ATR 42-300 Handling Manual Download

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ATR 42-300

AIRCRAFT HANDLING MANUAL

AIRCRAFT LIMITATIONS & FEATURES

Config.

Configuration Info

A/C REG

Mass Kg

Index

Aircraft prepared for Cargo-

services. Crew 2/0.

For additional crew see B.

LY-ETM

10291

-50

For additional crew:

Observer seat Kg/Index

No.

Index

+85

-5.0

Version vs. max

REG

MTM

MTOM

MLM

MZFW

MFM*

Pax. layout

LY-ETM

17.070

16.900

16.400

15.540

10.452

N/A

*MFM – minimum flight mass

!!! FOR EMPTY FERRY FLIGHTS AND/OR

LIGHT LOADED FLIGHTS BALLAST WEIGHTS

ARE NEEDED TO BALANCE THE AIRCRAFT !!!!

!!! TO PROTECT FROM TIP UP DURING

LOADING/UNLOADING SECTION “F”

MUST BE TOTALLY UNLOADED BEFORE

ANY FREIGHT HANDLING IN OTHER
SECTIONS !!!

Summary of Contents for 42-300

Page 1: ...al 1 1 List of aircraft 1 2 Exterior dimensions 1 3 Ground clearance 1 4 Weight and balance definitions 2 Aircraft limitations and features 2 1 Certificate limitations 2 1 1 Aircraft gross weight limitations 2 1 2 Performance operating weight 2 2 Standardized 3 Aircraft servicing 4 Loading 5 Form ...

Page 2: ...ATR 42 300 AIRCRAFT HANDLING MANUAL GENERAL 1 GENERAL 1 1 LIST OF AIRCRAFT This manual is effective for the following aircraft Model Registration number Configuration ATR 42 LY ETM Cargo ...

Page 3: ...eight plus take off fuel TOW 8 DEADLOAD WEIGHT Zero fuel weight DLW 9 MAXIMUM TAKE OFF Maximum weight at brake release as limited WEIGHT MTOW by aircraft MTOW strength and airworthiness requirements 10 MAXIMUM ZERO FUEL Maximum weight for landing as limited by WEIGHT MZFW aircraft MLDW strength and airworthiness requirements 11 MAXIMUM ZERO FUEL Maximum weight allowed before usable fuel WEIGHT MZF...

Page 4: ...ndex of deadload weight DLI The CG of aircraft dead load weight expressed with DLI index 22 MAC of Zero Fuel Weight The CG of aircraft zero fuel weight MACZFW expressed with MAC 23 MAC of take off weight The CG of aircraft take off weight expressed MACTOW with MAC 24 MAC of dead load weight The CG of aircraft dead load weight MACDLW expressed with MAC 25 Take off fuel The amount of fuel on board l...

Page 5: ...0 16400 2 1 2 PERFORMANCE OPERATING WEIGHT To comply with the performance requirements of the aircraft manufacturer the maximum allowable take off and landing weights may be less than structural limits The maximum allowable weight for that flight that must not exceed the least of the following weights Maximum allowable takeoff weight for the runway intended to be used including corrections for alt...

Page 6: ...0 27 3401 3800 9 451 500 21 10 1 12 22 30 3801 4200 10 501 550 23 11 1 13 24 33 4201 4500 11 551 600 25 12 1 14 28 37 601 650 27 12 1 15 28 40 651 700 30 13 2 17 31 43 701 750 32 14 2 18 33 46 751 800 34 15 2 19 35 49 801 850 36 16 2 20 37 52 851 900 38 17 2 21 39 55 901 950 40 18 2 23 41 58 951 1000 42 19 2 24 43 61 1001 1050 44 20 2 25 45 64 1051 1100 46 21 3 26 47 67 1101 1150 48 21 3 27 49 70 ...

Page 7: ...itional crew B Observer seat Kg Index No Kg Index 1 85 5 0 Version vs max REG MTM MTOM MLM MZFW MFM Pax layout LY ETM 17 070 16 900 16 400 15 540 10 452 N A MFM minimum flight mass FOR EMPTY FERRY FLIGHTS AND OR LIGHT LOADED FLIGHTS BALLAST WEIGHTS ARE NEEDED TO BALANCE THE AIRCRAFT TO PROTECT FROM TIP UP DURING LOADING UNLOADING SECTION F MUST BE TOTALLY UNLOADED BEFORE ANY FREIGHT HANDLING IN OT...

Page 8: ...ATR 42 300 AIRCRAFT HANDLING MANUAL AIRCRAFT LIMITATIONS FEATURES 2 3 STANDARDIZED WEIGHT PER CREW Specification Standard weight KG Charter flight Definition of age Crew Cockpit crew 90 ...

Page 9: ...ation exceeded The balance at MACZFW and MACTOW remains within the allowed limits All the LMC data on the loadsheet is completed b Useable fuel only Issue the new loadsheet when change in fuel figures ATR 42 300 AIRCRAFT HANDLING MANUAL AIRCRAFT SERVICING 3 AIRCRAFT SERVICING 3 1 ARRANGEMENT OF GROUND HANDLING EQUIPMENT This diagram shows an example of the arrangement of ground handling equipment ...

Page 10: ...ANDLING MANUAL AIRCRAFT SERVICING 3 2 SERVICING POINTS This diagram shows the locations of the servicing points of the ATR 42 300 aircraft from a top view NOTE A Air conditioning E Electrical F Fuel H Hydraulic O Oil Engine ...

Page 11: ...26 v despite the full load load shedding the GPU MUST BE CONSIDERED AS COMPLETELY UNUSABLE If DC EXT PWR voltage on maintenance panel is above 26 v the DC GPU may be used to maintain aircraft batteries charge whilst using all other ground services normally cargo door refueling cabin lighting etc WARNINGS Do not disconnect external power while the GPU is supplying power to the aircraft Failure to o...

Page 12: ...re extinguisher of suitable size and type is mounted externally on the GPU or is available in close vicinity to the GPU The fire extinguisher shall be sealed and date labeled This is an illustration of the AC External Power receptacle panel 1 Nose Landing Gear Service Light Switch allows operation of the service light in nose gear bay 2 AC Power not used light white is ON when AC external power is...

Page 13: ...raft and DC external power contactor is opened 3 Interphone Jack used by ground mechanic to connect a headset to communicate with crew 4 Pilot call button when depressed sends a call aural and visual to the cockpit Mechanic call light illuminates on the overhead panel The illustration below shows MAIN ELEC PWR panel 1 Battery toggle switch ...

Page 14: ...n the external power access door Connect the external power cable connector to the DC external power receptacle Make sure the cable connector is fully engaged 4 Switch on the GPU electrically and check that The white DC Connected light comes on 3 3 2 DISCONNECTING EXTERNAL POWER FLIGHT DECK MANNED Before disconnecting external power according to the procedure below you must be aware of the WARNING...

Page 15: ...ght is on If neither light is on call maintenance or the Commander for assistance 6 Place the BAT toggle switch in the ON position 7 Push the EXT PWR pushbutton and check that the switch light comes on 3 3 4 DISCONNECTING EXTERNAL POWER FLIGHT DECK UNMANNED Before disconnecting external power according to the procedure below you must be aware of the WARNINGS and CAUTIONS as described in 3 3 EXTERN...

Page 16: ...lug type door with a net opening of 64 cm 25 in wide without hand rail s and 1 73 m 68 in high The mechanism is essentially composed of a handle a lifting cam and one locking shoot bolt placed on the rear part of the door The door mechanism is driven by an external handle allowing the door to be operated from outside only of the aircraft ...

Page 17: ...ched by five shoot bolts which are locked by two latch locks A pressure vent door is operated simultaneously with the latch locks The door mechanism is driven by both internal and external handles allowing the door to be operated from inside or outside of the aircraft The door is equipped with a hold open device that engages the external handle when the door is open Two microswitches installed on ...

Page 18: ...m 3 5 3 SERVICE DOOR Right side The service door is an outward opening non plug type door with a net opening of 69 cm 27 wide and 1 27 m 50 high Opened position is forward This door is blocked closed and can be operated for maintenance purpose only ATR 42 300 AIRCRAFT HANDLING MANUAL AIRCRAFT SERVICING 3 5 4 INTERNAL DOORS A smoke barrier door separates the cargo compartment and the cockpit Four s...

Page 19: ...ndications provided on the external panel access to controls into cockpit not required Back up when normal mode not available back up function can be armed through a switch on internal panel Then door is operated via external panel controls indications are not available in back up mode External marking close to the door and panel reports instructions and caution information for the operator See sc...

Page 20: ...ATR 42 300 AIRCRAFT HANDLING MANUAL AIRCRAFT SERVICING ...

Page 21: ...ATR 42 300 AIRCRAFT HANDLING MANUAL AIRCRAFT SERVICING ...

Page 22: ...aximum localized load height of 64 inches and a maximum pallet side height of 55 11 inches Bulk freight may also be loaded behind the designated pallet area or in the absence of any pallet s The compartment floor structure is capable of supporting 408 pounds per foot and all floor panels are capable of carrying a surface distributed load of 82 pounds per square foot without appreciable deformation...

Page 23: ...s 88 x 108 Pallet 3 637 62 Lbs 88 x 54 Pallet 1818 00 Lbs Forward Crash Net 19 290 45 Lbs Forward Transverse Crash Net 3 086 47 Lbs Intermediate Transverse Crash Net 3 527 39 Lbs WARNING Good judgment must be used to position piercing or penetrating type cargo Load cargo of a piercing or penetrating nature at least 4 feet aft of compressible cargo density lower than 15 6 lb cu feet To prevent pene...

Page 24: ...t points must be translated for the same length respect to the forward limit ATR 42 300 AIRCRAFT HANDLING MANUAL LOADING 4 4 PACKAGE SIZE DIMENSIONS The maximum dimensions of the package which can be loaded in cargo compartment are given in following tables Dimensions are given in centimeters NOTE Lengths are determined for packages in full contact with compartment floor during loading operations ...

Page 25: ...Cargo Compartment Large Cargo Door ...

Page 26: ...ATR 42 300 AIRCRAFT HANDLING MANUAL LOADING 4 5 CARGO COMPARTMENT FLOOR CAPABILITY The dimensions maximum available width and height for the loads are presented in the figure 4 1 Figure 4 1 ...

Page 27: ...d above the water mark or red line painted in the cargo compartment of the ATR This water mark is located at 64 inches above the floor and provides adequate clearance for the smoke detectors and lights to function It is prohibited to carry freight between the forward 9G crash net and the cockpit partition Cargo of a piercing or penetrating nature must be loaded at least 4 feet aft of compressible ...

Page 28: ...olume30 0 m 1 057 cu ft Bulk available volume 11 9 m 421 cu ft Figure 4 2 The ATR has three sections to carry one full cookie sheet in the two aft sections and 1 cookie sheets in the forward section Figure 4 3 The ATR bulk freight configuration 9G Bulkhead Transverse Nets Aft Door Net ...

