(b) Test Trim Monitor 1) Engage autopilot and ground pitch TP-6. 2) Open stabilizer trim three-phase ac circuit breaker. 3) Apply 3 degrees noseup tilt to vertical gyro. Observe that STAB OUT OF TRIM light on center instrument panel illuminates after 8 to 16 seconds. 4) Disengage autopilot. 5) Engage autopilot and repeat 3) for nosedown vertical gyro. 6) Disengage autopilot, remove ground, close stabilizer trim three-phase ac circuit
breaker, and position stabilizer to zero degrees trim using trim switch on captain's control wheel.
(c)  Test Trim Speeds
NOTE: 1 unit of trim equals 9.5 revolutions of trim wheel.
1)  Manually trim the stabilizer to its maximum leading edge down (airplane noseup) position. Set flaps to 2 units. Engage ELEV engage switch. Ground  TP-6 on the pitch channel. Close autopilot 3 phase stabilizer trim circuit breaker. Tilt vertical gyro approximately 2 degrees nosedown. Observe that stabilizer does not move.
2)  Tilt vertical gyro approximately 2 degrees noseup and observe that stabilizer leading edge moves up (airplane nosedown) at a rate of 1 unit of trim in 4 to 7 seconds. Tilt vertical gyro in opposite direction until trim direction reverses. Allow stabilizer to run until it is automatically stopped by limit switches. Disengage ELEV engage switch. Check that dimension B is between 26.90  and 27.26 inches.
3)  Engage ELEV engage switch. Tilt vertical gyro 2 degrees noseup. Observe that stabilizer trims in a leading edge up (airplane nosedown) direction at a rate of 1 unit in 4 to 7 seconds. Let stabilizer run until it is automatically stopped by limit switches. Disengage ELEV engage switch. Check that dimension B is between
42.47 and 42.83 inches.
4)  Set flaps to 0 units. Engage ELEV engage switch. Hand crank stabilizer to airplane nosedown limit.
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5)  Tilt vertical gyro approximately 2 degrees nosedown. Observe that stabilizer moves in the leading edge down (airplane noseup) direction at a rate of 1 unit in 30 to 40 seconds.
6)  Tilt vertical gyro in either noseup or nosedown direction. With stabilizer trim operating, place autopilot trim cutout switch in CUTOUT position. Observe that stabilizer stops immediately and does not operate when vertical gyro is tilted in either direction. Observe that pitch axis disengages. Return autopilot trim cutout switch to NORMAL position. Engage ELEV engage switch and check that stabilizer operates when vertical gyro is tilted.
7)  Disengage ELEV engage switch, remove grounds and level gyro.
D.  Restore Airplane to Normal Configuration
(1) 
 Disengage autopilot.

(2)  
Remove vertical gyro(s) from tilt table. Refer to Vertical Gyro - Removal/Installation, Chapter 34.

(3)  
Turn off all systems.

(4)  
Disconnect and remove altimeter test set.

(5)  
Disconnect pressure source from pitot static system. Refer to Air Data Instruments, Chapter 34.

(6)  
Remove radio signal generators.

(7)  
Remove adapter assembly and restore control wheel hubs to normal configuration.

(8)  
Determine whether there is further need for electrical or hydraulic power on airplanes; if not, remove power.

3.  Yaw Damper System Test (All except coupler P/N 4084042)
NOTE: For aircraft with coupler P/N 4084042 installed (incorporating SB 27A1206), see 22-12-01
A.  Equipment and Materials
(1)  
Portable pressure equipment to simulate 0 to 35,000 feet altitude and 0 to 400 knots indicated airspeed (KIAS) type MB-1 Pitot Static System Tester, MIL-T-8076, Aircraft Products Part Number 381-100 or equivalent

(2)  
DC Volt-Ohmmeter, Simpson Model 260 or equivalent (with test leads and adapter to fit test points on face of yaw damper coupler)

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B.  Prepare to Test Yaw Damper System
(1)  
Connect pitot static pressure test equipment to air data computer pitot and static sources as required. Maintain ambient static pressure and pitot pressure to produce 120 KIAS.

CAUTION:  INSTRUMENT DAMAGE MAY RESULT IF PRESSURE TEST EQUIPMENT IS NOT CONNECTED PROPERLY. SEE AIR DATA INSTRUMENTS, CHAPTER 34 FOR DETAILED INSTRUCTIONS.

(2)  
Provide electrical power to airplane and energize load control center P6. 

(3)  
Energize hydraulic system B and ensure flight control system switch is positioned to ON.
　
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