B767/22/101 Autoflight System
Boeing 767-200/300
Autoflight System Training manual For training purposes only LEVEL 1
ATA 22
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B767/22/101 Autoflight System
Training manual
This publication was created by Sabena technics training department, Brussels-Belgium, following ATA 104 specifications. The information in this publication is furnished for informational and training use only, and is subject to change without notice. Sabena technics training assumes no responsibility for any errors or inaccuracies that may appear in this publication. No part of this publication may be reproduced, stored in a retrieval system, or transmitted, in any form or by any means, electronic, mechanical, photocopying, recording, or otherwise, without the prior written permission of Sabena technics training.
Contact address for course registrations course schedule information Sabena technics training
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LIST OF EFFECTIVE PAGES 1................................................ 12 - 04 - 2012 2................................................ 12 - 04 - 2012 3................................................ 12 - 04 - 2012 4................................................ 12 - 04 - 2012 5................................................ 12 - 04 - 2012 6................................................ 12 - 04 - 2012 7................................................ 12 - 04 - 2012 8................................................ 12 - 04 - 2012 9................................................ 12 - 04 - 2012 10.............................................. 12 - 04 - 2012 11.............................................. 12 - 04 - 2012 12.............................................. 12 - 04 - 2012 13.............................................. 12 - 04 - 2012 14.............................................. 12 - 04 - 2012 15.............................................. 12 - 04 - 2012 16.............................................. 12 - 04 - 2012 17.............................................. 12 - 04 - 2012 18.............................................. 12 - 04 - 2012 19.............................................. 12 - 04 - 2012 20.............................................. 12 - 04 - 2012 21.............................................. 12 - 04 - 2012 22.............................................. 12 - 04 - 2012 23.............................................. 12 - 04 - 2012 24.............................................. 12 - 04 - 2012 25.............................................. 12 - 04 - 2012 26.............................................. 12 - 04 - 2012 27.............................................. 12 - 04 - 2012 28.............................................. 12 - 04 - 2012 29.............................................. 12 - 04 - 2012
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TABLE OF CONTENTS 1. AUTOFLIGHT CONTROL SYSTEM GENERAL. .......................................................................6 1.1. FMCS/AFCS Systems. ...........................................................................................................6 1.2. Yaw Damper System. ...........................................................................................................8 1.3. Automatic Stabilizer Trim and Mach Trim. ..........................................................................10 1.4. Autopilot/Flight Director System. ........................................................................................12 1.5. Thrust Management Computer. .........................................................................................14 1.6. Maintenance Monitor System. ...........................................................................................16 1.7. Flight Controls/Autoflight Interface. ...................................................................................18 2. AUTOPILOT GENERAL. .......................................................................................................20 2.1. Component Description. ....................................................................................................20 2.1.1. AFCS Mode Control Panel. .......................................................................................20 2.1.2. Disengage and Go-Around Switches.........................................................................22 2.1.3. Warning and Caution Annunciators..........................................................................24 2.1.4. Autoland Status Annunciators. .................................................................................26 2.1.5. EADI and EHSI Displays. ............................................................................................28