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Page 32: ... 4 53 1 38 4 35 1 33 E 25 43 7 75 25 14 7 66 24 78 7 55 F 10 26 3 13 10 03 3 06 10 10 3 08 G 12 34 3 76 12 09 3 69 12 07 3 68 H 22 99 7 01 22 69 6 92 22 34 6 81 α 1 515 1 445 0 921 J 12 9 Ft 3 93 m K 5 Ft 6 3 in 1 683 m L 28 Ft 9 7 in 8 781 m M 74 Ft 4 5 in 22 670 m N 23 Ft 11 8 in 7 31 m P 13 Ft 5 4 in 4 100 m R 26 Ft 6 9 in 8 100 m S 80 Ft 7 4 in 24 572 m AA R R R R R R R R R R R R R R R R R R R...

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Page 41: ...tion is forward Door operation can be performed manually from inside or outside of the airplane refer to 1 07 30 INTERNAL DOORS Smoke doors separate the forward cargo compartment from the cockpit Four safety pins are provided two on each side in order to remove the doors in case of emergency AA AviationLearning net 01 07 2018 REV 1 These notes are not revised after issue For Training Purposes Only...

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Page 45: ...tion is forward Door operation can be performed manually from inside or outside of the airplane refer to 1 07 30 INTERNAL DOORS Smoke doors separate the forward cargo compartment from the cockpit Four safety pins are provided two on each side in order to remove the doors in case of emergency AA AviationLearning net 01 07 2018 REV 1 These notes are not revised after issue For Training Purposes Only...

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Page 50: ...ver is open Ground Handling Bus ON BAT red light Is ON when Ground Handling bus is directly supplied by Hot main Bat Bus Note This light shows that the main battery is emptying even if the BAT toggle switch is in OFF position visible even when the panel cover is closed Cargo Bay light switch Allows illumination of the cargo bay light from outside Actuator Selection Switch Is used to operate the do...

Page 51: ...D Use the actuator selection garded switch located in the internal operating panel CLOSING D Use the actuator selection garded switch located in the internal operating panel Note The locking and latching are not possible from inside However the latching position can be inspected from inside through the view ports located on the bottom part of the door FORWARD AVIONICS COMPARTMENT ACCESS HATCH An i...

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Page 61: ...system activation light will be supplied by DC EMER BUS If this source fails the batteries will be utilized automatically In case of flight with DC EMER BUS only the cockpit lighting is restricted to RH DOME light with the possibility to switch it off LH three lights located below the glareshield Overhead panel light illumination the pedestal One light is provided in the toilet illuminating when a...

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Page 63: ... 3 EMER EXIT LIGHT sélector ON Emergency light s illuminate ARM Normal selector position in operation Emergency lights will Illuminate if DC EMER BUS voltage is below 18V or if the two generators are lost Extinguish if DC EMER BUS voltage is over 20V and at least one generator running R Note With GPU power AVAIL and selected on non engine running the emergency lights will illuminate DISARM Normal ...

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Page 65: ... selector position in operation Emergency exit lights and evacuation path marking will Illuminate if DC EMER BUS voltage is below 18V or if the two generators are lost Extinguish if DC EMER BUS voltage is over 20V and at least one generator running R Note With GPU power AVAIL and selected on non engine running the emergency lights will illuminate DISARM Normal selector position with engines stoppe...

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Page 78: ...terfly valve HP valve which remains closed in absence of electrical supply S when the HP valve is closed air is directly bled from the LP stage through LP bleed air check valves S when the HP valve is open the HP air pressure is admitted into the LP pneumatic ducting and closes the check valves air is therefore bled from HP stage only without any recirculation into the engine Wing and engine de ic...

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Page 80: ...terfly valve HP valve which remains closed in absence of electrical supply S when the HP valve is closed air is directly bled from the LP stage through LP bleed air check valves S when the HP valve is open the HP air pressure is admitted into the LP pneumatic ducting and closes the check valves air is therefore bled from HP stage only without any recirculation into the engine Wing and engine de ic...

Page 81: ...nsulating material and are integrated in an inconel tube connected to aircraft ground Each sensing element is permanently subjected to the temperature of the compartment it protects For any temperature higher than a preset value 153 C 307 F applied to a part of the sensing element the resistance of the eutectic mixture rapidly decreases and the central lead is grounded This results in an alert sig...

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Page 84: ...CCAS is activated when the bleed valve position disagrees with the selected position this especially occurs in case of leak or overheat OVHT light The light illuminates amber and the CCAS is activated when either of the respective bleed duct dual overheat sw operates T u 274 C 525 F LEAK light The light comes on amber and the CCAS is activated when respective bleed leak detection system signals an...

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Page 88: ...eed valve position in disagree with command D See BLEED VALVE FAULT procedure in chapter 2 05 08 Overheat in bleed duct T duct u 274 C 525 F D See BLEED OVHT procedure in chapter 2 05 08 Bleed air leak Loop u 153 C 307 F D See BLEED LEAK procedure in chapter 2 05 08 AA AviationLearning net 01 07 2018 REV 1 These notes are not revised after issue For Training Purposes Only Page 60 of 764 ...

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Page 95: ...B VENT It is then evacuated through guides along the cabin side walls at floor level A part of it is recirculated by the fans the other part being evacuated overboard through the outflow valves installed in the rear under floor The toilet is ventilated by differential pressure through a vent line AA AviationLearning net 01 07 2018 REV 1 These notes are not revised after issue For Training Purposes...

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Page 99: ...B VENT It is then evacuated through guides along the cabin side walls at floor level A part of it is recirculated by the fans the other part being evacuated overboard through the outflow valves installed in the rear under floor The toilet is ventilated by differential pressure through a vent line AA AviationLearning net 01 07 2018 REV 1 These notes are not revised after issue For Training Purposes...

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Page 111: ...el MAN RH SIDE Pack valve DC ESS BUS on lateral panel PACK VALVE Recirculation fan DC UTIL BUS 2 on lateral panel PWR SUPPLY CTL Pack and recirculation fan alert DC ESS BUS on lateral panel PACK and RECIRC FAN CAUTION Automatic temperature control DC ESS BUS on lateral panel AUTO Manual temperature control DC ESS BUS on lateral panel MAN Compartment and duct temperature ind DC BUS 1 on lateral pan...

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Page 115: ...MPT Manual temperature control DC ESS BUS on lateral panel MAN RH SIDE Ground cooling fan DC BUS 2 on lateral panel GND COOLING FAN CTL Pack valve DC ESS BUS on lateral panel PACK VALVE Recirculation fan DC UTIL BUS 2 on lateral panel PWR SUPPLY CTL Pack and recirculation fan alert DC ESS BUS on lateral panel PACK and RECIRC FAN CAUTION Automatic temperature control DC ESS BUS on lateral panel AUT...

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Page 137: ...terfly valve HP valve which remains closed in absence of electrical supply S when the HP valve is closed air is directly bled from the LP stage through LP bleed air check valves S when the HP valve is open the HP air pressure is admitted into the LP pneumatic ducting and closes the check valves air is therefore bled from HP stage only without any recirculation into the engine Wing and engine de ic...

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Page 139: ...terfly valve HP valve which remains closed in absence of electrical supply S when the HP valve is closed air is directly bled from the LP stage through LP bleed air check valves S when the HP valve is open the HP air pressure is admitted into the LP pneumatic ducting and closes the check valves air is therefore bled from HP stage only without any recirculation into the engine Wing and engine de ic...

Page 140: ...sulating material and are integrated in an inconel tube connected to aircraft ground Each sensing element is permanently subjected to the temperature of the compartment it protects For any temperature higher than a preset value 153 C 307 F applied to a part of the sensing element the resistance of the eutectic mixture rapidly decreases and the central lead is grounded This results in an alert sign...

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Page 143: ...CAS is activated when the bleed valve position disagrees with the selected position this especially occurs in case of leak or overheat OVHT light The light illuminates amber and the CCAS is activated when either of the respective bleed duct dual overheat sw operates T u 274 C 525 F LEAK light The light comes on amber and the CCAS is activated when respective bleed leak detection system signals an ...

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Page 147: ...ed valve position in disagree with command D See BLEED VALVE FAULT procedure in chapter 2 05 08 Overheat in bleed duct T duct u 274 C 525 F D See BLEED OVHT procedure in chapter 2 05 08 Bleed air leak Loop u 153 C 307 F D See BLEED LEAK procedure in chapter 2 05 08 AA AviationLearning net 01 07 2018 REV 1 These notes are not revised after issue For Training Purposes Only Page 119 of 764 ...

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Page 154: ... VENT It is then evacuated through guides along the cabin side walls at floor level A part of it is recirculated by the fans the other part being evacuated overboard through the outflow valves installed in the rear under floor The toilet is ventilated by differential pressure through a vent line AA AviationLearning net 01 07 2018 REV 1 These notes are not revised after issue For Training Purposes ...

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Page 158: ... VENT It is then evacuated through guides along the cabin side walls at floor level A part of it is recirculated by the fans the other part being evacuated overboard through the outflow valves installed in the rear under floor The toilet is ventilated by differential pressure through a vent line AA AviationLearning net 01 07 2018 REV 1 These notes are not revised after issue For Training Purposes ...

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Page 170: ...el MAN RH SIDE Pack valve DC ESS BUS on lateral panel PACK VALVE Recirculation fan DC UTIL BUS 2 on lateral panel PWR SUPPLY CTL Pack and recirculation fan alert DC ESS BUS on lateral panel PACK and RECIRC FAN CAUTION Automatic temperature control DC ESS BUS on lateral panel AUTO Manual temperature control DC ESS BUS on lateral panel MAN Compartment and duct temperature ind DC BUS 1 on lateral pan...

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Page 174: ...MPT Manual temperature control DC ESS BUS on lateral panel MAN RH SIDE Ground cooling fan DC BUS 2 on lateral panel GND COOLING FAN CTL Pack valve DC ESS BUS on lateral panel PACK VALVE Recirculation fan DC UTIL BUS 2 on lateral panel PWR SUPPLY CTL Pack and recirculation fan alert DC ESS BUS on lateral panel PACK and RECIRC FAN CAUTION Automatic temperature control DC ESS BUS on lateral panel AUT...

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Page 207: ...ichever occurs first Stall alarm alert and shaker are inhibited when aircraft is onthe ground Stick pusher activation is inhibited S on ground R S during 10 seconds after lift off S in flight provided radio altimeter is operative when the aircraft descends below 500 ft if radio alitimeter gives an erroneous 500 ft signal meanwhile IAS 180 kt for more than 120 seconds cruise STICK PUSHER FAULT ambe...

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Page 215: ...0 1 DESCRIPTION 10 2 CONTROLS 10 3 ELECTRICAL SUPPLY MFC LOGIC SYSTEM MONITORING 10 4 SCHEMATIC 1 05 20 TRAFFIC ALERT AND COLLISION AVOIDANCE SYSTEM TCAS 20 1 DESCRIPTION 20 2 CONTROLS 20 3 OPERATION AA AviationLearning net 01 07 2018 REV 1 These notes are not revised after issue For Training Purposes Only Page 187 of 764 ...

