(3)
To verify software validity, perform the software sum check. To perform the software sum check press PMS CDU STS/TEST key, press line select switch 1, and then key in 0, 1, 0, 0, 0. Observe PMS CDU, and verify for the software sum check that the CDU display appears as shown below, with respect to the applicable computer unit software part number (P/N).
(a) For software P/N 7891910-005 verify that CDU display for sum check appears as follows:
STS 1/1
PMS 01000
041647
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(b)
For software P/N 7891910-009,
verify that CDU display for sum check appears as follows:
STS 1/1
PMS 01000
022537
(c)
For software P/N 7891910-110, verify that CDU display for sum check appears as follows:
STS 1/1
PMS 01000
004677
(d)
For software P/N 7891920-001, verify that CDU display for sum check appears as follows:
STS 1/1
PMS 01000
013055
(4) Press CDU CLEAR key.
C. Verify Air Data Mach Number.
(1)
Adjust the baro set knob on the F/O's altimeter to 29.92 inches of mercury.
(2)
Ensure that the airplane pitot static system is at ambient atmospheric pressure.
(3)
Press PERF DATA key on the PMS CDU. Push the CDU slew switch as required to display PERF DATA ..... 1/4 page. The left two spaces on data line 1 indicate CAS and Mach respectively as follows:
'XXX/“XXX'
(4)
Verify that the PMS CDU display of Mach is between 0.05 Mach and
0.2 Mach.
(5)
Press CDU CLEAR key.
D. Verify LRRA status
(1)
Confirm that both LRRA-1 and LRRA-2 systems are operating and indicating altiudes below 2500 ft.
(2)
On the PMS CDU press and release PERF DATA key, using FWD/BACK switch, slew to PERF DATA ... 4/4 page.
(3)
Verify that line 3 displays LRRA status as "R/A*".
(4)
Open LRRA-1 and LRRA-2 system circuit breakers on the P7 circuit breaker panel.
(5)
Verify LRRA status changes to "R/A".
(6)
Close LRRA-1 and LRRA-2 system circuit breakers.
(7)
Verify LRRA staus changes to "R/A*".
5. Restore Airplane to Normal
__________________________
A. Open all PMS circuit breakers on P7 circuit breaker panel.
B. On IB airplanes, also open all PMS circuit breakers on P6 circuit breaker panel.
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C. If operation of the INS is no longer required, place each INS mode selector switch in OFF position (Ref 34-41).
D. Remove electrical power if no longer required (Ref 24-22-00).
E. Remove equipment cooling if no longer required (Ref 21-58-00).
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PMS ENGINE INTERFACE UNIT - REMOVAL/INSTALLATION
________________________________________________
1. General
_______
A. The engine interface unit is installed in the main equipment center on shelf E2-5 and held in place by two hold down hooks and retaining nuts. The engine interface unit is electrically connected by one connector in the rear of the unit.
2. Equipment and Materials
_______________________
A. Extractor Assembly
3. Referenced Procedures
_____________________
A. 34-62-00, Performance Management System - Adjustment/Test
B. 20-11-22, Electrical/Electronic Black Box - Removal/Installation
4. Remove PMS Engine Interface Unit
________________________________
A. Open following circuit breakers on P6 circuit breaker panel.
(1)
WING ISO VALVE-R
(2)
WING ISO VALVE-L
B. Open following circuit breaker on P7 circuit breaker panel.
(1)
PMS CMPTR
(2)
PMS SU PRIM
C. Remove PMS engine interface unit (Ref 20-11-22).
5. Install PMS Engine Interface Unit
_________________________________
A. Place PMS engine interface unit on mounting shelf.
B. Install PMS engine interface unit (Ref 20-11-22).
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本文链接地址：747飞机维护手册AMM CHAPTER 34 - NAVIGATION 第34章导航4(177)
