TASK 22-21-31-715-012
3. Mach Trim Flap Switch Operational Test______________________________________
A. References
(1)
12-31-01/201, General Zone Digram
(2)
24-22-00/201, Manual Control
(3)
29-15-00/201, Hydraulic Systems A and B
(4)
34-28-01/501, Honeywell EFIS IRS
(5)
34-28-02/501, Litton EFIS IRS
B. Access
(1) Location Zone
217 Right Main Wheel Well
C. Prepare for Test
S 865-013
(1)
Supply electrical power (Ref 24-22-00/201).
S 865-014
(2)
Align the left and right IRS (34-28-00/501, 34-28-01/501, or 34-28-02/501).
D. Mach Trim Flap Switch Operational Test
S 865-015
(1) Close the circuit breakers shown below:
(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
EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. ú
22-21-31
ALL ú ú 01 Page 505 ú Jul 12/01
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A
737-300/400/500MAINTENANCE MANUAL
7) MACH TRIM A AC
8) MACH TRIM A DC
(b) P6-2 Circuit Breaker Panel
1) AFCS B SNSR EXC AC
2) AFCS B FCC DC
3) AFCS B ENGAGE INTLK
4) AFCS WARN LIGHT
5) AFDS MCP CRS 2 DC
6) MACH TRIM B AC
7) MACH TRIM B DC
S 865-016
(2)
Supply system A and B hydraulic power (Ref 29-15-00/201).
S 715-017
(3)
Do these steps to do the operational test of the Mach Trim Flap Switch:
(a)
Set the trailing edge (TE) flaps to 1 unit.
(b)
Put the A/P ENGAGE A switch to CWS.
(c)
Disengage the A/P ENGAGE A switch.
(d)
Set the TE flaps to 0 units.
(e)
Put the A/P ENGAGE A switch to CWS.
(f)
Disengage the A/P ENGAGE A switch.
(g)
Set the TE flaps to 1 unit.
(h)
Put the A/P ENGAGE A switch to CWS.
(i)
Set the TE flaps to 0 units.
(j)
Make sure the A/P ENGAGE A stays in CWS.
(k)
Set the TE flaps to 1 unit.
(l)
Make sure the A/P ENGAGE A stays in CWS.
(m)
Disengage the A/P ENGAGE A switch.
(n)
Repeat steps (a) thru (m) for system A/P ENGAGE B.
(4)
Remove system A and B hydraulic power (Ref 29-15-00/201).
(5)
Set the circuit breakers to their initial positions.
S 865-018
S 865-019
TASK 22-21-31-725-046
4. Mach Trim Flap Switch Functional Test_____________________________________
A. References
(1)
12-31-01/201, General Zone Digram
(2)
24-22-00/201, Manual Control
(3)
29-15-00/201, Hydraulic Systems A and B
EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. ú
22-21-31
ALL ú ú 01 Page 506 ú Mar 15/96
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A
737-300/400/500MAINTENANCE MANUAL
(4) 29-22-31/401, PTU Control Valve
B. Access
(1) Location Zone
217 Right Main Wheel Well
C. Autopilot/Flight Director System Interface Test
S 715-020
(1) Do the Mach Trim Flap Switch Operational Test.
D. Hydraulic Pump System Interface Test
S 865-021
(1) Close the circuit breakers shown below:
(a)
P6-2 Circuit Breaker Panel
1) SHUTOFF VALVES STBY RUD
2) SHUTOFF VALVES FLT CONT
3) ELEC HYD PUMP CONT SYS A
4) ELECT HYD PUMP CONT SYS B
(b)
P6-3 Circuit Breaker Panel
1) ANTI-SKID FAIL WARN & PARK BK
中國航空網 www.k6050.com
航空翻譯 www.aviation.cn
本文鏈接地址：737-300 400 500 AMM 飛機維護手冊 自動飛行 AUTOFLIGHT 2(129)
