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BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.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

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 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
　
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