(3)
Shake control column lightly fore and aft to ensure system is centered. Check that right elevator trailing edge aligns with index mark on tail cone within 0.06 inch.
(4)
Check that power control units are synchronized as follows:
(a) Alternately switch each flight controls hydraulic systems A and B switches off and then on. Check that deflection of elevator at inboard end of trailing edge does not exceed 0.02 inch.
(5)
Position flight controls hydraulic system B switch to OFF, leave system A switch ON.
(6)
Move captain's control column aft until column stops are contacted and hold while measuring. Check that following conditions are met:
(a)
Right elevator trailing edge deflects 14.60 +0.30/-0.55 inches up from index mark.
(b)
Right tab trailing edge deflects 0.92 +0.10/-0.14 inch down from right elevator trailing edge.
(c)
Left tab trailing edge is faired with left elevator trailing edge within 0.07 inch.
(7)
Move captain's control column forward until column stops are contacted and hold while measuring. Check that following conditions are met:
(a)
Right elevator trailing edge deflects 10.55 +0.60/-0.30 inches down from index mark on tail cone.
(b)
Right tab trailing edge deflects 1.03 +0.10 inches up from right elevator trailing edge.
(c)
Left tab trailing edge is faired with left elevator trailing edge within 0.07 inch.
(8)
Position flight controls hydraulic system A switch to OFF and system B switch to ON.
(9)
Move captain's control column aft until column stops are contacted and hold while measuring. Check that following conditions are met:
(a)
Right elevator trailing edge deflects 14.60 +0.30/-0.55 inches up from index mark on tail cone.
(b)
Left tab trailing edge deflects 0.92 +0.10/-0.14 inch down from left elevator trailing edge.
(c)
Right tab trailing edge is faired with right elevator trailing edge within 0.07 inch.
(10)
Move captain's control column forward until column stops are contacted and hold while measuring. Check that following conditions are met:
(a)
Right elevator trailing edge deflects 10.55 + 0.60/-0.30 inches down from index mark on tail cone.
(b)
Left tab trailing edge deflects 1.03 ±0.10 inches up from left elevator trailing edge.
(c)
Right tab trailing edge is faired with right elevator trailing edge within 0.07 inch.
(11)
Position flight controls hydraulic system B switch to OFF.
(12)
Check for pressure leakage in feel pitot system as follows:
(a)
Seal drain hole in each feel pitot tube located on fin.
(b)
Remove drain plugs from system A and system B pitot lines located below feel computer.
(c)
Attach pressure gage lines from air pressure regulator to pitot system A and B drain holes, located below feel computer.
(d)
Attach regulated air pressure line from air pressure regulator to both pitot tubes on fin and pressurize pitot system to 5.0 ±0.1 psi (437 ±4 knots).
CAUTION: DO NOT RAISE TEST PRESSURE ABOVE 6 PSI (474 KNOTS) AT ANY TIME DURING TEST.
(e)
Cut off pressure source by turning shutoff valve in air pressure regulator to off.
(f)
Pressure shall not drop more than 0.3 psi (12 knots) during a 2-minute period.
(g)
Reduce pitot pressure to zero.
(13)
Test autopilot authority as follows:
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NOTE: Ensure that entire pitch channel of autopilot system is operational before proceeding.
NOTE: Ensure that elevator and feel computer are properly adjusted before proceeding.
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(a) Set horizontal stabilizer B dimension at 41.57 + 0.01 inches.
(b) Make sure that the following circuit breakers involved with autopilot pitch channel
operation are engaged.
1) Central Air Data Computer
2) Vertical Gyro No. 1
3) Pitch Channel
4) Autopilot Interlock
(c) Open the stabilizer trim circuit breakers to disengage the stabilizer from electric
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