72-33-01
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BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
(6) S 096-007-N00Remove the protective mats from the inlet cowl.
(7) S 866-008-N00Remove the DO-NOT-OPERATE tags from the fuel control switches.
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BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
FRONT FAN CASE - REPAIRS
________________________
1. General
_______
A. This procedure has three repairs for the duct segments of the front fan case:
(1)
The repair of large holes,
(2)
The repair of cracks,
(3)
The repair of surface damage.
B.
The inlet cowl is attached to the front fan case. The front fan case is around the outer circumference of the fan blades.
C.
You can open the fan cowl panels, and remove the inlet cowl and the 1st-stage fan blades to get access to the front fan case.
TASK 72-33-01-308-001-N00
2. Repair of Large Holes in the Duct Segment
_________________________________________
A. Consumable Materials
(1)
G00000 Tape - Magic Mending
(2)
G00842 Cheesecloth - Unsized
(3)
A00000 Compound - Potting (PWA 603)
(4)
B00148 - Solvent, Methyl Ethyl Ketone (MEK) (PMC 1820)
(5)
B00143 - Solvent, Trichlorotriflourothane (PMC 9087)
B.
References
(1)
AMM 72-31-02/401, 1st-Stage Fane Blades
C.
Access
(1)
Location Zone
412 Engine 1 - Front Fan Case
422 Engine 2 - Front Fan Case
432 Engine 3 - Front Fan Case
442 Engine 4 - Front Fan Case
(2)
Access Panel
413 and 414 Fan Cowl Panels - Engine 1
423 and 424 Fan Cowl Panels - Engine 2
433 and 434 Fan Cowl Panels - Engine 3
443 and 444 Fan Cowl Panels - Engine 4
D.
Repair the Large Holes in a Duct Segment.
S 018-002-N00
(1)
If you cannot get acces to the damage, remove the 1st.stage fan blades (AMM 72-31-02/401).
(2)
Refer to the limits in Table 801 and Fig. 801 to do the repair.
S 348-003-N00
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////////////////////////A / PW4000 SERIES /747-400 / ENGINES/MAINTENANCE MANUAL ////////////////////////
~............................................................................... | Table 801 | | Large Hole Repair Limits | ................................................................................. | Type of Damage | Area A | Area B | Area C | ................................................................................. |1)Total Arc Length,| 6 inches | 6 inches | 6 inches | | on Each Segment |(152.4 mm) maximum |(152.4 mm) maximum |(152.4 mm) maximum | | ............................................................. | Total Arc Length,| | 15 inches | | | on All Segments | |(381.0 mm) maximum | | ................................................................................. |2) Circumferential | | 12 inches | | |separation between | | (304.8 mm) | | | incidents | | minimum | | ................................................................................. |3) Diameter | 0.125 inch | 0.125 inch | 0.125 inch | | |(3.175 mm) minimum |(3.175 mm) minimum |(3.175 mm) minimum | .................................................................................
|4)Material that You| 0.5 inch | 0.5 inch | 0.5 inch |
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本文链接地址：747-400 AMM 飞机维护手册 发动机 ENGINE 2(9)
