar 204 34W.1 WXR R/T FAIL...................................................204

ATA 36 - Pneumatics 205 36.1 WING BODY OVERHEAT - LEAD EDGE LEAK............................205 36.2 APU BLEED VALVE FAILS IN POS...................................206 36.3 BLEED TRIP OFF.................................................208 36.4 BLEED TRIP OFF - RESETTABLE....................................209 36.5 PRSOV VLV FAILS IN POS.........................................210 36.6 PRECOOLER CONTROL VALVE FAILS CLOSED...........................212 36.7 HP VALVE FAILS OPEN............................................213 36.8 HP VALVE FAILS CLOSED..........................................215 36.9 ISOLATION VALVE FAILS CLOSED...................................216 36.10 ZONE TEMP - RESETTABLE (ALSO VIA IOS)..........................217

ATA 49 - APU 218 49.1 APU START SWITCH - OFF INOP....................................218 49.2 APU HOT START..................................................219 49.3 HUNG START.....................................................220 49.4 OVERSPEED......................................................221 49.5 STARTER MOTOR FAIL.............................................222 49.6 APU LOW AIR PRESSURE...........................................223 49.7 HIGH OIL TEMPERATURE...........................................224 49.8 LOW OIL PRESSURE...............................................225

ATA 52 - Doors 226 52.1 CARGO DOOR OPEN................................................226 52.2 DOOR SYSTEM ANNUNCIATOR LT ON (SW).............................227 52.3 CRG/EQUIP DOOR SYSTEM ANNUNCIATOR LT ON (SW)...................228

ATA 71 - Engine - Failures 229 71.1 ENGINE TURBINE BLADE FAILURE...................................229 71.2 ENGINE FLAMEOUT (AUTO-RESTARTABLE).............................230 71.3 ENGINE FLAMEOUT (NO RESTART POSSIBLE)..........................231

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71.4 ENGINE SUDDEN SEIZURE..........................................232 71.5 ENG STALL/SURGE RECOVERABLE (IF N1 < 70%)......................233 71.6 ENGINE STALL/SURGE NOT RECOVERABLE.............................234 71.7 ENGINE FUEL SHUTOFF VALVE FAILURE..............................235 71.8 BIRD STRIKE - ENG FAILURE......................................237 71.9 VOLCANIC ASH...................................................238 71.10 ENGINE SEPARATION..............................................240

ATA 73 - Engine - Faults 241 73.1 ENGINE FUEL FILTER BYPASS......................................241 73.2 FADEC FAILED IN ALTERNATE MODE.................................242 73.3 VBVS OFF SCHEDULE..............................................244 73.4 HIGH ENGINE VIBRATIONS WITH MOTION EFFECTS.....................245 73.5 EEC DATA BUS TO BOTH DEUS FAIL.................................246 73.6 THRUST REVERSER UNLOCKED (WITH BUFFET).........................248 73.7 T/R SLEEVE LOCK DOES NOT UNLOCK................................250 73.8 T/R SLEEVES LOCK SENSORS SENSE "UNLOCKED"......................252 73.9 ENGINE OIL LOW PRESSURE........................................254 73.10 ENGINE OIL LEAK................................................255 73.11 OIL FILTER BYPASS..............................................256 73.12 ENGINE OIL HIGH TEMPERATURE....................................257 73.13 FADEC FAULT....................................................259 73.14 ENGINE IDLE DISAGREE...........................................260 73.15 EGT OVERLIMITS (ABOVE 950 DEG C)...............................262

ATA 80 - Engine - Start Faults 263 80.1 ENGINE HOT START...............................................263 80.2 ENGINE HUNG START - LOW FUEL...................................265 80.3 START VALVE FAILS IN POSITION..................................266 80.4 IGNITION EXCITER FAILURE.......................................267

Total Malfunctions: 185

Boeing 737-800 FFS Standard Product Specification – Addendum 1 ATA 21 - Air Conditioning & Press List of Malfunctions

CAE Inc. TPD No: A1600-B737 Thu, 29 September 2005 1 Revision 3.0

Use or disclosure of this document is subject to the restriction

On the title page of this document.

ATA 21 - Air Conditioning & Press

21.1 EQUIPMENT COOLING OFF - EXHAUST

CDB Label: TF2127001 NORM TF2127002 ALTN

Failure Description

Overheat condition is detected on the Exhaust fan.

Failure Effects/Indications

FLIGHT DECK EFFECTS: ------------------- - EQUIPMENT COOLING EXHAUST OFF lt illuminates - MASTER CAUTION lts illuminate - OVERHEAD annunciator illuminates - EQUIPMENT COOLING EXHAUST OFF lt, MASTER CAUTION lts, and the OVERHEAD annunciator can be extinguished if remaining fan is not failed and selected

Malfunction Check

1. Select TAKEOFF B via ATM REPOSITIONS page. 2. Position the EQUIP COOLING EXHAUST sw to NORMAL. Insert the NORM malfunction. (a) EQUIP COOLING EXHAUST illuminates when the __ __ __ OFF lt temperature rises above the overheat value (b) MASTER CAUTION lts illuminate __ __ __ (2) (c) OVERHEAD lt illuminates __ __ __ 3. Position the EQUIP COOLING EXHAUST sw to ALTERNATE. (a) EQUIP COOLING EXHAUST extinguishes when the __ __ __ OFF lt temperature decreases below the overheat reset value (b) MASTER CAUTION lts extinguish __ __ __ (2)





(c) OVERHEAD lt extinguishes __ __ __ 4. Insert the ALTN malfunction. (a) EQUIP COOLING EXHAUST illuminates __ __ __ OFF lt 5. Remove the malfunctions. Return the EQUIP COOLING EXHAUST sw to NORMAL.





ATA 123Hidden123

21.2 RAPID DEPRESSURIZATION (DIGITAL CPC)

CDB Label: TF2131001

Failure Description

Cabin window blowout.


FLIGHT DECK EFFECTS: ------------------- - Outflow VALVE indicator goes fully closed - CABIN CLIMB rate indicator shows max climb rate - CABIN ALT indicator increases to A/C altitude - DIFF PRESS indicator decreases towards 0 psi - Altitude warning horn sounds for CABIN ALT above 10,000 ft Note: Please allow 30 seconds for pressurization system to stabilize after a REPOSITION, CABIN PRESSURE RESET (or a SYSTEM RESET, or a TOTAL RESET). Inserting a depressurization malfunction before the end of this delay will not produce the expected effects.

Malfunction Check

1. Select AIR WORK FL370 via ATM REPOSITIONS page. 2. Insert the malfunction. (a) Effects as above __ __ __ 3. Remove the malfunction. Select the CABIN PRESSURE RESET to SCHEDULE via the IOS. (a) Cabin pressure return to normal __ __ __ indications





ATA 123Hidden123

21.3 AUTO FAIL - OUTFLOW VALVE OPENS

CDB Label: TF2131021 AUTO TF2131022 ALTN

Failure Description

Internal automatic pressure controller failure drives the outflow valve to open.


FLIGHT DECK EFFECTS: -------------------- - Outflow VALVE indicator is driven toward the open position when malfunction is inserted - AUTO FAIL lt illuminates and the ALTN lt illuminates - AUTO FAIL lt extinguishes if the PRESSURIZATION MODE selector is selected to ALTN and a single automatic channel failure condition exists - AUTO FAIL lt and the ALTN lt extinguish if the PRESSURIZATION MODE selector is selected to MAN - AUTO FAIL lt illuminates and the ALTN lt extinguishes if a dual automatic channel failure condition exists and the PRESSURIZATION MODE selector is selected to AUTO or ALTN - Aircraft depressurizes if a dual automatic channel failure condition exists - Manual mode is available to control cabin pressure If the AUTO FAIL lt illuminates: - MASTER CAUTION lts illuminate - AIR COND annunciator illuminates

Malfunction Check

1. Select AIR WORK FL200 via ATM REPOSITIONS page. Wait approximately 30s for the CPC RESET. 2. Insert the AUTO malfunction. (a) CABIN ALTITUDE starts increasing __ __ __ indicator (b) CABIN VERTICAL SPEED starts increasing __ __ __ indicator (c) AUTO FAIL lt and illuminate when CPC __ __ __





ALTN lt detect a fault*; controllers turn automatically to alternate mode * Several faults can be detected by the CPC, such as a loop closure fault or a cabin pressure rate of change fault. 3. Position the pressurization mode selector to ALTN. (a) AUTO FAIL lt extinguishes __ __ __ 4. Insert the ALTN malfunction. (a) AUTO FAIL lt illuminates __ __ __ (b) ALTN lt extinguishes __ __ __ 5. Remove the malfunctions. Position the mode selectors to MAN, then back the AUTO. (a) AUTO FAIL lt extinguishes __ __ __ (b) ALTN lt remains extinguished __ __ __





ATA 123Hidden123

21.4 PACK TRIP OFF

CDB Label: TF2151001 LEFT TF2151002 RIGHT

Failure Description

Compressor Discharge OVHT switch fails closed.


FLIGHT DECK EFFECTS: ------------------- - Pack shuts down - Failure remains when TRIP RESET switch is depressed On Air Conditioning Two Zones Option only: - PACK TRIP OFF lt illuminates - MASTER CAUTION lts illuminate - AIR COND annunciator illuminates On Air Conditioning Three Zones Option only: - PACK lt illuminates - MASTER CAUTION lts illuminate - AIR COND annunciator illuminates

Malfunction Check

1. Select TAKEOFF B via ATM REPOSITIONS page. 2. Insert the LEFT malfunction. (a) Effects as above __ __ __ __ __ __ 3. Press the TRIP RESET button. (a) Effects as above __ __ __ __ __ __ 4. Remove the malfunction. Press the TRIP RESET button. 5. Repeat checks 2 to 4 for the RIGHT malfunction.





ATA 123Hidden123

21.5 PACK TRIP OFF RESETTABLE


Failure Description

Temporary malfunction of the Compressor Discharge OVHT switch which detects a false overheat.


FLIGHT DECK EFFECTS: ------------------- - Pack shuts down - Failure is reset when TRIP RESET switch is depressed On Air Conditioning Two Zones Option only: - PACK TRIP OFF lt illuiminates - MASTER CAUTION lts illuminate - AIR COND annunciator illuminates - AIR MIX VALVE indicator drives to fully COLD On Air Conditioning Three Zones Option only: - PACK lt illuminates - MASTER CAUTION lts illuminate - AIR COND annunciator illuminates

Malfunction Check

1. Select TAKEOFF B via ATM REPOSITIONS page. 2. Insert the LEFT malfunction. (a) Effects as above __ __ __ __ __ __ 3. Press the TRIP RESET button. (a) Effects as above __ __ __ __ __ __ 4. Repeat checks 2 and 3 for the RIGHT malfunction.





ATA 123Hidden123

21.6 CABIN LEAK VARY 0% TO 100%

CDB Label: TV2131001 LEFT

Failure Description

Abnormal structural leak. Range is 0 to 100%.


FLIGHT DECK EFFECTS: ------------------- - Cabin may not pressurize depending on the size of the leak selected Note: After removing the malfunction, CABIN ALTITUDE indication decreases and returns to pressure schedule. The delay required for the CABIN ALTITUDE indicator to return to schedule varies depending on the cabin altitude at which the malfunction is removed. If the altitude is allowed to diverge greatly off-schedule before the malfunction is removed, the delay can exceed 10 minutes.

Malfunction Check

1. Select flight altitude to 37 000 ft on the Pressurization panel. Select AIR WORK FL370 via the ATM REPOSITIONS page. Wait 30 seconds for the CPC RESET. 2. Insert the malfunction. 3. Set a leak at several percentages. (a) CABIN ALTITUDE increases at a rate in __ __ __ indicator accordance with the percentage selected 4. Remove the malfunction. (a) Outflow valve starts modulating __ __ __ position indicator





(b) CABIN ALTITUDE decreases and returns __ __ __ indicator to pressure schedule* * The delay required for the CABIN ALTITUDE indication to return to schedule varies depending on the cabin altitude at which the malfunction is removed. If the altitude is allowed to diverge greatly off-schedule before the malfunction is removed, the delay can exceed 10 minutes. To accelerate the return to schedule (optional): 5. Press the CABIN PRESSURE RESET TO SCHEDULE button on the Pressurization Maintenance Page. Allow 30s for system to stabilize. (a) Outflow valve position returns to the position __ __ __ indicator it had before inserting the malfunction (b) CABIN ALTITUDE returns to pressure __ __ __ indicator schedule

Boeing 737-800 FFS Standard Product Specification – Addendum 1 ATA 22 - AutoFlight List of Malfunctions




ATA 22 - AutoFlight

22.1 LOCALIZER OFFSET

CDB Label: TF2201001 1 TF2201002 2

Failure Description

Offset introduced to sensed APFD signal equivalent to 0.75 dot deviation.


FLIGHT DECK EFFECTS: ------------------- - A/P tracks localizer 0.75 dots left/right of the beam

Malfunction Check

1. Select ON ILS 6 NM via ATM REPOSITIONS page. Establish the A/C in a dual A/P approach. 2. Insert the system 1 malfunction. (a) EFIS LOC indicator shows 0.75 dot deviation __ __ __ to the left of the __ __ __ runway centerline (b) A/C lands 0.75 dot to the __ __ __ left of the runway __ __ __ centerline 3. Remove the malfunction. 4. Repeat checks 1 to 3 for the system 2 malfunction.





ATA 123Hidden123

22.2 FCC FAILURE

CDB Label: TF2201011 A TF2201012 B

Failure Description

Internal computer failure.


FLIGHT DECK EFFECTS: ------------------- - F/D flag appears on the Primary EFIS display or PFD - A/P disconnects and/or can not be engaged - With both malfunctions selected, SEL SPD message appears above CAPT & F/O airspeed indicator & airspeed cursor removed - With both malfunctions selected, SPEED TRIM & MACH TRIM FAIL lts illuminate

Malfunction Check

1. Select TAKEOFF B via ATM REPOSITIONS page. Engage A/P A in CMD or CWS. Insert the system A malfunction. (a) A/P A disengages __ __ __ __ __ __ (b) Capt and F/O A/P red flash __ __ __ disengage lts __ __ __ (c) A/P disengage warning sounds __ __ __ tone __ __ __ (d) Capt F/D flag A(B) in view, B(A) __ __ __ out of view __ __ __ (e) F/O F/D flag B(A) out of view, A(B) __ __ __ in view __ __ __ 2. Attempt to position A/P A in CMD or CWS. (a) A/P A does not latch in CMD __ __ __ or CWS __ __ __





3. Cancel the disengage warnings. Remove the malfunction. 4. Repeat checks 1 to 3 for the system B malfunction.





ATA 123Hidden123

22.3 FLARE MODE FAILURE

CDB Label: TF2201061 A TF2201062 B TF2201063 BOTH

Failure Description

No flare mode.


FLIGHT DECK EFFECTS: ------------------- System A & B malfunctions or BOTH inserted: - Channels A & B annunciate FLARE armed but do not flare System A or B malfunction only: - Channels A & B annunciate FLARE armed - At 50ft RA, FLARE mode engages on non-failed side - FLARE arm annunciation disappears on failed side - A/P disconnects

Malfunction Check

1. Select ON ILS 6 NM via ATM REPOSITIONS page. Establish the A/C in a dual A/P approach. 2. Insert the system A and B malfunctions. 3. 16s after 1500 ft radio altitude: (a) PFD FMA displays FLARE (arm) __ __ __ __ __ __ 4. Continue approach to touchdown. (a) PFD FMA does not display FLARE __ __ __ (engaged) __ __ __ (b) A/C does not flare __ __ __ __ __ __ 5. Remove the malfunctions. Repeat checks 2 to 5 for the BOTH malfunction.





6. Select ON ILS 6 NM via ATM REPOSITIONS page. Establish the A/C in dual A/P approach. 7. Insert the system A malfunction. 8. 16s after 1500 ft radio altitude: (a) PFD FMAs display FLARE (arm) __ __ __ __ __ __ 9. At 50 ft radio altitude: (a) PFD FMA on displays FLARE (engaged) __ __ __ non-failed side __ __ __ (b) PFD FMA on FLARE (arm) disappears __ __ __ failed side __ __ __ (c) A/P disconnects __ __ __ __ __ __ 10. Remove malfunction and repeat checks 6 to 10 for the system B malfunction.





ATA 123Hidden123

22.4 AUTOPILOT ACTUATOR FAILURE


Failure Description

Autopilot aileron actuator transfer valve fails.


FLIGHT DECK EFFECTS: ------------------- - A/P disengages

Malfunction Check

1. Select AIR WORK FL100 via ATM REPOSITIONS page. Engage A/P A or B. 2. Insert the malfunction. (a) A/P disengages __ __ __ 3. Remove the malfunction.





ATA 123Hidden123

22.5 FD FAIL

CDB Label: TF2211021 1 TF2211022 2

Failure Description

FD switch fails internally.


FLIGHT DECK EFFECTS: ------------------- - FD disengages (bar bias out of view) if engaged - FD cannot be engaged

Malfunction Check

1. Select TAKEOFF B via ATM REPOSITIONS page. Position the Capt and F/O F/D sws to ON. Press MCP ALT HLD & HDG SEL MSS. 2. Insert A system malfunction. (a) Capt PFD FMA no modes displayed __ __ __ __ __ __ (b) Capt F/D BARS out of view __ __ __ __ __ __ 3. Remove the malfunction. (a) Capt PFD FMA displays FD __ __ __ __ __ __ 4. Repeat checks 2 and 3 for B system malfunction.





ATA 123Hidden123

22.6 RUNAWAY STABILIZER


Failure Description

Latched trim detector.


FLIGHT DECK EFFECTS: ------------------- - Stab out of trim lt illuminates - Stabilizer runs away in the direction of the last trim demand Notes: - Column activates the cutout sw at +5.5 degrees (AFT) position and -2.8 degrees (FWD) position

Malfunction Check

1. Select AIR WORK FL100 via ATM REPOSITIONS page. Engage A/P A or B. Insert the malfunction and initiate an A/P trim command. (a) Stabilizer runs away in the __ __ __ direction of the last trim demand (b) Stabilizer out of illuminates __ __ __ trim light 2. Remove the malfunction. Note: Column activates cutout sw at +5.5 degrees (AFT) position and -2.8 degrees (FWD) position.





ATA 123Hidden123

22.7 A/T COMPUTER FAILURE


Failure Description

Internal computer failure.


FLIGHT DECK EFFECTS: ------------------- - A/T disconnects and/or cannot be engaged

Malfunction Check

1. Select TAKEOFF B via ATM REPOSITIONS page. Initialize the FMC with OAT. Arm the A/T for takeoff. 2. Insert the malfunction. (a) A/T disengages __ __ __ 3. Attempt to arm the A/T. (a) A/T does not arm __ __ __ 4. Remove the malfunction.





ATA 123Hidden123

22.8 AUTOPILOT DISENGAGE SWITCH FAILED

CDB Label: TF2212021 FCC A TF2212022 FCC B

Failure Description

Pressing disengage switch has no effect.


FLIGHT DECK EFFECTS: ------------------- - A/P does not disengage

Malfunction Check

1. Select AIR WORK FL100 via ATM REPOSITIONS page. Engage A/P A in CMD. 2. Insert the FCC A malfunction. Press the Capt A/P disengage switch. (a) A/P remains engaged __ __ __ __ __ __ 3. Remove the malfunction. 4. Repeat checks 1 to 3 for the FCC B malfunction.





ATA 123Hidden123

22.9 LNAV SWITCH FAILURE


Failure Description

MCP LNAV switch failure.


FLIGHT DECK EFFECTS: ------------------- - LNAV mode cannot be engaged or disengaged using MCP switch - Selecting another mode still possible

Malfunction Check

1. Select TAKEOFF B via ATM REPOSITIONS page. Load the FMC with Route & Performance data. Perform a normal T/O and at 400 ft and engage A/P A in CMD. Insert the system A malfunction. Press the MCP LNAV MSS. (a) Effects none __ __ __ __ __ __ __ __ __ 2. Remove the malfunction and disengage LNAV mode. Reinsert the system A malfunction. 3. Press the MCP LNAV MSS. (a) Effects none __ __ __ __ __ __ __ __ __ 4. Remove the malfunction. 5. Repeat checks 1 to 4 for the system B and BOTH malfunction.





ATA 123Hidden123

22.10 VNAV SWITCH FAILURE


Failure Description

MCP VNAV switch fails.


FLIGHT DECK EFFECTS: ------------------- - VNAV mode cannot be either engaged or disengaged using the MCP switch - Selecting other mode still possible

Malfunction Check

1. Select TAKEOFF B via ATM REPOSITIONS page. Load the FMC with Route & Performance data. Perform a normal T/O and at 400 ft and engage A/P A in CMD. Insert the system A malfunction. Select VNAV mode using the VNAV switch. (a) PFD FMA VNAV extinguished __ __ __ display __ __ __ __ __ __ (b) VNAV mode doesn't engage __ __ __ __ __ __ __ __ __ 2. Remove the malfunction. 3. Select VNAV mode using the VNAV switch. 4. Reinsert the system A malfunction. 5. Press the MCP VNAV MSS. (a) VNAV mode does not disengage __ __ __





__ __ __ __ __ __ (b) PFD FMA VNAV illuminated __ __ __ display __ __ __ __ __ __ 6. Remove the malfunction. 7. Repeat checks 1 to 6 for the system B and BOTH malfunctions.





ATA 123Hidden123

22.11 TAKEOFF/GO-AROUND SWITCH FAILURE

CDB Label: TF2211091 1 TF2211092 2

Failure Description

Throttle TOGA switch fails.


FLIGHT DECK EFFECTS: ------------------- - FCC does not recognize pushbutton presses and will not engage TOGA modes

Malfunction Check

1. Select TAKEOFF B via the ATM REPOSITIONS page. Program TEMPERATURE on the FMC takeoff page. Position the A/T ARM sw to ARM. Position the Capt and F/O F/D sws to ON. 2. Insert the system 1 malfunction. 3. Press the left TO/GA sw. (a) Left TO/GA sw has no effect __ __ __ __ __ __ 4. Press the right TO/GA sw. (a) Right TO/GA sw AFDS take-off mode __ __ __ __ __ __ 5. Select ON ILS 6 NM via the ATM REPOSITONS page. Establish the A/C on a dual F/D approach. At 200 ft radio altitude, press the left TO/GA sw. (a) Left TO/GA sw has no effect __ __ __ __ __ __





6. Shortly after, press the right TO/GA sw. (a) Right TO/GA sw AFDS go-around __ __ __ __ __ __ 7. Remove the malfunction. 8. Repeat checks 2 to 7 for the system 2 malfunction.

Boeing 737-800 FFS Standard Product Specification – Addendum 1 ATA 23 - Communications List of Malfunctions




ATA 23 - Communications

23.1 VHF COMM TRANSCEIVER FAIL

CDB Label: TF2312001 1 TF2312002 2 TF2312003 3

Failure Description

VHF transmitter/receiver fails.


FLIGHT DECK EFFECTS: ------------------- - No transmission/reception possible on VHF radio

Malfunction Check

1. Select GRD PWR via ATM REPOSITIONS page. Ensure all CBs are in. 2. Insert the system 1 malfunction. (a) VHF 1 transmission not possible __ __ __ from any crew member __ __ __ to instructor __ __ __ (b) VHF 1 transmission not possible __ __ __ from instructor to __ __ __ crew __ __ __ 3. Repeat check 2 for the VHF2 and VHF3 malfunctions. Maintenance: (if applicable) ----------- Collins LRU: 4. Press and release the test button on LRU. (a) LRU led still illuminated red __ __ __ after test __ __ __ __ __ __

Boeing 737-800 FFS Standard Product Specification – Addendum 1 ATA 23 - Communications List of Malfunctions




Allied Signal LRU: 5. Press on the "Push to Test" button on LRU. (a) Failure page appears after test is __ __ __ finished __ __ __ __ __ __ Press the right button ("Why?" button). (a) Failed page with or appears __ __ __ without external __ __ __ failure __ __ __ 6. Press the left button ("Return" button). 7. Remove malfunction. 8. Repeat checks 2 to 7 for system 2 and 3 malfunctions.

Boeing 737-800 FFS Standard Product Specification – Addendum 1 ATA 24 - Electrics List of Malfunctions




ATA 24 - Electrics

24.1 GENERATOR DRIVE DISCONNECT FAIL

CDB Label: TF2410011 1 TF2410012 2

Failure Description

Protective CB trips due to short circuit on generator drive disconnect solenoid circuit.


FLIGHT DECK EFFECTS: ------------------- - Generator drive cannot be disconnected from engine when generator drive DISCONNECT sw is selected to DISCONNECT Notes: - The popped CB is located on P6-4/F08 and P6-4/F09

Malfunction Check

1. Select ENGINES via ATM REPOSITIONS page. 2. Insert the system 1 malfunction. (a) Effects as above __ __ __ __ __ __ 3. Remove the malfunction. Reset the popped CB (located on P6-4/F08 and P6-4/F09). 4. Repeat checks 2 and 3 for the system 2 malfunction.





ATA 123Hidden123

24.2 GENERATOR DRIVE LOW OIL PRESSURE

CDB Label: TF2410021 1 TF2410022 2

Failure Description

Low oil quantity.


FLIGHT DECK EFFECTS: ------------------- - DRIVE lt illuminates - System annunciator ELEC and MASTER CAUTION lts illuminate

Malfunction Check

1. Select ENGINES via ATM REPOSITIONS page. 2. Insert the system 1 malfunction. (a) Effects as above __ __ __ __ __ __ 3. Remove the malfunction. 4. Repeat checks 2 and 3 for the system 2 malfunction.





ATA 123Hidden123

24.3 GENERATOR DRIVE SHAFT SHEAR

CDB Label: TF2410031 1 TF2410032 2

Failure Description

Sheared shaft.


FLIGHT DECK EFFECTS: ------------------- - GCB trips - DRIVE lt illuminates - GEN OFF BUS lt illuminates - SOURCE OFF lt illuminates - ELEC and MASTER CAUTION annunciator illuminate

Malfunction Check

1. Select ENGINES via ATM REPOSITIONS page. 2. Insert the system 1 malfunction. (a) Effects as above __ __ __ __ __ __ 3. Remove the malfunction. 4. Repeat checks 2 and 3 for the system 2 malfunction.





ATA 123Hidden123

24.4 APU GENERATOR DRIVE FAIL (EXCITER FIELD)


Failure Description

Short in exciter circuit.


