(2)
Install first locknut on forward bolt and tighten 120 to 140 pound-inches.
(3)
Install second locknut and tighten 60 to 85 pound-inches.
(4)
Install first locknut on aft bolt and tighten 85 to 100 pound-inches.
(5)
Install second locknut and tighten 30 to 35 pound-inches.
501
May 01/00 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 27-31-161 Page 401
Feel Actuator Installation 500
27-31-161Page 402 Figure 401 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. Feb 20/91
CAUTION: AFTER SETTING TORQUE ON SECOND LOCKNUTS, DO NOT ATTEMPT TO RESET TORQUE VALUE ON FIRST LOCKNUTS.
D. Remove protective plugs and caps and refit four flexible hydraulic lines to feel actuator.
E. Remove rigging pin E-5 from aft control quadrant.
F. Provide elevator systems A and B hydraulic power (Ref 27-31-0, MP).
G. Move control column fore and aft through full range of travel until movement is smooth and artificial feel is normal to bleed air from system. As air is bled out, artificial feel forces increase.
H. Check hydraulic connections at feel actuator for signs of leakage.
I. Test feel force system.
(1)
Test differential pressure switch.
(a)
Set T.E. flaps to full up position.
(b)
Check that feel differential pressure light is OFF.
pressure light is ON.
(d)
Position flight controls hydraulic system A switch to ON and system B switch to OFF. Check that feel differential pressure light is ON.
(e)
Position flight controls hydraulic system B switch to ON.
(f)
Operate captain's control column at a constant rate from full forward to full aft to full forward in approximately 2 seconds (27.5°/sec). The feel differential pressure light may flicker when stops are contacted, but check that light does not remain ON.
(2)
Check for pressure leakage in feel pitot system as follows:
(a)
Seal drain hole in each feel pitot tube located on fin.
(b)
Remove drain plugs from system A and system B pitot lines, located below feel computer.
(c)
Attach pressure gage lines from air pressure regulator to pitot system A and B drain holes, located below feel computer.
(d)
Attach regulated air pressure line from air pressure regulator to both pitot tubes on fin and pressurize pitot system to 5.0 + 0.1 psi (437 ± 4 knots).
CAUTION: DO NOT RAISE TEST PRESSURE ABOVE 6 PSI (474 KNOTS) AT ANY TIME DURING TEST.
(e)
Cut off pressure source by turning shutoff valve in air pressure regulator to off.
(f)
Pressure shall not drop more than 0.3 psi (12 knots) during a 2-minute period.
(g)
Reduce pitot pressure to zero.
(3)
Check feel forces as follows:
506
Oct 20/84 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 27-31-161 Page 403
NOTE: Ensure that elevator and feel computer are properly adjusted before proceeding.
(a)
Set the horizontal stabilizer B dimension at 41.57 + 0.01 inches.
(b)
Set mach trim actuator in null position (Ref 27-31-0 MP).
(c)
Check that flight controls hydraulic systems A and B switches are positioned to ON.
(d)
Using air pressure regulator, pressurize pitot system to 3.50 + 0.05 psi (370 ± 3 knots).
CAUTION: DO NOT RAISE TEST PRESSURE ABOVE 6 PSI (474 KNOTS) AT ANY TIME DURING TEST. OVERPRESSURE MAY DAMAGE COMPUTER.
(e)
Apply masking tape on tail cone along direction of right elevator trailing edge travel.
NOTE: Elevator travel measuring tool may be used in lieu of tape method.
(f)
Shake captain's control column lightly fore and aft to ensure that system is centered, and release.
NOTE: Ensure that control columns are not disturbed from this position during the next step.
(g)
Mark actual elevator trailing edge neutral position on masking tape.
(h)
Move captain's control column slowly aft and hold at indicated elevator position of
501
27-31-161 Page 404 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. Jun 20/92
1.95 + 0.05 inches up on right elevator. Check that force to hold column is 37.5 + 4.0 pounds.
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