EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. ú

 27-09-00
 ALL  ú ú 01 Page 1 ú May 28/99
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A

757
MAINTENANCE MANUAL

12.
 STABILIZER TRIM/ELEV ASYM LIMIT MODULE L (M524)

13.
 SPOILER CONTROL MODULE NO. 2 L (M531)

14.
 RUDDER RATIO CHANGER MODULE L (M528)

15.
 SPOILER CONTROL MODULE NO. 1 L (M530)

16.
 CSEU POWER SUPPLY MODULE NO. 1 L (M536)

(REF)
MAIN ELECTRONICS EQUIPMENT CENTER

Flight Control System Electronics Unit (CSEU)
Figure 1

EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. ú

 27-09-00
 ALL  ú ú 01 Page 2 ú Dec 15/83
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A

757
MAINTENANCE MANUAL

1
INERTIAL 2 REFERENCE SYSTEM (IRS)

AIR DATA SYSTEM (ADS)
LATERAL CONTROL SENSORS

AIRPLANES WITH THE ALTERNATE STAB TRIM SWITCHES ON THE CENTER CONTROL STAND
AIRPLANES WITH THE MANUAL STAB TRIM LEVERS ON THE CENTER CONTROL STAND
CSEU System Interface
Figure 2

EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. ú

 27-09-00
 ALL  ú
 ú  02  Page 3
 ú  Mar 20/93 

BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
B67973
A

757
MAINTENANCE MANUAL

 B. Rudder Ratio Changer (RRC) Function
 (1)  
The RRC varies rudder control authority as a function of airplane speed. Two RRCs are installed. One RRC is always in control and the other is on standby. If one RRC fails, the other RRC takes over the control functions. The RRC uses airspeed inputs from the air data computers (ADC) and the SAMs to control rudder deflection. Refer to 27-21-00 for more information.

 C.
Stabilizer Trim/Elevator Asymmetry Limit Function (SAM)

 (1)  
The SAM supplies stabilizer trim control and elevator asymmetry limit functions relative to the airspeed, and the airspeed output to the RRC. Two SAMs are installed. One SAM is always in control and the other is on standby. If one SAM fails, the other SAM switches over when the airplane is in the mach/speed trim mode, or if two or more flight control computers (FCC) are engaged.

 (2)  
Two SAMs are installed, one on the E3-1 and one on the E4-1 shelf in the main equipment center. Either SAM will provide the automatic control of the horizontal stabilizer position.

 (3)  
The trim up or trim down commands for the stabilizer can come to the SAM from one of these four sources:

 (a)  
An engaged flight control computer (FCC).

 (b)  
The air data computer (ADC) based on mach/speed data received from the airspeed sensors.

 (c)  
The manual electric trim switches on the control wheels.

 (d)  
AIRPLANES WITH THE STAB TRIM LEVERS ON THE CONTROL STAND; The manual trim levers on the center control stand.

 (e)  
AIRPLANES WITH THE ALTERNATE STAB TRIM SWITCHES ON THE CONTROL STAND; The alternate trim switches on the center control stand.

 (4)  
The SAM built-in test equipment (BITE) monitors its electrical circuits, and its input and output signals. When a fault is detected, the SAM sets one of its eleven faultballs to yellow. The SAM BITE also activates the STAB TRIM warning light and EICAS message to show a system failure.

 (5)  
The SAM gets ADC inputs and supplies its outputs to the elevator asymmetry limiter actuators to limit the elevator travel. Electrical information supplied from the FCC, ADC, stabilizer position modules (SPM), stabilizer trim control modules (STCM), aisle stand trim levers (ASTL), and captain's and first officer's trim switches, controls the stabilizer trim operation. Refer to 27-41-00 and 27-31-00 for more information.

 D.
Spoiler Control Module (SCM)

 (1)  
　
中國航空網 m.k6050.com
航空翻譯 www.aviation.cn
本文鏈接地址：757 AMM 飛機維護手冊 飛行操縱 FLIGHT CONTROLS 1(35)