Annexes — Direct Transcription from PNG Pages¶
Source: ATR_Systems_Guide_42_72-600 PNG pages 189–236 Extracted via OCR Page 189 = ANNEXES section divider (page 187 in PDF numbering) Page 219 = Intentionally blank
ANNEXES / ANNEX 1. COCKPIT PANELS¶
Page 189 (PDF 187)¶
ANNEXES ANNEX 1. COCKPIT PANELS For New Air Management System (NAMS), refer to annex 2 For Freighter aircraft, refer to annex 3 72-600F
[Panel descriptions — Cockpit overhead, fire, flight control, fuel, lights, wipers, call panels]
SQUIB TEST Elect test of squibs. FAULT resistance/capacitance. Inhibits fire signals until turned off. LOOP on FWS (DC EMER) SQUIB armed when T handle pulled. Discharges bottle. (DC EMER / HOT MAIN BAT). DISCH bottle depressurized. Opposite agent DISCH Lt will also illuminate on other fire panel.
ENGINE FIRE HANDLE Pulled: on the respective engine Prop - Feather Fuel - LP valve closed Air - Bleed valve closed Deice - Deice & shutoff valve closed Elect - DC & ACW gen. disconnected Squibs - Armed (Lts illuminated) Hydraulic - Hyd prop brake (eng 2 only)
[Panels described further: SQUIB, FIRE, TLU, FLT CTL, MFC, SPLR, LDG GEAR, DOORS, ENG 1/2, FUEL VALVE, PUMP, FLT COMPT LT, CALLS, STORM, SELCAL, NAMS, CAPT WIPER, DOME, MIN CAB LT]
Page 190 (PDF 188)¶
[Continued cockpit panel descriptions — Electrical system panels]
UNDV DC STBY <19.5V. FWS. OVRD Transfer of STBY buses from HOT MAIN to HOT EMER BAT BUS. INV FAULT Inv failure or supply loss Auto-Xfer of all AC buses to remaining inverter. FWS. Emergency supply indicators (Amber arrows) (Respective battery discharging). ON Pb pressed IN (ON illuminated CYAN). TRU is connected to ACW BUS 2 - ARROW illuminates green when supply of DC EMER BUS, DC STBY BUS, INV 1 (AC STBY BUS) and DC ESS BUSS from TRU is effective. FAULT Battery charger failure detected by MFC. FWS. Contactor Auto opens (MFC) if: thermal runaway/Bus voltage <25V / start sequence/Bat sw on OVRD. Respective bus not supplied. FWS. SHED One of the DC SVCE / UTLY 1 and 2 busses is shed (BPCU). FWS OFF: all the DC SVCE BUS/ UTLY 1 and 2 busses are shed Opposite generator has not come on line to assist start at 10% NH (on ground only). Generator FAULT LT Extinguishes above 61.5% NH if GEN is operating normally. ON started engaged. At 45% NH, light out, starter disengages automatically. CRANK dry monitoring (no ignition). START selects a start sequence. In flight regardless of start selection (A, B, A+B) both exciters are energized. Prop Brake not fully locked or not fully released. After 15 sec = FWS. Supplied by DC SVCE BUS (Back up DC BUS 1). Supplied by ACW. 190
[Further panel descriptions: MAIN ELEC PWR, LAC BUS, INV, TRU, BAT, DC BUS, DC GEN, EXT PWR, START, ENG START, EXT LT, BEACON, NAV, STROBE, LOGO, TAXI & TO, LAND, WING]
Page 191 (PDF 189)¶
[Continued — Hydraulic, ACW, Probes, Anti-Icing, Seat Signs panels]
Main BLUE PUMP Supplied by ACW, controlled by DC EMER BUS.
AUX PUMP Running conditions: - AUX PUMP pb depressed - at least one engine running - blue system press < 1500 psi - prop brake off - gear lever down (supply: DC BUS 2 or HOT MAIN BAT BUS) OVHT Temp > 121C (250F). FWS (no auto off)
[Further panels: HYD PWR, ACW ELEC PWR, ACW BUS, ACW GEN, EXT PWR, PROBES HTG, WINDSHIELD HTG, ANTI ICING, DE ICING, AIRFRAME, ENG 1/2, AFRAIR BLEED, SEAT SIGNS, EMER EXIT LT, BELTS, Main GREEN PUMP, XFEED, LO PR, LO LEVEL, ISOL, STAT, TAT, PITOT, PITOT STBY, PROP 1/2, MODE SEL, DE ICING, MODE SEL AUTO, MAN, FAST/SLOW, FAULT, ON, LOVRE, NO DEVICE, EMER LOC XMTR, etc.]
191
Page 192 (PDF 190)¶
[Continued — Fire, Oxygen, Avionics Vent, Air Bleed, Pack Valve, De-Icing panels]
Tests all three smoke detections (elec. fwd. aft smoke Red alarms in FWS + MW +CRC). Stops extract fan, only on ground (FAULT on EXHAUST MODE). To restart extract fan it is necessary to reset EXHAUST MODE Pb PB in: Crew supply only. If below 1400 psi, use table.