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LIST OF ILLUSTRATIONS ADI - AFDS DISPLAY - ABNORMAL ......................................................................................... 29 AFDS MODE CONTROL PANEL ............................................................................................... 21 A/P DISENGAGE GO-AROUND SWITCHES .............................................................................. 23 A/P WARNING & CAUTION ANNUNCIATIONS......................................................................... 25 AUTOFLIGHT INTERFACE SIMPLIFIED ...................................................................................... 19 AUTOLAND STATUS ANNUNCIATORS .................................................................................... 27 AUTOPILOT FLIGHT DIRECTOR SYSTEM.................................................................................. 13 AUTO STAB, TRIM & MACH TRIM SYSTEMS ........................................................................... 11 EADI & EHSI AFDS DISPLAY - NORMAL ................................................................................... 28 FMCS/AFCS SYSTEMS .............................................................................................................. 7 MAINTENANCE MONITOR SYSTEM ........................................................................................ 17 THRUST MANAGEMENT COMPUTER FUNCTIONS .................................................................. 15 YAW DAMPER SYSTEM ............................................................................................................ 9
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ABBREVIATIONS AND ACRONYMS A/P DISC A/T ADC AFCS AFDS ALT ALTN ARINC ASA CDU CMD CONF CONT CPU EADI EFI EFIS EHSI EHSV EICAS F/D FCC FLT FMA FMC FMCS FSPM GEN HDG HYD I/O ILS INOP IRS IRU LCCA LVDT MCDP MCP NAV
Autopilot Disconnect Auto/Thrust Air Data Computer Auto Flight Control System Autopilot Flight Director System Altitude Alternate Aeronautical Radio Incorporated Autoland status Annunciator Control Display Unit Command Configuration Control Central Processor Unit Electronic Attitude Director Indicator Electronic Flight Instruments Electronic Flight Instrument System Electronic Horizontal Situation Indicator Elctro-Hydraulic Servo Valve Engine Indicating & Crew Alerting System Flight/Director Flight Control Computers Flight Flight Mode Annunciator Flight Management Computer Flight Management Computer System Flap/Stabilizer Position Module Generator Heading Hydraulic(ally) Input/Output Instrument Landing system Inoperation Inertial Reference System Inertial Reference Unit Lateral Central Control Actuator Lineair Variable difference Transformer Maintenance Control and Display Panel Mode Control Panel Navigation
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NCD No Computed Data PCA Power Control Actuators PDU Power Drive Unit PTU Power Transfer Unit RA Radio Altimeter RVDT Rotary Variable difference Transformer SAM Stab trim and Aileron lockout Module SCM Spoiler Control Module SPD Speed SSFD Source selector Fault Detector STAB Stabilizer STCM Stab Trim Control Module THSP Thrust Mode Select Panel TMC Thrust Management Computer TMS Thrust Management System UNSCHED Unscheduled VAL Valve VLV Valve VNAV Vertical Navigation WEU Warning Electronics Unit
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1. AUTOFLIGHT CONTROL SYSTEM GENERAL. 1.1. FMCS/AFCS Systems. The flight management computer system (FMCS) and autoflight control system (AFCS) are shown along with the subsystems and major elements that comprise these systems. Interfaces and relationships between the individual elements are not shown. The primary elements of the FMCS are two flight management computers (FMC) and two control and display units (CDU). The CDU’s provide pilot interface with the flight management computer system. The flight management computers gather the necessary sensor data, perform computations and drive displays and other systems to navigate and guide the airplane.
The AFDS has three flight control computers and an AFCS mode control panel. A single computer, the thrust management computer (TMC) controls the throttles and calculates thrust limits. The TMS and AFDS use the AFCS mode control panel to provide an interface with the flight crew. The TMS also includes a thrust mode select panel for selecting the thrust limit mode. The yaw damper system and an automatic stabilizer trim system provide dutch roll damping and pitch trim respectively. The maintenance control and display panel (MCDP) provides a central location for storage and display of fault data for the FMCS, AFDS, and TMS via the flight management, flight control, and thrust management computers. It also provides ground test control and display for the autopilot-flight director and thrust management systems.
The autoflight control system (AFCS) automatically controls the airplane’s surfaces and engine thrust as required. Two subsystems, the autopilot-flight director system (AFDS) and the thrust management system (TMS) provide the primary surface and throttle control respectively.
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FMCS/AFCS SYSTEMS EFFECTIVITY ALL
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1.2. Yaw Damper System. Purpose. The yaw dampers move the rudder to dampen dutch roll, improve ride quality and to provide automatic turn coordination. Installation. Two yaw damper modules are installed moving two separate control actuators. The actuators operate independently and their outputs combine to move the rudder. There is no feedback to the rudder pedals from yaw damper operation. Operation. The yaw damper module uses inputs from the air data computers, inertial reference units, flight management computer system and the modal suppression accelerometers to compute commands which provide corrective rudder action through the yaw damper actuators. System Status. The yaw damper system may be tested while on the ground from the flight compartment. Proper operation is confirmed by appropriate INOP annunciation and rudder movement. The INOP lights on the yaw damper control panel indicate disengagement of the yaw damper.
