weight) Thickening Agent (PWA 424-1 or 424-2) to the Adhesive Paste Epoxy (P08-025). 2) Mix the compound fully.

 (c)  
Apply the epoxy mixture on both sides of the patch with a tongue depressor or a spatula. 1) If there is too much material, put it on the inner side of

 the patch to fill in the damage.
 EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. ú

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(d)  Put the patch on the repair area.
 NOTE: There must not be adhesive leakage from the patch.
____
 (e)  
Put a sheet of Tape (P05-145), or equivalent, on the patch.

 (f)
Carefully attach the patch to the vane with a clamp.

 NOTE: To make sure that the patch has a good fit and makes a
____ continuous surface with the vane, use a silicone rubber tool that is cast from the leading edge or use shims.
 (g)  Apply a pressure of 5-10 psi (34.5-68.9 kPa) to the repair for a minimum of 24 hours at room temperature.
 NOTE: An alternate procedure is to apply the same pressure for
____ 90 minutes at a temperature of 140-260 degrees F (116-127 degrees C).
 S 958-112-N00
 (11)
 Remove the clamp and the tape.

 S 358-113-N00

 (12)
 Blend all areas where there is unwanted adhesive with 240-400 grit sandpaper.

 S 358-114-N00

 (13)
 Measure the difference between the level of the patch and the surface of the vane.

 (a)  
The difference between the levels must not be more than 0.030 inch (0.762 mm).

 H.
Put the Airplane Back to Its Usual Condition

 S 418-115-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).

 S 418-116-N00
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////////////////////////A / PW4000 SERIES /747-400 / ENGINES/MAINTENANCE MANUAL ////////////////////////
S 418-117-N00
 (3)  
Close the core cowl panels (AMM 71-11-06/201).

 S 448-118-N00

 (4)  
Do the activation procedure for the thrust reversers
 (AMM 78-31-00/201).

 TASK 72-33-02-308-119-N00
 9. Repair (Replacement) of the Damaged Fan Exit Vane
_________________________________________________
 A. General
 (1)  
It is not necessary to remove the fan blades. If you remove the fan blades, the procedure will continue two times longer (take two times longer to do).

 (2)  
It will be necessary to have no less than two people do this task.

 (3)  
Foam fairings become rigid with time. When you remove a group of vanes, it will help if you use new foam fairings for the installation of the vanes.

 B.
Consumable Materials

 (1)  
G00842 Cheesecloth, Unsized (PWA P05-038)

 (2)  
A00482 Sealant, Silicone Rubber (PWA P09-014)

 (3)  
B00130 Alcohol - Isopropyl

 (4)  
G02334 Lockwire, (P05-289) 0.032 inch (0.813 mm) - AS3214-02

 C.
Reference

 (1)  
AMM 71-11-04/201, Fan Cowl Panels

 (2)  
AMM 71-11-06/201, Core Cowl Panels

 (3)  
AMM 72-33-02/601, Fan Exit Case and Vane

 (4)  
AMM 78-31-00/201, Thrust Reverser System

 D.
Access

 (1)  
Location Zone
 412 Engine 1 - Fan Exit Case
 422 Engine 2 - Fan Exit Case
 432 Engine 3 - Fan Exit Case
 442 Engine 4 - Fan Exit Case

 (2)  
Access Panel
 415 and 416 Thrust Reverser Halves - Engine 1
 425 and 426 Thrust Reverser Halves - Engine 2
　
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