34-62-00
1) Ensure that the Autopilot/Flight Director Pitch Channel is
operational (Refer to 22-12).
2) Verify that the Auto Throttle System is operational
(Refer to 22-31).
3) Ensure that the trailing edge (TE) flaps and the leading
edge (LE) flaps are retracted to the full up position.
NOTE: For trailing edge flap operation refer to 27-51-00,____
Maintenance Practices. For leading edge flap
operation refer to 27-81-00, Maintenance
Practices.
4) Select CLB limit mode on the PMS limit select panel (LSP).
Verify that the PMS limit indicator (LI) displays CLB.
5) Open LRRA-1 and LRRA-2 system circuit breakers, to
simulate a radio altitude above 2500 feet on LRRA-1 and
LRRA-2 respectively.
6) Ensure that present position latitude and longitude
coordinates are entered into each INS (Refer to 34-41).
Verify that the mode selector switch, on each INS MSU,
is set to ALIGN.
7) Ensure that gross weight of airplane is entered into the
PMS.
8) Select a clearance altitude on the autopilot flight
director mode select panel (A/P-F/D MSP).
9) Position all engine throttle levers to the aft limit.
10) On the A/P-F/D MSP place the autopilot engage switches to the command (CMD) position, and the Captain's and F/O's FLT DIR switches to ON.
11) Set the TURB/SPEED switch to the PMS position, on the A/P-F/D MSP.
12) On the A/P-F/D MSP set the auto throttle engage switch to ON.
(13) PMS Shut Down
(a)
Place the A/P-F/D TURB/SPEED switch away from the PMS position. Set the auto throttle engage switch to OFF.
(b)
Open all PMS circuit breakers.
(c)
Remove electrical power if no longer required.
EFFECTIVITY
AIRPLANES WITH PMS 03 Page 66 Aug 25/83
34-62-00
PERFORMANCE MANAGEMENT SYSTEM - TROUBLE SHOOTING
________________________________________________
1. General
_______
A. The performance management system (PMS) contains self testing features that provide warning indications when a failure occurs. The warning indications consist of a PMS annunciator on the PMS CDU and a PMS annunciator on the pilots instrument panel. When the PMS computer unit detects a malfunction both PMS annunciators light steadily.
B. The conditions that cause PMS annunciators to light also produce PMS malfunction codes, for storage in the memory of the PMS computer unit. These codes are displayed on the PMS CDU when the CDU STS/TEST key is pressed.
2. PMS Malfunctions
________________
A. If the PMS has waypoint control over the INS, INS failures cause PMS malfunction codes (pertaining to the INS failures) to be displayed on the PMS CDU.
B. PMS malfunction codes are stored in the PMS computer memory, until cleared from the memory by pressing the STS/TEST key on the PMS CDU. The memory will not retain a record of malfunctions after they are cleared.
NOTE: If the codes are not cleared by pressing the STS/TEST key, the
____ computer memory retains the codes even after a PMS off-on cycle.
EFFECTIVITY
AIRPLANES WITH PMS 02 Page 101 Apr 25/82
34-62-00
C. Displaying Malfunction Codes (Fig. 101)
(1)
Press STS/TEST key on the PMS CDU, to display the PMS status page. If malfunction codes are present they will be displayed next to the page title (for example code 14). An action code message will also be displayed, on data line 1. Record the malfunction code number.
(2)
Press STS/TEST key again, another malfunction code if present, will appear next to the page title (for example code 38 or code 52). An action code message will be displayed on data line 1. Record the new malfunction code number.
NOTE: If there is more than one active malfunction code and
____ these codes have different action codes, only the message for the most serious action code is displayed.
(3)
Press the STS/TEST key repeatedly until the malfunction codes begin to repeat or until the codes disappear.
(4)
If all malfunction codes disappear, the original problem was intermittent. If the codes begin to repeat the problem is not temporary; in this case refer to the action code message on data line 1.
D. PMS Malfunction Codes (Fig. 102)
(1) PMS malfunction and action codes are listed on the figure, with a description of the codes. Also described are the affects of PMS malfunctions upon computer unit valid output signals.
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