G09923
500 Stabilizer B Dimension
Feb 15/73 Figure 402 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 27-31-101 Page 405
Elevator Power Control Unit Reaction Link Inspection 500
27-31-101 Figure 403 Feb 20/90
Page 406
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
ELEVATOR POWER CONTROL UNIT - ADJUSTMENT/TEST
1. Elevator Power Control Unit Adjustment (Fig. 501)
A. Equipment and Materials
(1)
Trammel Bar - F80055-1
(2)
Rigging Pins Kit - F70207-3, -52, -61, or -84:
(3)
Scale - 0 to 2 feet, graduated in inches, tenths and hundredths of an inch
REF NO. F70207-( ) DIAMETER (INCHES) LENGTH (INCHES) FUNCTION
E-5 -11 0.309-0.311 6.7 +0.25 AFT CONTROL QUADRANT
B. Prepare for Adjustment
(1)
Ensure that horizontal stabilizer B dimension (Fig. 502) is set at 41.57 +0.05 inches, that mach trim actuator is in null position per 27-31-0 MP, and install rigging pin E-5 in aft control quadrant.
(2)
Gain access to power control unit input rods through tail cone access panels.
(3)
Provide hydraulic power as follows:
(a)
Provide elevator systems A and B hydraulic power (Ref 27-31-0 MP).
(b)
Position flight controls hydraulic system A switch to OFF, leave system B switch ON.
C. Adjust Elevator Power Control Unit
(1)
Measure right elevator trailing edge deviation from index mark on tail cone (Fig. 501).
(2)
Position flight controls hydraulic system B switch to OFF.
(3)
Loosen checknuts on right power control unit input rod, but do not change rod length. If required, remove rigging pin E-5 and push elevator trailing edge down for access to checknuts, then restore elevator to neutral as follows:
(a) Push elevator back to align trailing edge with index mark, position flight controls hydraulic system B switch to ON, shake control column lightly fore and aft to ensure system is centered, then release. Position flight controls hydraulic system B switch to OFF, and install rigging pin E-5.
(4)
If deviation is less than 0.4 inch, proceed to step (5) for fine adjustment. If deviation is greater than 0.4 inch, carry out coarse adjustment as follows:
(a)
Check that flight controls hydraulic system B switch is positioned to OFF.
WARNING: HYDRAULIC POWER MUST BE OFF BEFORE DISCONNECTING INPUT ROD.
(b)
Disconnect lower end of input rod from quadrant crank (Fig. 501).
(c)
Adjust input rod to bring elevator trailing edge within 0.4 inch from index mark on tail cone. See Fig. 501 for adjustment between clevis, sleeve, and rod.
(5)
Pre SB 27-1207;
(a)
Install lockbolt assembly with washer under bolthead through lower end of power control unit input rod and aft control quadrant crank and into nutplate on input rod. Tighten outer bolt 75 to 85 pound-inches.
(b)
Install lock nut with washer over end of inner bolt and tighten 15-20 pound-inches.
500
Feb 20/88 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 27-31-101 Page 501
CAUTION: AFTER SETTING TORGUE ON LOCKNUT, DO NOT ATTEMP TO RESET TORQUE OF OUTER NUT.
(6)
Post SB 27-1207;
(a)
Install bolt assembly through lower end of power control unit input rod and aft control quadrant crank and into input rod.
(b)
Tighten inner nut to 45-60 pound-inches.
(c)
Tighten outer nut to 15-20 pound-inches.
CAUTION: AFTER TIGHTENING NUT, DO NOT RETIGHTEN INNER NUT.
(d)
Move control columns fore and aft through two full travels while visually inspecting for clearance between the control rod dual-loadpath bolts and surrounding structures.
(e)
Proceed to following step to make fine adjustment.
(7)
Carry out fine adjustment as follows:
(a)
Position flight controls hydraulic system A switch to OFF and system B switch to ON.
(b)
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.
(c)
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: 1) Push elevator back to align with index mark, position flight controls hydraulic
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