Booklet Atr-600 Rev 01.pdf

ATR 600 - BOOKLET Maintenance Training Practical Part

Rev 01 – January 2014

© ATR. All rights reserved. Confidential and proprietary document. For Training Purpose Only.

1

CONTENT

ATA 21 AIR CONDITIONING

3

ATA 22 AUTO FLIGHT

12

ATA 23 COMMUNICATIONS

18

ATA 24 ELECTRICAL POWER

22

ATA 26 FIRE PROTECTION

33

ATA 27 FLIGHT CONTROLS

40

ATA 28 FUEL

56

ATA 29 HYDRAULIC POWER

65

ATA 30 ICE AND RAIN PROTECTION

69

ATA 31 INDICATING/RECORDING SYSTEMS

78

ATA 32 LANDING GEAR

86

ATA 33 LIGHTS

103

ATA 34 NAVIGATION

105

ATA 35 OXYGEN

112

ATA 36 PNEUMATIC

118

ATA 38 WATER/WASTE

124

ATA 42 INTEGRATED MODULAR AVIONICS (IMA)

126

ATA 45 ONBOARD MAINTENANCE SYSTEMS

129

ATA 52 DOORS

131

ATA 61 PROPELLERS

132

ATA 70 POWERPLANT

142

TECHNICAL PUBLICATION

157

Rev 01 – January 2014

© ATR. All rights reserved. Confidential and proprietary document. For Training Purpose Only.

2

ATR-600: AIR CONDITIONING

Air Conditioning Schematic

Rev 01 – January 2014

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3

ATR-600: AIR CONDITIONING

Air Conditioning Labels Pack FAULT Pack OFF

Duct Overheat Alert

Recirculation Fan FAULT Recirculation Fan 1 or 2 FAULT Recirculation Fan OFF Recirculation Fan 1 or 2 OFF but no Fan Fault

Extraction Fan FAULT

OVBD VLV failed, last known position: open OVBD VLV failed, last known position: closed OVBD VLV failed, last known position: intermediate

Cabin altitude between 6,800ft and 10,000ft Cabin altitude upper than 10,000ft

Cabin/outside differential pressure between -0,5 PSI (-0,03 bar) and 0 PSI and between 6 PSI (0,41 bar) and 6,35 PSI (0,44 bar) Cabin/outside differential pressure between -1 PSI (-0,07 bar) and -0,5 PSI (-0,03 bar) and between 6,35 PSI (0,44 bar) and 8 PSI (0,55 bar) Rev 01 – January 2014

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4

ATR-600: AIR CONDITIONING

Air Conditioning Panel for Maintenance

Left Hand Maintenance Panel

Right Hand Maintenance Panel

Multi Function Control Display Unit (MCDU) LH Maintenance Panel: Provides to the ground crew the possibility to test the excessive cabin altitude warning and the excessive cabin differential pressure warning. Multi Function Control Display Unit: On ground, by selecting MISC1, the failure detection will be displayed. RH Maintenance Panel: Provides MFC bite loaded magnetic indicator which turn amber when a pack overheat detection has been recorded by the MFC.

MFC code: MISCELANEOUS 1 Definition Air Conditioning : Left Pack Maint Overheat Indication Air Conditioning : Right Pack Maint Overheat Indication

Rev 01 – January 2014

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5

ATR-600: AIR CONDITIONING

Air Conditioning Components

Pack Valve (19HB-20HB)

Zone:

191

Service Pressure (6141HQ-6142HQ)

Zone:

191

Cooling Turbo Fan (6001HB6002HB)

Zone:

Zone:

191 Turbo Fan Shut Off Valve (66HB-67HB-88HB89HB)

191 Turbo Fan Pressure Switch (80HB-81HB)

Zone:

Two pack valves, one in each pack, pneumatically operated and electrically controlled, regulate the air flow and pressure. These valves also work as shut-off valves. Pneumatically activated poppet-type differential pressure regulator. It provides a constant source of regulated supply air to the temperature control valve. Allows the air cooling operation on ground or in flight when the aircraft speed is lower than 150 KTS, landing gear lever down.

Spring loaded normallyclosed, in-line poppet valve. It is pneumatically actuated with an electrical control solenoid (controlled by MFC) Detects a Δp of 8 PSI between the shut-off valve out let and the ambient pressure.

191

Rev 01 – January 2014

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6

ATR-600: AIR CONDITIONING

Air Conditioning Components

Dual Heat Exchanger (6135HB-6138HB)

Zone:

191

Air Cycle Machine (6131HB-6134HB)

Zone:

It consists of a compressor section and a turbine section.

191

Pack Overheat Switch (17HB-18HB)

Zone:

Air-to-air plate-fin unit composed of a primary and a secondary section.

Protects the air cycle machine in the event of a cooling-air circuit restriction or leakage and from excessive bleed air temperature.

191

Condenser (6133HB-6136HB) Plate-fin, single-pass cross flow, air to air heat exchanger. Zone: 191

Rev 01 – January 2014

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7

ATR-600: AIR CONDITIONING

Air Conditioning Components

Water Extractor (6129HB-6132) Removes the water from the moisture produced by the condenser. Zone:

191

Water Spray Nozzle (6121HB-6122HB)

Zone:

191

Turbine Inlet Temperature Control Valve (6005HB-6006HB)

Zone:

Controls turbine inlet temperature to a minimum of 24°C and reduces the possibility of turbine icing.

191

Additional De icing Pressure Switch (86HB-87HB)

Zone:

Orifice fitting that provides a means to attach the line from the water extractor to the heat exchanger.

The purpose is to detect condenser icing by monitoring the differential pressure across the condenser bleed air path.

191

Rev 01 – January 2014

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8

ATR-600: AIR CONDITIONING

Air Conditioning Components

Temperature Control Valve (17HH-18HH)

Zone:

191

Hot By Pass Valve (6231HB-6232HB)

Zone:

214 94VU

Recirculation Fan (30HB-31HB)

Zone:

In conjunction with the temperature control valve, works to control air temperature.

191

Compartment Temperature Controller (9HH)

Zone:

Adjusts the pressure coming from the service pressure regulator to actuate the valve and to slave the hot bypass valve

121

Cabin Foot Lever Temperature Switch (68HB)

Zone: 232

Rev 01 – January 2014

Regulate temperature control valve in AUTO mode in order to keep independent air temperature compartment controls. Each recirculation fan recycles air from under floor area which is mixed with fresh air coming from packs (variable speed). If the temperature drops below 18°C, the switch will activate recirculation fans at high speed to warm up the cabin.

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9

ATR-600: AIR CONDITIONING

Avionic Ventilation Components

Air extraction Fan (7HR)

Zone:

121

Access:

Extracts air from the flight compartment and electronic racks to ventilate electrical and electronic components (variable speed).

221 BF

Overboard Ventilation Valve (14HR) Used to discharge avionics ventilation air out of the aircraft. Zone:

122

Access:

122 AR

Under floor Ventilation Valve (15HR) Butterfly-type valve electrically supplied with 28 VDC from the EMER BUS. Zone:

121

Access:

231 BF

Ambient Temperature Sensor (36HR)

Zone:

211

Rev 01 – January 2014

This sensor transmits an electrical signal to the fan speed control system, according to the flight compartment ambient temperature.

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10

ATR-600: AIR CONDITIONING

Pressurization Components

Jet Pump (6203HM) Used to create vacuum in the control circuit of the pressurization system. Zone:

121

Electro Pneumatic Outflow Valve (14Hm)

Zone:

142

Pneumatic Outflow Valve (13HM)

Zone:

141

Rev 01 – January 2014

Regulates cabin air evacuation, Limits cabin normal differential pressure, provides negative pressure safety, and prevents water ingestion during aircraft ditching.

Functions are the same as the electro pneumatic outflow valve. The electro-pneumatic outflow valve stays closed while the pneumatic outflow valve regulates.

© ATR. All rights reserved. Confidential and proprietary document. For Training Purpose Only.

11

ATR-600: AUTO FLIGHT CONTROL SYSTEM

AFCS Schematic

Rev 01 – January 2014

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12

ATR-600: AUTO FLIGHT CONTROL SYSTEM

AFCS Labels

Trim control is required FD function fails FD complete failure Disengagement of the YD function Failure in the AP/YD function Failure in the AP function Disengagement of the AP Disengagement of the AP and YD The elevator is improperly trimmed The rudder is improperly trimmed Loss of the auto trim function Invalid data from one sensor is detected Invalid data miscompare are detected on ADCs, AHRSs, or ILSs FD1 Master Channel has failed The selected mode is incompatible with the navigation source or the navigation source is lost An armed or engaged mode is lost

Rev 01 – January 2014

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13

ATR-600: AUTO FLIGHT CONTROL SYSTEM

AFCS Labels

AP/YD disengagement is due to a ROLL or Pitch discrepancy from AHRU AP/YD disengagement is due to a Calibrated AirSpeed or a True AirSpeed discrepancy from Air Data Computer Heading discrepancy occurs from Attitude and Heading Reference Unit

FD mode cannot be engaged because of NAV data failure Vertical ALT mode is disengaged due to a new target altitude setting Yaw damper is disengaged Only the auto pilot is disengaged The Yaw Damper and Auto Pilot are disengaged Attempting to engage AP with a condition making this impossible Attempting to engage YD with a condition making this impossible

Rev 01 – January 2014

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14

ATR-600: AUTO FLIGHT CONTROL SYSTEM

AFCS Panels for Maintenance

Multi-purpose Control and Display Unit

Multi-purpose Control and Display Unit: The MCDU is the interface which offers to the maintenance operator several services via pages in order to perform a diagnostics.

Rev 01 – January 2014

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15

ATR-600: AUTO FLIGHT CONTROL SYSTEM

AFCS Components

AFCS Computer (1CA) The architecture of the AFCS includes 2 Core Avionic Cabinets (CAC 1 and 2). The Core Avionic Cabinets use Line Replaceable Units (LRU): 6 cards in each Cabinet. In the basic configuration, each CAC is composed of: one CPM, one I/OM-S, one IOM-AP, two IOMDC, and one SWM.

Zone:

213 82VU Access: 213 CZ

Power Trim Boxes (201GC-203GC)

Zone:

Independent boxes which provides power for the electric pitch or yaw trim, with no mechanical subassembly or component and no software. For the automatic pitch or yaw trim function, the AFCS must be interface with the trim actuators. Because the IOM AP is not able to manage power signals, an interface is needed in order to command the trim actuator. This interface is assured by Power Trim Boxes, which converts command signals into power signals.

213 81-85VU

Rev 01 – January 2014

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16

ATR-600: AUTO FLIGHT CONTROL SYSTEM

Flight Control Actuators

Actuator – AP Roll (7CA)

Zone:

295

Access:

295 BL

Actuator – AP Pitch (18CA)

Zone:

312

Access:

851

Actuator – AP Yaw (19 CA)

Zone:

311

Access:

Rev 01 – January 2014

The AFCS commands are applied to the control surfaces by three identical actuators, the pitch, yaw, and roll actuators. Pitch actuator is in the left avionics compartment, zone 312. Roll actuator is located in the wing center box, zone 295. Yaw actuator is in the aft avionics compartment, zone 311. When AP is engaged, the pitch actuator controls the elevators, the roll actuator controls both ailerons, and the yaw actuator controls the rudder.

851

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17

ATR-600: COMMUNICATIONS

Communication Schematic

Rev 01 – January 2014

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18

ATR-600: COMMUNICATIONS

Communication Labels

The frequency tuning is failed The VHF status is not available or in “Test In Progress” The frequency entered is out of range

The VHF status is failed

The squelch level is different than the selected squelch The squelch level is not available

The cabin attendant calls the cockpit in case of an emergency call from the cabin

Rev 01 – January 2014

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19

ATR-600: COMMUNICATIONS

Communication Components

SSCVR Solid State Cockpit Voice Recorder (1RK)

Zone:

311

ELT Emergency Locator Transmitter (1MX)

Zone:

256 Access: 255BC

PA Passenger Address Amplifier (3RY)

Zone: 213 81VU Access: 213 CZ

Rev 01 – January 2014

The SSCVR is located in the aft unpressurized area and is supplied by 28VDC and has a recording capacity of 120 minutes. The cockpit voice recorder is equipped with an underwater acoustic beacon located on the face and permits the localization of the recorder in the event of an accident over the sea. The ELT system comprises a transmitter in the pressurized ceiling, close to the toilet door, an antenna in the fairing ahead of the stabilizer fin, and a Remote Control Unit in the flight compartment. The ELT is able to transmit a distress signal on 121.500 Mhz and 243.000 Mhz frequencies and a geographical position on 406.000 Mhz frequency. The PA amplifier enables broadcasting to announcements to passengers. It also enables broadcasting of recorded announcements. Cockpit announcements are given priority over cabin attendant announcements and music tape reproducer via the Cockpit Priority System.