NORM - On ground, ENG 1 off: extract fan on. Ovbd valve full open, U/F valve closed. - On ground, ENG 1 on: extract fan on. Ovbd valve closed, U/F valve opened. FAULT Fan failure / overheat (fan inhibited for 120s after every eng start. FWS). OVBD Extract fan off. OVBD valve partially opened (in flight only). U/F valve closed. Duct temperature limited to 88C. (191F) by pneumatic temp limiter. NORM: 22 psi HIGH: 30 psi regulated by pack valve
[Further panels: FIRE, COMPT SMK, OXYGEN, AVIONICS VENT, EXHAUST MODE, OVBD VALVE, RECIRC FAN, COMPT TEMP, CABIN TEMP SEL, PACK VALVE, AIR BLEED, GRD X FEED, ENG 1/2 BLEED, LEAK, OVHT, FAULT, ENG/WING DE ICING, F/O WIPER, TEST, DIM]
192
Page 193 (PDF 191)¶
[Continued — EFCP, FGCP, IESI, PWR MGT, APM, Stick Pusher panels]
Menu P/B Enable sub function selection menu Brightness SEL P/B Change cursor selection between VHF COM, VHF NAV, BARO SETTING and COURSE when VOR mode.
BOOST (if installed) ON The boost can be selected on ground with the PL below Fl, or in flight after an engine failure. When the torque is thermodynamically limited, the boost increase the torque: - With PWR MGT in TO by: - 4.5% up to 4000ft - 4% above 4000ft - With PWR MGT in MCT by 4% The selection of the boost is latched when the PLs are advanced above Fl, and cannot be changed during flight (except in case of engine failure). FAULT For any disagreement between the position of the push button and the rating of both EEC (MC+SC+FAULT+ENG BOOST on FWS).
ICING AOA Lt illuminates green as soon as 1 horn anti-icing ON. Stall alarm (stick shaker threshold lowered). It can be extinguished manually only by releasing ICING AOA Pb (DC EMER) provided both Horns anti-icing selected OFF.
PTT pb press for 3 sec. -icing will flash on the display if system works correctly (steady if ice detector failure is detected). - FAULT LT illuminate. A-ICING DETECT is displayed steady on the FWS.
[Further: MENU, SEL, STD P/B, IESI display, PWR MGT, APM, STICK PUSHER, FAULT, OFF, TEST, PEC, BOOST]
193
Page 194 (PDF 192)¶
[Continued — ATPCS, EEC, PFD/MFD instrument displays]
Arming conditions: PWR MGT set on TO + ATPCS pb in + both PL >49 + both TQ > 53%(42) / both TQ > 46% (72) ARM green LT on. UPTRIM signal sent to respective eng during ATPCS sequence. Eng power = RTO.
[Further displays: TORQUE Ind display, Trim indicator, LO PITCH, Brake messages, Flaps indicator, NP Ind display, Alert window, TAT-SAT indicator, ELAPSED TIME, Panel with EWD format, ATPCS triggers and cancels, EEC FAULT flashing/steady, OFF, SPEED LIMIT, Primary engine parameters display, FUEL USED Readout, Procedure window, DISPLAY UNIT 3 (DU3), ITT, etc.]
194
Page 195 (PDF 193)¶
[Continued — Landing Gear, Antiskid, Pressurization panels]
Gear position sensed by system I (MFC 1A) ANTISKID Operative if speed >10 kts. Activates when speed >23 kts + 50% diff between wheels (locked wheel protection). Braking action inhibited at touchdown as long as wheel spin up speed <35 kts or 5 sec. (touchdown protection). CAUTION: THE TEST INHIBITS BRAKES OFF Pb released, system deactivated
[Further: LDG GEAR, UNLOCK, Green Lt, NORM, MAN, FAULT, AUTO PRESS, ELV SET, LANDING ELEVATION, DUMP, DESCENT RATE, TEST, CAB PRESS, DITCH, INCREAS, CABIN RATE KNOB, etc.]
195
Page 196 (PDF 194)¶
[Continued — MCDUs, MCP, PL, GA, Emergency parking brake, EFCP, Weather Radar, Cockpit Door, Audio Panels]
MCDUs (Multifunction Control Display Unit) Access to the FMS, MPC, and ACARS (Data Link) when the ACARS is installed. MULTIPURPOSE CONTROL PANEL (MCP) Allows cockpit crew to control the virtual control panel format (VCP) on MFD POWER LEVER (PL) EMER & PARKING BRAKE GA push button when depressed the GA FD mode is selected with: - HDG HOLD lateral mode with the wings level - GA vertical mode HYD AUX PUMP CONTROL (HOT MAIN BAT BUS) - Aux pump stopped 30" after p/b released (MFC supplied) - Aux pump stopped after p/b released (MFC not supplied) IDLE GATE IDLE GATE FAIL activated when the gate does not engage automatically in flight or does not extend automatically on ground In this case the idle gate lever enables manual override in case of failure of the automatic logic - In flight: push - On ground pull (an amber band appears)
[Further: EFCP, ND, WD, Weather Radar Control Panel, Cockpit Door Control Panel, TO CONFIG TEST, EMER AUDIO CANCEL, F/O and CAPT Audio Control Panel, ACARS & MPC Printer, Panel & flood light control, Aileron rudder & stby pitch trims, ATPCS test]
196
Page 197 (PDF 195)¶
[Continued — FGCP controls, AP, YD, CPL, NAV SOURCE, FD modes, VNAV, BaroVNAV, RNP AR]
HDG SEL / VOR / LNAV / IAS / ALT SEL / V/S / VNAV
[Lateral and vertical mode descriptions: HDG SEL, VOR, LNAV, IAS, ALT SEL, ALT, APP, BC, VS, VNAV mode] NAV SOURCE Selector CAPT side / F/O side ALT knob, FD bars ON/OFF switch, CRS 1/2 knobs Pitch wheel to adjust VS or Pitch attitude in basic mode STBY COMPASS HDG knob selects HDG bug on both EHSI and ND
