(4)  
TG69 Pliers - Electrical Connector
 06324 Glenair Inc.
 1211 Air Way, Glendale, CA 91201-2497

 (5)  
CTE5100 Pump - Portable Hydraulic
 Pratt and Whitney (see United Technologies)

 (6)  
Wrench (or alternative tool)

 (a)  
TG70 Wrench - Strap, Electrical Connector (recommended) 06324 Glenair Inc. 1211 Air Way, Glendale, CA 91201-2497

 (b)  
BTBS609 Wrench - Strap, Electrical Connector (alternative) 11851 Daniels Mfg Corp. 526 Thorp Rd. PO Box 593872, Orlando, FL 32859-3872

 B.  
Consumable Materials

 (1)  
A00482 Sealant - Silicone Rubber, RTV 159

 (2)  
B00148 Solvent - Methyl Ethyl Ketone (MEK), TT-M-261

 (3)  
D00137 Engine Oil - PWA 521, (P03-001)

 (4)  
D00247 Compound, Antigalling - PWA 586-3

 (5)  
G00842 Cheesecloth - Unsized, GA-100-11

 (6)  
G02334 Lockwire - AS3214-02

 (7)  
G02332 Ferrule - P05-292 (Optional)

 (8)  
G02335 Cable - Safety - P05-291 (Optional)

 EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. ú

 75-32-01
 ALL  ú ú N01 Page 501 ú Feb 18/01
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
////////////////////////A / PW4000 SERIES /747-400 / ENGINES/MAINTENANCE MANUAL ////////////////////////
C. Reference
 (1)  
AMM 72-34-03/401, Fan Exit Liner Segment

 (2)  
AMM 75-32-01/201, 2.5 Bleed Valve Actuator

 D.
Access

 (1)  
Location Zone
 412 Engine 1 - Intermediate Case Aft Face 7 o'clock
 422 Engine 2 - Intermediate Case Aft Face 7 o'clock
 432 Engine 3 - Intermediate Case Aft Face 7 o'clock
 442 Engine 4 - Intermediate Case Aft Face 7 o'clock

 (2)  
Access Panel
 415 Left Thrust Reverser Half - Engine 1
 425 Left Thrust Reverser Half - Engine 2
 435 Left Thrust Reverser Half - Engine 3
 445 Left Thrust Reverser Half - Engine 4

 E.
Prepare to Adjust the 2.5 Bled Valve Actuator

 S 015-080-N00
 (1)  
Remove the fan exit liner segment (inner) at the No. 5 position which covers the actuator (AMM 72-34-03/401).

 S 025-081-N00

 (2)  
Use the TG-69 Glenair Soft Jawed Pliers or the TG-70 Glenair Strap wrench to disconnect the electrical connector (W3P15) from the actuator (Fig. 501).

 S 915-082-N00

 (3)  
Put a fluid drain collector/container under the actuator.

 S 025-083-N00

 (4)  
Remove pressure from the hydraulic tubes as follows:

 (a)  
Remove lockwire or safety cable from the tube nuts at both ends of each tube (CP06) and (CR02).

 (b)  
While you hold the tee with a wrench, disconnect the hydraulic pressure tube (CP06) at the (CP02) tee to remove any pressure.

 (c)  
While you hold the tee with a wrench, disconnect the hydraulic return tube (CR02) at the (CR04) tee to remove any pressure.

 S 025-084-N00
 (5)  
Remove the hydraulic pressure tube (CP06) and hydraulic return tube (CR02) as follows:

 (a)  
Hold the adapters with a wrench and disconnect the tube nuts from the actuator.

 NOTE: It is not necessary to disconnect the drain manifold
____
 (DR11) from the actuator.

 EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. ú

 75-32-01
 ALL  ú ú N01 Page 502 ú Jun 18/99
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
SEE A
INTERMEDIATE
PISTON HEX HEAD CASE (REF) SHOULDER BOLT (LEFT HAND THREAD)
COTTER PIN
B
ELECTRICAL CONNECTOR (W3P15)
SUPPLY PORT ADAPTER
PISTON SHAFT
SEE C SEE B
FWD
BA
SUPPLY TUBE (CP06)
A
2.5 BLEED VALVE
ACTUATOR

RETURN TUBE (CR02)
BLEED AIR
EXIT DUCT

RETURN PORT DRAIN TUBE ADAPTER (REF)
A
　
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