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ATR72 -AIRCRAFT MAINTENANCE MANUAL - Description/Operation

HIGHLIGHTS REVISION NO. 09 Mar 01/15 Pages which have been revised are outlined below, together with the Highlights of the Revision CH/SE/SU C PAGES

REASON FOR CHANGE

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ATR72 -AIRCRAFT MAINTENANCE MANUAL - Description/Operation

CHAPTER 00 INTRODUCTION LIST OF EFFECTIVE PAGES N, R or D indicates pages which are New, Revised or Deleted respectively Remove and insert the affected pages and complete the Record of Revisions and the Record of Temporary Revisions as necessary CH/SE/SU

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CHAPTER 00 INTRODUCTION TABLE OF CONTENTS SUBJECT INTRODUCTION General Chapter Breakdown Policy Selection Policy

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INTRODUCTION 1. General The Description Operation Manual for the ATR42 or ATR72 Aircraft is in accordance with ATA Specification No. 100, Revision 21. GIE ATR declines all responsability in the event that the instructions given in the Description/Operation Manual are not observed in their entirety. If any or all of the Manual is translated, the official version shall be the original French Language version produced by the GIE ATR. ATR Technical Publications use both metric and non-metric systems of measurement. The system used in the original reference documents is quoted first, followed by the conversion into the other system in brackets. 2. Chapter Breakdown Policy Each chapter is broken down into sections or subsystems (combinations of functional/physical groups). Example : 29-00-00 - Hydraulic Power 29-10-00 - Main 29-20-00 - Auxiliary Each section is broken down into sub-sections or sub-subsystems (Installations/Circuits). Example : 29-10-00 Main 29-11-00 Main Hydraulic Power - Green 29-12-00 Main Hydraulic Power - Blue XX-00-00 System

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XX-20-00 Group of Installations/Circuits

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XX-12-00 Installations/Circuits

00 Description and Operation X allocated by the ATA 100 specification X allocated by GIE ATR 3. Selection Policy The information contained in the "DESCRIPTION AND OPERATION" is covered at three Levels : A. At Chapter/System Level (Example XX-00-00) Describes the relationship of functional/physical groups of the system, together with scope and outstanding features. Relationship between subsystems and other systems is also explained. As a rule, illustrations at this Level are simplified block diagrams or general views of the aircraft giving the Location of the main compo-

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ATR72 -AIRCRAFT MAINTENANCE MANUAL - Description/Operation

nents (i.e. flight controls and Landing gear, etc.). B. At Section/Subsystem Level (XX-10-00) Details the functional/physical groups of the subsystem, the relationship between the groups and other systems, and the scope of each group. At this Level, the information is illustrated in the form of block diagram and simplified schematics. C. At Sub-Section/Sub-Subsystem Level (XX-11-00) (Installation/Circuit Level) This Level includes the following : (1)General Main functions of the functional/physical group and their relationship with other groups and systems. (2)Details all the components within an installation/circuit - Component electrical or mechanical identification (ITEM) - Component name (the designation in this column and on the illustrations indicates the functions performed by the component) - Instrument panel which accommodates the controls/indicators - The zone in which the component is Located - Means of access to the component (access door No. XXXZZ). (3)Description The part of the system concerned is briefly detailed. (4)Component description Broad descriptive and operational information on each component of the functional/physical group. When a complex component is involved, an illustration is provided to show the component Location on the aircraft, a perspective view, a simplified cross-section, and the symbol used in schematics. For simple components, the symbols used are those prescribed by ATA Specification No. 100. (5)0peration Detailed operational information on the installation/circuit. The associated schematic shows the identification numbers of each component and associated electrical connections.

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HIGHLIGHTS REVISION NO. 09 Mar 01/15 Pages which have been revised are outlined below, together with the Highlights of the Revision CH/SE/SU C PAGES

REASON FOR CHANGE

EFFECTIVITY

CHAPTER 10

L.E.P. 1- 1 Revised to Reflect this revision indicating new,revised, and/or deleted pages

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CHAPTER 10 PARKING & MOORING LIST OF EFFECTIVE PAGES N, R or D indicates pages which are New, Revised or Deleted respectively Remove and insert the affected pages and complete the Record of Revisions and the Record of Temporary Revisions as necessary CH/SE/SU

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CHAPTER 10 PARKING & MOORING TABLE OF CONTENTS SUBJECT ACCESSORY EQUIPMENT Aircraft Tool Kit

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ACCESSORY EQUIPMENT 1. Aircraft Tool Kit A. Description The aircraft Tool Kit comprises - a set of Landing gear safety pins, - a cargo compartment door emergency control crank handle (if installed), - a tool kit.