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Page 219: ... a VHF control box with dual frequency selection In case of audio control panel loss two AUDIO SEL pbs allow to select one VHF on each side HF COMMUNICATION SYSTEM The system provides the pilot access to 40 programmable channels plus a full 280 000 operating frequencies in the 2 0 to 29 9999 MHz range It is controlled by a HF control box through its transceiver AA AviationLearning net 01 07 2018 R...

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Page 221: ...vide communications on more than 2000 channels from 118 000 to 136 975 MHz with 8 33 KHz spacing and is controlled by a VHF control box with dual channel selection In case of audio control panel loss two AUDIO SEL pbs allow to select one VHF on each side AA AviationLearning net 01 07 2018 REV 1 These notes are not revised after issue For Training Purposes Only Page 193 of 764 ...

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Page 224: ...nd aural calls will be cancelled To call the ground crew from the cockpit see 1 05 10 p 9 D Depress MECH pb overhead panel A horn call is generated in the nose gear bay In case of ground crew call MECH pb illuminates blue on overhead panel and a door bell is generated by the MFC By pressing RESET both visual and aural calls will be cancelled PASSENGER ADDRESS SYSTEM The passenger address system al...

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Page 228: ...decimal point an inner knob is used for selection of numbers right of the decimal point Channel display The active channel is displayed on the first line The preset channel is displayed on the second line Annunciators are displayed on both lines XFR MEM switch This is a three positions spring loaded toggle switch NEUTRAL XFR exchanges preset and active channel MEM successive actions cycle the six ...

Page 229: ...itiate the radio self test diagnostic routine Annunciators Three types of messages can appear in this location MEM illuminates when a preset channel is being displayed on the second line RMT illuminates when the VHF is remotely tuned by an FMS e g TXi illuminates when the VHF is transmitting Compare annunciator ACT signal illuminates when channels are being changed ACT flashes if the actual channe...

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Page 232: ...rs TX is displayed when the ATC replies to an interrogation RMT is displayed when the ATC is remotely tuned ACT Compare annunciator ACT is displayed during code changes ACT flashes when the actual reply code is not identical to the code shown in the active code display PRE button Preset Push and hold the PRE button while turning the code select knobs to select a preset code for storage The storage...

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Page 235: ...minates amber MAN allows commanded operation X MIT ALERT It illuminates amber AUTO TEST RST Is used in case of undue alert resert or to test the emergency beacon Two cases are possible for the test Net work X MIT ALERT illuminates amber during 2 seconds Failure X MIT ALERT It flashes during 15 seconds CAUTION The test must not be performed in MAN mode Aircraft on ground and electrically supplied w...

Page 236: ...f associated RCAU processing board NORM pb depressed RCAU functions normally FAULT illuminates amber and the CCAS is activated when when an associated RCAU processing board failure or power loss is detected ALTN pb released affected crew station is connected directly to VHF 1 if CAPT station is affected or VHF 2 if F O station is affected Volume is adjusted by affected loudspeaker volume control N...

Page 237: ...minates amber MAN allows commanded operation X MIT ALERT It illuminates amber AUTO TEST RST Is used in case of undue alert resert or to test the emergency beacon Two cases are possible for the test Net work X MIT ALERT illuminates amber during 2 seconds Failure X MIT ALERT It flashes during 15 seconds CAUTION The test must not be performed in MAN mode Aircraft on ground and electrically supplied w...

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Page 240: ...y stored When an ITU channel is selected received frequency is displayed on 4 When transmitting transmit frequency is displayed on 4 3 CHANNEL FREQUENCY selection knobs When FREQ CHAN selector is in FREQ position Left outer knob Selects and displays the MHz digits 1 through 29 Left inner knob Pushed in selects the 100 Hz digits 0 through 9 Pulled out selects HF modes USB AM or LSB Right outer knob...

Page 241: ...play blinks Select the desired frequency and mode by using selecting knobs 3 Press PGM button again to store the frequency At this point three ways are possible Store a received only frequency only wait 20 s that the display blinking stops Store a simplex channel press PGM button a third time to store the blinking frequency as a transmit frequency Received and transmit frequencies are now the same...

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Page 249: ...o occur Threat aircraft with mode A transponders will not provide altitude information therefore TCAS will not issue resolution advisories for these threats The TCAS will not detect aircraft without transponders The TCAS is a single system installation consisting of one TCAS processor two high resolution bearing antennae one top mounted and one bottom mounted two mode S transponders two modified T...

Page 250: ...ed restrictions exist F Proximate traffic Nearby aircraft within 850 ft and 6NM which are neither an RA nor a TA G Resolution advisory RA Oral and visual information provided to the flight crew to avoid a potential collision H Threat A target that has satisfied the threat detection logic and thus requires a resolution advisory I Traffic advisory TA Information given to the pilot pertaining to the ...

Page 251: ...mb maneuvers resulting in an unsafe situation for the aircraft see limitations on 2 01 05 Note If altitude reporting is off or not valid Mode S transponder is selected TCAS will be in standby RA OFF on TCAS VSI If appropriate TCAS will automatically go into the TA only mode when the TCAS equipped aircraft is below the RA descent altitude and in a climb inhibit configuration TCAS test function The ...

Page 252: ...he TCAS resolution advisories are annunciated by the following voice messages as appropriate CLIMB CLIMB CLIMB Climb at the rate depicted by the green fly to arc on the TCAS VSI DESCEND DESCEND DESCEND Descend at the rate depicted by the green fly to arc MONITOR VERTICAL SPEED MONITOR VERTICAL SPEED Spoken only once if issued after a previous corrective advisory Assure that vertical speed is out o...

Page 253: ...mb maneuvers resulting in an unsafe situation for the aircraft see limitations on 2 01 05 Note If altitude reporting is off or not valid Mode S transponder is selected TCAS will be in standby RA OFF on TCAS VSI If appropriate TCAS will automatically go into the TA only mode when the TCAS equipped aircraft is below the RA descent altitude and in a climb inhibit configuration TCAS test function The ...

Page 254: ...ardy The TCAS resolution advisories are annunciated by the following voice messages as appropriate CLIMB CLIMB Climb at the rate depicted by the green fly to arc on the TCAS VSI DESCEND DESCEND Descend at the rate depicted by the green fly to arc MONITOR VERTICAL SPEED Initial preventive RAs adjust vertical speed to a value within the illuminated green arc MAINTAIN VERTICAL SPEED MAINTAIN Non cros...

Page 255: ...nal climb rate required to achieve safe vertical separation from a maneuvering threat aircraft CLIMB CLIMB NOW CLIMB CLIMB NOW climb at the rate depicted by the green fly to arc on the TCAS VSI Received after a DESCENT resolution advisory and indicates a reversal in sense is required to achieve safe vertical separation from a maneuvering threat aircraft DESCEND DESCEND NOW DESCEND DESCEND NOW desc...

Page 256: ...ite the RA Since the increase climb RA is inhibited the climb RA remains posted As soon as the threat passes through own aircraft s altitude the RA sense will be reversed and a DESCEND RA will be posted If the threat never crosses through the CLIMB RA will remain posted for the duration of the encounter S DESCEND RA s are inhibited until the aircraft is above 1200 ft AGL on take off below 1000 ft ...

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Page 258: ...rters supplied by the DC system provide constant frequency AC power The ACW electrical system can also supply DC electrical system through a transformer rectifier unit TRU The electrical distribution is ensured by busses which feed equipments Two seperate networks left and right run individually and can be connected in case of generation failure thanks to bus tie contactors BTC AA R AviationLearni...

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Page 263: ...With all switches in normal position the DC power transfer is achieved by automatic opening and or closure of electrical contractors according to the particular electrical conditions On ground D When EXT PWR is connected p 15 16 Note The electrical power transfer is achieved in the same way as in flight as long as EXT POWER is not connected In flight D Both engine driven generator operating p 19 2...

Page 264: ...associated generator contactor is open The OFF light illuminates white FAULT illuminates amber and the CCAS is activated in event of A protection trip initiated by the associated GCU If it is caused by a generator underspeed reset will be automatic For the other cases a manual reset has to be performed An opening of a generator contactor except if pb is selected OFF In both cases the BUS TIE CONTA...

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Page 270: ...FF procedure in chapter 2 05 04 Incipient battery thermal runaway or charge contactor failure D See CHG FAULT procedure in chapter 2 05 04 DC EMER BUS no longer supplied D See DC EMER BUS OFF procedure in chapter 2 05 04 Battery ies discharge in flight but DC main sources available D See BATTERY IES DISCHARGE IN FLIGHT in chapter 2 05 04 One UTLY BUS automatically shed after a source overload D Se...

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Page 279: ...ely from DC BUS 1 and DC BUS 2 The input voltage range is between 18 VDC and 31 VDC for satisfactory operation In event of one DC BUS loss corresponding inverter is not supplied but corresponding AC BUS is supplied by AC BTR BTC pb In event of both DC BUS power loss INV1 is automatically supplied by HOT MAIN BAT BUS or by HOT EMER BAT BUS in OVRD configuration or by TRU when selected ON The maximu...

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Page 294: ... SPOILERS IND STICK PUSHER PWR and CTL LEFT STICK SHAKER 28 FUEL LP VALVE 1 Normal TANK TEMP IND 30 ICE AND RAIN PROTECTION CAPT STATIC PORTS STBY STATIC PORTS LH SIDE WINDOW ANTI ICING RH WINDSHIELD HTG IND 31 INDICATING REĆ CORDING MFC 1B Primary 33 LIGHTS GENERAL ILLUMINATION LEFT LATERAL RAMP 1 FLUORESCENT LIGHT OUT OF 2 CAPT LTS DOME CHARTHOLDER CONSOLE READING F O DOME Normal STORM F O PANEL...

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Page 296: ...SPOILERS IND STICK PUSHER PWR and CTL LEFT STICK SHAKER 28 FUEL LP VALVE 1 Normal TANK TEMP IND 30 ICE AND RAIN PROTECTION CAPT STATIC PORTS STBY STATIC PORTS LH SIDE WINDOW ANTI ICING RH WINDSHIELD HTG IND 31 INDICATING REĆ CORDING MFC 1B Primary 33 LIGHTS GENERAL ILLUMINATION LEFT LATERAL RAMP 1 FLUORESCENT LIGHT OUT OF 2 CAPT LTS DOME CHARTHOLDER CONSOLE READING F O DOME Normal STORM F O PANELS...

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Page 298: ...or NORMAL command RIGHT STICK SHAKER 28 FUEL LP VALVE 2 Normal 29 HYDRAULIC POWER DC AUX HYD PUMP NORM CTL IND and PWR in flight 30 ICE AND RAIN PROTECTION DE ICE VALVES ENG 2 BOOTS A and B Normal WINGS and EMPENNAGE BOOTS B Normal F O WIPER F O STATIC PORTS F O PROBES IND LH WINDSHIELD HTG INDICATOR RH SIDE WINDOW ANTI ICING 31 INDICATING REĆ CORDING F O CLOCK MFC 2B Primary 32 LANDING GEAR WOW 2...