VNAV mode / BaroVNAV / RNP AR 0.3/1 / RNP AR 0.3/0.3 to use FD with associated VNAV path coded in the FMS database. The VNAV mode has to be used with the LNAV mode. NOTE: If VNAV P/B is pressed and VNAV function is not available, a yellow message VNAV INHIB will be generated on FMA
AP pb engages autopilot and yaw damper and disengages only autopilot YD pb engages yaw damper and disengages yaw damper and autopilot if engaged CPL pb permit to couple AP/FD On CAPT or F/O side In CAT 2 (ILS selected on NAV 1&2) - 1200 ft RA: Dual coupling - 800 ft RA: CAT 2 invalid if still in single coupling - 500 ft RA: ILS excess dev activated - 100 ft RA: GS excess dev deactivated
197
Page 198 (PDF 196)¶
[Continued — TAWS, AHRS, ADC, FD displays, ND, MFD, EWD, DU1, DU2, VCP, MFK, ICP]
TAWS / GPWS switch and associated lights: ON: All basic GPWS modes are operative FLAP OVRD: In reduced flaps landing, to inhib the mode 4 alert OFF: All basic GPWS modes inhibited. OFF: light come on FAULT: GPWS FAULT -> some or all GPWS basic modes are lost FAULT: TERR FAULT -> some or all enhanced modes are lost OFF: All enhanced (TCF & TAD) modes inhibited
AHRS switching P/B To select the opposite side AHRS source. When depressed, SYS 2 is illuminated on CAPT side, while CAPT / 2 is illuminated green on [F/O side] The CAPT P/B has priority
ADC switching P/B [Similarly]
STEEP APP P/B (optional) When selected ON, moves the mode 1 threshold, to avoid TAWS triggering in steep slope approach
TAWS visual alert PULL UP [if any TAWS mode is activated] Alert triggered after the GPWS alert in mode 1, 2 and terrain and obstacle awareness modes
[Further: ACARS message, MASTER WARNING, MASTER CAUTION, Display P/B, MFD upper window (ND/SYST/PERF/MAP/MISC/VD), ND page, PFD, FMA, DU1, DU2, VCP, Memo Panel Display, CAPT SWITCHING PWR, AUDIO 1 SEL, ICP, etc.]
198
Page 199 (PDF 197)¶
[Continued — DU4, DU5, F/O displays, switching panels, clocks, loudspeakers, audio]
MFD upper window Displays the different pages selected on the EFCP: - ND page (Navigation Display) - SYST page (System) - PERF page (Performance) - MAP page (airport mapping) - MISC page (in provision) - VD page (Video in provision)
MASTER WARNING / MASTER CAUTION SYST page Different mode selected on the EFCP: - ACW-HYDRAULIC - ENGINE (secondary engine display) - CABIN - AC-DC ELECTRIC
DISPLAY UNIT 4 (DU4) In the normal configuration, with F/O as PM, the MFD format is displayed with the SYST page. FMA 2 and RMA 2 are included in the DU4 functions
Airspeed Indicator (ASI) Flight Mode Annunciator (FMA) Attitude Display Indicator (ADI) Altimeter Vertical Speed Indicator (VSI) CLOCK DISPLAY UNIT 5 (DU5) In the normal configuration, with F/O as PM, the PFD format is displayed.
Navigation Area With the ND on the MFD, the EHSI is displayed on the PFD. With an other page on the MFD, a mini ND is displayed on the PFD.
[Further: ADC switching P/B, AHRS switching P/B, LOUDSPEAKERS VOLUME KNOBS, F/O SWITCHING, ICP (baro setting, DH/MDA), F/O CONSOLE LT, READING LT knob, CONSOLE LT knob, AUDIO 2 SEL]
199
Pages 200-201 (PDF 198-199)¶
[End of Cockpit Panels annex — Preliminary Cockpit Preparation, Oxygen Mask Test, Flight Deck Ventilation, Main Panel, BRK TEMP TEST]
Page 200: Parking/emergency braking accumulator pressure indicator N/W STEERING PRELIMINARY COCKPIT PREPARATION: OXYGEN MASK TEST [Oxygen mask test instructions: INT/RAD SELECTOR, PRESS TO TEST AND RESET PB, RED GRIPS, EMERGENCY KNOB, N/100% Selector] 200
Page 201: FLIGHT DECK VENTILATION ISOLATION EXTRACT AIR FLOW CAUTION: Close only in case of FWD COMPT smoke MAIN PNL - Before the flight, check that all the switch and selector are in the normal position. BITE LOADED magnetic indicator BRK TEMP TEST 201
ANNEX 2. AIR MANAGEMENT SYSTEM (NAMS)¶
Page 202 (PDF 200) — End of Cockpit Panels (continued)¶
[Oxygen mask / preliminary cockpit prep content continues]
Page 203 (PDF 201) — Flight Deck Ventilation Isolation¶
[Flight deck ventilation isolation, Main Panel, BITE LOADED, BRK TEMP TEST] 201
Page 204 (PDF 202) — NAMS Title, Pneumatic System Schematic¶
ANNEX 2. AIR MANAGEMENT SYSTEM (NAMS)
PNEUMATIC SYSTEM The pneumatic system supplies aircraft systems which use pressurized air: These systems are: - Air conditioning - Ventilation - Pressurization - De-icing
SCHEMATIC IASC (Integrated Air System Controller) [Pneumatic system schematic with bleed valves, cross bleed, HP valves, LEAK/OVHT detection loops] 202
Page 205 (PDF 203) — AIR BLEED PANEL¶
AIR BLEED PANEL ENG BLEED Controls the associated ENG 1 or ENG 2 bleed valve. ON (p/b pressed) Associated Bleed Valve solenoids are energized. OFF (p/b released) Associated bleed valve and HP valve are closed.
