75-32-05
 ALL  ú ú N01 Page 405 ú Jun 10/97
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
2.9 BLEED VALVE THERMOCOUPLE PROBE - REMOVAL/INSTALLATION
_________________________________________________________
 1.  General
_______
 A.  This procedure gives the instructions to the remove and install the left or right thermocouple probe on the 2.9 bleed valve.
 B.  The thermocouple probe is installed on the aft case of the high pressure compressor (HPC) at the 1 and 10 o'clock positions.
 C.  You can get access to the thermocouple probe through the applicable thrust reverser.
 TASK 75-32-06-004-014-N00
 2.  Remove the 2.9 Bleed Valve Thermocouple Probe (Fig. 401)
_____________________________________________
 A.  References
 (1)  
AMM 71-11-04/201, Fan Cowl Panels

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

 (3)  
AMM 78-31-00/201, Thrust Reverser System

 B.  
Access

 (1)  
Location Zone
 412 Engine 1 - HPC 1 or 10 o'clock
 422 Engine 2 - HPC 1 or 10 o'clock
 432 Engine 3 - HPC 1 or 10 o'clock
 442 Engine 4 - HPC 1 or 10 o'clock

 (2)  
Access Panel
 415 Left Thrust Reverser Half - Engine 1
 416 Right Thrust Reverser Half - Engine 1
 425 Left Thrust Reverser Half - Engine 2
 426 Right Thrust Reverser Half - Engine 2
 435 Left Thrust Reverser Half - Engine 3
 436 Right Thrust Reverser Half - Engine 3
 445 Left Thrust Reverser Half - Engine 4
 446 Right Thrust Reverser Half - Engine 4

 C.  
Prepare to Remove the Thermocouple Probe

 S 864-018-N00
 (1)  For the applicable engine, open these circuit breakers and install the DO-NOT-CLOSE tags:
 (a)  AIRPLANES WITH THE AUTOMATIC ENGINE START; P6 Main Power Distribution Panel 1) 6G15 SCU ALT PWR ENG 1 2) 6G23 ENG SCU 1 3) 6G16 SCU ALT PWR ENG 2 4) 6G24 ENG SCU 2 5) 6G17 SCU ALT PWR ENG 3 6) 6G25 ENG SCU 3 7) 6G18 SCU ALT PWR ENG 4
 EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. ENGINES WITH 2.9 BLEED ú

 75-32-06
 VALVE THERMOCOUPLE PROBE  ú ú N02 Page 401 ú Jun 18/01
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
////////////////////////A / PW4000 SERIES /747-400 / ENGINES /MAINTENANCE MANUAL ////////////////////////
SEE  A  RIGHT 2.9 BLEED VALVE  SEE  B 
GASKET 
SEE  C  A  FWD 
SEE C BLEED VALVE LEFT 2.9 
FWD  B 

2.9 Bleed Valve Thermocouple Probe Installation
Figure 401 (Sheet 1)

EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. ENGINES WITH 2.9 BLEED ú

 75-32-06
 VALVE THERMOCOUPLE PROBE  ú ú N02 Page 402 ú Oct 10/91
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
BRACKET  2 
NUT 
2.9 BLEED VALVE THERMOCOUPLE PROBE 
BRACKET BOLT (2 LOCATIONS) 1  NUT (LARGER) NUT (SMALLER) 
CLAMP BOLT 
FWD  2.9 BLEED VALVE THERMOCOUPLE PROBE  (2 LOCATIONS) BOLT  NUT (LARGER) NUT (SMALLER) 
C RIGHT SIDE, MIRROR IMAGE 
2 1  ENGINES WITHOUT THE CLAMP BOLT WELDED TO THE BRACKET ENGINES WITH THE CLAMP BOLT WELDED TO THE BRACKET  L-A6243 0391 

2.9 Bleed Valve Thermocouple Probe Installation
Figure 401 (Sheet 2)

EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. ENGINES WITH 2.9 BLEED ú

 75-32-06
 VALVE THERMOCOUPLE PROBE  ú ú N02 Page 403 ú Oct 10/91
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
////////////////////////A / PW4000 SERIES /747-400 / ENGINES/MAINTENANCE MANUAL ////////////////////////
8) 6G26 ENG SCU 4
 (b)  AIRPLANES WITHOUT THE AUTOMATIC ENGINE START; P414 Power Distribution Center - Left 1) 414D21 EEC GND TEST PWR ENG 1 2) 414D22 EEC GND TEST PWR ENG 2 3) 414D23 EEC GND TEST PWR ENG 3 4) 414D24 EEC GND TEST PWR ENG 4
　
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