Customer : ATLAS Manual : AMM

Type : A340 Selected applicability : 163-163

Rev. Date : Apr 01, 2018
72-00-00-200-803-A - Inspection/Check after
the Engine has Exceeded the Operational Limits

** ON A/C ALL

TASK 72-00-00-200-803-A
Inspection/Check after the Engine has Exceeded the Operational Limits

1. Reason for the Job

If an exceedance occurs, the DMC memorizes in its memory the maximum value reached during the last flight
leg for N1, N2 , EGT and Hard Landing or Hard Overweight Landing.
2 Job Set-up Information
A. Fixtures, Tools, Test and Support Equipment

REFERENCE QTY DESIGNATION

No specific AR ACCESS PLATFORM 3M (10 FT)- ADJUSTABLE
No specific AR ACCESS PLATFORM 5M (16 FT)- ADJUSTABLE
No specific AR SAFETY CLIP - CIRCUIT BREAKER

B. Work Zones and Access Panels

ZONE/ACCESS ZONE DESCRIPTION

811
FOR 4000EM1 (ENGINE-1)
415AL, 416AR,
417AL, 418AR
FOR 4000EM2 (ENGINE-2)
425AL, 426AR,
427AL, 428AR
FOR 4000EM3 (ENGINE-3)
435AL, 436AR,
437AL, 438AR
FOR 4000EM4 (ENGINE-4)
445AL, 446AR,
447AL, 448AR

C. Referenced Information

REFERENCE DESIGNATION
(Ref. 05-51-11-200-802-A). Inspections after a Hard Landing or Hard Overweight Landing
(Ref. 12-13-79-610-801-A). Check of the Oil Level and Gravity Filling
(Ref. 12-13-79-610-803-A). Oil Tank Draining
(Ref. 24-42-00-861-801-A). Energize the Ground Service Network
(Ref. 24-42-00-862-801-A). De-energize the Ground Service Network
(Ref. 71-00-00-000-801-A). Removal of the Engine
(Ref. 71-00-00-000-801-A). Removal of the Engine
(Ref. 71-00-00-000-801-A-02). Removal of the Engine with the Engine Positioner TWW 75E (MIAG)
(Ref. 71-00-00-000-801-A-03). Removal of the Engine with Cobra Tool
(Ref. 71-00-00-400-801-A). Installation of the Engine
(Ref. 71-00-00-400-801-A-02). Installation of the Engine with the Engine Positioner TWW 75E (MIAG)

Print Date: November 02, 2018 Page 1 of 19

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 Customer : ATLAS Manual : AMM
Type : A340 Selected applicability : 163-163
Rev. Date : Apr 01, 2018
72-00-00-200-803-A - Inspection/Check after
the Engine has Exceeded the Operational Limits

REFERENCE DESIGNATION

** ON A/C 051-099, 101-150, 153-159, 161-163, 165-199

(Ref. 71-00-00-400-801-A-03). Installation of the Engine with Cobra Tool

** ON A/C ALL
(Ref. 71-00-00-710-801-A). Operation and Reference Data
(Ref. 71-13-00-010-801-A). Opening of the Fan Cowl Doors
(Ref. 71-13-00-410-801-A). Closing of the Fan Cowl Doors
(Ref. 71-21-11-210-801-A). Detailed Visual Inspection of the Forward Engine Mount
(Ref. 71-22-11-210-801-A). Detailed Visual Inspection of the Aft Engine Mounts
(Ref. 72-00-00-100-801-A). Engine Dry-Out and Relubrication
(Ref. 72-00-00-100-804-A). Washing of the Engine Gas Path with Pure Water
(Ref. 72-00-00-100-805-A). Engine External Cleaning
(Ref. 72-00-00-200-801-A). Inspection/Check of Foreign Object Damage (FOD) (Bird Strike in-
cluded)
(Ref. 72-00-00-210-802-A). General Visual Inspection (as far as visible from the ground) of Power
Plant Inlet, Fan Blades and Power Plant Outlet.
(Ref. 72-00-00-600-808-A). Engine Preservation after IFSD or Ferry Flight - General
(Ref. 72-21-00-210-801-A). Detailed Inspection of Fan Blades and Spinner
(Ref. 72-21-00-290-801-A). Borescope Inspection/Check of the Booster Rotor Blades
(Ref. 72-23-00-210-801-A). Detailed Inspection of Visible Area of Engine Inlet and Fan Outlet for
Damage and/or Missing Abradable Material.
(Ref. 72-23-00-210-804-A). Inspection of the Upper Radial Drive Shaft
(Ref. 72-23-00-210-805-A). Visual Inspection of the Junction Box
(Ref. 72-23-00-280-801-A). Inspection/Check of the PS12 Line
(Ref. 72-23-00-280-802-A). Inspection/Check of the PS13 Line
(Ref. 72-31-00-290-801-A). Inspection of the High Pressure Compressor Rotor Assembly
(Ref. 72-51-00-290-801-A). Borescope Inspection of HPT Nozzle from Two Ports on Forward Side
(Ref. 72-52-00-290-801-A). Borescope Inspection of the High Pressure Turbine Blades (from the
rear).
(Ref. 72-52-00-290-802-A). Borescope Inspection of the High Pressure Turbine Blades (from the
front).
(Ref. 72-54-00-290-801-A). Borescope Inspection of the Low Pressure Turbine Rotor Blades
(stages 1 thru 5) , Nozzle Segments (stages 2 thru 5) and Outer Sta-
tionary Air Seals.
(Ref. 72-56-00-200-801-A). Inspection/Check of the Turbine Frame Module
(Ref. 73-21-00-740-804-A). Reading of the FADEC System SPECIFIC DATA Report
(Ref. 77-00-00-710-802-A). Reset of the N1,N2 and EGT Max Pointer
(Ref. 78-11-10-210-801-A). Detailed Visual Inspection of the Exhaust Nozzle
(Ref. 78-30-00-040-801-A). Making of the Thrust Reverser Unserviceable for Maintenance
(Ref. 78-30-00-040-802-A). Deactivation of the Thrust Reverser
(Ref. 78-30-00-440-801-A). Making of the Thrust Reverser Serviceable after Maintenance
(Ref. 78-31-19-210-801-A). Detailed Visual Inspection of the Pivoting Door Primary Locks.
(Ref. 78-32-11-210-801-A). Detailed Visual Inspection of the Thrust Reverser Cowls
(Ref. 78-32-41-210-801-A). Visual Inspection of the Pivoting Doors
(Ref. 78-32-45-230-801-A). Dye Penetrant Inspection of the Adaptor Ring Outer Flanges
(Ref. 78-36-00-010-801-A). Opening of the Thrust Reverser Doors
(Ref. 78-36-00-410-801-A). Closing of the Thrust Reverser Doors
(Ref. 79-00-00-280-801-A). Inspection/Check of the Antisiphon Device.
(Ref. 79-00-00-281-801-A). Check of the Electrical Master Chip Detector for Particles

