EFFECTIVITY ALL
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(o)
On autopilot/flight director mode select panel, place channel A autopilot engage switch to COMMAND position and altitude switch to ALT SEL position.
(p)
Turn BARO set knob on captain's altitude indicator in the CCW direction. Observe that control columns move back (pitchup maneuver).
(q)
Turn BARO set knob on captain's altitude indicator in the CW direction. Observe that control columns move forward (pitchdown maneuver).
(r)
On autopilot/flight director mode select panel, place channel A autopilot engage switch to OFF position.
(42) Test the indicated airspeed/mach indicators.
NOTE: The following steps test the command airspeed and pneumatic
____ portions of the airspeed indicators. The servo operated portions are tested as part of the CADC test.
(a)
Operate pneumatic test set to provide pressures required for test step one of Fig. 506.
(b)
On captain's and first officer's indicated airspeed/mach indicators, observe that indicated airspeed pointers (solid white) and maximum operating airspeed pointers (striped red and white) are reading within their respective tolerances for test step one of Fig. 506.
(c)
Repeat (a) and (b) for test steps two through seven on figure
506.
(d)
Return pitot and static pressures to ambient upon completion of last test step.
(e)
On autopilot/flight director mode select panel, set readout counter to 000.
(f)
On panel P7, verify that AUTO THROT AC and AUTO THROT DC circuit breakers are closed.
CAUTION: BEFORE ENERGIZING AUTO THROTTLE SYSTEM ENSURE THE
_______ FOLLOWING TO PREVENT AIRPLANE DAMAGE: ENGINES ARE SHUT DOWN, FUEL PUMPS ARE OFF, AND THROTTLE LEVERS ARE FREE TO MOVE.
(g) On autopilot/flight director mode select panel, place auto throttle ON-OFF switch to ON position and note that on lamp illuminates. Verify that internal vibrator is activated in each airspeed indicator.
DLH (h) On autopilot/flight director mode select panel, place auto DLH throttle ON-OFF switch to ON position and note that on lamp DLH illuminates.
(i) Adjust A/T speed control on mode select panel until counter readout indicates command airspeed of test point one on Fig.
508. On captain's and first officer's airspeed indicators, note that reference marker reads the airspeed commanded within tolerances of Fig. 508. Repeat for test steps 2 through 7 on Fig. 508.
EFFECTIVITY
ALL ATG Page 522 Apr 25/9834-12-00
(43) Test instantaneous vertical velocity indicators.
(a) On captain's and first officer's vertical velocity indicators,
locate zero adjust screw in lower left corner.
(b) Operate and ensure each is capable of moving indicator dial
over a range of at least | 400 feet-per-minute and position
both dials to zero feet-per-minute.
NOTE: When setting or reading a dial, lightly tap instrument____
case (not glass).
(c) Operate pitot-static system pneumatic test set such that
static system pressure is being reduced at a constant rate
equivalent to ascent at 1000 feet per minute as indicated on
test gauge. Verify that captain's and first officer's vertical
velocity indicators indicate 1000 (| 200) feet-per-minute.
(d) Continue this equivalent rate of ascent and verify, on both
indicators, that time required to go from an altitude of 2000
feet (27.821 inches of mercury) to 3000 feet (26.817 inches of
mercury) is between 50 and 75 seconds.
(e) Stabilize static system pressure above 3000 feet simulated
altitude and note that both vertical velocity indicator dials
return to zero (| 150) feet-per-minute.
(f) Operate pneumatic test set such that static system pressure
is being increased at a constant rate equivalent to descent at
1000 feet per minute as indicated on test gauge. Verify that
both vertical velocity indicators indicate 1000 (| 200) feet-
per-minute.
(g) Continue this equivalent rate of descent and verify, on both
indicators, that time required to go from an altitude of 3000
feet to 2000 feet is between 50 and 75 seconds.
(h) Return static system pressure to ambient and note that both
vertical velocity indicator dials return to zero (| 150) feet-
per-minute.
(44) Remove the two thermometers adjacent to the two total air
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