FLIGHT DECK EFFECTS: ------------------- - ACB trips - APU GEN OFF BUS lt illuminates - TRANSFER BUS OFF lts (2) illuminate if APU generator is supplying both AC TRANSFER buses - Associated SOURCE OFF lt illuminates - System annunciator ELEC and MASTER CAUTION lts illuminate Note: If only one AC XFER BUS is powered by APU GEN (the other one being powered by the associated engine generator), inserting the malfunction will cause the TRANSFER BUS OFF light to illuminate momentarily until BTB's close and both XFER busses are powered by the same engine generator.

Malfunction Check

1. Select APU via ATM REPOSITIONS page. 2. Insert the malfunction. (a) Effects as above __ __ __ 3. Remove the malfunction.





ATA 123Hidden123

24.5 BTB FAIL IN OPEN POSITION

CDB Label: TF2420041 1 TF2420042 2

Failure Description

BTB mechanically stuck in open position.


FLIGHT DECK EFFECTS: ------------------- - Auto transfer of AC power not available - Associated GEN OFF BUS lt illuminates when applicable gen is switched off - SOURCE OFF lt illuminates when applicable gen is switched off - TRANSFER BUS OFF lts illuminate - System annunciator ELEC and MASTER CAUTION lts illuminate

Malfunction Check

1. Select ENGINES via ATM REPOSITIONS page. 2. Insert the system 1 malfunction. Ensure the BUS TRANS sw is in the AUTO position. Momentarily position the GEN 1 sw to OFF and release. (a) Effects as above __ __ __ __ __ __ 3. Remove the malfunction. 4. Repeat checks 2 and 3 for the system 2 malfunction.





ATA 123Hidden123

24.6 BTB FAIL IN CLOSED POSITION

CDB Label: TF2420051 1 TF2420052 2

Failure Description

BTB mechanically stuck in closed position.


FLIGHT DECK EFFECTS: ------------------- If external power is supplying both AC TRANSFER buses: - Selecting associated GEN sw causes associated generator to remain off-line - Selecting left or right APU GEN sw causes no effect on normal transfer If APU starter/generator is supplying both AC TRANSFER buses: - Selecting associated GEN sw causes associated generator to remain off-line - Selecting GRD PWR sw causes no effect on normal transfer

Malfunction Check

1. Select GRD ELECT via ATM REPOSITIONS page. Ensure BUS TRANS sw is in AUTO position. 2. Insert system 1 malfunction. Start engine 1 using ENGINES QUICKSTART. Momentarily position GEN 1 sw to ON and release. (a) Effects as above __ __ __ __ __ __ 3. Momentarily position GRD PWR sw to ON and release. Start APU using APU QUICKSTART. 4. Momentarily position left APU GEN sw to ON and release. (a) Effects as above __ __ __ __ __ __





5. Remove malfunction. 6. Repeat checks 2 to 4 for system 2 malfunction. 7. Insert system 1 malfunction. Momentarily position left and right APU GEN sws to ON and release. Momentarily position GEN 1 sw to ON and release. (a) Effects as above __ __ __ __ __ __ 8. Momentarily position GRD PWR sw to ON and release. (a) Effects as above __ __ __ __ __ __ 9. Remove malfunction. 10. Repeat checks 6 to 8 for system 2 malfunction.





ATA 123Hidden123

24.7 GENERATOR DRIVE OVERVOLTAGE

CDB Label: TF2420061 1 TF2420062 2

Failure Description

Voltage regulator fails (GCU internal failure),


FLIGHT DECK EFFECTS: ------------------- - Voltage out of limits - GCB trips - GEN OFF BUS lt illuminates - SOURCE OFF lt illuminates - ELEC and MASTER CAUTION annunciators illuminate

Malfunction Check

1. Select ENGINES via ATM REPOSITIONS page. 2. Insert system 1 malfunction. (a) Effects as above __ __ __ __ __ __ 3. Remove malfunction. 4. Repeat checks 2 and 3 for system 2 malfunction.





ATA 123Hidden123

24.8 LOSS OF BOTH ENGINE DRIVEN GENERATORS


Failure Description

For each GCU, a generator feeder differential current fault is detected (a current offset greater than 20 Amps is sensed between the IDG and GCB) and the GCB is commanded to trip.


FLIGHT DECK EFFECTS: ------------------- - The AC indications are blank FREQ, 0 AMPS and 0 VOLTS - Both GCBs trip - Both TRANSFER BUS OFF lts illuminate - Both SOURCE OFF lts illuminate - Both GEN OFF BUS lts illuminate - ELEC and MASTER CAUTION annunciators illuminate - Generators are resettable NOTE: - Although a current offset of only 20 Amps is required for the GCU to trip the GCB, this malfunction creates an offset of 80 Amps. This value is arbitrary

Malfunction Check

1. Select ENGINES via ATM REPOSITIONS page. 2. Insert the malfunction. (a) Effects as above __ __ __ 3. Momentarily position the GEN 1 sw to ON and release. (a) Effects as above __ __ __ 4. Momentarily position the GEN 2 sw to ON and release. (a) Effects as above __ __ __ 5. Remove the malfunction.





ATA 123Hidden123

24.9 BATTERY BUS OFF

CDB Label: TF2430001 1 TF2430002 2

Failure Description

Open wire between SPCU and battery bus.


FLIGHT DECK EFFECTS: ------------------- For system 1: - Loads connected on the battery bus unpower. This includes, among others: - STBY ATT indicator - Oxygen indicator For system 2: - STANDBY PWR OFF lt illuminates - System annunciator ELEC and MASTER CAUT lts illuminate - BAT BUS DC VOLTS indicates zero - Loads connected on the battery bus upower. This includes, among others: - Brake pressure indicator - APU Fire detectors - Packs 1 and 2

Malfunction Check

1. Select ENGINES via ATM REPOSITIONS page. 2. Insert system 1 malfunction. (a) Effects as above __ __ __ __ __ __ 3. Remove malfunction. 4. Repeat checks 2 and 3 for system 2 malfunction.





ATA 123Hidden123

24.10 TRANSFORMER RECTIFIER FAIL

CDB Label: TF2430011 TR1 TF2430012 TR2 TF2430013 TR3

Failure Description

TR internal failure. No DC output.


FLIGHT DECK EFFECTS: ------------------- - Selected TR DC AMPS indicate zero, TR DC VOLTS indicates normal power voltage except for TR3 malfunction (which indicates zero) - Buses powered by TR may lose power - TR UNIT lt illuminates for any single TR failure on ground or for single TR1 failure or for dual TR2 and TR3 failures in flight - System annunciator ELEC and MASTER CAUTION lts illuminate

Malfunction Check

1. Select ENGINES via ATM REPOSITIONS page. Ensure BUS TRANS sw is in AUTO position. 2. Insert TR1 malfunction. (a) Effects as above __ __ __ __ __ __ __ __ __ 3. Remove malfunction. 4. Repeat checks 2 and 3 for TR2 and TR3 malfunctions. 5. Select AIRWORK FL100 via ATM REPOSITIONS page. 6. Insert TR1 malfunction. (a) Effects as above __ __ __ 7. Remove malfunction. 8. Insert TR2 malfunction.





(a) Effects as above __ __ __ 9. Insert TR3 malfunction. (a) Effects as above __ __ __ 10. Remove malfunctions.





ATA 123Hidden123

24.11 STATIC INVERTER FAIL


Failure Description

Static inverter internal failure. No AC output.


FLIGHT DECK EFFECTS: ------------------- - ELEC lt on electric metering panel P5-13 illuminates - ELEC and MASTER CAUTION annunciators illuminate If static inverter is commanded on: - AC STANDBY BUS are not powered - AC VOLTS and AC FREQ indicate zero and AC FREQ is blank - STANDBY PWR OFF lt illuminates - ELEC and MASTER CAUTION annunciators illuminate If AC and DC rotary selector switches are positioned to TEST and MAINT pb is pressed: - STAT INV INOP message is displayed on AC/DC meter alphanumeric display

Malfunction Check

1. Select ENGINES via ATM REPOSITIONS page. 2. Insert malfunction. (a) Effects as above __ __ __ 3. Momentarily position GEN 1 and GEN 2 sws to OFF and release. (a) Effects as above __ __ __ 4. Remove malfunction. 5. Select ACFT SYSTEM reset via IOS.





ATA 123Hidden123

24.12 BATTERY CHARGER FAIL

CDB Label: TF2430031 MAIN TF2430032 AUX

Failure Description

Internal battery charge TR failure. No DC output.


FLIGHT DECK EFFECTS: ------------------- - Battery charger fails to recharge associated battery - ELEC lt on P5-13 panel illuminates - System annunciator ELEC and MASTER CAUTION lts illuminate If AC and DC rotary selector switches are positioned to TEST and MAINT pushbutton is pressed: - Associated BAT CHGR INOP or AUX BAT CHGR INOP message is displayed on AC/DC meter alphanumeric display Note: The ELEC lt on P5-13 panel could have a 60s delay before turning ON, depending on the actual panel part number.

Malfunction Check

1. Select ENGINES via ATM REPOSITIONS page. 2. Insert MAIN malfunction. (a) Effects as above __ __ __ __ __ __ 3. Remove malfunction and select SYSTEM reset via IOS. 4. Repeats checks 2 and 3 for AUX malfunction.





ATA 123Hidden123

24.13 BATTERY DISCHARGED

CDB Label: TF2430041 .

Failure Description

Battery is completely discharged.


DUAL battery configuration -------------------------- - Corresponding MAIN or AUX battery is discharged If either the MAIN or AUX battery is discharged when the A/C is powered with batteries only: - Discharged battery P5-13 DC Volts drops briefly - Discharged battery is recharged by the remaining charged battery - Discharged battery P5-13 DC Amps is positive (recharging) and remaining charged batter P5-13 DC Amps is negative (battery charge is depleting) - All battery powered buses remain powered due to parallelled batteries - BAT DISCHARGE lt illuminates after normal delay time - MASTER CAUTION and ELEC system annunciator lts illuminate If both the MAIN and AUX battery are discharged when the A/C is powered by batteries only: - Both battery on electric metering panel (P5-13) DC Volts indicate zero - All battery buses are unpowered - All lights extinguish NOTE: MAIN and AUX batteries are isolate by the BAT RCCB during an APU start. Hence, the APU will not start if the MAIN battery is discharged (this can be verified by connecting GRD PWR and selecting the Ground Service switch). If the MAIN or AUX battery is discharged when the A/C is powered by ENG GENs or the APU GEN: - P5-13 BAT or AUX BAT DC Volts drops briefly - MAIN or AUX battery is recharged by its respective battery charger NOTE: If the MAIN battery is discharged, the APU will start using DC current provided by the MAIN battery charger in T/R mode SINGLE battery configuration ----------------------------





- MAIN battery is discharged If the MAIN battery is discharged when the A/C is powered with batteries only: - P5-13 BAT DC Volts indicates zero - All battery powered buses are unpowered - All lights extinguish NOTE: The APU will not start if the MAIN battery is discharged If the MAIN battery is discharged when the A/C is powered by ENG GENs or the APU GEN: - P5-13 BAT DC Volts drops briefly - MAIN battery is recharged by the battery charger NOTE: The APU will start using DC current provided by the battery charger in T/R mode

Malfunction Check

1. Select ALL POWER OFF via ATM REPOSITIONS page. Select BAT switch to ON. 2. Insert the malfunction. (a) Effects as above __ __ __ 3. Position the APU sw to START and release. (a) Effects as above __ __ __ 4. Remove the malfunction and recharge the MAIN battery via the IOS ELEC MAINTENANCE page.





ATA 123Hidden123

24.14 AC STBY POWER AUTO TRANSFER FAIL


Failure Description

SPCU internal failure of circuit driving inverter on command (logical AND gate enabling closure of static inverter RCCB is always false).


FLIGHT DECK EFFECTS: ------------------- - Standby power is not available when AC power is lost - STANDBY PWR OFF lt illuminates until the STANDBY PWR sw is selected to BAT - System annunciator ELEC and MASTER CAUTION lts illuminate when STANDBY PWR OFF lt illuminates

Malfunction Check

1. Select ENGINES via ATM REPOSITIONS page. 2. Insert malfunction. Ensure STANDBY PWR sw is in AUTO position. Momentarily position GEN 1 and GEN 2 sws to OFF and release. (a) Effects as above __ __ __ 3. Position STANDBY PWR sw to BAT. (a) Effects as above __ __ __ 4. Remove malfunction. Position STANDBY PWR sw to AUTO.





ATA 123Hidden123

24.15 AC TRANSFER BUS OFF

CDB Label: TF2450001 1 TF2450002 2

Failure Description

AC transfer bus short circuit.


FLIGHT DECK EFFECTS: ------------------- - GCB trips and BTB closure is inhibited due to overcurrent - TRANSFER BUS OFF lt illuminates - SOURCE OFF lt illuminates - GEN OFF BUS lt illuminates - System annunciator ELEC and MASTER CAUTION lts illuminate

Malfunction Check

1. Select ENGINES via ATM REPOSITIONS page. 2. Insert system 1 malfunction. (a) Effects as above __ __ __ __ __ __ 3. Remove malfunction. Momentarily position GEN 1 sw to ON and release. 4. Repeat checks 2 and 3 for system 2 malfunction.





ATA 123Hidden123

24.16 MAIN BUS OFF

CDB Label: TF2450021 1 TF2450022 2

Failure Description

Protective CB trips due to a short circuit on main bus. For MAIN BUS 1: CB 815 (P91/F06)* For MAIN BUS 2: CB 817 (P92/F06)* * Refer to the IOS Simulator Maintenance Index, Electrics, Software BCs page.


FLIGHT DECK EFFECTS: ------------------- - Load increases momentarily and then drops to zero - Connected loads on Main bus unpower - Electrical load on supplying source decreases

Malfunction Check

1. Select ENGINES via ATM REPOSITIONS page. 2. Insert the system 1 malfunction. (a) Effects as above __ __ __ __ __ __ 3. Remove the malfunction. 4. Repeat checks 2 and 3 for the system 2 malfunction. 5. Reset both CBs.





ATA 123Hidden123

24.17 STBY BUS OFF

CDB Label: TF2450011 AC TF2460011 DC

Failure Description

Open wire between SPCU and standby bus.


FLIGHT DECK EFFECTS: ------------------- - Standby bus cannot be powered by either TRUs nor batteries - Connected loads on standby bus unpower - Electrical load on supplying source decreases on the ELEC Maint page via IOS - Selected standby bus VOLTS indicates zero - STANDBY PWR OFF lt illuminates - System annunciator ELEC and MASTER CAUTION lts illuminate

Malfunction Check

1. Select ENGINES via ATM REPOSITIONS page. 2. Insert the AC malfunction. (a) Effects as above __ __ __ __ __ __ 3. Remove the malfunction. 4. Repeat checks 2 and 3 for the DC malfunction.

Boeing 737-800 FFS Standard Product Specification – Addendum 1 ATA 26A - Fire Protection (No Smoke) List of Malfunctions




ATA 26A - Fire Protection (No Smoke)

26A.1 WHEEL WELL FIRE - CONTROLLABLE


Failure Description

Main wheel well fire detector activated due to fire in wheel well bay.


FLIGHT DECK EFFECTS: ------------------- - Master FIRE WARN lts (2) illuminate - Fire bell sounds - WHEEL WELL lt illuminates - Wheel well fire extinguishes 1 minute after landing gear is extended

Malfunction Check

1. Select TAKEOFF B via the ATM REPOSITIONS page. Ensure the OVHT DET sws (2) are selected to NORMAL. 2. Perform a takeoff, retract the landing gear and establish a cruise configuration. 3. Insert the malfunction. (a) Effects as above __ __ __ 4. Extend the landing gear and wait 1 minute. (a) Effects as above __ __ __ 5. Remove the malfunction.





ATA 123Hidden123

26A.2 ENGINE OVERHEAT

CDB Label: TF2610011 ENG 1 TF2610012 ENG 2

Failure Description

Engine overheat due to bleed duct leak, upstream bleed control valve.


FLIGHT DECK EFFECTS: ------------------- - Appropriate ENG OVERHEAT lt illuminates - MASTER CAUTION lts (2) illuminate - OVHT/DET ANNUNCIATOR lt illuminates - When the engine is shut down or the thrust lever is retarded, lts extinguish - Fire handle unlocks Notes: - Thrust lever must be advanced to get full effects

Malfunction Check

1. Set up A/C on ground under the following conditions: Select ENGINES via the ATM REPOSITIONS page. OVHT DET sws (2) NORMAL 2. Insert the ENG 1 malfunction. Advance the thrust lever. (a) Effects as above __ __ __ __ __ __ 3. Retard the thrust lever. (a) Effects as above __ __ __ __ __ __ 4. Remove the malfunction. 5. Repeat checks 2 to 4 for the ENG 2 malfunction.





ATA 123Hidden123

26A.3 ENGINE FIRE - 1 BOTTLE


Failure Description

Engine fire automatically extinguishes 15s after one fire extinguisher bottle is discharged.


FLIGHT DECK EFFECTS: ------------------- - Appropriate ENG OVERHEAT and ENG FIRE HANDLE lts illuminate - MASTER CAUTION lts (2) illuminate - OVHT/DET and FIRE WARN annunciator lts illuminate - Fire bell sounds - Fire handle unlocks - Fire extinguishes 15s after one bottle is discharged

Malfunction Check

1. Select ENGINES via the ATM REPOSITIONS page. Ensure the OVHT DET sws (2) are selected to NORMAL. 2. Insert the ENG 1 malfunction. (a) Effects as above __ __ __ __ __ __ 3. Pull the ENG 1 fire handle. Rotate the ENG 1 fire handle to the left or to the right. (a) Effects as above __ __ __ __ __ __ 4. Remove the malfunction. 5. Reset the ENG 1 fire handle. Refill the fire extinguisher bottle using the FREEZES/ RESETS page via the IOS.





Select ENG QUICK START. 6. Repeat checks 2 to 5 for the ENG 2 malfunction.





ATA 123Hidden123

26A.4 ENGINE FIRE - 2 BOTTLES


Failure Description

Engine fire automatically extinguishes 15s after a second fire extinguisher bottle is discharged.


FLIGHT DECK EFFECTS: ------------------- - Appropriate ENG OVERHEAT and ENG FIRE HANDLE lts illuminate - MASTER CAUTION lts (2) illuminate - OVHT/DET and FIRE WARN annunciator lts illuminate - Fire bell sounds - Fire handle unlocks - Fire extinguishes 15s after second bottle is discharged

Malfunction Check

1. Select ENGINES via the ATM REPOSITIONS page. Ensure the OVHT DET sws (2) are selected to the NORMAL. 2. Insert the ENG 1 malfunction. (a) Effects as above __ __ __ __ __ __ 3. Pull the ENG 1 fire handle. Rotate the ENG 1 fire handle to the right. (a) Effects as above __ __ __ __ __ __ 4. Rotate the ENG 1 fire handle to the left. After 15s: (a) Effects as above __ __ __ __ __ __ 5. Remove the malfunction.





6. Reset the ENG 1 fire handle. Refill the fire extinguisher bottle using the FREEZES/ RESETS page via the IOS. Select ENG QUICK START. 6. Repeat checks 2 to 6 for the ENG 2 malfunction.





ATA 123Hidden123

26A.5 ENGINE FIRE - UNEXTINGUISHABLE


Failure Description

Engine fire does not extinguish until the malfunction is removed.


FLIGHT DECK EFFECTS: ------------------- - Appropriate ENG OVERHEAT and ENG FIRE HANDLE lts illuminate - MASTER CAUTION lts (2) illuminate - OVHT/DET and FIRE WARN annunciator lts illuminate - Fire bell sounds - Fire handle unlocks - Fire unextinguishable

Malfunction Check

1. Select ENGINES via the ATM REPOSITIONS page. Ensure the OVHT DET sws (2) are selected to NORMAL. 2. Insert the ENG 1 malfunction. (a) Effects as above __ __ __ __ __ __ 3. Pull the ENG 1 fire handle. Rotate the ENG 1 fire handle to the right and then to the left. (a) Fire unextinguishable __ __ __ __ __ __ 4. Remove the malfunction. 5. Reset the ENG 1 fire handle. Refill the fire extinguisher bottle using the FREEZES/ RESETS page via the IOS. Select ENG QUICK START via the IOS.





6. Repeat checks 2 to 6 for the ENG 2 malfunction.





ATA 123Hidden123

26A.6 APU FIRE - EXTINGUISHABLE


Failure Description

APU fire automatically extinguishes 15 seconds after one fire extinguisher bottle is discharged.


FLIGHT DECK EFFECTS: ------------------- - APU shuts down automatically - APU FIRE HANDLE lt illuminates - MASTER CAUTION lts (2) illuminate - FIRE WARN annunciator lt illuminates - Fire bell sounds - Fire handle unlocks - Fire extinguishes 15s after one bottle is discharged - APU bottle discharge lt illuminates

Malfunction Check

1. Select GND ELEC via the ATM REPOSITIONS page. Ensure the APU is running. 2. Insert the malfunction. Pull and rotate the APU fire handle either to the left or to the right. (a) Effects as above __ __ __ After the fire is extinguished: (b) MASTER FIRE WARNING extinguishes __ __ __ lt (c) Fire bell silences __ __ __ (d) APU FIRE WARN lts extinguish __ __ __ 3. Reset the APU fire handle.





Refill the fire extinguisher bottle using the FREEZES/ RESETS page via the IOS.





ATA 123Hidden123

26A.7 APU FIRE - UNEXTINGUISHABLE


Failure Description

APU fire does not extinguish until malfunction is removed.


FLIGHT DECK EFFECTS: ------------------- - APU shuts down automatically - APU FIRE HANDLE lt illuminates - MASTER CAUTION lts (2) illuminate - FIRE WARN annunciator lt illuminates - Fire bell sounds - Fire handle unlocks - Fire unextinguishable

Malfunction Check

1. Select GND ELEC via the ATM REPOSITIONS page. Ensure the APU is running. 2. Insert the malfunction. Pull and rotate the APU fire handle either to the left or to the right. (a) Effects as above __ __ __ 3. Reset the APU fire handle. 4. Remove the malfunction. Refill the fire extinguisher bottle using the FREEZES/ RESETS page via the IOS.





ATA 123Hidden123

26A.8 ENG L(R) BOTTLE FAILS TO DISCH

CDB Label: TF2620001 1-L TF2620003 1-R TF2620002 2-L TF2620004 2-R

Failure Description

Fire extinguisher bottle does not discharge due to a faulty cartridge. Squib test is unsatisfactory.


FLIGHT DECK EFFECTS: ------------------- - Bottle does not discharge when the applicable ENG fire handle is rotated left or right - Squib test is unsatisfactory

Malfunction Check

1. Select GRD ELECT via the ATM REPOSITIONS page. 2. Insert the 1-L malfunction. Pull and rotate the ENG 1 fire handle to the left. (a) L BOTTLE DISCHARGED does not illuminate __ __ __ lt 3. Position the EXT TEST sw to 1. (a) L EXT TEST lt does not illuminate __ __ __ 4. Release the EXT TEST sw. Reset the ENG 1 fire handle. Remove the malfunction. 5. Insert the 2-L malfunction. Pull and rotate the ENG 2 fire handle to the left. (a) L BOTTLE DISCHARGED does not illuminate __ __ __ lt





6. Position the EXT TEST sw to 2. (a) L EXT TEST lt does not illuminate __ __ __ 7. Release the EXT TEST sw. Reset the ENG 2 fire handle. Remove the malfunction. 8. Insert the 1-R malfunction. Pull and rotate the ENG 1 fire handle to the right. (a) R BOTTLE DISCHARGED does not illuminate __ __ __ lt 9. Position the EXT TEST sw to 1. (a) R EXT TEST lt does not illuminate __ __ __ 10. Release the EXT TEST sw. Reset the ENG 1 fire handle. Remove the malfunction. 11. Insert the 2-R malfunction. Pull and rotate the ENG 2 fire handle to the right. (a) R BOTTLE DISCHARGED does not illuminate __ __ __ lt 12. Position the EXT TEST sw to 2. (a) R EXT TEST lt does not illuminate __ __ __ 13. Release the EXT TEST sw. Reset the ENG 2 fire handle. Remove the malfunction.





ATA 123Hidden123

26A.9 APU BOTTLE FAILS TO DISCH


Failure Description



FLIGHT DECK EFFECTS: ------------------- - Bottle does not discharge when the APU fire handle is rotated left or right - Squib test is unsatisfactory

Malfunction Check

1. Select GRD ELECT via the ATM REPOSITIONS page. 2. Insert the malfunction. Pull and rotate the APU fire handle to the left or right. (a) APU BOTTLE DISCHARGE does not illuminate __ __ __ lt 3. Position the EXT TEST sw to 1 or 2. (a) APU EXT TEST lt does not illuminate __ __ __ 4. Release the EXT TEST sw. Reset the APU fire handle. Remove the malfunction.





ATA 123Hidden123

26A.10 CARGO FIRE

CDB Label: TF2620041 FWD TF2620042 AFT

Failure Description

Cargo compartment fire. Extinguishes automatically 30 seconds after the fire extinguisher bottle is discharged.


FLIGHT DECK EFFECTS: ------------------- - Appropriate FWD and AFT alarm lts illuminate - FIRE WARN lts illuminate - Fire bell sounds - Fire extinguishes 30 seconds after the fire extinguisher bottle is discharged* - DISCH lt illuminates when bottle is discharged *Note: On models with 2 cargo fire extinguisher bottles, only one bottle is necessary to extinguish the fire.

Malfunction Check

1. Select GRD ELECT via the ATM REPOSITIONS page. Ensure the FWD and AFT DET SELECT switches are selected to NORM. 2. Insert the FWD malfunction. (a) Effects as above __ __ __ __ __ __ 3. Press the FWD (AFT) ARM pb. Press the DISCH switch. (a) Effects as above __ __ __ __ __ __ 4. Remove the malfunction. 5. Reset the FWD (AFT) ARM pb.





Refill the fire extinguisher bottle using the FREEZE/ RESET page via the IOS. 6. Repeat checks 2 to 5 for the AFT malfunction using the AFT ARM pb.





ATA 123Hidden123

26A.11 APU DETECTOR FAIL


Failure Description

Detector failure; APU DETECTOR INOP light illuminates.


FLIGHT DECK EFFECTS: ------------------- - APU DET INOP lt illuminates - MASTER CAUTION lts (2) illuminate - APU fire cannot be detected

Malfunction Check

1. Select GRD ELECT via the ATM REPOSITIONS page. 2. Insert the malfunction. (a) Effects as above __ __ __ 3. Remove the malfunction.

