Procedure After the Engine has Exceeded the Operational Limits [CFMI]

TASK 72-00-00-200-003-A
Procedure After the Engine has Exceeded the Operational Limits

WARNING: BE CAREFUL WHEN YOU DO WORK ON THE ENGINE PARTS AFTER THE ENGINE SHUTDOWN. USE APPLICABLE THERMAL GLOVES. THE ENGINE PARTS CAN STAY HOT FOR ONE HOUR AFTER SHUTDOWN AND CAN BURN YOU.

1. Reason for the Job

NOTE: If an exceedance occur, the DMC memorizes in its memory the maximum value reached during the last flight leg for N1, N2 and EGT.

2. Job Set-up Information
A. Fixtures, Tools, Test and Support Equipment

REFERENCE	QTY	DESIGNATION
No specific	AR	WARNING NOTICE(S)

B. Work Zones and Access Panels

ZONE/ACCESS	ZONE DESCRIPTION
FOR [1000EM1] (ENGINE-1)
437AL, 438AR, 451AL, 452AR
FOR [1000EM2] (ENGINE-2)
447AL, 448AR, 461AL, 462AR

C. Referenced Information

REFERENCE	DESIGNATION
TASK 05-51-11-200-004-B	Inspections After a Hard Landing or a Hard Overweight Landing for Aircraft with Enhanced DMU/FDIMU Load Report 15
TASK 05-51-11-200-004-C	Inspections After a Hard Landing or a Hard Overweight Landing for Aircraft with FDIMU Load Report 15 included in Software 10TVSW2 or 10TVSW5
TASK 12-13-79-610-001-A	Check Oil Level and Replenish
TASK 12-13-79-610-001-A-01	Check Oil Level and Replenish (Pressure Filling)
TASK 12-13-79-610-003-A	Oil Tank Draining
TASK 12-13-79-610-004-A	Draining of the Accessory Drive Section
TASK 71-00-00-000-040-A	Removal of the Power Plant
TASK 71-00-00-000-040-A-01	Removal of the Power Plant with the Engine Positioner TWW 75E
TASK 71-00-00-000-040-A-03	Removal of the Power Plant with Jacxson Tool
TASK 71-13-00-010-040-A	Opening of the Fan Cowl Doors
TASK 71-13-00-410-040-A	Closing of the Fan Cowl Doors
TASK 72-00-00-100-002-A	Engine Washing Requirements
TASK 72-21-00-210-025-A	Inspect Fan Rotor Blades Installed on the Fan Disk
TASK 72-21-00-290-001-A	Standard Borescope Inspection of Booster Rotor Blades, Stages 2, 3 and 4 through the Booster Inlet and Borescope Port SO
TASK 72-23-00-210-001-A	Visual Inspection of the Fan Frame Assembly
TASK 72-23-00-210-003-A	Detailed Inspection of Spinner, Engine Inlet, Fan Blades, Fan Outlet and Abradable Material
TASK 72-31-00-290-001-A	Inspection of the High Pressure Compressor Rotor Assembly
TASK 72-52-00-290-001-A	Borescope Inspection of the HPT Blades (from the Front and the Rear)
TASK 72-54-00-290-001-A	Inspection of the Stage 1-3 Blades
TASK 72-56-00-210-001-A	Inspection/Check of the Turbine Frame Assembly
TASK 77-00-00-710-040-A	Reset of the N1,N2 and EGT Max Pointers
TASK 78-30-00-081-041-A	Make the Thrust Reverser Serviceable after Maintenance
TASK 78-30-00-481-041-A	Make the Thrust Reverser Unserviceable for Maintenance
TASK 78-36-00-010-040-A	Opening of the Thrust Reverser Doors
TASK 78-36-00-410-040-A	Closing of the Thrust Reverser Doors
TASK 79-21-10-000-002-A	Removal of the Magnetic Plug Assembly
TASK 79-21-10-000-003-A	Removal of the Lube Supply and/or Common Scavenge Filters
TASK 79-21-10-210-002-A	Check of the Lubrication Unit Magnetic Plugs and Scavenge Screens
TSM 73-00-00-810-865	Engine 1 or 2 Stall at Flight Phase 1 or 2 (Start/Ground Operations)
TSM 73-00-00-810-866	Stall of Engine 1 or 2 in Flight
TSM 77-00-00-810-849	EGT Overlimit on Engine 1 or 2
TSM 77-00-00-810-850	N1 Overlimit on Engine 1 or 2
TSM 79-00-00-810-805	Abnormal Oil Temperature on Engine 1 or on Engine 2
TSM 79-00-00-810-818	Incorrect Oil Quantity Level on Engine 1
TSM 79-00-00-810-819	Incorrect Oil Quantity Level on Engine 2
TSM 79-00-00-810-836	Low Oil Pressure Indication on Engine 1
TSM 79-00-00-810-837	Low Oil Pressure Indication on Engine 2
TSM 79-00-00-810-840	Engine Oil External leakage
Oil Pressure Versus Core Speed (N2)
Operational EGT (T495) Limits for Ground Starting and Sub-idle Operation
Operational EGT (T495) Limits Above Idle
Operational EGT Limits at Take off
Operational EGT Limits at Climb, Cruise and Max Continuous

