1)  The mach/speed trim mode is selected as a default mode when neither the automatic nor manual-electric trim is engaged.
 B.  Fault Indication (Fig. 8)
 (1)  
Stabilizer trim control system faults are monitored by the SAM. When a fault is detected the SAM enables corresponding fault balls , EICAS messages , and light indicators.

 (2)  
Stabilizer trim system fault indications include:

 (a)  
STCM faultball

 (b)  
COL LEVER SW faultball

 (c)  
MAN LEVER SW faultball

 (d)  
STAB TRIM message on EICAS and light indicator

 (e)  
UNSCD STAB TRIM message on EICAS and light indicator

 (3)  
The conditions to enable above fault indications are covered in Flight Control System Electronics Unit (CSEU) 27-09-00.

 (4)  
Refer to Automatic Stabilizer Trim System (AMM 22-22-00), and Mach Trim/Speed Stability System (AMM 22-24-00) for other fault indications.

 C.  
Control

 (1)  
General

 (a)  
This section provides instructions for stabilizer trim control in the manual-electric and manual-mechanical modes.

 (b)  
For information concerning control in the automatic mode, refer to AMM 22-22-00, Stabilizer Trim System-Description and Operation

 (c)  
For information concerning control in the Mach/Speed mode, refer to AMM 22-24-00, Mach Trim/Speed Stability System -Description and Operation.

 (2)  
Prepare For Operation

 (a)  
Provide electrical power (AMM 24-22-00/201).

 (b)  
Check that the following circuit breakers on panel P11 are closed: 1) AIRPLANES WITH ALTERNATE STAB TRIM SWITCHES ON THE CONTROL

 STAND;
 11B19, ALT STAB TRIM

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BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A
757
MAINTENANCE MANUAL

STABILIZER TRIM PILOT'S CENTERPOSITION INDICATOR INSTRUMENT PANEL P2
B (TYP)  C 
Stabilizer Trim Fault Indications Figure 8 

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 ú  01  Page 25
 ú  Sep 20/90 

BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A

(3)

(4)

(5)

(6)

757 MAINTENANCE MANUAL
 2) 11C12, STAB TRIM SHUTOFF LEFT 3) 11C13, STAB TRIM SHUTOFF RIGHT 4) 11F19, STAB POS MOD CENTER 5) 11G15, STAB POS MOD LEFT 6) 11G24, STAB POS MOD RIGHT 7) 11H10, STAB TRIM POS IND L
 or STAB TRIM LEFT POS IND 8) 11H11 or 11C05, STAB TRIM LEFT CONT 9) 11H19, STAB TRIM POS IND RIGHT 10) 11H20, STAB TRIM CONT RIGHT
 (c)  Check that RIGHT and CENTER STAB TRIM SHUTOFF switches on panel P10 are in NORM position.
 WARNING:_______ AILERONS, ELEVATORS, RUDDER, FLAPS, SLATS, SPOILERS,
 AND STABILIZER ARE FULLY POWERED SURFACES.  CHECK THAT ALL
 PERSONNEL AND EQUIPMENT ARE CLEAR OF ALL CONTROL SURFACES
 BEFORE PROVIDING HYDRAULIC POWER.  INJURY TO PERSONNEL OR

 DAMAGE TO EQUIPMENT COULD OCCUR.
 (d)  
Pressurize right and center hydraulic systems

 (AMM 29-11-00/201).Manual - Electric Operation

 (a)  
Move stabilizer in AIRPLANE NOSE DOWN (stabilizer leading edge up) direction by moving up either the captain's or first officer's stabilizer trim control wheel switches.

 (b)  
Move stabilizer in AIRPLANE NOSE UP (stabilizer leading edge down) direction by moving down either the captain's or first officer's stabilizer trim control wheel switches.

AIRPLANES WITH STAB TRIM LEVERS ON THE CONTROL STAND; Manual - Mechanical Operation

 (a)  
Move stabilizer in AIRPLANE NOSE DOWN direction (stabilizer leading edge up) by moving forward both STAB TRIM control levers on control stand.

 (b)  
Move stabilizer in AIRPLANE NOSE UP direction (Stabilizer leading edge down) by moving aft both STAB TRIM control levers on control stand.

AIRPLANES WITH ALTERNATE STAB TRIM SWITCHES ON THE CONTROL STAND; Alternate - Electric Operation
　
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