Print Date: November 02, 2018 Page 2 of 19

© AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.
 Customer : ATLAS Manual : AMM
Type : A340 Selected applicability : 163-163
Rev. Date : Apr 01, 2018
72-00-00-200-803-A - Inspection/Check after
the Engine has Exceeded the Operational Limits

REFERENCE DESIGNATION
(Ref. 79-00-00-281-802-A). Check of FWD Sump, AFT Sump, Accessory Gearbox and Transfer
Gearbox Scavenge Screens
(Ref. 79-00-00-710-804-A). Operational Check of the Electrical Magnetic Chip Detector.
Ref. TSM 77-20-00-810-813 EGT Overlimit
Ref. TSM 71-00-00-810-874 Engine Stall is Detected (for corrective action)
Ref. TSM 79-31-00-810-827 On One Engine the Oil Quantity Decreases Faster than on the Other
Engines (for corrective action)
Ref. TSM 80-00-00-810-835 Engine Stall During Start (for corrective action)
Operational EGT (T495) Limits for Ground Starting and Sub-Idle Operation SHEET 1
Operational EGT (T495) Limits at Take Off SHEET 1
Oil Pressure Versus Core Speed (N2) SHEET 1
Operational EGT (T495) Limits at Climb, Cruise or Max Continuous Power SHEET 1

Print Date: November 02, 2018 Page 3 of 19

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 Customer : ATLAS Manual : AMM
Type : A340 Selected applicability : 163-163
Rev. Date : Apr 01, 2018
72-00-00-200-803-A - Inspection/Check after
the Engine has Exceeded the Operational Limits

EGT
(T495) LEGEND:
°C
AREAS:

A :UNUSUAL START
1472°F
800
B :ABNORMAL START
790
C C :ABORT START
780

770
B D :NORMAL START
760
COCKPIT INDICATION

750 1382°F

740
A
730
725 1337°F
720

710

700

0 10 20 30 40 50 60

TIME-SECONDS

1145003-00-A
F_MM_720000_6_UAM0_01_00

Figure 72(CFMI)-00-00-991-00600-00-A / SHEET 1/1 - Operational

EGT (T495) Limits for Ground Starting and Sub-Idle Operation
** ON A/C ALL

Print Date: November 02, 2018 Page 4 of 19

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 Customer : ATLAS Manual : AMM
Type : A340 Selected applicability : 163-163
Rev. Date : Apr 01, 2018
72-00-00-200-803-A - Inspection/Check after
the Engine has Exceeded the Operational Limits

LEGEND:

AREAS:
INDICATED
EGT A: UNUSUAL OPERATION
(T495)
°C
B: ABNORMAL

C: OVERTEMPERATURE
990 ENGINE REMOVAL REQUIRED

980 D: 20 SECOND TRANSIENT

975 C
B
970
COCKPIT INDICATION (INDICATION MX)

965
960
A
D

950

940

TAKE OFF
930 NORMAL
OPERATION

920

910

900

890

0 1 2 3 4 5

TIME-MINUTES
(PHYSICAL TIME)

1236316-00

F_MM_720000_6_UBM0_01_00

Figure 72(CFMI)-00-00-991-00700-00-A / SHEET 1/1 - Operational EGT (T495) Limits at Take Off
** ON A/C ALL

Print Date: November 02, 2018 Page 5 of 19

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Type : A340 Selected applicability : 163-163
Rev. Date : Apr 01, 2018
72-00-00-200-803-A - Inspection/Check after
the Engine has Exceeded the Operational Limits

KPA DIFF. COLD START BY-PASS VALVE

PSID OPENS AT 305 PSID (2102 KPA DIFF.)