3. Job Set-up
Subtask 72-00-00-941-052-A ** ON A/C NOT FOR ALL

A. Safety Precautions
(1) On the center pedestal, on the ENG panel 115VU:
(a) Put a WARNING NOTICE(S) to tell persons not to start the engine.
(2) Make sure that the engine 1(2) shutdown occurred not less than 5 minutes before you do this procedure.
(3) On the overhead maintenance panel 50VU:
(a) Make sure that the ON legend of the ENG/FADEC GND PWR/1(2) pushbutton switch is off.
(b) Put a WARNING NOTICE(S) to tell persons not to energize the FADEC 1(2).

Subtask 72-00-00-010-052-A ** ON A/C NOT FOR ALL

B. Open the fan cowl doors (Ref. AMM TASK 71-13-00-010-040):
(1) FOR [1000EM1] (ENGINE-1)
437AL 438AR
(2) FOR [1000EM2] (ENGINE-2)
447AL 448AR

Subtask 72-00-00-040-052-A ** ON A/C NOT FOR ALL

C. Make the thrust reverser unserviceable (Ref. AMM TASK 78-30-00-481-041).

Subtask 72-00-00-010-057-A ** ON A/C NOT FOR ALL

D. Open the thrust reverser doors (Ref. AMM TASK 78-36-00-010-040):
(1) FOR [1000EM1] (ENGINE-1)
451AL 452AR
(2) FOR [1000EM2] (ENGINE-2)
461AL 462AR

4. Procedure
Subtask 72-00-00-290-050-A ** ON A/C NOT FOR ALL

A. Checks to be Done after a Hot Start

NOTE: Starting exhaust gas temperature (EGT) (T495) limits are given.

Operational EGT (T495) Limits for Ground Starting and Sub-idle Operation ** ON A/C NOT FOR ALL

(1) Area A: EGT (T495) is more than 725 deg.C but less than or equal to 750 deg.C for a period of less than 30 seconds.
(a) Do the trouble shooting procedure to find and correct the cause of the hot start before the subsequent flight TSM 77-00-00-810-849.
(b) A maximum service extension of 5 flight cycles is permitted before you must correct the problem.
(2) Area B: EGT (T495) is more than 750 deg.C but less than or equal to 800 deg.C for less than 10 seconds.
(a) Do a borescope inspection of the HPT blades and stage 1 LPT blades (borescope port S17) (Ref. AMM TASK 72-54-00-290-001) and (Ref. AMM TASK 72-52-00-290-001).
(b) Do the trouble shooting procedure to find and correct the cause of the hot start before the subsequent flight TSM 77-00-00-810-849.
(c) A maximum service extension of one start is permitted and, if that start is satisfactory, 1 cycle is permitted before you must correct the problem.
(3) Area C: Stop the start and do these checks before you try to start the engine again.

CAUTION: HPT BLADES THAT HAVE HAD ENGINE EGT MORE THAN 990 DEG.C (1814 DEG.F) CANNOT BE REPAIRED. THE ENGINE MUST BE REMOVED AND RETURNED TO SHOP FACILITY TO EXAMINE FOR DAMAGE.

(a) Do a borescope inspection of the HPT blades and stage 1 LPT blades (borescope port S17). (Ref. AMM TASK 72-52-00-290-001) and (Ref. AMM TASK 72-54-00-290-001)
(b) Do the trouble shooting procedure to find and correct the cause of the hot start before the subsequent flight TSM 77-00-00-810-849
(4) If EGT is more than 890 deg.C reset the EGT max pointer after you correct the problem (Ref. AMM TASK 77-00-00-710-040).

