R. Test feel force system and autopilot authority.
(1)
Test differential pressure switch.
(a)
Set T.E. flaps to full up position.
(b)
Check that feel differential pressure light is OFF.
(c)
Position flight controls hydraulic system A switch to OFF. Check that feel differential 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 ful1 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.
(3)
Check feel forces as follows:
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Jun 20/92 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 27-31-131 Page 407
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 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
1.95 + 0.05 inches up on right elevator. Check that force to hold column is 37.5 + 4.0 pounds.
NOTE: Pitot system check per step (2) must be satisfactory. Jiggle control column prior to each reading. Elevator position refers to actual elevator travel as measured from actual elevator neutral position. Using actual elevator trailing edge neutral position as a reference, mark elevator positions on masking tape.
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27-31-131 Page 408 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. Jun 20/92
(i)
Move captain's control column slowly forward and hold at indicated elevator position of 1.95 + 0.05 inches down on right elevator. Check that force to hold column is 38.5
+ 4.0 pounds.
(j)
Position flight controls hydraulic system B switch to OFF, leave system A switch ON.
(k)
Move captain's control column slowly aft and hold at indicated elevator position of
1.95 + 0.05 inches up on right elevator. Check that force to hold column is 37.5 + 4.0 pounds.
(l)
Move captain's control column slowly forward and hold at indicated elevator position of 1.95 + 0.05 inches down on right elevator. Check that force to hold column is 38.5
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