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B. Description and Location (1)1n the flight compartment a set of three Landing gear safety pins stowed behind of the First Officer's seat (See IPC 25-71-10 for Localization).

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(2)1n the aircraft tool kit Located in aft cargo compartment (See IPC 25-71-20 for Localization) 2 engine covers, 2 main Landing gear nacelle air intake covers, - 2 wing NACA intake blanking covers, 6 static probe covers, 3 pitot probe covers, 1 or 2 temperature probe covers, 2 engine air intake covers (if installed), 2 propeller straps (if installed), - 1 pilot control column strap (if installed).

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(3)1n forward/aft cargo compartment : - a cargo compartment door emergency control crank handle (See IPC 25-71-20 for Localization).

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HIGHLIGHTS REVISION NO. 06 Mar 01/19 Pages which have been revised are outlined below, together with the Highlights of the Revision CH/SE/SU C PAGES

REASON FOR CHANGE

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L.E.P. 1- 2 Revised to Reflect this revision indicating new,revised, and/or deleted pages T. OF C. Revised to reflect this revision 2

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Layout Improved or Effectivity Updated 3

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ATR72 -AIRCRAFT MAINTENANCE MANUAL - Description/Operation

CHAPTER 22 AUTO FLIGHT LIST OF EFFECTIVE PAGES N, R or D indicates pages which are New, Revised or Deleted respectively Remove and insert the affected pages and complete the Record of Revisions and the Record of Temporary Revisions as necessary CH/SE/SU

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CHAPTER 22 AUTO FLIGHT TABLE OF CONTENTS SUBJECT CH/SE/SU AUTO FLIGHT - GENERAL 22-00-00 Introduction Functions Available Modes AFCS Organization AUTOPILOT/FLIGHT DIRECTOR - YAW DAMPER 22-10-00 Introduction Functions Performances System Description AFCS Components Control Indicating System Architecture AFCS Architecture Interface in AFCS AP, FD, YD and Associated Functions Engagement - Disengagement Associated Functions AFCS Alerts AP/FD Modes - FD Modes AP/FD or FD Mode Engagement Disengagement Autopilot Basic Modes IAS HOLD Mode VS HOLD Mode ALT SEL Mode ALT HOLD Mode GO AROUND Mode HDG SEL Mode Heading Selection LNAV Mode VOR Mode NAV LOC mode BC LOC Mode ILS Approach Mode 22-12-00 ELECTRICAL POWER SUPPLY General Direct Current Power Supply Sources Circuit breaker panels FLIGHT CONTROL/ACTUATOR INTERFACE General Actuator subfunctions Mechanical Linkage Actuator Architecture

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ATR72 -AIRCRAFT MAINTENANCE MANUAL - Description/Operation

SUBJECT Leading Particulars Interface with pitch and trim actuator

CH/SE/SU

INTERFACE WITH PERIPHERAL SYSTEMS General Peripheral Systems Type of Information Exchanged Signal Characteristics Discretes Analog Signals AFCS - Peripherals Interface Direct acquisition by AFCA Acquisition through RMA or FDA Acquisition through DCA

22-14-00

DISPLAYS, WARNINGS, LIGHTING General Flight Mode Annunciator Description Functional Description Miscellaneous Indicating Devices Lighting Flight Guidance Control Panel (FGCP) FMA Lamp Test

22-15-00

ENGAGEMENT - DISENGAGEMENT General Flight Guidance Control Panel (FGCP) General Description Hardware Description Various Controls YD engagement Logics YD software engagement Logics YD hardware engagement Logics AP Engagement Logics AP software engagement Logics AP hardware engagement Logics

22-16-00

AFCS COMPUTER Hardware Organization Principle of architecture to fulfill safety requirements Analog part Digital part Software Organization AutoPilot continuous monitoring AutoPilot Power on safety tests

