(4)
AMM 72-33-02/801, Fan Exit Case and Vane
(5)
AMM 78-31-00/201, Thrust Reverser System
(6)
IPC 72-33-02 Fig. 5
B.
Access
(1)
Location Zone
412 Engine No. 1
422 Engine No. 2
432 Engine No. 3
442 Engine No. 4
(2)
Access Panel 415 and 416 Thrust Reverser Halves - Engine No. 1 425 and 426 Thrust Reverser Halves - Engine No. 2 435 and 436 Thrust Reverser Halves - Engine No. 3 445 and 446 Thrust Reverser Halves - Engine No. 4
EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. ú
72-33-02
ALL ú ú N01 Page 601 ú Feb 10/94
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
////////////////////////A / PW4000 SERIES /747-400 / ENGINES/MAINTENANCE MANUAL ////////////////////////
C. Prepare for the Procedure
S 046-025-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 OR DAMAGE TO EQUIPMENT.
(1)
Do the deactivation procedure for the thrust reverser for ground maintenance (AMM 78-31-00/201).
S 016-026-N00
(2)
Open the fan cowl panels (AMM 71-11-04/201).
S 016-027-N00
(3)
Open the core cowl panels (AMM 71-11-06/201).
S 016-018-N00
WARNING: OBEY THE INSTRUCTIONS IN THE PROCEDURE TO OPEN THE THRUST
_______ REVERSERS. IF YOU DO NOT OBEY THE INSTRUCTIONS, INJURIES TO PERSONS OR DAMAGE TO EQUIPMENT CAN OCCUR.
(4)
Open the thrust reversers (AMM 78-31-00/201).
D.
Procedure
S 216-028-N00
(1)
Visually compare the damage you find (on areas other than the vanes) to the damage limits in Table 601 (Fig. 601).
(a)
If you find damage that could cause a crack in a repair weld or a permitted dent, do a fluorescent penetrant inspection with ultra high sensitivity penetrant for cracks. (AMM 70-31-01/201).
EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. ú
72-33-02
ALL ú ú N01 Page 602 ú Oct 10/97
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
~............................................................................... | TABLE 601 | | INSPECTION OF AREAS OTHER THAN THE VANES | ................................................................................. | Examine | Damage Limits | Necessary Procedure | .................................................................................
| ENGINES | | |
| PRE-PW-SB | | |
| 72-262; | | |
| Lockwire: | None are permitted | Repair the damaged lockwire |
| missing, | | immediately (AMM 72-33-02/801) |
| loose, or | | |
| broken | | |
................................................................................. | ENGINES | | | | POST-PW-SB | | | | 72-262; | | | | Nuts: | None are permitted | Replace the nuts that are missing | | missing, | | and tighten the nuts that are loose | | or loose | | (AMM 72-33-02/801). | ................................................................................. | Flanges B1 | | If the damage is less than the limits,| | and B2, | | repair the flange in less than 50 | | damaged | | hours. | | corners: | | | | Index 1 | 0.060 inch (1.542 mm), | Damage that is more than the limits | | | maximum, 2 locations | is not permitted. | | | | | | Index 2 | 0.060 inch (1.524 mm), | | | | maximum | | | | | | ................................................................................. | Index 3 | This must not be less | | | | than ten times Index 2 | | | ................................................................... | Circumferen-| 1.000 inch (25.400 mm) | Damage that is more than the limits | | tial length | maximum | is not permitted. | | of each | | | | incident | | |
EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. ú
中國航空網 m.k6050.com
航空翻譯 www.aviation.cn
本文鏈接地址：747-400 AMM 飛機維護手冊 發動機 ENGINE 2(15)