Page 299: ...RAL RAMP 1 FLUORESCENT LIGHT OUT OF 2 34 NAVIGATION ATC 2 DME 2 VOR ILS 2 ADF 2 CAPT RMI SGU 2 F O EADI AHRS 1 Auxiliary Back up DC EMER BUS AHRS 2 Primary F O EHSI GPS 36 PNEUMATIC HP VALVE 2 52 DOORS ALERTS 61 PROPELLERS OVSPD TEST ENG 2 AFU 2 Normal 73 ENGINE FUEL and CTL FUEL FLOW FUEL USED IND 2 FUEL TEMP IND 2 FUEL CLOG IND 2 EEC 2 Normal IDLE GATE FAIL IND 79 OIL Press Temp IND 2 AA R Aviat...

Page 300: ...for NORMAL command RIGHT STICK SHAKER 28 FUEL LP VALVE 2 Normal 29 HYDRAULIC POWER DC AUX HYD PUMP NORM CTL IND and PWR in flight 30 ICE AND RAIN PROTECTION DE ICE VALVES ENG 2 BOOTS A and B Normal WINGS and EMPENNAGE BOOTS B Normal F O WIPER F O STATIC PORTS F O PROBES IND LH WINDSHIELD HTG INDICATOR RH SIDE WINDOW ANTI ICING 31 INDICATING REĆ CORDING F O CLOCK MFC 2B Primary 32 LANDING GEAR WOW ...

Page 301: ...RAL RAMP 1 FLUORESCENT LIGHT OUT OF 2 34 NAVIGATION ATC 2 DME 2 VOR ILS 2 ADF 2 CAPT RMI SGU 2 F O EADI AHRS 1 Auxiliary Back up DC EMER BUS AHRS 2 Primary F O EHSI GPS 36 PNEUMATIC HP VALVE 2 52 DOORS ALERTS 61 PROPELLERS OVSPD TEST ENG 2 AFU 2 Normal 73 ENGINE FUEL and CTL FUEL FLOW FUEL USED IND 2 FUEL TEMP IND 2 FUEL CLOG IND 2 EEC 2 Normal IDLE GATE FAIL IND 79 OIL Press Temp IND 2 AA R Aviat...

Page 302: ... BUS 1 EMER BAT AMMETER EMER BAT VOLT IND EMER BUS and INV 1 ON EMER BAT IND ARROW TRU IND 28 FUEL LP VALVES 1 and 2 Back up DC BUS 1 DC BUS 2 31 INDICATING REĆ CORDING MFC 1 MOD A Auxiliairy Back up DC ESS BUS SECT 1 34 NAVIGATION STBY HORIZON Back up ADC 1 Back up ADC 2 Back up AA R R AviationLearning net 01 07 2018 REV 1 These notes are not revised after issue For Training Purposes Only Page 27...

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Page 304: ...BY BUS IND UNDV OVRD EMER BAT CHG IND DC STBY BUS CTL BUS REMAIN SUPPLIED BY DC BUS 1 AC 1 BUSSES CTL BUSSES REMAIN SUPPLIED BY INV 2 26 FIRE PROTECTION ENG FIRE EXTINGUISHING CTL and IND NorĆ mal FIRE HANDLE IND ENG 1 and 2 FIRE DETECTION ENG 1 and 2 27 FLIGHT CONTROLS PITCH TRIM NORMAL COMMAND RUDDER TRIM AILERON TRIM 29 HYDRAULIC POWER BLUE PUMP CTL and IND GREEN PUMP IND 30 ICE and RAIN PROTEC...

Page 305: ...NELS PYLON STBY COMPASS LAVATORY EMERGENCY F O DOME Back up DC BUS 1 34 NAVIGATION ATC 1 AHRS 2 ON GROUND Auxiliary AHRS 1 Primary ADC 1 Primary ADC 2 Primary 61 PROPELLERS AFU 1 and 2 Back up DC BUS 1 DC BUS 2 A F AUX PUMPS CTL TORQUE IND 1 and 2 PEC 1 and PEC 2 Normal associated PVM and PIU 73 ENGINE FUEL and CTL EEC 1 and 2 PWR and IND Back up DC BUS 1 DC BUS 2 76 ENGINE CTL CL FIRE IND 1 and 2...

Page 306: ...IND UNDV OVRD EMER BAT CHG IND DC STBY BUS CTL BUS REMAIN SUPPLIED BY DC BUS 1 AC 1 BUSSES CTL BUSSES REMAIN SUPPLIED BY INV 2 26 FIRE DETECTION ENG FIRE EXTINGUISHING CTL and IND NorĆ mal FIRE HANDLE IND ENG 1 and 2 FIRE DETECTION ENG 1 and 2 27 FLIGHT CONTROLS PITCH TRIM NORMAL COMMAND RUDDER TRIM AILERON TRIM AILERON LOCKING IND 29 HYDRAULIC POWER BLUE PUMP CTL and IND GREEN PUMP IND 30 ICE and...

Page 307: ...NELS PYLON STBY COMPASS LAVATORY EMERGENCY F O DOME Back up DC BUS 1 34 NAVIGATION ATC 1 AHRS 2 ON GROUND Auxiliary AHRS 1 Primary ADC 1 Primary ADC 2 Primary 61 PROPELLERS AFU 1 and 2 Back up DC BUS 1 DC BUS 2 A F AUX PUMPS CTL TORQUE IND 1 and 2 PEC 1 and PEC 2 Normal associated PVM and PIU 73 ENGINE FUEL and CTL EEC 1 and 2 PWR and IND Back up DC BUS 1 DC BUS 2 76 ENGINE CTL CL FIRE IND 1 and 2...

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Page 310: ...DRESS MECHANIC CALL COCKPIT and CABIN CREW CALL CVR 24 ELECTRICAL POWER GCU 2 DC BackĆup GCU 1 and 2 ACW Back up BPCU ACW Back up DC SVCE and UTLY BUSSES 1 and 2 CTL MAIN BAT CHG IND INV 2 FAULT IND AC 2 and STBY BUSSES CTL BUSSES REMAIN SUPPLIED BY INV 1 26 FIRE PROTECTION TOILETS SMK DET AVIONICS SMK DET FWD and AFT CAB SMK DET AFT COMPT and TOILETS DET FANS CTL and IND FWD CAB DET FANS CTL and ...

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Page 314: ...HANIC CALL COCKPIT and CABIN CREW CALL CVR 24 ELECTRICAL POWER GCU 2 DC BackĆup GCU 1 and 2 ACW Back up BPCU ACW Back up DC SVCE and UTLY BUSSES 1 and 2 CTL MAIN BAT CHG IND INV 2 FAULT IND AC 2 and STBY BUSSES CTL BUSSES REMAIN SUPPLIED BY INV 1 26 FIRE PROTECTION TOILETS SMK DET AVIONICS SMK DET FWD and AFT COMPT SMK DET AFT COMPT and TOILETS DET FANS CTL and IND FWD COMPT DET FANS CTL and IND C...

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Page 316: ...R PRESS TRIPLE IND INTERCONNECTING VALVE 32 LANDING GEAR PRIMARY IND LANDING GEAR CTL HYDRAULIC VALVE ANTISKID INOP and BRAKE OVTEMP IND R and L INBOARD and OUTBOARD BRAKES TEMP XMITTERS 33 LIGHTS EMERGENCY 34 NAVIGATION VOR ILS MKR 1 SGU 1 CAPT EADI CAPT EHSI RMI F O ADF 1 AA R R AviationLearning net 01 07 2018 REV 1 These notes are not revised after issue For Training Purposes Only Page 288 of 7...

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Page 332: ... 42 Model 400 500 GENERAL EMERGENCY EQUIPMENT P 3 4 DEC 95 001 1 07 10 SCHEMATICS AA AviationLearning net 01 07 2018 REV 1 These notes are not revised after issue For Training Purposes Only Page 304 of 764 ...

Page 333: ...vided to 3 cockpit crew for a duration of 120 mn 10 minutes to descend from 25 000 ft to 13 000 ft and continuation of flight between 13 000 ft and 10 000 ft for 110 minutes In case of smoke or noxious gas emission with the dilution control in the 100 position oxygen is provided to 3 cockpit crew for a duration of 15 minutes at demand flow CABIN ATTENDANT PORTABLE UNIT One portable oxygen bottle i...

Page 334: ...supply solenoid valve ON pb pressed in The valve is open low pressure oxygen is supplied to the cockpit crew oxygen masks OFF pb released The valve is closed OFF illuminates white LO PR Illuminates amber and the CCAS is activated when a low pressure below 50 PSI is detected in the low pressure distribution circuit PAX SUPPLY pb ON pb pressed in Passengers supply valve is open ON illuminates blue O...

Page 335: ... ft and 10 000 ft for 110 minutes In case of smoke or noxious gas emission xith the dilution control in the 100 position oxygen is provided to 2 pilots and 1 observer for a duration of 15 minutes at demand flow CABIN ATTENDANT PORTABLE UNITS One 120 l 4 25 cu ft portable oxygen bottle is stowed under the cabin attendant seat It permits a continuous diluted flow to cabin attendant at 13 000 ft for ...

Page 336: ...PR illuminates amber and the CCAS is activated when alow pressure below 50 PSI is detected in the low pressure distribution circuit PAX SUPPLY SW MAN OVRD Controls manually the oxygen masks unfolding and PAX SUPPLY R Valve opening at cabin altitude between 10000 ft and 25000 ft AUTO Oxygen masks unfolding in case of depressurization The PAX SUPPLY Valve is connected to the ALT PRESS switch which e...

Page 337: ... mask delivers 100 undiluted oxygen N The mask delivers diluted oxygen TEST RESET pb Permits a test of oxygen flow without removing the mask from the container It is springloaded to the RESET position TEST Provided MAIN SUPPLY pb is selected ON oxygen flows through the mask The blinker momentarily displays yellow cross and the flow is audible A lengthened hose is provided on the observer mask enab...

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Page 341: ...42 Model 400 500 OXYGEN SYSTEM EMERGENCY EQUIPMENT P 7 8 NOV 97 100 1 07 20 20 4 SCHEMATICS AA AviationLearning net 01 07 2018 REV 1 These notes are not revised after issue For Training Purposes Only Page 313 of 764 ...

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Page 347: ...1 NOV 98 110 1 07 30 EMERGENCY EVACUATION IN CASE OF DITCHING EMERGENCY EXIT SERVICE DOOR PASSENGER CREW DOOR Note Be sure that safety pin is removed AA A B C AviationLearning net 01 07 2018 REV 1 These notes are not revised after issue For Training Purposes Only Page 319 of 764 ...