22-18-00

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AUTO FLIGHT - GENERAL

GLOSSARY OF ABBREVIATIONS ABBREVIATION I ADC AFCA AFCS AFDX AHRS AP APAU-P APAU-R APM BC CAC CAP CDS CMA COM CPL CPM DCA DH EFIS EWD FD FDA FDAU FGCP FMA FMS FWA F/0 GA G/S (M)HDG HSI IAS ICP IOM-AP IOM-DC LOC MFC MLS MON ND PCI

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SIGNIFICATION Air Data Computer

s Auto Flight Control System Automatic Flight Control System Avionics Full Duplex network Attitude and Heading Reference System Autopilot AutoPilot Actuator Unit Pitch AutoPilot Actuator Unit Roll Aircracft Performance Monitoring Back Course Core Avionic Cabinet Captain Cockpit Display System Centralized Maintenance Application Command Coupling Core Processing Module Data Concentration Application Decision Height Electronic Flight Instrument System Engine and Warning Display Flight Director Flight Display Application Flight Data Acquisition Unit Flight Guidance and Control Panel Flight Mode Annunciator Flight Management System Flight Warning Application First Officer Go Around Glide Slope (Magnetic) Heading Horizontal Situation Indicator Indicated Airspeed Index Control Panel Input Output Module-Auto Pilot Input Output Module-Data Concentration Localizer Multifunction Computer Microwave Landing System Monitor Navigation Display Peripheral Component Interconnect

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ATR72 -AIRCRAFT MAINTENANCE MANUAL - Description/Operation

GLOSSARY OF ABBREVIATIONS

I ABBREVIATION I PFD PTB PTW PWM QRC RA RMA TAWS TCS TTL VCP VmHB VOR

vs YD YDAU

SIGNIFICATION Primary Flight Display Power Trim Box Pitch Thumbwheel Pulse Width Modulation Quick Release Control Radio Altitude Radio Management Application Terrain Awareness and Warning System Touch Control Steering Tuned To LOC Virtual Control Panel Velocity minimum High Bank VHF Omnidirectional Range Vertical Speed Yaw Damper Yaw Damper Actuator Unit

1. Introduction A. Functions The automatic flight control system (AFCS) fulfills the three following functions : - Flight director (FD) : When the FD is active the crew is provided with tendency data by means of the FD crossed bars on the PFDs. The crew guides the aircraft along a flight path by centering the bars and keeping them centered. The FD bar position on the PFDs varies according to the difference between the parameter advisory value which is to be acquired or held and its present value. - Autopilot (AP) : Effective guidance is ensured by the AP. It is possible to keep FD data in upper modes (AP/FD function) but not in basic mode (AP function alone). The AP commands are applied to the control surfaces by three actuators : the pitch, roll and yaw actuators. Moreover elevator compensation command sent to the normal pitch trim actuator (autotrim function). The controls (control column, rudder pedals) are driven by the actuators. - Yaw damper/turn coordination or YD : In addition to yaw damper in manual flight, this function ensures turn coordination. Commands are sent to the AP yaw actuator. As the rudder pedals are driven by the actuator, the crew does not have to operate them.

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ATR72 -AIRCRAFT MAINTENANCE MANUAL - Description/Operation

Moreover, a rudder compensation command is sent to the normal rudder trim actuator (autotrim function). B. Available Modes AP basic modes : These modes are available if the AP is engaged (with or without FD). AP/FD or FD modes : The outer Loop modes are available in FD alone and in AP/FD as well. Some modes can be armed but this phase results only in checking the Logic conditions which make the mode automatically active. When the mode is active : - in FD alone : the corresponding bar is controlled so that the pilot can slave the aircraft to the outer Loop. - in AP/FD : the commands are sent to the corresponding actuators with the same purpose. The corresponding bar is visible and shows AP activity. (Ref. Fig. 001 ) C. AFCS Organization The auto flight control system (AFCS) installed on the aircraft is divided into eight sections : AUTO FLIGHT - GENERAL - (Ref. 22-00-00) - (Ref. 22-10-00) AUTOPILOT/FLIGHT DIRECTOR YAW DAMPER - (Ref. 22-12-00) ELECTRICAL POWER SUPPLY - (Ref. 22-13-00) FLIGHT CONTROL/ACTUATOR INTERFACE - (Ref. 22-14-00) INTERFACE WITH PERIPHERAL SYSTEMS - (Ref. 22-15-00) DISPLAYS, WARNINGS, LIGHTING - (Ref. 22-16-00) ENGAGEMENT, DISENGAGEMENT - (Ref. 22-18-00) AFCS COMPUTER