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20

ATR-600: COMMUNICATIONS

Communication Components

RCAU Remote Control Audio Unit (1RN)

Zone: 213 81VU Access: 213 CZ

Hand Microphone and Jacks (8RN1-8RN28RN3)

Zone:

211-212-213

INT/RAD Push-To-Talk Switch on Control Wheels 14RN1-14RN2

Zone:

211

Rev 01 – January 2014

The RCAU is the main component of the audio integrating system. It allows the use of any communication or navigation system with any earphone and microphone combination. The RCAU is power supplied by the 28VDC ESS Bus in flight and by the 28VDC STBY Bus on ground. Two hand microphones are provided on each side of the cockpit, one for each pilot. After one of the six transmission keys on the ACP has been selected, the microphone can be used for any communication through actuation of the PTT switch. The outboard horn of both control wheels is provided with a three-position PTT selector controlling the transmission mode. The three-position PTT selector effective only when boomset or oxygen mask mike is used for transmission. © ATR. All rights reserved. Confidential and proprietary document. For Training Purpose Only.

21

ATR-600: ELECTRICAL POWER

AC-DC Schematic

Battery Configuration

Rev 01 – January 2014

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22

ATR-600: ELECTRICAL POWER

AC-DC Schematic

Ground Power Configuration

Rev 01 – January 2014

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23

ATR-600: ELECTRICAL POWER

Labels AC-DC power Abnormal configuration

Main DC BUS is not supplied

UTLY BUS is disconnected or not supplied DC SVCE / UTLY BUS pushbutton is released

If a considerable overload condition is detected and the corresponding UTLY BUS is disconnected

Load shed condition is present and the DC SVCE BUS is disconnected DC SVCE BUS / UTLY BUS pushbutton is released on Overhead Panel

TRU pushbutton is released and ACW is invalid TRU is not supplied TRU pushbutton is pressed in and TRU is supplied TRU pushbutton is pressed in and TRU is failed TRU pushbutton is released but TRU remains supplied TRU pushbutton is pressed in but ACW is invalid

DC Emergency bus voltage is low

Rev 01 – January 2014

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24

ATR-600: ELECTRICAL POWER

Labels AC-DC power DC Standby bus voltage is low DC Standby bus, selected to OVRD, is supplied by the DC Hot Emer Bus

An under voltage appears on the DC STBY Bus

DC Essential bus voltage is low

DC Hot Main bus voltage is low DC Battery toggle switch is set to OVRD position

DC Hot bus voltage is low DC Hot bus voltage is invalid

BAT charge failure is detected

The corresponding battery is discharging

The Battery toggle switch is set to OVRD position

Main AC BUS is not supplied

AC STBY BUS is not supplied

The inverter is in abnormal configuration Rev 01 – January 2014

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25

ATR-600: ELECTRICAL POWER

ACW Schematic

Rev 01 – January 2014

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26

ATR-600: ELECTRICAL POWER

ACW power Labels

ACW Generation is in abnormal configuration

ACW BUS is not supplied

TRU pushbutton is released and the ACW is invalid TRU is not supplied TRU pushbutton is pressed in and the TRU is supplied TRU pushbutton is pressed in but the TRU is failed TRU pushbutton is released but the TRU remains supplied TRU pushbutton is pressed in but the ACW BUS 2 is invalid

Rev 01 – January 2014

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27

ATR-600: ELECTRICAL POWER

AC-DC and ACW Panels for Maintenance

LH Maintenance Panel

Multi Function Control and Display Unit

RH Maintenance Panel

LH Maintenance Panel: Various AC / DC parameters can be checked as selected. For maintenance purposes, a guarded toggle switch is used to check the ACW BTC’s operation. Multi Function Control Display Unit: On ground, it permits to access to MFC memory. Electrical system failure codes can be read in Miscellaneous 1 or 2 page of the MCDU. RH Maintenance Panel: A bite loaded magnetic indicator turns amber when a system failure has been recorded and dedicated to the maintenance teams. MFC code: MISCELANEOUS 1 Definition Electricity: Left Open Wire Maint Indication Electricity: Right Open Wire Maint Indication

Electricity: Service Utility Contactor Fault Maint Indication MFC code: MISCELANEOUS 2 Definition Electricity: Standby Contactor Default

Rev 01 – January 2014

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28

ATR-600: ELECTRICAL POWER

AC-DC and ACW components

DC Starter / Generators (1PU)

Zone:

431-441

ACW Generators (1XU)

Zone:

Provide the DC power source by the High Pressure compressors through the Auxiliary Gear Boxes.

Provide the ACW power source by the Power Turbines through the Propeller Reduction Gear Box.

431-441

Generator Control Unit (5PU-9PG-9XU-9XG) Associated with each starter generator provides control for generator and starter operation.

Zone:

214 95VU

Rev 01 – January 2014

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29

ATR-600: ELECTRICAL POWER

Bus Power Control Unit (9PG-9XG)

Zone:

Associated with each starter generator provides control for generator and starter operation.

214 95VU

Static inverters (1XA-2XA)

Converts DC into AC.

Zone:

214 93VU-94VU

Transformer Rectifier Unit (92PA)

Zone:

TRU transforms ACW power (115/200V AC, 3 phase, 341/488 HZ) into 28 VDC(60 Amp max). Need a manual selection by pilot. When TRU is activated, an amber arrow is illuminated on the push button

214 90VU

Rev 01 – January 2014

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30

ATR-600: ELECTRICAL POWER

Main Battery (21PA) And Emergency Battery (72PA)

Zone:

213

Main Battery

Main Battery: Used to start the Engine and to supply emergency power.

Emergency Battery

Emergency Battery: Avoids power transient on critical equipment during Engine start and supplies emergency power after Main Battery has been discharged.

Multi Function Computer (1UA1-1UA2)

Provide controls for batteries proper operation and transfer contactors controls.

Zone:

214 91VU-92VU

Rev 01 – January 2014

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31

ATR-600: ELECTRICAL POWER

DC (1PG) and AC (1XG) external receptacle Allow the aircraft to be supplied from Ground Power Unit.

Zone:

114

114 CR Access: 114 BR

Contactors Used to connect the generators, the alternators the external power and the batteries to the electrical network.

Zone:

214

The “CNCTD” white light corresponds, when illuminated, to the cockpit “AVAIL” light. The “PWR NOT USED” white light corresponds, when illuminated, to the “SHED” light on the flight attendant panel.

Rev 01 – January 2014

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32

ATR-600: FIRE PROTECTION

Fire Protection Schematic

Rev 01 – January 2014

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33

ATR-600: FIRE PROTECTION

Labels Fire Protection Alternate fan in service fails

Air Extraction Fan stops EXHAUST MODE pushbutton of the AVIONICS VENT Panel has been selected to "OVBD" mode

Smoke is detected in the "ELEC" Compartment area Smoke is detected in the FWD Compartment area Smoke is detected in the AFT Compartment area Smoke is detected in the Lavatory Compartment area

Hot temperature detected on right Engine Nacelle Fire alert on the corresponding Engine Fire detection loop failure on the corresponding engine Smoke is detected in the AFT Compartment and in the Lavatory Compartment areas

Rev 01 – January 2014

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34

ATR-600: FIRE PROTECTION

Fire Protection Panels for Maintenance

Compartment Smoke Panel

Left Hand Maintenance Panel Avionics Vent Panel LH Maintenance Panel: The compartment smoke protection system test is located on the left maintenance panel. Compartment Smoke Panel: Compartment smoke protection system indications are located on the compartment smoke panel. The smoke test is also located on this panel. Avionics Vent Panel: When the “SMK TEST” pushbutton is pressed, “FAULT” amber light (EXHAUST MODE) illuminates on Avionics Vent Panel. To restart the extract fan, it is necessary to reset the “EXHAUST MODE” pushbutton.

MFC code: MISCELANEOUS 1 Definition FWD N°1 Extinguisher Bottle Test Failed AFT Extinguisher Bottle Test Failed FWD N°2 Extinguisher Bottle Test Failed

Rev 01 – January 2014

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35

ATR-600: FIRE PROTECTION

Engine Fire Detection / Extinguishing Components

Engine Fire Loops

Zone:

400

FDCU Fire Detection Control Unit (13WD-14WD)

Zone:

214

Fire Extinguishing Bottles (9WE-10WE)

Zone:

295-296

Rev 01 – January 2014

295 GL Access: 296 GR

The fire Sensing Element is a flexible coaxial cable. The electrical characteristics of the fire Sensing Element vary with temperature. The fire detection control unit processes the warning signals from the sensing element according to an AND logic and triggers the corresponding indications in the Flight Compartment (FIRE circuit). Two fixed fire extinguisher bottles are installed in the wing-to-fuselage junction fillet. The bottles are of the quick-discharge type. A pressure gauge displays the pressure inside the bottle.

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36

ATR-600: FIRE PROTECTION

Smoke Detection Components

Photoelectric Cell Type Smoke Detector (150WA-151WA-184WA)

Zone:

223-264

Alternate Extract Fans (155WA-157WA170WA172WA)

Zone:

Three photoelectric cell type smoke detectors are installed on the aircraft : - One in Aft Cargo Compartment, - One in Toilets, - One in the Forward Cargo Compartment.

The alternate extraction fans are installed in series on Air Extraction System of the Lavatory and the Aft Cargo. They run alternatively and ensure a permanent airflow through the smoke detectors.

223-264

Smoke Detection Fan Control Unit (174WA-176WA

Zone:

214

Rev 01 – January 2014

The fan control unit supplied by circuit breakers 154WA and 166WA controls alternate operation of the Air Extraction Fans 170WA and 172WA.

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37

ATR-600: FIRE PROTECTION

Portable Fire Extinguisher Components

Halon Portable Extinguisher (6208WM)

255

Zone:

Water Portable Extinguisher

Zone:

The portable fire extinguisher is installed in the area of Forward Compartment. The water type extinguisher is fitted without manometer.

230

Toilet Dust Bin Extinguisher Bottle (6204WX)

Zone:

The portable fire extinguishers are installed in the Cockpit, behind the first officer seat and in the Cabin, between the galleys partition and the last line of cabin seats. The extinguishers are Halon type with a manometer indicating the pressure of the nitrogen cartridge.

In case of fire in the lavatory dustbin, a Halon fire extinguisher is installed above the bin. The fire extinguisher is activated automatically when a heat source in the region of 77°C (170°F) is detected.

261

Rev 01 – January 2014

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38

ATR-600: FIRE PROTECTION

Nacelle Overheat Detection Components

Nacelle Overheat Sensor (2WH)

Zone:

480

Nacelle overheat is detected by a sensor located in the right engine nacelle only. Overheat signal is sent to the Detection Control Unit. When the right nacelle temperature reaches 170°C +/- 5°C, CCAS is activated and triggers WARNING and continuous repetitive chime.

Nacelle Overheat Control Unit (4WH)

The nacelle overheat control unit is supplied with 28VDC from BUS 2 and receives overheat signal from the overheat sensors.

Zone:

214 94VU

Rev 01 – January 2014

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39

ATR-600: FLIGHT CONTROL

Flight Control Schematic

Rev 01 – January 2014

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40

ATR-600: FLIGHT CONTROL

Labels Flight Control

Pitch Trim Asym Pitch Mistrim or Pitch Trim failed with AP engaged

Electrical signal CAC or DU failure

Roll Mistrim with AP engaged

Rudder Mistrim with AP engaged

Flaps Asymmetry is detected Flaps Jam is detected Flaps Command failure is detected Flaps unlocked is detected

Rev 01 – January 2014

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41

ATR-600: FLIGHT CONTROL

Flight Control Panels for Maintenance

Multi Function Control and Display Unit

LH Maintenance Panel

RH Maintenance Panel

MCDU: MFC fault codes can be displayed on MCDU when a Flight Controls failure has been recorded. LH Maintenance Panel: On this panel, “WARN” rotary selector enables selection of the STICK PUSHER/SHAKER system to be tested. When activated CCAS is triggered. RH Maintenance Panel: Several tests and control devices are provided. “PITCH TRIM COMP” push to test button enables to test the pitch trim asymmetry monitoring. “ELEV CLUTCH REARM” pushbutton enables to reconnect both elevators after a disconnection. “BITE LOADED” magnetic indicator turns amber when a Flight Controls failure has been recorded.

Rev 01 – January 2014

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42

Flight Control

MFC code: MISCELANEOUS 1 Definition PLA 1 /ENG 1 Torque (indicator) discrepancy PLA 1 /ENG 2 Torque (indicator) discrepancy IAS 1 > VFE with Radio Alti < 500 ft during 2 mn IAS 2 > VFE with Radio Alti < 500 ft during 2 mn Failure of signal Radio Alti < 500 ft

Trim Direction Fault Flaps Position Switch Fault Stick Pusher : Left Alpha Probe Disagree Stick Pusher : Left Right Probe Disagree

Rev 01 – January 2014

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43

ATR-600: FLIGHT CONTROL

Flight Control General Components

Trim Actuator (1CG21CG-22CG-28CG)

327 333 Zone: 544-644

TLU Control (10CY)

Zone:

311

Rev 01 – January 2014

The aircraft is provided with four trim actuators which are all interchangeable. Aileron trim is performed by varying the neutral position setting of the left aileron spring tab with respect to the aileron. The rudder trim actuator modifies the neutral position of the spring tab. Pitch trim is performed by varying the neutral position setting of the tabs with respect to the elevator via two trim actuators, linked by a flexible shaft. The Travel Limit Unit comprises one electrical actuator, identical type to those used for the aileron control trim, rudder control trim and elevator control trim. The electrical actuator includes two separate coils which enable two speeds of travel, high speed coil corresponds to normal control, and low speed coil corresponds to standby control.