2100
300

2000

700
100

90
600
ZONE E
80 PRESSURE IN THIS AREA
ACCEPTABLE IN TRANSIENT
UNDER VERY COLD CONDITIONS MAXIMUM NORMAL
500
70 CLOSE MONITORING OF OTHER OIL PRESS.
OIL SYSTEM PARAMETERS

60 MINIMUM NORMAL
400
GROUND OIL PRESS.

50 MINIMUM NORMAL
NORMAL OPERATING FLIGHT PRESS.
300
FLIGHT OIL
40 PRESSURE RANGE

30 NORMAL OPERATING
200
GROUND OIL
ZONE C
PRESSURE RANGE
IN THIS AREA
20 ZONE D CLOSE MONITORING
ZONE B OF TEMP. AND PRESS.
100
10
MINIMUM ACCEPTABLE PRESSURE 13 PSID (90 KPA DIFF.)
ZONE A LESS THAN MINIMUM OIL PRESSURE REQUIRES ENGINE SHUT DOWN
0
40 50 60 70 80 90 100 110
S-M56-MM-00697-01-B

CORE ENGINE SPEED / PERCENT

CAUTION :
MAINTENANCE ACTION IS REQUIRED PRIOR TO NEXT FLIGHT
IF ENGINE OIL PRESSURE LEVELS ARE REPORTED TO BE IN AREAS Band C
OPERATION IN AREAS and B, C E
REQUIRES CLOSE
MONITORING OF OTHER OIL SYSTEM PARAMETERS.

F_MM_720000_6_UCM0_01_01

Figure 72(CFMI)-00-00-991-00800-00-A / SHEET 1/1 - Oil Pressure Versus Core Speed (N2)
** ON A/C ALL

Print Date: November 02, 2018 Page 6 of 19

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 Customer : ATLAS Manual : AMM
Type : A340 Selected applicability : 163-163
Rev. Date : Apr 01, 2018
72-00-00-200-803-A - Inspection/Check after
the Engine has Exceeded the Operational Limits

EGT LEGEND :
(T495)
°C AREAS :

A: UNUSUAL OPERATION

B: ABNORMAL
990
C: OVERTEMPERATURE

980

970

960
C
950

940

930 A B

920
915
910

900

890

0 1 2 3 4 5 6 7 8 9 10

TIME - MINUTES
(PHYSICAL TIME)
(TOTAL TIME ABOVE 915°C AT CLIMB, CRUISE, OR MAX CONTINUOUS POWER)

S-M56-MM-04740-00-B

F_MM_720000_6_USM0_01_00

Figure 72(CFMI)-00-00-991-28500-00-A / SHEET 1/1 - Operational

EGT (T495) Limits at Climb, Cruise or Max Continuous Power
** ON A/C ALL

Print Date: November 02, 2018 Page 7 of 19

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 Customer : ATLAS Manual : AMM
Type : A340 Selected applicability : 163-163
Rev. Date : Apr 01, 2018
72-00-00-200-803-A - Inspection/Check after
the Engine has Exceeded the Operational Limits

3. Job Set-up
Subtask 72-00-00-861-052-A
A. Energize the ground service network
(Ref. AMM TASK 24-42-00-861-801) .
Subtask 72-00-00-941-053-A
B. Safety Precautions
(1) Make sure the engine 1, (2), (3), (4) shutdown occurred not less than 5 minutes before you do this
procedure.
Subtask 72-00-00-010-061-A
C. Get access to the avionics compartment.
(1) Put the ACCESS PLATFORM 3M (10 FT)- ADJUSTABLE in position at the access door 811.
(2) Open the access door 811.
(3) Open the protective door of the AC/DC emergency power-center 740VU.
Subtask 72-00-00-865-054-A
D. Open, safety and tag this(these) circuit breaker(s):

PANEL DESIGNATION FIN LOCATION

FOR FIN 4000EM1 (ENGINE-1)
722VU FADEC B ENG 1 13KS1 K46
742VU FADEC A ENG 1 12KS1 N74
FOR FIN 4000EM2 (ENGINE-2)
722VU FADEC B ENG 2 13KS2 D43
742VU FADEC A ENG 2 12KS2 Q73
FOR FIN 4000EM3 (ENGINE-3)
722VU FADEC B ENG 3 13KS3 K47
742VU FADEC A ENG 3 12KS3 Q74
FOR FIN 4000EM4 (ENGINE-4)
722VU FADEC B ENG 4 13KS4 D44
742VU FADEC A ENG 4 12KS4 N75
Subtask 72-00-00-010-053-A
E. Get Access
(1) Install an ACCESS PLATFORM 5M (16 FT)- ADJUSTABLE.
(2) Open the fan cowl doors (Ref. AMM TASK 71-13-00-010-801)
(a) FOR 4000EM1 (ENGINE-1)
415AL, 416AR
(b) FOR 4000EM2 (ENGINE-2)
425AL, 426AR
(c) FOR 4000EM3 (ENGINE-3)
435AL, 436AR
(d) FOR 4000EM4 (ENGINE-4)
445AL, 446AR
Subtask 72-00-00-040-052-A
F. Make the thrust reverser unserviceable (Ref. AMM TASK 78-30-00-040-801)

Print Date: November 02, 2018 Page 8 of 19

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Rev. Date : Apr 01, 2018
72-00-00-200-803-A - Inspection/Check after
the Engine has Exceeded the Operational Limits

Subtask 72-00-00-010-062-A
G. Get Access
(1) Open the thrust reverser doors: (Ref. AMM TASK 78-36-00-010-801)
(a) FOR 4000EM1 (ENGINE-1)
417AL, 418AR
(b) FOR 4000EM2 (ENGINE-2)
427AL, 428AR
(c) FOR 4000EM3 (ENGINE-3)
437AL, 438AR
(d) FOR 4000EM4 (ENGINE-4)
447AL
4. Procedure
(Ref. Fig. Operational EGT (T495) Limits for Ground Starting and Sub-Idle
Operation SHEET 1) (Ref. Fig. Operational EGT (T495) Limits at Take Off SHEET 1) (Ref. Fig. Oil Pressure
Versus Core Speed (N2) SHEET 1) (Ref. Fig. Operational EGT (T495) Limits at Climb, Cruise or Max
Continuous Power SHEET 1)
Subtask 72-00-00-290-051-A
A. Checks to be done after a Hot Start
(1) Area A: EGT (T495) is more than 725 deg.C (1337 deg.F) but less than or equal to 750 deg.C (1382
deg.F) for a period of less than 30 seconds.
(a) Do the troubleshooting procedure to find and correct the cause of the hot start before the
subsequent flight: Refer to TSM/77.
(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 (1382 deg.F) but less than or equal to 800 deg.C (1472
deg.F) 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 72-52-00-290-801) and (Ref. AMM TASK 72-54-00-290-801) .
(b) Do the troubleshooting procedure to find and correct the cause of the hot start before the
subsequent flight: Refer to TSM/77.
(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.
(a) Do a borescope inspection of the HPT blades (Ref. AMM TASK 72-52-00-290-801) or
(Ref. AMM TASK 72-52-00-290-802) and stage 1 LPT blades (borescope port S17)
(Ref. AMM TASK 72-54-00-290-801) .