Page 348: ...V 98 110 1 07 30 EMERGENCY EVACUATION IN CASE OF FORCED LANDING EMERGENCY EXIT SERVICE DOOR C PASSENGER CREW DOOR Note Be sure that safety pin is removed AA A B C AviationLearning net 01 07 2018 REV 1 These notes are not revised after issue For Training Purposes Only Page 320 of 764 ...

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Page 350: ...esistance associated loop will be declared failed by the fire detection control unit fault signal Red ENG FIRE illuminates on CAP in case of Fire signal detected by both loops A and B or Fire signal detected by one of the 2 loops if the other one is selected OFF RIGHT NACELLE OVERHEAT DETECTION SYSTEM Right nacelle is equipped with an overheat detector When right nacelle temperature exceeds 170 C ...

Page 351: ...uibs are installed in the discharge heads on each bottle For fire extinguishing the squibs are ignited by depressing the correcponding illuminated AGENT pb on the ENG FIRE panel The extinguishing agent freon or halon is pressurized by nitrogen COCKPIT CABIN AND CARGO COMPARTMENTS FIRE EXTINGUISHING SYSTEM Portable extinguishers are provided to be operated manually refer to schematic 1 07 10 p 2 fo...

Page 352: ...LE OVERHEAT DETECTION SYSTEM Right nacelle is equipped with an overheat detector When right nacelle temperature exceeds 170 C NAC2 OVHT red alarm is triggered on CAP and the CCAS is activated CARGO AND TOILETS SMOKE DETECTION SYSTEM Forward cargo and after cargo are each equipped with one optical smoke detector Ambient transmittance is monitored by reflection measurement Toilets are equipped wih o...

Page 353: ...uibs are installed in the discharge heads on each bottle For fire extinguishing the squibs are ignited by depressing the correcponding illuminated AGENT pb on the ENG FIRE panel The extinguishing agent freon or halon is pressurized by nitrogen COCKPIT CABIN AND CARGO COMPARTMENTS FIRE EXTINGUISHING SYSTEM Portable extinguishers are provided to be operated manually refer to schematic 1 07 10 p 2 fo...

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Page 355: ...erated by the fire detection control unit LOOP amber light illuminates on CAP TEST sw Spring Loaded in neutral position Spring loaded in neutral position allows a test of the detection of fire and fault signals when both LOOP pbs are selected ON FAULT FAULT lights of both LOOP A and LOOP B pb illuminate CCAS is activated LOOP amber light illuminates on CAP FIRE ENG FIRE red light illuminates in as...

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Page 358: ...F It is extinguished OFF pb released Both cabin ventilation isolating valves are closed OFF It illuminates white CONTAINER SMK ACTIVATION pb ON pb pressed in in cargo configuration allows to connect the container smoke detectors ON It illuminates white pb released in pax configuration only FWD and AFT smoke detectors are used CONTAINER SMK Its Are associated to the container smoke detectors only w...

Page 359: ...IGURATION CNTNR SMK pb is ON CAUTION FWD SMK or AFT SMK CAP alert may be associated or not with CONTAINER SMK local alert on overhead panel PAX CONFIGURATION CNTNR SMK pb is released AA AviationLearning net 01 07 2018 REV 1 These notes are not revised after issue For Training Purposes Only Page 331 of 764 ...

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Page 363: ...The following conditions are monitored by visual and aural alerts ENG fire signal See ENG FIRE procedure in chapter 2 04 02 Smoke detected in the avionics ventilation circuit See ELECTRICAL SMOKE procedure in chapter 2 04 03 Smoke detected in the FORWARD cargo compartment See FWD CARGO SMOKE procedure in chapter 2 04 03 Smoke detected in the aft cargo compartment or in the lavatory See AFT COMPT S...

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Page 370: ...forts Wheel travel 87 Ailerons travel 14 up 14 down ROLL TRIM Aileron trim is performed by varying the neutral position setting of the left aileron spring tab with respect to the aileron It is electrically controlled from a twin control sw through an electrical actuator LH aileron trim controlled tab travel 6 7 up 6 7 down Full roll trim travel requires about 15s TOFA 01 09 20 001 A100AA AA R R Av...

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Page 373: ...ase of pitch tabs desynchronization An alert is generated by the CCAS Normal and STBY pitch trim control are inoperative AP disconnects Trim tab travel displayed on the pitch trim position indicator is added to the automatic tab travel Elevators trim controlled tab travel 9º up 4º down Full pitch trim travel requires about 30s in normal and in STBY control A stick pusher and a stick shaker are pro...

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Page 386: ...as the lever is not in one of the three distinct positions and release the lever FLAPS POSITION IND Indicates flaps position A blue EXT flag appears to indicate that the flap valve is hydraulically commanding flap extension Note If EXT flag appears when flaps are extended it means that there is a leak in the flaps hydraulic circuit FLAP ASYM It Illuminates amber when flaps asymmetry exceeds 6 7 AA...

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Page 397: ...essed in the LDG FLAP 25 push button is self maintained in this state until Touch down WOW condition Go around at least one PLA 62_ condition Another press of the pilot Selection of STEEP APP function It is impossible to select both functions at the same time AA AviationLearning net 01 07 2018 REV 1 These notes are not revised after issue For Training Purposes Only Page 369 of 764 ...

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Page 404: ...ashing amber FLT CTL amber light illuminates on CAP AIL LOCK amber light illuminates on the pedestal Aural alert is single chime SC Aileron locking actuators not fully retracted and PL on TO position MW flashing red CONFIG red light illuminates on CAP FLT CTL amber light illuminates on CAP Aural alert is Continuous Repetitive Chime CRC Disagree between aileron locking actuators and gust lock contr...

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Page 408: ... TAS Total Air Temperature TAT Static Air Temperature SAT ADC 1 supplies CAPT flight instruments altimeter airspeed ind vertical speed ind other systems AHRS 1 FDAU MFC GPWS pressurization AFCS ATC 1 and ATC 2 through TCAS control box and TCAS through ATC 1and ATC 2 if installed and mode S only ADC 2 supplies F O flight instruments altimeter airspeed ind vertical speed ind other systems AHRS 2 FDA...

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Page 410: ...om this data each ADC computes pressure altitude vertical speed Indicated Air Speed IAS True Air Speed TAS Total Air Temperature TAT Static Air Temperature SAT ADC 1 supplies CAPT flight instruments altimeter airspeed ind vertical speed ind other systems AHRS 1 FDAU ATC 1 MFC GPWS pressurization AFCS ADC 2 supplies F O flight instruments altimeter airspeed ind vertical speed ind other systems AHRS...

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Page 412: ...e Air Speed TAS Total Air Temperature TAT Static Air Temperature SAT ADC 1 supplies CAPT flight instruments altimeter airspeed ind vertical speed ind other systems AHRS 1 FDAU MFC GPWS pressurization AFCS ATC 1 and ATC 2 through TCAS control box and TCAS through ATC 1 and ATC if installed and mode S only ADC 2 supplies F O flight instruments altimeter airspeed ind vertical speed ind other systems ...

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Page 416: ...en thousands thousands and hundreds of feet A black and white flag marks the LH drum ten thousands when altitude is between 0 and 9999 ft An orange and white flag marks the two LH drums ten thousands and thousands when altitude is below 0 ft Note Allowable deviation between normal altimeter indications and between normal and standby altimeter indications FL ft NORM NORM ft NORM STBY ft 0 55 70 5 0...

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Page 418: ...en thousands thousands and hundreds of feet A black and white flag marks the LH drum ten thousands when altitude is between 0 and 9999 ft An orange and white flag marks the two LH drums ten thousands and thousands when altitude is below 0 ft Note Allowable deviation between normal altimeter indications and between normal and standby altimeter indications FL ft NORM NORM ft NORM STBY ft 0 55 70 5 0...

Page 419: ...R Mod 3832 or 8259 ATR 42 Model 400 500 NOV 01 AviationLearning net 01 07 2018 REV 1 These notes are not revised after issue For Training Purposes Only Page 391 of 764 ...

Page 420: ...en thousands thousands and hundreds of feet A black and white flag marks the LH drum ten thousands when altitude is between 0 and 9999 ft An orange and white flag marks the two LH drums ten thousands and thousands when altitude is below 0 ft Note Allowable deviation between normal altimeter indications and between normal and standby altimeter indications FL ft NORM NORM ft NORM STBY ft 0 55 70 5 0...

Page 421: ... increments and from 1000 to 6000 ft mn in 500 ft mn increments Display accuracy is 40 ft mn Vertical speed flag Appears if the indicator is not able to display vertical speed information In that case the vertical speed pointer disappears when V S flag appears Test When depressed indicator will display a test pattern Light sensort Not available AA 1 2 3 4 5 AviationLearning net 01 07 2018 REV 1 Th...

Page 422: ...NOV 01 R Mod 3832 or 8259 ATR 42 Model 400 500 AviationLearning net 01 07 2018 REV 1 These notes are not revised after issue For Training Purposes Only Page 394 of 764 ...

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Page 424: ... ALTM CAPT altimeter recording FDAU Nil 26 VAC STBY BUS on overhead panel ALTM F O airspeed ind and vertical speed ind Nil 26 VAC BUS 2 on overhead panel ASI VSI F O altimeter Nil 26 VAC BUS 2 on overhead panel ALTM Standby altimeter vibrator DC BUS 1 on overhead panel STBY ALTM Nil SYSTEM MONITORING The following conditions are monitored by visual alerts Loss of ADC See ADC FAULT procedure in cha...

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Page 426: ...ATR 42 Model 400 500 AIR DATA SYSTEM FLIGHT INSTRUMENTS P 9 10 NOV 01 060 1 10 10 10 4 SCHEMATIC AA AviationLearning net 01 07 2018 REV 1 These notes are not revised after issue For Training Purposes Only Page 398 of 764 ...

Page 427: ...NOV 00 Mod 3952 or 4890 or 5021 or 5022 ATR 42 Model 400 500 AviationLearning net 01 07 2018 REV 1 These notes are not revised after issue For Training Purposes Only Page 399 of 764 ...

Page 428: ...r 5021 or 5022 ATR 42 Model 400 500 AIR DATA SYSTEM FLIGHT INSTRUMENTS P 9 10 NOV 01 150 1 10 10 10 4 SCHEMATIC AA AviationLearning net 01 07 2018 REV 1 These notes are not revised after issue For Training Purposes Only Page 400 of 764 ...

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Page 436: ...e selected decision height in feet blue and the DH letters in white When selected DH is set to zero DH information disappears from EADI Maximum selectable Decision Height is 990 ft When aircraft radio altitude reaches selected decision height 100 ft a white box appears near the radio altitude information on EADI When aircraft radio altitude becomes lower than selected decision height the amber DH ...

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Page 443: ...nly functional on the ground all failure messages appear on EFIS Radio altimeter test is performed in flight as well as on ground RA indication displays 100 ft on EADI CAUTION In flight the RA test provides the radar with altitude information which trigger undue GPWS alerts HSI DIM WX DIM knobs Outer knob HSI DIM is used to select EHSI ON OFF and to set brightness Automatic setting is also perform...

