S 416-007-N00
(7)
Close the core cowl panel (AMM 71-11-06/201).
S 416-008-N00
(8)
Close the fan cowl panel (AMM 71-11-04/201).
S 446-009-N00
(9)
Do the activation procedure for the thrust reverser
(AMM 78-31-00/201).
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COMPRESSOR INTERMEDIATE CASE - INSPECTION/CHECK
_______________________________________________
1. General
_______
A. This procedure gives the steps to do the inspection of the compressor intermediate case.
B. The compressor intermediate case is aft of the fan case and forward of the HPC (High Pressure Compressor).
C. You can open each half of the thrust reverser to get access to the compressor intermediate case.
TASK 72-34-07-206-011-N00
2. Compressor Intermediate Case Inspection
_______________________________________
A. General
(1)
This task examines two areas:
(a)
The bracket assemblies which attach the aft edges of the intermediate case fairings (outer) to the outer circumference of the intermediate case.
(b)
The E Flange bolts which attach the intermediate case to the HPC.
B.
References
(1)
AMM 71-11-04/201, Fan Cowl Panel
(2)
AMM 71-11-06/201, Core Cowl Panel
(3)
AMM 78-31-00/201, Thrust Reverser Opening
C.
Access
(1)
Location Zone
412 Engine 1 - LPC Intermediate Case
422 Engine 2 - LPC Intermediate Case
432 Engine 3 - LPC Intermediate Case
442 Engine 4 - LPC Intermediate Case
D.
Do the Inspection of the compressor intermediate case.
S 046-001-N00
WARNING: DO THE DEACTIVATION PROCEDURE TO PREVENT THE OPERATION OF THE
_______ THRUST REVERSER. THE ACCIDENTAL OPERATION OF THE THRUST REVERSER CAN CAUSE INJURIES TO PERSONS AND DAMAGE TO EQUIPMENT.
(1)
Do the deactivation procedure for the thrust reverser for ground maintenance (AMM 78-31-00/201).
(2)
Open the fan cowl panels (AMM 71-11-04/201).
(3)
Open the core cowl panels (AMM 71-11-06/201).
S 016-002-N00
S 016-003-N00
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BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
////////////////////////A / PW4000 SERIES /747-400 / ENGINES/MAINTENANCE MANUAL ////////////////////////
S 016-004-N00
WARNING: OBEY THE INSTRUCTIONS IN THE PROCEDURE TO OPEN THE THRUST
_______ REVERSERS. IF YOU DO NOT OBEY THE INSTRUCTIONS, INJURIES TO PERSONS AND DAMAGE TO EQUIPMENT CAN OCCUR.
(4)
Open the thrust reversers (AMM 78-31-00/201).
S 226-006-N00
(5)
Compare the damage that you find on the compressor intermediate case with the limits in Table 601.
(a)
If the damage to the intermediate case is more than the limits in Table 601, remove the engine before the subsequent flight.
~............................................................................... | VISUAL INSPECTION OF THE COMPRESSOR INTERMEDIATE CASE | | Table 601 | ................................................................................. | AREA: CONDITION OBSERVED | DAMAGE LIMITS | ................................................................................. | Brackets: Wear or galling | No more than 0.250 inch (6.350 mm) in width, | | on the surfaces which touch | 0.015 inch (0.381 mm) in depth, and 24.00 inch | | the nacelle | (609.600 mm) in length | ................................................................................. | Rivets/Screws which attach | No damage is permitted | | the brackets to the inter-| | | mediate case (screws are on | | | ENGINES POST-PW-SB 72-264) | | ................................................................................. | E Flange: Bolts that are | No more than one (1) bolt that is missing. | | missing | | ................................................................................. | External skin for scratches,| Any amount less than 6.00 inches (152.40 mm) | | nicks and dents | maximum length and 0.012 inch (0.305 mm) | | | maximum depth and 1.00 inch (25.40mm) | | | minimum separation from other similar damage. | | | | | | Blends for damage below the handling pads at | | | 3 and 9 o'clocl positions can not extend into | | | the fillet radius. | 2.............................….................................................1
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