(3)
Inertial Navigation System
C. All systems and components that are operational during this test should be maintained at their normal operating conditions with the airplane on the ground unless otherwise specified.
2. Referenced Procedures
_____________________
A. 21-58-00, Rack-Mounted Equipment Cooling System
B. 24-22-00, Manual Control (Apply Power)
C. 33-11-00, Pilots Panel Lights
D. 34-41-00, Inertial Navigation System
3. Prepare for Test
________________
A. Set the altitude selector on the autopilot flight director mode select panel (A/P-F/D MSP) to zero altitude.
B. Set the AUTOPILOT ENGAGE switch on the A/P-F/D MSP to OFF.
C. Ensure the TURB/SPEED switch on the A/P-F/D MSP is not set to PMS.
D. Provide electrical power (Ref 24-22-00).
E. Check for proper operation of pilot's panel illumination, indicator lamps, and annunciator lights using master test and dim control (Ref 33-11-00).
F. Provide cooling air to electronic equipment (Ref 21-58-00).
CAUTION: ENSURE EQUIPMENT COOLING IS OPERATING BEFORE TURN ON OF
_______ ELECTRONIC SYSTEMS, OR DAMAGE TO EQUIPMENT MAY RESULT. EQUIPMENT COOLING SYSTEM MUST BE SET FOR NORMAL COOLING AS DESCRIBED IN 21-58-00.
G. Provide cooling air to INS equipment (Ref 21-58-00).
CAUTION: ENSURE THAT COOLING AIR IS AVAILABLE TO INS NAVIGATION UNITS
_______ BEFORE OPERATING INS. FAILURE TO PROVIDE ADEQUATE AIR SUPPLY WILL RESULT IN FAILURE OF INS NAVIGATION UNITS.
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34-62-04
H. Ensure that present position latitude and longitude coordinates are entered into each INS (Ref 34-41). Verify that the mode selector switch, on each INS MSU, is set to ALIGN.
I. On IB airplanes, ensure that the AUTO/MAN/RMT switch on each INS CDU is set to MAN.
J. Ensure that the airplane pitot static system is at ambient atmospheric pressure.
K. Ensure the following circuit breakers are closed.
CIRCUIT BREAKER_______________ LOCATION
PMS CDU P7 PMS SU ALTN P7 PMS SU PRIM P7 PMS CMPTR P7 PMS LSP P7 PMS ADS P7 PMS LIMIT IND P7 CONT POS FLAP OUTBD P6
L. On IB airplanes,
also ensure that the following circuit breakers are closed.
CIRCUIT BREAKER_______________ LOCATION
PMS EPR-1 REF P6 PMS EPR-2 REF P6 PMS EPR-3 REF P6 PMS EPR-4 REF P6
M. Ensure that gross weight of airplane is entered into the PMS.
4. Test PMS Computer Unit______________________
A. Verify PMS computer unit software part number.
(1) Observe program label on front panel of PMS computer unit; and note the PMS software program part number (P/N).
NOTE: The PMS computer unit is located on the E2 rack, in the main
____
equipment center.
(2) To check software P/N on PMS CDU; press PLNG key on CDU to display PLNG INIT.....1/6 page, and then press line select switch 2. Verify that PMS CDU display appears as shown below, with respect to the applicable computer unit software P/N.
(a) On IB airplanes, for software P/N 7891910-005, top line of CDU display is as follows:
PMS 7891910-005 1/6
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34-62-04
(b)
On IB airplanes,
for software P/N 7891910-009,
top line of CDU display is as follows:
PMS 7891910-009 1/6
(c)
On IB airplanes,
for software P/N 7891910-110,
top line of CDU display is as follows:
PMS 7891910-110 1/6
(d)
On AF airplanes,
for software P/N 7891920-001,
top line of CDU display is as follows:
PMS 7891920-001 1/6
(3)
When displaying the PMS software P/N on PMS CDU, the INS software P/N can be observed on CDU data lines 1, 2, and 3. An example of INS software P/N, appearing on CDU data lines 1, 2, and 3, is shown below:
INS 1 25-20
INS 2 25-20
INS 3 25-20
(4)
Press CDU CLEAR key.
B. PMS Computer Software Sum Check
(1)
Press PLNG key on the PMS CDU, and then press line select switch
2. Observe and note the PMS computer unit software part number; on the top line of the CDU display.
(2)
Press CDU CLEAR key.
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