Boeing 737-800 FFS Standard Product Specification – Addendum 1 ATA 26B - Fire Protection (Smoke) List of Malfunctions




ATA 26B - Fire Protection (Smoke)

26B.1 WHEEL WELL FIRE - CONTROLLABLE


Failure Description

Main wheel well fire detector activated due to fire in wheel well bay.


FLIGHT DECK EFFECTS: ------------------- - Master FIRE WARN lts (2) illuminate - Fire bell sounds - WHEEL WELL lt illuminates - Wheel well fire extinguishes 1 minute after landing gear is extended

Malfunction Check

1. Select TAKEOFF B via the ATM REPOSITIONS page. Ensure the OVHT DET sws (2) are selected to NORMAL. 2. Perform a takeoff, retract the landing gear and establish a cruise configuration. 3. Insert the malfunction. (a) Effects as above __ __ __ 4. Extend the landing gear and wait 1 minute. (a) Effects as above __ __ __ 5. Remove the malfunction.





ATA 123Hidden123

26B.2 ENGINE OVERHEAT


Failure Description

Engine overheat due to bleed duct leak, upstream bleed control valve.


FLIGHT DECK EFFECTS: ------------------- - Appropriate ENG OVERHEAT lt illuminates - MASTER CAUTION lts (2) illuminate - OVHT/DET ANNUNCIATOR lt illuminates - When the engine is shut down or the thrust lever is retarded, lts extinguish - Fire handle unlocks Notes: - Thrust lever must be advanced to get full effects

Malfunction Check

1. Set up A/C on ground under the following conditions: Select ENGINES via the ATM REPOSITIONS page. OVHT DET sws (2) NORMAL 2. Insert the ENG 1 malfunction. Advance the thrust lever. (a) Effects as above __ __ __ __ __ __ 3. Retard the thrust lever. (a) Effects as above __ __ __ __ __ __ 4. Remove the malfunction. 5. Repeat checks 2 to 4 for the ENG 2 malfunction.





ATA 123Hidden123

26B.3 ENGINE FIRE - 1 BOTTLE


Failure Description

Engine fire automatically extinguishes 15s after one fire extinguisher bottle is discharged.


FLIGHT DECK EFFECTS: ------------------- - Appropriate ENG OVERHEAT and ENG FIRE HANDLE lts illuminate - MASTER CAUTION lts (2) illuminate - OVHT/DET and FIRE WARN annunciator lts illuminate - Fire bell sounds - Fire handle unlocks - Fire extinguishes 15s after one bottle is discharged

Malfunction Check

1. Select ENGINES via the ATM REPOSITIONS page. Ensure the OVHT DET sws (2) are selected to NORMAL. 2. Insert the ENG 1 malfunction. (a) Effects as above __ __ __ __ __ __ 3. Pull the ENG 1 fire handle. Rotate the ENG 1 fire handle to the left or to the right. (a) Effects as above __ __ __ __ __ __ 4. Remove the malfunction. 5. Reset the ENG 1 fire handle. Refill the fire extinguisher bottle using the FREEZES/ RESETS page via the IOS.





Select ENG QUICK START. 6. Repeat checks 2 to 5 for the ENG 2 malfunction.





ATA 123Hidden123

26B.4 ENGINE FIRE - 2 BOTTLES


Failure Description

Engine fire automatically extinguishes 15s after a second fire extinguisher bottle is discharged.


FLIGHT DECK EFFECTS: ------------------- - Appropriate ENG OVERHEAT and ENG FIRE HANDLE lts illuminate - MASTER CAUTION lts (2) illuminate - OVHT/DET and FIRE WARN annunciator lts illuminate - Fire bell sounds - Fire handle unlocks - Fire extinguishes 15s after second bottle is discharged

Malfunction Check

1. Select ENGINES via the ATM REPOSITIONS page. Ensure the OVHT DET sws (2) are selected to the NORMAL. 2. Insert the ENG 1 malfunction. (a) Effects as above __ __ __ __ __ __ 3. Pull the ENG 1 fire handle. Rotate the ENG 1 fire handle to the right. (a) Effects as above __ __ __ __ __ __ 4. Rotate the ENG 1 fire handle to the left. After 15s: (a) Effects as above __ __ __ __ __ __ 5. Remove the malfunction.





6. Reset the ENG 1 fire handle. Refill the fire extinguisher bottle using the FREEZES/ RESETS page via the IOS. Select ENG QUICK START. 6. Repeat checks 2 to 6 for the ENG 2 malfunction.





ATA 123Hidden123

26B.5 ENGINE FIRE - UNEXTINGUISHABLE


Failure Description

Engine fire does not extinguish until the malfunction is removed.


FLIGHT DECK EFFECTS: ------------------- - Appropriate ENG OVERHEAT and ENG FIRE HANDLE lts illuminate - MASTER CAUTION lts (2) illuminate - OVHT/DET and FIRE WARN annunciator lts illuminate - Fire bell sounds - Fire handle unlocks - Fire unextinguishable

Malfunction Check

1. Select ENGINES via the ATM REPOSITIONS page. Ensure the OVHT DET sws (2) are selected to NORMAL. 2. Insert the ENG 1 malfunction. (a) Effects as above __ __ __ __ __ __ 3. Pull the ENG 1 fire handle. Rotate the ENG 1 fire handle to the right and then to the left. (a) Fire unextinguishable __ __ __ __ __ __ 4. Remove the malfunction. 5. Reset the ENG 1 fire handle. Refill the fire extinguisher bottle using the FREEZES/ RESETS page via the IOS. Select ENG QUICK START via the IOS.





6. Repeat checks 2 to 6 for the ENG 2 malfunction.





ATA 123Hidden123

26B.6 APU FIRE - EXTINGUISHABLE


Failure Description

APU fire automatically extinguishes 15 seconds after one fire extinguisher bottle is discharged.


FLIGHT DECK EFFECTS: ------------------- - APU shuts down automatically - APU FIRE HANDLE lt illuminates - MASTER CAUTION lts (2) illuminate - FIRE WARN annunciator lt illuminates - Fire bell sounds - Fire handle unlocks - Fire extinguishes 15s after one bottle is discharged - APU bottle discharge lt illuminates

Malfunction Check

1. Select GND ELEC via the ATM REPOSITIONS page. Ensure the APU is running. 2. Insert the malfunction. Pull and rotate the APU fire handle either to the left or to the right. (a) Effects as above __ __ __ After the fire is extinguished: (b) MASTER FIRE WARNING extinguishes __ __ __ lt (c) Fire bell silences __ __ __ (d) APU FIRE WARN lts extinguish __ __ __ 3. Reset the APU fire handle.





Refill the fire extinguisher bottle using the FREEZES/ RESETS page via the IOS.





ATA 123Hidden123

26B.7 APU FIRE - UNEXTINGUISHABLE


Failure Description

APU fire does not extinguish until malfunction is removed.


FLIGHT DECK EFFECTS: ------------------- - APU shuts down automatically - APU FIRE HANDLE lt illuminates - MASTER CAUTION lts (2) illuminate - FIRE WARN annunciator lt illuminates - Fire bell sounds - Fire handle unlocks - Fire unextinguishable

Malfunction Check

1. Select GND ELEC via the ATM REPOSITIONS page. Ensure the APU is running. 2. Insert the malfunction. Pull and rotate the APU fire handle either to the left or to the right. (a) Effects as above __ __ __ 3. Reset the APU fire handle. 4. Remove the malfunction. Refill the fire extinguisher bottle using the FREEZES/ RESETS page via the IOS.





ATA 123Hidden123

26B.8 ENG L(R) BOTTLE FAILS TO DISCH


Failure Description



FLIGHT DECK EFFECTS: ------------------- - Bottle does not discharge when the applicable ENG fire handle is rotated left or right - Squib test is unsatisfactory

Malfunction Check

1. Select GRD ELECT via the ATM REPOSITIONS page. 2. Insert the 1-L malfunction. Pull and rotate the ENG 1 fire handle to the left. (a) L BOTTLE DISCHARGED does not illuminate __ __ __ lt 3. Position the EXT TEST sw to 1. (a) L EXT TEST lt does not illuminate __ __ __ 4. Release the EXT TEST sw. Reset the ENG 1 fire handle. Remove the malfunction. 5. Insert the 2-L malfunction. Pull and rotate the ENG 2 fire handle to the left. (a) L BOTTLE DISCHARGED does not illuminate __ __ __ lt





6. Position the EXT TEST sw to 2. (a) L EXT TEST lt does not illuminate __ __ __ 7. Release the EXT TEST sw. Reset the ENG 2 fire handle. Remove the malfunction. 8. Insert the 1-R malfunction. Pull and rotate the ENG 1 fire handle to the right. (a) R BOTTLE DISCHARGED does not illuminate __ __ __ lt 9. Position the EXT TEST sw to 1. (a) R EXT TEST lt does not illuminate __ __ __ 10. Release the EXT TEST sw. Reset the ENG 1 fire handle. Remove the malfunction. 11. Insert the 2-R malfunction. Pull and rotate the ENG 2 fire handle to the right. (a) R BOTTLE DISCHARGED does not illuminate __ __ __ lt 12. Position the EXT TEST sw to 2. (a) R EXT TEST lt does not illuminate __ __ __ 13. Release the EXT TEST sw. Reset the ENG 2 fire handle. Remove the malfunction.





ATA 123Hidden123

26B.9 APU BOTTLE FAILS TO DISCH


Failure Description



FLIGHT DECK EFFECTS: ------------------- - Bottle does not discharge when the APU fire handle is rotated left or right - Squib test is unsatisfactory

Malfunction Check

1. Select GRD ELECT via the ATM REPOSITIONS page. 2. Insert the malfunction. Pull and rotate the APU fire handle to the left or right. (a) APU BOTTLE DISCHARGE does not illuminate __ __ __ lt 3. Position the EXT TEST sw to 1 or 2. (a) APU EXT TEST lt does not illuminate __ __ __ 4. Release the EXT TEST sw. Reset the APU fire handle. Remove the malfunction.





ATA 123Hidden123

26B.10 CARGO FIRE

CDB Label: TF2620041 FWD TF2620042 AFT

Failure Description

Cargo compartment fire. Extinguishes automatically 15 seconds after one fire extinguisher bottle is discharged.


FLIGHT DECK EFFECTS: ------------------- - Appropriate FWD and AFT alarm lts illuminate - FIRE WARN lts illuminate - Fire bell sounds - Fire extinguishes 30 seconds after the fire extinguisher bottle is discharged* - DISCH lt illuminates when bottle is discharged *Note: On models with 2 cargo fire extinguisher bottles, only one bottle is necessary to extinguish the fire.

Malfunction Check

1. Select GRD ELECT via the ATM REPOSITIONS page. Ensure the FWD and AFT DET SELECT switches are selected to NORM. 2. Insert the FWD malfunction. (a) Effects as above __ __ __ __ __ __ 3. Press the FWD (AFT) ARM pb. Press the DISCH switch. (a) Effects as above __ __ __ __ __ __ 4. Remove the malfunction. 5. Reset the FWD (AFT) ARM pb.





Refill the fire extinguisher bottle using the FREEZE/ RESET page via the IOS. 6. Repeat checks 2 to 5 for the AFT malfunction using the AFT ARM pb.





ATA 123Hidden123

26B.11 APU DETECTOR FAIL


Failure Description

Detector failure; APU DETECTOR INOP light illuminates.


FLIGHT DECK EFFECTS: ------------------- - APU DET INOP lt illuminates - MASTER CAUTION lts (2) illuminate - APU fire cannot be detected

Malfunction Check

1. Select GRD ELECT via the ATM REPOSITIONS page. 2. Insert the malfunction. (a) Effects as above __ __ __ 3. Remove the malfunction.





ATA 123Hidden123

26B.12 ELECTRICAL SMOKE (P6 CB PANEL)


Failure Description

Smoke escapes from the CB panel.


FLIGHT DECK EFFECTS: ------------------- - Smoke escapes from CB P6 panel - Smokes ceases when the malfunction is removed or power is removed from the switched hot battery bus (sector 2)

Malfunction Check

1. Select ENGINES via the ATM REPOSITIONS page. 2. Insert the malfunction. (a) Effects as above __ __ __ 3. Select the BAT BUS switch to OFF. (a) Smoke ceases __ __ __ 4. Remove the malfunction.





ATA 123Hidden123

26B.13 PACK SMOKE


Failure Description

Smokes escapes from the air conditioning outlets.


FLIGHT DECK EFFECTS: ------------------- - Smoke escapes from the air conditioning outlets - Smoke ceases when the malfunction is removed or the associated pack is switched OFF

Malfunction Check

1. Select TAKEOFF B via the ATM REPOSITIONS page. Position both PACK sws to ON. 2. Insert the LEFT malfunction. (a) Smoke appears __ __ __ 3. Position the L PACK sw to OFF. (a) Smoke ceases __ __ __ 4. Remove the malfunction. 5. Insert the RIGHT malfunction. (a) Smoke appears __ __ __ 6. Position the R PACK sw to OFF. (a) Smoke ceases __ __ __ 7. Remove the malfunction. 8. Position the L and R PACK sws to ON. (a) Smoke does not enter cockpit __ __ __

Boeing 737-800 FFS Standard Product Specification – Addendum 1 ATA 27 - Flight Controls List of Malfunctions




ATA 27 - Flight Controls

27.1 YAW DAMPER HARDOVER

CDB Label: TF2223021 L TF2223022 R

Failure Description

A failure in the primary yaw damper transfer valve or actuator causes full yaw damper deflection.


- Yaw damper indicator operates normally

Malfunction Check

1. Select AIR WORK FL100 via ATM REPOSITIONS page. 2. Insert L malfunction with flaps UP. (a) A/C yaws to corresponding __ __ __ side __ __ __ 3. Use the control wheel to stabilize the aircraft. (a) Rudder position approximately 2degrees __ __ __ __ __ __ (b) Rudder can be centered using __ __ __ pedals __ __ __ 4. Remove rudder pedal input. Disengage the yaw damper. (a) Rudder returns to neutral __ __ __ __ __ __ 5. Remove malfunction. 6. Repeat checks 2 to 5 for R malfunction.





ATA 123Hidden123

27.2 AILERON SURFACE JAM


Failure Description

Aileron stuck in position due to jammed wing cable (ABSB, ABSA).


FLIGHT DECK EFFECTS: ------------------- - Only one aileron operational which results in decreased aileron effectiveness and residual aerodynamic effects - Shearout of a single jammed surface can be accomplished provided that both aileron PCUs work in unison

Malfunction Check

1. Select ENGINES via ATM REPOSITIONS page. 2. Insert LEFT malfunction. Move control wheel. (a) Left aileron does not move __ __ __ surface (b) Right aileron moves according to wheel __ __ __ surface input 3. Release control wheel, remove LEFT malfunction and insert RIGHT malfunction. Move control wheel. (a) Left aileron moves according to wheel __ __ __ surface input (b) Right aileron does not move __ __ __ surface 4. Release control wheel and remove RIGHT malfunction. Set FLT CONTROL A sw to OFF.





5. Insert LEFT malfunction. Move control wheel. (a) Conrol wheel moves to PCU stops __ __ __ __ __ __ (b) Aileron surfaces do not move __ __ __ __ __ __ 6. Remove malfunction. 7. Repeat checks 5 and 6 for RIGHT malfunction. 8. Set FLT CONTROL A sw to ON.





ATA 123Hidden123

27.3 ELEVATOR SURFACE JAM


Failure Description

Elevator surface stuck in current position.


FLIGHT DECK EFFECTS: ------------------- - Column can only be moved to PCU valve stops - Surface position does not change

Malfunction Check

1. Select ENGINES via ATM REPOSITIONS page. 2. Insert malfunction. (a) Control columns movement limited to PCU __ __ __ valve stops (b) Elevator surfaces do not move __ __ __ 3. Remove malfunction.





ATA 123Hidden123

27.4 ELEVATOR FEEL COMPUTER FAIL

CDB Label: TF2731021 1 TF2731022 2

Failure Description

Feel computer internal failure.


FLIGHT DECK EFFECTS: ------------------- - Metered feel pressure from affected system A and/or B drops to minimum - The feel differential pressure switch that monitors both computer metered pressures closes when it measures a difference of 25% between system A and B metered pressure. The FEEL DIFF PRESS lt comes on when there is this difference for more than 30 seconds - If both system A and B metered pressures drop down, column forces drop to minimum

Malfunction Check

1. Select AIR WORK FL100 via ATM REPOSITIONS page. 2. Insert system 1 malfunction. (a) FEEL DIFF PRESS lt illuminates __ __ __ after 30s __ __ __ (b) Elevator column loads not affected __ __ __ __ __ __ (c) MASTER CAUTION lts (2) illuminate __ __ __ __ __ __ (d) FLT CONT system illuminates __ __ __ annunciator __ __ __ 3. Remove malfunction. 4. Repeat checks 2 and 3 for system 2 malfunction. 5. Insert Systems 1 and 2 malfunctions. (a) FEEL DIFF PRESS lt extinguishes __ __ __





(b) Elevator column loads drop to minimum __ __ __ (c) MASTER CAUTION lts (2) extinguish __ __ __ (d) FLT CONT system extinguishes __ __ __ annunciator 6. Remove both malfunctions. (a) Elevator column loads return to normal __ __ __





ATA 123Hidden123

27.5 JAMMED STABILIZER


Failure Description

Jam of stabilizer actuation path between electric motor and cable drum.


FLIGHT DECK EFFECTS: ------------------- - Main electric and A/P trim inoperative - Manual trim is possible with enough force to override the clutch

Malfunction Check

1. Select ENGINES via ATM REPOSITIONS page. 2. Insert the malfunction. 3. Operate the main trim switches. (a) Stabilizer does not move __ __ __ 4. Manually operate the trim wheel. (a) Fore to move stab enough force to overcome __ __ __ wheel clutch friction (b) Stabilizer surface normal __ __ __ movement 5. Remove the malfunction.





ATA 123Hidden123

27.6 STABILIZER RUNAWAY - MAIN ELECTRIC


Failure Description

Failure in the electrical system causes main electric motor to run away.


FLIGHT DECK EFFECTS: ------------------- - Stabilizer will run away at first actuation of trim switches, in the direction called for - Manual and A/P trim sys remain operable

Malfunction Check

1. Select ENGINES via ATM REPOSITIONS page. 2. Insert malfunction. (a) Stabilizer runs away at first __ __ __ actuation of trim sws (b) Runaway controlled by positioning __ __ __ MAIN ELEC STAB TRIM sw to CUTOUT or operation of trim sws in opposition to wheel movement, normal column use or manual override 3. Remove malfunction. 4. Select ATM reposition FL100. 5. Insert malfunction. (a) Stabilizer runs away at first __ __ __ actuation of trim sws (b) Runaway controlled by positioning __ __ __ MAIN ELEC STAB TRIM sw to CUTOUT or operation of trim sws in opposition to wheel movement, normal column use





or manual override Note: Ensure that A/P cutout switch is set at normal (c) Trim available by manual __ __ __ trim wheel or autopilot 6. Remove malfunction.





ATA 123Hidden123

27.7 STAB TRIM ACTUATOR CIRCUIT BREAKER TRIP


Failure Description

Main electric stabilizer trim actuator CB pops (P6-2/D10).


FLIGHT DECK EFFECTS: ------------------- - No electrical trim but Manual and A/P trim available

Malfunction Check

1. Select AIR WORK FL100 via ATM REPOSITIONS page. 2. Insert malfunction. (a) F/C STAB TRIM trips __ __ __ ACTUATOR CB (b) Electric trim not available __ __ __ (c) Manual trim available __ __ __ (d) Autopilot trim available __ __ __ 3. Remove malfunction and reset F/C STAB TRIM ACTUATOR CB (P6-2/D10).





ATA 123Hidden123

27.8 FLIGHT SPOILER PANEL JAM - LEFT WING

CDB Label: TF2760012 2 TF2760013 3 TF2760014 4 TF2760015 5

Failure Description

Spoiler panel jammed in current position.


FLIGHT DECK EFFECTS: ------------------- - Appropriate spoiler panel fails in last position - Adverse roll effect

Malfunction Check

1. Select AIR WORK FL100 via ATM REPOSITIONS page. 2. Raise speedbrake lever to FLIGHT detent. Insert spoiler panel 2 malfunction. Move control wheel. (a) Associated flight does not move __ __ __ spoiler __ __ __ __ __ __ __ __ __ (b) All remaining move according to wheel __ __ __ flight spoilers input __ __ __ __ __ __ __ __ __ 3. Remove malfunction. 4. Repeat checks 2 and 3 for the remaining malfunctions.





ATA 123Hidden123

27.9 FLIGHT SPOILER PANEL JAM - RIGHT WING

CDB Label: TF2760018 8 TF2760019 9 TF276001A 10 TF276001B 11

Failure Description

Spoiler panel jammed in current position.


FLIGHT DECK EFFECTS: ------------------- - Appropriate spoiler panel fails in last position - Adverse roll effect

Malfunction Check

1. Select AIR WORK FL100 via ATM REPOSITIONS page. 2. Raise speedbrake lever to FLIGHT detent. Insert spoiler panel 8 malfunction. Move control wheel. (a) Associated flight does not move __ __ __ spoiler __ __ __ __ __ __ __ __ __ (b) All remaining move according to wheel __ __ __ flight spoilers input __ __ __ __ __ __ __ __ __ 3. Remove malfunction. 4. Repeat checks 2 and 3 for the remaining malfunctions.





ATA 123Hidden123

27.10 SPEED BRAKE DO NOT ARM LIGHT - ON


Failure Description

Autospeedbrake actuator not fully retracted.


FLIGHT DECK EFFECTS: ------------------- - SPEEDBRAKE DO NOT ARM lt illuminates when speed brake lever moved to ARMED detent

Malfunction Check

1. Select ON ILS 200 FT via ATM REPOSITIONS page. 2. Insert malfunction. Arm the speed brake. (a) SPEED BRAKE DO NOT illuminates __ __ __ ARM lt 3. Remove malfunction.





ATA 123Hidden123

27.11 AUTO SPEEDBRAKE MODULE FAIL


Failure Description

K2 and K4 wheel speed relays in auto speedbrake module fail.


FLIGHT DECK EFFECTS: ------------------- - Auto speedbrake inoperative - Indications normal except that the SPEEDBRAKE DO NOT ARM lt will illuminate when the auto speedbrake would normally activate

Malfunction Check

1. Select TAKEOFF reposition. 2. Insert malfunction. 3. Set A/C on jacks. Set speedbrake lever to ARMED detent. (a) SPEEDBRAKE ARMED lt illuminates __ __ __ (b) SPEEDBRAKE DO NOT ARM remains extinguished __ __ __ lt 4. Remove A/C on jacks. (a) SPEEDBRAKE ARMED lt extinguishes for 4s __ __ __ (b) SPEEDBRAKE DO NOT ARM illuminates for 4s __ __ __ lt 5. Accelerate A/C slowly. 6. While A/C speed is less that 60 knots: (a) SPEEDBRAKE ARMED lt illuminated __ __ __ (b) SPEEDBRAKE DO NOT ARM extinguished __ __ __ lt





7. When A/C speed reaches 60 knots: (a) SPEEDBRAKE ARMED lt extinguishes __ __ __ (b) SPEEDBRAKE DO NOT ARM illuminates __ __ __ lt 8. Set throttle levers to idle. (a) Speedbrake does not extend __ __ __ 9. Bring A/C to a stop. Remove malfunction.





ATA 123Hidden123

27.12 SPEEDBRAKE EXTENDED LIGHT ON


Failure Description

SPEEDBRAKE EXTENDED indicator fails in ON mode.


FLIGHT DECK EFFECTS: ------------------- - False indication that speedbrakes are extended when they are not

Malfunction Check

1. Select ENGINES via ATM REPOSITIONS page. Ensure speedbrakes are in DOWN position. 2. Insert malfunction. (a) SPEEDBRAKE EXTENDED illuminates __ __ __ lt 3. Remove malfunction.





ATA 123Hidden123

27.13 STANDBY RUD ON


Failure Description

Force fight monitor (FFM) trips.


FLIGHT DECK EFFECTS: ------------------- - The standby pump is automatically activated by the main PCU force fight monitor (FFM) and pressurizes the rudder standby PCU - The "STBY RUD ON" light on the P5-3 overhead panel will be illuminated and the master caution light will annunciate

Malfunction Check

1. Select AIR WORK FL100 via ATM REPOSITIONS page. 2. Insert malfunction. (a) Standby pump automatically activated __ __ __ by the FFM (b) STBY RUD ON lt illuminates when the __ __ __ standby pump is activated (c) Master Caution and illuminate on the Systems __ __ __ Flight Control lts Annunciation Panel 3. Avoid large or abrupt pedal control inputs. 4. Remove malfunction.

Boeing 737-800 FFS Standard Product Specification – Addendum 1 ATA 27F - Flaps/Slats List of Malfunctions




ATA 27F - Flaps/Slats

27F.1 FLAP POSITION IND FAIL


Failure Description

Flap indicator failure or bad connection from the FSEU.


FLIGHT DECK EFFECTS: ------------------- - Appropriate flap position indicator freezes

Malfunction Check

1 Select ENGINES via ATM REPOSITIONS page. Ensure flaps are retracted. 2. Select flap lever to 40. While the flaps are moving, insert LEFT malfunction. (a) Effects as above __ __ __ __ __ __ 3. Select flap lever to 0. 4. Remove malfunction. 5. Repeat checks 2 to 4 for RIGHT malfunction.





ATA 123Hidden123

27F.2 TE FLAP FAILS IN POSITION

CDB Label: TF2750011 LOB TF2750012 LIB TF2750013 RIB TF2750014 ROB

Failure Description

Trailing edge flap transmission sheared.


FLIGHT DECK EFFECTS: ------------------- - Appropriate flap jam in position - Flap asymmetry protection freezes other side's movement - Appropriate aerodynamic effects due to asymmetrical flaps L & R Outbd: - The corresponding flap position indicator freezes in failed position - The other flap position indicator travels until an asymmetry is detected by the FSEU L & R Inbd: - Both flap position indicators show the flap position from the flap position transmitters (on outbd flaps) - When asymmetry is detected, the failed side needle moves back to the failed flap position (bias of 15degrees synchro) Flap position indicator needle split caused by asymmetry of the L or R inboard flap (in deg): Flap Range Needle Split ---------- ------------ 0 to 1 0.4 1 to 2 0.4 2 to 5 1.2 5 to 10 2.0 10 to 15 2.5 15 to 25 5.0 25 to 30 2.5 30 to 40 5.0 NOTE: - If the malfunction is inserted when the TE FLAPS are near the position to which they are commanded, the asymmetry is not yet detected and the other side will move to the selected position. If the TE FLAPS are moved





further, the asymmetry protection will react to stop the other side's movement - Assymetry is removed after malfunction has been removed

Malfunction Check

1. Set up A/C under the following conditions: Select FL100 via ATM REPOSITIONS page. Ensure flaps are at 0. 2. Select flap lever to 40. Insert the LOB malfunction. (a) Effects as above __ __ __ __ __ __ __ __ __ __ __ __ 3. Select flap lever to 0. 4. Remove the malfunction. Select SYSTEM RESET. 5. Repeat checks 2 to 4 for the LIB, RIB and ROB malfunctions.





