(v) Position flight controls hydraulic system B switch to OFF.
(7)
Test Neutral Shift Operation
(a)
Set horizontal stabilizer B dimension at 21.32 士0.05 inches (ball nut against lower stop).
(b)
Set mach trim actuator in null position (Ref 27-31-0 MP).
(c)
Provide elevator systems A and B hydraulic power (Ref 27-31-0, MP).
(d)
Shake control column lightly fore and aft to ensure system is centered, and release.
(e)
Check that right elevator position is 16.00 士0.50/-0.10 inches up from index mark on tail cone.
(f)
Set horizontal stabilizer B dimension at 45.84 士0.05 inches (ballnut against upper stop).
(g)
Shake control column lightly fore and aft to ensure system is centered, and release.
(h)
Check that right elevator position is 2.60 +0.40/-0.20 inches down from index mark on tail cone.
(8)
Test Feel Force System and Autopilot Authority
(a) Test differential pressure switch as follows: 1) Set TE flaps to full up position. 2) Check that MASTER DIM C311, C312, C316, and MASTER CAUTION circuit
breakers on panel P6 are closed.
3) Provide elevator systems A and B hydraulic power (Ref 27-31-0, MP), and position flight controls hydraulic system B switch to OFF, leave system A switch ON.
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4) Check that following lights come on: FEEL DIFF PRESS light on P5 overhead panel, FLIGHT CONTROL on Master Caution annunciator on P7 lightshield and both MASTER CAUTION lights on P7.
5) Position flight controls hydraulic system A switch to OFF and system B switch to ON.
6) Check that FEEL DIFF PRESS, both MASTER CAUTION and FLIGHT CONTROL lights come on.
7) Position flight controls hydraulic system A switch to ON. Check that lights go off.
8) With both systems on, operate captain's control column at a constant rate, starting from full forward to full aft to full forward in approximately 2 seconds
(27.5 degrees per second).
NOTE: FEEL DIFF PRESS light may come on when stops are contacted, for up to 1 second but should extinguish within 0.5 seconds after input motion ceases.
9) Set flaps to 5-unit position.
10) Position flight controls hydraulic system B switch to OFF and check that FEEL DIFF PRESS light is off.
11) Position flight controls hydraulic system B switch to ON and system A switch to OFF, and check that FEEL DIFF PRESS light is off.
12) Raise flaps to full up position.
13) Position flight controls hydraulic systems A and B switches to OFF.
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(b) Check for pressure leakage in feel pitot system as follows: 1) Seal drain hole in each feel pitot tube located on fin. 2) Remove drain plugs from system A and system B pitot lines located below feel
computer. 3) Attach pressure gage lines from air pressure regulator to pitot system A and B drain holes located below feel computer. 4) Attach regulated air pressure line from air pressure regulator to both pitot tubes on fin and pressurize pitot system to 5.0 士0.1 psi (437 士4 knots).
CAUTION: DO NOT RAISE TEST PRESSURE ABOVE 6 PSI (474 KNOTS) AT ANY TIME DURING TEST.
5) Cut off pressure source by turning shutoff valve in air pressure regulator to off. 6) Pressure shall not drop more than 0.3 psi (12 knots) during a 2-minute period. 7) Reduce pitot pressure to zero.
(c) Check feel forces as follows:
NOTE: Ensure that elevator and feel computer are properly adjusted before proceeding.
1) Set horizontal stabilizer B dimension at 41.57 士0.01 inches.
2) Set mach trim actuator in null position (Ref 27-31-0 MP).
Jun 20/92 27-31-0 Page 532A/532B BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
3) 4) Position flight controls hydraulic systems A and B switches to ON. Using air pressure regulator, pressurize pitot system to 3.50 ±0.05 psi (370 ±3 knots).
CAUTION: DO NOT RAISE TEST PRESSURE ABOVE 6.0 PSI (474 KNOTS) AT ANY TIME DURING TEST. OVERPRESSURE MAY DAMAGE COMPUTER.
5) Apply masking tape on tail cone along direction of right elevator trailing edge travel.
NOTE: Elevator travel measuring tool may be used in lieu of tape method.
6) Shake captain's control column lightly fore and aft to ensure that system is centered, and release.
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