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 RE-
TURNED TO SHOP FACILITY TO EXAMINE FOR DAMAGE.

(b) Do the troubleshooting procedure to find and correct the cause of the hot start before the
subsequent flight: Refer to TSM/77.
(c) If EGT is more than 906 deg.C (1663 deg.F) reset the EGT max pointer (Ref. AMM TASK 77-00-
00-710-802) after you correct the problem.
Subtask 72-00-00-290-052-A

Print Date: November 02, 2018 Page 9 of 19

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Rev. Date : Apr 01, 2018
72-00-00-200-803-A - Inspection/Check after
the Engine has Exceeded the Operational Limits

B. Checks to be done if overtemperature condition at all engine ratings other than starting occur.
(1) Get the "EGT INDICATED MAX" value and the "PHYSICAL MAX TIME" value from the POWER
SETTING MAX VALUES of the SPECIFIC DATA REPORT (Ref. AMM TASK 73-21-00-740-804) .
If the POWER SETTING MAX VALUES report cannot be retrieved, the aircraft flight data or ACMS
GAS PATH ADVISORY REPORT <06> can be used to get the exceedance range and duration.
(2) If the EGT exceedance is 2 seconds or less duration, troubleshoot the indicating system. Do not
count or record exceedances that are determined to be caused by the EGT indication system.
(3) Follow instructions for the applicable power range where the engine overtemperature occurred:

NOTE: EGT applicable limit (915 C or 950 C) depends on the throttle lever position, not of the FWC
flight phase. If the engine is at TOGA thrust, flex take off, derated take off, the redline is 950
C. IF the engine is at cruise, climb, max climb or max continuous, the redline is 915 C.

(a) Takeoff power range (engine at TOGA thrust, flex take off, derated take off)
(Ref. Fig. Operational EGT (T495) Limits at Take Off SHEET 1)
1 Put points on the graph to show the maximum EGT and the total cumulative time the EGT
was over the 950 deg.C redline limit.

NOTE: Consider "EGT INDICATED MAX" value and "PHYSICAL MAX TIME" value, as prin-
ted out from PWR SETTING MAX VALUES report.

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

· No maintenance action is necessary when the maximum EGT is between 950 and
960 deg.C for less that 20 seconds (Transient) when takeoff or go around power is
set (area D).
(b) Climb, Cruise or Max Continuous power range: Throttle Resolver Angle below MCT position or at
MCT position (Except flex take off and derated take off).
(Ref. Fig. Operational EGT (T495) Limits at Climb, Cruise or Max Continuous Power SHEET 1)
1 Put points on the graph to show the maximum EGT and the total cumulative time the EGT
was over the 915 deg.C limit.

NOTE: Consider "EGT INDICATED MAX" value and "PHYSICAL MAX TIME" value, as prin-
ted out from PWR SETTING MAX VALUES report.

NOTE: If the flight crew has logged an EGT indication above the 915 deg.C climb, cruise,
or max continuous power limit, maintenance personnel should be concerned with
the total time the engine was at 915 deg.C or above regardless of the time that has
elapsed since takeoff power was reduced to climb, cruise or max continuous power.

NOTE: There can be many causes of an EGT overtemperature. Some examples follow :
- Engine deterioration (low remaining EGT margin), - Engine warm-up not suffi-
cient before take off, - FOD, dirty compressor airfoils, - Engine control system failure
(VBV, VSV), - Engine EGT indication failure, - Engine hardware failure (airfoils fail-
ure, hot air leaks, etc).

NOTE: An engine waterwash can help to restore a significant positive EGT margin, if
the EGT overtemperature condition is because of dirty compressor airfoils (com-
pressor fouling). It is recommended to perform an engine gaspath waterwash
(Ref. AMM TASK 72-00-00-100-804) or (Ref. AMM TASK 72-00-00-100-805) to
restore EGT margins.

Print Date: November 02, 2018 Page 10 of 19

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Rev. Date : Apr 01, 2018
72-00-00-200-803-A - Inspection/Check after
the Engine has Exceeded the Operational Limits

NOTE: An engine warm-up time of ten minutes minimum can help to reduce the EGT over-
shoot on engines which show low remaining EGT margin for take-off operation.

NOTE: The ACMS exceedance report (if available) also contains the max EGT value that
was recorded during the event as well as the duration of the exceedance.

