(6)
Ensure that any VOR, localizer or glide slope signals, which are required to perform any of the tests, are provided with the respective flag out of view, with an on-course, zero deviation display prior to starting the test.
(7)
Obtain simulated compass headings by setting up desired heading in DG mode on the appropriate compass system.
(8)
Whenever control wheel or control column displacements are being measured, care should be exercised to assure travel is not restricted by the control system being against its stops at either end of travel.
(8A) On single cue (V-bar) ADI's, throughout the test, references to roll command bar implies roll action of V-bars. Pitch command bar action implies vertical movement of V-bars. To enable V-bars to in-view condition, a pitch and roll mode must be selected.
Feb 20/85 22-11-01 Page 502A/502B BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
(8B) Adjust ALPHA vanes to faired condition (vane parallel with airplane axis); for left sensor, 14 degrees as indicated on calibration tool; for right sensor, 346 degrees as indicated on calibration tool.
(9)
Before each test, ensure that hydraulic power is applied to the control system being tested and controls are centered with flaps up unless specified otherwise.
(10)
Ensure that stabilizer trim motor is turned off for all tests requiring control column travel with no reference to stabilizer travel. This may be accomplished by opening autopilot stabilizer trim circuit breaker.
CAUTION: TO PREVENT STABILIZER TRIM MOTOR FROM BURNING OUT, DO NOT OPERATE MORE THAN 1 MINUTE IN EVERY 10 MINUTES.
(11)
Performance of tests in accordance with the sequence presented herein is required for items within a given paragraph. All required sequences start from energized systems, with the autopilot disengaged, the respective controls in a neutral condition, the F/D switches off and the ADI command bars and FD (CMPTR) flag out of view except as indicated.
(12)
When the autopilot is first engaged, there may be an apparent roll engage transient observed by watching the control wheel move away from center. This is the action of the wings leveling circuit in the autopilot and is entirely normal providing the control wheel error does not exceed 6 degrees. Recenter the wheel by offsetting the tilt table base (bubble level platform) when the tilt table protractor is set at zero if necessary.
(13)
Test points referred to in certain tests are on test connectors on the front of the AFCS computers. The F80225-19 test set provides remote access for pin to pin jumpers and voltage checks on FCC test connector pins. The test set allows all monitoring and jumpering to be performed in the flight deck by test operator.
(14)
Connect test point breakout boxes to AFCS computers. Verify that all switches are in open position unless otherwise specified.
(15)
Connect radio altitude signal simulator.
(16)
Connect adapter assemblies to control wheel hubs.
(17)
Check that all control surface areas are cleared of obstructions and personnel.
(18)
Provide electrical and hydraulic power. Verify that BAT switch is positioned to ON.
(19)
Position hydraulic system A and B switches to ON and close FLT CONT SYS circuit breaker.
WARNING: MAKE SURE ALL PERSONNEL AND OBSTRUCTIONS ARE CLEAR OF ELEVATOR, AILERON, RUDDER AND TAB SURFACES. SURFACES MAY MOVE ABRUPTLY WHEN HYDRAULIC POWER IS APPLIED.
(19A) Simulation of in air (flight) mode is done by:
(a)
Position GRD INTERCONNECT switch on overhead panel to OPEN.
(b)
Open HYD SYSTEM - GRD INTERvalve circuit breaker.
(c)
Open LANDING GEAR - LIGHTS circuit breaker.
(d)
Wait 20 seconds.
597
Feb 20/85 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 22-11-01 Page 503
(20) Ensure following circuit breakers are closed on load control centers P6 and P18.
(a)
NO. 1 INSTR NO. 2 INSTR
VERT GYRO-1 VERT GYRO-2
INSTR TRANS COMPASS-2
COMPASS-1 ADI (F/O)
ADI (CAPT) AUX VG (ALT)
VG-1 ALT INSTR XFMR-2
AUX VG NO. 1 RMI ALT
AUX VG STBY (ALT)
INSTR XFMR-1
NO. 2 RMI ALT
(b)
NO. 1 AIR DATA NO. 2 AIR DATA
AUTO XFMR AUTO XFMR
COMPUTER-1 AC COMPUTER-2 AC
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