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ATR72 - AMM - Description/Operation

Modes Available in AP, FD or AP/FD Figure 001

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AUTOPILOT/FLIGHT DIRECTOR - YAW DAMPER 1. Introduction A. Functions The Automatic Flight Function fulfills the following functions - AutoPilot (with automatic pitch trim), - Flight Director, - Yaw Damper/turn coordination (YD with automatic yaw trim). (1)Autopilot (AP) The AP system controls the pitch and roll actuators as well as the elevator trim actuators to ensure balance of the elevator. AP engagement automatically engages the yaw damper (YD) which is the third AP axis and controls the yaw actuator. When an upper mode is active, the FD is coupled to the AP; the corresponding FD bar is in view and follows the AP commands. The functions performed by the AP/FD are as follows : - stabilizing the aircraft around its center of gravity while holding pitch attitude and heading (basic modes available in AP only). - flying the aircraft on a flight path (upper modes). - acquisition of new flight paths (upper modes with arming, capture and hold phases). These functions are available in AP and FD as well - automatic pitch trim function (auto trim). The AFCS computer controls, through the normal pitch trim interface, the elevator trim actuators in order to reduce permanent Loads on the pitch actuator and thus avoid jerks on the elevator in the event of a disconnection. The auto trim deflection is a function of the pitch actuator torque It Leads to a reduction in actuator control force. (2)Yaw damper/turn coordination (YD) The YD ensures yaw damping and turn coordination through the rudder control Linkage. The YD function can be engaged alone or with FD. AP engagement automatically engages the YD (which is then the third AP axis). The AFCS computer controls, through the normal yaw trim interface, the rudder trim actuators in order to reduce permanent Loads on the yaw actuator and thus avoid jerks on the rudder in the event of YD disconnection. The auto trim deflection is a function of the pitch actuator torque. It Leads to a reduction in actuator control force. (3)Flight director (FD) The FD is available as soon as an upper mode is active on one axis, independently of AP engagement. Commands are sent to the PFD crossed bars which : - in FD operation, provide the pilot with tendency data to follow a flight path; - in combined AP/FD operation, follow the AP commands. The FD can be used alone or in conjunction with the AP. B. Performances

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ATR72 -AIRCRAFT MAINTENANCE MANUAL - Description/Operation

LONGITUDINAL

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MODE

ACCURACY IN CALM AIR

ACCURACY IN TURBULENCE

Pitch Hold

±1°

±2°

IAS Hold

±2 kts or ±3 kts in turn

Vertical Speed

±100 ft/min

Altitude Hold

±10 ft or ±50 ft during configuration changes

Altitude Sel

Max overshoot 50 ft

Roll Hold

±10

±30

Heading Hold

±1.5°

±30

Heading Sel

Max overshoot ±1.5°

LATERAL

VOR

Max overshoot ±30

±0.5 dots

Ultimately, the AutoPilot authority was set to be a good trade off between the three following criteria: - performances - passengers comfort - aircraft Loads The resulting Autopilot authority is gathered in the two following tables Lateral axis :

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MODE I

MAX BANK I

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MAX ROLL RATE

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Normal

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1----------------1----------------1-----------------1-------------------------1 I

WING LVL

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1----------------1 I

HDG HOLD

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VOR*

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1----------------1

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1----------------1----------------1 I

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±13° ±4°/s

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±24°

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MODE

MAX ROLL RATE

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MAX BANK

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Normal

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---------------- ----------------1-----------------1-------------------------1 I

VOR

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---------------- ----------------1-----------------1 LOC ---------------BC

±24° or I ±10° I below 700 ft

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±5.5°

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±3°/s

---------------- ----------------1-----------------1 ROLL HOLD

---------------DHG SEL ---------------LOC*

±27°

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±4°/s

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±7°/s

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±4°/s

1-----------------1

---------------BC*

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1-----------------1

LNAV

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The automatic bank angle Limitation can Limit to a roll angle of ±15° according to IAS and height for more details (Ref. 22-10-00) Lateral axis MAX LONGITUDINAL LOAD FACTOR