Subtask 72-00-00-290-051-A ** ON A/C NOT FOR ALL

B. Checks to be Done if an Overtemperature Condition Occurs at all Engine Ratings other than Starting

NOTE: There can be many causes for an EGT overtemperature condition, such as:

engine warm up before take off is not sufficient
full rated take-off in hot day condition
dirty compressor airfoils, engine deterioration (low remaining EGT margin), engine bleed selected during take off after throttle push
FOD, engine system malfunction (for example: VBV actuation), or engine hardware malfunction (for example: airfoil failure, hot air leak, etc.).

NOTE: Some positive EGT margin can result by doing an engine gas path water wash (Ref. AMM TASK 72-00-00-100-002). This makes engine performance better but is temporary. It is not a long term repair for high EGT or engine deterioration.

Read the DMU Exceedance Report, the DMC Max Value Report and/or the ECU data by the Menu Mode Specific Data Report (if available) to find the maximum EGT value that was recorded during the event, as well as the amount of time of the overtemperature condition. If none of these reports are available, get the data from the AIDS or DFDR.

(1) Follow these instructions for the applicable power range where the engine overtemperature occurred:
(a) Takeoff (identified as Flight Phase 5 on report PFR)

Operational EGT Limits at Take off ** ON A/C NOT FOR ALL

NOTE: Consider EGT indicated max value and physical max time value, as printed out from PWR SETTING MAX VALUES report.

1 Find if there was an Area A, B, C or D takeoff exceedance.

NOTE: No maintenance action is necessary when the maximum EGT is between 890 and 900 degrees C for less than 20 seconds (Transient) when takeoff or go around power is set (area D).

(b) Climb, Cruise or Max Continuous (identified as Flight Phase 6 on report PFR)

Operational EGT Limits at Climb, Cruise and Max Continuous ** ON A/C NOT FOR ALL

NOTE: Consider EGT indicated max value and physical max time value, as printed out from PWR SETTING MAX VALUES report.

NOTE: If the flight crew has logged an EGT indication above the 855 degrees C climb, cruise, or max continuous power limit, maintenance personnel should be concerned with the total time the engine was at 855 degrees C or above regardless of the time that has elapsed since takeoff power was reduced to climb, cruise or max continuous power.

(2) Find if there was an Area A, B, C or D takeoff exceedance.

NOTE: No maintenance action is necessary when the maximum EGT is between 890 and 900 degrees C for less than 20 seconds (Transient) when takeoff or go around power is set (area D).

(3) Area A: (Unusual Operation)
(a) Area D includes annunciated EGT exceedances up to 900 deg.C (1625 deg.F) for a maximum of 20 seconds physical time for the models listed below,

CFM 56-5A1 CFM (-5A) SB 72-0630 ENGINES ONLY
CFM 56-5A1/F
CFM 56-5A3
CFM 56-5A4 CFM (-5A) SB 72-0630 ENGINES ONLY
CFM 56-5A4/F
CFM 56-5A5 CFM (-5A) SB 72-0630 ENGINES ONLY
CFM 56-5A5/F

1 Annunciated EGT exceedances are permitted for this condition with no maintenance step necessary.
2 The total time of the EGT exceedance is found from the Physical Max Time value shown in the peak values report. For the models listed above, Physical Max Time may be more than Indicated Max Time.

NOTE: If the temperature goes into Area D again and again, it can show performance deterioration or other indications and the possible movement into Area A.

(b) If the EGT overtemperature condition is identified to be caused by not having sufficient engine warm-up before take off:
1 No troubleshooting is necessary.

NOTE: Warm-up time is not sufficient if engine is as follows:

shut down for more than 4 hours
operated at idle or above for less than 15 minutes

(c) If the EGT overtemperature condition is identified to be caused by engine deterioration (low remaining EGT margin), or engine bleed selected during take off after throttle push:
1 No troubleshooting is necessary.
(d) If the cause of the EGT overtemperature condition cannot be identified by the above, or you think it could have been caused by FOD or engine hardware failure:
1 Do troubleshooting for EGT OVERLIMIT TSM 77-00-00-810-849.
2 Troubleshooting can be deferred for five overtemperature conditions in Area A but can not go over 25 cycles after the first overtemperature condition.

NOTE: There are known engine malfunctions that can lead to an EGT overtemperature condition and thus a Class 1 ECAM warning message. These malfunctions require troubleshooting prior to engine operation. (Example: "VBV ACT, HMU ", "CHECK HOT AIR LEAKS", "NAC TEMP SENSOR", etc.).

