(b)  
With a brush, apply the antigalling compound to the mating surface of the midspan shroud of the fan blades.

 NOTE: It is not necessary to cure the antigalling compound.
____
 S 424-113-N00
 CAUTION:_______BE CAREFUL WITH THE FAN BLADE WHEN YOU INSTALL IT. YOU CAN
 EASILY CAUSE DAMAGE TO THE RUBBER SEAL THAT IS BONDED TO THE
 BOTTOM OF THE FAN BLADE PLATFORM.

 (3)  
Do the steps that follow to install the fan blades in the correct
 position.

 (a)  
Go clockwise while you install the fan blades (2), in the correct sequence, in the hub slot with the applicable number.

 EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. ú

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BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
////////////////////////A / PW4000 SERIES /747-400 / ENGINES/MAINTENANCE MANUAL ////////////////////////
(b)  
Continue to install the fan blades, but do not install the last blade.

 (c)  
Put the empty blade slot at the 12 o'clock position.

 (d)  
Align the cutout with the empty blade slot.

 (e)  
Install the last fan blade.

 S 424-114-N00
 (4)  
While you complete the fan blade installation, do the steps that follow to keep the blade shroud and root free to move.

 (a)  
Put the replacement blades in their position.

 (b)  
Put each fan blade at the 12 o'clock position.

 (c)  
Go clockwise, as seen from the front, and carefully push each blade rearward, in the hub slot, in small increments.

 (d)  
Continue to move each fan blade rearward, at the 12 o'clock position, until all of the fan blades are fully installed.

 G.
Put the Airplane Back to its Usual Condition.

 S 094-101-N00
 (1)  
Remove the PWA 85035 support fixture (Fig. 401, sheet 2).

 S 434-102-N00

 (2)  
Install the blade lock (1) as follows (Fig. 401, sheet 1):

 (a)  
Put the anti-rotation pin of the blade lock with the slot in the hub.

 (b)  
With a fiber drift, start at the lock joint to fully install the blade lock.

 (c)  
Make sure the blade lock in correctly installed by measurement of the gap between the lock ends. The gap must be 0.010 -

0.060 inch (0.25 - 1.52 mm). If you can not get the correct gap measurement, you must make sure the lock is fully seated.
 S 414-105-N00
 (3)  
Install the inlet cone (AMM 72-31-01/401).

 (4)  
Remove the protective mat from the inner surface of the inlet cowl.

 S 094-106-N00
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BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
1ST-STAGE (FAN) BLADE - INSPECTION/CHECK
________________________________________
 1.  General
_______
 A.  This procedure contains information on the inspection of the blades for the LPC 1st-stage fan. These blades are the first stage of the front compressor and can be seen from the front of the engine.
 B.  The instructions that follow are standard inspection conditions which apply during all the inspection tasks.
 NOTE: Fan Blades must be cleaned with a clean cloth before the blades
____
 are visually inspected.

 (1)  
Blend limits are made to give blades the most satisfactory structural strength. The use of a large number of blades repaired to or near the maximum limits, or the use of blades which have many repaired areas, can decrease compressor efficiency and thus decrease the performance of the engine. Refer to AMM 72-31-02/801 for the limits on the quantity and size of the repaired areas.

 (2)  
All blade surfaces must be smooth. All signs of leading and trailing edge repairs must be smooth and rounded. Refer to AMM 72-31-02/801 for the minimum edge thickness limits.
　
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