RAM AIR This is a guarded pb ON (pb pressed) The Emergency Ram Air Ventilation system is running FAULT The IASC reports the ERAV position failure
PACK VALVE ON (pb pressed) Associated PACK valve is open if electrical supply and air pressure are available OFF (pb released) Associated PACK valve is closed. FAULT Comes on when associated PACK failure or associated pack sensors failure occur.
LEAK The MFC turns on the amber LEAK light when a bleed leak is detected on bleed ducting (T loop > 153C). The bleed valve is automatically closed. DO NOT RESET BLEED.
OVHT The IASC turns on the OVHT light in the case of bleed overheating (bleed temperature above 274C). The system automatically closes the associated bleed valve.
X FEED / X VALVE OPEN [Further: ENG 1/2 BLEED, GRD X FEED, ENG/WING DE ICING, CREW/PACK indicators]
203
Page 206 (PDF 204) — MFD Air Conditioning Display¶
[MFD display showing bleed/pack/temp/pressurization data for PAX/CREW + GPU] 204
Page 207 (PDF 205) — Bleed System Status Legend¶
[Bleed valve, X-FEED status display legend table] Item 1: BLEED VALVE ON, OPENED AND ENGINE RUNNING / BLEED VALVE OFF / etc. Items 2-5: Display descriptions for BLEED OFF, FAULT, LEAK, OVHT, X FEED open/closed 205
Page 208 (PDF 206) — Air Conditioning Schematic & Hotel Mode¶
[Full air conditioning schematic: IASC, PACK 1/2, mixing chamber, cargo compartment, outflow valve, RAM AIR, heat exchangers, ACM, water extractor, etc.]
AIR CONDITIONING IN HOTEL MODE On ground, when engine 2 is started in hotel mode: - The right HP bleed valve is opened (air supplied by HP compressor at low engine power) - The cross feed valve is opened - The PACK valves opening sequence delay of 25 sec is controlled by the IASC and supports smooth air pressure into the cabin - Both packs are supplied with air at 38 psi 206
Page 209 (PDF 207) — Air Conditioning in Normal Flight¶
[Air conditioning schematic (repeated)]
AIR CONDITIONING IN NORMAL FLIGHT - Both HP bleed valves are closed (air supplied by LP compressor at high engine power) - The cross feed valve is closed - Each pack is supplied by its dedicated engine with air at 25 psi 207
Page 210 (PDF 208) — Air Conditioning with Bleed Fault¶
[Air conditioning schematic (repeated)]
AIR CONDITIONING IN FLIGHT WITH A BLEED FAULT In case of: - Overtemperature (T>274C) - Leak (T>153C outside the duct) - Overpressure (P>57 psi) The eng bleed valve is closed and the FAULT is triggered on the bleed P/B and on the pack P/B. The other engine supplies the cockpit and cabin ducts through the mixing chamber - HP bleed valves is closed (air supplied by LP compressor at high engine power) - The cross feed valve is closed - One pack is supplied by its dedicated engine with air at 25 psi 208
Page 211 (PDF 209) — Temperature Control, ERAV¶
In normal operation, the crew command the temperature through the IASC AUTO mode, temperature range from +16C to +32C. If both temperature target signals from rotary selectors are invalid, a +24C default temperature is automatically targeted by the IASC. By selecting manual mode the rotary selector control directly the temperature control valve. MANUAL mode, temperature range from +2C to +71C.
An Emergency Ram Air Valve (ERAV) is mounted on the RIGHT fuselage ram air inlet. In case of complete BLEED/PACK fault, the cabin and flight compartments can be supplied with external air by the ERAV, removing the 80 minutes CO2 cabin limitation. 209
Page 212 (PDF 210) — [Diagram page, minimal text]¶
210
Page 213 (PDF 211) — Compartment Temperature, PACK, Recirculation, ERAV¶
Compartment Temperature indication by the VENTS. PACK pushbutton: FAULT (FWS "AIR PACK 1/2"): - PACK inlet air pressure sensor out of range - Both PACK inlet temperature sensors (PITS) out of range - Air Cycle Machine compressor outlet overheat (CDTS > 232C) Note: If CDTS > 160C, RARV is fully opened. If CDTS > 190C, the airflow is limited by 60% of the targeted airflow. - ACM turbine is frozen - PACK outlet OVHT (MIXTS > 92C) - PACK inlet OVHT (PITS > 274C) - PACK overflow (airflow > 13% of flow target) - PACK failure - IASC Channel A (resp. B) leads to left (resp. right) PACK failure
[Further panels: RECIRC FAN 1/2, COMPT TEMP, FLT COMPT TEMP SEL, CARGO TEMP SEL, COMPT SEL, FLOW HIGH, RAM AIR, PACK, ENG 1/2 BLEED, AIR BLEED, ENG/WING DE ICING, Emergency Ram Air Valve control]
211
Page 214 (PDF 212) — MFD Air Conditioning Display Variants¶
[MFD display examples: 8 different configurations showing PAX/CREW, PACK, TEMP, AP PSI, CAB ALT, CAB RATE] 212
Page 215 (PDF 213) — Air Conditioning Display Legend¶
[Legend tables for display items] Item 1: PACK ON/OFF/FAULT/STBY Item 2: RECIRC ON/OFF/FAULT Item 3: [Combined pack/recirc status] Item 4: EXHAUST/OVBD/FAULT/FULL OPEN/FULL CLOSE Item 5: OVBD VALVE AUTO/MAN Item 6: OVHT Item 7: Temperature display (valid/invalid) Item 8: AIR HIGH FLOW 213
Page 216 (PDF 214) — Avionics Ventilation¶
AVIONICS VENTILATION ATA 21 The ventilation system provides cooling through ambient air extraction to limit the internal operating temperature of the electronic equipment.
