EFFECTIVITY

 
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 On panel P7, close all PMS circuit breakers. On panel P6, close PMS EPR 1, PMS EPR 2, PMS EPR 3, and PMS EPR 4.
 (5)  
On panel P6, check that following circuit breakers are closed: PANEL LIGHTS, F/O and CTR; FLT DECK LIGHTS, PILOT PANEL.

 (6)  
On far right and left ends of main instrument lightshield panel (P72) rotate controls marked PANEL to right and note that uniform illumination appears in face of captain's and first officer's altimeter, airspeed indicator and vertical velocity indicator. On LH 011-030, 051-070, 082-099; AF 121, 122, 152-199; AT ALL; GN ALL; MD ALL, note that uniform illumination also appears in captain's and first officer's IAS/MACH indicator and first officer's static air temperature indicator.

 (7)  
On aft right corner of pilots' control stand P8, rotate control marked CENTER FWD PANEL to right and note that uniform illumination appears in face of pilots' total air temperature indicator and true airspeed indicator.

 (8)  
On flight engineer's auxiliary panel No. 6, rotate control marked PANEL to right and observe that uniform illumination appears in face of flight engineer's total air temperature indicator.

 (9)  
AF 121, 122, 157, 161, 183, 184; note that illumination also appears in the face of the TAT/EPRL (or TAT/N1) indicator.

 (10)
 In main equipment center, locate central air data computers (CADC) one and two. Examine each CADC to determine if it is a Boeing part number 60B00058, 60B40126, or HG480C1. On part numbers 60B00058 and 60B40126, check that no maintenance annunciators are yellow on front panels.

 (a)  
If annunciator shows yellow, reset annunciator.

 (b)  
Press and release self-test button.

 (c)  
If annunciator trips again, replace CADC. (Ref 34-12-01).

 (11)
 Adjust BARO set knob on altimeters until inches-of-mercury readout

 counter reads 29.92. Note altitude readout.  (12) If CADC No. 1 or 2 is a Boeing P/N 60B00058, perform the following  tests:
 (a)  
On CADC 1, 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.

 (b)  
Depress and hold SELF-TEST switch on CADC NO. 1; observe that ALT, M and TAS chassis warning lamps illuminate within 6 seconds and then extinguish within a maximum of 120 seconds.

 (c)  
With SELF-TEST switch depressed, check that warning flags are displayed on captain's indicated airspeed/mach indicator; and pilots' true airspeed indicator.

 (d)  
With SELF-TEST switch depressed, check that captains's servo-pneumatic altimeter reverts to standby mode, a STBY flag is displayed, and readout reverts to altitude previously set before altitude readout has slewed approximately 550 feet.

 EFFECTIVITY

 
 ALL  39.1 Page 502  Oct 25/9834-12-00
 (e)  While three chassis warning lamps are illuminated, observe that captain's indicator readouts of mach number; and pilots' readout of true airspeed 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.
 (f)  Release SELF-TEST switch and check that:
 1)  While computer servos are slewing to their normal positions, ALT, M and TAS chassis warning lamps illuminate. The CAS lamp will illuminate momentarily when SELF-TEST switch is released.
 2)  When normal position is reached, the three lamps 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.
 (13) If CADC No. 1 is a Boeing P/N 60B40126, perform the following tests:
 (a)  
Set functional test select switch to A/R position; depress button A and hold. All chassis warning lights should illuminate within 6 seconds and then extinguish within a maximum of 130 seconds.

 (b)  
With button A depressed, check that warning flags are displayed on captain's altimeter and indicated airspeed/mach indicator; and the true airspeed indicator.

 (c)  
With button A depressed, check that captain's servo-pneumatic altimeter reverts to standby mode, a STBY flag is displayed, and readout reverts to altitude previously set before altitude readout has slewed approximately 550 feet.

 (d)  
While three chassis warning lamps are illuminated, observe that captain's indicator readout of mach number; and readout of true airspeed are all slewing.
　
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