NOTE: Since warning flags cover above indicator counters,
____ actual readout cannot readily be seen. It is possible, however, to observe that indicator readout is slewing.
(e) Release button A and check that: 1) While computer outputs are slewing to their normal positions, ALT chassis warning light illuminates. 2) When normal position is reached, the light will extinguish. 3) The indicators (except for the altimeter) slew to their original position and warning flags are out of view. 4) The servo-pneumatic altimeter remains in standby mode.
(14) If CADC No. 1 or 2 is a P/N HG480C1 or HG480C2, perform the following test:
(a) On CADC front panel, set the TEST SELECT switch to SLF-TST, depress and hold PUSH-TO-TEST button.
EFFECTIVITY
ALL 42.1 Page 503 Oct 25/9834-12-00
(b)
Check that warning flags are displayed on captain's servo-pneumatic altimeter and mach/airspeed indicator and the TAS indicator.
(c)
Check that captain's servo-pneumatic altimeter reverts to the standby mode before the altimeter readout has slewed 550 feet. Altimeter will return to the barometric altitude noted in step
10.
(d)
Check that captain's mach/airspeed indicator and the TAS indicator are slewing.
NOTE: Since warning flags cover above indicator counters,
____ actual readout cannot readily be seen. It is possible, however, to observe that indicator readout is slewing.
(e)
On CADC front panel, check that TEST VALID WHEN LIT light comes on and indicators stop slewing within 130 seconds.
(f)
Release the PUSH-TO-TEST button, the TEST VALID WHEN LIT light will go out.
(g)
The captain's mach/airspeed indicator and the TAS indicator will slew to original values and warning flags will be out of view.
(h)
The captain's servo-pneumatic altimeter will remain in the
standby mode. (i) Open the CADC 1 or 2 circuit breaker on the P7 Overhead Panel. (j) Close the CADC 1 or 2 circuit breaker on the P7 Overhead Panel.
(k) On CADC 1 and then CADC 2, set functional test select switch to A/R position; depress PUSH-TO-TEST switch and observe that A/R chassis warning lamp illuminates. Release PUSH-TO-TEST switch.
(l) Depress and hold SELF-TEST switch; observe that ALT, M, and TAS chassis warning lamps illuminate within 6 seconds and then extinguish within a maximum of 120 seconds.
(m)
With SELF-TEST switch depressed, warning flags are displayed on first officer's indicated airspeed/mach and static air temperature indicators.
(n)
With SELF-TEST switch depressed, first officer's altimeter reverts to standby mode, a STBY flag is displayed and readout reverts to altitude previously set before altitude readout has slewed 550 feet.
(o)
While three chassis warning lamps are illuminated, observe that first officer's indicator readouts of mach number, and static air temperature are all slewing.
NOTE: Since warning flags cover above indicator counters,
____ actual readout cannot readily be seen. It is possible however, to observe that indicator readout is slewing.
(p) Release SELF-TEST switch and check that:
EFFECTIVITY
ALL 44.1 Page 504 Oct 25/9834-12-00
PANEL P7 ELECTRONIC CIRCUIT BREAKER being operated) closed except one (All breakers INDICATORS
Altitude (Mach Number) Airspeed Static Air Temp Airspeed True Total Air Temp
CAPT F/O CAPT F/O F/O PILOTS' PILOTS'
PILOTS' TAS IND PILOTS' TAT IND SVO-PNEU ALTM IND 2 IAS/MACH IND 2 SAT IND CADC 2 CADC 2 ALTM IND 1 SVO-PNEU CADC 1 associated with Circuit breakers IAS/MACH IND 1 CADC 1 SYNC EXCIT CADC 1 associated with Circuit breakers CADC 2 SYNC EXCIT XX X X XX X X X X X X X X X X X X X X X
X = warning flag showing XX = warning flag showing - digital CADC only
____ All warning flags show OFF except altimeters which show STBY.
NOTE:
Flag Test
Figure 501
EFFECTIVITY
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C59390
CIRCUIT BREAKER ELECTRONIC INDICATORS
being operated) closed except one (All breakers PANEL P7 Altitude Airspeed (Mach Number) Temp Air Static Airspeed True TAT/N1 ORTAT/EPRL Temp Total Air
CAPT F/O CAPT F/O F/O PILOTS' PILOTS' FLT ENG
TAT/EPRL IND TAT/N1 IND ALTM IND 2 IAS/MACH IND 1 IAS/MACH IND 2 TAS IND F/E TAT IND CADC 2 PWR CADC 2 associated with Circuit breakers ALTM IND 1 CADC 1 SYNC EXCIT CADC 1 PWR CADC 1 associated with Circuit breakers SAT IND CADC 2 SYNC EXCIT X X X X X X X X X X X X X X X X X X X X X
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本文鏈接地址：747飛機維護手冊AMM CHAPTER 34 - NAVIGATION 第34章導航1(65)