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YAW DAMPER SYSTEM EFFECTIVITY ALL
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1.3. Automatic Stabilizer Trim and Mach Trim. Purpose. The stabilizer is automatically trimmed using commands generated by the autopilot and the mach trim systems. Operation. A/P stabilizer trim commands are generated when prolonged elevator deflection beyond the trim threshold occurs. The consequent change of stabilizer position reduces elevator deflection and drag. Mach trim operates if the A/P is not engaged and there is no manual electric trim command. As mach increases the stabilizer leading edge moves down. The pilot can override any automatic trim or mach trim command by applying opposite column force. Indicators and Annunciation. Two stabilizer position indicators are located on the aisle stand. An UNSCHED STAB TRIM (amber) light indicates when the stabilizer is trimming without a command to trim.
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AUTO STAB, TRIM & MACH TRIM SYSTEMS
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1.4. Autopilot/Flight Director System. General. The autopilot and flight director system (AFDS) provides automatic guidance and control of the airplane ailerons, elevators, and, for autoland, the rudder. It also provides the guidance processing for the flight director displays. Engagement and mode selection of the autopilot and flight director are accomplished through the AFCS mode control panel. Annunciation and Display. Each electronic attitude director indicator (EADI) displays flight director commands and an AFDS flight mode annunciator (FMA). The FMA indentifies AFDS status, roll/pitch arm and engaged modes. The autoland status annunciators identify the system capability and limitation status for autoland operations. The AFCS mode control panel has mode selector switch annunciation and reference readouts. A red A/P DISC light and an amber AUTOPILOT caution light gives visual alerts for A/P warnings and cautions.
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AUTOPILOT FLIGHT DIRECTOR SYSTEM EFFECTIVITY ALL
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1.5. Thrust Management Computer. Purpose. The thrust management computer (TMC) acts as a thrust limit computer and an autothrottle computer. These functions each have different modes, which are selected and annunciated in different places. Thrust Limit Functions. The thrust limit modes are selected on the Thrust Mode Select Panel (TMSP) or by the FMC in VNAV mode. They are annunciated on EICAS. The thrust limit functions are always engaged. The value of the thrust limit is annunciated on EICAS and used as an upper limit for autothrottle computations. Autothrottle Functions. The autothrottle modes are selected on the AFCS Mode Control Panel (MCP) or by the FMC in VNAV mode. They are annunciated on the EADI via EFIS. The autothrottle functions will not be engaged in a mode unless the AFCS MCP is in the A/T ARM position and a mode has been selected on the AFCS MCP. These functions will be used to position the throttles.
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THRUST MANAGEMENT COMPUTER FUNCTIONS EFFECTIVITY ALL
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1.6. Maintenance Monitor System. Purpose. The maintenance monitor system combines flight fault storage and ground test functions for the autopilot flight director system, thrust management system, and flight management system. Installation. One maintenance control and display panel (MCDP) is installed in the main equipment center. It is directly connected to the flight control computers, flight management computers, and the thrust management computer. Through these computers much of the airplane avionics can be tested. Operation. The MCDP is normally off. It turns on automatically at touchdown, and the connected computers send information about failures that occurred during the flight. This failure information is stored in the MCDP memory, and the maintenance technician can use it for fault isolation. The MCDP can also perform ground tests, which allow the technician to check proper operation of the autoflight systems. The MCDP is operated using the switches and readout on its front panel. It may also be operated from the flight compartment using a carry-on remote control panel. The MCDP readout is displayed on the EICAS CONF/MCDP page. This page may be displayed in flight if the EICAS flight test switch is in the flight test position.
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MAINTENANCE MONITOR SYSTEM EFFECTIVITY ALL
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1.7. Flight Controls/Autoflight Interface. Flight control computers (3) use the autoflight (A/P) servos to control airplane movement. FCC interfaces the thrust management computer (TMC), flight management computer (FMC), maintenance control and display panel (MCDP) with the specific A/P servo needed for airplane axis movement. FCC then commands the control valves in the appropriate servos to allow hydraulic pressure to move the output cranks. Output cranks connect to mechanical linkage for power control actuator (PCA) input. LVDT’s in each servo compare surface position versus servo position for the information needed to null commanded control valve inputs. Manual/electric overrides are available for each system.
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AUTOFLIGHT INTERFACE SIMPLIFIED EFFECTIVITY ALL
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Training manual
2. AUTOPILOT GENERAL. 2.1. Component Description. 2.1.1. AFCS Mode Control Panel. Function. The mode control panel (MCP) provides the primary interface between the flight crew and the flight director, the autopilot and the thrust management systems. These are subsystems to the automatic flight control system (AFCS). Front panel controls and displays allow for engagement mode selection, and control of these systems.