(4) Area D :
(a) Includes annunciated EGT exceedances up to 960 deg. C (1760 deg. F) shown for a maximum
of 20 seconds physical time.
If the temperature goes into Area D again and again, it can show performance deterioration or
other indications problem, and the possible movement into Area A.
1 Do not count or record as an exceedance.
2 No maintenance action is necessary.
(5) Area A :
(a) Make a visual inspection of the inlet and the exhaust before the subsequent flight
(Ref. AMM TASK 72-00-00-210-802) .
If there is evidence of foreign object damage (FOD), do an inspection (Ref. AMM TASK 72-00-
00-200-801) .
(b) Identify and correct (if possible) the cause for the EGT overtemperature at the first opportunity
within 5 cycles.
· If a FADEC system fault or hardware problem is confirmed and corrected, then the previous
exceedance is not counted.
(c) Use the applicable troubleshooting Ref. TSM 77-20-00-810-813 .
(d) A maximum of 20 overtemperature conditions in area A is permitted before engine removal.

NOTE: The exceedance limit applies to all exceedances, before and after water wash, and in-
cludes cold and warm engine starts.

(6) Area B :
(a) Make a visual inspection of the inlet and the exhaust before the subsequent flight
(Ref. AMM TASK 72-00-00-210-802) .
If there is evidence of foreign object damage (FOD), do an inspection (Ref. AMM TASK 72-00-
00-200-801) .
(b) Identify and correct (if possible) the cause for the EGT overtemperature at the earliest
opportunity.
· Use the applicable troubleshooting Ref. TSM 77-20-00-810-813 .
· If one or more exceedance occured before in area B ,identify the cause and correct (if
possible) before the next flight Ref. TSM 77-20-00-810-813 .
(c) If the cause of the EGT exceedance cannot be identified, do a borescope inspection of the HPT
blades and stage 1 LPT blades (borescope port S17) (Ref. AMM TASK 72-52-00-290-801) and
(Ref. AMM TASK 72-54-00-290-801) before the next flight.
(d) If the cause of the EGT exceedance has been identified and no more exceedances occur, the
borescope inspection can be deferred for up to 5 cycles.
(e) A maximum of 20 exceedances in areas A and B combined or 10 exceedances in area B is
permitted before the engine must be removed.
(7) Area C :

Print Date: November 02, 2018 Page 11 of 19

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 Customer : ATLAS Manual : AMM
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Rev. Date : Apr 01, 2018
72-00-00-200-803-A - Inspection/Check after
the Engine has Exceeded the Operational Limits

(a) Remove (Ref. AMM TASK 71-00-00-000-801) and (Ref. AMM TASK 71-00-00-400-801) and
return the engine to the shop facility for damage investigation.
(b) One non revenue flight for fly back is permitted before engine removal if there is no damage
beyond the serviceable limits :
. Make a visual inspection of the inlet and the exhaust before the subsequent flight
(Ref. AMM TASK 72-00-00-210-802) .
If there is evidence of foreign object damage (FOD), do an inspection (Ref. AMM TASK 72-00-
00-200-801) .
. Do a borescope inspection of the HPT blades and stage 1 LPT blades (borescope port S17)
(Ref. AMM TASK 72-52-00-290-801) and (Ref. AMM TASK 72-54-00-290-801) before the next
flight.
. Do a troubleshooting for "EGT OVERLIMIT" per Ref. TSM 77-20-00-810-813 .
(8) Reset the EGT max pointer (Ref. AMM TASK 77-00-00-710-802) after you correct the problem.
Subtask 72-00-00-280-059-A
C. Take off power kept for more than 5 minutes.
(1) Make an inspection as required by:
(Ref. Fig. Operational EGT (T495) Limits at Take Off SHEET 1)

** ON A/C 153-159, 161-163, 165-199, 301-349, 351-399

Subtask 72-00-00-280-054-B
D. Checks to be done when abnormal rotation speeds are reached.
(1) Overspeed
(a) The speed limits are as follows:
· fan speed (N1): 104.2 percent
· core speed (N2): 105 percent.
(2) Fan (N1) overspeed inspections
(a) If the fan is operated at speeds from 104.2 percent to 105.3 percent, do an inspection of the
engine as follows:
· examine the available data to understand the reason for the overspeed
· correct the cause
· do a visual inspection of the engine inlet (Ref. AMM TASK 72-23-00-210-801) , fan blades
(Ref. AMM TASK 72-21-00-210-801) , primary exhaust nozzle (Ref. AMM TASK 78-11-10-
210-801) , and stage 5 LPT blades (Ref. AMM TASK 72-54-00-290-801) .
· do a check of the fan rotor for freedom of rotation and shingling of blades
(Ref. AMM TASK 72-21-00-210-801)
· do an inspection of the abradable material in the fan inlet case for rubbing
(Ref. AMM TASK 72-23-00-210-801)
· do a borescope inspection of the stage 5 booster rotor blades (borescope port S05 at 4:30
o'clock location and at the rear of the booster) (Ref. AMM TASK 72-21-00-290-801)
· do a borescope inspection of the stage 1 LPT blades (borescope port S17)
(Ref. AMM TASK 72-54-00-290-801) .
(b) If the fan speed is greater than 105.3 percent, remove the engine and return it to the shop for
overspeed inspection.
(c) If the fan speed has exceeded 104.2 percent, the N1 max pointer must be reset after corrective
action has been performed (Ref. AMM TASK 77-00-00-710-802) .
(3) Core engine (N2) overspeed inspections
(a) If the core engine rotor is operated at speeds from 105 percent to 105.8 percent, do an
inspection of the engine as follows:

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© AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.
 Customer : ATLAS Manual : AMM
Type : A340 Selected applicability : 163-163
Rev. Date : Apr 01, 2018
72-00-00-200-803-A - Inspection/Check after
the Engine has Exceeded the Operational Limits

· do an inspection of the mixer and primary exhaust nozzle for particles.

