AIRPLANES WITH PMS 02 Page 401 Dec 25/83
34-62-05
PMS ENGINE INTERFACE UNIT - ADJUSTMENT/TEST
___________________________________________
1. General
_______
A. This procedure tests the PMS engine interface unit (EIU). This test is designed to verify that a replaced PMS EIU has been properly installed and will operate. If the integrity of the total performance management system is in doubt, perform Performance Management System -Adjustment/Test (Ref 34-62-00).
B. Proper completion of this test requires the following systems or components be operational during the test.
CAUTION: ALL THE SAFETY PRECAUTIONS/WARNINGS REQUIRED TO BE OBSERVED
_______ DURING OPERATION OF THE FOLLOWING AIRPLANE SYSTEMS MUST BE ADHERED TO IN ORDER TO PREVENT DAMAGE TO TEST EQUIPMENT, AIRPLANE SYSTEMS AND INJURIES TO PERSONNEL.
(1)
Autopilot/Flight Director Pitch Channel
(2)
Central Air Data Computer System
(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. 32-09-02, Ground Safety Relay
D. 33-11-00, Pilots Panel Lights
E. 34-12-00, Central Air Data Computer System
F. 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.
EFFECTIVITY
AIRPLANES WITH PMS 02 Page 501 Apr 25/82
34-62-05
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 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
K. 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
L. Ensure that gross weight of airplane is entered into the PMS.
4. Test PMS Engine Interface Unit______________________________
A. Press PERF DATA key on the PMS CDU. Push the CDU slew switch as required to advance the display to PERF DATA ..... 4/4 page. With airplane on the ground, verify that data line 3 displays the word 'GND'.
B. Simulate AIR mode by opening GND SAFETY RELAY circuit breaker on the P6 circuit breaker panel. Verify that the word on CDU data line 3 changes from 'GND' to 'AIR'.
NOTE: Before opening circuit breaker for AIR mode simulation, refer to
____ 32-09-02 and observe all necessary safety precautions.
C. Close the GND SAFETY RELAY circuit breaker. Verify that the CDU display returns to 'GND'.
D. Press CDU CLEAR key.
5. Restore Airplane to Normal__________________________
A. Open all PMS circuit breakers on P7 circuit breaker panel.
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