D.
Repair the Damaged Corners on the B1 and B2 Flanges (Fig. 805). S 218-089-N00
(1)
Find the damaged B1 and B2 Flanges that can be repaired
(AMM 72-33-02/601).
NOTE: All damage must be repaired immediately.
____
S 358-090-N00
(2) Make the damaged corners, on the B1 and B2 Flanges, smooth
(Table 801).
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~............................................................................... | TABLE 801 | | FLANGES B1 and B2 REPAIR LIMITS | ................................................................................. | Examine | Repair Limits | ................................................................................. | Damaged Corners: | | | Index 1 | 0.060 inch (1.542 mm), maximum, 2 locations | | ................................................ | Index 2 | 0.060 inch (1.524 mm), maximum | | ................................................ | Index 3 | This must not be less than ten times Index 2 | | ................................................ | Circumferential length of | 1.000 inch (25.400 mm) maximum | | each incident | | | ................................................ | Total Circumferential length | 24.000 inches (609.600 mm) maximum | | of all damage on each Flange | | 2................................…..............................................1
S 238-091-N00
(3)
After you repair the damaged area, examine it with high sensitivity penetrant.
(a)
No cracks are permitted.
S 378-092-N00
(4)
Apply anodize touch-up solution to the repaired areas (AMM 70-42-02/201).
E.
Put the Airplane Back to Its Usual Condition
S 418-093-N00
WARNING: OBEY THE INSTRUCTIONS IN THE PROCEDURE TO CLOSE THE THRUST
_______ REVERSERS. IF YOU DO NOT OBEY THE INSTRUCTIONS, INJURIES TO PERSONS OR DAMAGE TO EQUIPMENT CAN OCCUR.
(1)
Close the thrust reversers (AMM 78-31-00/201).
(2)
Close the fan cowl panels (AMM 71-11-04/201).
(3)
Close the core cowl panels (AMM 71-11-06/201).
S 448-096-N00
(4)
Do the activation procedure for the thrust reversers (AMM 78-31-00/201).
S 418-094-N00
S 418-095-N00
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////////////////////////A / PW4000 SERIES /747-400 / ENGINES /MAINTENANCE MANUAL ////////////////////////
SEE B
SEE A
A
OUTER
DIAMETER
BASE
A A
CORNER
LIFTED APPLY THAT IS
CORNER SEALANT GONE
HERE
FILL THIS
AREA WITH
SEALANT
INNER A-A
DIAMETER
BASE
BASE AND VANE ASSEMBLY (EXAMPLE)
B
Fan Exit Case and Vane Repair (Repair of Damaged Bases)
Figure 804
D20363
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TASK 72-33-02-728-211-N00
7. Repair Of The Fan Exit Vane Leading Edge With Tape
__________________________________________________
A. General
(1)
This repair should be applied if the fan exit guide vane leading edge (SST Wiremesh Weave) is loose, broken, or missing due to service damage.
(2)
Use this repair only if leading edge damage is 0.300 inch (7.620 mm) of the vane airfoil chord or less.
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本文链接地址：747-400 AMM 飞机维护手册 发动机 ENGINE 2(26)
