(b)  
Remove the generator wiring harness connectors D7066 and D7068 to the airplane wiring.

 (c)  
Disconnect the hydraulic pressure, return, and case lines at the HMG and install caps and plugs.

 (d)  
Remove the two generator mounting bolts, washers and nuts.

 (e)  
Remove the generator by lifting clear of the locator support pin.

 S 144-006
 CAUTION:_______QUICKLY CLEAN THE INSTALLATION AREA OF ALL FLUID. HYDRAULIC FLUID CAN CAUSE DAMAGE TO THE AIRPLANE EQUIPMENT.
 (2)  
Clean all hydraulic fluid from the installation area (Ref 12-25-01).

 S 034-007

 (3)
Remove the three unions from the HMG and discard the O-rings.

 TASK 24-25-01-424-020
 3.  Install the Hydraulic Motor Generator (Fig. 401)_____________________________________
 A. References
 (1)  
24-22-00/201, Electrical Power Control

 (2)  
29-11-00/201, Main Hydraulic Systems

 B. Access
 (1)  
Location Zones
 143 Main Land Gear Wheel Well (Left)
 211 Control Cabin - Section 41 (Left)
 212 Control Cabin - Section 41 (Right)

 (2)  
Access Panel
 732 Main Landing Gear Body Door (Left)

 C. Prepare for Installation
 S 644-015
 (1)  
Install new O-rings on the unions.

 (a)  Apply hydraulic lubricant or hydraulic fluid to O-rings and union threads.

 (2)  
Install unions in the HMG ports.

 S 434-019
 EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. AIRPLANES WITH HYDRAULIC MOTOR GENERATOR ú

 24-25-01
 ú ú 01 Page 403 ú May 28/99
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A
757 MAINTENANCE MANUAL
 D.  Procedure
 S 424-008
 (1)  Install the HMG as follows:
 (a)  
Put the generator on the locator support pin and install: 1) two mounting bolts 2) two nuts 3) two washers

 (b)  
Connect the hydraulic pressure, case and return lines.

 (c)  
Install the electrical connector D7022 on the servo valve.

 (d)  
Install the generator wiring harness connectors D7066 and D7068 to the airplane wiring.

 S 864-018
 (2) Remove DO-NOT-CLOSE tag, and close this P6 panel circuit breaker:
 (a)  6C3, HYD GEN CONT
 E.  Test the HMG Installation.
 S 864-009
 (1)  
Supply electrical power (Ref 24-22-00).

 S 214-010

 (2)  
Make sure the six EICAS circuit breakers on overhead circuit breaker panel P11 are closed.

 S 614-011

 (3)  
Pressurize the left hydraulic system (Ref 29-11-00).

 (a)  If you use the ACMPs to pressurize the left hydraulic system, do these steps: 1) Pressurize the left hydraulic system and the right
 hydraulic system with the ACMPs (Ref 29-11-00). 2) Put the PTU switch on the P61 panel to the ON position.
 S 214-012
 (4)  
Examine the HMG installation for hydraulic fluid leaks.

 S 714-013

 (5)  
Do an operational check.

 (a)  
Hold the GND PROX/HYD GEN switch on the miscellaneous test panel P61 in HYD GEN position. 1) Make sure the HMG operates.

 (b)  
Press the STATUS DISPLAY switch on the EICAS display select panel P9. 1) Make sure the EICAS status message HYD GEN ON is displayed.

 (c)  
Release the GND PROX/HYD GEN switch to the off position.

 1)  Make sure the HMG stops and status message HYD GEN ON is not displayed.
 S 864-014
 (6)  Remove hydraulic power if it is not necessary (Ref 29-11-00).
 EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. AIRPLANES WITH HYDRAULIC MOTOR GENERATOR ú

 24-25-01
 ú ú 01 Page 404 ú Sep 28/00
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
　
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