CAUTION: DO NOT EXCEED MAIN ELECTRICAL ACTUATOR DUTY CYCLE OF 2 MINUTES ON AND 13 MINUTES OFF.
(o)
Check that time required to operate system through full travel in either direction is 13 to 19 seconds. Check that operation is smooth and free from chatter.
NOTE: Initial surges or chatter may be experienced due to cable stretch and mass of front end system.
Nov 15/76 27-41-0
Page 511
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
(p)
Perform several consecutive actuations of approximately 3 seconds duration in stabilizer leading edge up (airplane nosedown) direction. Check that operation is smooth and free from chatter.
(q)
Actuate in AIRPLANE NOSEUP direction until system comes up to full trim speed, then return trim switch to OFF position for approximately 0.2 seconds and actuate in opposite direction.
NOTE: Initial surges or chatter may be experienced due to cable stretch and mass of front end system.
(r)
Check that response in reverse direction is immediate.
(s)
Repeat steps (q) and (r) for AIRPLANE NOSEDOWN direction.
(t)
With stabilizer trim operating, using captain's stabilizer trim switch, place main electrical stabilizer trim cutout switch in CUTOUT position. Check that stabilizer stops immediately and does not operate in either direction with either captain's or first officer's stabilizer trim switch. Return main electrical stabilizer trim cutout switch to NORMAL position and check that stabilizer operates.
(9)
Test stabilizer trim wheel coast.
(a)
Actuate a stabilizer trim switch in AIRPLANE NOSEUP direction until system comes up to full trim speed, release stabilizer trim switch and observe coast of stabilizer trim wheel.
(b)
Repeat step (a) for AIRPLANE NOSEDOWN direction. Check that maximum coast in either direction is two revolutions.
(10)
Test stabilizer trim brake.
(a)
Provide elevator hydraulic systems A and B power (Ref 27-31-0, Maintenance Practices).
(b)
Check that stabilizer trim actuator and stabilizer trim control circuit breakers on panel P6 are closed.
NOTE: During following tests, neutral position of control column will be defined as an angle of 6.90 degrees forward of a station plane, unless otherwise specified.
(c)
Use captain's stabilizer trim switch to operate system in AIRPLANE NOSEUP direction.
(d)
While system is in operation, push control column rapidly forward until brake stops stabilizer system and then immediately return control column to neutral.
WARNING: BEFORE MOVING ELEVATOR CONTROL COLUMN, CHECK THAT RIGGING PIN ST-2 IS REMOVED FROM BRAKE ARM ON STABILIZER TRIM BRAKE. IF RIGGING PIN ST-2 IS LEFT IN BRAKE MECHANISM AND CONTROL COLUMN IS MOVED 50% OR MORE OF FULL TRAVEL, LEAF SPRINGS ON CONTROL COLUMN TORQUE TUBE WILL BE PERMANENTLY DEFORMED AND MUST BE REPLACED. A DEFORMED LEAF SPRING MAY RESULT IN UNWANTED ENGAGEMENT OF COLUMN ACTUATED STABILIZER TRIM BRAKE.
(e)
With control column in neutral, check that system resumes trimming in AIRPLANE NOSEUP direction.
(f)
Use captain's stabilizer trim switch to operate system in AIRPLANE NOSEDOWN direction.
(g)
While system is in operation, pull control column rapidly aft until brake stops stabilizer system and then immediately return control column to neutral.
(h)
With control column in neutral, check that system resumes trimming in AIRPLANE NOSEDOWN direction.
(i)
Use captain's stabilizer trim switch to operate system in AIRPLANE NOSEUP direction.
(j)
While system is in operation, push control column rapidly forward until brake stops system. While holding control column in this position, immediately release trim switch. Check that control column is between 0.70 and 2.48 degrees forward from neutral position.
(k)
With control column held in this position, actuate captain's stabilizer trim switch in AIRPLANE NOSEDOWN position. System should operate freely in AIRPLANE NOSEDOWN direction.
(l)
Use captain's stabilizer trim switch to operate system in AIRPLANE NOSEDOWN direction.
(m)
While system is in operation, pull control column aft rapidly until brake stops system. While holding control column in this position, immediately release trim switch. Check that control column is between 2.42 and 4.21 degrees from neutral position.
(n)
With control column held in this position, actuate captain's stabilizer trim switch in AIRPLANE NOSEUP direction. System should operate freely in AIRPLANE NOSEUP direction.
(o)
Pull stabilizer brake release handle and pull control column from neutral in aft direction until quadrant stops are contacted. Stabilizer trim system should be operable in either direction.
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