5C1
Jun 20/88 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 22-11-01 Page 511
SUB TEST # DISP LIBRARY TESTS
.33 26 APPROACH (If BITE fails, -114 FCC MOD A through D,
see *[1])
.34 30 ALT RATE
.35 35 DADC ANALOG INTERFACE
.36 36 ACCEL INTERFACE
.37 19 ROLL CWS
.38 20 PITCH CWS
.39 25 VOR O/C TC
.40 17 VG INTERFACE (INSTR SWITCHING)
.41 18 COMPASS INTERFACE
.42 33 ALPHA VANE
.43 21 EXTENDED RAM TESTS
.44 8 DME INTERFACE
.45 70 L NAV (OPTIONAL)
-INITIALIZATION
.46 27 ELEV CONTROL
.47 22 AILERON CONT
.48 29 STAB TRIM
.49 34 FLAPS
.50 11 DUAL APP LOGIC *[2]
--EXIT BITE
*[1] If subtest fails with diagnostic; VOR/ILS 1 or (2); VG 1 or (2); MCP: ACCEL 1 or (2); FCC 1 of (2), enter engineering data mode (CLR-100-ENT) and repeat test. If test 2.33 subtest 2 (NOM-3.02 to -5.62) and 2.33 subtest 3 (NOM-.83 to -1.53) fail, ignore failure indication. Normal system operation can be ensured by performing Dual Channel Approach Test.
*[2] This test runs if YES is answered to BOTH channels installed or A/B test. Due to tolerance build-up, this test might fail. Disregard this test if Dual Channel Approach Mode Test is passed.
(g) At completion of BITE, switch PDC to any mode except STBY. Verify that A/P warning lights extinguish and AFCS Mode Control Panel displays are restored to normal.
(10A) Test A/P Trim Threshold
(a)
Set stabilizer to 13 units of trim and open autopilot stabilizer trim servo 3-phase circuit breaker.
(b)
Apply A hydraulic power only (disengage B system).
(c)
Place A/P ENGAGE A switch to CMD. Ground integrator reset J6-82. Connect voltmeter to J6-23 and another voltmeter to J6-22 on AFCS computer A.
5B8 22-11-01 Jun 20/88 Page 512
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
(d)
Select V/S mode. Slowly apply fly-up signal (50 to 250 ft/min) until stab trim is actuated, +10vdc to -10vdc at J6-23. Observe the voltage reading at J6-22 just prior to trim actuation is +1.20 VDC maximum. Check that the maximum voltage at J6-20 is +0.6 (+0.4, -0.2) vdc and reconnect voltmeter to J6-22.
(e)
Repeat step (d) using fly-down V/S, monitoring for change of +10vdc to -10vdc at J6-
23. The voltage reading at J6-22 and J6-20 should have opposite polarity.
(f)
Disengage autopilot. Repeat steps (b) thru (e) with channel B autopilot and B hydraulic only.
(g)
Remove ground from J6-82.
(11)
Test A/P Trim Speeds
(a)
Manually trim stabilizer to 3 units.
(b)
Position control column to neutral.
(c)
Check that voltage at J6-20 to ground is less than 1 volt and voltage at J6-21 to ground is less than 2 volts.
(d)
Manually trim stabilizer to maximum leading edge down (airplane nose up) position. Set flaps to 2 units. Close autopilot stabilizer trim 3-phase circuit breaker.
(e)
Place A/P ENGAGE A switch to CMD. Ground integrator reset J6-82.
(f)
Engage V/S mode and select -6000 feet/minute V/S. Observe that the stabilizer leading edge moves up (airplane nose down) at a rate of 1 unit of trim in 4 to 7 seconds.
NOTE: One unit of trim equals 9.5 revolutions of trim wheel.
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