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RELAYS C793
PMS Vertical Path Deviation Display
Figure 17
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B7025CAPT VERT ALERT (P1) F/O PMS MODE ANNUNCIATOR (P72)
PMS Mode and Alert Annunciators
Figure 18
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N255 PMS LIMIT INDICATOR (P2) THAT REQUIRE AN INCREASED Vmo, WHEN
OPERATING WITH FUEL IN RESERVE FUEL TANKS
Performence Management System Power Distribution
Figure 19
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21. Performance Management System and INS Interface (Fig. 15)
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A. Digital data is transmitted between PMS units (control display unit, limit select panel, limit indicator, computer unit and engine interface unit) by a two wire connection. The data is on a binary (return to zero) format.
B. Binary data is transmitted between INS units and between the INS and the PMS by a six wire clock, sync and data connection.
C. The flight engineer's clock provides GMT to the computer unit.
22. PMS, Autothrottle, A/P-F/D Interface (Fig. 16)
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A. Below 2500 feet of radio altitude the PMS cannot be coupled (due to a signal from the LRRA) to the autopilot flight director or to the throttle servomotor. Above 2500 feet the PMS can be coupled to these systems for vertical flight control.
B. The PMS mode of operation is selected at the A/P-F/D mode select panel, by placing the TURB/SPEED switch to the PMS position.
C. When the PMS mode is selected; placing the AUTOPILOT ENGAGE switch to COMMAND (CMD) and/or placing the FLT DIR switch to ON, causes the A/P-F/D pitch computers to receive vertical (pitch) steering from the PMS computer.
NOTE: The AUTOPILOT ENGAGE switch and the FLT DIR switch are on the
____
A/P-F/D mode select panel.
D. The throttle servomotor, which drives the throttles on the aisle stand, can be coupled either to the auto throttle computer or to the PMS computer. When the PMS mode of operation is selected the Ledex relay in the switching unit transfers the servomotor from the auto throttle computer to the PMS computer.
E. When the PMS is in the PMS mode of operation, placing the autothrottle engage switch (on the A/P-F/D mode select panel) to ON causes the throttle servomotor to receive thrust commands from the PMS computer.
23. PMS Vertical Path Deviation Display (Fig. 17)
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A. When INS lateral navigation is displayed on the HSI, and the PMS mode of operation is selected, the HSI glide slope pointer indicates airplane vertical path deviation from the PMS computed descent path; if the PMS descent is oriented to a bottom of descent (BOD) waypoint (geographically oriented descent).
B. When the PMS is without regard to waypoints (non-geographically oriented descent) the PMS causes the pointer to be biased up out of view. Also, the pointer is biased up out of view when the PMS is not in the PMS mode of operation.
C. In the PMS mode of operation the ADI fast/slow pointer is biased out of view.
24. PMS Mode and Alert Annunciators (Fig. 18).
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A. The vertical alert annunciators light just prior to a vertical flight path change; the annunciators extinguish just after the change occurs.
B. The PMS alert annunciator lights when the PMS computer unit detects a PMS malfunction.
C. The PMS mode annunciators light to indicate descent mode of operation.
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D. The vertical alert, PMS alert, and PMS mode annunciator lights can be tested from the master dim and test switch. In addition bright or dim illumination can be selected for the PMS mode annunciators.
25. Performance Management System Power Distribution (Fig. 19)________________________________________________
A. The PMS requires 115V AC power, 26V AC power, and 28V DC from the airplane electrical system.
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