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44

ATR-600: FLIGHT CONTROL

Aileron & Tab Components

Control Wheel (15VU-16VU)

Zone:

Captain and first officer control wheels are identical. They are linked together thanks to the torque tube located under floor. Control wheel travel is limited by two bump stop crews installed in the column. They are adjusted to 107° either side of the neutral position.

211

AP Actuator (7CA)

Zone:

295

Access:

Rev 01 – January 2014

295BL

The AP roll actuator is connected to the quadrant upper part by means of a cable. The actuator is divided in two different parts, the capstan and the servomotor. They are independent, which allows the change of the servomotor without removing the capstan integrated in the flight controls.

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45

ATR-600: FLIGHT CONTROL

Aileron & Tab Components

Tension Regulator Quadrant (5002CB)

Zone:

114

Its function is to transmit the movement to the aft quadrant. It also maintains the cable tension between 20 and 25 daN for all temperatures encountered during flight or on the ground.

Aft Quadrant The aft quadrant receives movement of the cables from the control wheels. It is connected to the RH crank (unpressurized area). Zone:

312

Aileron Control

Rev 01 – January 2014

The final push-pull rods actuate each aileron fixed bellcrank through the input lever. Each aileron deflection is limited by one upper and one lower adjustable aileron stop.

© ATR. All rights reserved. Confidential and proprietary document. For Training Purpose Only.

46

ATR-600: FLIGHT CONTROL

Aileron Trim Components

Aileron Tab

Zone:

Two spring tab are provided on the aircraft, one on each aileron. The spring tab operates mechanically. Its deflection rate with respect to the aileron varies in proportion to aerodynamic resistance to aileron deflection.

540-640

Aileron Position Transmitter (172TU-173TU)

Zone:

533-633

Fr:

Rev 01 – January 2014

12-13

There are two aileron position transmitters, one on each aileron. The position of each aileron is measured by a position transmitter. Each position transmitter is of the synchro type. Adjustment is done by alignment of marks on the body of the transmitter and its shaft.

© ATR. All rights reserved. Confidential and proprietary document. For Training Purpose Only.

47

ATR-600: FLIGHT CONTROL

Spoilers Components

SBV Spoiler Block Valve (5003CS-5004CS)

Zone:

542-642

Fr:

20-21

Spoiler

Zone:

543-643

Fr:

20-23

Pipes, hydraulic Actuator (5001CS5002CS) and Proximity Switch (5CT-6CT)

Zone:

542-642

Fr:

20-23

Rev 01 – January 2014

Each SBV is installed close to its associated spoiler actuator, underneath the spoiler surface. It is linked to the push-pull rods of the roll mechanical control. The Spoiler Block Valves are identical, they comprise an input lever following the aileron position and a position feedback shaft linked to the spoiler. Each roll spoiler deploys proportionally to aileron deflection. They are hydraulically powered by the blue hydraulic system and the command orders are mechanical. Spoiler deflection is initiated at 2.5° aileron deflection and is limited by an internal stop at 57°. For pressure and return, hydraulic pipes are provided from the Spoiler Block Valve SBV the spoiler actuator. A proximity switch is also provided to indicate spoiler extension. The hydraulic pipes are mounted in such a way to follow wing deformation or dilatation. The spoiler actuators are a differential cross section type. Spoiler proximity switches supply spoiler extension indicator lights on the overhead panel and send a signal “spoiler extended” to the AP. © ATR. All rights reserved. Confidential and proprietary document. For Training Purpose Only.

48

ATR-600: FLIGHT CONTROL

Rudder & Tab Components

Force Detection Rod

Zone:

113

211FF Access: 211HF

Forward and Rear Quadrants

Zone:

311

Spring Tab Mechanism

Zone:

The force detector (157CA158CA) rod is located underneath the flight compartment floor. The left pedal set is connected to a force detector rod, which is link to the forward quadrant The forward quadrant is located under the flight compartment, the cable loop runs beneath the flight compartment floor and above the cabin compartment ceiling. The rudder forward quadrant transmits the linear movement from the pedals assemblies to the ruder cable loop. The aft quadrant is located in the aircraft rear section. The rudder rear quadrant receives the linear movement from the cable loop and transmits it to the rudder control rod. It is connected to the rudder bell crank by a pushpull rod. The spring tab provides flexible compensation which automatically increases with aerodynamic loads applied on the rudder, thus ensuring pilots effort reduction.

327

Rev 01 – January 2014

© ATR. All rights reserved. Confidential and proprietary document. For Training Purpose Only.

49

ATR-600: FLIGHT CONTROL

Releasable Centering Unit (25CG)

Zone:

312

Trailing Edge and Rudder

Zone:

324

Pedals

Zone:

The rudder is hinged on the fin rear spar by means of three hinges. It is statically and dynamically balanced, using weights, placed on the forward side of the tip. The top of the rudder is anti-iced.

328

Rudder Damper (5005CB)

Zone:

The RCU stabilizes the rudder position when no action is applied on the pedals. This device is automatically centered on the linkage position every time a trim control command is applied, and is inhibited when the yaw damper is active.

210

Rev 01 – January 2014

The rudder damper is a double-effect damper. Damping is obtained by the transfer of oil via a flow regulator. In flight, the rudder damper regulates rudder travel speed. On ground, it limits excessive movement generated by gust and avoids damage to the structural stops. Both pedals operate the rudder mechanically. The Captain and First Officer each have one identical pedal set. The neutral position of each pedal assembly is adjustable from a handle installed under the front panel.

© ATR. All rights reserved. Confidential and proprietary document. For Training Purpose Only.

50

ATR-600: FLIGHT CONTROL

Rudder Trim Components

Trim Tab A spring tab is provided on the rudder. Rudder trim tab deflection is limited by two stops in the trim actuator. Trim tab deflection to either side of the rudder is approximately 16°.

Zone:

328

DFDR Rudder Position Transmitter (13TU)

Zone:

333

Rev 01 – January 2014

The rudder position transmitter is linked by a rod and a lever to the rudder surface. The position of the rudder is transmitted to the Flight Data Acquisition Unit, part of the MPC, then to the Digital Flight Data Recorder through a synchro signal from the position transmitter.

© ATR. All rights reserved. Confidential and proprietary document. For Training Purpose Only.

51

ATR-600: FLIGHT CONTROL

Elevator & Tab and Trim Elevator Components

Cable Tension Regulator Rear Quadrants and Linkage (5003CB-5004CB)

Zone:

113

The cable tension regulator function is to transmit the movement to the rear quadrant. It also maintains the cable tension between 20 and 25 daN for all temperatures encountered during flight or on the ground. The rear quadrants receive the linear movement from the cable loops and transmit it to the pitch control rods.

Elevator

The elevator are hinged on three points fixed to the rear stabilizer spar. The elevator deflection is limited by one upper and one lower stop. Five static dischargers ensure static discharging by corona effect.

Pitch Uncoupling Mechanism

Pitch uncoupling occurs when one elevator is jammed. It is detected by a micro switch. In this case, only the operable elevator provides aircraft pitch control. Reconditioning is performed on the ground using a manual tool or by means of an electrical actuator actuated by a pushbutton installed on the RH maintenance panel.

330

Zone:

Zone:

326

Rev 01 – January 2014

© ATR. All rights reserved. Confidential and proprietary document. For Training Purpose Only.

52

ATR-600: FLIGHT CONTROL

Elevator & Tab and Elevator

Trim Components Rear Elevator Clutch Actuator (8CB)

Zone:

326

Auto Pilot Actuator (18CA)

Zone:

312

Flexible Shaft and Push Pull Rod

Zone:

An electrical actuator is installed close to the pitch uncoupling mechanism. Activation of the elevator clutch pushbutton energizes the electrical actuator which pushes the roller inside the V profile cam by means of a fork. The autopilot is linked to the right rear quadrant in the tail cone, by means of a cable loop. The actuator includes a clutch which allows free movement when the autopilot is not engaged. The flexible shaft is located between the two actuators reduction gears. It synchronizes the two actuators in both operating directions and allows one actuator to be driven by the other in case of failure.

326

Rev 01 – January 2014

© ATR. All rights reserved. Confidential and proprietary document. For Training Purpose Only.

53

ATR-600: FLIGHT CONTROL

Stall Warning Components

Alpha Probe (19FU-20FU)

Zone:

Each probe sends an electrical voltage via four potentiometers to the MFCs which is proportional to aircraft angle-of-attack. The Angle Of Attack sensor includes a vane which is heated (anti-icing function).

211

Stick Shakers (7FU-10FU)

Zone:

113

Access:

211FF 212FF

Stick Pusher (1FU)

Zone:

311

Access:

Rev 01 – January 2014

851

Stick shakers are designed to give warning of approaching stall by vibrating their associated control column. The device is a part of the primary stall warning. The principle of operation is based on a reduction of rotary movement of an electrical motor shaft, used to drive an unbalanced rotor. This creates a vibration of a given frequency. The stick pusher is the secondary stall warning. This device permits aircraft recovery through an immediate and strong nose down order. The stick pusher actuator is normally in the extended position. When a stall configuration is detected, the actuator retracts which causes the aircraft nose to go down.

© ATR. All rights reserved. Confidential and proprietary document. For Training Purpose Only.

54

ATR-600: FLIGHT CONTROL

Flaps Components

Flaps Position Transmitters (15CV-16CV)

Zone:

295

Access:

296AR 295AL

Left and right inboard flap position information is supplied by two synchrotype position transmitters (one for each inboard flap). Each transmitter is connected to the mobile fitting of the flap inner hinge via a rod.

Flaps Actuator Inboard (5002CV-5003CV)

Zone:

551-651

Flaps Actuator Outboard (5001CV-5004CV)

Zone:

The actuators are sliding type. They are connected to the wing structure and the flap by means of selflubricated spherical bearings. The spherical bearings must be lubricated at regular intervals.

553-653

Rev 01 – January 2014

© ATR. All rights reserved. Confidential and proprietary document. For Training Purpose Only.

55

ATR-600: FLIGHT CONTROL

Flaps Components

Flaps Block Valve (1CV)

Zone:

541

Rib :

5-6

Interconnection Torque Shaft (5006CV)

Zone:

295

295 BL Access: 296 CR

Rev 01 – January 2014

The hydraulic control unit is designed to supply the four hydraulic actuators, through rigid pipes. The flap block valve includes two solenoid valves operating a selector valve, one for extension, the other for retraction. The flap block valve is supplied through the inlet pressure port by 3000 PSI blue hydraulic system. The interconnection torque shaft connects the inboard flaps together. It is used to give the same angular displacement to the aircraft RH and LH flaps. The rigidity of the shaft is sufficient to maintain the flap positions within acceptable limits.

© ATR. All rights reserved. Confidential and proprietary document. For Training Purpose Only.

56

ATR-600: FUEL

Fuel Schematic

Rev 01 – January 2014

© ATR. All rights reserved. Confidential and proprietary document. For Training Purpose Only.

57

ATR-600: FUEL

Labels Fuel The value of fuel level is less than 160 kg (353 lbs) The fuel quantity is less than 50 kg (110lbs)

Fuel gauged in one tank is less than 160 kg (353 lbs) Amber feeder tank indication when the fuel feeder tank is in low level condition

Fuel electrical pump pushbutton is in "OFF" position and electrical pump is running Pump signal is invalid

When fire handle is pulled:

First, green flow bar disappears and this state is displayed Then, this state is displayed After three seconds a commanded valve position (open or closed) there is a disagreement between valve position and fire handle

Feed Low Pressure is detected by the fuel feed low pressure switch when fuel delivery is below 4 PSI in case of fuel pump failure or fuel shortage

After a three seconds commanded valve position (open or closed) there is a disagreement between valve position and X-FEED pushbutton

Rev 01 – January 2014

© ATR. All rights reserved. Confidential and proprietary document. For Training Purpose Only.

58

ATR-600: FUEL

Fuel Panel for Maintenance

Right Hand Maintenance Panel

Right Hand Maintenance Panel: A bite loaded magnetic indicator on the RH maintenance panels turns amber when a system failure has been recorded.

MFC code: MISCELANEOUS 2 DEFINITION

Engine 1 Feeder Jet Pump Fault Engine 2 Feeder Jet Pump Fault

Rev 01 – January 2014

© ATR. All rights reserved. Confidential and proprietary document. For Training Purpose Only.

59

ATR-600: FUEL

Fuel Distribution Components

Electrical Pump (15QA-16QA)

Zone:

522

The 28 VDC electric pump supplies fuel to the engine during starting. It also serves to supply the engine throughout the flight envelope, in the event of feed jet pump failure or a restart in emergency.

Rib:

4-6

Feeder Jet Pump (5005QA-5006QA) Operated by fuel from the engine feed system, the jet pump maintains the feeder tank with fuel by drawing the fuel from beyond rib 5. Zone:

522

Rib:

4-6

Engine Feed Jet Pump (5003QA-5004QA)

Zone:

522

Rib:

Rev 01 – January 2014

The engine feed jet pump delivers fuel to the engine after starting. Driving fuel flow is supplied through a return line from the Hydro-Mechanical Unit.

4-6

© ATR. All rights reserved. Confidential and proprietary document. For Training Purpose Only.

