(a) This section covers the general description of the TMS. It covers the component details and operation of the autothrottle servomotor generator, disengage switches, leading edge slat switch, microswitch pack with thrust reverse switches, and clutch pack assembly.
(5)
Thrust Management Engine (Ref 22-33-00)
(a) This section covers the component detail and operation of the power lever angle transducers on the engines.
(6)
Thrust Management Warning and Annunciation (AMM 22-34-00)
(a) This section covers the general description and operation of the thrust management system warning and annunciation.
F. Maintenance Monitor (AMM 22-41-00) (Fig. 6)
(1)
The maintenance monitor system consists of a Maintenance Control Display Panel (MCDP). It provides a centralized record of flight faults from the flight control computers, thrust management computer, flight management computers, and their related sensors. It allows maintenance crews to perform ground tests on the AFDS, TMS, and their related sensors without additional ground test equipment.
(2)
This section covers the general description, component details, and operation of the MCDP.
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G. ILS Deviation Monitor (AMM 22-42-00).
(1) The ILS Deviation Monitor indicates excessive deviations from ILS centerlines (glideslope or localizer) during an approach to landing. This section covers the general description and operation of the ILS Deviation Monitor.
2. Abbreviations
_____________
A. The following list contains abbreviations commonly used in this chapter. ACARS ARINC Communications Addressing and Reporting System A/D Analog to Digital ADC Air Data Computer ADCS Air Data Computing System ADF Automatic Directing Finder ADIRS Air Data Inertial Reference System ADIRU Air Data Inertial Reference Unit AFCS Autoflight Control System AFDS Autopilot/Flight Director System AIDS Airborne Integrated Data System AIL Aileron ALCS Autopilot Lateral Control Servo ALT Altitude or Altimeter AOA Angle of Attack A/P Autopilot APCS Autopilot Pitch Control Servo APP Approach
Maintenance Monitor System
Figure 6
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APU Auxiliary Power Unit ARINC Aeronautical Radio Inc. ARR Arrival ARGS Autopilot Rollout Guidance Servo ASA Autoland Status Annunicator A/T Autothrottle ATC Air Traffic Control B/A Bank Angle BAT Battery BCD Binary Coded Decimal B/CRS Back Course BIT Built-In-Test BITE Built-In-Test-Equipment BNR Binary Numerical Representation CAA Civil Aviation Agency CAS Computed Airspeed CDU Control Display Unit CFT Control Force Transducer CLB Climb CMD Command CON Continuous CPU Central Processing Unit CRS Course CRT Cathode Ray Tube CRZ Cruise CSEU Control System Electronics Unit CWS Control Wheel Steering D/A Digital to Analog DADC Digital Air Data Computer DDM Difference in Depth of Modulation DEP Departure DES Descent DFDAU Digital Flight Data Acquisition Unit DH Decision Height DITS Digital Information Transfer System DME Distance Measuring Equipment D-TO Derated Takeoff EADI Electronic Attitude Director Indicator EAROM Electrically Alterable ROM ECS Environmental Control System EDHP Engine Driven Hydraulic Pump E/E Electrical/Electronics EFCU Elevator Feel and Centering Unit EFIS Electronic Flight Instrument System EGT Exhaust Gas Temperature EHSI Electronic Horizontal Situation Indicator EHSV Electrohydraulic Servovalve EICAS Engine Indication and Crew Alerting System EMHP Electric Motor Hydraulic Pump EMI Electromagnetic Interference ENG or ENGA Engage
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