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 C.  The PMS receives inertial reference data from the inertial navigation system (INS). The PMS transmits waypoint data to the INS. Lateral steering equations are solved in the INS while vertical steering (pitch) is computed in the PMS.
 3.  System Functional Description_____________________________
 A.  Control of the performance management system (PMS) is provided by the keyboard on the PMS CDU. The PMS CDU also functions as a display device to display PMS related information in alphanumeric format.
 B.  If the INS is in the PMS waypoint control mode, waypoint data for lateral navigation is loaded at the PMS CDU. In the PMS waypoint control mode, the INS CDU's operate only as display units, control of the INS is through the PMS CDU.
 NOTE: To control the INS from the INS CDU, INS waypoint control is
____ selected at the PMS CDU. However, present position coordinates are inserted only at the INS CDU. These coordinates may be loaded into the INS, when the INS is in either the PMS waypoint control mode or the INS waypoint control mode.
 C.  Variables required for performance computing are entered into the PMS CDU. These variables include fuel, gross weights and static air temperature. The PMS CDU displays engine and performance parameters for monitoring purposes.
 D.  On IB Airplanes, the limit select panel provides a means to select alternate engine ratings, a decremental derate and flight limit modes for computing EPR limits.
 E.  On AF Airplanes, the limit select panel provides a means to select alternate engine ratings, a decremental derate and flight limit modes for computing engine N1 percent RPM limits.
 F.  On IB Airplanes, the limit indicator provides a display of total air temperature, the selected engine rating, EPR limit and the selected flight limit mode.
 EFFECTIVITY

 AIRPLANES WITH PMS    03 Page 7  Apr 25/83

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 G.  On AF Airplanes, the limit indicator provides a display of total air temperature, the selected engine rating, engine percent RPM limit and the selected flight limit mode.
 H.  The engine interface unit receives data signals from each engine and converts the data into a format usable by the PMS computer unit.
 I.  The PMS computer unit computes vertical steering and thrust commands as dictated by the PMS mode of operation. The computer unit provides a vertical steering signal to the autopilot flight director system.
 J.  The throttle servomotor drives the throttles on the aisle stand. Under normal conditions the throttle servomotor receives thrust commands from the auto throttle system; however, when the PMS mode of operation is selected the throttle servomotor receives thrust commands from the PMS.
 K.  The PMS mode of operation is selected at the autopilot flight director mode select panel (A/P-F/D MSP), by placing the TURB/SPEED switch to the PMS position. In the PMS mode of operation, the PMS vertical steering signal is coupled to the autopilot flight director by placing the MSP autopilot engage switch to the command position. Also in the PMS mode of operation, PMS thrust commands are coupled to the throttle servomotor by placing the MSP auto throttle engage switch to ON. Clearance altitudes are selected at the altitude select control on the MSP.
 L.  The performance management system is designed to be used only during the climb, cruise and descent phases of a flight. Therefore, below 2500 feet of radio altitude the PMS cannot be coupled to the autopilot flight director or to the throttle servomotor. On IB Airplanes, however, the PMS continuously computes the EPR limit based on dynamic parameters and selected engine ratings. This data is available on a full time basis for display purposes. On AF Airplanes, however, the PMS continuously computes the N1 limit based on dynamic parameters and selected engine ratings. This data is available on a full time basis for display purposes.
 M.  The PMS has the capacity to store up to 36 waypoints for lateral navigation. All waypoints are loadable through the PMS CDU and are transferred remotely into the INS. During the transfer, the PMS remotely loads the TO waypoint and the next seven waypoints into the INS. This process continues automatically as the airplane progresses on the flight path. Additionally, the PMS CDU has the capability to add altitude and speed restrictions to the waypoints for defining a Bottom of Descent (BOD) point in the vertical profile.
 N.  The mode options available for performance management system operation during each phase of flight are as follows:
 (1)
Climb

 (a)
Optimum (Minimum Fuel Speed)

 (b)
Maximum Angle

 (c)
Manual (Selectable Speed)

 

 (2)
Cruise

 (a)
　
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本文鏈接地址：747飛機維護手冊AMM CHAPTER 34 - NAVIGATION 第34章導航4(118)