(a) Dynamic Test 1) Remove stabilizer trim electric actuator (Ref 27-41-71, R/I). 2) Insert pinion adapter or pinion gear wrench assembly into female spline on
gearbox. Hold adapter to prevent rotation.
3) Check that manual force required in both directions at stabilizer trim wheel handle to disengage manual clutch does not exceed 45 pounds (184 pound-inches). Travel is accomplished by ratcheting of clutch.
4) Remove adapter and install stabilizer trim electric actuator (Ref 27-41-71, R/I).
(b) Static Test (Optional to Dynamic Test) 1) Remove stabilizer trim electric actuator (Ref 27-41-71, R/I). 2) Insert pinion adapter or pinion gear wrench assembly into female spline on
gearbox. Hold adapter to prevent rotation.
3) Move one of the two stabilizer trim wheels airplane nose down until the manual clutch disengages one time. Make sure the maximum necessary force is between 39 pounds (160 pound-inches) and 52 pounds (215 pound-inches). Stop the handwheel. (Do this step 5 times.) Repeat this test in the airplane nose up direction.
4) Remove adapter and install stabilizer trim electric actuator (Ref 27-41-71, R/I).
(7) Test stabilizer trim auxiliary brake (Fig. 503).
(a)
At pilots' control stand, rotate captain's stabilizer trim control wheel several turns clockwise, as viewed from captain's side.
(b)
Apply 500 pound-inches torque to stabilizer jackscrew clockwise, as viewed from above jackscrew, and hold. Apply torque to flats on upstop, not to safety rod nut.
(c)
Mark a single reference line on both gearbox coverplate and umbrella assembly.
(d)
Release torque. Apply 500 pound-inches torque counterclockwise to jackscrew and hold.
(e)
Mark a reference line on umbrella in line with mark made on coverplate in step (c). Release torque.
(f)
At outer edge of umbrella, use a flexible scale to measure arc distance between reference marks made in steps (c) and (e). 1) On 65-49970-1 thru -24 stab. trim actuators, make sure that arc distance
dimension is not more than 0.52 inch (17.6 degrees).
2) On 65-49970-25 and subsequent stab. trim actuators, and 65-49970-1 thru -24 actuators with SB 27-1176, make sure that arc distance dimension is not more than 0.62 inch (21.0 degrees).
(g) Repeat steps (a) thru (f) except rotate captain's stabilizer trim control wheel counterclockwise and apply torques in directions opposite of those in steps (b) and (d).
(8) Test electrical trim system.
(a) Open stabilizer trim actuator and close stabilizer trim control circuit breakers on panel P6, and reverse any two 115-volt power leads to main electric stabilizer trim control relay at circuit breakers on panel P6.
502
27-41-0 Page 510 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. May 01/99
B61299
500 Stabilizer Trim Auxiliary Brake System Test Feb 20/93 Figure 503 27-41-0 Page 510A/510B BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
(b)
Close stabilizer trim actuator circuit breaker on panel P6 and provide electrical power.
(c)
Position main electric actuator cutout switch to NORMAL.
(d)
Position left stabilizer trim switch to AIRPLANE NOSEUP and then to AIRPLANE NOSEDOWN. Check that stabilizer does not operate.
(e)
Repeat step (d) with right stabilizer trim switch.
(f)
Open stabilizer trim actuator circuit breaker on panel P6 and restore power leads to normal. Close stabilizer trim actuator circuit breaker on panel P6.
(g)
Position left stabilizer trim switch momentarily to AIRPLANE NOSEDOWN and check that stabilizer leading edge moves up.
(h)
Position left stabilizer trim switch momentarily to AIRPLANE NOSEUP and check that stabilizer leading edge moves down.
(i)
Repeat steps (g) and (h) with right stabilizer trim switch to ensure correct direction of operation.
(j)
Separately move each lever on each stabilizer trim switch and check that stabilizer does not move.
(k)
Open stabilizer trim control circuit breaker on panel P6. Move each stabilizer trim switch in both nose up and nose down direction. Check that stabilizer does not move. Release trim switch and close circuit breaker.
(l)
Check that stabilizer trim on warning light illuminates when each stabilizer trim switch is actuated in each direction.
(m)
Test stabilizer trim limit switch adjustment per 27-41-101, Adjustment/Test, and stabilizer takeoff warning switch adjustment per 31-26-0, Adjustment/Test.
(n)
Operate stabilizer through one complete cycle from AIRPLANE NOSEUP to AIRPLANE NOSEDOWN and return to AIRPLANE NOSEUP.
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