· do a borescope inspection of the stages 1, 3 and 8 HPC blades (borescope ports S1, S3 and
S8) (Ref. AMM TASK 72-31-00-290-801) .
· do a borescope inspection of the HPT blades (borescope port S17) (Ref. AMM TASK 72-51-
00-290-801) (Ref. AMM TASK 72-52-00-290-801) and (Ref. AMM TASK 72-52-00-290-
802) .
(b) If the core engine rotation speed is greater than 105.8 percent, remove the engine and return it to
the shop for overspeed inspection.
(c) If the core engine rotation speed has exceeded 105.0 percent the N2 max pointer must be reset
after corrective action has been performed (Ref. AMM TASK 77-00-00-710-802) .

** ON A/C ALL
Subtask 72-00-00-280-061-A
E. Checks to be done if the lubrication system is operated out of the limits
(Ref. Fig. Oil Pressure Versus Core Speed (N2) SHEET 1)
(1) Oil pressure in critical zone A lower than 13 psi (0.8963 bar)
(a) If engine operation with no oil or very low pressure does not agree with one of the data which
follow, remove the engine and return it on the shop:
· takeoff power for 10 seconds.
· cruise power for 10 seconds.
· idle (flight or ground) for 30 seconds.
(b) If an engine which is in the time limits given just above, was operated with no oil pressure or very
low pressure do these steps:
· remove all filters, screens, and magnetic chip detector.
· examine them for the presence of unwanted metal particles (Ref. AMM TASK 79-00-00-281-
802)
· if none of those unwanted metal particles are found, do a troubleshooting.
(2) Oil pressure in zone B and/or E.
(a) Do a troubleshooting.
(3) Oil temperature for continuous engine operation:
(a) 284 deg.F (140 deg.C) maximum.
(4) Engine operation with oil temperature between 284 deg.F (140 deg.C) and 311 deg.F (155 deg.C).
(a) Permitted for 15 minutes.
(5) If the oil temperature is higher than 311 deg.F (155 deg.C) do as follows:
(a) Drain and fill the oil system (Ref. AMM TASK 12-13-79-610-801) and (Ref. AMM TASK 12-13-
79-610-803) .
(b) Do a troubleshooting.
(6) After engine operation at unusually high oil temperature, do as follows:
(a) Examine the supply filter and the master chip detector of the lubrication unit for the presence of
metal particles.
(b) If there are metal particles, remove and disassemble the engine for inspection.

CAUTION: ABOVE 0.53 QUART/HR (0.5 LITER/HR) AND UP TO 1.57 QUART/HR (1.5 LITER/HR),
AIRCRAFT DISPATCH IS ALLOWED PROVIDED ENGINE OIL CONSUMPTION PER-
MITS TO FULFILL THE MISSION (10 QUARTS + (ESTIMATED OIL CONSUMPTION
RATE X FLIGHT DURATION)).

Print Date: November 02, 2018 Page 13 of 19

© AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.
 Customer : ATLAS Manual : AMM
Type : A340 Selected applicability : 163-163
Rev. Date : Apr 01, 2018
72-00-00-200-803-A - Inspection/Check after
the Engine has Exceeded the Operational Limits

(7) Oil consumption.

NOTE: During normal engine operation, the average oil consumption rate should not be higher than
0.53 quart/hr (0.5 liter/hr).

NOTE: Oil consumption rate must be based on the average oil consumption over the last 25 flight
hours.

NOTE: Oil consumption can be obtained by the ACMS report (01QH), the servicing report or manual
counting by oil topping.

(a) Above 0.6 quart/hr (0.57 liter/hr) engine oil consumption must be closely monitored and flight
crew must be informed.
(b) Troubleshooting Ref. TSM 79-31-00-810-827 must be performed when the oil consumption rate
is more than 0.8 quart/hr (0.76 liter/hr). No specific inspection is required under 0.8 quart/hr (0.76
liter/hr).
(c) Troubleshooting Ref. TSM 79-31-00-810-827 must also be performed as soon as one of the
following occurs:
· The oil consumption rate, on a given engine, significantly exceeds that of the other operating
engines.
· The oil consumption rate shows a sudden step.
· The oil consumption rate indicates a continuous increasing trend.
(d) The maximum SERVICEABLE oil consumption rate is limited to 1.57 quart/hr (1.5 liter/hr):
· Troubleshooting Ref. TSM 79-31-00-810-827 must be performed as soon as the oil
consumption rate OVERSHOOT 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 is to be replaced (Ref. AMM TASK 71-00-00-000-801) and
(Ref. AMM TASK 71-00-00-400-801) .
Subtask 72-00-00-210-057-A
F. Procedure to be done after an IFSD or an engine windmilling.

NOTE: Subsequent ferry flights after an engine windmilling incident can not exceed a total of 21 hours
which includes the flight time of the windmilling event.

(1) Dry-out the engine if you can not restart within 24 hours (Ref. AMM TASK 72-00-00-100-801) .

NOTE: If there will be multiple ferry flights which must not exceed the 21 hour recommendation, dry-
out the engine between ferry flights (Ref. AMM TASK 72-00-00-100-801) .

(2) If necessary, do the engine preservation (Ref. AMM TASK 72-00-00-600-808) .

Subtask 72-00-00-210-058-A
G. Inspections after a Hard Landing or Hard Overweight Landing

NOTE: The inspection must be do if the aircraft sustained a hard landing or hard overweight landing. For
hard landing and hard overweight landing definition refer to (Ref. AMM TASK 05-51-11-200-802) .

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

Print Date: November 02, 2018 Page 14 of 19

© AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.
 Customer : ATLAS Manual : AMM
Type : A340 Selected applicability : 163-163
Rev. Date : Apr 01, 2018
72-00-00-200-803-A - Inspection/Check after
the Engine has Exceeded the Operational Limits

· 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.

