R (3) Do a check for evidence of overheat on the inner wall of both
R reverser cowls. If hot spots are visible, do a check for leaks in the
R area next to the spot.

R (4) Do a check for excessive presence of black deposit streaks on the hot
R section of the engine. If black streaks are visible, do a check for
R leaks in the area next to the spot.

R (5) Make sure that the 12 o'clock EGT probe deflector is correctly
R installed.

R NOTE : The purpose of this deflector is to avoid EGT probe hot air

____ R impingement onto the nacelle temperature sensor.
R (6) Do a check of the cooling holes in the inner wall of the reverser R cowls for blockage.
R (7) Do a check for proper installation of all engine and bleed valves R located in the core compartment.
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R (8) Do a visual check for cracks in the combustor casing, HP compressor
R casing and turbine casing.

R (9) Do a visual inspection of the nacelle temperature sensor and wiring
R for any signs of external damage. Do a check on connectors of the
R nacelle temperature sensor (13KS2) and associated harness for
R contamination/corrosion and for damaged pins. Clean repair wiring or
R replace the sensor as required (Ref. AMM TASK 75-41-15-000-041) and
R (Ref. AMM TASK 75-41-15-400-041).

R (10) If nothing is found:
R - do a check for correct installation and sealing of the EGT probes
R (Ref. AMM TASK 77-21-10-200-002).

R (11) Do a check for correct installation and sealing of the TCC sensor(s)
R (Ref. AMM TASK 73-21-70-400-001):
R - replace the gasket seal if suspect.

R (12) Do a check for correct torquing and sealing of the borescope plugs
R located on the HP compressor, HP and LP turbines and combustor case.

R (13) Do a check for correct installation and sealing of the T3 sensor on
R the combustor case (Ref. AMM TASK 77-23-10-400-002):
R - replace the gasket seal if suspect.

R (14) Do a check for correct torquing and sealing of the 2 LPT pipes fitted
R at 11:30 and 2:30 on the HPT case:
R - replace the gasket seal if suspect.

R (15) Do a check for correct torquing and sealing of the cover plates and
R bleed bias adaptor installed on the combustor case just upfront of
R the fuel manifold:
R - replace the gasket seal if suspect.

R (16) If no evidence of hot air leaks from the engine is found:
R - do one of the following procedures for leakage identification
R (leakage identification with engine at idle using aluminum foil or
R leakage identification with engine motoring or leakage
R identification with engine at idle using leak developer).
R

R B. Leakage Identification at Idle using Aluminum Foil.

R NOTE : This procedure is mainly applicable if you suspect a leak located

____ R at a piping or duct joint.
R (1) Install aluminum foils around all pneumatic bleed ducts and engine R air piping connections.
R (2) Close the thrust reverser doors (Ref. AMM TASK 78-36-00-410-040).
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R (3) Do a minimum idle leak check (Ref. AMM TASK 71-00-00-710-006).
R - On the AIR COND panel 30VU, push the ENG 2 BLEED pushbutton switch
R (4HA2) to operate the engine bleed system.
R - On the ANTI-ICE section of the panel 25VU, push the ANTI ICE/ENG 2
R pushbutton switch (2DN2) to operate the engine anti-ice system.

R (4) Stop the engine (Ref. AMM TASK 71-00-00-710-028).

R (5) Open the thrust reverser doors (Ref. AMM TASK 78-36-00-010-040).

R (6) Do a visual inspection of the aluminum foil condition. Correct the
R hot air leaks where applicable.

R (7) If no leak identified:
R - repeat the inspection of the aluminum foils after a few flights.

R C. Leakage Identification with Engine Motoring.

R WARNING : AVOID PHYSICAL CONTACT WITH THE HARDWARE LOCATED IN THE CORE

_______ R COMPARTMENT (MAINLY ON THE TOP AREA) IF THE ENGINE IS STILL R HOT. ENGINE HARDWARE MAY BE VERY HOT IN THIS AREA IF THE R TROUBLE SHOOTING IS PERFORMED WITHIN 2 HOURS AFTER AN ENGINE R SHUTDOWN.
　
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