(2)
Open instrument transfer circuit breaker for test and reclose at the completion of each test.
VG TRANSFER REPOSITION VG
SWITCH OPEN TRANSFER FLAG APPEARS
TEST POSITION CIRCUIT BREAKER SWITCH TO ON ADI
1 NORMAL INSTR TRANS BOTH ON 2 BOTH ON 1 Captain’s F/O’s
2 BOTH ON 2 INSTR TRANS NORMAL BOTH ON 1 Captain’s Captain’s & F/O’s
3 BOTH ON 1 INSTR TRANS NORMAL BOTH ON 2 F/O’S Captain’s & F/O’s
E. Remove electrical power from airplane
May 01/76 34-22-0
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BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
3. System Test
A. Equipment and Materials
(1)
Calibrated tilt tables (2 required)
(2)
Gyro extension cables suitably terminated to extend airplane wiring to tilt tables (2 required)
B. Prepare for System Test
(1)
Remove vertical gyros from mountings and install on calibrated tilt tables (oriented as installed in airplane).
(2)
Connect jumper cables between gyros and their respective airplane connector.
(3)
Adjust tilt tables to zero degrees roll and pitch.
(4)
Connect electrical power to airplane and close GND PWR switch on panel P5. Energize No. 1 and 2 electronics buses by closing ac and dc circuit breakers on panel P6 and placing master switches in ON position.
(5)
Check that following circuit breakers are closed: VERT GYRO-2, F/O HORIZ (ALT), INST XFMR-2, F/O's HORIZ and INV CONT on panel P6; VERT GYRO-1, CAPT'S HORIZ (ALT), INST XFMR-1, CAPT'S HORIZ, and INSTR TRANS on panel P18.
C. Roll and Pitch Servo Test
(1)
Place VERTICAL GYRO transfer switch in NORMAL position. Check that both ADI's indicate 0.0 ±2 degrees roll and pitch attitude 1 minute after power is applied.
(2)
Adjust each ADI for zero pitch attitude using adjustment screw on lower left corner of ADI's.
(3)
Tilt vertical gyro No. 1 until captain's ADI indicates 10 degrees pitch down (attitude assembly moves toward top of indicator). Check that tilt table indicates 10 ±2 degrees pitch down attitude.
NOTE: ADI should follow displacements of vertical gyro smoothly with no sluggishness or overshoot.
(4)
Tilt vertical gyro No. 1 until captain's ADI indicates 10 degrees pitch up. Check that tilt table indicates 10 ±2 degrees pitch up attitude.
(5)
Tilt vertical gyro No. 1 until captain's ADI indicates 20 degrees right roll (attitude assembly rotates counterclockwise). Check that tilt table indicates 20 ±3 degrees right roll.
(6)
Tilt vertical gyro No. 1 until captain's ADI indicates 20 degrees left roll. Check that tilt table indicates 20 ±3 degrees left roll.
(7)
Repeat steps (3) thru (6) using vertical gyro No. 2 and first officer's ADI.
(8)
Place VERTICAL GYRO transfer switch in BOTH ON 2 position and repeat steps (3) thru (6) using vertical gyro No. 2 and captain's ADI.
(9)
Place VERTICAL GYRO transfer switch in BOTH ON 1 position and repeat steps (3) thru (6) using vertical gyro No. 1 and F/O's ADI.
(10)
Return vertical gyros to level attitude.
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D. Restore Airplane to Normal
(1)
Open all attitude reference system circuit breakers.
(2)
Allow 3 minutes for gyros to run down; install in airplane and connect electrical cables.
(3)
Close system circuit breakers and verify that system indicates attitude of airplane.
(4)
Determine whether there is further need for electrical power, if not, remove power.
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ATTITUDE REFERENCE SYSTEM - DESCRIPTION AND OPERATION
EFFECTIVITY
GJ B-2509 and B-2510
1. General
A. The attitude reference system is designed primarily to furnish the captain and first officer with information concerning the airplane's attitude in both PITCH and ROLL axes at all times during flight. It also provides pitch and roll displacement signals to the autothrottle speed control computer, flight control system, and weather radar antenna stabilization system. Two systems are installed; system No. 1 feeding information to the captain's ADI, flight control system channel A, and autothrottle speed control computer; while system No. 2 feeds information to the F/O ADI, flight control system channel B, and weather radar.
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