+ 4.0 pounds.
(j)
Position flight controls hydraulic system B switch to OFF, leave system A switch ON.
(k)
Move captain's control column slowly aft and hold at indicated elevator position of
1.95 + 0.05 inches up on right elevator. Check that force to hold column is 37.5 + 4.0 pounds.
(l)
Move captain's control column slowly forward and hold at indicated elevator position of 1.95 + 0.05 inches down on right elevator. Check that force to hold column is 38.5
+ 4.0 pounds.
(m)
Position flight controls hydraulic system A switch to OFF and system B switch to OFF.
(n)
Move Captain's control column slowly aft and hold at indicated elevator position of
1.95 +0.05 inches up on right elevator. Check that force to hold column is 37.5 +4.0 pounds.
(o)
Move captain's control column slowly forward and hold at indicated elevator position of 1.95 +0.05 inches down on right elevator. Check that force to hold column is 38.5 +4.0 pounds.
(p)
Position flight controls hydraulic system A switch to ON.
(q)
Reduce 3.50 ±0.05 psi (370 ±3 knots) dynamic pressure being applied to pitot tubes to zero pressure. Then increase pressure to 0.50 +0.05 psi (145 ±7 knots).
CAUTION: DO NOT RAISE TEST PRESSURE ABOVE 6 PSI (474 KNOTS) AT ANY TIME DURING TEST. OVERPRESSURE MAY DAMAGE COMPUTER.
(r)
Move captain's control column slowly aft and hold at indicated elevator position. Check that following conditions are met:
(s)
Move captain's control column slowly forward and hold at indicated elevator position. Check that following conditions are met.
(t)
Position flight controls hydraulic system B switch to OFF, leave system A switch ON.
(u)
Perform test of step (n).
(v)
Perform test of step (s).
(w)
Position flight controls hydraulic system A switch to OFF and system B switch to ON.
(x)
Perform test per step (r).
(y)
Perform test per step (s).
(z)
Position flight controls hydraulic system B switch to OFF.
501
Aug 1/74 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 27-31-161 Page 405
CAPTAIN’S CONTROL COLUMN AFT
RIGHT ELEVATOR POSITION COLUMN FORCE REQUIRED – POUNDS
1.95 ±.05 in. up 6.95 ±0.05 in. up 18.0 ±2.0 35.0 ±3.5
CAPTAIN’S CONTROL COLUMN FORWARD
RIGHT ELEVATOR POSITION COLUMN FORCE REQUIRED – POUNDS
1.95 ±0.05 in. dn 6.95 ±0.05 in. dn 19.0 ±2.0 35.0 ±3.5
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27-31-161 Page 406 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. Jun 20/92
J. Restore Airplane to Normal
(1)
Ensure that all tools used during testing are removed.
(2)
Remove all masking tape.
(3)
Remove seals from drain holes in each vertical fin pitot tube.
CAUTION: MAKE SURE SEALS ARE REMOVED FROM PITOT TUBES.
(4)
Remove pressure gage lines from systems A and B drain lines located below feel computer.
(5)
Install drain plugs on system A and B drain lines located below feel computer.
(6)
Remove regulated air pressure lines from both vertical fin pitot tubes.
(7)
Install access panels.
(8)
Restore airplane to normal hydraulic configuration (Ref 27-31-0).
(9)
Service hydraulic reservoirs, if required (Ref Chapter 13, Hydraulic Servicing).
(10)
Remove electrical power if no longer required.
501
Aug 1/74 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 27-31-161 Page 407
ELEVATOR SEALS - ADJUSTMENT/TEST
1. Elevator Seals Adjustment
A. Equipment and Materials
(1) Trammel Bar - F80055-1 (Ref 27-00 MP)
B. Prepare for Adjustment
(1)
Remove elevator systems A and B hydraulic power (Ref 27-31-0 MP).
(2) 中国航空网 www.aero.cn 航空翻译 www.aviation.cn 本文链接地址：737 AMM 飞机维护手册 飞行操纵 FLIGHT CONTROLS 2(121)
