(2)
The limit select panel is located on the pilots aft control stand electronics panel (P8).
(3)
The limit indicator is located on the pilots center instrument panel (P2).
(4)
The computer unit, engine interface unit and the switching unit are located on the E-2 rack in the main equipment center.
D. Principal airplane systems and indicators that are connected to the PMS (Fig. 2) are listed below:
(1)
Air Cycle Pack System (Chapter 21-51).
(2)
Autopilot/Flight Director Pitch Channel (Chapter 22-12).
(3)
Auto Throttle System (Chapter 22-31).
(4)
Triple-Slotted Trailing Edge Flap System (Chapter 27-51).
(5)
Leading Edge Flap System (Chapter 27-81).
(6)
Engine Nacelle Thermal Anti-Icing (Chapter 30-21).
(7)
Central Air Data Computer System (Chapter 34-12).
(8)
Air Data Pressure Instruments (Chapter 34-13).
(9)
Low Range Radio Altimeter (Chapter 34-33).
(10)
Inertial Navigation System (Chapter 34-41).
(11)
DME System (Chapter 34-55).
(12)
Engine Bleed Air Distribution System (Chapter 36-11).
(13)
Fuel Flow Indicating System (Chapter 73-31).
(14)
Engine Pressure Ratio (EPR) Indicating System (Chapter 77-11).
(15)
Engine Tachometer System (Chapter 77-12).
2. Operational Description
_______________________
EFFECTIVITY
AIRPLANES WITH PMS 04 Page 1 Apr 25/82
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SEE J
SEE SEE I C MH GSEE K O P N SEE SEE SEE I G L K O P
SEE A
SEE B
E-3
RACK
E-2 RACK
E-1 RACK
FWD
MAIN EQUIPMENT CENTERSEED E F
P73 RELAY PANEL
Performance Management System Component Location
Figure 1 (Sheet 1)
EFFECTIVITY
AIRPLANES WITH PMS704 Page 2
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LIMIT SELECT PANEL
CONTROL DISPLAY UNIT COMPUTER UNITLIMIT INDICATOR PANEL
Performance Management System Component Location Figure 1 (Sheet 2)
647432
EFFECTIVITY AIRPLANES WITH PMS
704 Page 3
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ENGINE INTERFACE UNIT
a PATHARM
gPATH
VERT
ALERT
a
1
VA L
E E
R R
T T
a
SPD ARM a
gSPEED
PMS
a
PMS ALERT LIGHT
2
VERTICAL ALERT LIGHT
IB AIRPLANES
PMS MODE ANNUNCIATOR
AF AIRPLANES
Performance Management System Component Location
Figure 1 (Sheet 3)
EFFECTIVITY AIRPLANES WITH PMS
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Performance Management System Component Location
Figure 1 (Sheet 4)
EFFECTIVITY AIRPLANES WITH PMS
704 Page 5
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HORIZONTAL SITUATION INDICATOR ATTITUDE DIRECTOR INDICATOR
IB AIRPLANES
AF AIRPLANES
Performance Management System Component Location Figure 1 (Sheet 5)
EFFECTIVITY AIRPLANES WITH PMS
714 Page 6
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A. The performance management system (PMS) controls the flight path of the airplane so as to acheive the maximum fuel efficient operation possible within the constraints imposed by air traffic control (ATC); during the climb, cruise and descent phases of the flight. PMS control is through the autopilot-flight director and through the throttle servomotor. Fuel efficiency is achieved in two basic ways:
(1)
Steering the airplane to the most fuel efficient speed/altitude and geographic schedules.
(2)
Smoothly following the desired schedule in such a way as to reduce losses due to unnecessary airplane or engine accelerations.
B. In order for the PMS to compute optimum fuel saving parameters, the airplane and engine performance characteristics and limitations are stored in the PMS computer unit. These data are used as the basis for the control of pitch and thrust. Also dynamic airframe and engine performance data are received by the computer unit from other airplane systems (Fig. 2).
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