ATA 123Hidden123

27F.3 TE FLAP ASYM WING


Failure Description

Broken torque tube inboard of R inboard flap.


FLIGHT DECK EFFECTS: ------------------- - Appropriate wing TE flap freezes - Asymmetric protection operates when threshold exceeded - No asymmetric protection on alternate flap system

Malfunction Check

1. Set up A/C under the following conditions: Select ENGINES via ATM REPOSITIONS page. Ensure flaps are at 0. 2. Select flap lever to 40. Insert malfunction. (a) Effects as above __ __ __ 3. Select ALTERNATE FLAPS master sw to ARM. Select ALTERNATE FLAPS sw to DOWN. (a) Effects as above __ __ __ 4. Select ALTERNATE FLAPS master sw to OFF. Select ALTERNATE FLAPS sw to OFF. Select flap lever to 0. 5. Remove malfunction. 6. Select TOTAL RESET via IOS.





ATA 123Hidden123

27F.4 LE FLAP FAILS IN POSITION

CDB Label: TF2780001 1 TF2780002 2 TF2780003 3 TF2780004 4

Failure Description

Leading edge flap jammed in current position.


FLIGHT DECK EFFECTS: ------------------- - Appropriate flap freezes in position - LE TRANSIT lt illuminates and does not extinguish - Appropriate aerodynamic effect due to asymmetrical flaps Failed Retracted then Extended: - LE DEVICE EXTEND lt does not illuminate - LE EXTEND lt does not illuminate Failed Extended then Retracted: - LE DEVICE EXTEND lt does not extinguish - LE EXTEND lt extinguishes

Malfunction Check

1. Select FL100 via ATM REPOSITIONS page. Ensure flaps are at 0. 2. Select flap lever to 1. Insert system 1 malfunction. (a) Effects as above __ __ __ __ __ __ __ __ __ __ __ __ 3. Remove malfunction and wait for LE flap to extend. Re-insert system 1 malfunction. Select flap lever to 0.





(a) Effects as above __ __ __ __ __ __ __ __ __ __ __ __ 4. Remove malfunction and wait for LE flap to retract. 5. Repeat checks 2 to 4 for systems 2,3 and 4 malfunctions.





ATA 123Hidden123

27F.5 AUTO SLAT FAIL

CDB Label: TF2780021 SYS 1 TF2780022 SYS 2

Failure Description

Autoslat computers fail.


FLIGHT DECK EFFECTS: ------------------- If one computer fails: - Autoslats continue to operate normally - AUTOSLAT FAIL, MASTER CAUTION and FLT CONT system warning lts illuminate on recall If both computers fail: - Autoslat is inoperative - AUTOSLAT FAIL, MASTER CAUTION and FLT CONT system warning lts illuminate immediately

Malfunction Check

1. Select AIR WORK FL200 via ATM REPOSITIONS page. Accelerate aircraft to 210 knots and retract flaps on schedule. Select flaps lever to 1. 2. Insert SYS 1 malfunction. 3. Press SYSTEM ANNUNCIATOR RECALL sw. (a) AUTOSLAT FAIL lt illuminates __ __ __ __ __ __ (b) MASTER CAUTION lts illuminate __ __ __ (2) __ __ __ (c) FLT CONT lt illuminates __ __ __ __ __ __ 4. Press MASTER CAUTION sw.





(a) AUTOSLAT FAIL lt extinguishes __ __ __ __ __ __ (b) MASTER CAUTION lts extinguish __ __ __ (2) __ __ __ (c) FLT CONT lt extinguishes __ __ __ __ __ __ 5. Increase the AOA slowly by decreasing airspeed. At a vane AOA of 18.5degrees for 700 model or 17.2degrees for 800 model: (a) LE SLATS move from EXT to FULL __ __ __ EXT __ __ __ 6. Decrease the AOA by increasing airpseed. At a vane AOA of 17.5degrees for 700 model or 16.2degrees for 800 model: (a) LE SLATS move from FULL EXT to __ __ __ EXT __ __ __ 7. Remove malfunction. 8. Repeat checks 2 to 6 for SYS 2 malfunction. 9. Insert SYS 1 and SYS 2 malfunctions. (a) AUTOSLAT FAIL lt illuminates __ __ __ (b) MASTER CAUTION lts illuminate __ __ __ (2) (c) FLT CONT lt illuminates __ __ __ 10. Press MASTER CAUTION sw. (a) AUTOSLAT FAIL lt remain illuminated __ __ __ (b) MASTER CAUTION lts extinguish __ __ __ (2) (c) FLT CONT lt extinguishes __ __ __ 11. Remove both malfunctions. (a) AUTOSLAT FAIL lt extinguishes __ __ __





ATA 123Hidden123

27F.6 LE FLAP EXTENDED LIGHT FAIL


Failure Description

FSEU fails to illuminate LE FLAP EXT lamp (bad connection between FSEU and LE FLAP EXT lt).


FLIGHT DECK EFFECTS: ------------------- - LE FLAP EXT lt does not illuminate - PRESS TO TEST and LIGHTS TEST will illuminate the LE FLAP EXT lt

Malfunction Check

1. Select ENGINES via ATM REPOSITIONS page. Ensure flaps are at 1. 2. Insert malfunction. (a) Effects as above __ __ __ 3. Remove malfunction.





ATA 123Hidden123

27F.7 LE FLAPS TRANSIT LIGHT ON


Failure Description

The output from the FSEU shorted to ground.


FLIGHT DECK EFFECTS: ------------------- - LE FLAP TRANSIT lt illuminates even if the flaps are not in transit

Malfunction Check

1. Select ENGINES via ATM REPOSITIONS page. Ensure flaps are at .0. 2. Insert malfunction. Select flaps lever to 1. (a) Effects as above __ __ __ 3. Remove malfunction.





ATA 123Hidden123

27F.8 FLAP LOAD LIMITER FAILS


Failure Description

Flap load limiter valve solenoid fails.


FLIGHT DECK EFFECTS: ------------------- - Flaps do not automatically retract from 40 to 30 units when airspeed exceeds 163 knots and from 30 to 25 when airspeed exceeds 176 knots

Malfunction Check

1. Set up A/C under the following conditions: Select AIR WORK FL200 via ATM REPOSITIONS page. Flaps 40degrees A/C speed 150 knots 2. Insert malfunction. Increase airspeed to above 165 knots. (a) Effects as above __ __ __ 3. Remove malfunction. (a) L and R FLAP retract to 30 __ __ __ position indicators 4. Select flap lever to 30degrees. 5. Insert malfunction. Increase airspeed to above 180 knots. (a) Effects as above __ __ __ 6. Remove malfunction.





(a) L and R FLAP retract to 25 __ __ __ position indicators 7. Select flap lever to 25degrees. Decrease airspeed to 150 knots. 8. Set up A/C under the following conditions: Select GND ELEC via ATM REPOSITIONS page. Flaps 0degrees FSEU ON 9. Insert malfunction. Select GROUND TESTS? on FSEU Main Menu. Slect TE FLAP LD REL? test on Ground Tests Menu. (a) Effects as above __ __ __ 10. Remove malfunction. Select flap lever to 0. NOTE: Checks 8 through 10 are applicable only if FSEU panel is available via IOS.

Boeing 737-800 FFS Standard Product Specification – Addendum 1 ATA 28 - Fuel List of Malfunctions




ATA 28 - Fuel

28.1 TANK BOOST PUMP FAILS

CDB Label: TF2820001 1 AFT TF2820003 2 AFT TF2820002 1 FWD TF2820004 2 FWD

Failure Description

Pump failure.


FLIGHT DECK EFFECTS: ------------------- - Low Pressure lt illuminates when pump selected to ON position

Malfunction Check

1. Select ENGINES via ATM REPOSITIONS page. Ensure all FUEL PUMP sws (6) are ON. 2. Insert Tank 1 AFT malfunction. (a) Effects as above __ __ __ __ __ __ __ __ __ __ __ __ 3. Remove malfunction. 4. Repeat checks 2 and 3 for remaining malfunctions.





ATA 123Hidden123

28.2 CENTER TANK BOOST PUMP FAILS

CDB Label: TF2820005 L TF2820006 R

Failure Description

Pump failure.


FLIGHT DECK EFFECTS: ------------------- - Low Pressure lt illuminates when pump selected to ON position

Malfunction Check

1. Select ENGINES via ATM REPOSITIONS page. Ensure all FUEL PUMP sws (6) are ON. 2. Insert L malfunction. (a) Effects as above __ __ __ __ __ __ 3. Remove malfunction. 4. Repeat checks 2 and 3 for R malfunction.





ATA 123Hidden123

28.3 CROSSFEED VALVE FAIL IN POSITION


Failure Description

Valve stays in position.


FLIGHT DECK EFFECTS: ------------------- - VALVE OPEN lt (P5) illuminates bright if command differs from position

Malfunction Check

1. Select ENGINES via ATM REPOSITIONS page. Ensure that CTR PUMP sws (2) are OFF and TANK 1 and 2 pump sws (4) are ON. Ensure CROSSFEED selector is closed. 2. Insert malfunction. Position CROSSFEED selector to OPEN. (a) Effects as above __ __ __ 3. Remove malfunction. (a) VALVE OPEN lt dims __ __ __ 4. Reinsert malfunction Position CROSSFEED selector to CLOSE. (a) Effects as above __ __ __ 5. Remove malfunction. (a) VALVE OPEN lt extinguishes __ __ __





ATA 123Hidden123

28.4 TANK LEAK

CDB Label: TF2840001 1 TF2840002 2 TF2840003 CTR

Failure Description

Fuel leak from tank at 20,000 lbs/hr.


FLIGHT DECK EFFECTS: ------------------- - Tank quantity decreases on gauge - For left and right tank, low indication displayed when fuel quantity is less than 2,000 lbs (907 kg) - If malfunction is inserted in-air, imbalance indication is displayed 60s after imbalance becomes more than 1000 lbs

Malfunction Check

1. Select GRD ELECT via ATM REPOSITIONS page. All tanks 4,000 lbs (1810 kg) 2. Insert TANK 1 malfunction. (a) Effects as above __ __ __ __ __ __ __ __ __ 3. Remove malfunction. Restore TANK 1 quantity to capacity. 4. Repeat checks 2 and 3 for TANK 2 and CTR malfunctions. 5. Select A/C ON JACKS. All tanks 4,000 lbs (1810 kg) 6. Insert TANK 1 malfunction. (a) Effects as above __ __ __ __ __ __ __ __ __





7. Remove malfunction. Restore TANK 1 quantity to capacity. 8. Repeat checks 6 and 7 for TANK 2 and CTR malfunctions.

Boeing 737-800 FFS Standard Product Specification – Addendum 1 ATA 29 - Hydraulics List of Malfunctions




ATA 29 - Hydraulics

29.1 HYDRAULIC PUMP LOW PRESSURE - ENGINE PUMP

CDB Label: TF2910001 EDP 1-A TF2910002 EDP 2-B

Failure Description

Mechanical failure in EDP.


FLIGHT DECK EFFECTS: ------------------- - LOW PRESSURE lt illuminates

Malfunction Check

1. Set up A/C under the following conditions: Select ENGINES via ATM REPOSITIONS page. Ensure HYD SYS sws and FLT CONTROL sws are in the following conditions: EDP 1 & 2 HYD PUMP sws ON (2) ELEC 1 & 2 HYD PUMP sws OFF (2) ALTERNATE FLAPS master OFF (guarded) sw FLT CONTROL sw (2) ON (guarded) SPOILER sws (2) On (guarded) 2. Insert EDP 1-A malfunction. (a) Effects as above __ __ __ __ __ __ 3. Remove malfunction. 4. Repeat checks 2 and 3 for EDP 2-B malfunction.





ATA 123Hidden123

29.2 HYDRAULIC PUMP LOW PRESSURE - ELECTRIC PUMP

CDB Label: TF2910021 2-A TF2910022 1-B TF2910023 STBY

Failure Description

Mechanical failure in EMDP.


FLIGHT DECK EFFECTS: ------------------- For systems A & B: - LOW PRESSURE lt illuminates and hydraulic pressure of corresponding system drops to 40 psi (ambient) For STBY system: - STBY hydraulic pressure slowly drops to 47 psi (ambient) - STBY hydraulic LOW PRESSURE lt illuminates when pressure is below 1200 psi

Malfunction Check

1. Set up A/C under the following conditions: Select ENGINES via ATM REPOSITIONS page. Ensure HYD SYS sws and FLT CONTROL sws are in the following conditions: EDP 1 & 2 HYD PUMP sws OFF (2) ELEC 1 & 2 HYD PUMP sws ON (2) ALTERNATE FLAPS master OFF (guarded) sw FLT CONTROL sws (2) ON (guarded) SPOILER sws (2) ON (guarded) 2. Insert EMDP 2-A malfunction.





(a) Effects as above __ __ __ __ __ __ 3. Remove malfunction. 4. Repeat checks 2 and 3 for EMDP 1-B malfunction. 5. Select ELEC 1 & 2 HYD PUMP sws to OFF. 6. Insert STBY malfunction and select ALTERNATE FLAPS master sw to ARM. (a) Effects as above __ __ __ 7. Remove malfunction.





ATA 123Hidden123

29.3 ELECTRIC PUMP OVERHEAT

CDB Label: TF2910031 EMDP 2-A TF2910032 EMDP 1-B

Failure Description

Mechanical failure in EMDP causing overheat.


FLIGHT DECK EFFECTS: ------------------- - Appropriate PUMP OVERHEAT lt illuminates - Appropriate pump LOW PRESSURE lt illuminates - Pump stops

Malfunction Check

1. Set up A/C under the following conditions: Select ENGINES via ATM REPOSITIONS page. Ensure HYD SYS sws and FLT CONTROL sws are in the following conditions: EDP 1 & 2 HYD PUMP sws OFF (2) ELEC 1 & 2 HYD PUMP sws ON (2) ALTERNATE FLAPS master sw OFF (guarded) FLT CONTROL sws (2) ON (guarded) SPOILER sws (2) ON (guarded) 2. Insert EMDP 2-A malfunction. (a) Effects as above __ __ __ __ __ __ 3. Remove malfunction. 4. Repeat checks 2 and 3 for EMDP 1-B malfunction.





ATA 123Hidden123

29.4 SYS RSVR FLUID LOSS - EMDP LINE


Failure Description

Leakage between EMDP and pressure module (rate 1 gal/min).


FLIGHT DECK EFFECTS: ------------------- - HYD annunciator lt illuminates - MASTER CAUTION lts illuminate - LOW PRESSURE lts illuminate when the reservoir quantity drops to 0 gal for system A and 1.29 gal for system B (standpipe level) - Leak stops if the pump is turned off - Hydraulic quantity reduces to 0 gal for system A and 1.29 gal for system B - ELEC PUMP OVERHEAT lts illuminate approx. 45s after related LOW PRESSURE lt Note: 0% is not equivalent to 0 gal, to observe the actual fluid quantity in the reservoirs, use the hydraulic maintenance page on the IOS.

Malfunction Check

1. Set up A/C under the following conditions: Select ENGINES via ATM REPOSITIONS page. Ensure HYD SYS sws and FLT CONTROL sws are in the following conditions: EDP 1 & 2 HYD PUMP sws OFF (2) ELEC 1 & 2 HYD PUMP sws ON (2) ALTERNATE FLAPS master sw OFF (guarded) FLT CONTROL sws (2) ON (guarded) SPOILER sws (2) ON (guarded)





2. Insert SYS-A malfunction. (a) Effects as above __ __ __ __ __ __ 3. Remove malfunction. 4. Select HYDRAULIC FLUID SYS RESET via IOS page. 5. Repeat checks 2 to 4 for SYS-B malfunction.





ATA 123Hidden123

29.5 RESERVOIR LEAK - HI RATE

CDB Label: TF2910071 SYS A TF2910072 SYS B TF2910073 STBY

Failure Description

Large leak in the reservoir.


FLIGHT DECK EFFECTS: ------------------- For SYS A and SYS B malfunction: - Hydraulic quantity reduces to 0 at a rate of 10 gpm - ENG LOW PRESSURE lts illuminate when the quantity drops to 2.25 gal for system A and 1.29 gal for system B - EMDP LOW PRESSURE lts illuminate when the quantity drops to 0 gal for system A and 1.29 gal for system B - ELEC PUMP OVERHEAT lts illuminate approx. 45s after related EMDP LOW PRESSURE lts For STBY malfunction: - System B hydraulic quantity reduces to the balance line quantity at a rate of 10 gpm - Thereafter, STBY system hydraulic quantity reduces to 0 at a rate of 10 gpm - LOW QUANTITY lt illuminates - STBY LOW PRESSURE lt illuminates when the STBY pressure drops below 1200 psi Note: - 0% is not equivalent to 0 gal, to observe the actual fluid quantity in the reservoirs, use the hydraulic maintenance page on the IOS.

Malfunction Check

1. Set up A/C under the following conditions: Select ENGINES via ATM REPOSITIONS page. EDP 1 & 2 HYD PUMP ON sws (2) ELEC 1 & 2 HYD PUMP ON sws (2)





ALTERNATE FLAPS master sw ARM FLT CONTROL sw (2) ON (guarded) SPOILER sws (2) ON (guarded) 2. Insert SYS A malfunction. (a) Effects as above __ __ __ __ __ __ 3. Remove malfunction. 4. Select HYDRAULIC FLUID SYS RESET via IOS page. 5. Repeat checks 2 to 4 for SYS B and STBY malfunctions. Alternate flaps to ARM for STBY.





ATA 123Hidden123

29.6 SYS RSVR FLUID LOSS - EDP LINE


Failure Description

Leakage between EDP and pressure module (rate 1 gal/min).


FLIGHT DECK EFFECTS: ------------------- - LOW PRESSURE lt illuminates when the reservoir quantity drops to the standpipe level - System A quantity reduces to standpipe level (2.25 gallons) (18.7%) - System B quantity reduces to standpipe level (1.29 gallons) (0%) - Leak stops if the pump is off Note: - 0% is not equivalent to 0 gal, to observe the actual fluid quantity in the reservoirs, use the hydraulic maintenance page on the IOS.

Malfunction Check

1. Set up A/C under the following conditions: Select ENGINES via ATM REPOSITIONS page. Ensure HYD SYS sws and FLT CONTROL sws are in the following conditions: EDP 1 & 2 HYD PUMP sws ON (2) ELEC 1 & 2 HYD PUMP sws OFF (2) ALTERNATE FLAPS master sw OFF (guarded) FLT CONTROL sws (2) ON (guarded) SPOILER sws (2) ON (guarded) 2. Insert SYS A malfunction.





(a) Effects as above __ __ __ __ __ __ 3. Remove malfunction. 4. Select HDYRAULIC FLUID SYS RESET via IOS page. 5. Repeat checks 2 to 4 for SYS B malfunction.

Boeing 737-800 FFS Standard Product Specification – Addendum 1 ATA 30 - Ice and Rain List of Malfunctions




ATA 30 - Ice and Rain

30.1 ENGINE COWL VALVE - PRESSURE VALVE FAILS


Failure Description

Engine cowl anti-ice valve fails in position.


FLIGHT DECK EFFECTS: ------------------- - Engine COWL VALVE OPEN lts illuminate bright when engine anti-ice valve position disagrees with the engine anti-ice switch setting - Duct pressure indicator remains stable when cowl anti-ice system is commanded to a different state - TAI indicator turns amber after approx 8s when valve and switch positions disagree If the valve is failed open and the thrust levers are advanced to a high power setting (overpressure condition): - Engine COWL ANTI-ICE lt illuminates - MASTER CAUTION lts illuminate - ANTI-ICE annunciator illuminates

Malfunction Check

1. Select TAKEOFF B via ATM REPOSITIONS page. 2. Position ENG 1 ANTI-ICE sw to ON. Insert ENG 1 malfunction. (a) Effects none __ __ __ __ __ __ 3. Position ENG 1 ANTI-ICE sw to OFF. (a) Effects as above __ __ __ __ __ __ 4. Advance throttles. (a) Effects as above __ __ __ __ __ __





5. Remove malfunction. 6. Repeat checks 2 to 5 for ENG 2 malfunction.





ATA 123Hidden123

30.2 WINDOW OVERHEAT - RESETTABLE

CDB Label: TF3041001 LSIDE TF3041002 RSIDE TF3041003 L FWD TF3041004 R FWD

Failure Description

Momentary malfunction of overheat function of the WHCU which detects a temporary overheat condition on the aircraft window.


FLIGHT DECK EFFECTS: ------------------- - MASTER CAUTION lts illuminate - ANTI-ICE annunciator illuminates When the Left or Right SIDE window fails: - L/R side window heat OVERHEAT lt illuminates - L/R side window heat ON lt extinguishes 70s after the overheat When the Left or Right FWD windshield fails: - L/R Fwd window heat OVERHEAT lt illuminates - L/R Fwd window heat ON lt extinguishes 70s after the overheat

Malfunction Check

1. Select TAKEOFF B via ATM REPOSITIONS page. Ensure all WINDOW HEAT sws (4) are ON. (a) All WINDOW HEAT ON illuminated __ __ __ lts 2. Insert L FWD malfunction. (a) Effects as above __ __ __ 3. Position L FWD WINDOW HEAT sw to OFF. (a) L FWD OVERHEAT lt extinguishes __ __ __ (b) L FWD ON lt remains extinguished __ __ __ (c) MASTER CAUTION lts (2) extinguish __ __ __





(d) System annunciator extinguishes __ __ __ ANTI-ICE lt 4. Position L FWD WINDOW HEAT sw to ON. (a) L FWD OVERHEAT lt remains extinguished __ __ __ (b) L FWD ON lt illuminates __ __ __ (c) MASTER CAUTION lts (2) remain extinguished __ __ __ (d) System annunciator remains extinguished __ __ __ ANTI-ICE lt 5. Repeat checks 1 to 4 for R FWD, L SIDE and R SIDE malfunctions.





ATA 123Hidden123

30.3 WING A/I VALVE FAILS IN POSITION


Failure Description

Wing thermal anti-ice valve fails in position.


FLIGHT DECK EFFECTS: ------------------- - Wing anti-ice VALVE OPEN lt illuminates bright when wing thermal anti-ice valve position disagrees with the WING ANTI-ICE sw setting - Duct pressure indicator remains stable when wing anti-ice system is commanded to a different state

Malfunction Check

1. Select TAKEOFF B via ATM REPOSITIONS page. Ensure WING ANTI-ICE sw is OFF. 2. Insert LEFT malfunction. Select WING ANTI-ICE sw to ON. (a) L VALVE OPEN lt illuminates brightly __ __ __ __ __ __ (b) R VALVE OPEN lt illuminates brightly, __ __ __ then dims after a short __ __ __ delay 3. Remove malfunction. (a) L VALVE OPEN lt remains bright, then __ __ __ dims after a short delay __ __ __ (b) R VALVE OPEN lt remains dim __ __ __ __ __ __ 4. Insert malfunction. Select WING ANTI-ICE sw to OFF. (a) L VALVE OPEN lt remains bright __ __ __ __ __ __





(b) R VALVE OPEN lt brightens then __ __ __ extinguishes __ __ __ 5. Remove malfunction. (a) L VALVE OPEN lt extinguishes __ __ __ __ __ __ (b) R VALVE OPEN lt remains extinguished __ __ __ __ __ __ 6. Repeat steps 2 to 5 for RIGHT malfunction.

Boeing 737-800 FFS Standard Product Specification – Addendum 1 ATA 31 - Instruments & Displays List of Malfunctions




ATA 31 - Instruments & Displays

31.1 MAP FAILURE FOR DEUS

CDB Label: TF3162011 L-8 TF3162012 L-9 TF3162013 R-8 TF3162014 R-9

Failure Description

Output buses connecting FMC to each DEU fails.


FLIGHT DECK EFFECTS: ------------------- - A MAP failure occurs - GPS position, FMC position, V speeds, distance to go (to next waypoint), ETA, range to altitude, vertical deviation and landing altitude indications are lost - If the ND is in MAP or PLAN mode, the MAP data is removed and the MAP and VTK flags are displayed. If the ND is in PLAN mode, the MAP data is removed and the MAP flag is only displayed

Malfunction Check

For Single FMC configuration ---------------------------- 1. Set up the A/C under the following conditions: Select GRD ELEC via the ATM REPOSITIONS page. Display Select NORMAL Module sws (4) Displays Source sw AUTO Displays CP Source sw NORMAL Capt & F/O EFIS CP MAP mode 2. Insert the L-8 malfunction. (a) Capt inboard DU VTK flag appears __ __ __ (b) Capt outboard and effects as above __ __ __





inboard DU (c) Capt inboard DU MAP data disappears and __ __ __ MAP flag appears after approximately 35s 3. Reset the malfunction. 4. Insert the L-9 malfunction. (a) F/O inboard DU VTK flag appears __ __ __ (b) F/O outboard and effects as above __ __ __ inboard DU (c) F/O inboard DU MAP data disappears and __ __ __ MAP flag appears after approximately 35s 5. Reset the malfunction. For Dual FMC configuration -------------------------- 1. Set up the A/C under the following conditions. Select GRD ELEC via the ATM REPOSITIONS page. FMC source select sw NORMAL Display Select NORMAL Module sws (4) Displays Source sw AUTO Displays CP Source sw NORMAL Capt & F/O EFIS CP MAP mode 2. Insert the L-8 malfunction. (a) Capt inboard DU VTK flag appears __ __ __ (b) Capt outboard and effects as above __ __ __ inboard DU (c) Capt inboard DU MAP data disappears and __ __ __ MAP flag appears after approximately 35s 3. Reset the malfunction. Select the FMC SOURCE select sw to BOTH ON LEFT.





