G08727
551 Elevator Power Control Unit Input Rod Adjustment
May 01/76 Figure 506 27-31-0
Page 513
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
2) Rotate sleeve on right elevator power control unit input rod until right elevator trailing edge is aligned with index mark on tail cone within 0.06 inch.
3) Tighten both checknuts on input rod. If required for access to checknuts, position flight controls hydraulic system B switch to OFF, remove rigging pin E-5, and push elevator trailing edge down, then restore elevator to neutral as follows: a) Push elevator back to align with index mark, position flight controls
hydraulic system B switch to ON, shake control column fore and aft lightly to ensure system is centered, then release. Position flight controls hydraulic system B switch to OFF and install rigging pin E-5.
(h)
Position flight controls hydraulic system A switch to ON and system B switch to OFF, if not done previously.
(i)
Measure right elevator trailing edge deviation from index mark on tail cone (Fig. 505).
(j)
Position flight controls hydraulic system A switch to OFF.
(k)
Loosen checknuts on left power control unit input rod, but do not change rod length. If required, remove rigging pin E-5 and push elevator trailing edge up for access to checknuts, then restore elevator to neutral as follows: 1) Push elevator back to align trailing edge with index mark, position flight controls
hydraulic system A switch to ON, shake control column lightly fore and aft to ensure system is centered, then release. Position flight controls hydraulic system A switch to OFF and install rigging pin E-5.
(l)
If deviation is less than 0.4 inch, proceed to step (m) for fine adjustment. If deviation is greater than 0.4 inch, carry out coarse adjustment as follows: 1) Check that flight controls hydraulic system A switch is positioned to OFF.
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27-31-0 Page 514 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. Jun 20/84
WARNING: HYDRAULIC POWER MUST BE OFF BEFORE DISCONNECTING INPUT ROD.
2) Repeat steps (f)2) thru (f)6) on left power control unit input rod, taking
measurements at right elevator.
(m) Carry out fine adjustment as follows: 1) Position flight controls hydraulic system switch A to ON and system B switch to OFF. 2) Repeat step (g)2) on left power control unit input rod. 3) Tighten both checknuts on input rod. If required for access to checknuts, position flight controls hydraulic system A switch to OFF, remove rigging pin E-5 and push elevator trailing edge up, then restore elevator to neutral as follows: a) Push elevator back to align trailing edge with index mark, position flight controls hydraulic system A switch to ON, shake control column lightly fore and aft to ensure system is centered, then release. Position flight controls hydraulic system A switch to OFF and install rigging pin E-5.
4) Position flight controls hydraulic system A switch to OFF, if not done previously.
(n)
Check both left and right power control unit input rods for minimum thread engagement. Combined number of threads visible on clevis and sleeve shall not exceed 32 for each input rod.
(o)
Check that power control units are synchronized as follows: 1) Position flight controls hydraulic systems A and B switches to ON. 2) Alternately switch each system off and then on. Deflection of elevator at inboard
end of trailing edge shall not exceed 0.02 inch. 3) If necessary, repeat fine adjustment of power control unit input rods by repeating steps (g) and (m).
(p)
Remove rigging pin E-5.
Jun 20/84 27-31-0 Page 514A/514B BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
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