MCP Power Up. At power up the following displays are shown : - IAS/MACH display shows 200, - HDG shows 000, - Vert SPD is blanked, - ALT shows 10000, - All mode switch lights off.
Electrical Characteristics. Airplane power, 28 V dc and 5 V ac for panel lighting, is provided through three quick-disconnect connectors mounted on the rear panel. ARINC data buses, discrete inputs/outputs and 28 Vdc servo power are also routed through the quick-disconnects. Cooling Air. Forced airflow from the airplane main equipment cooling duct is supplied to the MCP at the rear of the MCP that automatically mates with the forced air system when the MCP is installed. Mechanical Characteristics. The MCP is installed and held in place by four screws. The four screws are captivated in the mounting rails provided by the glareshield structure and align with floating locknuts located in the bottom of the MCP. Each illuminated pushbutton switch contains four bulbs which are replaceable from the front without removing the MCP.
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AFDS MODE CONTROL PANEL
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2.1.2. Disengage and Go-Around Switches. Autopilot Disengage Switches. One autopilot disengage switch is located on each pilot’s control wheel. It is positioned on the side of the wheel farthest from the throttle handles. Each switch is a single action, multiple pole, pushbutton switch. Go-Around Switches. There is one thumb actuated switch assembly on each thrust lever. Each assembly contains three switches which provide the logic discrete used in go around mode of operation.
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2.1.3. Warning and Caution Annunciators. Autopilot Warning Light. The red A/P DISC warning light comes on to indicate that the autopilot has been disconnected either manually or automatically. This warning may be cancelled by pushing one of the autopilot wheel disengage switches or by reengaging the autopilot. Autopilot Caution Light. The amber AUTOPILOT caution light comes on to indicate a degraded autopilot condition. This caution is removed by disengaging the autopilot or engaging a different mode for which the condition does not apply. Other Systems Displays. The master warning and master caution lights on the glareshield are driven by the autopilot disconnect and mode fail logic respectively. These displays can be cancelled by pressing the lens caps. The EICAS upper display indicates “AUTOPILOT DISC” and “AUTOPILOT” for autopilot disconnect and autopilot caution respectively.
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A/P WARNING & CAUTION ANNUNCIATIONS EFFECTIVITY ALL
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2.1.4. Autoland Status Annunciators. Function. The autoland status annunciators provide the pilot with information on degradation from a triple redundant autoland capability. Component Details. Displays : - There is an upper and a lower display on each autoland status annunciator. The upper display indicates the autopilot systems actual autoland capability and the lower display indicates the degradation from land 3 capability. - Each display has three faces : one blank face, one A face and one B face. The displays are driven by magnetic coils. Switches : - There are two test switches. Pressing TEST 1 rotates the upper and lower display A faces into view. TEST 2 rotates the B faces into view. The reset switch can be used to clear the lower display (not during test).
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2.1.5. EADI and EHSI Displays. Normal Function. The EADI is the display for AFDS flight director commands, engage request status, and flight mode annunciation. The EHSI displays the selected heading index.
EADI Displays. AFDS Status is displayed at the upper right hand corner top line in green. AFDS Pitch Armed Mode is displayed at the upper left middle sector, bottom line in white. AFDS Pitch Operate Mode is displayed at the upper left middle sector, top line in green. AFDS Roll Armed Mode is displayed at the upper right middle sector, bottom line in white. AFDS Roll Operate Mode is displayed at the upper right middle sector, top line in green. EHSI Display. Selected Heading Index is displayed in magenta.
EADI & EHSI AFDS DISPLAY - NORMAL EFFECTIVITY ALL
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Abnormal Function. To notify the pilot of failures to the data driving his display. Display action taken by EFIS SG when data from FCC is valid. Bar drawn through display message response to a mode fail of affected mode. Flight director command bars removed response to NCD. Display action taken by EFIS SG when data from FCC is not valid. F/D displayed in upper right quadrant (Area 2) and all AFDS display removed response to data bus shutdown, invalid parity, or wrong word length.
ADI - AFDS DISPLAY - ABNORMAL
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