+ 4.0 pounds.
(m)
Position flight controls hydraulic system A switch to OFF and system B switch to ON.
(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 3.5 ± 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 (r).
(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.
CAPTAIN'S CONTROL COLUMN AFT
RIGHT ELEVATOR POSITION COLUMN FORCE REQUIRED - POUNDS
1.95 + 0.05 in. up 6.95 + 0.05 in. up 18.0 + 2.0 35.0 + 3.5
501
Jun 20/92 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 27-31-131 Page 409
CAPTAIN'S CONTROL COLUMN FORWARD
RIGHT ELEVATOR POSITION COLUMN FORCE REQUIRED - POUNDS
1.95 +0.05 in. dn 6.15 + 0.05 in. dn 19.0 +2.0 35.0 +3.5
(4) Check autopilot authority as follows:
NOTE: Ensure that entire pitch channel of autopilot system is operational before proceeding.
Ensure that elevator and feel computer are properly adjusted before proceeding.
501
27-31-131 Page 410 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. Aug 15/78
(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
operation.
(d) Loosen vertical gyro No. 1 from its mounting in the electronics bay.
(e) Using air pressure regulator, increase pitot pressure to 3.50\+ 0.05 psi (370 ± 3
knots).
CAUTION: DO NOT EXCEED 6 PSI (474 KNOTS) TO THE PITOTS AT ANY TIME
DURING THIS TEST. OVERPRESSURE MAY DAMAGE FEEL
COMPUTER.
(f) Position flight controls hydraulic system B switch to ON. Make sure flight controls
system A switch is OFF.
(g) Select system B on the autopilot control panel.
(h) Wait 10 seconds and then engage the pitch axis on the autopilot control panel.
(i) Tilt the vertical gyro approximately 20 degrees front end down and hold.
(j) Measure and record right elevator trailing edge displacement with respect to index
mark.
(k) Tilt the vertical gyro approximately 20 degrees front end up and hold.
(l) Measure and record right elevator trailing edge displacement with respect to index
mark.
Jun 20/92 27-31-131
Page 411
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
(m)
Relevel the vertical gyro.
(n)
Disengage the pitch axis.
(o)
Add the displacements of steps (j) and (l). Check that total displacement is 3.51 +
0.56 inches.
(p)
Turn on hydraulic system A flight controls switch.
(q)
Repeat steps (h) thru (n) above.
(r)
Check that total displacement of steps (j) and (l) is 2.88 + 0.46 inches.
(s)
Set stabilizer jackscrew B dimension at 42.28 + 001 inches.
(t)
Reduce 3.5 psi (370 ± 3 knots) pitot pressure to zero. Then increase pressure to 2.80
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