I. Connect EAL, EBL, EAR, and EBR control cables to quadrants on input torque tube.
J. Install tail cone (Ref 53-53-0 R/I).
K. Set stabilizer B dimension to 41.57 + 0.05 inches and mach trim actuator in null position per 27-31-0 MP.
L. Install rigging pins E-1, E-2, E-3, and E-5 and rig EAL, EBL, EAR, and EBR control cables to proper cable tension Fig. 401 using aft turnbuckles.
NOTE: Ensure turnbuckle-locking clips are installed at completion of rigging.
M. Remove rigging pins E-1, E-2, E-3, and E-5.
N. Slowly rotate elevator by hand through full travel up and down and check for roughness or binding.
O. With rigging pin E-5 installed and hydraulic system B pressurized, right elevator trailing edge should align with index mark on tail cone within 0.06 inch. Alignment may be obtained by adjusting right power control unit input rod per 27-31-0 A/T.
P. With rigging pin E-5 installed and hydraulic system A pressurized, right elevator trailing edge should align with index mark on tail cone within 0.06 inch. Alignment may be obtained by adjusting left power control unit input rod per 27-31-0 A/T.
Q. With rigging pin E-5 installed and hydraulic system A and B pressurized, synchronized operation of power control units may be verified by alternately switching each system off. Elevator trailing edge shall not deviate more than 0.02 inch. This condition may be met by adjusting input rods per 27-31-0 A/T.
R. Check feel and centering unit output rod with rig pin E-5 installed, lower bolthole in feel and centering unit output rod should align with bolthole in aft control quadrant crank. Alignment may be obtained by adjusting feel and centering unit output rod per 27-31-0 A/T.
S. Check that rig pin E-4 will fit freely through rig pinholes in computer input arm and feel computer housing.
T. Test power mode operation.
(1)
Ensure stabilizer B dimension is set at 41.57 +0.05 inches and all rigging pins are removed.
(2)
Set mach trim actuator in null position (Ref 27-31-0 MP).
(3)
Provide elevator system A and B hydraulic power (Ref 27-31-0 MP).
(4)
Shake captain's control column lightly fore and aft to ensure that system is centered.
(5)
Mark actual elevator trailing edge neutral position.
(6)
Turn flight controls hydraulic system B to off and move captain's control column aft until stops are contacted. Right elevator trailing edge shall deflect 14.60 +0 30/-0.55 inches up from index mark. Right tab trailing edge shall deflect 0.92 +0.10/-0.14 inch down from right trailing edge. Left tab trailing edge shall be faired with left elevator trailing edge within 0.07 inch.
May 01/99 27-31-71 Page 405 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
(7)
Move captain's control column forward until stops are contacted. Right elevator trailing edge shall defect 10.55 + 0.20/-0.30 inches down from index mark. Right tab trailing edge shall deflect 1.03 + 0.10 inches up from right trailing edge. Left tab trailing edge shall be 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 stops are contacted. Right elevator trailing edge shall deflect 14.60 + 0.30/-0.55 inches up from index mark. Right tab trailing edge shall be faired with right elevator trailing edge within 0.07 inch. Left tab trailing edge shall deflect
0.92 +0.10/-0.14 inch down from left elevator trailing edge.
(10)
Move captain's control column forward until stops are contacted. Right elevator trailing edge shall deflect 10.55 + 0.20/-0.30 inches down from index mark. Right tab trailing edge shall be faired with right elevator trailing edge within 0.07 inch. Left tab trailing edge shall deflect 1.03 + 0.10 inches up from left elevator trailing edge.
(11)
Position flight controls hydraulic system B switch to off.
U. Restore airplane to normal hydraulic configuration (Ref 27-31-0, MP).
V. If no longer required, remove electrical power from airplane.
551
27-31-71 Page 406 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. Oct 20/84
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本文鏈接地址：737 AMM 飛機維護手冊 飛行操縱 FLIGHT CONTROLS 2(99)