4. Insert the L-9 malfunction. (a) F/O inboard DU VTK flag appears __ __ __ (b) F/O outboard and effects as above __ __ __ inboard DU (c) F/O inboard DU MAP data disappears and __ __ __ MAP flag appears after approximately 35s 5. Reset the malfunction. Select the FMC SOURCE select sw to BOTH ON RIGHT. 6. Insert the R-8 malfunction. (a) Capt inboard DU VTK flag appears __ __ __ (b) Capt outboard and effects as above __ __ __ inboard DU (c) Capt inboard DU MAP data disappears and __ __ __ MAP flag appears after approximately 35s 7. Reset the malfunction. Select FMC SOURCE select sw to NORMAL. 8. Insert the R-9 malfunction. (a) F/O inboard DU VTK flag appears __ __ __ (b) F/O outboard and effects as above __ __ __ inboard DU (c) F/O inboard DU MAP data disappears and __ __ __ MAP flag appears after approximately 35s 9. Reset the malfunction.





ATA 123Hidden123

31.2 EFIS CONTROL PANEL POWER FAIL

CDB Label: TF3162051 CAPT TF3162052 F/O

Failure Description

Power to EFIS control panel fails.


FLIGHT DECK EFFECTS: ------------------- - EFIS CP shuts down and ceases to transmit data to the DEU and WXR On selected side: - ND mode defaults to expanded MAP mode - MAP/WXR range defaults to 40 nm - TFC button defaults ON - MAP buttons default OFF - WXR button defaults OFF on ground and ON in air - Altimeter display blanks and ALT flag appears - Decision height disappears - "DISPLAYS CONTROL PANEL" message appears - When both EFIS Control Panels are failed, or the EFIS CP source sw is set to the failed one, the previous effects are observed on both sides and the TMA displays dashes if the A/T LIM flag is not displayed, N1 reference readout displays "---.-" and the N1 reference bugs disappear

Malfunction Check

1. Select ENGINES via ATM REPOSITIONS page. Display Select Modules sws (4) NORMAL Displays Source sw AUTO Displays Control Panel Source sw NORMAL 2. Insert CAPT EFIS CP malfunction. (a) Captain EFIS Control not functional __ __ __ Panel (b) F/O EFIS Control fully functional, __ __ __





Panel controls the F/O Displays (c) Captain CDS displays effects as above __ __ __ (d) Captain Displays fully functional __ __ __ Select Module (e) Engine Control Module fully functional __ __ __ 3. Select CONTROL PANEL SOURCE sw to both on 2. (a) Captain EFIS Control not functional __ __ __ Panel (b) F/O EFIS Control fully functional, __ __ __ Panel controls the Captain and F/O displays (c) Captain PFD "DISPLAYS CONTROL __ __ __ PANEL" message blanks 4. Reset CAPT EFIS CP malfunction and select CONTROL PANEL SOURCE sw to NORMAL. Insert F/O EFIS CP malfunction. (a) F/O EFIS Control not functional __ __ __ Panel (b) Captain EFIS Control fully functional, __ __ __ Panel controls the Captain displays (c) F/O CDS Displays effects as above __ __ __ (d) F/O Displays Select fully functional __ __ __ Module (e) Engine Control Module fully functional __ __ __ 5. Select CONTROL PANEL SOURCE sw to both on 1. (a) F/O EFIS Control not functional __ __ __ Panel (b) Captain EFIS Control fully functional, __ __ __ Panel controls the Captain and F/O displays (c) F/O PFD "DISPLAYS CONTROL __ __ __ PANEL" message blanks 6. Reset F/O EFIS CP malfunction and select CONTROL PANEL SOURCE sw to NORMAL.





ATA 123Hidden123

31.3 DISPLAY ELECTRONIC UNIT (DEU) FAIL

CDB Label: TF3162061 DEU 1 TF3162062 DEU 2

Failure Description

Power to DEU fails.


FLIGHT DECK EFFECTS: ------------------- - DEU shuts down and ceases to transmit data - DSPLY SOURCE flag will appear on PFDs when the engines are running - CDS FAULT flag will appear on PFDs when both engines are not running and A/C is on ground - ALTN lt on EEC panel on overhead illuminates 15s after malfunction insertion and extinguish approximately 5s after malfunction is removed - DSPLY SOURCE flag will appear when a single DEU has been selected, either manually or automatically, to drive all the six display units If the DEU fails on the same side as the engaged autopilot during climb or descent: - The flight director pitch command bars are removed from both pilots' displays - The pitch command bars reappear at ALT ACQ - The pitch mode reverts to CWS pitch - The autopilot remains engaged If the DEU fails on the same side as the engaged autopilot during level flight: - Climb or descent to a new MCP altitude is not possible in LVL CHG, VNAV, or V/S modes with autopilot engaged If the DEU fails on the opposite side as the engaged autopilot or while in manual F/D mode during climb or descent: - The flight director pitch command bars are removed from the pilot's display on the failed side until ALT ACQ - Climb or descent is possible in LVL CHG, VNAV or V/S modes with the autopilot engaged If the DEU fails on the same side as the engaged autopilot in the APPROACH mode: - The flight director pitch and roll command bars are removed from the pilot's display on the failed side





Malfunction Check

1. Select GROUND ELECTRICS via REPOSITIONS page. Display Select Module sws (4) NORMAL Displays Source sw AUTO Displays Control Panel Source sw NORMAL 2. Insert Left DEU malfunction. (a) CDS displays effect as above __ __ __ 3. Select DISPLAYS SOURCE sw to ALL on 2. (a) All 6 DUs (6) no change __ __ __ 4. Select DISPLAYS SOURCE sw to ALL on 1. (a) All 6 DUs (6) blank after approximately __ __ __ 2s * 5. Reset Left DEU malfunction and select DISPLAYS SOURCE sw to AUTO. (a) CDS displays revert to normal formats __ __ __ and flags disappear after approximately 90s 6. Insert Right DEU malfunction. (a) CDS displays effect as above __ __ __ 7. Select DISPLAYS SOURCE sw to ALL on 1. (a) All 6 DUs (6) no change __ __ __ 8. Select DISPLAYS SOURCE sw to ALL on 2. (a) All 6 DUs (6) blank after approximately __ __ __ 2s * 9. Reset Right DEU malfunction and select DISPLAY SOURCE sw to AUTO. (a) CDS displays revert to normal formats __ __ __ and flags disappear after approximately 90s * DUs will blank in less than 2 seconds in the case of simulated DEUs





ATA 123Hidden123

31.4 DU FAIL - INBOARD/OUTBOARD

CDB Label: TF3162071 LOB TF3162072 LIB TF3162075 RIB TF3162076 ROB

Failure Description

Power to DU fails.


FLIGHT DECK EFFECTS: ------------------- - DU shuts down, stops displaying an image and no longer transmits on its ARINC output bus - Affected DU blanks Classic Format Displays aircraft: --------------------------------- If all Display Select switches are on NORM, then: - A failure to outboard DU causes the inboard DU to display compacted EFIS page - A failure to inboard DU causes the outboard DU to display compacted EFIS page PFD/ND Format Displays aircraft: --------------------------------- If all Display Select switches are on NORM, then: - A failure to outboard DU causes the inboard DU to display PFD format - A failure to inboard DU causes the affected DU to blank

Malfunction Check

1. Select GROUND ELECTRIC via ATM REPOSITIONS page. Display Select Module sws (4) NORMAL Displays Source sw AUTO Displays Control Panel Source sw NORMAL 2. Insert Capt Outboard DU (LOB) malfunction.





(a) CDS DUs effects as above __ __ __ 3. Reset Capt Outboard DU malfunction. Insert Capt Inboard DU (LIB) malfunction. (a) CDS DUs effects as above __ __ __ 4. Reset Capt Inboard DU malfunction. Insert F/O Inboard DU (RIB) malfunction. (a) CDS DUs effects as above __ __ __ 5. Reset F/O Inboard DU malfunction. Insert F/O Outboard DU (ROB) malfunction. (a) CDS DUs effects as above __ __ __ 6. Reset F/O Outboard DU malfunction.





ATA 123Hidden123

31.5 DU FAIL - UPPER/LOWER

CDB Label: TF3162073 UPR TF3162074 LWR

Failure Description

Power to DU fails.


FLIGHT DECK EFFECTS: ------------------- - DU shuts down, stops displaying an image and no longer transmits on its ARINC output bus - Affected DU blanks Classic Format Displays aircraft: --------------------------------- If all Display Select switches are on NORM, then: - A failure to center upper DU causes the center lower DU to display Normal Engines page - A failure to center lower DU causes the center upper DU to display Normal Engines page PFD/ND Format Displays aircraft: --------------------------------- If all Display Select switches are on NORM, then: - A failure to the center upper DU causes the center lower DU to display Primary Engine - A failure to the center lower DU causes the affected DU to blank

Malfunction Check

1. Select GROUND ELECTRIC via ATM REPOSITIONS page. Display Select Module sws (4) NORMAL Displays Source sw AUTO Displays Control Panel Source sw NORMAL 2. Insert Center Upper DU (UPR) malfunction. (a) CDS DUs effects as above __ __ __





3. Reset Center Upper DU malfunction. Insert Center Lower DU (LWR) malfunction. (a) CDS DUs effects as above __ __ __ 4. Reset Center Lower DU malfunction.

Boeing 737-800 FFS Standard Product Specification – Addendum 1 ATA 32 - Landing Gear/Brakes List of Malfunctions




ATA 32 - Landing Gear/Brakes

32.1 AIR/GND SENSOR FAIL IN POSITION - NOSEGEAR

CDB Label: TF3209041 N1 TF3209042 N2

Failure Description

Sensor is failed in position.


FLIGHT DECK EFFECTS: ------------------- If one system is failed: - No flight deck effects If two systems are failed: - Landing gear lever latch stays down locked following takeoff - Systems considered on ground

Malfunction Check

1. Select TAKEOFF B via ATM REPOSITIONS page. 2. Insert N1 malfunction and perform a normal takeoff. (a) Effects as above __ __ __ __ __ __ __ __ __ 3. Remove malfunction. 4. Select SYSTEM RESET or MAINT RESET (as appropriate) via IOS. 5. Repeat checks 2 to 4 using the N2 malfunction. 6. Repeat checks 2 to 4 using both N1 & N2 malfunctions.





ATA 123Hidden123

32.2 AIR/GND SENSOR FAIL IN POSITION - MAIN GEAR

CDB Label: TF3209043 L1 TF3209044 L2 TF3209045 R1 TF3209046 R2

Failure Description

Sensor is failed in position.


FLIGHT DECK EFFECTS: ------------------- If one system or more are failed: - No flight deck effects If two systems are failed: - Landing gear lever latch stays down locked following takeoff - Systems considered on ground

Malfunction Check

1. Select TAKEOFF B via ATM REPOSITIONS page. 2. Insert L1 malfunction and perform a normal takeoff. (a) Effects as above __ __ __ __ __ __ __ __ __ __ __ __ __ __ __ 3. Remove malfunction. 4. Select SYSTEM RESET or MAINT RESET (as appropriate) via IOS. 5. Repeat checks 2 to 4 using L2, R1 and R2 malfunctions. 6. Repeat checks 2 to 4 using any two malfunctions.





ATA 123Hidden123

32.3 GEAR COLLAPSE

CDB Label: TF3210001 NOSE TF3210002 LEFT TF3210003 RIGHT

Failure Description

Landing gear collapses.


FLIGHT DECK EFFECTS: ------------------- - Gear locks down hydraulically or manually and collapses on ground with appropriate sound effects - Green lt illuminates when the gear locks down and before the collapse - Red lt illuminates after the collapse

Malfunction Check

1. Select ON ILS 200 FT via ATM REPOSITIONS page. 2. Insert NOSE malfunction. 3. Perform a normal approach and landing. (a) Effects as above __ __ __ __ __ __ __ __ __ 4. Remove malfunction. 5. Repeat checks 2 to 4 for LEFT and RIGHT malfunctions.





ATA 123Hidden123

32.4 GEAR LEVER FAIL IN POSITION


Failure Description

Gear lever stuck in current position.


FLIGHT DECK EFFECTS: ------------------- Stuck in UP position: - Extension possible only by Manual Emergency handles Stuck in DOWN position: - Gear cannot be raised

Malfunction Check

1. Select AIR WORK 2000 via ATM REPOSITIONS page. Ensure all HYD PUMPS sws (4) are ON. 2. Insert malfunction. Position the Landing Gear lever to DOWN. (a) Effects as above __ __ __ 3. Remove malfunction and wait until landing gear is fully extended. Insert malfunction. Retract the landing gear. (a) Effects as above __ __ __ 4. Remove malfunction.





ATA 123Hidden123

32.5 GEAR SELECTOR VALVE FAIL


Failure Description

Gear selector valve does not put pressure into the landing gear system.


FLIGHT DECK EFFECTS: ------------------- If gear is up: - Only manual extension possible If gear is down: - Retraction not possible

Malfunction Check

1. Select AIR WORK 2000 via ATM REPOSITIONS page. Ensure all HYD PUMPS sws (4) are ON. 2. Insert malfunction. Position the Landing Gear lever to DOWN. (a) Effects as above __ __ __ 3. Remove malfunction and wait until landing gear is fully extended. 4. Reinsert malfunction. Retract the landing gear. (a) Effects as above __ __ __ 5. Remove malfunction.





ATA 123Hidden123

32.6 GEAR UP LOCK FAIL


Failure Description

Gear does not lock up due to faulty lock actuator.


FLIGHT DECK EFFECTS: ------------------- During gear retraction: - Gear red lt remains illuminated

Malfunction Check

1. Select TAKEOFF B via ATM REPOSITIONS page. 2. Insert NOSE malfunction and perform a normal takeoff. Position the Landing Gear lever to UP. (a) Effects as above __ __ __ __ __ __ __ __ __ 3. Remove malfunction. 4. Extend the landing gear. 5. Repeat checks 2 to 4 for LEFT and RIGHT malfunctions.





ATA 123Hidden123

32.7 PARTIAL OR GEAR UP LANDING


Failure Description

Landing gear does not lock down due to faulty lock actuator.


FLIGHT DECK EFFECTS: ------------------- During the extension sequence: - Gear red lt remains illuminated - Green lt remains extinguished - Gear extends normally but does not lock when down - Gravity extension possible, but does not lock down

Malfunction Check

1. Select ON ILS 200 FT via ATM REPOSITIONS page. Ensure all HYD PUMPS sws (4) are ON. 2. Insert NOSE malfunction. Position the Landing Gear lever to DOWN. (a) Effects as above __ __ __ __ __ __ __ __ __ 3. Remove malfunction. Retract the landing gear. 4. Repeat checks 2 and 3 for LEFT and RIGHT malfunctions.





ATA 123Hidden123

32.8 WHEEL BRAKE STUCK IN POSITION

CDB Label: TF3240071 L O/B TF3240072 L I/B TF3240073 R I/B TF3240074 R O/B

Failure Description

Mechanical brake disc failure.


FLIGHT DECK EFFECTS: ------------------- - Dragging force on brake occurs even with brake pedals released

Malfunction Check

1. Select TAKEOFF B via ATM REPOSITIONS page. Ensure ANTISKID is ON and autobrake is selected OFF. 2. Insert L O/B malfunction. Advance throttles and accelerate to 60 knots. 3. Full depress brake pedals and then release. (a) Effects as above __ __ __ __ __ __ __ __ __ __ __ __ 4. Remove malfunction. Stop A/C. Select brake temperature reset. 5. Repeat checks 2 to 4 for L I/B, R I/B and R O/B malfunction.





ATA 123Hidden123

32.9 WHEEL BRAKE INOP


Failure Description

Wheel brake inoperative (actuator fails).


FLIGHT DECK EFFECTS: ------------------- - Appropriate brake inoperative

Malfunction Check

1. Select TAKEOFF B via ATM REPOSITIONS page. Ensure ANTISKID is ON and Autobrake is selected OFF. 2. Insert L O/B malfunction. Advance throttles and accelerate to 60 knots. Fully depress brake pedals. (a) Effects as above __ __ __ __ __ __ __ __ __ __ __ __ 3. Remove malfunction. Stop A/C. Select brake temperature reset. 4. Repeat checks 2 and 3 for the L I/B, R I/B and R O/B malfunctions.





ATA 123Hidden123

32.10 BRAKE PRESS INDICATE ZERO PSI


Failure Description

No input to HYD BRAKE PRESSURE indicator due to open wiring.


FLIGHT DECK EFFECTS: ------------------- - Brake pressure indicator shows 0 psi - Pressure is still available to the brake system

Malfunction Check

1. Select TAKEOFF B via ATM REPOSITIONS page. Ensure ANTISKID is ON and autobrake is selected OFF. 2. Insert malfunction. Advance throttles and accelerate to 60 knots. Fully depress brake pedals and then release. (a) Effects as above __ __ __ 3. Remove malfunction. Stop A/C. Select brake temperature reset.





ATA 123Hidden123

32.11 ANTI-SKID INOPERATIVE

CDB Label: TF3242111 L O/B TF3242112 R O/B TF3242113 L I/B TF3242114 R I/B

Failure Description

Anti-skid valve fails in fully open position.


FLIGHT DECK EFFECTS: ------------------- - ANTI-SKID INOP lt illuminates - No anti-skid protection on the affected wheel - No autobrake available, AUTOBRAKE DISARM lt illuminates when autobrake selector not in OFF position

Malfunction Check

1. Select TAKEOFF B via ATM REPOSITIONS page. Ensure ANTISKID is ON and autobrake is selected OFF. 2. Insert L O/B malfunction. (a) ANTI-SKID INOP lt illuminates __ __ __ __ __ __ __ __ __ __ __ __ 3. Advance throttles and accelerate to 60 knots. Fully depress brake pedals and then release. (a) Effects as above __ __ __ __ __ __ __ __ __ __ __ __ 4. Remove malfunction. Stop A/C.





Select brake temperature reset. 5. Repeat checks 2 to 4 for R O/B, L I/B and R I/B malfunctions.





ATA 123Hidden123

32.12 AUTOBRAKE INOPERATIVE


Failure Description

Control unit autobrake capability fails.


FLIGHT DECK EFFECTS: ------------------- - AUTOBRAKE DISARM lt illuminates if the A/B sw is not in the OFF position - No autobraking available

Malfunction Check

1. Select TAKEOFF B via ATM REPOSITIONS page. 2. Insert malfunction. Select AUTOBRAKE to any position other than OFF. (a) Effects as above __ __ __ 3. Select AUTOBRAKE to OFF. 4. Remove malfunction.





ATA 123Hidden123

32.13 TIRE BURST - MAIN GEAR


Failure Description

Tire explosion.


FLIGHT DECK EFFECTS: ------------------- - Muffled tire explosion - Appropriate motion effects

Malfunction Check

1. Select TAKEOFF B via REPOSITIONS page. Taxi the A/C. 2. Insert L O/B malfunction. (a) Effects as above __ __ __ __ __ __ __ __ __ __ __ __ 3. Remove malfunction. Select TIRE BURST RESET. 4. Repeat checks 2 and 3 for L I/B, R I/B, and R O/B malfunctions.





ATA 123Hidden123

32.14 TIRE BURST - NOSE GEAR

CDB Label: TF3245005 L NOSE TF3245006 R NOSE

Failure Description

Tire explosion.


FLIGHT DECK EFFECTS: ------------------- - Muffled tire explosion - Appropriate motion effects

Malfunction Check

1. Select TAKEOFF B via REPOSITIONS page. Taxi the A/C. 2. Insert L NOSE malfunction. (a) Effects as above __ __ __ __ __ __ 3. Remove malfunction. Select TIRE BURST RESET. 4. Repeat checks 2 and 3 for the R NOSE malfunction.





ATA 123Hidden123

32.15 GEAR FAILS TO UNLOCK


Failure Description

Uplock fails to unlock.


FLIGHT DECK EFFECTS: ------------------- - Red lt stays illuminated - Landing gear can only be lowered by manual extension handles

Malfunction Check

1. Select AIR WORK 2000 via ATM REPOSITIONS page. Ensure landing gear is up. 2. Insert NOSE malfunction. 3. Select landing gear lever to DOWN. (a) Effects as above __ __ __ __ __ __ __ __ __ 4. Remove malfunction. 5. Repeat checks 2 to 4 for LEFT and RIGHT malfunctions.





ATA 123Hidden123

32.16 GEAR DN LK IND FAIL


Failure Description

Respective center instrument panel gear downlock indication fails due to open wiring from PSEU sensors.


FLIGHT DECK EFFECTS: ------------------- - Gear extends and locks down normally - Green light on Center Instrument Panel remains extinguished - Green light on Aft Overhead Panel illuminates

Malfunction Check

1. Select AIR WORK 2000 via ATM REPOSITIONS page. Ensure all HYD PUMPS sws (4) are ON. 2. Insert NOSE malfunction. Position the Landing Gear lever to DOWN. (a) Effects as above __ __ __ __ __ __ __ __ __ 3. Remove malfunction. Retract the landing gear. 4. Repeat checks 2 and 3 for LEFT and RIGHT malfunctions.

Boeing 737-800 FFS Standard Product Specification – Addendum 1 ATA 34 - Navigation List of Malfunctions




ATA 34 - Navigation

34.1 ILS RECEIVER FAIL

CDB Label: TF3431001 1 TF3431002 2

Failure Description

ILS receiver failure.


FLIGHT DECK EFFECTS: ------------------- ILS 1 failure: General: - ILS audio lost On the CAPT EFIS displays: - LOC and GS deviation and scale displays blank - LOC and GS flags in view On the ISFD (or STBY ADI)*: - LOC and GS flags in view ** - LOC and GS pointers out of view ILS 2 failure: General: - ILS audio lost On the F/O EFIS displays: - LOC and GS deviation and scale displays blank - LOC and GS flags in view * Applicable only for those simulators having a STBY ADI installed. ** On the ISFD, the GS flag comes into view 11s after system 1 failure.

Malfunction Check

1. Set EFIS CP mode selectors (2) to APP CTR. On the VHF NAV CP(s), tune the frequency selectors (2) to 110.50 MHz. Set the MCP course selectors (2) to 270 deg.





On the ISFD (or STBY ADI)*, set the ILS mode to APP. Select the NAV sws on the audio selector panels. 2. Ensure NATF is activated on the IOS. Select setup no. 139. 3. Insert the system 1 malfunction. (a) Failure effects as above __ __ __ __ __ __ 4. Remove the malfunction. 5. Repeat checks 3 and 4 for the system 2 malfunction.





ATA 123Hidden123

34.2 GLIDESLOPE RECEIVER FAIL

CDB Label: TF3431011 1 TF3431012 2

Failure Description

ILS glideslope receiver failure.


FLIGHT DECK EFFECTS: ------------------- System 1 failure: On the CAPT EFIS displays: - GS scale and deviation displays blank - GS flag in view On ISFD (or STBY ADI)*: - GS flag in view** - GS pointer out of view System 2 failure: On the F/O EFIS displays: - GS scale and deviation displays blank - GS flag in view * Applicable only for those simulators having a STBY ADI installed. ** On the ISFD, the GS flag comes into view 11s after system 1 failure

Malfunction Check

1. Set EFIS CP mode selectors (2) to APP CTR. On the VHF NAV CP(s), tune the frequency selectors (2) to 110.50 MHz. Set the MCP course selectors (2) to 270 deg. On the ISFD (or STBY ADI)*, set the ILS mode to APP. 2. Ensure NATF is activated on the IOS. Select setup no. 139.





3. Insert the system 1 malfunction. (a) Failure effects as above __ __ __ __ __ __ 4. Remove the malfunction. 5. Repeat checks 3 and 4 for the system 2 malfunction. * Applicable only to simulators having a STBY ADI installed.

Boeing 737-800 FFS Standard Product Specification – Addendum 1 ATA 34A - Flight Instruments List of Malfunctions




ATA 34A - Flight Instruments

34A.1 PITOT PROBE HEAT FAIL

CDB Label: TF3031001 CAPT TF3031002 F/O TF3031003 AUX

Failure Description

Pitot probe heater element fails.


FLIGHT DECK EFFECTS: ------------------- System 1 (CAPT) failure: On the Window and Pitot Heat panel: - CAPT PITOT annunciator illuminates On the Master Caution panel: - ANTI-ICE system annunciator illuminates - MASTER CAUTION lts illuminate On the CAPT and F/O EFIS: - IAS DISAGREE message appears (if applicable) System 2 (F/O) failure: On the Window and Pitot Heat panel: - F/O PITOT annunciator illuminates On the Master Caution panel: - ANTI-ICE system annunciator illuminates - MASTER CAUTION lts illuminate On the CAPT and F/O EFIS: - IAS DISAGREE message appears (if applicable) System 3 (AUX) failure: On the Window and Pitot Heat panel: - AUX PITOT annunciator illuminates On the Master Caution panel: - ANTI-ICE system annunciator illuminates - MASTER CAUTION lts illuminate





Note 1: When in icing conditions, pitot probe freezes/blocks. AUX indications appear on ISFD (or STBY altimeter/Airspeed Ind)*. EECs go into ALT mode. Note 2: Altitude slightly underreads/overreads when A/C climbs/descends, due to an indirect effect of the Static Source Error Correction that is a function of mach. * Applicable only to simulators with a STBY Altimeter/Airspeed Ind. installed.

Malfunction Check

1. Select AIR WORK FL100 via ATM REPOSITIONS page. 2. Set up severe icing conditions and fly level at FL100. Set OAT in order to get a TAT between -20 deg C and +6 deg C. 3. Insert the CAPT malfunction. (a) CAPT PITOT illuminates __ __ __ annunciator __ __ __ __ __ __ (b) MASTER CAUTION lt illuminates __ __ __ __ __ __ __ __ __ (c) ANTI-ICE system illuminates __ __ __ annunciator __ __ __ __ __ __ 4. Increase altitude. (a) IAS indication on overreads __ __ __ CAPT EFIS display __ __ __ __ __ __ (b) MACH indication on overreads __ __ __ CAPT EFIS display __ __ __ N/A for AUX __ __ __ (c) IAS DISAGREE msg appears __ __ __ on Capt EFIS __ __ __ N/A for AUX __ __ __ 5. Decrease altitude past FL100. (a) IAS indication on underreads __ __ __ CAPT EFIS display __ __ __ __ __ __





(b) MACH indication on underreads __ __ __ CAPT EFIS display __ __ __ N/A for AUX __ __ __ (c) IAS DISAGREE msg appears __ __ __ on Capt EFIS __ __ __ N/A for AUX __ __ __ 6. Remove the malfunction. (a) Pitot annunciator extinguishes __ __ __ __ __ __ __ __ __ (b) MASTER CAUTION lt extinguishes __ __ __ __ __ __ __ __ __ (c) ANTI-ICE system extinguishes __ __ __ annunciator __ __ __ __ __ __ (d) IAS indication on returns to normal __ __ __ CAPT EFIS display __ __ __ N/A for AUX __ __ __ (e) MACH indication on returns to normal __ __ __ CAPT EFIS display __ __ __ N/A for AUX __ __ __ 7. Repeat checks 1 to 6 for the F/O and AUX malfunctions.