--------------1-------------MODE

MAX PITCH ANGLE

Normal

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MAX RATE

---------------- ---------------- --------------1-------------- ------------I I I I I

PITCH HOLD

---------------vs ---------------IAS 0.2 g

±15°

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ALT*

GS

1---------------1

ALT

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0.1 g

0.3 g/s

1--------------1 I

0.1 g

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2. System Description The AFCS is composed of : - two applications (Auto Flight Control Application) embedded in CPM1

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(Command) and CPM2 (Monitor), two dedicated 1/0 card IOM AP 1 and IOM AP 2, three control panels (FGCP and ICP 1 & 2 upper part), two Flight Mode Annunciator (on each PFD upper part), three identical actuators on the three axis (pitch, roll, yaw). The actuators are installed in parallel on the flight control Linkage and are equipped with a clutch, - two Power Trim Boxes (to interface with existing pitch trim and yaw actuator). (Ref. Fig. 001 ) -

A. AFCS Components (1)Functional Item Number (Ref. Fig. 002 ) (2)Component Location - FGCP (3CA) is placed on glareshield 13VU, ICP 1 (4WK1) is placed on glareshield's Left side, - ICP 2 (4WK2) is placed on glareshield's right side. - CPM 1 (1TF1A) is Located on shelf 81VU in L electronics rack 80VU, - CPM 2 (1TF2A) is Located on shelf 82VU in L electronics rack 80VU, - IOM AP 1 (1TF1F) is Located on shelf 81VU in L electronics rack 80VU, - IOM AP 2 (1TF2F) is Located on shelf 82VU in L electronics rack 80VU, - Power Trim Box (201CG) is Located on shelf 81VU in L electronics rack 80VU, - Power Trim Box (203CG) is Located on shelf 85VU in L electronics rack 80VU, - AP yaw actuator (19CA) and AP pitch actuator (18CA) are in the aft avionics compartment, zones 311 and 312, - AP roll actuator (7CA) is Located in the wing center box, zone 295. The auto flight control system is also composed of the following controls and warnings : - dynamometric rod (40CA) installed between rudder pedals and forward quadrant, - two dynamometric rods (157CA and 158CA) installed on each pitch control Linkage, between captain and first officer control column and forward quadrant, - two quick release control pushbutton switches. One (11CA) Located on Captain control wheel. The other (12CA) is Located on First Officer control wheel, - two TCS pushbutton switches 13CA and 14CA for AP neutralizing I FD synchronization (TCS) function, installed respectively on Captain and First Officer control wheels, - two go around pushbutton switches 15CA and 17CA Located respectively on the Left and right power Levers. These switches are indicated on the above glasscockpit global view. (Ref. Fig. 003 ) (Ref. Fig. 004 ) B. Control - Flight Guidance and Control Panel:

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Page 4 Sep 01/17 Printed in France

ATR72 -AIRCRAFT MAINTENANCE MANUAL - Description/Operation

The FGCP is the main control panel of the Automatic Flight Control System (AFCS) on ATR. The FGCP allows the pilot to perform: • engagement of Auto Pilot and Yaw damper, • selection of flight targets, • selection of AP/FD modes, • selection of navigation sources. - Index Control Panel: The ICP's upper part allows the crew to interact with the autoflight speed targets. The speed target value can be modified through a rotary switch, and the source can be selected by a toggle switch (Auto = FMS, MAN = manual selection). (Ref. Fig. 003 ) C. Indicating AFCS information are concentrated on the Primary Flight Display. At a glance, the crew can determine the state of the AFCS. The mode of operation and the status of the AFCS is continuously displayed in the Flight Mode Annunciator (upper area of the PFD), the autopilot's objective (symbolized by bugs) are displayed directly on each corresponding part of the PFD. (Ref. Fig. 005 ) (Ref. Fig. 006 ) R **ON A/C

051-051, 053-056,

(Ref. Fig. 007 ) **ON A/C

052-052,

(Ref. Fig. 008 ) **ON A/C

ALL

(Ref. Fig. 009 ) 3. System Architecture A. AFCS Architecture The AFCS is built around the AutoFLight Control Application embedded in CPM1 & 2. The AFCS is - fail-passive (a simple failure does not result in a significant flight path modification) with duplicated sensors; - fail-safe (a simple failure results in Limited downgrading which does not affect the flight safety) in the event of a single sensor