60

ATR-600: FUEL

Fuel Distribution Components

Motive Flow Valve (9QA-10QA) It is open when the valve solenoid is not energized and with fuel pressure. It closes if there is not fuel pressure or with the solenoid energized. Zone:

512

Rib:

12-13

LP Shut Off Valve (5001QG-5002QG) Valve operation is controlled by the corresponding engine fire handle.

521 Zone: 475

Rib:

11-12

LP Pressure Switch (13QA-14QA) The fuel LP switch detects a drop of pressure (4 PSI) in the corresponding engine feed system.

Zone:

486 475

Rib:

Rev 01 – January 2014

11-12

© ATR. All rights reserved. Confidential and proprietary document. For Training Purpose Only.

61

ATR-600: FUEL

Fuel Distribution Components

Cross Feed Valve (5001QE) The left and right systems are interconnected by a cross feed line including a single motor electric valve. Zone:

521

Rib:

0-4

Electric Pump Auto Control Pressure Switch (17QA-18QA)

Zone:

511

Rev 01 – January 2014

Rib: 4-5

The pressure switch deenergizes the electric pump after engine starting, when the pressure supplied by the engine feed jet pump reaches 8.5 PSI + 30s delay. In the event of engine feed jet pump failure P < 350mb (5 PSI), pressure switch provides electric pump opening which ensures fuel supply to the engine.

© ATR. All rights reserved. Confidential and proprietary document. For Training Purpose Only.

62

ATR-600: FUEL

Fuel Indicating Components

Fuel Control Unit (204QT)

Zone:

211

Indicator Probes (151QT-152QT)

Zone:

522

Dipsticks (7QT ->14QT)

Zone:

522-523

The FCU is a dual channels unit (CPU1 and CPU2) which processes fuel quantity information for both tanks. The two channels are completely isolated and have their dedicated power supply. Fuel mass is measured by six capacitance probes installed in each tank. They are attached to the tank upper surface wall and can be removed from outside without emptying the tank.

By pressing and turning the control knob, the rob magnetically linked to the float, falls under its own weight. The fuel level is read in cm on the section of the scale which protrudes from the wing lower surface.

Clinometer (5005QW) The clinometer gives the A/C roll attitude in order to perform the corrections for limiting A/C attitude effects for dipstick reading. Zone:

195

Rev 01 – January 2014

© ATR. All rights reserved. Confidential and proprietary document. For Training Purpose Only.

63

ATR-600: FUEL

Refuel/Defuel Components

Refuel and Defuel Valve (14QU) ATR 72

ATR 42 Zone:

621

Access:

Each 28 VDC refuel/defuel valve is equipped with a metal ring located under the electrical connection. The element called manual override enables the valve to be operated manually, in the event of an electrical control failure.

295BL

High Level Sensor (11QU-12QU) When the fuel reaches the maximum fuel quantity value and the refueling does not stop, the high level sensors, as a safety device, send an electrical signal to the RCP Zone:

523

Rib:

23-24

Gravity Refuel Cap (5001QU-5002QU) Each cap includes a support attached to the structure and a filter. The cap is equipped with a locking mechanism flush with the wing upper surface Zone:

523

Rev 01 – January 2014

Rib:

23

© ATR. All rights reserved. Confidential and proprietary document. For Training Purpose Only.

64

ATR-600: HYDRAULIC POWER

Hydraulic Schematic

Rev 01 – January 2014

© ATR. All rights reserved. Confidential and proprietary document. For Training Purpose Only.

65

ATR-600: HYDRAULIC POWER

Labels Hydraulic Power

Hydraulic system is in low pressure condition Hydraulic system is in low level condition Hydraulic pump is in overheat condition

Auxiliary pump is not supplied Auxiliary pump is started by the pushbutton on the pedestal Pumps are « OFF »

the main battery power supply is available.

the DC BUS 2 power supply is available.

X FEED valve operation is inhibited

the Hydraulic system is in low pressure condition the signals are invalid the Hydraulic systems are unpressurized

Rev 01 – January 2014

© ATR. All rights reserved. Confidential and proprietary document. For Training Purpose Only.

66

ATR-600: HYDRAULIC POWER

Hydraulic components

Reservoir (6007GX) It is an unpressurized type, divided in two equal compartments containing hydraulic fluid. Zone:

195

ACW electric pumps (9GX-10GX) Pressurize the system at 3000 PSI

Zone:

195

DC electric pump (12GF)

Zone:

Provides hydraulic power to operate the users of the blue hydraulic system if the main ACW pump fails.

195

Return module Is bolted to the rear side of the reservoir and receives fluid from the users of the green system Zone:

195

Rev 01 – January 2014

© ATR. All rights reserved. Confidential and proprietary document. For Training Purpose Only.

67

ATR-600: HYDRAULIC POWER

Hydraulic components

Nitrogen-charged accumulators (6001GX-6003GX)

Zone:

195

Parking brake and emergency accumulator (6033GD)

Zone:

Are installed to absorb pump pulsations and surges caused by high fluid demands.

Is available as soon as the parking brake and emergency brake accumulator pressure is above 1.600 PSI.

195

Ground service panel On this panel are ground power pressure and suction quickdisconnect fittings to apply external hydraulic power to the green or blue system. Zone:

196

Case drain

Zone:

195

Rev 01 – January 2014

Filters, pressure transmitters, low pressure switches, over temperature sensors, low level switches, pressure relief valves and cross feed valve are located in the case drain.

© ATR. All rights reserved. Confidential and proprietary document. For Training Purpose Only.

68

ATR-600: ICE AND RAIN PROTECTION

Ice And Rain Protection Schematic

Rev 01 – January 2014

© ATR. All rights reserved. Confidential and proprietary document. For Training Purpose Only.

69

ATR-600: ICE AND RAIN PROTECTION

Labels Ice and Rain Protection

Dual distribution valve inflation sequencing of boots A or B is not correct

- Air pressure on the airframe distribution line is less than 14 PSI. - Air temperature upstream of the pressure and regulator shut-off valve exceeds 230°C for more than 6 seconds.

-Both MFC modules associated to air intake boots control fail resulting in an incorrect inflation sequencing.

-Ice accretion is detected

-Fault of propellers anti-icing is detected

Rev 01 – January 2014

© ATR. All rights reserved. Confidential and proprietary document. For Training Purpose Only.

70

ATR-600: ICE AND RAIN PROTECTION

Ice And Rain Protection Panels for Maintenance

Ice Detector Panel

APM Panel

Propellers Anti-Icing PTT Switch

Windshields Heating PTT Pushbutton

Ice Detector Panel: Information ICING AOA is displayed when any horns is selected ON. The PTT pushbutton allows to test ICE detection activation light. APM Panel: Controls and monitors the APM system. The PTT pushbutton allows to test the system functioning. Propellers Anti-Icing PTT Switch: is used to test propeller anti-icing functioning. Windshields heating PTT Pushbutton: Is used to test windshields heating functioning.

Rev 01 – January 2014

© ATR. All rights reserved. Confidential and proprietary document. For Training Purpose Only.

71

ATR-600: ICE AND RAIN PROTECTION

MFC code: MISCELANEOUS 1 Definition Anti-Ice: Left Main W/S Control Open Failure Signal Anti-Ice: Right Main W/S Control Open Failure Signal

MFC code: MISCELANEOUS 2 Definition

Anti-Ice: Auto Mode Switches Disagree

Anti-Ice: Left Propeller Heater Fault Anti-Ice: Right Propeller Heater Fault

MFC code: MISCELANEOUS 4 Definition Right Empennage Boot A Fault Right Empennage Boot B Fault

Rev 01 – January 2014

© ATR. All rights reserved. Confidential and proprietary document. For Training Purpose Only.

72

ATR-600: ICE AND RAIN PROTECTION

Ice Detection Components

Ice Detector (3DD)

Zone:

515

Access:

515

Ice Evidence Probe (5DD)

Zone:

211

Rev 01 – January 2014

It alerts the crew as soon as and as long as ice accretion is sensed by the probe. The detection probe has its own axial vibration frequency, approximately 40 KHz, which is modified by ice accretion. It enables the cockpit crew members to visually detect the beginning of ice formation, and visually check that aircraft is free of ice after an icing encounter. During night operation, ice accumulation masks a light source controlled by the NAV lights switch.

© ATR. All rights reserved. Confidential and proprietary document. For Training Purpose Only.

73

ATR-600: ICE AND RAIN PROTECTION

De-Icing Components

Dual Distributor Valves (9DM-10DM)

Zone:

513

513 Access: 613

Pressure and Regulator Shut Off Valve (13DM-14DM)

Zone:

435

Access:

When operating, the dual distributor valves serves to supply pressure for alternate inflation and deflation of the de-icers boots. When the system is not operative, negative pressure maintains the de-icers against the structure.

Two de-ice valves regulate the pressure of the air bleed from the engines, to the same pressure supplying the deicers. The air bleed pressure is 20.3 PSI (1.4 bar).

435 AL 445 AL

Shut Off Valve (81DM - 82DM) Two isolation valves are provided to isolate the engine air intake or airfoil de-icing system in case of local failures. Zone:

435

Access:

435 AL 445 AL

Rev 01 – January 2014

© ATR. All rights reserved. Confidential and proprietary document. For Training Purpose Only.

74

ATR-600: ICE AND RAIN PROTECTION

Anti-Icing Components

Standby Controller (109DM)

Zone:

214 93VU

Access:

222 PZ 222 CZ

A standby de-icing control unit is there to ensure an emergency de-icing in case of failure of the normal system.

Horns Controller (57DM-58DM) They supply power to the horn heating resistors and monitor correct operation of the horns anti-icing system.

Zone:

214 93-94VU

Rev 01 – January 2014

Access:

222 PZ 222 CZ

© ATR. All rights reserved. Confidential and proprietary document. For Training Purpose Only.

75

ATR-600: ICE AND RAIN PROTECTION

Anti-Icing Components

Windshield Heating Control Units (1FP11FP2)

Zone:

One per windshield are installed on the forward fuselage section, just after the pressure bulkhead. The system ensures that the outer surface temperature remains above 1.6°C (35°F) and that the inner surface temperature remains above 21.1°C (70°F).

122

Side Window Heating Control (1UA1-1UA2)

The Side windows left & right are controlled by the MFC 1 and 2 through two relays, one for each side. The system ensures that the outer surface temperature remains above 1.6°C (35°F) and that the inner surface temperature remains above 21.1°C (70°F). Zone:

214

Rev 01 – January 2014

© ATR. All rights reserved. Confidential and proprietary document. For Training Purpose Only.

76

ATR-600: ICE AND RAIN PROTECTION

Anti-Icing Cycles

De-Icing Cycles

180s

Rev 01 – January 2014

© ATR. All rights reserved. Confidential and proprietary document. For Training Purpose Only.

77

ATR-600: INDICATING AND RECORDING SYSTEMS

Indicating and Recording Schematic

Rev 01 – January 2014

© ATR. All rights reserved. Confidential and proprietary document. For Training Purpose Only.

78

ATR-600: INDICATING AND RECORDING SYSTEMS

Labels Indicating and Recording

Aircraft is not in take-off configuration

A malfunction or electrical supply fault is detected in the associated MFC module.

The DU firmware has detected that the DU is empty i.e. has no operational software

A fatal failure has been detected by DU software or by hardware

The hardware pin prog parity check on pin programming is failed

Loading failure

Safety test in progress

Rev 01 – January 2014

© ATR. All rights reserved. Confidential and proprietary document. For Training Purpose Only.

79

ATR-600: INDICATING AND RECORDING SYSTEMS

Indicating and Recording Panels for Maintenance

Left Hand Maintenance Panel

Right Hand Maintenance Panel Multi-Purpose Control and Display Unit

LH Maintenance Panel: The rotary selector enables selection of the system to be tested. It must be replaced in the NORM-FLT position before flight. The Push-To-Test (PTT) pushbutton allows the selected test to be activated. RH Maintenance Panel: The BITE LOADED magnetic indicator indicates that a failure has been recorded by the maintenance system. The TEST pushbutton is used to check operation of the BITE LOADED magnetic indicator. When pressed for more than 3 seconds, the magnetic indicator is activated. The PTA/ERS P/B allows CROSS-TALK test of MFC, internal reset bite MFC and reset the bite loaded. Multi-Purpose Control and Display Unit: The maintenance BITE function allows the display of maintenance information through the MCDU.

Rev 01 – January 2014

© ATR. All rights reserved. Confidential and proprietary document. For Training Purpose Only.

80

ATR-600: INDICATING AND RECORDING SYSTEMS

Indicating Components

EFCP (EFIS Control Panel): The EFCP allows cockpit crew to control the display of MFD pages, some Navigation Display functionalities and the Alert Window and Procedure Window of the EWD. MCDU (Multi-Purpose Control and Display Unit): The MCDU is used to interface with the FMS, the ACARS, the RMS and the CMS. ICP (Index Control Panels): The ICP allows cockpit crew to control speed target, pressure (barometric pressure setting), and Decision Height (DH) and Minimum Descent Altitude (MDA).

Rev 01 – January 2014

© ATR. All rights reserved. Confidential and proprietary document. For Training Purpose Only.

