WARNING:_______ MAKE SURE THAT PERSONS AND EQUIPMENT ARE CLEAR OF ALL
 CONTROL SURFACES BEFORE YOU SUPPLY HYDRAULIC POWER.
 AILERONS, RUDDERS, ELEVATORS FLAPS, SLATS, SPOILERS,
 LANDING GEAR, AND THRUST REVERSERS CAN MOVE QUICKLY WHEN
 YOU SUPPLY HYDRAULIC POWER.  THIS CAN CAUSE INJURY TO

 PERSONS AND DAMAGE TO EQUIPMENT.
 (i)  Refer to the instructions on the CDU and pressurize hydraulic systems A and B (AMM 29-15-00/201, Hydraulic Systems).
 EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. ú

 22-21-11
 ALL  ú ú 01 Page 505 ú Jul 12/00
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A 737-300/400/500MAINTENANCE MANUAL
 (j)  
Push the LSK adjacent to (<CONTINUE).

 (k)  
Refer to instruction on the CDU and set the horizontal stabilizer B dimension at 41.57 |0.01 inches equal to 3 units of trim (AMM 27-41-00/501, Horizontal Stablizer Trim Control System).

 NOTE: One person must be in the tail with a headset and the
____ other person in the control cabin.
 (l)  
Push the LSK adjacent to (<CONTINUE) for more of the MACH TRIM RIG pages on the CDU.

 (m)  
Follow the instructions on the CDU and write down the actuator positions down when it is necessary.

 E. Put the Airplane Back to Its Initial Condition
 S 865-038
 (1)  
Push the INIT REF key on the CDU to go out of BITE.

 S 865-039

 (2)  
Remove pressure from hydraulic systems A and B.

 S 415-040

 (3)  
Install access panel 3802 on the tail cone.

 TASK 22-21-11-745-041
 4. Mach Trim Actuator System Test
______________________________
 NOTE:____The Mach Trim BITE test is done as part of the DFCS BITE tests. DFCS BITE is done with the FMCS CDU and is found in the flight compartment.
 A. References
 (1)  
AMM 12-31-01/201, General Zone Diagram

 (2)  
AMM 24-22-00/201, Electrical Power Control

 (3)  
AMM 34-28-00/501

 (4)  
AMM 34-28-01/501

 B. Prepare for DFCS BITE
 S 865-042
 (1)  
Make sure the BAT switch is in the ON position (Pilots forward overhead panel).

 S 865-043

 (2)  
Make sure that the STANDBY POWER switch is in the AUTO position (Pilots forward overhead panel).

 S 865-044

 (3)  
Supply electrical power (AMM 24-22-00/201, Electrical Power Control).

 EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. ú

 22-21-11
 ALL  ú ú 02 Page 506 ú Jul 12/01
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A
737-300/400/500MAINTENANCE MANUAL
 S 865-045
 (4)  
Put the MASTER DIM and TEST switch, on the P2 center instrument panel, to the TEST position.

 S 865-048

 (5)  
Make sure all indicator lamps and annunciator lights on the pilots panel operate correctly.

 S 865-049

 (6)  
Make sure that all circuit breaker (P6 and P18 circuit breaker panels) for the systems shown below are closed and that the systems will operate.

 (a)  
P18-1 Circuit Breaker Panel
 1) AFCS A SNSR EXC AC
 2) AFCS A FCC DC
 3) AFCS A ENGAGE INTLK
 4) AFCS WARN LIGHT
 5) AFDS AIL FORCE LIMITER (737-300/-400 only)
 6) AFDS MCP DC
 7) MACH TRIM A AC
 8) MACH TRIM A DC
 9) AFC AUTO THROTTLE AC
 10) AFC AUTO THROTTLE DC
 11) AFC YAW DAMPER AC
 12) AFC YAW DAMPER DC

 (b)  
P18-2 Circuit Breaker Panel
 1) DAA No. 1 FMC AC
 2) DAA No. 1 IRS AC
 3) DAA No. 1 DC
 4) IRS No. 1 AC
 5) IRS No. 1 DC
 6) FMCS CDU No. 2
 7) FMCS MODE ANN
 8) FMCS CMPTR
 9) FMCS CDU No. 2
 10) No. 1 AIR DATA AUTO XFMR
 11) No. 1 AIR DATA TAT IND
 12) No. 1 AIR DATA COMPUTER AC
 13) No. 1 AIR DATA COMPUTER 26 VAC
　
中國航空網(wǎng) m.k6050.com
航空翻譯 www.aviation.cn
本文鏈接地址：737-300 400 500 AMM 飛機維護(hù)手冊 自動飛行 AUTOFLIGHT 2(123)