A

(0991) Fan Exit Liner Segment (Inner Rear) Inspection
Figure 601
E01219
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 ALL  ú ú N01 Page 603 ú Jun 10/94
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
////////////////////////A / PW4000 SERIES /747-400 / ENGINES/MAINTENANCE MANUAL ////////////////////////
~............................................................................... | INSPECTION FOR NICKS, DENTS, AND OTHER SURFACE DAMAGE | | Table 602 | ................................................................................. | CONDITION | | NECESSARY | | OBSERVED | DAMAGE LIMITS | PROCEDURE | ................................................................................. | Nicks and | More than 1.000 inch (25.400 mm) in width or length, | Replace | | Gouges | or more than 0.030 inch (0.762 mm) in depth, or less | before the| | | than 2.000 inches (50.80 mm) apart from other damage,| subsequent| | | or there are more than five (5) nicks and gouges. | flight. | ................................................................................. | Dents with | More than 0.030 inch (0.762 mm) in depth or on more | Replace | | Rounded | than 10% of the surface area | Within 50 | | Bottoms | | hours | .................................................................................
 | Cracks | More than 1.000 inch (25.400 mm) in length or less  | Replace  |
 |  | than 0.500 inch (12.700 mm) from the center of an  | Within 50 |
 |  | attachment rivet screw or bolt  | hours  |

 ................................................................................. | Areas of | Between 1.000 and 2.500 inches (25 and 63.5 mm) in | Replace | | broken or | width or length, or more than 0.030 inch (0.762 mm) | Within 50 | | fuzzy stray| in depth, or less than 2.000 inches (50.800 mm) from | hours | | fibers | other damage | | | .................................................................... | | More than 2.500 inches (63.500 mm) in width or length| Replace | | | |Immediately| ................................................................................. | Holes or | None Permitted. | Replace in| | Punctures | | 50 hours | ................................................................................. | No Bond of | More than 0.500 inch (12.700 mm) in length or width. | Replace in| | a Wire | | 50 hours | | Cloth Patch| | | ................................................................................. | Leading | More than 0.500 inch (12.700 mm) in length or width | Replace in| | Edge | (of a dull or rough surface finish, visible fibers) | 50 hours | | Erosion | | | 2............…......................................................…...........1
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BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
~............................................................................... | INSPECTION FOR DELAMINATION | | Table 603 | ................................................................................. | DELAMINATION | EXAMINE AFTER | REPLACE WITHIN | REPLACE BEFORE YOU | | DIMENSION | EACH 50 HOURS | 50 HOURS | OPERATE THE ENGINE | ................................................................................. | Width or | Not more than 1.000 | Between 1.000-2.500| More than 2.500 | | Length | inch (25.400 mm) | inches (25-64 mm) | inches (63.500 mm) | ................................................................................. | Depth | Mot more than 0.030 | More than 0.030 | -----| | | inch (0.762 mm) | inch (0.762 mm) | | ................................................................................. | Distance from| More than 2.000 | Less than 2.000 | -----| | other damage | inches (50.800 mm) | inches (50.800 mm) | | 2..............….....................…....................….....................1
 S 416-007-N00
 WARNING: OBEY THE INSTRUCTIONS IN THE PROCEDURE TO CLOSE THE THRUST
_______ REVERSERS. IF YOU DO NOT OBEY THE INSTRUCTIONS, INJURIES TO PERSONS AND DAMAGE TO EQUIPMENT CAN OCCUR.
 (6)  
Close the thrust reverser (AMM 78-31-00/201).

 S 416-008-N00

 (7)  
Close the core cowl panel (AMM 71-11-06/201).
　
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