SCHEMATIC [Ventilation schematic: VENTILATION TEMP SENSOR, FLT CMPT, EXTRACT AIR FLOW VALVE, FWD CARGO SMOKE DETECTOR, LAVATORY SMOKE DETECTOR, AFT CARGO SMOKE DETECTOR, AVIONICS VENT EXTRACT FAN, U/F VENTILATION VALVE, OVBD VALVE]
AVIONICS VENT PANEL EXHAUST MODE NORM - On ground, ENG 1 off: extract fan on. OVBD valve full open, U/F valve closed. - Air/ground, ENG 1 on: extract fan operates. OVBD valve closed. U/F valve opened OVBD extract fan off, OVBD valve partially opened (in flight only). U/F valve closed FAULT fan failure/overheat (fan inhibited for 120 s. after eng start or after a GPU power on. FWS) OVBD valve [further controls]
Page 217 (PDF 215) — Pressurization¶
PRESSURISATION The pressurization system is based on an enhanced cabin pressure program with improved cabin comfort automatically controlled at -300 ft/min and +500 ft/min. It is managed by the IASC using data from the FMS and the ADCs. This new system has one electrical driven outflow valve located in the aft left fuselage. The system uses landing elevation from the FMS or can be manually selected by the crew.
[Pressurization schematic with altitude profile showing 6 phases: Takeoff, Pre-pressurization, Climb, Cruise, Descent, Ground Depressurization]
AUTO MODE: FMS -> IASC Management -> Outflow valve / ADC MANUAL MODE: Manual controller knob -> IASC Management -> Outflow valve
CABIN PRESS / OUTFLOW / MODE SEL / DEC 215
Page 218 (PDF 216) — Cabin Pressure Indicators¶
CABIN PRESSURE INDICATORS Pressure control mode: AUTO or MAN MFD display showing: DIFF - Differential pressure: max +6.35/-0.5 ALT - Cabin alt: based on 29.92 in.hg (1013.2 Hpa) RATE - Cabin rate of climb 216
Page 219 (PDF 217) — Intentionally Blank¶
INTENTIONALLY BLANK PAGE 217
Page 220 (PDF 218) — MFD Cabin Press / EWD Display¶
[MFD display with PWR MGT, LO PITCH, PRKG BRK, PROP BRK, ITT, SAT, FUEL, GW, etc. and CABIN PRESS panel: LANDING ELEV, SOURCE SEL, MAN SET, DUMP, OUTFLOW, MODE SEL, DITCH, DEC] 218
Page 221 (PDF 219) — Auto Press Panel¶
AUTO PRESS PANEL SOURCE SEL p/b enable to select landing elevation value source. NO light -> Landing elevation value comes from the FMS MAN light -> Landing elevation value is set manually with MAN SET knob DUMP p/b enables dump function to depressurize the cabin in case of emergency. DITCH p/b enables ditching to seal the aircraft in case of ditching. MODE SEL p/b enable/disable MAN mode for cabin pressure control. OUTFLOW MANAGEMENT STATUS: NORM is lit in the event of/or a combination of: IASC Channel B failure / Stepper motor (OFV) failure / etc. BACKUP is lit in the event of/or a combination of: IASC Channel A failure / DC motor (OFV) failure / etc.
[CABIN PRESS panel: LANDING ELEVATION, SOURCE SEL, MAN SET, DUMP, DITCH, MODE SEL, FAULT, MAN, INC/DEC, CAB ALT, OUTFLOW NORM/BCKUP] 219
Page 222 (PDF 220) — Cabin Press Display Legend¶
[Display legend for Cabin Pressure indications] Items 1-3: AP NOMINAL/PRE-ALERTING/ALERTING/INVALID AP Items 4-5: RATE OF CLIMB / DESCENT / INVALID RATE
[Cabin press status display legend: AUTO/MAN PRESS, CAB ALT, FAULT, TARGET, INVALID, PRE-ALERTING, ALERTING, etc.] 220
ANNEX 3. 72-600F FREIGHTER¶
Page 223 (PDF 221) — Freighter Title, Aircraft Dimensions, Cargo Door¶
ANNEX 3: 72-600F FREIGHTER
AIRCRAFT GENERAL FCOM DSC 20, 25, 33, 38, 52
AIRCRAFT DIMENSIONS AND CATEGORIES
CARGO DOOR DIMENSIONS FWD CARGO DOOR - 110 deg 1.78 m x 2.93 m (approx.)
CARGO COMPARTMENT CLASSIFICATION For the ATR 72-600F Freighter, the cargo compartment classification is: Class E Class E cargo compartment is one on airplanes used only for the carriage of cargo and in which: (1) There is a separate approved smoke or fire detector system to give warning at the pilot station; (2) There are means to shut off the ventilating airflow to, or within, the compartment, and the controls for these means are accessible to the flight crew in the crew compartment; (3) There are means to exclude hazardous quantities of smoke, flames, or noxious gases, from the flight crew compartment; and (4) The required crew emergency exits are accessible under any cargo loading condition. 221
Page 224 (PDF 222) — Doors Location¶
DOORS LOCATION [Diagram] crew door / Aft cargo door / Aft avionics compartment door / Large cargo door / Pilot emergency hatch / Forward avionics access hatch ATA 52 222
Page 225 (PDF 223) — Cargo Door Panel, Cargo Load Light¶
CARGO DOOR PANEL ARMED light: Selector armed green light is ON, when actuator selection switch working conditions are met: cover panel opened / door unlocked by operating handle: all hooks are disengaged and FWD latchlock is unfastened LCHD light (Latched light): blue light is ON when all door hooks and latch locks are fully engaged GND HDL light (Ground handling light): Ground handling bus ON BAT red light is ON when ground handling bus is directly supplied by HOT main bat bus This red light is ON when: The refueling panel is open / The cargo door control panel is open
Actuator selection switch: - Normal mode: used to operate the door (OPEN or CLOSE) when the CARGO DOOR ARMED green light is on - Back-up mode: used to operate the door (OPEN or CLOSE) In Back-up mode, ARMED and LCHD lights of the door control panel are INOPERATIVE CAUTION: Cargo door actuator is not automatically stopped when the cargo door reaches the completely open position in back-up mode: Take care to immediately release selector when door is fully opened.