81

ATR-600: INDICATING AND RECORDING SYSTEMS

MCP (Multi-Purpose Control Panel): The MCP allows cockpit crew to control the virtual control panel (VCP) on MFD. The VCP is functionally interfaced with the Radio Management Application and the Flight Management Application. Switching Panel: In normal conditions, CAPT Display PFD/EWD/MFD pushbutton transmits data to DU2 through discrete, in case of DU2 failure, data are transmitted to DU1. In normal condition, F/O Display PFD/EWD/MFD pushbutton transmits data to DU4 through discrete, in case of DU4 failure, data are transmitted to DU5. Clock: Time is given on two digital electronic clocks. The Electronic Clock contains an integrated time base and is controlled by a microcontroller.

Rev 01 – January 2014

© ATR. All rights reserved. Confidential and proprietary document. For Training Purpose Only.

82

ATR-600: INDICATING AND RECORDING SYSTEMS

Master Warning Display

Master Caution Display

Engine Warning Display

Engine Warning Display: The EWD is presented on the centre display unit in normal configuration. It provides the primary system information, crew alerting information and procedure included into the Crew alerting System. Master Warning Lights: Black inscription on red background, they flash red together with simultaneous transmission of continuous repetitive chime when a level 3 failure is detected, associated to a red warning on EWD alert window. Master Caution Lights: Black inscription on amber back ground they flash amber together with simultaneous transmission of single chime when a level 2 failure is detected. TO CONFIG TEST Pushbutton: The TO CONFIG TEST pushbutton enables, before take-off: checking that the aircraft is in correct take-off configuration by simulating Power Levers at TO position without taking the parking position into account. EMER AUDIO CANCEL Switch: The EMER AUDIO CANCEL switch is safety guarded. If a false system indication generates an undue continuous aural warning, the use of this switch will cancel the aural specific to this false alert without loss of the other aural alerts even if they are identical to the inhibited one. Rev 01 – January 2014

© ATR. All rights reserved. Confidential and proprietary document. For Training Purpose Only.

83

ATR-600: INDICATING AND RECORDING SYSTEMS

CAC Core Avionic Cabinet

Zone:

213 80VU

MFC Multi Function Computer (1UA1-1UA2)

Zone:

Logic functions are performed by CAC’s which acquires and process system failures. The CAC manage the display of all alert messages. All CAC’s card are connected to the 28VDC aircraft electrical network.

214

Rev 01 – January 2014

The system integrates management and monitoring logical functions for different aircraft systems. It consists of two computers MFC1 and MFC2 and results in reducing the number of relays significantly, replacing small electronic units which ensure weight saving and simplifying definition, installation and modifications of related systems.

© ATR. All rights reserved. Confidential and proprietary document. For Training Purpose Only.

84

ATR-600: INDICATING AND RECORDING SYSTEMS

Recording Components

MPC Multi-Purpose Computer (zone 213): A MPC (191TU) is located in the LH electronic racks. It is composed of two independent applications, Flight Data Acquisition Unit FDAU software part, and Data Management Unit DMU software part. Accelerometer (zone 121): The three axis accelerometer (7TU) is located at the aircraft centre of gravity, under the cabin floor. The accelerometer sends three signals, proportional to the acceleration applied on each axis, to the FDAU. SSFDR Solid State Flight Data Recorder (zone:312) : The SSFDR (9TU) is located in the unpressurized tail cone on the RH side of the aircraft. It encloses two subassemblies, one containing the data processing part, the other containing the crash protected memory part which is placed on equipment handle side. PCMCIA Card: PCMCIA card is divided in several area allowing recording of data. Two modes of recording are provided, a continuous mode (recommended), and a simple mode. Recording Panel: The Recorder (RCDR) panel permits to energize the SSFDR by selecting ON the RCDR GND CTL pushbutton and de-energize by pushing the RESET pushbutton on the pedestal panel.

Rev 01 – January 2014

© ATR. All rights reserved. Confidential and proprietary document. For Training Purpose Only.

85

ATR-600: LANDING GEAR

Landing gear Schematic

Rev 01 – January 2014

© ATR. All rights reserved. Confidential and proprietary document. For Training Purpose Only.

86

ATR-600: LANDING GEAR

Normal Braking Schematic

Rev 01 – January 2014

© ATR. All rights reserved. Confidential and proprietary document. For Training Purpose Only.

87

ATR-600: LANDING GEAR

Steering Schematic

Rev 01 – January 2014

© ATR. All rights reserved. Confidential and proprietary document. For Training Purpose Only.

88

ATR-600: LANDING GEAR

Labels Landing Gear

Emergency Brake Accumulator Pressure is in low pressure condition Information is invalid

Blue hydraulic pressure is in low pressure condition or N/W Steering switch is in OFF position Information is invalid

Anti Skid failure is detected during test Anti Skid information is invalid Anti Skid test information is invalid

Parking brake is set Information is invalid Green hydraulic system is in low pressure condition Information is invalid

Emergency Brake Accumulator pressure is in low pressure condition Information is invalid

Rev 01 – January 2014

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89

ATR-600: LANDING GEAR

Landing Gear Panels for Maintenance

LH Maintenance Panel

RH Maintenance Panel

LH Maintenance Panel: On this panel, “WARN” rotary selector enables selection of the LDG GEAR NOT DOWN system to be tested. When activated CCAS is triggered. RH Maintenance Panel: On this panel, “BRK TEMP” push to test button enables the entire system of the brake temperature monitoring to be tested. When A/C is jacked, “WEIGHT ON WHEELS” selector must be set to FLIGHT position to accept electrical external power from Ground Power Unit. “BITE LOADED” magnetic indicator turns amber when a Weight On Wheels, Landing Gears or Brakes failure has been recorded.

Rev 01 – January 2014

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90

ATR-600: LANDING GEAR

Landing Gear

MFC code: BRAKE Definition Left Inboard Brake Overheat Left Outboard Brake Overheat Right Inboard Brake Overheat Right Outboard Brake Overheat Left Inboard Transmitter Power Loss/Output Open Left Outboard Transmitter Power Loss/Output Open Right Inboard Transmitter Power Loss/Output Open Right Outboard Transmitter Power Loss/Output Open Left Inboard Sensor/Transmitter Test Failure

Left Outboard Sensor/Transmitter Test Failure Right Inboard Sensor/Transmitter Test Failure Right Outboard Sensor/Transmitter Test Failure

Rev 01 – January 2014

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91

ATR-600: LANDING GEAR

Main Landing Gear Components

Main Gear Doors The main landing gear supports a three section door to restore fairing contour when the L/G is locked up. The three section door has a honeycomb panel type structure, sections are held together by multiple hinges. Zone:

193-194

Structure Attachment Each main gear is connected to frame 25 and 27 of the fuselage by a trunnion support plate and two side struts. Zone:

731-741

Trunnion Leg (6509GM-6514GM)

Zone:

Main landing gear trunnion leg upper part has two pivot pins which engage to the aircraft structural hinge point. On its lower end, the trailing arm is pivoted.

731-741

Rev 01 – January 2014

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92

ATR-600: LANDING GEAR

Main Landing Gear Components

Shock Absorber (6538GM-6539GM)

Zone:

731-741

Trailing Arm

Zone:

731-741

Side Brace (6508GM-6511GM)

Zone:

The oleo pneumatic double acting shock absorber absorbs landing energy and provides an elastic suspension when the aircraft taxies. It is pivoted between a pin fitted to the trunnion leg and a universal joint fitted to the trailing arm. The trailing arm is hinged to the barrel. Two torque spigots ensure attachment. It supports the axle for the two wheels and brakes and a fitting for the shock absorber. Hydraulic pipes and wires run along the trailing arm.

The folding side brace supports and locks the main gear in the extended position. It includes two arms connected by a hinge, and a secondary alignment, acting between the trunnion and the lower arm of the main alignment.

731-741

Rev 01 – January 2014

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93

ATR-600: LANDING GEAR

Nose Landing Gear Components

Nose Gear Doors The nose gear retracts in a wheel well enclosed by four doors. The four doors are made by honeycomb panels. Zone:

711

Leg Leg is the upper part of NLG. NLG leg is of barrel type with two ribbed arms connected to frame 6 by two pivot pins. Zone:

711

Turning Tube The turning tube is fitting on the nose landing gear structure. The shock absorber is housed in the turning tube.

Zone:

711

Rev 01 – January 2014

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94

ATR-600: LANDING GEAR

Nose Landing Gear Components

Drag Brace (6500GM)

Zone:

711

Shock Absorber

Zone:

711

Rev 01 – January 2014

The folding drag brace is installed between the fuselage and the NLG leg to support and lock the NLG in down position. On ground, a safety pin can be installed in two holes on the secondary alignment, to prevent NLG accidental retraction during maintenance operations The shock absorber is housed in the barrel of the NLG. On its lower part, there is the wheels axle. This is a double oleo pneumatic shock absorber with no separator piston. It absorbs the energy released on impact of the wheels during landing and provides the aircraft with smoother rolling conditions.

© ATR. All rights reserved. Confidential and proprietary document. For Training Purpose Only.

95

ATR-600: LANDING GEAR

Emergency Extension Components

Emergency Handle The emergency handle located on the rear part of the pedestal permits the landing gear emergency extension operation. Zone:

210

Nose Landing Gear Free Fall Assister

Zone:

The NLG free fall assister is installed on the wheel well ceiling under the nose of the aircraft. The NLG free fall assister lever pushes at the towing point for a leg rotation angle of 4 degrees only, allowing opening the door.

711

Main Landing Gear Free Fall Assister (6515GA-6516GA)

Free Fall Assister Zone:

The MLG free fall assisters is connected to the fuselage and to the MLG leg. The free fall assister lever is a pneumatic spring (nitrogen/oil accumulator), and comprises two parts, a fixed one and a sliding one.

193-194

Rev 01 – January 2014

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96

ATR-600: LANDING GEAR

Emergency Extension Components

Gearboxes

Zone:

Forwar Gearbox

116 After Gearbox

Zone:

122

Selector Valve (13GA)

Zone:

Two forward gearboxes are located under flight compartment floor and a third one located under passenger compartment floor. Each box includes a worn gear wheel, whose rotation drives a pushpull cable through its coils. The two forward boxes are mounted on a common shaft, one is actuated by the emergency handle and the other one, driven by the common shaft, actuates the NLG uplock box lever. The aft box is driven by cables which are actuated by the forward boxes assembly. The lever of the landing gear selector valve is operated by the emergency extension handle via push-pull cables. When the lever actuates the valve, both chambers of the three actuating cylinders and the unlocking actuators are connected to the green system return line, to prevent lock out of actuators during landing gear emergency extension.

195

Rev 01 – January 2014

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97

ATR-600: LANDING GEAR

Braking Components

Pedals

Zone:

113-114

Master Cylinder (6028GG-6029GG)

Zone:

The brakes are mechanically controlled by pivoting the upper end of rudder pedals. Each pedal is connected through a linkage to the relevant master cylinder which generates the braking control pressure. Each dual master cylinder is installed below the pedal set. The unit consists of two identical master cylinders enclosed in a common body provided with an integral inlet port.

113-114

Antiskid Control Box (15GG) The box receives inputs from the wheel speed sensors and from ground and flight position relays. The front panel of the unit contains a wheel selector switch, five LEDs and five switches for test purposes. Zone:

214

Rev 01 – January 2014

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98

ATR-600: LANDING GEAR

Braking Components

Wheels Speed Transducer

Zone:

731-741

Brakes (6631GG-6132GG6633GG6634GG)

Zone:

731-741

Brakes Temperature Transducer and Transmitter (38GG39GG-40GG-41GG)

Zone:

Two transducers are mounted inside each, one per wheel main gear axle (18GG, 19GG) & (20GG, 21GG). The speed signal is a sine wave having 36 pulses for one complete revolution wheel. The speed sensor sends to the control box a sinusoidal varying voltage, with a frequency proportional to the rotational speed of the wheel. Each main gear wheel is fitted with a carbon brake (72) steel brake (42). The four brake units are interchangeable for either right or left hand installation.

Temperature transducer are installed on the brake assy. The thermocouple transducer consists of a chromel-alumel junction isolated from housing.

731-741

Rev 01 – January 2014

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99

ATR-600: LANDING GEAR

Braking Components

Metering Valve (6027GG)

Zone:

195

Antiskid Module (16GG)

Zone:

195

Rev 01 – January 2014

The metering valve is a dual type. It is provided with four ports connected to the pilot and copilot master cylinders, two ports connected to the pressure and the returns of the green hydraulic system, and two ports to send the metered pressure to the L and R brakes, through the Antiskid Module. Oil pressure from the normal metering valve to the A/S module is modulated to each brake according to the electrical signals received from A/S control box. If A/S system is switched off, the module does not perform any control on the oil , control pressure passing through only. The module also receives the oil pressure from the parking/emergency braking valve to supply the brakes in parking or emergency operations.

© ATR. All rights reserved. Confidential and proprietary document. For Training Purpose Only.

100

ATR-600: LANDING GEAR

Braking Components Hydraulic Fuse (6037GD-6039GD) They are mounted on the antiskid module. Each of the four fuses stops hydraulic flow to the respective brake in the event of brake line failure. A manual by-pass system is fitted on each fuse for maintenance purpose. This by pass is manually operated bt mecanical lever Zone:

195

Low Pressure Relief Valve (6801GG)

Zone:

The low pressure relief valve consists essentially of a spring-loaded poppet assembly within a body. The low pressure allows flow in one direction only.

