F.
Prepare to Install the 2.5 Bleed-Valve Actuator

 (1)
Remove the protection caps from the open ports of the actuator (1).

 S 424-050-N00
 EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. ú

 75-32-01
 ALL  ú ú N02 Page 406 ú Jun 18/99
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
S 424-051-N00
 (2)  If it is necessary to install a new actuator (1), do the steps that follow:
 (a)  
Lubricate the packings (5, 6) with engine oil.

 (b)  
Lubricate the threads of the adapters (7, 8) with engine oil.

 (c)  
Install the packing (6) on the adapter (8).

 (d)  
Install the adapter (8) in the servo fuel supply port of the actuator (1). 1) Tighten the adapter (8) to 150-170 pound-inches (16.9-19.2

 newton-meters).

 (e)  
Install the packing (5) on the adapter (7).

 (f)  
Install the adapter (7) in the servo fuel return port of the actuator (1). 1) Tighten the adapter (7) to 110-120 pound-inches (12.4-13.6

 newton-meters).
 G. Procedure
 S 424-052-N00
 (1)  Install the actuator for the 2.5 bleed valve:
 (a)  
Lubricate the outer threads of the rod end clevis with engine oil.

 (b)  
Lubricate the threads of the attaching bolts (13) of the actuator (1) with engine oil.

 CAUTION:_______DO NOT TURN THE ROD END CLEVIS. IF YOU TURN THE ROD END CLEVIS, YOU CAN CAUSE DAMAGE TO THE 2.5 BLEED VALVE LINKAGE.

 (c)  
Move the piston shaft of the actuator (1) on the rod end clevis.

 (d)  
Turn the piston shaft hex-head clockwise until the actuator (1) touches the intermediate case.

 (e)  
Attach the actuator (1) to the intermediate case with the bolts (13) and washers (14).

 EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. ú

 75-32-01
 ALL  ú ú N02 Page 407 ú Jun 18/01
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
////////////////////////A / PW4000 SERIES /747-400 / ENGINES/MAINTENANCE MANUAL ////////////////////////
CAUTION:_______ YOU MUST ADJUST THE TORQUE WRENCH INDICATION FOR THE
 EFFECT OF THE TORQUE ADAPTER ON THE APPLIED TORQUE
 (AMM 70-23-00/201).  IF TOO MUCH TORQUE IS APPLIED TO THE

 BOLT, DAMAGE TO THE THREADS OF THE BOLT CAN OCCUR.
 (f)  
Use the PWA 85928 torque adapter to tighten the bolts (13) to 180-200 pound-inches (20.3-22.6 newton-meters).

 (g)  
Install the support bracket for the actuator with the steps that follow: 1) Lubricate the threads of the attaching bolts of the support

 bracket with engine oil.
 2)  Install the support bracket to the actuator with the two bolts. a) Tighten the bolts with your hand.
 3)  Align the three bolt holes in the support bracket with the three bolt holes in the bracket on the flange E.
 4)  ENGINES PRE-PW-SB 75-126; Attach the support bracket to the bracket on the flange E with the three bolts and nuts. a) Tighten the nuts with your hand.
 5)  ENGINES POST-PW-SB 75-126; Attach the support bracket to the bracket on the flange E with the three bolts. a) Tighten the bolts with your hand.
 6)  Tighten the bolts which attach the support bracket to the actuator to 65-85 pound-inches (7.3-9.6 newton-meters). a) Safety the bolts with lockwire or safety cable and
 safety cable ferrule.
 7)  Tighten the bolts which attach the support bracket to the bracket on the flange E to 85-95 pound-inches (9.6-10.7 newton-meters).
 (h)  Remove the protection caps from the EEC electrical connector
 (4) and the receptacle on the actuator (1).
 CAUTION: USE THE CORRECT ASSEMBLY PROCEDURE, AND TOOLS, FOR THE
_______ HARNESS CONNECTOR INSTALLATION (AMM 70-24-05/201). IF YOU USE THE INCORRECT ASSEMBLY PROCEDURE, OR TOOLS, A DAMAGED OR LOOSE CONNECTOR CAN OCCUR. A LOOSE CONNECTOR PERMITS VIBRATION, WHICH CAUSES THE CONTACTS TO WEAR AND DECREASES THE LIGHTNING PROTECTION.
 (i)  Connect the EEC electrical connector (4) to the actuator (1) (AMM 70-24-05/201).
　
中國航空網 www.k6050.com
航空翻譯 www.aviation.cn
本文鏈接地址：747-400 AMM 飛機維護手冊 大氣 AIR 2(61)