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Page 445: ...ter test is performed in flight as well as on ground RA indication displays 100 ft on EADI CAUTION In flight the RA test provides the radar with altitude information which trigger undue GPWS alerts HSI DIM WX DIM knobs Outer knob HSI DIM is used to select EHSI ON OFF and to set brightness Automatic setting is also performed when ambient brighness changes Inner knob WX DIM is used to select ON OFF ...

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Page 454: ...ert hour and minutes on data entry panel UPDATE pb depressed correction is taken into account and is displayed for 5 seconds The following sequence must be initiated during these 5 seconds S Second sequence month and day Repeat first sequence and insert month and day S Third sequence year Repeat first sequence and insert year Note Once data are inserted reset the flight number on data entry panel ...

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Page 463: ...ctrical pump is automatically actuated FF FU IND A fuel flow fuel used ind is provided for each engine FF indication The mass fuel flow to the engine is indicated by a pointer on a scale graduated in kg h X 100 FU counter On the digital read out fuel used is indicated in kg This value is computed by integration of the fuel flow parameter FU reset knob The fuel used counter is reset to 0 by pulling...

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Page 466: ...NOV 00 001 1 11 10 xxx Yellow sector 54ºC to 0ºC Green sector 0ºC to 50ºC Yellow sector 50ºc to 57ºC Red dash 54ºC and 57ºC AA AviationLearning net 01 07 2018 REV 1 These notes are not revised after issue For Training Purposes Only Page 438 of 764 ...

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Page 468: ...NOV 00 001 1 11 10 xxx Yellow sector 54ºC to 0ºC Green sector 0ºC to 50ºC Yellow sector 50ºc to 57ºC Red dash 54ºC and 57ºC AA AviationLearning net 01 07 2018 REV 1 These notes are not revised after issue For Training Purposes Only Page 440 of 764 ...

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Page 477: ...F pb released Auxiliary pump is deactivated OFF illuminates white LO PR The light illuminates amber and CCAS is activated when auxiliary pump outlet pressure is detected lower than 1500 PSI and functioning conditions are met XFEED pb Controls opening and closure of the crossfeed valve OFF pb released Crossfeed valve is closed Both hydraulic circuits are separated ON pb pressed in Crossfeed valve i...

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Page 488: ...test button for 3 seconds ICING amber light flashes on central panel with associated warning if system works correctly ICE DET FAULT illuminates with associated central warnings if an ice detector failure is detected ICING AOA pb ICING AOA It illuminates green as soon as one horns anti icing Pb is selected ON reminding the crew of stall alarm threshold being lower in icing conditions ICING AOA It ...

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Page 490: ...ctor correct operation Press and hold test button for 3 seconds ICING amber light flashes on central panel with associated warning if system works correctly ICE DET FAULT illuminates with associated central warnings if an ice detector failure is detected ICING AOA pb ICING AOA It illuminates green as soon as one horns anti icing Pb is selected ON reminding the crew of stall alarm threshold being l...

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Page 493: ...E FOLLOWING SEQUENCE AT 60 SEC FAST MODE 180 SEC SLOW MODE OVRD MODE SEPARATED TIMER BEGINNING OF THE FOLLOWING SEQUENCE AT 60 SEC FAST MODE Note When de icing OVRD mode is selected boots inflate according to a separate timer and MFC is totally by passed AA R AviationLearning net 01 07 2018 REV 1 These notes are not revised after issue For Training Purposes Only Page 465 of 764 ...

Page 494: ...on sequencing of airframe boots A or B is not correct Air temperature upstream of the de ice valves exceeds 230 C The alert is inhibited when pb is released AIRFRAME pb Controls the outputs A and B of both wings and stabilizers distribution valves ON pb pressed in Signal is sent to the MFC in order to initiate a de icing cycle depending on MODE SEL pb ON light illuminates blue Pb released In norma...

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Page 496: ...s Inflation sequencing of airframe boots A or B is not correct Air temperature upstream of the de ice valves exceeds 230 C The alert is inhibited when pb is released AIRFRAME pb Controls the outputs A and B of both wings and stabilizers distribution valves ON pb pressed in Signal is sent to the MFC in order to initiate a de icing cycle depending on MODE SEL pb ON light illuminates blue Pb released...

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Page 498: ...AULT Illuminates amber and the CCAS is activated when MFC 1B or 2B and or ADC failure occurs The DE ICING MODE SEL pb 4 is inoperative In this case the FAST mode is automatically activated MAN pb pressed in The DE ICING MODE SEL pb 4 is operative and allows the crew to select the appropriate timing cycle depending on SAT MAN illuminates white AA 6 R R R AviationLearning net 01 07 2018 REV 1 These ...

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Page 501: ...G FAULT procedure in chapter 2 05 09 Power loss on a horn anti icing unit See HORNS ANTI ICING FAULT procedure in chapter 2 05 09 MFC 1B or 2B and or ADC failure Discrepancy between outputs See MODE SEL AUTO FAULT procedure in chapter 2 05 09 Boots do not operate following MFC failure or both boots A and B of the same engine are supplied 200 sec after eng cycle beginning or Boots A B of both engin...

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Page 503: ... ANTI ICING FAULT procedure in chapter 2 05 09 Power loss on a horn anti icing unit See HORNS ANTI ICING FAULT procedure in chapter 2 05 09 MFC 1B or 2B and or ADC failure Discrepancy between outputs See MODE SEL AUTO FAULT procedure in chapter 2 05 09 Boots do not operate following MFC failure or both boots A and B of the same engine are supplied 200 sec after eng cycle beginning or Boots A B of ...

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Page 511: ...2 and MFC2B FAULT Illuminates amber and the CCAS is activated when MFC 1B or 2B and or ADC failure occurs The ANTI ICING MODE SEL pb 2 is inoperative In this case the HIGH POWER mode is automatically activated MAN pb pressed in The ANTI ICING MODE SEL pb 2 is operative and allows the crew to select the appropriate timing cycle depending on SAT MAN illuminates white AA 3 R R R AviationLearning net ...

Page 512: ...CING PWR SPLY AC wild BUS 2 on lateral panel PROP2 ANTI ICING PWR SPLY Note Propeller anti icing is inhibited when Np is below 63 MFC LOGIC See chapter 1 01 SYSTEM MONITORING The following conditions are monitored by visual and aural alerts One or more blade heating unit s inoperative SSee PROP ANTI ICING FAULT procedure in chapter 2 05 09 MFC 1B or 2B and or ADC failure discrepancy between output...

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Page 519: ...m speed to operate the wipers is 160 kt 70 2 CONTROLS WIPER rotary selector Controls the windshield wiper on the associated side FAST wiper operates at 130 cycles mn SLOW wiper operates at 80 cycles mn OFF wiper operation stops at the end of travel Park position 70 3 ELECTRICAL SUPPLY EQUIPMENT DC BUS SUPPLY C B Captain wiper DC ESS BUS on lateral panel CAPT F O wiper DC BUS 2 on lateral panel F O...

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Page 543: ...1 GENERAL 2 01 02 WEIGHT AND LOADING 2 01 03 AIRSPEED AND OPERATIONAL PARAMETERS 2 01 04 POWER PLANT 2 01 05 SYSTEMS 2 01 06 TCAS 2 01 07 GPS 2 01 08 CABIN LIGHTING AA R AviationLearning net 01 07 2018 REV 1 These notes are not revised after issue For Training Purposes Only Page 515 of 764 ...

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Page 545: ...ank angle in turns and the severity of pull up maneuvers CARGO DOOR OPERATION Do not operate cargo door with a cross wind component of more than 45 kt DISPATCHIBILITY For dispatch in the event of equipment failure or missing equipment refer to MEL CDL MAXIMUM NUMBER OF PASSENGER SEATS 60 R R R AA AviationLearning net 01 07 2018 REV 1 These notes are not revised after issue For Training Purposes On...

Page 546: ... given in percentage of the mean aerodynamic chord MAC landing gear extended The MAC is 2 285 meters long 89 961 in Station 0 is located 2 362 meters 92 992 in forward of the fuselage nose The distance from station 0 to reference chord leading edge is 11 425 meters 449 803 in CARGO COMPARTMENT LOADING LIMITATIONS See W B M 1 10 04 p 1 AA R R R AviationLearning net 01 07 2018 REV 1 These notes are ...

Page 547: ...ravity are given in percentage of the mean aerodynamic chord MAC landing gear extended The MAC is 2 285 meters long 89 961 in Station 0 located 2 362 meters 92 992 in forward of the fuselage nose The distance from station 0 to reference chord leading edge is 11 425 meters 449 803 in CARGO COMPARTMENT LOADING LIMITATIONS See W B M 1 10 04 p 1 AA AviationLearning net 01 07 2018 REV 1 These notes are...

Page 548: ...gravity are given in percentage of the mean aerodynamic chord MAC landing gear extended The MAC is 2 285 meters long 89 961 in Station 0 located 2 362 meters 92 992 in forward of the fuselage nose The distance from station 0 to reference chord leading edge is 11 425 meters 449 803 in CARGO COMPARTMENT LOADING LIMITATIONS See W B M 1 10 04 p 1 AA AviationLearning net 01 07 2018 REV 1 These notes ar...

Page 549: ... given in percentage of the mean aerodynamic chord MAC landing gear extended The MAC is 2 285 meters long 89 961 in Station 0 is located 2 362 meters 92 992 in forward of the fuselage nose The distance from station 0 to reference chord leading edge is 11 425 meters 449 803 in CARGO COMPARTMENT LOADING LIMITATIONS See W B M 1 10 04 p 1 AA R R R AviationLearning net 01 07 2018 REV 1 These notes are ...

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Page 558: ...TION INCREASE BY 1 5 KT FOR TAKE OFF BLEED ON 40 30 20 0 10 20 30 40 50 OUTSIDE AIR TEMPERATURE DG C 80 84 88 92 96 100 104 AA R R R R R R R R R R R R R R R R R R R R R R R R R R R R R R R R R R R R R R R R R R AviationLearning net 01 07 2018 REV 1 These notes are not revised after issue For Training Purposes Only Page 530 of 764 ...

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Page 562: ...ATIONAL PARAMETERS ENVIRONMENTAL ENVELOPE TAKE OFF AND LANDING TAIL WIND LIMIT 15 KT The maximum demonstrated cross wind on dry runway is 30 KT MAXIMUM MEAN RUNWAY SLOPE 2 AA R AviationLearning net 01 07 2018 REV 1 These notes are not revised after issue For Training Purposes Only Page 534 of 764 ...

Page 563: ...NSIENT 20 s 137 5 840 104 3 106 5 106 3 40 to 100 5 s 120 20 mn 140 STARTING 5 s 950 54 mini 1 Value linked to 100 NP 2 Oil temperature must be maintained above 45 C to ensure protection for the engine air inlet against ice accumulation 3 Permissible for completion of flight provided TQ does not exceed 85 during climb and 84 during cruise 4 Up to 75 NH only 5 ITT limits depend on outside air tempe...