195

PEMBV (6031GD) The parking and emergency metering valve is located in the rear area of the left main gear well, and is actuated through parking brake lever. Zone:

195

Rev 01 – January 2014

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101

ATR-600: LANDING GEAR

Steering Components

Steering Solenoid Valve (5GC)

Zone:

195

Steering Differential Control Valve

Zone:

711

Swivel Selector Valve (13GA)

Zone:

195

Rev 01 – January 2014

Electro-hydraulic normally closed valve. There are two main parts: the electro-magnet and the hydraulic. In flight the solenoid valve is de-energized and the steering system is connected to the blue system return, through the valve while the pressure is in standby at the valve inlet.

Two lines connect the actuator chambers to the valve ports B and C. The two ports A and D allow connection of the valve to the blue hydraulic pressure and the return through the swivel valve and the solenoid valve. The valve is equipped on the upper side with a lever linkage at its ends to pilot’s driving mechanism and to feed-back linkage. The valve consists of a fixed part and a rotating part following the strut leg movement. The swivel selector valve cuts the oil pressure if Nose Landing Gear is not in down position.

© ATR. All rights reserved. Confidential and proprietary document. For Training Purpose Only.

102

ATR-600: LIGHTS

Emergency Lights Schematic

Rev 01 – January 2014

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103

ATR-600: LIGHTS

Emergency Lights Panels

Sign Panel The emergency system operation is controlled by means of ON/ARM/DISARM three-position switch. The emergency lighting system enables passenger and crew to exit safely from the aircraft during emergency evacuation. Zone:

211 24 VU

Flight Attendant Panel (2WM)

Zone:

Allows to controlled the cabin lighting, the emergency lighting, and the rear cargo compartment lighting. Emergency lights will automatically illuminate if both DC generators are lost, or if standby bus voltage drop below 18 VDC.

261

Rev 01 – January 2014

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104

ATR-600: NAVIGATION

General Navigation

YAW

PITCH

Rev 01 – January 2014

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105

ATR-600: NAVIGATION

General Navigation Panels For Maintenance

Multi Function Control Display Unit (MCDU)

Multi Function Control Display Unit: Allows to manage the navigation equipments maintenance . The user can access to the "AVIONICS STATUS" page which provide the list of AVS LRU affected by at least one internal failure detected during maintenance phase "ground" (in real time). Since the four "SYSTEM REPORT/TEST", the user accesses to the list of all AVS sub system managed by the CMA.

Rev 01 – January 2014

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106

ATR-600: NAVIGATION

General Navigation Components

Air Data Computers (1FL1-1FL2)

Zone:

213

AHRU Altitude Heading Reference Unit (1FP11FP2)

Zone:

122

RMM Removable Memory Module

Zone:

122

Flux Valves (1FF1-1FF2)

Zone:

524

524 AT Access: 624 AT

Rev 01 – January 2014

The ADUs receive static pressure information, total pressure information, and total air temperature information. The ADUs are connected to the pneumatic system by hoses and self sealing quick attach / detach unions. The longitudinal axes of the AHRUs are parallel to the aircraft centerline. Harmonization is performed at first platform installation: the roll, pitch and yaw deviations with respect to the aircraft are stored in the RMM. A removable memory module stores compensation parameters which serve to correct the magnetic field line interference induced by the aircraft. Each flux valve provides the system with a long term heading reference. It indicates the local horizontal magnetic field vector with an accuracy of 1.0 degree or better.

© ATR. All rights reserved. Confidential and proprietary document. For Training Purpose Only.

107

ATR-600: NAVIGATION

General Navigation Components

VOR/LOC Antenna (5RS)

Zone:

323

The VOR/LOC antenna is made up of two blades which are located on either side of the vertical stabilizer and is common to both VOR/ILS. Coaxial cable length between both blades is an essential factor for the antenna tuning circuit.

Glide Antenna (1RT) The glide antenna is an allaluminium double antenna with a dielectric sealed feed point. This double antenna is common to both VOR/ILS receivers. Electrical bonding is ensured by antenna flange and mounting screws. Zone:

111

Access:

111AL

GPS Global Positioning System Receiver

Zone:

The GPS receiver (155SN1) automatically selects ranging sources for use to compute the localization solution and not use satellites with elevation angle below 5°. The GPS receiver records and stores the history of Power On Self Test (POST) and Continuous Built In Test (CBIT) failure into non volatile memory.

213 84-85VU

Rev 01 – January 2014

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108

ATR-600: NAVIGATION

General Navigation Components

VOR/ILS/MKR/ADF Receiver (1RS1)

Zone:

213 83VU

Rev 01 – January 2014

The VOR/ILS/ADF/ MKR/ADF receiver acquires via VOR/LOC antenna the bearing to the station and the TO/FROM information and provide data to CAC and IESI.

© ATR. All rights reserved. Confidential and proprietary document. For Training Purpose Only.

109

ATR-600: NAVIGATION

General Navigation Components

T²CAS Terrain Awareness Warning System & Traffic Alert and Collision Avoidance System (1SG)

Zone:

213 83VU

APM Aircraft Personality Module (249TU)

Zone:

213 83VU

Rev 01 – January 2014

The T²CAS computer combines TAWS with Ground Collision Avoidance Module and TCASII with Aircraft Collision Avoidance System. The T²CAS computer is supplied via 28VDC BUS 2 . The front panel has a test switch to initiate testing of T²CAS. When the pushbutton is pressed, the T²CAS computer will check its internal integrity and then, its required inputs. After the test, the green LED "TCAS PASS“ & TAWS PASS indicate the TCAS& TAWS system are operational. If TCAS or TAWS is not operational, the LEDs indicate the function which is in fault. The aircraft personality module is a piece of hardware installed on the rear of the equipment tray and remains with the aircraft. This piece of hardware contains: Aircraft specific Database Aircraft Configuration Data Climb capability data Sensor data, filter values, etc Texture, display settings Customer settings (male/female voice, callout, etc)

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110

ATR-600: NAVIGATION

General Navigation Components ATC Air Traffic Control Transponder

Zone:

213 84-85VU

Weather Radar System Transceiver (5002SQ)

Zone:

111

Access:

The weather radar antenna / transceiver generates and receives X-band radio frequency energy at 9345 +/- 25 MHz for the purposes of weather detection and ground mapping. Echo signals received by the antenna are routed to the transceiver.

111AL

Radio Altimeter Transceiver (1SA)

Zone:

ATC transponder provides aircraft identification and location (mode A), and aircraft identification, location and uncorrected barometric altitude (mode C) replies to interrogation from ground based radar. In addition, it provides all the information supplied by modes A and C plus a unique aircraft identifier (mode S) replies to selective interrogation from ground based radar and aircraft TCAS system.

The radio altimeter measures the vertical distance from the aircraft to the ground. It is used during the approach, landing and take off phases of flight. The transceiver houses the radio altimeter transmitter, receiver, and data processing components.

213 83VU

Rev 01 – January 2014

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111

ATR-600: OXYGEN SYSTEM

Oxygen Schematic

Rev 01 – January 2014

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112

ATR-600: OXYGEN SYSTEM

Panel & Labels Oxygen

HP INDICATOR indicates oxygen bottle pressure. It is displayed in PSI x 1000. The red arc is from 0 to 85 PSI.

If preflight pressure is < 1400 PSI, quantity must be checked to be adequate for intended flight.

LO PR illuminates in amber and the CCAS is activated when a low pressure (< 50 PSI) is detected in the low pressure distribution circuit.

Rev 01 – January 2014

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113

ATR-600: OXYGEN SYSTEM

Oxygen Components Zone:

231

Zone:

250

Oxygen cylinder (5306HT-5306HT) Supplies oxygen to the crew and passenger distribution system. Zone:

231-250

Pressure Gauge (1HT) The gauge indicates cylinder pressure with main shut off valve open, or closed. Zone:

231-250

Main Shut off Valve (5HT) The slow- opening manual shut off valve is designed with metal/metal type seats, to avoid ignitions (explosions). Zone:

231-250

Pressure Regulator (3HT) When the cylinder manual shut off is open, the pressure indicator shows: Red range 0 -> 5.86 bar (0 -> 86 PSI) and Green range 5.86 -> 140 bar (85 -> 2025 PSI). Zone:

231-250

Rev 01 – January 2014

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114

ATR-600: OXYGEN SYSTEM

Oxygen Components

High and Low Overpressure Safety Relief and Device (5121HT)

Zone:

Permits the oxygen discharge in case of a rise in ambient temperature, the oxygen increases and causes the expansion of the cylinder pressure.

211

Crew Feed Stop Valve (5HT) The crew feed stop valve solenoid controls opening and closing of the oxygen flow. Zone:

211

211SZ

Access:

Manifold Distributor (5111HT)

Zone:

211

Access:

211SZ

LP Pressure Switch (1HT)

Zone:

211

Access:

Rev 01 – January 2014

Two supply pipes for the crew, one supply pipe for passengers, one pipe for test port assembly and one LP pressure switch are connected to the supply manifold.

211SZ

The LP pressure switch provides an electrical signal LO PR light of the MAIN SUPPLY push button on the cockpit overhead panel when a pressure falls to 50 +/- 5 PSI (3.45 +/- 0.35 bars).

© ATR. All rights reserved. Confidential and proprietary document. For Training Purpose Only.

115

ATR-600: OXYGEN SYSTEM

Oxygen Components

Pax Feed Stop Valve (1WR)

Zone:

211

Access:

211SD

Test Port Assy (5131HT)

Zone:

This test enables a leakage test after any component replacement, functional test if the oxygen cylinder is not installed and cleaning pipes operations.

211

Crew Oxygen Masks

Zone:

The pax feed stop valve solenoid controls opening and closing of the oxygen flow for passengers.

212

Three crew oxygen (5141HT5142HT-5143HT) masks are located in the cockpit, two for the pilots and one for the observer. The mask assembly consists of a mask stowed in a box.

Smoke Goggles They can be automatically demisted by oxygen supplied from oxygen mask (5151HT5152HT-5153HT). Zone:

212

Rev 01 – January 2014

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116

ATR-600: OXYGEN SYSTEM

Oxygen Components

Altitude Compensating Regulator

It feeds oxygen boxes in case of rapid depressurization of the passengers compartment and operates between 25000ft and 10000ft cabin altitude.

Passenger Mask (5320HT5322HT) The oxygen mask supply line is a PVC type, 2.5m long. Zone:

230-250

Portable Oxygen Bottle(5302HT-5306HT)

Zone:

231

Zone:

250

Protective Breathing Equipment (5341HT-5343HT5345HT)

Zone:

230-255-256

Rev 01 – January 2014

The oxygen bottle is a green cylinder containing 120 liters of oxygen with a nominal charge of 1800 PSI (124 bars). The PBE protects the eyes, nose and mouth and provides a breathing chemical gas for 15 minutes in case of fire, smoke or noxious gases.

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117

ATR-600: PNEUMATIC SYSTEM

Pneumatic Schematic

Rev 01 – January 2014

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118

ATR-600: PNEUMATIC SYSTEM

Labels Pneumatic

Bleed Air Shut-Off Valve position disagreement with the relevant pushbutton

Bleed duct temperature exceeds 274°C (525 F)

Loop temperature exceeds 153°C

Cross feed Valve is stuck open with both Engine Bleed Valves open. Cross feed Valve is stuck open with both Engines shut down

Bleed Valve is "FAULT"

Rev 01 – January 2014

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119

ATR-600: PNEUMATIC SYSTEM

Pneumatic Panels for Maintenance

Multi-Purpose Control and Display Unit (MCDU)

RH Maintenance Panel

Multi-Purpose Control and Display Unit: Pneumatic System failure codes and Valves positions can be read through the MCDU. HP Bleed Valve failure codes can be read in Miscellaneous 1 page of the MCDU. HP Bleed Valve position can be read in Alpha Call Up page of the MCDU. RH Maintenance Panel: MFC bite loaded indicator indicates that HP Bleed Valve failures are recorded in the MFC memory. AIR BL LEAK PTT switch permits to check the continuity of the Loops, the controller and the associated warnings.

MISCELANEOUS 1 Definition Air Bleed: Left HP Valve Fault Main Indication Air Bleed: Right HP Valve Fault Main Indication

Rev 01 – January 2014

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120

ATR-600: PNEUMATIC SYSTEM

Pneumatic Components

HP Bleed Air Valve (17HA-18HA) Regulates HP bleed air pressure supply in low power conditions and during ground operation. Zone:

471

HP Bleed Air Thermal Resistance (19HA)

Zone:

471

LP Bleed Air Check Valve (5011HA-5012HA)

Zone:

Platinum resistance sensor inside an hermetic stainless steel case. The resistance of the sensor varies with the temperature, and works only on the ground.

The LP bleed air check valve prevents reverse airflow into the engine LP compressor when the HP bleed air valve is open in low engine power condition.

471

Rev 01 – January 2014

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121

ATR-600: PNEUMATIC SYSTEM

Pneumatic Components

Engine Bleed Air Shut Off Valve (15HA-16HA)

Zone:

476

Engine Bleed Air Over Temperature Switches

Zone:

They are hermetically sealed, stainless steel probes. When the bleed air pressure is > 80 PSI, the Engine Bleed Air S/OFF valve closes.

476

Handling Bleed Valve (5047EQ)

Zone:

They are hermetically sealed, stainless steel probes. They monitor the air bleed temperature (274°C). (11HA-12HA-13HA-14HA)

511

Engine Bleed Air Pressure Switches (67HA-68HA)

Zone:

It is a spring-loaded, normally closed shut-off valve, which is pneumatically actuated and electrically controlled.

