FORWARD VIEW OF FLANGE B1 OR
REAR VIEW OF FLANGE B2
L-A7755 (0000)
Fan Exit Case Inspection Figure 601 (Sheet 2)
D20319
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ALL ú ú N01 Page 607 ú Jun 10/95
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
////////////////////////A / PW4000 SERIES /747-400 / ENGINES/MAINTENANCE MANUAL ////////////////////////
S 216-029-N00
(3) Visually compare the damage you find on the vanes with the limits in
Table 602 (Fig. 602). ~............................................................................... | TABLE 602 | | INSPECTION OF THE FAN EXIT VANES | ................................................................................. | Examine | Damage Limits | Necessary Procedure (AMM 72-33-02/801) | .................................................................................
| Area A: | | No procedure is necessary, but you |
| Chord depth | 0.100 inch (2.540 mm) | must examine it again in less than 50 |
| (axial | maximum * | hours and at the next "A" check for |
| length)| | deterioration. If there is deteriora-|
| | | tion, repair the vane with a small |
| | | patch in less than 50 hours. |
| | | |
| | More than 0.100 inch | Remove the damaged fan exit vane in |
| | (2.54 mm) in depth.* | less than 50 hours. |
| | | |
................................................................................. | Area B: | | | | Chord depth | 0.100 inch (2.540 mm) | No procedure is necessary, but you | | (axial | maximum * | must examine it again in less than 50 | | length)| | hours and at the next "A" check for | | | | deterioration. If there is deteriora-| | | | tion, repair the vane with a small | | | | patch in less than 50 hours. | | | | | | | Between 0.100-0.375 | Repair the vane with a large patch in | | | inch (2.5-9.5 mm) in | less than 50 hours. | | | depth.* | | | | | | | | More than 0.375 inch | Remove the damaged vane immediately. | | | (9.525 mm) in depth.* | | | | | | | Radial | More than 0.750 inch | Remove the damaged vane immediately. | | Length | (19.050 mm) in length | | | | | | | Quantity | No damage is more than| No procedure is necessary. | | of damage | 0.100 inch (2.540 mm) | | | on each | in depth.* | | | vane | | | | | One (1) is more than | Repair the vane with a large patch in | | | 0.100 inch (2.540 mm) | less than 50 hours. | | | in depth.* | | | | | | | | Two or more that are | Remove the vane in less than 50 hours.| | | more than 0.100 inch | | | | (2.54 mm) in depth.* | | | | | |
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ALL ú ú N01 Page 608 ú Jun 18/01
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
~............................................................................... | TABLE 602 | | INSPECTION OF THE FAN EXIT VANES | ................................................................................. | Examine | Damage Limits | Necessary Procedure (AMM 72-33-02/801) | .................................................................................
| Area C for: | Broken composite | Repair the vane with a small patch |
| Nicks, | fibers | in less than 50 hours. |
| dents, | | |
| pits, and | More than 0.030 inch | Remove or replace the vane in less |
| chips | (0.762 mm) in depth | than 50 hours. |
| | | |
| | More than 0.300 inch | Remove or replace the vane in less |
| | (7.620 mm) in width | than 50 hours. |
| | or height | |
................................................................................. | Area D for: | Chord decreased by | Repair the vane with a small patch in | | Damage | not more than | less than 50 hours. | | that | 0.150 inch (3.810 mm) | | | decreased | | | | the chord | Chord decreased by | Remove or replace the vane in less | | length | more than 0.150 inch | than 50 hours. | | | (3.810 mm) | | ................................................................................. |Delamination | More than 1.0 square | Remove or replace the vane in less | | | inch (645. square mm) | than 50 hours. | | | in area | | ................................................................................. |Delamination/| Full axial width | Replace leading edge up to full | | Missing | both sides | span. | | Wire Mesh | up to full span. | | ................................................................................. | Erosion of | Up to 3.00 inch | Replace wire mesh leading edge up to | | Leading | (76.2 mm) in from OD | the full span. | | Edge | | | | | Beyond 3.00 inch | Install metal shield over vane | | | (76.2 mm) in from OD | leading edge. | | | and ID platform up to | Replace vane at next shop visit. | | | 0.150 inch (3.81 mm) | | | | maximum | | | | | | | | Beyond 3.00 inch | Install metal shield over vane | | | (76.2 mm) in from OD | leading edge. | | | and ID platform up to | Replace vane at next shop visit. | | | 0.150 inch (3.81 mm) | | | | maximum | | 中国航空网 www.aero.cn 航空翻译 www.aviation.cn 本文链接地址：747-400 AMM 飞机维护手册 发动机 ENGINE 2(17)