ATA 123Hidden123

34A.2 AOA PROBE HEAT FAIL


Failure Description

Alpha probe heater element fails.


FLIGHT DECK EFFECTS: ------------------- System 1 (LEFT) malfunction: On the Window and Pitot Heat panel: - L ALPHA VANE annunciator illuminates On the Master Caution panel: - ANTI-ICE system annunciator illuminates - MASTER CAUTION lts illuminate System 2 (RIGHT) malfunction: On the Window and Pitot Heat panel: - R ALPHA VANE annunciator illuminates On the Master Caution panel: - ANTI-ICE system annunciator illuminates - MASTER CAUTION lts illuminate Note: When in icing conditions, alpha vane freezes in position

Malfunction Check

1. Select TAKEOFF B via ATM REPOSITIONS page. 2. Insert the LEFT malfunction. (a) L ALPHA VANE illuminates __ __ __ annunciator __ __ __ (b) MASTER CAUTION lt illuminates __ __ __ __ __ __ (c) ANTI-ICE system illuminates __ __ __ annunciator __ __ __





3. Remove the malfunction. (a) L ALPHA VANE extinguishes __ __ __ annunciator __ __ __ (b) MASTER CAUTION lt extinguishes __ __ __ __ __ __ (c) ANTI-ICE system extinguishes __ __ __ annunciator __ __ __ 4. Repeat checks 2 and 3 for the RIGHT malfunction.





ATA 123Hidden123

34A.3 TAT PROBE HEAT FAIL


Failure Description

TAT probe heater element fails.


FLIGHT DECK EFFECTS: ------------------- On the Window and Pitot Heat panel: - TEMP PROBE annunciator illuminates On the Master Caution panel: - ANTI-ICE system annunciator illuminates - MASTER CAUTION lts illuminate Note: When in icing conditions, TAT indication slowly drops toward OAT (reads a lagged value of OAT when fully blocked)

Malfunction Check

1. Select AIR WORK FL100 via ATM REPOSITIONS page. 2. Set up icing conditions and fly level at FL100. 3. Insert the malfunction. (a) TEMP PROBE illuminates __ __ __ annunciator (b) MASTER CAUTION lt illuminates __ __ __ (c) ANTI-ICE system illuminates __ __ __ annunciator (d) TAT indication begins to drop toward OAT __ __ __ 4. Remove the malfunction. (a) TEMP PROBE extinguishes __ __ __ annunciator (b) MASTER CAUTION lt extinguishes __ __ __





(c) ANTI-ICE system extinguishes __ __ __ annunciator (d) TAT indication returns to normal __ __ __





ATA 123Hidden123

34A.4 RADIO ALTIMETER FAIL

CDB Label: TF3433011 1 TF3433012 2

Failure Description

Radio altimeter failure.


FLIGHT DECK EFFECTS: ------------------- System 1 failure: On the CAPT EFIS display: - RA flag in view - Rising runway symbol out view (if applicable) System 2 failure: On the F/O EFIS display: - RA flag in view - Rising runway symbol out view (if applicable)

Malfunction Check

1. Select TAKEOFF B via ATM REPOSITIONS page. 2. Insert the system 1 malfunction. (a) RA flag on appears __ __ __ CAPT EFIS display __ __ __ 3. Remove the malfunction. (a) RA indication on reads -4 ft __ __ __ CAPT EFIS display __ __ __ 4. Repeat checks 2 and 3 for the system 2 malfunction.





ATA 123Hidden123

34A.5 ISFD FAIL


Failure Description

The Integrated Standby Flight Display (ISFD) fails.


FLIGHT DECK EFFECTS: ------------------- On te ISFD: - Display blanks

Malfunction Check

1. Select AIR WORK FL100 via ATM REPOSITIONS page. (a) ISFD attitude indicates A/C pitch __ __ __ and roll attitudes (b) ISFD altitude indicates A/C altitude __ __ __ (c) ISFD airspeed indicates A/C IAS __ __ __ 2. Insert the malfunction. (a) Effects as above __ __ __ 3. Remove the malfunction. (a) ISFD display aligning __ __ __ Within 90s: (b) ISFD attitude indicates A/C pitch __ __ __ and roll attitudes (c) ISFD altitude indicates A/C altitude __ __ __ (d) ISFD airspeed indicates A/C IAS __ __ __





ATA 123Hidden123

34A.6 ISFD ROLL/PITCH FAIL

CDB Label: TF3433071 1 TF3433072 2

Failure Description

ISFD Roll and Pitch indications fail.


FLIGHT DECK EFFECTS: ------------------- System 1 (Roll) failure: On the ISFD: - ATT flag in view 11s after malfunction is activated - A/C symbol not displayed - Roll not displayed - Pitch not displayed System 2 (Pitch) failure: On the ISFD: - ATT flag in view 11s after malfunction is activated - A/C symbol not displayed - Roll not displayed - Pitch not displayed

Malfunction Check

1. Select AIR WORK FL100 via the ATM REPOSITIONS page. (a) ISFD attitude indicates A/C pitch __ __ __ and roll attitudes 2. Insert the system 1 malfunction. (a) Effects as above __ __ __ __ __ __ 3. Remove the malfunction. (a) ISFD attitude indicates A/C pitch __ __ __ and roll attitudes __ __ __ 4. Repeat checks 2 and 3 for the system 2 malfunction.

Boeing 737-800 FFS Standard Product Specification – Addendum 1 ATA 34E - EGPWS List of Malfunctions




ATA 34E - EGPWS

34E.1 EGPWS FAIL


Failure Description

GPWC capture total failure.


FLIGHT DECK EFFECTS: ------------------- - Ground Proximity test inoperative - No GPWS aural and visual warning - GPWS INOP lt illuminates

Malfunction Check

1. Select ENGINES via ATM REPOSITIONS page. Remove FLIGHT FREEZE. 2. Insert malfunction. (a) GPWS INOP lt illuminates __ __ __ (b) GPWS Test sw inoperative __ __ __ 3. Remove malfunction. (a) GPWS INOP lt extinguishes (after a __ __ __ short delay) (b) GPWS Test sw operative __ __ __





ATA 123Hidden123

34E.2 EGPWS FALSE MODE 2 WARNING


Failure Description

Closure rate detector on the GPWC senses false signal 4000 for 30s. Closure rate detector returns to normal after 30s.


FLIGHT DECK EFFECTS: ------------------- If the GPWC senses the airplane entering the mode 2A or 2B envelope: - PULL UP message is displayed - Appropriate warning sounds - PULL UP messages turn OFF and aural warning terminates after 30s, unless airplane does not enter mode 2 envelope - When the closure rate detector senses termination of the mode 2 condition, the detector starts the altitude gain function - The altitude gain function is terminated when the airplane has gained 300 ft in barometric altitude from the point where the mode 2 condition is terminated

Malfunction Check

1. Select TAKEOFF B via ATM REPOSITIONS page. 2. Initialize the FMS. 3. Select 12NM INTERCEPT via ATM REPOSITIONS page. 4. Increase airspeed to 250 knots and fly A/C level at an altitude of 1900 ft. Ensure gear and flaps are up. 5. Insert malfunction. As radio altitude goes below 1310 ft on avionics maintenance page: (a) Capt and F/O PFD "PULL UP" message __ __ __ appears (b) GPWS aural warning "TERRAIN TERRAIN" __ __ __





6. While the terrain closure remains: (a) GPWS aural warning "PULL UP" __ __ __ 7. When terrain closure disappears: (a) GPWS aural warning "TERRAIN" __ __ __ 8. Climb A/C. As A/C baro altitude increases by 300 ft: (a) Capt and F/O PFD "PULL UP" message __ __ __ disappears (b) GPWS aural warning ceases __ __ __

Boeing 737-800 FFS Standard Product Specification – Addendum 1 ATA 34F - FMS List of Malfunctions




ATA 34F - FMS

34F.1 FMC FAIL

CDB Label: TF3461001 1 TF3461002 2

Failure Description

FMC internal power failure.


FLIGHT DECK EFFECTS: ------------------- (For Single FMC configuration) L Malfunction: With DEU select sw in 'NORMAL' and N1 manual set knob to 'AUTO': For MCDU, the following occurs on L & R MCDUs: - MCDUs display MENU page and the FMC prompt is removed after approximately 3s On Autoflight Status Annunciator: - FMC alert lt illuminates On Capt and F/O Inboard DU: - The VTK flag appears - After approximately 35s, the map disappears and the MAP flag appears On Engine Primary Display: - Thrust Mode Annunciation blanks if the 'A/T LIM' flag is not displayed - N1 readouts display dashes --.- - N1 bugs stay at the last valid position Note: In Single FMC configuration, the FMC select source switch has no effect, no effects for the FMC right malfunction also. (For DUAL FMC configuration) L Malfunction: With FMC source select sw in 'NORMAL' or 'BOTH ON L' position, DEU select sw in 'NORMAL' and N1 manual set knob to 'AUTO': For MCDU, the following occurs on L & R MCDUs: - MCDUs display MENU page and the FMC prompt is removed after approximately 3s





On Autoflight Status Annunciator: - FMC alert lt illuminates On Capt. Inboard DU: - The VTK flag appears - After approximately 35s, the map disappears and the MAP flag appears On Primary Display: - Thrust Mode Annunciation blanks if the 'A/T LIM' flag is not displayed - N1 readouts display dashes ---- - N1 bugs stay at the last valid position With FMC source select sw in "BOTH ON R" position: On L & R MCDUs: - Normal page appears - SINGLE FMC OPERATION appears in scratchpad On CDS Inboard DUs: - FMC R annunciation is displayed in MAP or CTR MAP modes R malfunction: With FMC source select sw in 'NORMAL' or 'BOTH ON L' position, DEU select sw in 'NORMAL': On L & R MCDUs: - SINGLE FMC OPERATION appears in scratchpad after approximately 10s On Autoflight Status Annunciator: - FMC alert lt illuminates On F/O Inboard DU (if FMC Source Select sw is in NORMAL position): - The VTK flag appears - After 35s, the map disappears and the MAP flag appears With FMC source select sw in 'BOTH ON R' position, DEU select sw in 'NORMAL' and N1 manual set knob to 'AUTO': L & R MCDU: - MENU page without FMC prompts after approximatelty 3s CDS inboard DUs: - Warning flags appear On Autoflight Status Annunciator: - FMC alert lts illuminate On Primary Display: - Thrust Mode Annunciation blanks if the 'A/T LIM' flag is not displayed - N1 readouts display dashes ---- - N1 bugs stay at the last valid position





Malfunction Check

(For Single FMC configuration) 1. Select ENGINES via ATM REPOSITIONS page. Select FMC Source Select sw to NORMAL. Select DEU Source Select sw to NORMAL. Select both EFIS CP modes to MAP. 2. Insert L malfunction. (a) Capt and F/O MCDUs effects as above __ __ __ (b) Capt and F/O panels FMC amber lt illuminated __ __ __ (c) Capt and F/O effects as above __ __ __ inboard DUs (d) Engine primary effects as above __ __ __ displays 3. Remove L malfunction. After approximately 20s: (a) Capt and F/O MCDUs normal display __ __ __ (b) Capt and F/O panels FMC amber lt extinguished __ __ __ (c) Capt and F/O normal display __ __ __ inboard DUs (d) Engine primary normal display __ __ __ displays (For Dual FMC configuration) 1. Select ENGINES via ATM REPOSITIONS page. Select FMC Source Select sw to NORMAL. Select DEU Source Select sw to NORMAL. Select both EFIS CP modes to MAP. 2. Insert L malfunction. (a) Capt MCDU effects as above __ __ __ (b) Capt and F/O panels FMC amber lt illuminated __ __ __





(c) F/O MCDU effects as above __ __ __ (d) Capt inboard DU effects as above __ __ __ (e) Engine primary effects as above __ __ __ display 3. Set the FMC Source Select sw to BOTH ON R. (a) Capt MCDU effects as above __ __ __ (b) Capt and F/O panels FMC amber lt __ __ __ extinguishes if the "SINGLE FMC OPERATION" message is cleared (c) F/O MCDU effects as above __ __ __ (d) CDS inboard DUs effects as above __ __ __ 4. Remove L malfunction and reset the FMC Source Select sw to NORMAL. After approximately 20s: (a) Capt MCDU normal display __ __ __ (b) Capt and F/O panels FMC amber extinguished __ __ __ (c) F/O MCDU normal display __ __ __ (d) CDS inboard DUs normal display __ __ __ (e) Engine primary normal display __ __ __ display 5. Insert R malfunction. (a) Capt MCDU effects as above __ __ __ (b) Capt and F/O panels FMC amber lt illuminated __ __ __ (c) F/O MCDU effects as above __ __ __ (d) F/O inboard DU effects as above __ __ __ 6. Set the FMC Source Select sw to BOTH ON R. (a) Capt MCDU effects as above __ __ __ (b) Capt and F/O panels FMC amber lt illuminated __ __ __ (c) F/O MCDU effects as above __ __ __ (d) CDS inboard DUs effects as above __ __ __





(e) Engine primary effects as above __ __ __ display 7. Remove R malfunction and reset the FMC Source Select sw to NORMAL. (a) Capt MCDU normal display __ __ __ (d) Capt inboard DU normal display __ __ __ (c) F/O MCDU normal display __ __ __ (d) Capt and F/O panels FMC amber lt extinguished __ __ __ after approximately 15s (e) F/O inboard DU normal display after __ __ __ approximately 20s (f) Engine primary normal display __ __ __ display





ATA 123Hidden123

34F.2 MCDU FAIL

CDB Label: TF3461011 1 TF3461012 2

Failure Description

MCDU FAIL line from MCDU to both FMCs is made open circuit to give each FMC a failure warning.


FLIGHT DECK EFFECTS: ------------------- - MCDU CRT blanks - MCDU does not respond to any inputs

Malfunction Check

1. Select ENGINES via ATM REPOSITIONS page. 2. Insert L malfunction. (a) Capt MCDU effects as above __ __ __ 3. Remove malfunction. (a) Capt MCDU normal display __ __ __ 4. Insert R malfunction. (a) F/O MCDU effects as above __ __ __ 5. Remove malfunction. (a) F/O MCDU normal display __ __ __

Boeing 737-800 FFS Standard Product Specification – Addendum 1 ATA 34I - IRS List of Malfunctions




ATA 34I - IRS

34I.1 ADIRU - IR FUNCTION FAIL

CDB Label: TF3421001 1 TF3421002 2

Failure Description

IR function failure.


FLIGHT DECK EFFECTS: ------------------- System 1 failure: On the CAPT EFIS: - ATT flag in view - HDG flag in view - VSI pointer disappears - VSI/VERT flag in view On the RMI: - HDG flag in view On the ISFD*: - HDG flag in view 11s after system 1 fails On the Master Caution panel: - IRS system annunciator illuminates - Master Caution lts illuminate On the MSU: - FAULT annunciator illuminates for L system On the ISDU: - IRS STS for L system displays codes 02 and 37** System 2 failure: On the F/O EFIS: - ATT flag in view - HDG flag in view - VSI pointer disappears - VSI/VERT flag in view On the Master Caution panel: - IRS system annunciator illuminates - Master Caution lts illuminate





On the MSU: - FAULT annunciator illuminates for R system On the ISDU: - IRS STS for R system displays codes 02 and 37** * Applicable only for those simulators having an ISFD installed. ** Press CLR button on ISDU to toggle between codes.

Malfunction Check

1. Select TAKEOFF B via ATM REPOSITIONS page. 2. Insert the system 1 malfunction. (a) Failure effects as above __ __ __ __ __ __ Maintenance (if applicable): ----------- 3. Peform the IR L GROUND TEST. (a) TEST condition pass __ __ __ __ __ __ 4. Remove the malfunction. Perform an IR FAST ALIGN via the IOS. 5. Repeat checks 1 to 4 for the system 2 malfunction.





ATA 123Hidden123

34I.2 IR FAILS TO ALIGN

CDB Label: TF3421081 1 TF3421082 2

Failure Description

IRS latitude comparison test fails at the end of the alignment period.


FLIGHT DECK EFFECTS: ------------------- System 1 failure: On the MSU: - ALIGN annunciator flashes at the end of alignment for L system On the ISDU: - IRS STS displays code 04 for L system On the MSDU: - On FMC pages, ENTER IRS POSITION message appears System 2 failure: On the MSU: - ALIGN annunciator flashes at the end of alignment for R system On the ISDU: - IRS STS displays code 04 for R system On the MSDU: - On FMC pages, ENTER IRS POSITION message appears Note: IR does not go into NAV mode.

Malfunction Check

1. Select TAKEOFF B via ATM REPOSITIONS page. 2. Rotate the MSU L selector from OFF to NAV and start the stopwatch. 3. Wait at least 6s, then enter the A/C's present position via the ISDU.





4. Insert the system 1 malfunction. At the end of alignment: (a) Failure effects as above __ __ __ __ __ __ 5. Remove the malfunction. (a) MSU L ALIGN extinguishes __ __ __ annunciator __ __ __ (b) IR STATUS display blanks __ __ __ __ __ __ On the Capt's EFIS display: (c) ATT flag out of view __ __ __ __ __ __ (d) HDG flags out of view __ __ __ __ __ __ (e) VSI pointer in view __ __ __ __ __ __ (f) VSI/VERT flag out of view __ __ __ __ __ __ On the RMI: (g) HDG flag out of view __ __ __ __ __ __ On the ISFD*: (h) HDG flag out of view __ __ __ __ __ __ 6. Repeat checks 1 to 5 for the system 2 malfunction. * Applicable only for those simulators having an ISFD installed.





ATA 123Hidden123

34I.3 ADIRU - IR MOTION


Failure Description

Motion is detected during the alignment process.


FLIGHT DECK EFFECTS: ------------------- On the MSU: - ALIGN annunciation remains illuminated On the ISDU: - IRS STS display code 03 On the MCDU: - On FMC pages, IRS MOTION message appears Note: IRS alignment is halted as soon as A/C motion is detected and automatically resumes when motion terminates

Malfunction Check

1. Select TAKEOFF B via ATM REPOSITIONS page. 2. Rotate the MSU L and R selectors from OFF to NAV and start the stopwatch. 3. Wait at least 6s, then enter the A/C's present position via the FMC. 4. Insert the malfunction. (a) Failure effects as above __ __ __ Maintenance: (if applicable) ----------- 5. Peform the IR L GROUND TEST. (a) TEST condition pass __ __ __ 6. Remove the malfunction and restart the stopwatch.





(a) MSU L & R ALIGN remain illuminated __ __ __ annunciators (b) ISDU STATUS display blank after 30s __ __ __ for IR L and R 7. At the end of alignment: On the Capt's EFIS display: (c) ATT flag out of view __ __ __ (d) HDG flag out of view __ __ __ (e) VSI pointer in view __ __ __ (f) VSI/VERT flag out of view __ __ __ On the F/O's EFIS display: (g) ATT flag out of view __ __ __ (h) HDG flag out of view __ __ __ (i) VSI pointer in view __ __ __ (j) VSI/VERT flag out of view __ __ __ On the RMI: (k) HDG flag out of view __ __ __ (l) HDG card A/C heading __ __ __ On the ISFD*: (m) HDG flag out of view __ __ __ (n) Heading A/C heading displayed __ __ __ * Applicable only to simulators with an ISFD installed. Note: Only check 5 is applicable for maintenance configurations





ATA 123Hidden123

34I.4 ADIRU - IR POSITION DRIFT

CDB Label: TF3421094 1 TF3421095 2

Failure Description

The accelerometer auto-bias feature (used to estimate the residual level axis accelerometer biases) is inoperative. Increasing IR position error from the actual A/C position towards the following directions at a rate of 10 nm/hr. IR 1 - NORTH IR 2 - SOUTH


FLIGHT DECK EFFECTS: ------------------- System 1 failure: On the ISDU: - TK/GS for L system becomes innaccurate - PPOS drifts at the specified rate for L system On the MCDU: - On the FMCs POS REF page 2/3, GS for IRS L is inaccurate System 2 failure: On the ISDU: - TK/GS for R system becomes innaccurate - PPOS drifts at the specified rate for R system On the MCDU: - On the FMCs POS REF page 2/3, GS for IRS R is inaccurate Note: The following IR parameters become inaccurate: - Groundspeed - Position - Track - Drift indication

Malfunction Check

1. Select ENGINES via ATM REPOSITIONS page.





2. Rotate the MSU L and R selectors to NAV and FAST ALIGN the IRs via the IOS. 3. Set the A/C in cruise and fly on a northernly heading. 4. Insert the system 1 malfunction and start the stopwatch. After 15 minutes of flight: (a) Failure effects as above __ __ __ __ __ __ 5. Remove the malfunction. FAST ALIGN the IR via the IOS. (a) IR TRK and GS actual TRK and GS __ __ __ display on ISDU __ __ __ (b) IR PPOS display actual A/C position __ __ __ on ISDU and FMC __ __ __ 6. Re-synchronize the FMCs by selecting BOTH ON L (or BOTH ON R). 7. Repeat checks 1 to 6 for the system 2 malfunction, but fly the A/C on a southernly heading.





ATA 123Hidden123

34I.5 IR NON-CRITICAL FAULT

CDB Label: TF3421041 1 TF3421042 2

Failure Description

IR internal failure causing NAV mode function to fail. Attitude mode is selectable.


FLIGHT DECK EFFECTS: ------------------- System 1 failure: On the CAPT EFIS: - ATT flag in view - HDG flag in view - VSI pointer disappears - VSI/VERT flag in view On the RMI: - HDG flag in view On ISFD*: - HDG flag in view 11s after system 1 fails On the Master Caution panel: - IRS system annunciator illuminates - MASTER CAUTION lts illuminate On the MSU: - FAULT annunciator illuminates for L system On the ISDU: - IRS STS displays code 02 and 37** for L system System 2 failure: On the F/O EFIS: - ATT flag in view - HDG flag in view - VSI pointer disappears - VSI/VERT flag in view On the Master Caution panel: - IRS system annunciator illuminates





- MASTER CAUTION lts illuminate On the MSU: - FAULT annunciator illuminates for R system On the ISDU: - IRS STS displays code 02 and 37** for R system Note 1: All IR outputs are failed when malfunction is activated. Note 2: Selecting Attitude mode clears fault and will provide primary attitude and heading information. * Applicable only for those simulators having an ISFD installed. ** Press CLR button on ISDU to toggle between codes.

Malfunction Check

1. Select TAKEOFF B via ATM REPOSITIONS page. 2. Insert the system 1 malfunction. (a) Failure effects as above __ __ __ __ __ __ 3. Rotate the MSU L to ATT and start the stopwatch. (a) MSU L FAULT extinguishes __ __ __ annunciator __ __ __ (b) Malfunction automatically clears __ __ __ __ __ __ After 2s: (c) MSU L ALIGN illuminates __ __ __ annunciator __ __ __ After 20s: On the Capt's EFIS display: (d) ATT flag out of view __ __ __ __ __ __ (e) HDG flags out of view __ __ __ __ __ __ (f) VSI pointer in view __ __ __ __ __ __ (g) VSI/VERT flag out of view __ __ __ __ __ __





On the ISDU: (h) IRS STS display code 09 displayed __ __ __ __ __ __ On the RMI (System 1 only): (i) HDG flag in view __ __ __ On the ISFD* (System 1 only): (j) HDG flag in view __ __ __ 4. Enter the magnetic heading via the ISDU. On the Capt's EFIS display: (H__ __ __) (a) Magnetic heading entered heading __ __ __ displayed __ __ __ On the RMI (System 1 only): (b) HDG flag out of view __ __ __ (c) HDG card entered heading __ __ __ displayed On the ISFD* (System 1 only): (d) HDG flag out of view __ __ __ (e) Heading entered heading __ __ __ displayed 5. Rotate the MSU back to NAV and then FAST ALIGN the IRSs via the IOS. 6. Repeat checks 1 to 5 for the system 2 malfunction. * Applicable only for those simulators having an ISFD installed.





ATA 123Hidden123

34I.6 ADIRU ON DC


Failure Description

AC power fails and DC power is available.


FLIGHT DECK EFFECTS: -------------------- For system 1 failure: On the MSU: - ON DC annunciator illuminates for L system On the Master Caution panel: - IRS system annunciator illuminates - MASTER CAUTION lts illuminate General: - "IRS ON DC" warning horn sounds 20s after system 1 fails (A/C on ground only) For system 2 failure: On the MSU: - ON DC annunciator illuminates for R system On the Master Caution panel: - IRS system annunciator illuminates - MASTER CAUTION lts illuminate General: - "IRS ON DC" warning horn sounds 20s after system 2 fails (A/C on ground only) Note 1: When MSSs are set to OFF and only DC power is ON, on EFIS displays: - ALT flags in view - MASI SPD flags in view - "TAS" and dashes appear - TAS indication on FMC progress page displays 100 knots* - TAT indication on ENGINE DISPLAY reads normal* Note 2: F/O DC power is lost after 5 min.





* When both MSS L and R are set to OFF, TAS indications on FMC progress page and TAT indications on ENGINE DISPLAY disappear.

Malfunction Check

1. Select TAKEOFF B via ATM REPOSITIONS page. Turn the MSS L and R to NAV and FAST ALIGN the IRSs via the IOS. Ensure Flight Freeze is OFF. 2. Insert the system 1 malfunction. (a) MSU L ON DC lt illuminates __ __ __ (b) Master caution illuminate __ __ __ annunciators and IRS system annunciator (c) Ground crew call horn sounds after 20s __ __ __ 3. Turn the MSS L to OFF. (a) Capt air data invalid __ __ __ parameters 4. Remove the malfunction. Turn the MSS L to NAV and FAST ALIGN the IRSs via the IOS. 5. Insert the system 2 malfunction and start the stopwatch. 6. From 0 - 5 minutes: (a) MSU R ON DC lt illuminates __ __ __ (b) Master caution illuminate __ __ __ annunciators and IRS system annunciator (c) Ground crew call horn sounds after 20s __ __ __ Turn the MSS R to OFF. (d) F/O air data invalid __ __ __ parameters Turn the MSS R to NAV and FAST ALIGN the IRSs via the IOS.





(e) F/O air data valid __ __ __ parameters 7. After 5 minutes: (a) Right ADIRU fails __ __ __ (b) MSU R ON DC lt extinguishes __ __ __ (c) Ground crew call horn silences __ __ __ (d) F/O air data invalid __ __ __ (e) F/O IRS parameters invalid __ __ __ 8. Remove the malfunction.