473

Rev 01 – January 2014

Provides adequate surge margin mainly during rapid engine deceleration, to provide good steady state engine power characteristics and to reduce noise at low power.

© ATR. All rights reserved. Confidential and proprietary document. For Training Purpose Only.

122

ATR-600: PNEUMATIC SYSTEM

Pneumatic Components

Pneumatic Cross Feed Valve (36HA)

Zone:

122

Bleed Air Check Valve (6113HA-6114HA)

Zone:

291

Leak Control Unit (7HF)

Zone:

214-92VU

Leak Sensing Elements (10HF-11HF)

Zone:

It is electrically controlled, pneumatically actuated It interconnects the right and the left ducting to allow bleed air to flow from the system which is operating to the other side, only on ground without leak detected. The valve prevents reverse airflow to the left engine compressors when the cross feed valve is open with right engine operating in Hotel Mode. It is an electronic device with two monitoring circuits. The level circuit initiates an alarm when the impedance of the continuous element reaches a predetermined low level. The elements consist of a solid nickel conductor embedded in an insulating material and encased in an inconel tube hermetically sealed at both ends.

511

Rev 01 – January 2014

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123

ATR-600: WATER AND WASTE

Water and Waste Schematic

Rev 01 – January 2014

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124

ATR-600: WATER AND WASTE

Potable Water and Waste Components

Water Tank

The capacity of the water tank is 15 liters (4 us gal).

Zone:

261

Ventilation Valve (5111MB)

Zone:

261

Filter/Motor Pump (7MG)

Zone:

261

Rev 01 – January 2014

Ventilation is ensured by passengers compartment ambient air from a valve installed on the upper part of the tank. The shape of this valve prevents water from overflowing during filing operations. The waste disposal and toilet flushing system comprises a filter motor pump assembly. This includes a flush motor, the pump, a filter basket and a timer which controls the flush cycle. The flush motor is supplied with 28VDC/SVCE BUS.

© ATR. All rights reserved. Confidential and proprietary document. For Training Purpose Only.

125

ATR-600: INTEGRATED MODULAR AVIONICS

Integrated Modular Avionics Schematic

Rev 01 – January 2014

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126

ATR-600: INTEGRATED MODULAR AVIONICS

Modular Avionics Panels for Maintenance

Multi Function Control and Display Unit

Engine Warning Display

RH Maintenance Panel

MCDU Multi Function Controls and Display Unit: The multi function controls and display unit is used by maintenance engineers to check AVS memory, LRU identification, Aircraft Configuration and BITE functions. EWD Engine Warning Display: If a failure occurs on Line Replaceable Module (LRM) of the CAC, the EWD displays alert in Alert Window with corresponding procedure in Procedure Window. RH Maintenance Panel: The BITE LOADED magnetic indicator indicates that a failure has been recorded by the maintenance system. MFC code: MISCELANEOUS 3 Definition Module 1A PIN-PROG Disagree Module 1B PIN-PROG Disagree Module 2A PIN-PROG Disagree Module 2B PIN-PROG Disagree Module 1A PIN-PROG Acquisition Fault Module 1B PIN-PROG Acquisition Fault Module 2A PIN-PROG Acquisition Fault Module 2B PIN-PROG Acquisition Fault Rev 01 – January 2014

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127

ATR-600: INTEGRATED MODULAR AVIONICS

Integrated Modular Avionics Components

CPM Processing Module: The CPMs provide shared memory and computation resources to execute hosted avionics applications. CPMs process non-AFDX and AFDX Input/Output (I/O) data that comes from or goes to the other LRUs. CPM cards have the same software and the same part number. IOM Input/Output Module: IOM receives and route NON-AFDX data that could be read by the CPM and other equipment or systems for computation, back-up, display. The IOM-S type Module is dedicated to provide ARINC and discrete I/O for all functions. IOM-AP is dedicated to the Auto Flight application. IOM-DC1 and DC2 provides discrete and analog I/O for DCA application. SWM Switch Module: Each CPM is connected to two redundant AFDX Networks, one ADN network via SWM1 located in CAC, and on ADN network via SWM2 located in CAC2. The Avionic Digital Network purpose is to offer a mean for communication between Display Units and CACs, a crosstalk between the Display Units, and a connection with open world for data loading.

Rev 01 – January 2014

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128

ATR-600: CENTRAL MAINTENANCE SYSTEM

Central Maintenance Schematic

Rev 01 – January 2014

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129

ATR-600: CENTRAL MAINTENANCE SYSTEM

Central Maintenance Panels

Multi Function Control and Display Unit

RH Maintenance Panel

MCDU Multi Function Control and Display Unit: The Aircraft Centralized Maintenance System allows the maintenance operator to access information through a single interface, the MCDU. RH Maintenance Panel: The CPM and SWM software are loaded via a laptop equipped with the PMAT application and through a direct Ethernet connection to the CAC 1 via the “CAC DATA LOADING” plug on 702VU.

Rev 01 – January 2014

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130

ATR-600: DOORS

Cargo Door Schematic

Rev 01 – January 2014

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131

ATR-600: PROPELLER

Propeller Schematic

Rev 01 – January 2014

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132

ATR-600: PROPELLER

Labels Propeller

Abnormal operation, below 41.6% and 62.5% and above 103.5% Red limit is 120 % Invalid numeric NP

One PEC channel is lost or 3 sec illuminated when back up channel is tested

Propeller pitch is below 8° while PL is above FI. Any propeller pitch remains above 8° while PL is retarded to GI

Propeller brake not fully locked or not fully released

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ATR-600: PROPELLER

Propeller Panels for Maintenance

Multi Function Control Display Unit

Right Maintenance Panel

Multi Function Control Display Unit: On ground, by selecting MISC 2, MISC 3 or MISC 4, the failure detection will be displayed. Right Maintenance Panel: Several tests and control device are provided, for maintenance purpose only. All buttons on this panel are to be used on ground only. A bite loaded magnetic indicator turns amber when a system failure has been recorded in MFC memory.

Rev 01 – January 2014

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ATR-600: PROPELLER

Propeller

MFC code: MISCELANEOUS 2 Definition Prop Brake: Switches Disagree

MFC code: MISCELANEOUS 3 Definition Propeller Type Disagree Unknown Propeller Type

MFC code: MISCELANEOUS 4 Definition PEC 1 Failure PIU 2 Failure PEC 2 Failure PIU 2 Failure

Rev 01 – January 2014

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ATR-600: PROPELLER

Hub Blades Assembly Components (5001KH)

Spinner Pitch change mechanism Blades Hub

Zone:

412/422

Oil transfert Tube

Hub

The hub enables the installation of a pitch change mechanism, a six blades with their retention devices, a bulkhead. The hub encloses the propeller lubrication oil.

Blades

Each propeller blade has a composite spar/shell which is fitted on a hub.

Spinner (411AL-421AL)

The aluminium spinner is located at the front of the blades and is guided on the stationary dome of the pitch change mechanism.

Pitch Change Mechanism

Each blade is turned by means of a torque pin in the blade butt, off-centered in such a manner as to provide a crank arm.

Oil Transfer Tube

The oil transfer tube is located between propeller valve module and pitch change mechanism, through the reduction gearbox. The oil transfer tube enables mechanical and hydraulic connection.

Rev 01 – January 2014

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ATR-600: PROPELLER

Controlling Components

Feathering Pump (17KF1-17KF2)

Zone:

The electrical feathering pump supplies high pressure oil (690 PSI) to feather/unfeather the propeller. When energized, the auxiliary motor and pump can supply approximately 7.2 liters per minute.

432

HP Pump (5031KH) The HP pump is a constant flow type. It is driven by the propeller Reduction Gearbox and provides oil pressure to the propeller system. Zone:

430

PVM Oil Supply (52KH1-52KH2)

Zone:

430

Overspeed Governor (3KZ)

Zone:

PVM:

The PVM is secured on the reduction gearbox by means of an adapter and a clamp. It supplies information to the PEC, and provides pitch change oil to the propeller pitch change actuator. The overspeed governor is a back up protection which limits the propeller speed hydraulically or pneumatically.

430

Rev 01 – January 2014

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ATR-600: PROPELLER

Controlling Components

PEC (50KH)

Zone:

436

PIU Propeller Interface Unit (95KH-96KH)

Zone:

The PIU, one per PEC (95KH96KH), is an electronic box located in the electronic bay that provides the interface between the PEC and the flight compartment with propeller speed selection and PEC fault indicating logic.

214 95VU

AFU Auto Feather Unit (44KF-44KF2)

Zone:

The PEC is a dual channel electronic box which provides closed loop control of the propeller pitch change system. The PEC can detect failures and store up to 8 faults in an internal memory that can be displayed by means of MPC menus on MCDU.

400

Rev 01 – January 2014

The AFU comprises logic and control circuits enabling, in case of power loss of one of the engine at take-off, automatic feathering of the failed engine and an uptrim order to the other engine. These functions are activated only after arming of the system.

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ATR-600: PROPELLER

Coils Single-Coil Magnetic Sensor (6 pulses)

Zone:

Dual-Coil Magnetic Sensor

Single-Coil Magnetic Sensor (1 pulse)

411/421

Single-Coil Magnetic Sensor (6 pulses) (3KH)

A single coil sensor, associated with 6 targets, is installed only on the engine 1 bulkhead for synchrophasing purposes. The sensor produces and transmits an electrical signal to the right PEC each time a target pickup located on the bulkhead passes in front of the sensor.

Dual-Coil Magnetic Sensor (66KH)

A dual coil sensor, associated with 6 targets, is installed on the bulkhead for propeller speed measurement. The sensor produces and transmits an electrical signal to the PEC each time a target pickup located on the bulkhead passes in front of the sensor. Each PEC channel receives its own dual-coil sensor output.

Single-Coil Magnetic Sensor (1 pulse) (76KH)

A single coil sensor (one per engine) with one target is installed for propeller dynamic balancing (no link to PEC). These sensors are connected to a test plug in the cockpit.

Rev 01 – January 2014

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ATR-600: PROPELLER

PVM Components RVDT PLA and RVDT Blade in the PVM

Feather Solenoid RVDT PLA Position Sensors

Zone:

430-440

RVDT Blade Angle Feedback Sensors

Zone:

430-440

Feather Solenoid

Zone:

The PLA position sensor is a Rotary Variable Differential Transducer installed on the body section. The shaft of the RVDT engages with a drive spline that is attached to the drive shaft of the mechanism by a pin. The blade angle feed back mechanism is used to give an indication of the propeller blade angle to the PEC. The mechanism is operated by the axial movement of the oil transfer tube acting on a double RVDT giving “Blade angle feed back” to both primary and back-up PEC channels. The feather solenoid is installed to permit the propeller to go to the maximum coarse pitch (feather) position. It controls a drain from the large area side of the protection valve.

430-440

Rev 01 – January 2014

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ATR-600: PROPELLER

PVM Components EHV Electro Hydraulic Valve

Secondary Low Pitch Stop Retract Solenoid

EHV Electro Hydraulic Valve

Zone:

430-440

Secondary Low Pitch Stop Retract Solenoid

Zone:

The Electro Hydraulic Valve is commanded by the PEC via dual windings. The EHV modulates the high pressure supply oil from the gearbox mounted pump into two sources, increase pitch pressure and decrease pitch pressure. The amount of current provided to the EHV by the PEC determines the Blade Pitch Slew Rate (BPSR).

The SLPS solenoid is used to move a ball valve that permits or stops the fluid supply from the overspeed governor to the transfer bearings. This allows or cancels operation of the inflight fine pitch stop (Secondary Low Pitch Protection).

430-440

Rev 01 – January 2014

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ATR-600: ENGINE SYSTEMS

Engine Oil System Schematic

Rev 01 – January 2014

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ATR-600: ENGINE SYSTEMS

Engine Fuel System Schematic

Rev 01 – January 2014

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ATR-600: ENGINE SYSTEMS

Labels Engine System A fault occurs during a start sequence

The Cross Start function has failed

Torque indication is above 120%

NP digital counter, between 41.6% and 62.5% and above 103.5%

NP digital counter, red limit is 120%

ITT amber range is from 765°C to 840°C

Red limit point “H" in hotel mode is 715°C. Red line “S“ is 950°C, limit during starting

NH red line is 106.4%

NL amber range is from 104.2 to 106.4% NL red limit is 106.4%

Oil pressure indicator, red range is from 0 to 40 PSI

Rev 01 – January 2014

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ATR-600: ENGINE SYSTEMS

Upon detection of low pressure by low pressure switch, LO PR flag is displayed

Oil temperature arc range are, red line is set at 140°C Oil temperature pointer and counter ranges are, red values is below -40 and above 140°C

Fuel temperature, amber range is 54 to 0°C and 50 to 100°C Fuel temperature, a red line is set at 100°C

"CLOG" amber flag is displayed when HP pump fuel filter begin to be clogged

Illuminates amber and the CCAS is activated when the IDLE GATE does not engage engage automatically in flight or does not retract automatically at landing

BOOST disagreement between the automatic selection and the PB position

is

EEC pb :Illuminates amber and the CCAS is activated when the EEC failure is detected. When flashes, power is locked at its pre-failure value.