Entrance light push button CARGO LOAD LIGHT switch Panel cover switch FWD CARGO DOOR BACK-UP switch (NORM/ARM) CAUTION: LCD actuator is supplied by the blue hydraulic system through a control valve located downstream of the NWS. On ground, LCD actuation is possible when the NWS (Nose Wheel Steering) control switch is on "ON" position only.
[Cargo door panel diagram: CARGO, OFF, SVCE BUS, FWD CARGO DOOR, BACK-UP, NORM, LIGHTS, ENTRANCE PUSH TO LIGHT, etc.] 223
Page 226 (PDF 224) — Cargo Panel / Door Status¶
CARGO PANEL ATA 52 CREW OK and AFT OK - Light on when SW TEST depressed and check microswitches operation DOORS: CREW / FWD COMPT / AFT / EMER / UNLK SW TEST - Tests continuity of microswitch system (on ground, doors opened) CREW UNLK - At least 1 micro switch is opened [Further: FWD COMPT, DOOR indicators, BLEED, PACK, TEMP, CAB PRESS displays] 224
Page 227 (PDF 225) — Emergency Equipment / Oxygen (Freighter)¶
EMERGENCY EQUIPMENT FCOM DSC 33, 25, 26, 35
OXYGEN SCHEMATIC OXYGEN MAIN SUPPLY CREW HP LO PR OFF ATA 35
OXYGEN PANEL AND DISPLAY MAIN SUPPLY pb in: crew supply only HP INDICATOR oxygen bottle pressure. Red arc 0 to 85 psi / Green arc 85 to 2025 psi. If below 1400 psi, use table LO PR supply below 50 psi. OXY on FWS
MFD OXY SUPPLY display: CREW / LO PR / MAIN SUPPLY OFF / MAIN SUPPLY ON / LOW PRESSURE DETECTED 225
Page 228 (PDF 226) — Fire Protection (Freighter)¶
FIRE PROTECTION FCOM DSC 26 ELECTRICAL, FWD AND AFT SMOKE DETECTION ATA 26
[Smoke detection panel: MASTER, ELEC SMK, FWD SMK, AFT SMK, SMK]
SMOKE DETECTORS PANEL SMK TEST Tests the smoke detectors operation ATA 26
CARGO VENT AIRFLOW P/B The CARGO VENT AIRFLOW p/b controls the Cargo Shut Off Valve. AIRFLOW (pb pressed in) Normal use. The cargo shut-off valve is open and allows the conditioned air distribution to the cargo compartment. OFF (pb released) The cargo shut-off valve is closed. The air distribution to the cargo compartment is stopped. OFF white light comes on. SMK If any of the detectors detect smoke the associated SMK light comes on red. The respective indications on the SD cabin and on the EWD are also triggered. The extraction fan is not automatically shut down in the event of aft cargo compartment smoke detection, or after a "Smoke Detector Test" performed on ground. 226
Page 229 (PDF 227) — SD Cabin (Freighter)¶
SD CABIN ELEC SM / FWD SMK / AFT SMK ATA 26 Avionics smoke / Forward cargo compartment smoke / Aft cargo compartment smoke 227
Page 230 (PDF 228) — Hydraulic System (Freighter)¶
HYDRAULIC SYSTEM FCOM DSC 29 SCHEMATIC ATA 29
The aircraft has two hydraulic systems, designated blue and green. Each system is pressurized by an electric pump, supplied by ACW power. The blue system is also provided with an auxiliary pump, supplied by DC power (automatic or manual mode).