ATA 123Hidden123

34I.7 ADIRU DC FAIL


Failure Description

ADIRU DC voltage drops below the normal operation level triggering DC FAIL annunciation and continues to drop below the threshold resulting in a loss of DC power.


FLIGHT DECK EFFECTS: -------------------- System 1 failure: On the MSU: - DC FAIL annunciator illuminates for L system On Master Caution panel: - IRS system annunciator illuminates - Master Caution lts illuminate On ISFD*: - HDG flag in view 11s after ADIRU 1 loses power System 2 failure: On the MSU: - DC FAIL annunciator illuminates for R system On Master Caution panel: - IRS system annunciator illuminates - Master Caution lts illuminate On ISFD*: - HDG flag in view 11s after ADIRU 1 loses power Note: After 30s, ADIRU DC power lost * Applicable only to simulators with an ISFD installed.

Malfunction Check





1. Select TAKEOFF B via ATM REPOSITIONS page. Pull the ADIRU LEFT AC CB (P18-1/E7) and ADIRU RIGHT AC CB (P6-1/C14) and ensure the L and R ON DC annunciators illuminate. 2. Insert the CAPT malfunction. (a) MSU L DC FAIL lt illuminates __ __ __ __ __ __ (b) Master caution illuminate __ __ __ annunciators and IRS __ __ __ system annunciator After 30s: (c) MSU L and ISDU L inoperative __ __ __ __ __ __ On the EFIS displays and the MCDU: (d) Data from ADIRU L lost __ __ __ __ __ __ 3. Remove the malfunction. 4. Repeat checks 2 and 3 for the F/O malfunction. Reset the ADIRU LEFT and RIGHT AC CBs.

Boeing 737-800 FFS Standard Product Specification – Addendum 1 ATA 34N - GPS List of Malfunctions




ATA 34N - GPS

34N.1 GPS FAIL - BOTH SYSTEMS


Failure Description

Dual GPS failure.


FLIGHT DECK EFFECTS: ------------------- On the Master Caution panel: - IRS system annunciator illuminates On the MSU: - GPS FAULT annunciator illuminates On the MCDU: - On FMS POS SHIFT page, GPS L and R position displays are blank - On FMS SENSOR STATUS page, MMR L and R FAIL messages appear

Malfunction Check

1. Select TAKEOFF B via ATM REPOSITIONS page. 2. Ensure that both GPSs are in NAV mode and the IRSs are fully aligned. 3. Insert the malfunction. (a) Effects as above __ __ __ 4. Remove the malfunction.

Boeing 737-800 FFS Standard Product Specification – Addendum 1 ATA 34W - Weather Radar List of Malfunctions




ATA 34W - Weather Radar

34W.1 WXR R/T FAIL


Failure Description

Transceiver failure.


FLIGHT DECK EFFECTS: ------------------- - Weather returns removed - WXR FAIL failure message generated - WXR FAIL RT failure message generated during TEST mode

Malfunction Check

1. Select AIR WORK FL200 via ATM REPOSITIONS page. 2. Select and activate a weather system via the IOS. 3. Select WXCP mode to WX. Adjust the WXCP tilt and the EFIS ranges so that radar returns are seen on both EHSIs. 4. Insert malfunction and observe on both EHSIs. (a) Radar returns disappear __ __ __ (b) WXR appears at mid left __ __ __ FAIL side (c) WXR appears when in TEST mode __ __ __ FAIL RT 5. Remove malfunction and observe on both EHSIs. (a) Radar returns reappear __ __ __ (b) Failure message disappears __ __ __

Boeing 737-800 FFS Standard Product Specification – Addendum 1 ATA 36 - Pneumatics List of Malfunctions




ATA 36 - Pneumatics

36.1 WING BODY OVERHEAT - LEAD EDGE LEAK


Failure Description

Pneumatic leak in the wing leading edge (loose pneumatic duct clamp in the wing leading edge).


FLIGHT DECK EFFECTS: ------------------- - WING-BODY OVERHEAT lt illuminates - MASTER CAUTION lts illuminate - AIR COND annunciator illuminates - Duct Pressure indicator decreases - Failure is reset within 60s when the affected manifold duct is isolated and depressurized

Malfunction Check

1. Select TAKEOFF B via ATM REPOSITIONS page. 2. Insert the LEFT malfunction. (a) Effects as above __ __ __ __ __ __ __ __ __ 3. Remove the malfunction. Select TEMP RESET via the IOS. (a) Left WING BODY extinguishes __ __ __ OVERHEAT lt __ __ __ __ __ __ 4. Repeat checks 2 and 3 for the RIGHT and APU malfunctions.





ATA 123Hidden123

36.2 APU BLEED VALVE FAILS IN POS


Failure Description

APU bleed valve fails in the current position.


FLIGHT DECK EFFECTS: ------------------- - Duct pressure indicator remains stable when APU BLEED sw is selected to OFF or ON

Malfunction Check

1. Select APU via ATM REPOSITIONS page. Position both engine 1 and 2 BLEED sws to OFF. Ensure that left duct presure is zero psig. 2. Insert malfunction. Position APU BLEED sw to ON. (a) Left pneumatic duct no change __ __ __ pressure indicator 3. Remove malfunction. (a) Left pneumatic duct increases __ __ __ pressure indicator 4. Insert malfunction. Position APU BLEED sw to OFF. (a) Left pneumatic duct no change __ __ __ pressure indicator 5. Remove malfunction. (a) Left pneumatic duct decreases to zero __ __ __





pressure indicator





ATA 123Hidden123

36.3 BLEED TRIP OFF


Failure Description

Engine Bleed Air Overtemperature switch fails closed.


FLIGHT DECK EFFECTS: ------------------- - BLEED TRIP OFF lt illuminates - MASTER CAUTION lts illuminate - AIR COND annunciator lt illuminates - Failure remains when TRIP RESET switch is depressed - Related duct pressure indicator decreases to 0 psi

Malfunction Check

1. Select TAKEOFF B via ATM REPOSITIONS page. Position ISOLATION VALVE sw to CLOSE. 2. Insert LEFT malfunction. (a) Effects as above __ __ __ __ __ __ 3. Press TRIP RESET sw. (a) Effects as above __ __ __ __ __ __ 4. Remove malfunction. Press TRIP RESET sw. (a) Effects failure is cleared __ __ __ __ __ __ 5. Repeat checks 2 to 4 for RIGHT malfunction.





ATA 123Hidden123

36.4 BLEED TRIP OFF - RESETTABLE


Failure Description

Temporary malfunction of the Engine Bleed Air Overtemperature switch which detects a false overheat.


FLIGHT DECK EFFECTS: ------------------- - BLEED TRIP OFF lt illuminates - MASTER CAUTION lts illuminate - AIR COND annunciator lt illuminates - Failure is reset when TRIP RESET switch is depressed - Duct pressure indicator decreases to 0 psi

Malfunction Check

1. Select TAKEOFF B via ATM REPOSITIONS page. 2. Insert LEFT malfunction. (a) Effects as above __ __ __ __ __ __ 3. Press TRIP RESET sw. (a) Effects malfunction clears __ __ __ __ __ __ 4. Repeat checks 2 and 3 for RIGHT malfunction.





ATA 123Hidden123

36.5 PRSOV VLV FAILS IN POS


Failure Description

Mechanical failure. Pressure regulator and shutoff valve fails in the current position.


FLIGHT DECK EFFECTS: ------------------- - Duct pressure indicator remains stable when BLEED sw is selected to OFF or ON

Malfunction Check

1. Select TAKEOFF B via ATM REPOSITIONS page. Position Engine 1 and 2 BLEED sws to OFF. Position ISOLATION VALVE sw to CLOSE. 2. When both pneumatic duct pressure indicators are at zero, inser LEFT malfunction. Position left engine BLEED sw to ON. (a) Left pneumatic duct no change __ __ __ pressure indicator __ __ __ 3. Remove malfunction. (a) Left pneumatic duct increases to normal value __ __ __ pressure indicator __ __ __ 4. Insert LEFT malfunction. (a) Left pneumatic duct no change __ __ __ pressure indicator __ __ __ 5. Position left engine BLEED sw to OFF. (a) Left pneumatic duct no change __ __ __ pressure indicator __ __ __





6. Remove malfunction. (a) Left pneumatic duct decreases to zero __ __ __ pressure indicator __ __ __ 7. Repeat checks 2 to 6 RIGHT malfunction.





ATA 123Hidden123

36.6 PRECOOLER CONTROL VALVE FAILS CLOSED


Failure Description

The precooler control valve fails closed.


FLIGHT DECK EFFECTS: ------------------- If the thrust lever is advanced rapidly and an overheat is detected downstream of the PRSOV: - Duct pressure indicator decreases to 0 psi - BLEED TRIP OFF lt illuminates - MASTER CAUTION lts illuminate - AIR COND annunciator lt illuminates

Malfunction Check

1. Select TAKEOFF B via ATM REPOSITIONS page. 2. Insert ENG 1 malfunction. Advance throttles. (a) Effects as above __ __ __ __ __ __ 3. Remove malfunction and select System Reset. 4. Repeat checks 2 and 3 for ENG 2 malfunction.





ATA 123Hidden123

36.7 HP VALVE FAILS OPEN


Failure Description

High stage valve fails in fully open position.


FLIGHT DECK EFFECTS: ------------------- At high engine power setting and low altitude, overpressure condition might be detected in case pressure at PRSOV inlet exceeds 170/220 psi (-700/-800 configurations): - BLEED TRIP OFF lt illuminates - MASTER CAUTION lts illuminate - AIR COND annunicator lt illuminates - Failure is reset when TRIP RESET sw is depressed (after 30s) - Duct pressure indicator decreases to 0 psi

Malfunction Check

1. Select TAKEOFF B via ATM REPOSITIONS page. Ensure both throttles are at idle. 2. Insert ENG 1 malfunction. (a) Left pneumatic duct no change __ __ __ pressure indicator __ __ __ 3. Advance left throttle to high power setting. (a) Effects as above __ __ __ __ __ __ 4. Remove malfunction. Wait at least 30s for duct to depressurize. Press TRIP RESET sw. (a) LH BLEED TRIP OFF extinguishes __ __ __ lt __ __ __





5. Repeat checks 2 to 4 for ENG 2 malfunction.





ATA 123Hidden123

36.8 HP VALVE FAILS CLOSED


Failure Description

High stage valve fails in the closed position.


FLIGHT DECK EFFECTS: ------------------- At idle engine power setting: - DUCT PRESSURE indicator shows a lower value

Malfunction Check

1. Select TAKEOFF B via ATM REPOSITIONS page. Ensure PACK sws are OFF and ISOLATION VALVE sw is at CLOSE. (a) Left & right show the same value __ __ __ pneumatic duct __ __ __ indicators 2. Insert LEFT malfunction. (a) Left pneumatic duct decreases __ __ __ indicator __ __ __ (b) Right pneumatic duct no change __ __ __ indicator __ __ __ 3. Remove malfunction. (a) Left pneumatic duct increases to original __ __ __ indicator value __ __ __ (b) Right pneumatic duct no change __ __ __ indicator __ __ __ 4. Repeat checks 2 and 3 for RIGHT malfunction.





ATA 123Hidden123

36.9 ISOLATION VALVE FAILS CLOSED


Failure Description

Bleed air isolation valve fails in closed position.


FLIGHT DECK EFFECTS: ------------------- - Duct pressure indicator does not respond normally when crossbleed is used - Engine crossbleed start is impossible

Malfunction Check

1. Select TAKEOFF B via ATM REPOSITIONS page. Position Engine 2 BLEED sw to OFF. Ensure that ISOLATION VALVE sw is at CLOSE position. (a) Right pneumatic duct decreases __ __ __ pressure indicator 2. Insert malfunction. Position ISOLATION VALVE sw to OPEN. (a) Right pneumatic duct no change __ __ __ pressure indicator 3. Remove malfunction. (a) Right pneumatic duct similar to left duct __ __ __ pressure indicator pressure indicator





ATA 123Hidden123

36.10 ZONE TEMP - RESETTABLE (ALSO VIA IOS)

CDB Label: TF2161061 FD TF2161062 F-CAB TF2161063 A-CAB

Failure Description

Temporary malfunction of the Cabin Duct Overheat switch which detects a false overheat.


- ZONE TEMP lt illuminates - MASTER CAUTION lts illuminate - AIR COND annunciator illuminates - Trim air modulating valve is driven to close when overheat switch is failed - Valve may be re-opened and ZONE TEMP lt will extinguish after DUCT COOLS and TRIP RESET sw is pushed (malfunction is automatically deselected)

Malfunction Check

1. Select TAKEOFF B via ATM REPOSITIONS page. 2. Insert the FD malfunction. (a) Effects as above __ __ __ __ __ __ __ __ __ 3. Push the TRIP RESET button. (a) Effects as above __ __ __ __ __ __ __ __ __ 4. Remove the malfunction. 5. Repeat checks 2 to 4 for the F-CAB and A-CAB malfunctions.

Boeing 737-800 FFS Standard Product Specification – Addendum 1 ATA 49 - APU List of Malfunctions




ATA 49 - APU

49.1 APU START SWITCH - OFF INOP


Failure Description

Defective switch.


FLIGHT DECK EFFECTS: ------------------- - APU switch positioned at OFF does not shut down APU - APU can be shut down by fire handle, by selecting BAT sw to OFF or by pulling APU CONT CB (P6-4/A14) C33

Malfunction Check

1. Select GRD PWR via the IOS ATM REPOSITIONS page. Select APU QUICKSTART via IOS. 2. Insert the malfunction. (a) Effects as above __ __ __ 3. Remove the malfunction.





ATA 123Hidden123

49.2 APU HOT START


Failure Description

FCU failure that causes incorrect motion of the metering valve.


FLIGHT DECK EFFECTS: ------------------- - APU shuts down automatically and APU FAULT lt illuminates when exhaust gas overtemperature is detected by the ECU - APU FAULT lt illuminates

Malfunction Check

1. Select GRD PWR via the IOS ATM REPOSITIONS page. 2. Insert the malfunction. 3. Start the APU. (a) Effects as above __ __ __ 4. Remove the malfunction.





ATA 123Hidden123

49.3 HUNG START


Failure Description

Faulty Fuel Control Unit.


FLIGHT DECK EFFECTS: ------------------- - APU ignites, but EGT remains considerably low - APU shuts down and FAULT lt illuminates

Malfunction Check

1. Select GRD PWR via the IOS ATM REPOSITIONS page. 2. Insert the malfunction. 3. Try to start the APU. (a) Effects as above __ __ __ 4. Remove the malfunction.





ATA 123Hidden123

49.4 OVERSPEED


Failure Description

APU exceeds overspeed limit due to a fuel control torque motor stuck open.


FLIGHT DECK EFFECTS: ------------------- If malfunction is inserted while APU is running: - APU accelerates past overspeed threshold and shuts down due to overspeed protection - APU OVERSPEED lt illuminates If malfunction is inserted before APU is started: - APU accelerates and shuts down due to overtemperature protection - APU FAULT lt illuminates

Malfunction Check






ATA 123Hidden123

49.5 STARTER MOTOR FAIL


Failure Description

APU starter motor defective.


FLIGHT DECK EFFECTS: ------------------- If malfunction is inserted before APU master switch start: - APU does not start 20s after entering in the ECU starting mode on the APU Maintenance page: - APU shuts down - APU FAULT lt illuminates

Malfunction Check

1. Select GRD PWR via the IOS ATM REPOSITIONS page. 2. Insert the malfunction. 3. Start the APU. (a) Effects as above __ __ __ 4. Remove the malfunction.





ATA 123Hidden123

49.6 APU LOW AIR PRESSURE


Failure Description

APU Inlet Guide Vane is defective.


FLIGHT DECK EFFECTS: ------------------- - APU IGV cannot increase above 30degrees - APU supplies low pressure bleed air only

Malfunction Check

1. Select APU via the IOS ATM REPOSITIONS page. 2. Insert the malfunction. 3. Select the APU bleed air switch to ON. (a) Effects as above __ __ __ 4. Remove the malfunction.





ATA 123Hidden123

49.7 HIGH OIL TEMPERATURE


Failure Description

Oil temperature exceeds limit (290degreesF).


FLIGHT DECK EFFECTS: ------------------- 10s after the oil temperature exceeds 312degreesF: - APU shuts down - FAULT lt illuminates

Malfunction Check






ATA 123Hidden123

49.8 LOW OIL PRESSURE


Failure Description

Oil pressure decreases to operating minimum.


FLIGHT DECK EFFECTS: ------------------- - LOW OIL PRESSURE lt illuminates when oil pressure drops below 30 psi - 20s after oil pressure drops below 30 psi, APU shuts down automatically

Malfunction Check


Boeing 737-800 FFS Standard Product Specification – Addendum 1 ATA 52 - Doors List of Malfunctions




ATA 52 - Doors

52.1 CARGO DOOR OPEN

CDB Label: TF5271001 AFT

Failure Description

AFT(FWD) cargo door opens.


FLIGHT DECK EFFECTS: ------------------- On ground: - AFT (FWD) CARGO lt illuminates - MASTER CAUTION lts illuminate - DOORS annunciator lt illuminates In flight: - AFT (FWD) CARGO lt illuminates - MASTER CAUTION lts illuminate - DOOR annunciator lt illuminates - Outflow VALVE indicator goes fully closed - CABIN CLIMB rate indicator show maximum climb rate - CABIN ALT indicator increases to A/C altitude - DIFF PRESS indicator decreases towards 0 psi - Altitude warning horn sounds for CABIN ALT above 10,000 ft Note: Make sure that the CPC panel is inserted before you insert the malfunction

Malfunction Check

1. Select AIRWORK FL200 via ATM REPOSITIONS page. 2. Insert AFT malfunction. (a) Effects as above __ __ __ __ __ __ 3. Remove malfunction. 4. Repeat checks 2 and 3 for the FWD malfunction.





ATA 123Hidden123

52.2 DOOR SYSTEM ANNUNCIATOR LT ON (SW)

CDB Label: TF5271011 F ENT TF5271012 A ENT TF5271013 F SRV TF5271014 A SRV

Failure Description

False door warning due to a door sensor failure.


FLIGHT DECK EFFECTS: ------------------- - Door lt on the Door Warning Panel illuminates - MASTER CAUTION lts illuminate - DOORS annunciator lt illuminates - Aircraft remains pressurized if failure occurs in flight

Malfunction Check

1. Select AIRWORK FL200 via ATM REPOSITIONS page. 2. Insert FWD ENTRY malfunction. (a) Effects as above __ __ __ __ __ __ __ __ __ __ __ __ 3. Remove malfunction. 4. Repeat checks 1 to 3 for AFT ENTRY, FWD SERV and AFT SERV malfunctions.





ATA 123Hidden123

52.3 CRG/EQUIP DOOR SYSTEM ANNUNCIATOR LT ON (SW)

CDB Label: TF5271015 F CRG TF5271016 A CRG TF5271017 EQUIP

Failure Description

False door warning due to a door sensor failure.


FLIGHT DECK EFFECTS: ------------------- - Door lt on the Door Warning Panel illuminates - MASTER CAUTION lts illuminate - DOORS annunciator lt illuminates - Aircraft remains pressurized if failure occurs in flight

Malfunction Check

1. Select AIRWORK FL200 via ATM REPOSITIONS page. 2. Insert the F CRG malfunction. (a) Effects as above __ __ __ __ __ __ __ __ __ 3. Remove the malfunction. 4. Repeat checks 2 and 3 for the A CRG and EQUIP malfunctions.

Boeing 737-800 FFS Standard Product Specification – Addendum 1 ATA 71 - Engine - Failures List of Malfunctions




ATA 71 - Engine - Failures

71.1 ENGINE TURBINE BLADE FAILURE


Failure Description

Turbine blade failure, a blade detaches from the turbine (LPT).


FLIGHT DECK EFFECTS: ------------------- - A loud bang is heard - EGT rises rapidly - High vibrations at high power settings - Decrease in N1 efficiency (for same N1, higher N2, fuel flow and EGT) - Decrease in thrust

Malfunction Check

1. Select TAKEOFF B via ATM REPOSITIONS page. 2. Advance throttles to obtain take off power. 3. Insert ENG 1 malfunction. (a) Effects as above __ __ __ __ __ __ 4. Remove malfunction. 5. Repeat checks 2, 3 and 4 for ENG 2 malfunction.





ATA 123Hidden123

71.2 ENGINE FLAMEOUT (AUTO-RESTARTABLE)


Failure Description

Engine flames out due to temporary bad air conditions (heavy rain for example).


FLIGHT DECK EFFECTS: ------------------- - Engine flames out - ENG FAIL message appears on the EGT dial if N2 goes below 50% - Engine spools down normally - Engine auto-ignition system comes into action by turning igniters on - Engine will relight unless N2 drops below 50% before engine has relight - At 50% or after 30s, auto-ignition turns igniters off

Malfunction Check

1. Select 20 000 ft and 300 kts via POSITION SET page. 2. Insert ENG 1 malfunction. (a) Effects as above (auto-ignition __ __ __ relight engine) __ __ __ 3. Remove malfunction. 4. Repeat checks 2 and 3 for ENG 2 malfunction.





ATA 123Hidden123

71.3 ENGINE FLAMEOUT (NO RESTART POSSIBLE)


Failure Description

Engine flames out due to Hydro-Mechanical Unit (HMU) failure causing fuel supply to the engine to be interrupted.


FLIGHT DECK EFFECTS: ------------------- - Engine flames out - Engine spools down normally - ENG FAIL message appears on the EGT dial when N2 goes below 50% - Engine cannot be restarted normally - Auto-ignition system is not successful in restarting the engine

Malfunction Check

1. Select AIR WORK FL200 via ATM REPOSITIONS page. 2. Insert ENG 1 malfunction. (a) Effects as above __ __ __ __ __ __ 3. Initiate Start Procedure. 4. After Fuel Lever has been moved to IDLE. (a) Engine EGT does not increase; start __ __ __ is not completed __ __ __ 5. Remove malfunction and quickstart engine 6. Repeat checks 2 to 5 for ENG 2 malfunction.





ATA 123Hidden123

71.4 ENGINE SUDDEN SEIZURE


Failure Description

Engine N1 rotor seizes causing the engine to flame out.


FLIGHT DECK EFFECTS: ------------------- - Engine vibrations increase abruptly, then decrease - Engine N1 indication drops instantly to 0 and a loud bang is heard - Engine thrust decreases abruptly - ENG FAIL message appears on the EGT dial if N2 goes below 50% and while EEC is energized - Engine N2 drops and trys to recover for a few seconds, then starts dropping while engine flames out - Other engine parameters follow - If A/C is on ground, ENG CONTROL, MASTER CAUTION and ENG annunciator lights illuminate - Once the EEC is unpowered (i.e. fuel lever placed to CUTOFF and N2 is less than 12%), if N2 remains over 50% for at least 6s after N1 drops below 5%, then SPEED TRIM FAIL amber discrete light illuminates after a delay, with master caution warning - If the SPEED TRIM FAIL lt is illuminated then the autoflight modes LEVEL CHANGE and VERTICAL SPEED will not engage on the affected side, and if engaged become biased out of view

Malfunction Check

1. Select TAKEOFF A via ATM REPOSITIONS page. 2. Insert ENG 1 malfunction. (a) Effects as above __ __ __ __ __ __ 3. Perform Maintenance procedure (if applicable). 4. Remove malfunction and quickstart engine. 5. Repeat checks 1 to 4 for ENG 2 malfunction.





ATA 123Hidden123

71.5 ENG STALL/SURGE RECOVERABLE (IF N1 < 70%)


Failure Description

Engine stalls/surges if N1 is above 70%. Effects are repeated randomly as long as the engine N1 is above 70%.


FLIGHT DECK EFFECTS: ------------------- - Loud bang is heard while the engine RPMs drop significantly - Engine recovers temporarily and stalls again (randomly) if engine power is not reduced to a power setting where N1 is below 70% - Loss of thrust during the RPMs drops - EGT increases at each drop and will reach overheat conditions if engine power setting is not reduced

Malfunction Check

1. Select AIR WORK FL200 via ATM REPOSITIONS page. 2. Advance throttles to reach approximately 85% N1. 3. Insert ENG 1 malfunction. (a) Effects as above __ __ __ __ __ __ 4. Remove malfunction. 5. Repeat checks 2 to 4 for ENG 2 malfunction.





ATA 123Hidden123

71.6 ENGINE STALL/SURGE NOT RECOVERABLE


Failure Description

Engine stalls/surges.


FLIGHT DECK EFFECTS: ------------------- - Loud bang is heard while the engine RPMs drop significantly - Engine recovers temporarily and stalls again (randomly) - Loss of thrust during the RPMs drop - EGT increases at each drop and will reach overheat conditions - If N2 is below 50% and EGT reaches starting limit, EEC closes the engine FMV and engine shuts down; this is the Rollback Overtemperature Protection, only active on-ground

Malfunction Check

1. Select AIR WORK FL200 via ATM REPOSITIONS page. 2. Insert ENG 1 malfunction. (a) Effects as above __ __ __ __ __ __ 3. Remove malfunction. 4. Repeat checks 2 and 3 for ENG 2 malfunction. 5. Select TAKEOFF A via ATM REPOSITIONS page. 6. Repeat checks 2, 3 and 4. (a) Effects as above with Rollback __ __ __ Overtemperature __ __ __ Protection activated





ATA 123Hidden123

71.7 ENGINE FUEL SHUTOFF VALVE FAILURE


Failure Description

Engine Fuel HPSOV fails in position.


FLIGHT DECK EFFECTS: ------------------- - "ENG VALVE CLOSED" lt (P5) illuminates if commanded position and actual valve position disagree When Fuel Lever is moved to cutoff: - Engine shuts down after a 20-25s delay (this delay is needed to burn fuel contained in fuel lines between closed spar valve and engine) - EEC reset causes fuel flow to oscillate for a few seconds if A/C is on ground (in air status is assumed during EEC reset)

Malfunction Check

1. Select TAKEOFF A via ATM REPOSITIONS page. 2. Insert ENG 1 malfunction. 3. Place ENG 1 Fuel Lever to Cutoff. (a) ENG VALVE CLOSED lt illuminates bright __ __ __ (P5) __ __ __ 4. The spar valve closes, and fuel between spar valve and engine burn. When it has all burned (approx. 24s): (a) Engine parameters spool down __ __ __ __ __ __ (b) ENG VALVE CLOSED lt remains illuminated __ __ __ (P5) bright __ __ __ 5. Remove ENG 1 malfunction. (a) ENG VALVE CLOSED lt dims __ __ __





(P5) __ __ __ 6. Re-insert ENG 1 malfunction. 7. Attempt to start ENG 1. 8. After ENG 1 Fuel Lever has been placed to IDLE: (a) ENG VALVE CLOSED lt illuminates bright __ __ __ (P5) __ __ __ 9. After approx 15s, EEC closes ENG FMV (wet start protection). (a) ENG VALVE CLOSED lt stays illuminated __ __ __ (P5) bright __ __ __ 10. Place ENG 1 Fuel Lever to Cutoff (this inhibits wet start protection signal to close Eng FMV). 11. Repeat checks 2 to 10 for ENG 2 malfunction.