(e) You can have a maximum of 20 overtemperature conditions in Area A, before engine removal is required.
(4) Area B: (Abnormal)
(a) Do a borescope inspection of the HPT blades and stage 1 LPT blades (borescope port S17) (Ref. AMM TASK 72-52-00-290-001) and (Ref. AMM TASK 72-54-00-290-001).
(b) Do troubleshooting for "EGT OVERLIMIT" TSM 77-00-00-810-849.
1 Troubleshooting can be deferred for 10 cycles unless the fault repeats.
(c) If you can identify the cause of the EGT exceedance and no more exceedance occur, the borescope inspection can be deferred up to 5 cycles.
(d) You can have a maximum of 20 overtemperature conditions in Areas A and B together or 10 overtemperature conditions in Area B alone, before engine removal is required.
(5) Area C: (Overtemperature)
(a) Remove and return engine to a shop facility to examine damage.
(b) One non-revenue flight for fly-back is permitted before the engine must be removed, if there is no damage above the serviceable limits:
1 Do a borescope inspection of the HPT blades and stage 1 LPT blades (borescope port S17) (Ref. AMM TASK 72-52-00-290-001) and (Ref. AMM TASK 72-54-00-290-001).
2 Do a troubleshooting for "EGT OVERLIMIT" TSM 77-00-00-810-849.

Subtask 72-00-00-280-055-A ** ON A/C NOT FOR ALL

C. Checks to be Performed when Abnormal Rotation Speeds are Reached.
(1) Overspeed.
(a) The speed limits are as follows:
1 Fan speed (N1): 102 percent
2 Core speed (N2): 105 percent
(b) Fan (N1) overspeed inspections:
1 If fan is operated at speeds from 102.1 percent to 103.8 percent, the engine must be inspected as follows:

Review available data to understand reason for the overspeed.
Correct the cause. Troubleshoot TSM 77-00-00-810-850.
Do a visual inspection of the engine inlet, the fan blades, the exhaust nozzle, and the stage 4 LPT blades.
Check the fan rotor for freedom of rotation and shingling of blades (Ref. AMM TASK 72-21-00-210-025).
Do an inspection of the abradable material in fan inlet case for rubbing (Ref. AMM TASK 72-23-00-210-003).
Do a borescope inspection of the stage 4 booster rotor blades (borescope port SO) (Ref. AMM TASK 72-21-00-290-001).
Do a Borescope inspection of the stage 1 LPT blades (borescope port S17) (Ref. AMM TASK 72-54-00-290-001).

2 If fan speed exceeds 103.8 percent, remove engine and return to shop for overspeed inspection.
3 If fan speed has exceeded 102 percent, the N1 max pointer must be reset after corrective action has been performed (Ref. AMM TASK 77-00-00-710-040).
(c) Core engine (N2) overspeed inspections:
1 If core engine rotor is operated at speeds from 105.1 percent to 105.8 percent, the engine must be inspected as follows:

Inspect exhaust nozzles for particles.
Borescope inspect stages 1,3 and 8 HPC blades (borescope ports S1, S3 and S8) (Ref. AMM TASK 72-31-00-290-001)
Borescope inspect HPT blades (borescope port S17) (Ref. AMM TASK 72-52-00-290-001).

2 If core engine rotation speed exceeds 105.8 percent, shutdown, remove engine and return to shop for overspeed inspections.
3 If core engine rotation speed has exceeded 105 percent, the N2 max pointer must be reset after corrective action has been performed (Ref. AMM TASK 77-00-00-710-040).

Subtask 72-00-00-210-054-A ** ON A/C NOT FOR ALL

D. Checks Required After Lubrication System Operation Limits are Exceeded
(1) Oil pressure.

Oil Pressure Versus Core Speed (N2) ** ON A/C NOT FOR ALL

(a) The Figure gives the relation between oil pressure and N2 speed. Five operating zones have been determined.
(b) Critical zone A, with oil pressure lower than 13 psi (0.9 bar).
1 If engine operation with no oil or very low pressure has exceeded any one of the following, remove engine and return to shop.

Take-off power for 10 seconds.
Cruise power for 10 seconds.
Idle (flight or ground) for 30 seconds.