Total fluid volume: normal filling: 9.6 l minimum filling: 9.35 l alert level: 2.5 l
[Hydraulic schematic: RETURN, OVHT LO LVL, LO PR, AUX PUMP, NOSE WHEEL STEERING, LANDING GEAR, FLAPS, SPOILERS, PROPELLER BRAKE, FWD CARGO DOOR ACTUATOR, BRAKING, EMERG AND PARKING, NORMAL]
Large cargo door operated by hydraulic Actuator supplied by blue system. CAUTION: On ground, LCD actuation is possible when the NWS (Nose Wheel Steering) control switch is on "ON" position only. 228
Page 231 (PDF 229) — Freighter Door Panel / Smoke / Calls / Oxygen¶
[Continuation of Freighter-specific panels]
DOORS: CREW OK and AFT OK - Light on when SW TEST depressed and check microswitches operation SW TEST - Tests continuity of microswitch system (on ground, doors opened) CREW / FWD COMPT / UNLK / UNLK / CARGO VENT AIRFLOW P/B SMOKE DETECTORS - CREW / AFT / SW TEST SMK - If any of the detectors detect smoke the associated SM light comes on red. EWD CALLS MECH RESET OXYGEN MAIN SUPPLY / CREW / HP INDICATOR / LO PR CALLS PANEL MECH
On 72-600F: No signs and Emer Exit Light control On 72-600F: No Extract Air Flow lever
229
ANNEX 4. ABBREVIATIONS¶
Page 233 (PDF 231)¶
ANNEX 4. ABBREVIATIONS
A AAS Anti-icing Advisory System AC Alternating Current A/C Aircraft ACARS ARINC Communication Addressing and Reporting System AC BTC AC Bus Tie Contactor AC BTR AC Bus Tie Relay ACM Air Cycle Machine ACS Air Conditioning System ACU Air Conditioning Unit ACW Alternating Current Wild Frequency ADC Air Data Computer ADF Automatic Direction Finder ADI Attitude Director Indicator ADN Avionic Data Network ADS Air Data System AFCS Automatic Flight Control System AFDX Avionic Full Duplex A/FEATH Auto Feathering AFCA Auto Flight Control Application AFT Rear Part AFU Auto Feather Unit AGB Accessory Gear Box AHRS Attitude and Heading Reference System AHRU Attitude and Heading Reference Unit AIL Aileron ALT Altitude ALTM Altimeter ALTN Alternate AMP Ampere AOA Angle of Attack AP Auto-Pilot APP Approach APU Auxiliary Power Unit APAU AutoPilot Actuator Unit ARINC Aeronautical Radio INCorporated A 429 ARINC 429 ARM Armed ASI Air Speed indicator ASYM Asymmetry ATC Air Traffic Control ATPCS Automatic Take off Power Control System ATT Attitude ATTND Attendant AUTO Automatic AUX Auxiliary AVAIL Available
B BARO Barometric BaroVNAV Barometric Vertical NAVigation BAS Bleed Air System BAT Battery BC Back Course BCKV Bulkhead Check Valve BITE Built in Test Equipment BPCU Bus Power Control Unit BPU Battery Protection Unit BRG Bearing BRK Brake B-RNAV Basic Area Navigation BRT Bright BSPS Bleed Switching Pressure Sensor BTC Bus Tie Contactor BTR Bus Tie Relay
C CAB Cabin CAC Core Avionic Cabinet CAPT Captain CAS Crew Alerting System CAT Category C/B Circuit Breaker CBIT Continuous Built-In Test CBV or X-Valve Cross Bleed Valve CDI Course Deviation Indicator CDLS Cockpit Door Locking System CDTS Compressor Discharge Temperature Sensor CHAN Channel CHC Charge Contactor CL Condition Lever CLA Condition Lever Angle CLB Climb CLR Clear CMA Centralized Maintenance Application CMD Command CMS Cabin Management System CMPTR Computer CMU Communication Management Unit (ACARS) COM Communication COMPT Compartment CONFIG Configuration CPCS Cabin Pressure Control System CPL Auto Pilot Coupling CPM Core Processing Module CRC Continuous Repetitive Chime CRS Course CRZ Cruise CTL Control CVR Cockpit Voice Recorder
D DCA Data Concentration Application DELTA P Differential Pressure DEV Deviation DFDR Digital Flight Data Recorder DGR Degraded DH Decision Height DHX Dual Heat eXchanger DIFF Differential DISCH Discharge DIM Light Dimmer DIST Distance DLK Data LinK DME Distance Measuring Equipment DMU Data Management Unit DN Down DSO Discrete Signal Output DSPL Display DU Display Unit
E EBIT Event Built-In Test ECS Environmental Control System EEC Engine Electronic Control EFCP EFis Control Panel EFIS Electronic Flight Instrument System EHSI Electronic Horizontal Situation Indicator EHV Electro Hydraulic Valve ELEC Electrical ELV Elevation EMER Emergency ENG Engine EQPT Equipment ERACKV Emergency Ram Air Check Valve ERAV Emergency Ram Air Valve ESS Essential ETOPS Extended Twin Operations EWD Engine & Warning Display EXT Exterior, External
F F Fahrenheit FAIL Failed, Failure FAP Flight Attendant Panel FC Full Closed FCOC Fuel Cooled Oil Cooler FCS Flow Control System FCU Fuel Control Unit FCV Flow Control Valve FD Flight Director FDA Flight Data Application FDAU Flight Data Acquisition Unit FEATH, FTR Feathered, Feathering FF Fuel Flow FGC Flight Guidance Computer FGCP Flight Guidance and Control Panel FGS Flight Guidance System FI Flight Idle FLT Flight FMA Flight Management Application FMA Flight Modes Annunciators FMS Flight Management System F/O First Officer FO Full Open FOS Flight Operations Software FSV Flow Sensor Venturi FT Foot, Feet FU Fuel Used FWD Forward FWS Flight Warning System
G GA Go Around GCU Generator Control Unit GEN Generator GI Ground Idle GND Ground GPS Global Positioning System GPU Ground Power Unit GRD Ground G/S Glide Slope GSPD Ground Speed
H HBV Handling Bleed Valve HDG Heading HF High Frequency HI High HLD Hold HMU Hydromechanical Unit HP High Pressure HPV High Pressure Valve HSI Horizontal Situation Indicator HTG Heating HYD Hydraulic