Rev 01 – January 2014

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ATR-600: ENGINE SYSTEMS

Engine System Panels For Maintenance

Multi-Purpose Control and Display Unit (MCDU)

Right Hand Maintenance Panel

Right Maintenance Panel: Several tests and control devices are provided, for maintenance purpose only. All buttons on this panel are to be use on ground only. EEC/PEC SEL Switch: Used to select EEC or PEC depending on appropriate maintenance test on Engine TRIM switches or LRU code failures. Engine TRIM test and LRU Switches: Switch with two stable positions used to: Test EEC or PEC channel. Maintenance data appears on the MCDU. (Selected by EEC/PEC SEL switch). Perform EEC or PEC trim to ensure that power delivered corresponds to PL position (can be performed with engine not running and PL in the notch) or LRU code failures. BUS ARINC Switches: Bus ARINC function is tested

MFC code: MISCELANEOUS 2 Definition EEC 1 Fault Latch EEC 2 Fault Latch

Rev 01 – January 2014

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ATR-600: ENGINE SYSTEMS

Engine Components Pressure and Temperature Stations: P0/T0: at air inlet section (outside) P1/T1: at air inlet section P1.5/T1.5: in the middle air duct P1.8/T1.8: in the upper air duct P2/T2: LP compressor inlet P2.5/T2.5: HP compressor inlet P3/T3: HP compressor outlet P4/T4: HP turbine inlet P5/T5: HP turbine outlet P6/T6: LP turbine outlet P7/T7: free turbine outlet Mounts An engine mounts is a truss structure composed of titanium tubes welded onto Vshaped fittings. Zone:

435

Idle Gate

Zone:

The idle gate function is used to prevent Power Lever angle reduction below Flight Idle, in flight as soon as both landing gear absorbers are released.

211

Rev 01 – January 2014

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ATR-600: ENGINE SYSTEMS

Engine Fuel Components

Fuel Flow Meter (5QD) The flow meter transmitter does electrical power. flow across this 700kg/h.

Zone:

or fuel flow not use any The maximum transmitter is

434

Fuel Filter/Heater The filter is provided with a bypass valve which opens when the pressure drop equals 3 PSI. The fuel temperature is maintained between 10°C and 32°C. Zone:

430-440

HMU Hydro Mechanical Unit The fuel control is provided by the HMU. It provides the required fuel quantity to the nozzles.

Zone:

430-440

Rev 01 – January 2014

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ATR-600: ENGINE SYSTEMS

Engine Fuel Components

EEC Electronic Engine Control In normal operation, the fuel control is managed by the Engine Electronic Control (EEC).

Zone:

430-440

Fuel Pump The fuel pump assembly is composed of a 74 micron filter located before the gear pump, a pump, and a 10 micron filter located at high pressure fuel pump outlet.

Zone:

430-440

Rev 01 – January 2014

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ATR-600: ENGINE SYSTEMS

Engine Fuel & Controls Components

FCOC Fuel Cooled Oil Cooler

The Fuel Cooled Oil Cooler cools the propeller Reduction Gearbox lubrication oil and is equipped with a thermostatic bypass valve.

430-440

Zone:

Fuel Drain Tank At shut down, fuel is returned to the drain tank from the flow divider/dump valve. Fuel in the tank lifts the float and unseats the float valve from the orifice. Zone:

470-480

Flow Divider/Dump Valve

Zone:

The flow divider valve schedules the metered fuel, from the HMU, between the primary and secondary fuel manifold as a function of primary manifold pressure.

470-480

Fuel Nozzle

Zone:

470-480

Rev 01 – January 2014

14 fuel manifold adapters and nozzles are mounted all around the gas generator case. They are connected to the primary manifolds and secondary manifolds.

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ATR-600: ENGINE SYSTEMS

Engine Oil Components

Check Valve

430-440

Zone:

Flaps System

Zone:

450-460

Pressure Regulating Valve

Zone:

Cooling flaps are controlled by a thermal actuator in contact with the oil outflow. The flaps are completely closed for an oil temperature less or equal to 71°C. The pressure regulating valve piloted by the air pressure in the transfer gearbox casing, regulates oil pressure to ensure lubrication of the bearings.

430-440

Low Pressure Transmitter (6ES)

Zone:

The check valve prevents major oil leakage while internal air pressure is not yet built up. As soon as the pressure reaches 46 PSI, the check valve opens and all the bearings are lubricated.

Upon detection of a low pressure, the oil pressure switch generates a signal to the multifunction computer and CAC which triggers warnings.

430-440

Rev 01 – January 2014

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ATR-600: ENGINE SYSTEMS

Engine Oil Components

Oil Pressure Transmitter (5ES) The oil transmitter range is from 0 PSI to 90 PSI under normal operating conditions.

Zone:

430-440

Breather Venting System The centrifugal breather separates air from oil. Oil is centrifuged outwards and is drained to oil tank. Air is vented through the centre of shaft. Zone:

470-480

Oil Pump Pack The pack comprises a pressure pump and two scavenge pumps. A pressure relief valve returns oil to the tank to prevent a pressure surge during cold starting. Zone:

430-440

Rev 01 – January 2014

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ATR-600: ENGINE SYSTEMS

Engine Air Components

Air Switching Valve The air switching valve ensures an adequate air supply during starting by directing P3 air to areas normally pressurized by P2.5 (during initial startup, P3 is only pressurized air available). Zone:

470-480

HBV Handling Bleed Valve (5047EQ) The HBV is a piston type valve, air pressure operated, controlled by the EEC. Its purpose is to bleed low pressure compressor (P2.5) to provide adequate surge margin and good steady state engine power characteristics. Zone:

470-480

Rev 01 – January 2014

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ATR-600: ENGINE SYSTEMS

Engine Indicating Components

Torque Sensors (7EP1-7EP2)

Zone:

430-440

ITT Thermocouples Sensors

Zone:

Torque sensor TQ1 (left side) provides only one torque signal (ANALOG) for indication through the AFU. Torque sensor TQ2 (right side) provides two torque signals to the EEC, one for power management and torque indication , and one is used as a back up. It also provides a signal corresponding to the power turbine rotational speed for the EEC.

470-480

Rev 01 – January 2014

The nine thermocouples are connected together in parallel and to a junction box. The probe value is calibrated for each engine and marked on the engine data plate. The output signal corresponding to the average value obtained from thermocouples is sent to the ITT indicator and displayed in analog and digital form.

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ATR-600: ENGINE SYSTEMS

Engine Indicating Components

NH Sensors

NH1

NH1

NH2

NH2

Each sensor consists of a magnetic rod and at least one wire coil. The magnetic rod has an inherent magnetic field. As a gear tooth passes the sensor, this magnetic field is interrupted and a current is created through the coil.

NL Sensors

Rev 01 – January 2014

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ATR-600: ENGINE SYSTEMS

Engine Starting Components

Ignition Exciter (5031EQ)

Zone:

434

Ignition Plugs

Zone:

Each igniter has a central electrode enclosed in annular semi-conducting material. The electrical potential developed by the ignition exciter is applied across the gap between the central electrode and the shell.

470-480

High Voltage Leads

Zone:

The two exciters are sealed and fitted with one input connector which supplies the ignition exciter with 28VDC, and an output connector which is used to connect the high voltage leads supplying each plug. The ignition exciters transform the 28VDC in high voltage pulses. Each independent discharge circuit has a plug and produces a hundred sparks per minute.

470-480

Rev 01 – January 2014

Two identical leads provide the high voltage distribution. They transmit the power supplied by the ignition exciter to each plug. Each cable end is fitted with a connector enabling connection between the ignition exciter and the plug

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ATR-600: ENGINE SYSTEMS

Technical Publication

Here are the technical publications available for ATR aircrafts, of course, depending of your job, it's not necessary to know everything, however, it's nice to know that documents exist, even if you are not directly concerned... MPD Maintenance Planning Document CMM/M Component Maintenance Manual / -AMM Aircraft Maintenance Manual Manufacturer " D/O Description - Operation CMM/V Component Maintenance Manual / Vendors " JIC Job Instruction Cards SRKM Structural Repair Kit Manual " TSM Trouble Shooting Manual CPCICF Corrosion Prevention / Inspection / Findings IPC Illustrated Parts Catalog QEC Quick Engine Change " Parts Illustrated Parts Catalog VD Vendor Directory " CRT Cross Reference Table VWM Vendor Warranty Manual WDM Wiring Diagram Manual VPSA Vendor Support Agreement " ASM Aircraft Schematic Manual SB Service Bulletin / Letter " AWM Aircraft Wiring Manual AC Airplane Characteristics " AWL Aircraft Wiring List/Hook Up List FCOM Flight Crew Operating Manual CLM Component Location Manual AFM Airplane Flight Manual SRN Structural Repair Manual MMEL Master Minimum Equipment List NDTM Non Destructive Testing Manual CL Check List ITEM Illustrated Tool & Equipment Manual WBM Wight & Balance Manual CCC Crash Crew Chart Rev 01 – January 2014

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ATR-600: ENGINE SYSTEMS

Technical Publication Aircraft Maintenance Manual (AMM) The Aircraft Maintenance Manual for ATR conforms to ATA Specification No. 100, Revision 21. ATR declines all responsability in the event that the instructions given in the Aircraft Maintanance Manual are not observed in their entirety. 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. The Aircraft Maintenance Manual has been split into two manuals: 

The Description and Operation Manual whose technical content corresponds to pages 1 to 99 of the conventional Aircraft Maintenance Manual.



The Job Instruction Card Manual whose technical content corresponds to pages 201 to 899 ;this manual contains the necessary data to cover Scheduled Maintenance Procedures prescribed by the Maintenance Review Board (MRB) or the Minimum Master Equipment List (MMEL).

The Job Instruction Card manual has been divided into two sections: 

Section 1 contains general information.



Section 2 contains the Job Instruction cards only.

Trouble Shooting Manual - TSM Scope of the Trouble Shooting Manual The TSM is a manual for use when the aircraft is on the ground. It is intended to provide ground maintenance crews by means of isolating faults in order to reduce downtime. Its aim is to enable detection of faulty components within a failed system by analyzing fault symptoms appeared in flight or on the ground (Test).

The Illustrated Parts Catalog includes (IPC): All removable A / C manufacturer items with associated detail parts. All vendor units covered by a specific documentation (CMM) and associated maintenance-removable breakdown parts. All standard parts (screws, washers, connectors, pins, etc...). The IPC is so arranged to allow for very convenient utilization in conjunction with job cards. This publication complies with the requirements of the ATA specification No. 100. Rev 01 – January 2014

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ATR-600: ENGINE SYSTEMS

Technical Publication Wiring Diagram Manual (WDM): Diagram Make-Up The schematics contained in these manuals have been prepared to meet ATA specification No. 100 requirements and include four types, as follows: Block Diagrams : have broard scope but little depth. Simplified Schematics : have schematic symbols but do not show sufficient detail to permit fault isolation. Schematics : show all line replaceable items, all A/C wiring, within a sub-sub system and give sufficient depth for A/C fault isolation. Wiring Diagrams : show all components and wires. Charts In some cases, simplified schematics, logic diagrams or block diagrams have been incorporated in schematics whenever it has been deemed necessary, for full understanding of system operation.

Component Location Manual (CLM): The purpose of the CLM is to present the location the location of all major equipement intems of the aircraft. The location of an equipement can be found on the besis of the initial knowledge: Of the correspondig ATA Chapter Of its functional item number (FIN) Contents of manual This document is divided into six sections as follows: ATA entry FIN entry ATA zone zoning access

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ATR-600: ENGINE SYSTEMS

Technical Publication Structural Repair Manual (SRM): The structural repair manual provides descriptive information for the identification and repair of all aircraft structures. This manual is organized per ATA chapters as follows: 51 - General 52 - Doors 53 - Fuselage 54 - Nacelles / Pylons 55 - Stabilizers 56 - Windows 57 - Wings Illustrated Tool and Equipment Manual (TEM): This manual provides information on tools and ground equipment (including test and trouble shooting equipment) required for the accomplishment of all maintenance tasks as described in the aircraft maintenance manual. This manual does not deal with standard tools and equipment. However, it does cover the particular adaptations required for their operation. Ground equipment such as passenger stairways, luggage loading device, towing truck, etc... which is considered as airport equipment is not covered in this document. The information supplied is more or less comprehensive depending on whether the tool or equipment is of a complex nature, or not. In the case of a complex tool or equipment requiring specific information on its operation, maintenance and overhaul, the Manual gives identification data and cross-reference to Ground Equipment Manuals. In the case of a tool requiring no specific information, the Manual gives identification data for that tool and, if required, for the tool components.

QEC Build-up Guide: For instance installation of componenets which are not supplied by Pratt & Whitney such as AC generator, Propêller Control Unit (PCU)…. Electrical harness furnished by ATR… The purpose of this guide is to provide the operator with all data necessary to equip a basic engine delivered by PRATT & WHITNEY to convert it into a power plant suitable for use as a Quick Engine Change unit (Q.E.C. unit). ... For instance installation of components which are not supplied by Pratt & Whitney such as AC generator, Propeller Control Unit (PCU)... electrical harness furnished by ATR

Rev 01 – January 2014

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ATR-600: ENGINE SYSTEMS

Technical Publication

Rev 01 – January 2014

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161