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.
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(8)  
Position flight controls hydraulic system A switch to ON and system B switch to OFF, if not done previously.

(9)  
Measure right elevator trailing edge deviation from index mark on tail cone (Fig. 501).

(10)
Position flight controls hydraulic system A switch to OFF.

(11)
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:

(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.

(12)
If deviation is less than 0.4 inch, proceed to step (11) for fine adjustment. If deviation is greater than 0.4 inch, carry out coarse adjustment as follows:

(a)  
Check that flight controls hydraulic system A switch is positioned to OFF.

WARNING:  HYDRAULIC POWER MUST BE OFF BEFORE DISCONNECTING INPUT ROD.

(b)  
Repeat steps (4)(b) thru (4)(f) on left power control unit input rod, taking
measurements at right elevator.

May 01/03 27-31-101 Page 502A/502B BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.

(11)
Carry out fine adjustment as follows:

(a)  
Position flight controls hydraulic system switch A to ON and system B switch to OFF.

(b)  
Repeat step (5)(b) on left power control unit input rod.

(c)  
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: 1) Push elevator back to align with index mark, position flight controls hydraulic

system A switch to ON, shake control column fore and aft lightly to ensure system is centered, then release. Position flight controls hydraulic system A switch to OFF and install rigging pin E-5.

(d)
Position flight controls hydraulic system A switch to OFF, if not done previously.

(12)
Check both left and right power control unit input rods for minimum thread engagement. The combined number of threads visible on clevis and sleeve shall not exceed 32 for each input rod.

(13)
Check that power control units are synchronized as follows:

(a)  
Position flight controls hydraulic systems A and B switches to ON.

(b)  
Alternately switch each system off and then on. Check that deflection of elevator at inboard end of trailing edge does not exceed 0.02 inch.

(c)  
If necessary, repeat fine adjustment of power control unit input rods by repeating steps (5) and (11).

(14)
Remove rigging pin E-5.

(15)
If power control unit input rod required a coarse adjustment, the neutral shift sensor must be readjusted per Chapter 22, Elevator Neutral Shift Sensor - A/T.

(16)
Test elevator power control unit.

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2.  Elevator Power Control Unit Test (Fig. 501)
NOTE:  If left power control unit was replaced, the feel pitot system pressure leakage check and the autopilot authority test are not required.
A.  Equipment and Materials
(1)  
Trammel Bar - F80055-1

(2)  
Scale - 0 to 2 feet, graduated in inches, tenths and hundredths of an inch

(3)  
Air Pressure Regulator - F72928-53 (Preferred), or F72928-52 (Optional)

B.  Prepare for Test
(1)  
Set horizontal stabilizer B dimension (Fig. 502) at 41.57 +0.05 inches.

(2)  
Set mach trim actuator in null position (AMM 27-31-0/201).

(3)  
Provide elevator systems A and B hydraulic power (AMM 27-31-0/201).

C.  Test Elevator Power Control Unit
(1)  
Shake captain's control column lightly fore and aft to ensure that system is centered, and release.

(2)  
Move captain's control column approximately 2 degrees in forward direction and release. Check that right elevator trailing edge aligns with index mark on tail cone within 0.12 inch. Then move control column about 2 degrees aft and release. Check that right elevator trailing edge aligns with index mark within 0.12 inch. In both cases, check that tab is aligned with elevator within 0.07 inch.
　
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