2 If engine not exceeding time limits per step 1_ has been operated with no oil pressure or very low pressure, remove all oil filters, screens, magnetic plug and chip detectors, and check for presence of metal/debris (Ref. AMM TASK 79-21-10-210-002).If no suspect metal debris is observed, troubleshoot TSM 79-00-00-810-836 or TSM 79-00-00-810-837.
(c) Zones B and/or D: Troubleshoot TSM 79-00-00-810-836 or TSM 79-00-00-810-837.
(2) Supply Oil Temperature.
(a) Maximum oil temperature for continuous engine operation is 140 deg.C (284 deg.F).
(b) Engine operation with oil between 140 deg.C (284 deg.F) and 155 deg.C (311 deg.F) is allowed for 15 minutes.
(c) Above 155 deg.C (311 deg.F) the oil system must be drained (Ref. AMM TASK 12-13-79-610-003) and (Ref. AMM TASK 12-13-79-610-004) and serviced (Ref. AMM TASK 12-13-79-610-001). Troubleshoot TSM 79-00-00-810-805.
(d) After abnormally high oil temperature, remove the supply filter, common scavenge filter (Ref. AMM TASK 79-21-10-000-003) and chip detectors (Ref. AMM TASK 79-21-10-000-002) of the lube unit and check for the presence of metal particles. If metal particles are present, remove and disassemble the engine for inspection.
(3) Oil Consumption.
(a) Normal oil consumption is not expected to exceed 0.57 l.hr (approximately 0.60 quart.hr) (0.15 USgal.hr).
(b) As soon as one of the following cases occur, Troubleshooting TSM 79-00-00-810-818 or TSM 79-00-00-810-819 must be performed:

Oil consumption exceeds 0.85 l.hr (approximately 0.9 quart.hr) (0.22 USgal.hr).
Oil consumption substantially exceeds that of the other operating engines.
Oil consumption indicates a gradual increasing trend.
Oil consumption indicates sudden step increase.

Troubleshooting TSM 79-00-00-810-840 and TSM 79-00-00-810-818 or TSM 79-00-00-810-819 must be performed as soon as the oil consumption rate overshoots this limit.
If the result of the troubleshooting is not conclusive and no action can be taken to reduce the oil consumption rate, the engine has to be replaced.

Subtask 72-00-00-210-103-A ** ON A/C NOT FOR ALL

E. IFSD time limitation
(1) Dry-out the engine if you can not restart within 24 hours and after each ferry flight.

Subtask 72-00-00-210-055-A ** ON A/C NOT FOR ALL

F. Inspections after a Hard or Hard Overweight Landing

NOTE: The inspection must be done if the aircraft sustained a hard landing or hard overweight landing. For hard landing and hard overweight landing definition refer to (Ref. AMM TASK 05-51-11-200-004).

(1) General:
(a) Inspection Sequence
1 The inspections are divided into three phases:

Phase 1 is a general inspection for primary deterioration and indication of remote deterioration and is mainly external.
Phase 2 is a more detailed inspection and is mainly internal. Some component removals can be called up.
Phase 3 is a very detailed inspection involving component removal and strip down.

2 If the Phase 1 inspection shows no deterioration, no further examination is necessary.
3 If Phase 1 shows deterioration, then Phase 2 must be done.
4 If Phase 2 shows deterioration, then Phase 3 must be done.
5 If you find deterioration during Phase 1 or Phase 2 inspections, replace or repair the deteriorated component (refer to the applicable manuals (SRM, AMM, CMM)) and make sure that the adjacent area has no deterioration).
(2) Examine the engine.
(a) Phase 1
1 Turn the fan rotor.

WARNING: BE CAREFUL WHEN YOU TURN THE FAN ROTOR MANUALLY. USE HEAVY PROTECTIVE GLOVES AND MAKE SURE THAT YOU CANNOT SLIP. IF YOU DO NOT OBEY THESE INSTRUCTIONS, INJURY CAN OCCUR.

a Turn the fan rotor with your hand. Make sure that there is (are) no bearing roughness, unusual noises and bindings.
2 Do a visual inspection of the abradable material of the fan inlet case. Make sure that there is no unusual wear of the abradable material (Ref. AMM TASK 72-23-00-210-003).
3 Do a visual inspection of the fan frame assembly (Ref. AMM TASK 72-23-00-210-001).
4 Do a visual inspection of the turbine frame assembly (Ref. AMM TASK 72-56-00-210-001).
5 Do a visual inspection of the accessory and hardware attachments for metal fractures or excessive distortion.
6 Do a visual inspection of the piping connections for leaks.
7 Do a visual inspection of the lines and tubing for possible interferences.
(b) Phase 2, if you find deterioration in the above tasks:
1 Do a borescope inspection of the HPC blades (Ref. AMM TASK 72-31-00-290-001).
2 Do a borescope inspection of the LPC blades (Ref. AMM TASK 72-21-00-290-001).
3 Examine the lubrication unit magnetic plugs/electrical master chip detector for metal particles caused by bearing deterioration (Ref. AMM TASK 79-21-10-210-002).
a If you do not find metal particles, do the inspection each day for one week, then each week for one month.
(c) Phase 3, if you find deterioration in the above tasks, engine removal can be necessary (Ref. AMM TASK 71-00-00-000-040).