If the Phase 1 inspection shows no deterioration, no further

examination is necessary.
If Phase 1 shows deterioration, then Phase 2 must be done.
If Phase 2 shows deterioration, then phase 3 must be done.

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.

WARNING: USE CARE TO PREVENT INJURY. DO NOT TRY MANUAL ROTATION OF THE FAN
ROTOR WITHOUT HEAVY PROTECTIVE GLOVES. MAKE SURE OF SAFE, FIRM
FOOTING.

(a) Phase 1
1 Turn the fan rotor with your hand. Make sure that there is no bearing roughness, unusual
noises and binding.
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-
00-210-801) .
3 Do a visual inspection of the fan frame assembly (Ref. AMM TASK 72-23-00-210-
801) , (Ref. AMM TASK 72-23-00-280-801) , (Ref. AMM TASK 72-23-00-280-802) and
(Ref. AMM TASK 72-23-00-210-805) .
4 Do a visual inspection of the turbine frame assembly (Ref. AMM TASK 72-56-00-200-801) .
5 Do a visual inspection of the accessory and hardware attachments for metal fractures or
excessive distortion.
6 Do a visual inspection of piping connections for leaks.
7 Do a visual inspection of lines and tubing for possible interferences.
8 Do a visual inspection of engine mounts, forward and aft (Ref. AMM TASK 71-21-11-210-
801) and (Ref. AMM TASK 71-22-11-210-801) ..
(b) Phase 2, if you find deterioration in the above tasks:
1 Do a borescope inspection of the HPC blades (Ref. AMM TASK 72-31-00-290-801) .
2 Do a borescope inspection of the LPC blades (Ref. AMM TASK 72-21-00-290-801) .
3 Do a check of the electrical master chip detector for particles (Ref. AMM TASK 79-00-00-
281-801) , do a check of the fwd sump, aft sump, accessory gearbox and transfer gearbox
Scavenge screens (Ref. AMM TASK 79-00-00-281-802) , do a check of the antisiphon
device (Ref. AMM TASK 79-00-00-280-801) and do a operational check of the electrical
magnetic chip detector (Ref. AMM TASK 79-00-00-710-804) .
· If you do not find metal particles, do the inspection prior to each flight during one week,
then each two flights prior to departure during one week.

Print Date: November 02, 2018 Page 15 of 19

© AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.
 Customer : ATLAS Manual : AMM
Type : A340 Selected applicability : 163-163
Rev. Date : Apr 01, 2018
72-00-00-200-803-A - Inspection/Check after
the Engine has Exceeded the Operational Limits

(c) Phase 3, if you find deterioration in the above tasks, engine removal can be necessary
(Ref. AMM TASK 71-00-00-000-801) .
Subtask 72-00-00-210-059-A
H. Inspection After Stall
(1) General
(a) If a stall or suspected stall has occurred during engine start or ground run, ensure wind
envelop limit was respected (Ref. AMM TASK 71-00-00-710-801) , do the inspections and
troubleshooting per Ref. TSM 80-00-00-810-835 .
(b) If a stall or suspected stall has occurred, do the inspections and troubleshooting per Ref.
TSM 71-00-00-810-874 .
(2) Do visual inspection/checks of the fan rotor and abradable material (Ref. AMM TASK 72-21-00-210-
801) (Ref. AMM TASK 72-23-00-210-801) .
(3) Do borescope inspections of these items:
(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 (1337.00 deg.F) was exceeded, borescope inspect
HPT blades and stage 1 LPT blades (borescope port S17) (Ref. AMM TASK 72-52-00-290-
801) and (Ref. AMM TASK 72-54-00-290-801) .
(Ref. Fig. Operational EGT (T495) Limits for Ground Starting and Sub-Idle
Operation SHEET 1)
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 72-31-00-290-801) .
(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 72-52-00-290-801) and (Ref. AMM TASK 72-54-00-290-801) .
(Ref. Fig. Operational EGT (T495) Limits at Take Off SHEET 1)
2 If the cause of the stall is not known, borescope inspect stage 5 booster blades
(borescope port S0) stages 1, 3 and 8 HPC blades (borescope ports S1, S3 and S8).
(Ref. AMM TASK 72-21-00-290-801) and (Ref. AMM TASK 72-31-00-290-801) .
(c) If the stall occurred during start in cold weather operation (Snow/Icing) and damages have been
found on the HPC:
· Do a borescope inspection of the HPC on the three other engines.
· Previous experience has shown that IGB nut looseness can occur in such situation. Contact
CFM for further recommendations.
Subtask 72-00-00-210-060-A
J. Inspection after in flight excessive load factor due to turbulence or maneuver or in excess of VMO/MMO
(1) General:
(a) If you think that an engine has undergone too much G loading during transportation, you must
proceed to the following inspections.
(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.

Print Date: November 02, 2018 Page 16 of 19

© AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.
 Customer : ATLAS Manual : AMM
Type : A340 Selected applicability : 163-163
Rev. Date : Apr 01, 2018
72-00-00-200-803-A - Inspection/Check after
the Engine has Exceeded the Operational Limits

If the Phase 1 inspection shows no deterioration, no further

examination is necessary.
If Phase 1 shows deterioration, then Phase 2 must be done.
If Phase 2 shows deterioration, then phase 3 must be done.

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.

WARNING: USE CARE TO PREVENT INJURY. DO NOT TRY MANUAL ROTATION OF THE FAN
ROTOR WITHOUT HEAVY PROTECTIVE GLOVES. MAKE SURE OF SAFE, FIRM
FOOTING.

