(b)
Check that horizontal stabilizer B dimension is set at 41.57 士0.05 inches.
(c)
Open stabilizer trim actuator circuit breakers on panel P6.
(d)
Check that rigging pin E-4 fits freely through rig pin holes in computer input arm and feel computer housing. If rig pin E-4 does not fit freely adjust input rod per following:
500
27-31-0 Page 518H BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. Feb 01/95
WARNING: FEEL COMPUTER MAY BE DAMAGED IF COMPUTER INPUT ARM IS FORCED TO ROTATE BEYOND INTERNAL STOPS. BOTTOMING OF COMPUTER INPUT ARM AGAINST CAM STOPS MUST THEREFORE BE AVOIDED. DAMAGE TO CAM SHAFT SHEAR PINS MAY OCCUR IF TORQUE APPLIED TO COMPUTER INPUT ARM EXCEEDS 300 POUND-INCHES. A FAILURE OF SHEAR PINS MAY CHANGE STABILIZER INPUT PROGRAM TO COMPUTER AND AFFECT AUTOPILOT AUTHORITY.
1) Remove bolt attaching stabilizer input rod to computer input arm (Fig. 509).
2) Install rigging pin E-4 in computer input arm.
3) Check that bolt can be easily installed through input rod and computer input
arm. If bolt does not fit, loosen checknut on input rod and rotate rod end fitting
until bolt can be easily installed.
4) Tighten checknut and secure stabilizer input rod to computer input arm.
5) Check stabilizer input rod for minimum thread engagement. End of rod end must
cover at least 50% of inspection hole.
(e)
Remove rigging pin E-4.
(f)
Close stabilizer trim actuator circuit breakers.
(g)
Adjust stabilizer trim potentiometer per Chapter 22, Stabilizer Trim Potentiometer - A/T.
(8)
Restore airplane to normal hydraulic configuration (Ref 27-31-0 MP).
(9)
Test Elevator and Tab Control System
2. Elevator and Tab Control System Test
A. Equipment and Materials
(1)
Trammel Bar - F80055-1
(2)
0- to 50-pound push-pull spring scale with scale graduations of 0.5 pounds or smaller. Use Chatillon 50 x 0.50 Model DPP-50
500
Feb 20/92 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 27-31-0 Page 519
EFFECTIVITY
AIRPLANES WITH
COMPOSITE ELEVATORS
Elevator Tab Adjustment Measurement 501
27-31-0 Figure 508A Aug 01/94
Page 520
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A07510
500 Elevator Tab Adjustment After Flight Test May 01/98 Figure 508B 27-31-0 Page 520A/520B BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
500 Feel Computer Input Rod Adjustment
Jun 20/84 Figure 509 27-31-0
Page 521
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
(3)
Load measuring device, to measure elevator loads, perpendicular to the elevator surface at the trailing edge, consisting of loading block (17 inches long, 2 x 4 wood block, or equivalent) and push-pull spring scale in par. (2)
(4)
Load measuring device, to measure elevator tab loads, perpendicular to the tab surface at the trailing edge consisting of: loading block (6 inches long, 2 x 4 wood block, or equivalent) and push-pull spring scale in par. (2)
(5)
Device for measuring control column loads consisting of push-pull spring scale in par. (2) and a fitting for attachment of spring scale to control wheel
(a) Control Wheel Adapter Fitting - F72867-1
(6)
Scale - 0 to 2 feet, graduated in inches, tenths and hundredths of an inch
(7)
Control Column Protractor Assembly 4MIT65B80307-1 (Preferred) or F52485-500 (Optional)
(8)
Air Pressure Regulator - F72928-53 (preferred), -52 (alternate), or make to specification D6-32356
B. Test Elevator and Tab Control System
(1) Test Elevator Surface Friction and Balance
(a)
Remove elevator systems A and B hydraulic power (Ref 27-31-0).
(b)
Set horizontal stabilizer B dimension at 41.57 士0.05 inches, using trammel bar (Fig. 502).
(c)
Set mach trim actuator in null position (Ref 27-31-0, MP).
(d)
Move the control columns fore and aft through full travel at least 20 times.
(e)
Measure breakaway forces required to move elevator. Use spring scale and a loading block and apply force to elevator rear spar, adjacent to inboard rib.
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