Subtask 72-00-00-210-056-A ** ON A/C NOT FOR ALL

G. Engine Post Stall Inspection
(1) General.
(a) If a stall or suspected stall has occurred, the following inspection and the applicable troubleshooting procedure for the ECAM warning ENG 1(2) STALL must be done TSM 73-00-00-810-865 or TSM 73-00-00-810-866.
(2) For Visual Inspection/Checks, inspect the following:
(a) Fan rotor and abradable material (Ref. AMM TASK 72-21-00-210-025) and (Ref. AMM TASK 72-23-00-210-003).
(3) For Borescope Inspection/Checks, inspect the following:
(a) For engine stalls in the start region, or for off-idle stalls which result in engine rollback into sub-idle N2 range:
1 If the start region EGT limit of 725 deg.C was exceeded, borescope inspect HPT blades and stage 1 LPT blades (borescope port S17) (Ref. AMM TASK 72-52-00-290-001) and (Ref. AMM TASK 72-54-00-290-001).

Operational EGT (T495) Limits for Ground Starting and Sub-idle Operation ** ON A/C NOT FOR ALL

2 If the cause of the stall is not known, borescope inspect stages 1, 3 and 8 HPC blades (borescope ports S1, S3 and S8) (Ref. AMM TASK 72-31-00-290-001).
(b) For engine stalls at or above idle which do not result in engine rollback into sub-idle N2:
1 Borescope inspect HPT blades and stage 1 LPT blades (borescope port S17) (Ref. AMM TASK 72-52-00-290-001). and (Ref. AMM TASK 72-54-00-290-001)

Operational EGT (T495) Limits Above Idle ** ON A/C NOT FOR ALL

2 If the cause of the stall is not known, borescope inspect stage 4 booster rotor blades (borescope port S0) (Ref. AMM TASK 72-21-00-290-001) and stages 1, 3 and 8 HPC blades (borescope ports S1, S3 and S8) (Ref. AMM TASK 72-31-00-290-001).

Subtask 72-00-00-210-057-A ** ON A/C NOT FOR ALL

H. Inspection after in-Flight Excessive Load Factor due to Turbulence or Maneuver or in Excess of VMO/MMO
(1) General:
(a) Engine suspected of experiencing excessive g-loading during transportation must be given the following inspection.
(b) Inspection Sequence
1 The inspections are divided into three phases:

Phase 1 is a general inspection for primary deterioration and indication of remote deterioration and is mainly external.
Phase 2 is a more detailed inspection and is mainly internal. Some component removals can be called up.
Phase 3 is a very detailed inspection involving component removal and strip down.

WARNING: BE CAREFUL WHEN YOU TURN THE FAN ROTOR MANUALLY. USE HEAVY PROTECTIVE GLOVES AND MAKE SURE THAT YOU CANNOT SLIP. IF YOU DO NOT OBEY THESE INSTRUCTIONS, INJURY CAN OCCUR.

5. Close-up
Subtask 72-00-00-869-053-A ** ON A/C NOT FOR ALL

A. Make sure that the work area is clean and clear of tools and other items.

Subtask 72-00-00-410-052-A ** ON A/C NOT FOR ALL

B. Close Access
(1) Make sure that the work area is clean and clear of tools and other items.
(2) Close the thrust reverser doors (Ref. AMM TASK 78-36-00-410-040):
(3) FOR [1000EM1] (ENGINE-1)
451AL 452AR
(4) FOR [1000EM2] (ENGINE-2)
461AL 462AR

Subtask 72-00-00-440-052-A ** ON A/C NOT FOR ALL

C. Make the thrust reverser serviceable (Ref. AMM TASK 78-30-00-081-041).

Subtask 72-00-00-410-057-A ** ON A/C NOT FOR ALL

D. Close Access
(1) Close the fan cowl doors (Ref. AMM TASK 71-13-00-410-040):
(a) FOR [1000EM1] (ENGINE-1)
437AL 438AR
(b) FOR [1000EM2] (ENGINE-2)
447AL 448AR
(2) Remove the WARNING NOTICE(S).

[Rev.10 from 2021] 2026.04.01 02:37:37 UTC