Page 564: ... PW127E ATR 42 Model 500 POWER PLANT LIMITATIONS P 2 MAY 98 001 2 01 04 R R R R R AA AviationLearning net 01 07 2018 REV 1 These notes are not revised after issue For Training Purposes Only Page 536 of 764 ...

Page 565: ...HOTEL 7 MODE 785 55 to 65 120 TRANSIENT 20 s 132 4 850 104 1 110 40 to 100 5 s 120 OTHER 110 6 130 5 STARTING 5 s 950 40 mini 1 Value linked to 100 NP 2 Oil temperature must be maintained above 45 C to ensure protection for the engine air inlet against ice accumulation 3 Below FI only 4 Time beyond 5 mn is linked to actual single engine operations only 5 20 mn max 6 The flight can be completed wit...

Page 566: ...g PW121A ATR 42 Model 400 POWER PLANT LIMITATIONS P 2 MAY 98 400 2 01 04 R R R R AA AviationLearning net 01 07 2018 REV 1 These notes are not revised after issue For Training Purposes Only Page 538 of 764 ...

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Page 573: ...0 A 600 A 800 A NONE 2 mn 8 s INV 500 VA 575 VA 750 VA NONE 30 mn 5 mn ACW GEN 20 KVA 30 KVA 40 KVA NONE 5 mn 5 s TRU 60A 90A NONE 5 mn SINGLE DC GEN OPERATION In flight if OAT exceeds ISA 25 flight level must be limited to FL 200 HYDRAULIC SYSTEM SPECIFICATION HYJET IV OR SKYDROL LD 4 LANDING GEAR DO NOT PERFORM PIVOTING SHARP TURNS ON A LANDING GEAR WITH FULLY BRAKED WHEELS EXCEPT IN CASE OF EME...

Page 574: ...on at an altitude below 13 000 ft A 25 pax oxygen consumption is assumed In case of smoke emission the system protects the flight crew members during 15 min Note At dispatch the computed flight time after decompression should be at least 1 2 of estimated flight time to destination or flight time to the longest en route alternate which ever is higher Provision is made to cover unusuable quantity no...

Page 575: ...0 A 600 A 800 A NONE 2 mn 8 s INV 500 VA 575 VA 750 VA NONE 30 mn 5 mn ACW GEN 20 KVA 30 KVA 40 KVA NONE 5 mn 5 s TRU 60A 90A NONE 5 mn SINGLE DC GEN OPERATION In flight if OAT exceeds ISA 25 flight level must be limited to FL 200 HYDRAULIC SYSTEM SPECIFICATION HYJET IV OR SKYDROL LD 4 LANDING GEAR DO NOT PERFORM PIVOTING SHARP TURNS ON A LANDING GEAR WITH FULLY BRAKED WHEELS EXCEPT IN CASE OF EME...

Page 576: ...nd 100 of passengers protection with diluted oxygen during descent from FL 250 to holding level followed by descent to FL100 rate 3000 ft minutes Reference Temperature Cabin Temperature or OAT whichever is higher on ground Cabin Temperature in flight Note At dispatch the computed flight time after decompression should be at least 1 2 of estimated flight time to destination or flight time to the lo...

Page 577: ...CAL SYSTEM SOURCE MAX LOAD TIME LIMIT DC GEN 400 A 600 A 800 A NONE 2 mn 8 s INV 500 VA 575 VA 750 VA NONE 30 mn 5 mn ACW GEN 20 KVA 30 KVA 40 KVA NONE 5 mn 5 s TRU 60A 90A NONE 5 mn HYDRAULIC SYSTEM SPECIFICATION HYJET IV OR SKYDROL LD 4 LANDING GEAR DO NOT PERFORM PIVOTING SHARP TURNS ON A LANDING GEAR WITH FULLY BRAKED WHEELS EXCEPT IN CASE OF EMERGENCY MFC TAKE OFF WITH MORE THAN ONE FAILED MF...

Page 578: ...on at an altitude below 13 000 ft A 25 pax oxygen consumption is assumed In case of smoke emission the system protects the flight crew members during 15 min Note At dispatch the computed flight time after decompression should be at least 1 2 of estimated flight time to destination or flight time to the longest en route alternate which ever is higher Provision is made to cover unusuable quantity no...

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Page 580: ...42 Model 400 500 TCAS LIMITATIONS P 1 NOV 98 001 2 01 06 LEFT INTENTIONALLY BLANK AA AviationLearning net 01 07 2018 REV 1 These notes are not revised after issue For Training Purposes Only Page 552 of 764 ...

Page 581: ... is visually determined they are the only means to assure safe separation CAUTION Once a non crossing RA has been issued the vertical speed should be accurately adjusted to comply with the RA in order to avoid negating the effectiveness of a co ordinated maneuvre by the intruder WARNING Non compliance with a crossing RA by one airplane may result in reduced vertical separation Therefore safe horiz...

Page 582: ...r stick pusher shaker failure The table below entitled Flight Envelope in which climb resolution advisory can be accomplished without stick pusher shaker activation outlines the parameters used in the development of the performance inhibits This table does not consider worst turboprop flight conditions especially operations using minimum operating airspeeds as are sometimes required e g obstacle c...

Page 583: ...evel flight 15 UP 1 51 VSR 1 13 VSR Landing Transitioning to go around at RA FAR25 JAR 25 Climb limit Spin up to go around power during maneuver from power required for 3 Glide Slope Transition from 30 to 15 DN to Up VAPP 10 1 13 VSR Enroute Critical Wt Alt giving 1 3G to buffet onset Power for level flight increase to Max Continuous Up Up Long Range Cruise Higher of 1 13 VSR if defined or buffet ...

Page 584: ... CONFIGURATION RA CLIMB RA INCREASE CLIMB FLAPS 0 FLAPS 15 TO FLAPS 25 TO FLAPS 15 Approach FLAPS 25 Approach FLAPS 25 Landing FLAPS 35 Landing AUTHORIZED AUTHORIZED AUTHORIZED AUTHORIZED AUTHORIZED AUTHORIZED AUTHORIZED AUTHORIZED INHIBITED INHIBITED INHIBITED INHIBITED INHIBITED INHIBITED NOTE 1 Pilots are authorized to deviate from their current ATC clearance to the extent necessary to comply w...

Page 585: ...le with the addition of the following The TCAS must be turned TA ONLY in the following cases Engine out operations Stick pusher shaker failure Flight with landing gear down The TCAS must be turned STBY in the following cases ATC request ADC 1 failure LOSS OF RADIO ALTIMETER INFORMATION Errors or differences between independant air data sources PERFORMANCES The performances in Part 3 are applicable...

Page 586: ... applicable with the addition of the following The TCAS must be turned TA ONLY in the following cases Engine out operations Stick pusher shaker failure Flight with landing gear down The TCAS must be turned STBY in the following cases ATC request LOSS OF RADIO ALTIMETER INFORMATION Errors or differences between independant air data sources PERFORMANCES The performances in Part 3 are applicable AA A...

Page 587: ... 500 GPS LIMITATIONS GLOBAL POSITIONING SYSTEM P 1 NOV 98 001 2 01 07 LEFT INTENTIONALLY BLANK AA AviationLearning net 01 07 2018 REV 1 These notes are not revised after issue For Training Purposes Only Page 559 of 764 ...

Page 588: ...tion means en route and terminal area up to the Initial Approach Fix IAF The system must not be used for approaches beyond IAF No specific monitoring is required as long as the RAIM warning is OFF If RAIM warning appears navigation must be crosschecked with usual means Data base updating must be verified before each flight AA R R R AviationLearning net 01 07 2018 REV 1 These notes are not revised ...

Page 589: ... 400 500 GPS LIMITATIONS GLOBAL POSITIONING SYSTEM P 1 NOV 99 090 2 01 07 LEFT INTENTIONALLY BLANK AA AviationLearning net 01 07 2018 REV 1 These notes are not revised after issue For Training Purposes Only Page 561 of 764 ...

Page 590: ...ts position should be cross checked with official charts This equipment is approved for use as a VFR and IFR supplemental navigation means en route and in terminal area up to the Initial Approach Fix IAF The system must not be used for approaches beyond IAF This system may be used as a primary means of navigation for oceanic remote area where only one navigation system is required This statement d...

Page 591: ... terminal area up to the Initial Approach Fix IAF The system must not be used for approaches beyond IAF The CDI scale factor selectable in the MOD pages must not be set at the 0 3 NM full scale deflection value 3 PROCEDURES If the RAIM function is lost the flight crew must cross check the aircraft position using conventional means or must revert to an alternative means of navigation The following ...

Page 592: ...This equipment is approved for use as a VFR and IFR supplemental navigation means en route and in terminal area up to the Initial Approach Fix IAF The system must not be used for approaches beyond IAF 3 PROCEDURES In the event of DGR alarm illumination the flight crew must cross check the aircraft position using conventional means or must revert to an alternative means of navigation In addition wh...

Page 593: ...vigation means en route in terminal area and for non precision approach operations until the missed approach point with respect of the MDA NOTE Stand alone GPS approach is not approved Conventional means must be permanently cross checked during the approach advisory VNAV means NOTE VDEV function must be permanently monitored 3 PROCEDURES In the event of DGR alarm illumination the flight crew must ...

Page 594: ...area up to the Initial Approach Fix IAF The system must not be used for approaches beyond IAF The CDI scale factor selectable in the MOD pages must not be set at the 0 3 NM full scale deflection value 3 PROCEDURES If the RAIM function is lost the flight crew must cross check the aircraft position using conventional means or must revert to an alternative means of navigation The following procedures...

Page 595: ...l 400 500 CABIN LIGHTING LIMITATIONS P 1 NOV 99 001 2 01 08 CABIN LIGHTING NOT APPLICABLE AA AviationLearning net 01 07 2018 REV 1 These notes are not revised after issue For Training Purposes Only Page 567 of 764 ...

Page 596: ...S P 1 NOV 99 100 2 01 08 CABIN LIGHTING The general cabin illumination system must be used during not less than 15 minutes before each flight AA AviationLearning net 01 07 2018 REV 1 These notes are not revised after issue For Training Purposes Only Page 568 of 764 ...

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Page 617: ...Fail A F F Left Main Gear WOW 2 Prox Switch Fail B F F F Nose Gear WOW 2 Prox Switch Fail C F F Right Main Gear WOW 2 Prox Switch Fail D E SYS DOORS CODE 8 4 2 1 DEFINITION 1 F 2 F 3 F F Left Aft Door Unlock Prox Switch 1 Fail 4 F Left Aft Door Unlock Prox Switch 2 Fail 5 F F 6 F F 7 F F F Right Aft Door Unlock Prox Switch 1 Fail 8 F Right Aft Door Unlock Prox Switch 2 Fail 9 F F Emergency Hatch P...