I IAS Indicated Air Speed IASC Integrated Air System Controller ICP Index Control Panel IDT Ident IESI Integrated Electronic Standby Instrument IGN Ignition ILS Instrument Landing System IMA Integrated Modular Avionics IND Indicator IN/HG Inches of Mercury INHI Inhibit INOP Inoperative INST Instrument INT Interphone INV Inverter IOM Input Output Module ISOL Isolation ITT Inter Turbine Temperature
J JK [blank]
K KHZ Kilo-Hertz KT Knot
L LAT Lateral LAV Lavatory LB Pound LDG Landing L/G Landing Gear LH Left Hand LMU Light Management Unit LNAV Lateral Navigation LO Low LOC Localizer LO-PR Low Pressure LP Low Pressure LPV Localizer Performance with Vertical guidance LRU Line Replaceable Unit LT Light LVL Level
M MAN Manual MAX Maximum MAP Mapping MB Millibar MC Master Caution MCDU Multifunction Control Display Unit MCP Multifunction Control Panel MCT Maximum Continuous MECH Mechanic MFC Multi Function Computer MFCU Mechanical Fuel Control Unit MFD Multi Function Display MGMT Management MHX Main Heat eXchanger MHZ Megahertz MIC Microphone MLG Main Landing Gear MIN Minimum MIP Main Instrument Panel MISC Miscellaneous MIXTS MIX manifold Temperature Sensor MKR Marker MLW Maximum Landing Weight MM Millimeter MMO Maximum Operating Mach MOD Modification MPC Multi Purpose Computer MPU Micro Processor Unit MSG Messages MSN Manufacturer Serial Number MTOW Maximum Take off Weight MW Master Warning MZFW Maximum Zero Fuel Weight
N NAC Nacelle NAMS New Air Management System NAV Navigation ND Navigation Display NDB Non Directional Beacon NEG Negative NH High Pressure Spool Rotation Speed NIL Nothing, No Object NL Low Pressure Spool Rotation Speed NM Nautical Mile NORM Normal NP Propeller Rotation Speed NVM Non-Volatile Memory N/W Nose Wheel NWS Nose Wheel Steering
O OAT Outside Air Temperature OOR Out Of Range OVBD Overboard OVERTEMP Overtemperature OVHT OVerHeaT OVRD Override OXY Oxygen
P PA Passenger Address PACK Air Conditioning Unit (= ACU) PB Push Button PBA Push Button Annunciator PBIT Power Built-in Test PDPS Pack Discharge Pressure Sensor PDTS Pack Discharge Temperature Sensor PEC Propeller Electronic Control PED Pedestal PERF Performance PFD Primary Flight Display PHX Primary Heat eXchanger PIFS Pack Inlet Flow Sensor PIPS Pack Inlet Pressure Sensor PITS Pack Inlet Temperature Sensor PIU Propeller Interface Unit PLA Plenum PL Power Lever Angle PNL Panel POS Position P-RNAV Precision Area Navigation PRESS Pressurization, Pressure PRIM Primary PRKG Parking PROP Propeller PRSOV Pressure Regulating Shut-Off Valve PSI Pound per Square Inch PSU Pax Service Unit PT Point PTS Pack Temperature Sensor PT (TCAS) Proximity traffic PTB Pitch Trim Box PTT Push To Talk, Push To Test PTW Pitch Thumb Wheel (same as PW) PVM Propeller Valve Module PWR Power PW Pitch Wheel (same as PTW)
Page 236 (PDF 234) — Abbreviations Q-Z¶
Q QAR Quick Access Recorder QT Quart QTY Quantity
R RA (TCAS) Resolution Advisory RA Radio Altitude RAD/ALT Radio Altitude RAD/INT Radio/Interphone RARV Ram Air Regulating Valve RCAU Remote Control Audio Unit RCDR Recorder RCL Recall RCU Releasable Centering Unit RECIRC Recirculation REV Reverse RFAN Recirculation Fan RGA Reserve Go-Around RGB Reduction Gear Box RH Right Hand RHX - REH/RCO ReHeater/Condenser RLY Relay RMA Radio Management Application RMI Radio Magnetic Indicator RMS Radio Management System RNP Required Navigation Performance RNP AR RNP with Authorization Required RPM Revolution Per Minute RTO Reserve Take-Off RUD Rudder
S SAT Static Air Temperature SBY Stand By SC Single Chime, Starter Contactor SD System Display SEL Selector SGL Single SGU Symbol Generator Unit SMK Smoke SMKG Smoking S/O (SO) Shut Off SOV Shut Off Valve SPD Speed SPLR Spoiler SPLY Supply STBY Stand By STRG Steering SSFDR Solid State Flight Data Recorder SURV Surveillance SVCE Service SW Switch (Microswitch) SWM gateway and SWitch Module SYS System
T TA (TCAS) Traffic Advisory TAD Terrain Awareness Display TAS True Air Speed TAT Total Air Temperature TAWS Terrain Awareness Warning System TCF Terrain Clearance Floor TCS Touch Control Steering TCV Temperature Control Valve TEMP Temperature TEMP SEL TEMPerature SELector TGT Target TK Tank TLU Travel Limiting Unit TM Torque Motor T/O (TO) Take off TOW Take off weight TQ Torque TRU Transformer Rectifier Unit TTG Time To Go
U U/F Underfloor UHF Ultra High Frequency UNCPL Uncouple UNDV Undervoltage UNLK Unlock UTLY Utility
V VC Calibrated Airspeed VCP Virtual Control Panel VCS Vapor Cycle System VENT Ventilation VENTS VENtilated Temperature Sensor VERT Vertical VHF Very High Frequency VID Video VMO Maximum Operating Speed VNAV Vertical Navigation VOR VHF OMNI Directional Range VSI Vertical Speed Indicator
W WARN Warning WE Water Extractor WOW Weight On Wheel WS Water Sprayer
X XFEED Cross feed XER Transfer
Y YD Yaw Damper YDAU Yaw Damper Actuator Unit
Z ZA Aircraft Altitude ZCTH Theoretical Cabin Altitude ZFW Zero Fuel Weight ZP Pressure Altitude ZRA Radio Altimeter Altitude
Page 237 (PDF 235) — Colophon¶
Dear Readers, Every effort has been made to ensure document quality. However please do not hesitate to share your comments and information with us by using the following address: ops.support@atr-aircraft.com Yours faithfully, Your ATR Training and Flight Operations support team.
Page 238 (PDF 236) — Copyright¶
ATR. 2024. All rights reserved.
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