(2)  
Access Panels
 451 Forward Fairing - Engine Strut 1
 452 Forward Fairing - Engine Strut 2
 453 Forward Fairing - Engine Strut 3
 454 Forward Fairing - Engine Strut 4

 C.  
Do a Check of the Disagree Circuit.

 (1)
Make sure the thrust reverser is in the fully stowed position.

 S 865-002-N02
 S 865-081-N02
 WARNING: MAKE SURE THAT ALL PERSONS AND EQUIPMENT ARE CLEAR OF THE LE
_______ AND TE FLAPS AND FLAP DRIVE MECHANISMS DURING THIS ADJUSTMENT/TEST PROCEDURE. THE FLAPS WILL MOVE IF YOU MOVE THE FLAP CONTROL LEVER. THIS CAN CAUSE INJURIES TO PERSONS AND DAMAGE TO EQUIPMENT.
 WARNING: MAKE SURE THAT ALL PERSONS AND EQUIPMENT ARE CLEAR OF THE SPEED
_______ BRAKES. THE SPEED BRAKES CAN RETRACT QUICKLY AND CAUSE INJURY TO PERSONS OR DAMAGE TO EQUIPMENT.
 (2) Supply electrical power (AMM 24-22-00/201).
 EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. AIRPLANES WITH -10 OR -11 VERSIONS OF ú

 78-36-00
 IDS SOFTWARE.  ú CONFIG 2 ú N02 Page 501 ú Oct 18/00
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
////////////////////////A / PW4000 SERIES /747-400 / ENGINES/MAINTENANCE MANUAL ////////////////////////
S 865-082-N02
 CAUTION: DO ALL PRECAUTIONARY PROCEDURES FOR THE "AIR MODE SIMULATION".
_______ DAMAGE TO EQUIPMENT CAN OCCUR IF YOU DO NOT DO THESE PROCEDURES.
 (3)  Put airplane in the GROUND mode (AMM 32-09-02/201).
 S 865-004-N02
 WARNING:_______REMOVE THE HYDRAULIC PRESSURE BEFORE YOU DO THIS CHECK. IF YOU DO NOT REMOVE THE HYDRAULIC PRESSURE, THE THRUST REVERSER SLEEVES CAN MOVE QUICKLY WHEN THE REVERSE THRUST LEVERS ARE MOVED. THIS COULD CAUSE INJURY TO PERSONS AND DAMAGE TO EQUIPMENT.
 (4)  
Do this task: Hydraulic System Depressurization (AMM 29-11-00/201).

 S 865-005-N02

 (5)  
Make sure the fire handle is in the usual position.

 S 865-006-N02

 (6)  
For the applicable engine, make sure these circuit breakers on the Main Power Distribution Panel, P6, are closed:

 (a)  
6A09 DC 1 DIST-P6

 (b)  
6A17 DC 2 DIST-P6

 (c)  
6C12 ENG 4 T/R IND

 (d)  
6C13 ENG 4 T/R CONT

 (e)  
6D12 ENG 3 T/R IND

 (f)  
6D13 ENG 3 T/R CONT

 (g)  
6E12 ENG 2 T/R IND

 (h)  
6E13 ENG 2 T/R CONT

 (i)  
6F12 ENG 1 T/R IND

 (j)  
6F13 ENG 1 T/R CONT

 EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. AIRPLANES WITH -10 OR -11 VERSIONS OF ú

 78-36-00
 IDS SOFTWARE.  ú CONFIG 2 ú N02 Page 502 ú Oct 18/00
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
(k)  
6C11 ENG 4 T/R LOCK CONT

 (l)  
6D11 ENG 3 T/R LOCK CONT

 (m)  
6E11 ENG 2 T/R LOCK CONT

 (n)  
6F11 ENG 1 T/R LOCK CONT

 S 865-007-N02
 (7)  For the applicable engine, make sure these circuit breakers on the Overhead Circuit Breaker Panel, P7, are closed:
 (a)  
7F22 LANDING GEAR DSP & CONT PRI

 (b)  
7F23 LANDING GEAR DSP & CONT ALTN

 (c)  
7F25 PSEU SECT 1

 (d)  
7F26 PSEU SECT 2

 (e)  
7H08 GND SAFETY RELAY

 S 715-009-N02
 (8)  
Push the STATUS button on the EICAS control panel.

 S 215-010-N02

 (9)  
Make sure the status message ENG X REVERSER does not show on the EICAS display.

 (a)  If the status message ENG X REVERSER shows on the EICAS display, erase the message (AMM 31-61-00/201).
 S 035-011-N02
 (10) On the applicable engine strut, disconnect the electrical connector for the hydraulic pressure switch on the isolation valve.
 (a)  
Strut No. 1 DS1683

 (b)  
Strut No. 2 DS1684
　
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