ON AIRPLANES WITH YD COUPLER P/N 4030952-902
ON AIRPLANES WITH YD COUPLER P/N 4030952-906
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AUTOPILOT AND YAW DAMPER SYSTEM - ADJUSTMENT/TEST
EFFECTIVITY
GJ ALL EXCEPT B-2509 and B-2510
1. General
A. This series of tests ensures that the autopilot and yaw damper system is not malfunctioning. It is assumed that all systems furnishing signal inputs to the autopilot and yaw damper system are in proper working order and that the stabilizer, elevator, and aileron control systems have been properly rigged.
B. The following sources supply input signal data to the autopilot and yaw damper system (Ref Chapter 34).
(1)
VHF navigation
(2)
Glide slope
(3)
Vertical gyro
(4)
Compass
(5)
Radio altimeter
(6)
Air data computer
(7)
OMEGA navigation system
C. To ensure complete system operability, all tests contained herein must be performed. However the autopilot system or the yaw damper system may be tested separately without degrading overall system performance. Further, tests contained within each system test are arranged to allow testing on a selective basis.
D. The pitch, roll, and yaw test points (TP) referenced throughout the tests, refer to test points located on the front panel of the pitch, roll and yaw control channels.
2. Autopilot System Test
A. Equipment and Materials
(1)
Signal Generator - Collins, 972Q-4; Instrument Flight Research, NAV401; Tel Instruments, T30B/B; Cossor, CRM 555A
(2)
Portable pressure equipment to simulate 0 to 35,000 feet altitude and 0 to 400 knots airspeed and 400 to 1000 feet per minute altitude rate signals
(3)
Tilt table (for vertical gyro)
(4)
Protractor F-52485-500 (or 4MIT65B80307-l) plus Adapter F-72790
(5)
Vertical gyro extension cable
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(6)
Radio Altimeter Test Set; Collins Radio Co., Model 980N-1; Bendix Radio Corp., Model AMT-51A; Honeywell, Model UG2559AB as applicable
(7)
Radio signal simulator (Fig. 501)
(8)
VTVM - Hewlett Packard, Model 410C, (with test leads and adapter to fit test points on face of roll and pitch channels)
(9)
Chatillon Spring Scale - Model DPP-50
(10)
Steel measuring tape
(11)
Adapter assemblies (2), Control Wheel Torque Tool - F80075-1
B. Prepare to Test Autopilot System
(1)
Mount vertical gyro(s) on tilt table as required to measure roll and pitch displacements. Connect attitude reference to system using extension cable.
(2)
Ensure that autopilot trim cutout switch is in NORMAL position.
(3)
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 knots indicated airspeed (KIAS).
CAUTION: INSTRUMENT DAMAGE MAY RESULT IF PRESSURE TEST EQUIPMENT IS NOT CONNECTED PROPERLY. REFER TO CHAPTER 34, AIR DATA INSTRUMENT, FOR DETAILED INSTRUCTIONS.
(4)
Use the radio signal simulator to generate required localizer and omnirange signals. Equivalent localizer and omnirange signals may be generated using signal generators. Place localizer and omnirange signal generators 75 feet from VOR antennas.
NOTE: Whenever VHF navigation receivers are required to be energized and no localizer or VOR signal is required, receivers should be detuned from any local station.
Omniradial, as used in this test, is the signal as it exists along a line in the magnetic direction from the VOR station, specified by the number of the radial; i.e., 0 degree radial is north of the station, 90 degrees radial is east of the station. As presented on the course deviation indicator (CDI), it is the signal which will produce a FROM indication when the course selector is placed on the radial number.
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H19067
500 Radio Signal Simulator
Feb 15/70 Figure 501 22-11-0
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BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
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