(a) Phase 1
1 Turn the fan rotor with your hand. Make sure that there is no bearing roughness, unusual
noises and binding.
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-
00-210-801) .
3 Do a visual inspection of the fan frame assembly (Ref. AMM TASK 72-23-00-210-
801) , (Ref. AMM TASK 72-23-00-280-801) , (Ref. AMM TASK 72-23-00-280-802) ,
(Ref. AMM TASK 72-23-00-210-804) and (Ref. AMM TASK 72-23-00-210-805) .
4 Do a visual inspection of the turbine frame assembly (Ref. AMM TASK 72-56-00-200-801) .
5 Do a visual inspection of the accessory and hardware attachments for metal fractures or
excessive distortion.
6 Do a visual inspection of piping connections for leaks.
7 Do a visual inspection of 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 72-31-00-290-801) .
2 Do a borescope inspection of the LPC blades (Ref. AMM TASK 72-21-00-290-801) .
3 Do a check of the electrical master chip detector for particles (Ref. AMM TASK 79-00-00-
281-801) , do a check of the fwd sump, aft sump, accessory gearbox and transfer gearbox
Scavenge screens (Ref. AMM TASK 79-00-00-281-802) , do a check of the antisiphon
device (Ref. AMM TASK 79-00-00-280-801) and do a operational check of the electrical
magnetic chip detector (Ref. AMM TASK 79-00-00-710-804) .
· If you do not find metal particles, do the inspection prior to each flight during one week,
then each two flights prior to departure during one week.
(c) Phase 3, if you find deterioration in the above tasks, engine removal can be necessary
(Ref. AMM TASK 71-00-00-000-801) .

** ON A/C ALL

EMB SB 78-4018 for A/C 051-051, 101-102, 153-159, 161-163, 201-202, 252-253
Subtask 72-00-00-210-083-B

Print Date: November 02, 2018 Page 17 of 19

© AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.
 Customer : ATLAS Manual : AMM
Type : A340 Selected applicability : 163-163
Rev. Date : Apr 01, 2018
72-00-00-200-803-A - Inspection/Check after
the Engine has Exceeded the Operational Limits

K. High N1 Vibration Advisory, or Suspected FOD, or Abnormal Vibration Perceived by the crew, without
Advisory Indication.
(1) Do a detailed visual inspection of pivoting door latches (Ref. AMM TASK 78-31-19-210-801) .
(2) Do a dye penetrant inspection of PRE SB RA34078-37 adapter ring outer flanges
(Ref. AMM TASK 78-32-45-230-801) .

NOTE: A dye penetrant inspection of POST SB RA34078-37 adapter ring outer flanges is not re-
quired.

(3) Do a detailed visual inspection of the latch fitting of the pivoting doors (Ref. AMM TASK 78-32-41-
210-801) .
(4) If the engine thrust reverser was de-actived during the same flight:
(a) replace the 4 lock-out bolts (Ref. AMM TASK 78-30-00-040-802) . The replacement lock-out
bolts can be taken from a spare thrust reverser.
(5) Do a visual inspection of the 6/12 O'clock "J" ring, the upper and lower lockout fittings, and the
adjacent structure (Ref. AMM TASK 78-32-11-210-801) .

** ON A/C ALL
5. Close-up
Subtask 72-00-00-410-053-A
A. 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 78-36-00-410-801)
(a) FOR 4000EM1 (ENGINE-1)
417AL, 418AR
(b) FOR 4000EM2 (ENGINE-2)
427AL, 428AR
(c) FOR 4000EM3 (ENGINE-3)
437AL, 438AR
(d) FOR 4000EM4 (ENGINE-4)
447AL, 448AR
Subtask 72-00-00-440-052-A
B. Make the thrust reverser serviceable (Ref. AMM TASK 78-30-00-440-801)
Subtask 72-00-00-865-055-A
C. Remove the safety clip(s) and the tag(s) and close this(these) circuit breaker(s):

PANEL DESIGNATION FIN LOCATION

FOR FIN 4000EM1 (ENGINE-1)
722VU FADEC B ENG 1 13KS1 K46
742VU FADEC A ENG 1 12KS1 N74
FOR FIN 4000EM2 (ENGINE-2)
722VU FADEC B ENG 2 13KS2 D43
742VU FADEC A ENG 2 12KS2 Q73
FOR FIN 4000EM3 (ENGINE-3)
722VU FADEC B ENG 3 13KS3 K47

Print Date: November 02, 2018 Page 18 of 19

© AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.
 Customer : ATLAS Manual : AMM
Type : A340 Selected applicability : 163-163
Rev. Date : Apr 01, 2018
72-00-00-200-803-A - Inspection/Check after
the Engine has Exceeded the Operational Limits

PANEL DESIGNATION FIN LOCATION

742VU FADEC A ENG 3 12KS3 Q74
FOR FIN 4000EM4 (ENGINE-4)
722VU FADEC B ENG 4 13KS4 D44
742VU FADEC A ENG 4 12KS4 N75
Subtask 72-00-00-410-059-A
D. Close Access
(1) Close the protective door of the AC/DC emergency power center 740VU.
(2) Close the access door 811.
(3) Close the fan cowl doors: (Ref. AMM TASK 71-13-00-410-801)
(a) FOR 4000EM1 (ENGINE-1)
415AL, 416AR
(b) FOR 4000EM2 (ENGINE-2)
425AL, 426AR
(c) FOR 4000EM3 (ENGINE-3)
435AL, 436AR
(d) FOR 4000EM4 (ENGINE-4)
445AL, 446AR.
(4) Remove the access platform(s).
Subtask 72-00-00-862-052-A
E. De-energize the ground service network
(Ref. AMM TASK 24-42-00-862-801) .

End of document

Print Date: November 02, 2018 Page 19 of 19

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