ATA 123Hidden123

71.8 BIRD STRIKE - ENG FAILURE


Failure Description

A bird strike causes a fan blade to be out of balance.


FLIGHT DECK EFFECTS: ------------------- - Ingestion noise is heard - Engine parameters vary suddenly when the bird hits the engine - Fan blade(s) have FOD damage causing engine stall - Engine vibrations are higher than normal

Malfunction Check

1. Select TAKEOFF B via ATM REPOSITIONS page. Remove FLIGHT FREEZE at the end of the reposition. 2. Insert the ENG 1 malfunction and perform a normal takeoff. (a) Effects as above with proper __ __ __ flight effects __ __ __ 3. Stabilize the A/C on ground and remove the malfunction. (a) Effects all indications and __ __ __ engine operation __ __ __ back to normal 4. Repeat checks 2 and 3 for the ENG 2 malfunction.





ATA 123Hidden123

71.9 VOLCANIC ASH

CDB Label: TF71_M_ASH0_L1

Failure Description

Flight through a volcanic ash cloud.


FLIGHT DECK EFFECTS: ------------------- - Upon malfunction insertion in cruise configuration (above 19,000 feet), the A/C enters a continuous volcanic ash cloud Upon entering dust cloud: - Loss of visibility through windows (dependent on device specifications) Approximately 1 or 2 min after entering the cloud: - Both engines efficiency will decrease The following effects will occur within approximately 2 mins: - Engine 1 will begin to roll back towards idle, with EGT increasing, no throttle control and will then flame out after EGT has peaked above the red limit - Engine 2 will begin to roll back towards idle, with EGT increasing, no throttle control and will eventually hang-up below idle NOTES: - At any time, shutting down engines, results in a slow EGT decay towards ambient - Engine 1 relight attempts above FL190 are unsuccessful - Engine 2 relight attempts result in engine hanging-up at or below idle, EGT higher than normal and no throttle control

Malfunction Check

1. Select AIR WORK FL370 or higher via ATM REPOSITIONS page. 2. Insert the malfunction. (a) Visibility effects as above __ __ __ (b) Engines effects as above __ __ __





3. Remove the malfunction and perform a SYSTEM RESET via the IOS. 4. Perform an ENGINE QUICKSTART via the IOS.





ATA 123Hidden123

71.10 ENGINE SEPARATION


Failure Description

Engine separates with appropriate indications and malfunctions.


FLIGHT DECK EFFECTS: ------------------- - Engine becomes detached from the wing with associated loss of thrust and asymmetric performance - Engine indications reflect loss of signal - Hydraulic, electrical, fuel and pneumatic systems behave appropriately

Malfunction Check

1. Select AIR WORK FL200 via ATM REPOSITIONS page. 2. Insert the ENG 1 malfunction. (a) Effects as above __ __ __ __ __ __ 3. Set the ENG 1 FUEL LEVER to CUTOFF. 4. Attempt to restart ENG 1. (a) Restart unsuccessful __ __ __ __ __ __ 5. Remove the malfunction and perform a SYSTEM RESET via the IOS. 6. Perform an ENGINE QUICKSTART via the IOS. 7. Repeat checks 2 to 6 for the ENG 2 malfunction.

Boeing 737-800 FFS Standard Product Specification – Addendum 1 ATA 73 - Engine - Faults List of Malfunctions




ATA 73 - Engine - Faults

73.1 ENGINE FUEL FILTER BYPASS


Failure Description

Fuel filter gets clogged and pressure in the circuit increases.


FLIGHT DECK EFFECTS: ------------------- If engine power setting is increased near takeoff power: - FUEL FILTER BYPASS lt, MASTER CAUTION and FUEL annunciator lts illuminate after 60s (internal EEC logic)

Malfunction Check

1. Select TAKEOFF B via ATM REPOSITIONS page. 2. Insert the ENG 1 malfunction. (a) Effects none __ __ __ __ __ __ 3. Initiate a takeoff. (a) Effects as above __ __ __ __ __ __ 4. Remove the malfunction. 5. Repeat checks 2 to 4 for the ENG 2 malfunction.





ATA 123Hidden123

73.2 FADEC FAILED IN ALTERNATE MODE


Failure Description

Engine reverts to the soft ALTN mode of operation due to an invalid PT2 input signal.


FLIGHT DECK EFFECTS: ------------------- - Engine EEC "ALTN" lt illuminates after a delay of 15s - MASTER CAUTION lts (2) and ENG annunciator lt illuminates - Engine parameters vary as flight condions change because N1 command is based on a synthesized mach number NOTE: Engine will revert to HARD ALTN mode if throttle is pulled back to idle. In this case, the synthesized mach number is estimated in a different way

Malfunction Check

1. Select AIR WORK FL200 via ATM REPOSITIONS page. 2. Insert ENG 1 malfunction. (a) Effects as above __ __ __ __ __ __ 3. Perform Maintenance procedure (if applicable). 4. Remove malfunction. 5. Repeat checks 1 to 4 for ENG 2 malfunction. Maintenance: (if applicable) ----------- 1. Reposition on ground and shut down engine. 2. When N2 has spooled below 5%, select ENGINE 1 BITE through the MAINT selection on the FMC CDU.





(a) Effects as above __ __ __ __ __ __





ATA 123Hidden123

73.3 VBVS OFF SCHEDULE


Failure Description

VBV positions do not follow the EEC commanded positions.


FLIGHT DECK EFFECTS: ------------------- - At maximum throttle position, N1 is lower (approx. 10% if A/C is on ground), EGT is higher and fuel flow is lower than normal maximum power values - If A/C is on ground, ENG CONTROL, MASTER CAUTION and ENG annunciator lights illuminate

Malfunction Check

1. Select TAKEOFF B via ATM REPOSITIONS page. 2. Insert ENG 1 malfunction and initiate takeoff. (a) Effects as above __ __ __ __ __ __ 3. Perform Maintenance procedure (if applicable). 4. Remove malfunction. 5. Repeat checks 1 to 4 for ENG 2 malfunction. Maintenance: (if applicable) ----------- 1. Reposition on ground and shut down engine. 2. When N2 has spooled below 5%, select ENGINE 1 BITE through the MAINT selection on the FMC CDU. (a) Effects as above __ __ __ __ __ __





ATA 123Hidden123

73.4 HIGH ENGINE VIBRATIONS WITH MOTION EFFECTS


Failure Description

Engine vibrations increase significantly enough to cause an AVM alert (if applicable).


FLIGHT DECK EFFECTS: ------------------- - Engine vibration higher than normal, if throttles are advanced, engine vibrations increase above 4.0 units - Vibrations are felt through motion system* * Dependent on device specifications

Malfunction Check

1. Select TAKEOFF A via ATM REPOSITIONS page. 2. Insert the ENG 1 malfunction. (a) Effects as above __ __ __ __ __ __ 3. Remove the malfunction. 4. Repeat checks 2 and 3 for the ENG 2 malfunction.





ATA 123Hidden123

73.5 EEC DATA BUS TO BOTH DEUS FAIL

CDB Label: TF7700011 1-A TF7700013 2-A TF7700012 1-B TF7700014 2-B

Failure Description

EEC data bus to both DEUs fail.


FLIGHT DECK EFFECTS: ------------------- - Auto-throttle is not working for the affected side If both channel buses are failed: - All engine indications except N1, N2, oil quantity and engine vibration on Common Display System blank - If A/C is on ground, ENG CONTROL, MASTER CAUTION and ENG annunciator light illuminate

Malfunction Check

1. Select TAKE OFF A via ATM REPOSITIONS page. 2. Insert ENG 1-A malfunction. (a) Effects none __ __ __ __ __ __ 3. Perform Maintenance Procedure (if applicable) 4. Insert ENG 1-B malfunction. (a) Engine indications, blank __ __ __ except N1, N2, oil __ __ __ quantity and engine vibration 5. Remove both malfunctions. Perform a SYSTEM RESET. 6. Repeat checks 2 to 5 for ENG 2 malfunction.





Maintenance: ----------- 1. Reposition on ground and shut down engine. 2. When N2 has spooled below %5, select ENGINE 1 BITE through the MAINT selection on the FMC CDU. (a) Effects as above __ __ __ __ __ __





ATA 123Hidden123

73.6 THRUST REVERSER UNLOCKED (WITH BUFFET)


Failure Description

Engine Thrust Reverser sleeves unlock and open slightly, causing aerodynamic buffets. Auto-restow occurs and partially closes T/R sleeves. Sleeves become stuck when 15% opened (auto-restow maintains sleeve position, but a mechanical failure prevents any further stowing).


FLIGHT DECK EFFECTS: ------------------- - EEC limits power to idle - Auto-restow procedure occurs (no Flight Deck Effects) - "REV" indication on CDS appears (amber) - "REVERSER" fault lt illuminates on aft overhead and remains illuminated until auto-restow procedure stops - MASTER CAUTION lt and ENG annunciator lt illuminate if "REVERSER" lt remains illuminated for more than 13s

Malfunction Check

1. Select AIR WORK FL200 via ATM REPOSITIONS page. 2. Insert ENG 1 malfunction. (a) Effects as above __ __ __ __ __ __ 3. Remove malfunction. 4. Perform the EAU BITE TEST stow procedure (if applicable). 5. Perform a SYSTEM RESET to stop EAU auto-restow procedure and to clear EAU non-volatile memory. (a) REVERSER lt extinguishes __ __ __ __ __ __ 6. Repeat checks 2 to 5 for ENG 2 malfunction. Maintenance: (if applicable)





----------- 1. Select TAKEOFF A via ATM REPOSITIONS page. 2. Select E3-2 rack and Engine Accessory Unit device via IOS. (a) On EAU front "T/R STOW FAULTS" lt is __ __ __ panel display illuminated __ __ __ 3. Perform EAU BITE procedure. (a) Push and hold T/R All EAU lts illuminate __ __ __ STOW FAULTS push- (test) __ __ __ button After 2s, all EAU lights extinguish except: (b) "L SLEEVE STOW remains illuminated __ __ __ SENSOR" lt __ __ __ (c) "L SLEEVE LOCK remains illuminated __ __ __ SENSOR" lt __ __ __ (d) "R SLEEVE STOW remains illuminated __ __ __ SENSOR" lt __ __ __ (e) "R SLEEVE LOCK remains illuminated __ __ __ SENSOR" lt __ __ __ (f) "HYD ISO VALVE remains illuminated __ __ __ SENSOR" lt __ __ __ (g) "L SLEEVE SYNC remains illuminated __ __ __ LOCK PWR" __ __ __ (h) "R SLEEVE SYNC remains illuminated __ __ __ LOCK PWR" __ __ __ 4. Release T/R STOW FAULTS pushbutton.





ATA 123Hidden123

73.7 T/R SLEEVE LOCK DOES NOT UNLOCK


Failure Description

T/R sleeve lock failure; does not unlock.


FLIGHT DECK EFFECTS: ------------------- In all cases: - T/R affected sleeve will not deploy - "REVERSER" lt on aft overhead panel illuminates 5s after deploy command is given and stays illuminated until EAU non volatile memory is reset - If "REVERSER" lt remains illuminated for more than 13s, MASTER CAUTION lt and ENG annunciator lt illuminate - Reverse interlock not removed If only one sleeve is affected: - After deploy command is given, "REV" indication appears amber for a few seconds, then disappears If both sleeves are affected: - After deploy command is given, "REV" indication will not appear on CDS

Malfunction Check

1. Select TAKEOFF A via ATM REPOSITIONS page. 2. Insert ENG 1-L malfunction. 3. Try to deploy ENG 1 T/R. (a) REVERSER lt illuminates after 5s __ __ __ __ __ __ (b) T/R only right sleeve deploys,__ __ __ thrust lever stopped by __ __ __ reverse interlock (c) REV indication on appears amber then __ __ __





CDS disappears __ __ __ 4. Bring reverse lever back to idle. (a) T/R stows __ __ __ __ __ __ (b) REVERSER lt remains illuminated __ __ __ __ __ __ 5. Perform a SYSTEM RESET to clear EAU non volatile memory. (a) REVERSER lt extinguishes __ __ __ __ __ __ 6. Insert ENG 1-R malfunction and try to deploy reversers. (a) REVERSER lt illuminates after 5s __ __ __ __ __ __ (b) T/R does not deploy __ __ __ __ __ __ 7. Remove malfunctions. (a) T/R deploys __ __ __ __ __ __ (b) REVERSER lt remains illuminated __ __ __ __ __ __ 8. Stow T/R. 9. Perform a TOTAL RESET. (a) REVERSER lt extinguishes __ __ __ __ __ __ 10. Repeat checks 2 to 9 for ENG 2 malfunction.





ATA 123Hidden123

73.8 T/R SLEEVES LOCK SENSORS SENSE "UNLOCKED"


Failure Description

T/R sleeves lock sensors failure; the unlocked state is permanently sensed.


FLIGHT DECK EFFECTS: ------------------- - T/R stows and deploys normally If malfunction is inserted with T/R stowed: - "REVERSER" lt illuminates and remains illuminated until auto-restow procedure is stopped (by deploying and stowing reversers with no faults) If fault occurs when the T/R is deployed: - "REVERSER" lt remains illuminated after T/R is stowed until the EAU non-volatile memory is reset and auto-restow procedure is stopped If "REVERSER" lt remains illuminated for more than 13s: - ENG annunciator and MASTER CAUTION lts illuminate

Malfunction Check

1. Select TAKEOFF A via ATM REPOSITIONS page. 2. Insert ENG 1-L malfunction. (a) REVERSER lt illuminates __ __ __ __ __ __ __ __ __ __ __ __ (b) Engine responds to throttle __ __ __ movements __ __ __ __ __ __ __ __ __ 3. Remove malfunction.





(a) REVERSER lt remains illuminated __ __ __ __ __ __ __ __ __ __ __ __ 4. Perform a TOTAL RESET to clear non-volatile memory and to stop auto-restow procedure. (a) REVERSER lt extinguishes __ __ __ __ __ __ __ __ __ __ __ __ 5. Deploy T/R and insert ENG 1-L malfunction. (a) REVERSER lt remains extinguished __ __ __ __ __ __ __ __ __ __ __ __ 6. Try to stow T/R. (a) T/R stows __ __ __ __ __ __ __ __ __ __ __ __ (b) REVERSER lt illuminates and __ __ __ remains illuminated __ __ __ __ __ __ __ __ __ 7. Remove ENG 1-L malfunction and deploy and stow reversers. (a) REVERSER lt extinguishes __ __ __ __ __ __ __ __ __ __ __ __ 8. Perform a TOTAL RESET to reset the EAU non-volatile memory. 9. Repeat checks 2 to 8 for remaining malfunctions.





ATA 123Hidden123

73.9 ENGINE OIL LOW PRESSURE


Failure Description

Engine oil supply pump failure.


FLIGHT DECK EFFECTS: ------------------- - Engine oil pressure drops to atmospheric pressure due to supply pump failure - If this condition lasts for more than 60s with engines running, permanent damage will result to the engine - LOW OIL PRESS alert appears on CDS - Message blinks for first 10s unless inhibited by the takeoff and landing inhibit - Engine oil temperature slowly rises after oil pressure starts dropping

Malfunction Check

1. Select TAKEOFF A via ATM REPOSITIONS page. 2. Insert ENG 1 malfunction. (a) Effects as above __ __ __ __ __ __ 3. If engine keeps runnings for 60s with 0 oil pressure: (a) Permanent damage N2 is greater for __ __ __ results equivalent N1, Fuel flow __ __ __ is greater and vibrations are higher 4. Remove malfunction. 5. Repeat checks 2 to 4 for ENG 2 malfunction. 6. Perform a TOTAL or SYSTEM RESET.





ATA 123Hidden123

73.10 ENGINE OIL LEAK


Failure Description

Engine oil leaks at a rate of 1 gal/min.


FLIGHT DECK EFFECTS: ------------------- - Engine oil quantity drops slowly to 0 in approximately 1 min - Appropriate oil temperature (rise) and pressure (drop) effects are also present once tank is empty - Once engine oil quantity indicates 0, engine seizes after 60s of operation - LOW OIL PRESS alert appears on Engine Display when pressure drops - Message blinks for first 10s unless inhibited by the takeoff and landing inhibit

Malfunction Check

1. Select TAKEOFF A via ATM REPOSITIONS page. 2. Insert ENG 1 malfunction. (a) Effects as above __ __ __ __ __ __ 3. Remove malfunction. 4. Repeat checks 2 and 3 for ENG 2 malfunction. 5. Perform a TOTAL or SYSTEM RESET.





ATA 123Hidden123

73.11 OIL FILTER BYPASS


Failure Description

Oil filter gets clogged and pressure across the filter rises above limit, causing the oil flow to bypass the filter.


FLIGHT DECK EFFECTS: ------------------- - OIL FILTER BYPASS message appears on CDS after a delay of 60 seconds - Message blinks for first 10s unless inhibited by the takeoff and landing inhibit

Malfunction Check

1. Select TAKEOFF A via ATM REPOSITIONS page. 2. Insert ENG 1 malfunction. (a) Effects as above __ __ __ __ __ __ 3. Remove malfunction. 4. Repeat checks 2 and 3 for ENG 2 malfunction.





ATA 123Hidden123

73.12 ENGINE OIL HIGH TEMPERATURE


Failure Description

Engine oil temperature rises due to a failure in the fuel/oil heat exchanger. Oil temperature will reach redline limit if engine is not shutdown.


FLIGHT DECK EFFECTS: ------------------- - Engine oil temperature increases to a value above redline limit - Temperature rises more rapidly at high power settings - Oil depletion rate is greater due to high oil temperatures - Drop in engine oil pressure is observed

Malfunction Check

1. Select TAKEOFF A via ATM REPOSITIONS page. 2. Insert ENG 1 malfunction. (a) Effects as above __ __ __ __ __ __ 3. Perform Maintenance procedure (if applicable). 4. Remove malfunction. 5. Repeat checks 2 to 4 for ENG 2 malfunction. Maintenance: (if applicable) ----------- 1. Once oil temperature reaches 175 reposition on ground and shut down engine. 2. When N2 has spooled below 5%, select ENGINE 1 BITE through the MAINT selection on the FMC CDU. (a) Effects as above __ __ __ __ __ __





ATA 123Hidden123

73.13 FADEC FAULT


Failure Description

Both EEC channels fail.


FLIGHT DECK EFFECTS: ------------------- - Fuel flow, oil pressure, oil temperature and EGT indications on CDS blank - Fuel metering valve goes to minimum position, causing the engine to stabilize below idle and to eventually flameout - Engine does not respond to throttle movements - ENG FAIL message appears on EGT dial if both engines were at or above idle at any time prior to malfunction insertion - ENG FAIL message disappears if N2 > 50%

Malfunction Check

1. Select TAKEOFF A via ATM REPOSITIONS page. 2. Insert the ENG 1 malfunction. (a) Effects as above __ __ __ __ __ __ 3. Remove the malfunction and perform ENGINE QUICKSTART via the IOS. 4. Repeat checks 2 and 3 for the ENG 2 malfunction.





ATA 123Hidden123

73.14 ENGINE IDLE DISAGREE


Failure Description

Engine idle speed incorrect for phase of flight.


FLIGHT DECK EFFECTS: ------------------- During flight phase only: If engine is originally in high idle: - it decelerates to low idle If engine is originally in low idle: - it accelerates to high idle - Engine will latch in wrong idle state, whatever the position of flaps and anti-ice sws.

Malfunction Check

1. Select 6 NM via ATM REPOSITIONS page (High Idle). 2. Move the ENG 1 throttle lever to IDLE and let the engine stabilize. 3. Insert the ENG 1 malfunction. (a) Effects as above __ __ __ __ __ __ 4. Remove the malfunction. 5. Repeat checks 2 to 4 for the ENG 2 malfunction. 6. Select AIR WORK FL100 via ATM REPOSITIONS page (Low Idle). 7. Move the ENG 1 throttle lever to IDLE and let the engine stabilize. 8. Insert the ENG 1 malfunction.





(a) Effects as above __ __ __ __ __ __ 9. Remove the malfunction. 10. Repeat checks 7 to 9 for the ENG 2 malfunction.





ATA 123Hidden123

73.15 EGT OVERLIMITS (ABOVE 950 DEG C)


Failure Description

Engine experiences abnormally high EGT values exceeding 950 at T/O power.


FLIGHT DECK EFFECTS: ------------------- - EGT readout box, dial, pointer and shading turn red if EGT redline limit of 950 degrees C is exceeded by more than 10 degrees C or by more than 3 degrees C for more than 20s - EGT readout red boxed after shutdown (on ground with both engines off, i.e., fuel level at cutoff and N2 < 12%) if EGT redline limit is exceeded by more than 10 degrees C or by more than 3 degrees C for more than 20s

Malfunction Check

1. Select TAKEOFF A via ATM REPOSITIONS page. 2. Insert the ENG 1 malfunction. 3. Using the brakes, apply takeoff thrust. (a) Effects as above __ __ __ __ __ __ 4. Remove the malfunction. 5. Repeat checks 2 to 4 for the ENG 2 malfunction.

Boeing 737-800 FFS Standard Product Specification – Addendum 1 ATA 80 - Engine - Start Faults List of Malfunctions




ATA 80 - Engine - Start Faults

80.1 ENGINE HOT START


Failure Description

Offset in the fuel metering valve position resulting in a higher than normal fuel flow during an engine start.


FLIGHT DECK EFFECTS: ------------------- - Engine lt up normally, but EGT increases too rapidly and a HOT start is detected - EGT digital readout starts flashing; flashing stops if START lever is placed to CUTOFF - If start is not aborted, EGT reaches start limit (725 deg C) and EEC shuts down the engine (on ground only) - If engine exceedance has occured, EGT readout box is displayed red - If A/C is on ground, ENG CONTROL, MASTER CAUTION and ENG annunciator lights illuminate

Malfunction Check

1. Select APU via ATM REPOSITIONS page. 2. Insert ENG 1 malfunction. 3. Perform an engine start. (a) Effects as above __ __ __ __ __ __ 4. Turn off engine start switch. 5. Perform Maintenance procedure (if applicable). 6. Remove malfunction. 7. Repeat checks 2 to 6 for ENG 2 malfunction. Maintenance: (if applicable) ----------- 1. Reposition on ground and shut down engine.





2. On the FMC CDU, select MAINT, ENGINE and EXCEEDANCES. (a) Effects as above __ __ __ __ __ __ 3. When N2 has spooled below 5%, select ENGINE 1 BITE through the MAINT selection on the FMC CDU. (a) Effects as above __ __ __ __ __ __





ATA 123Hidden123

80.2 ENGINE HUNG START - LOW FUEL


Failure Description

Offset in the fuel metering valve position resulting in a lower than normal fuel flow during an engine start.


FLIGHT DECK EFFECTS: ------------------- - Engine lights up normally, but accelerates slower than normal - Engine does not reach starter cutout speed and start is not completed

Malfunction Check

1. Select APU via ATM REPOSITIONS page. 2. Insert ENG 1 malfunction. 3. Perform an engine start. (a) Effects as above __ __ __ __ __ __ 4. Turn off engine start switch. 5. Perform Maintenance procedure (if applicable). 6. Remove malfunction. 7. Repeat checks 2 to 6 for ENG 2 malfunction. Maintenance: (if applicable) ----------- 1. Reposition on ground and shut down engine. 2. When N2 has spooled below 5%, select ENGINE 1 BITE through the MAINT selection on the FMC CDU. (a) Effects as above __ __ __ __ __ __





ATA 123Hidden123

80.3 START VALVE FAILS IN POSITION


Failure Description

Engine start valve gets stuck in position.


FLIGHT DECK EFFECTS: ------------------- If failed in the open position: - Engine starts successfully - "START VLV OPEN" indication on CDS does not disappear after starter cutout speed has been reached - "START VLV OPEN" message blinks for first 10s if airplane is on ground and airspeed is below 80 knots If failed in the closed position when attempting to do an engine start: - "START VLV OPEN" message on CDS does not appear after START SW has been selected to GND - Engine does not accelerate - It is impossible to complete an engine start

Malfunction Check

1. Select APU via ATM REPOSITIONS page. 2. Insert ENG 1 malfunction. (a) Effects as above __ __ __ __ __ __ 3. Remove malfunction. 4. Repeat checks 2 and 3 for ENG 2 malfunction.





ATA 123Hidden123

80.4 IGNITION EXCITER FAILURE

CDB Label: TF8000011 1 L TF8000012 1 R TF8000013 2 L TF8000014 2 R

Failure Description

Engine ignition exciter fails causing lightoff to be impossible during engine start-ups when ignition exciter is selected (it will fail if both exciters are failed for one engine or if the exciter of the selected ignitor is failed).


FLIGHT DECK EFFECTS: ------------------- During an engine start with both exciters for one engine or exciter of selected ignitor is failed, after start lever has been moved to IDLE: - Lightoff is not observed - EGT never rises - Fuel flow is normal - If fuel is not cut after 15s (20s if ambient temperature < 2 degrees C), EEC cuts it automatically

Malfunction Check

1. Select APU via ATM REPOSITIONS page. 2. Insert the 1 L malfunction. 3. Perform an engine start. (a) Effects as above __ __ __ __ __ __ __ __ __ __ __ __ 4. Perform Maintenance procedure (if applicable). 5. Remove the malfunction. 6. Repeat checks 2 to 5 for the remaining malfunctions. Maintenance: (if applicable) -----------





1. Reposition on ground and shut down the engine. 2. Pull the Fuel Spar Valve Eng 1 circuit breaker (P6-3/B04). 3. When N2 has spooled below 5%, select ENGINE 1 BITE via the MAINT selection on the FMC CDU. (a) Effects as above __ __ __ __ __ __ __ __ __ __ __ __

B737-800 Full Flight Simulator · ATA 27 - Flight Controls 84 ... 31.2 EFIS CONTROL PANEL POWER...

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Transcript of B737-800 Full Flight Simulator · ATA 27 - Flight Controls 84 ... 31.2 EFIS CONTROL PANEL POWER...