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Page 626: ...O ALTIMETER 30 1 DESCRIPTION 30 2 ELECTRICAL SUPPLY 1 15 40 GROUND PROXIMITY WARNING SYSTEM 40 1 DESCRIPTION 40 2 CONTROLS 40 3 ELECTRICAL SUPPLY SYSTEM MONITORING 40 4 SCHEMATIC 1 15 50 WEATHER RADAR 50 1 DESCRIPTION 50 2 CONTROLS 50 3 ELECTRICAL SUPPLY 1 15 60 GLOBAL NAVIGATION SATELLITE SYSTEM GNSS 60 1 DESCRIPTION 60 2 CONTROLS 60 3 ELECTRICAL SUPPLY 60 4 SCHEMATIC AA AviationLearning net 01 0...

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Page 637: ...n the ACT button the bottom window displays dashes the knobs directly act on the active frequency A second push on the button enables return to normal operation TEST button Is used to initiate the radio self test diagnostic routine Annonciators MEM Memory illuminates when a preset frequency is being displayed in the lower window RMT Remote illuminates when the ADF control box is being remotely con...

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Page 642: ...ADC 1 ILS 2 radio altimeter flaps position transmitter and gear lever position transmitter Mode 5 is active whenever a valid ILS glideslope signal is supplied If the ILS converter signals no computed data mode 5 alert is inhibited The mode 5 alert is also inhibited in back course operation Visual alert is provided In mode 1 2 3 or 4 by illumination of the GPWS red lights one on each pilots panel I...

Page 643: ...penetrated the WHOOP WHOOP PULL UP alert is given This mode does not depend on the aircraft configuration MODE 2 EXCESSIVE TERRAIN CLOSURE RATE D FLAPS NOT IN LANDING CONFIGURATION When the aircraft penetrates the envelope the TERRAIN voice alert is given twice and the red GPWS warning lts illuminate As long as the aircraft remains in the envelope the WHOOP WHOOP PULL UP warning is given When the ...

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Page 649: ...nate on both pilots panels Voice alert GLIDE SLOPE is given One second time delay GPWS red lights illuminate on both pilots panels Voice alert WHOOP WHOOP PULL UP is given several times GPWS red lights extinguish G S lights and GPWS FAULT light will extinguish as soon as the pb is released Below 1000 ft will inhibit the mode 5 alerts aural and visual GPWS SELECTOR The selector is guarded in the NO...

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Page 651: ...S red lights illuminate on both pilots panels Voice alert WHOOP WHOOP PULL UP is given several times GPWS red lights extinguish G S lights and GPWS FAULT light will extinguish as soon as the pb is released Below 1000 ft will inhibit the mode 5 alerts aural and visual GPWS SELECTOR The selector is guarded in the NORM position NORM All alerts are operative FLAP OVRD Mode 4 alert caused by flap exten...

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Page 656: ... path Weather impediments are displayed on the EHSI S in ARC mode in 4 colors according to the intensity of rain detected Weather radar can also be used in MAP mode to display ground obstacles System is controlled with the weather radar control panel Modes selected on this panel are displayed on the EHSI AA AviationLearning net 01 07 2018 REV 1 These notes are not revised after issue For Training ...

Page 657: ...l 3 Red Strong storm Level 4 Magenta Intense storm On the ground the system is automatically forced in SBY position for safety If needed it is possible to restore the active WX mode by pushing the STAB button four times in three seconds GMAP position GMAP displayed green on the EFIS Selects the ground mapping mode using four different levels Level 0 Black No return Level 1 Cyan Least reflective re...

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Page 660: ... it passes through rain fall The cyan field indicates areas where further compensation is not possible Any target detected in these areas will be displayed in magenta and should be considered dangerous STAB push button Turns the pitch and roll stability ON and OFF TGT push button Activates and deactivates the radar target alert mode When activated TGT is displayed green on the EFIS and the system ...

Page 661: ...er to indicate that radar is not working when Ąit is either selected ON on EFIS Control Panel ECP but OFF on Radar Control box or selected ON on both ECP and Radar Control box but antenna is not scanning D G MAP green enables to display the ground obstacles D RCT green Rain Echo Attenuation Compensation Technique mode is engaged D TX magenta illuminates when radar operates with the screen dimmed D...

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Page 664: ...Model 400 500 WEATHER RADAR NAVIGATION SYSTEM P 5 NOV 99 010 1 15 50 LEFT INTENTIONALLY BLANK AA AviationLearning net 01 07 2018 REV 1 These notes are not revised after issue For Training Purposes Only Page 636 of 764 ...

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Page 666: ...ing the KLN 90 with the computer via an interface cable Each data base contains information about airports communication frequencies VORs NDBs Intersections flight service stations SID and STAR There is also room for up to 250 user defined way points and 25 different flight plans with 30 waypoints each Finally KLN 90 receives indications from ADC and AHRS and gives information to autopilot and SGU...

Page 667: ... concentric knobs and the cursor button to the left of the screen are used to select data on LH page just as the right knobs and cursor on the right control the RH page The selected page is displayed at the bottom of the screen The large outer knobs control the chapters and the small inner knobs turn the pages To change data in a page use the cursor function This function is an area of inverse vid...

Page 668: ...ctive date periods are displayed on the MCDU IDENT page The navigation is normally performed using the GPS sensor GPS mode In the case where the GPS position becomes unavailable the dead reckoning mode DR is used like a back up utilizing true airspeed heading and the last computed wind data FUNCTIONS HT 1000 is capable of performing all the functions associated with the great circle navigation It ...

Page 669: ...terface for operation and data entry of the HT 1000 and also displays routes and advisory data on a color 5 5 liquid crystal display The display has 14 lines of data with 24 characters per line The MCDU keyboards provides for data input and display selection and control AA AviationLearning net 01 07 2018 REV 1 These notes are not revised after issue For Training Purposes Only Page 641 of 764 ...

Page 670: ...yed on the MCDU IDENT page The navigation is normally performed using the GPS sensor GPS mode In the case where the GPS position becomes unavailable the HT 1000 reverts to DME DME mode if the radio coverage allows it If not the dead reckoning mode DR is used like a back up utilizing true airspeed heading and the last computed wind data FUNCTIONS HT 1000 is capable of performing all the functions a...

Page 671: ...terface for operation and data entry of the HT 1000 and also displays routes and advisory data on a color 5 5 liquid crystal display The display has 14 lines of data with 24 characters per line The MCDU keyboards provides for data input and display selection and control AA AviationLearning net 01 07 2018 REV 1 These notes are not revised after issue For Training Purposes Only Page 643 of 764 ...

Page 672: ...U IDENT page The navigation is normally performed using the GPS sensor GPS mode In the case where the GPS position becomes unavailable the dead reckoning mode DR is used like a back up utilizing true airspeed heading and the last computed wind data FUNCTIONS HT 1000 is capable of performing all the functions associated with the great circle navigation It mainly allows to perform Direct To navigati...

Page 673: ...terface for operation and data entry of the HT 1000 and also displays routes and advisory data on a color 5 5 liquid crystal display The display has 14 lines of data with 24 characters per line The MCDU keyboards provides for data input and display selection and control AA AviationLearning net 01 07 2018 REV 1 These notes are not revised after issue For Training Purposes Only Page 645 of 764 ...

Page 674: ... ARC display on EHSI In MAP selection waypoints of the flight plan are displayed in white except the active waypoint which is magenta V L pb Action on this pushbutton causes selection of the VOR LOC mode RNV pb Action on this pushbutton causes selection of the GPS mode Refer to 1 10 30 AA 1 2 3 4 AviationLearning net 01 07 2018 REV 1 These notes are not revised after issue For Training Purposes On...

Page 675: ...n only one crew member uses GPS It becomes amber when both Pilot and F O use GPS as navigation source Distance counter Indicates the distance computed by GPS to the next waypoint Next waypoint magenta indicates a VOR indicates an airport indicates an ADF an intersection or a user defined waypoint AA 1 2 3 AviationLearning net 01 07 2018 REV 1 These notes are not revised after issue For Training Pu...

Page 676: ... ARC display on EHSI In MAP selection waypoints of the flight plan are displayed in white except the active waypoint which is magenta V L pb Action on this pushbutton causes selection of the VOR LOC mode RNV pb Action on this pushbutton causes selection of the GPS mode Refer to 1 10 30 AA 1 2 3 4 AviationLearning net 01 07 2018 REV 1 These notes are not revised after issue For Training Purposes On...

Page 677: ...n only one crew member uses GPS It becomes amber when both Pilot and F O use GPS as navigation source Distance counter Indicates the distance computed by GPS to the next waypoint Next waypoint magenta indicates a VOR indicates an airport indicates an ADF an intersection or a user defined waypoint AA 1 2 3 AviationLearning net 01 07 2018 REV 1 These notes are not revised after issue For Training Pu...

Page 678: ...y and ARC display on EHSI In MAP selection waypoints of the flight plan are displayed in white except the active waypoint which is magenta V L pb Action on this pushbutton causes selection of the VOR LOC mode RNV pb Action on this pushbutton causes selection of the GNSS mode Refer to 1 10 30 AA 1 2 3 4 AviationLearning net 01 07 2018 REV 1 These notes are not revised after issue For Training Purpo...

Page 679: ...rmation is blue when only one crew member uses GNSS It becomes amber when both Pilot and F O use GNSS as navigation source Distance counter Indicates the distance computed by GNSS to the next waypoint Waypoints G next waypoint magenta G other waypoint white f indicates an airport indicates a VOR AA 1 2 3 AviationLearning net 01 07 2018 REV 1 These notes are not revised after issue For Training Pur...

Page 680: ...y and ARC display on EHSI In MAP selection waypoints of the flight plan are displayed in white except the active waypoint which is magenta V L pb Action on this pushbutton causes selection of the VOR LOC mode RNV pb Action on this pushbutton causes selection of the GNSS mode Refer to 1 10 30 AA 1 2 3 4 AviationLearning net 01 07 2018 REV 1 These notes are not revised after issue For Training Purpo...

Page 681: ...n is blue when only one crew member uses GNSS It becomes amber when both Pilot and F O use GNSS as navigation source Distance counter Indicates the distance computed by GNSS to the next waypoint Waypoints G next waypoint magenta G other waypoint white f indicates an airport indicates a VOR AA 1 2 3 AviationLearning net 01 07 2018 REV 1 These notes are not revised after issue For Training Purposes ...

Page 682: ...and a figure indicates the direction and the velocity in kt of the wind VOR symbols Only VOR DME will be presented on the MAP display VOR 1 is displayed in blue VOR 2 is displayed in green WPT alerting Illuminates amber when approaching a waypoint TO FROM indicator magenta Drift angle indicator magenta Radar s range selector may be used to select the distance scale AA 4 5 6 7 8 9 10 11 AviationLea...

Page 683: ...r when both Capt and F O use GPS as navigation source Distance counter Indicates the distance computed by GPS to the next waypoint Ground speed indicator Indicates the ground speed calculated by the GPS Desired track indication Lateral deviation to the track WPT alerting Illuminates amber when approaching a waypoint TO FROM annunciator AA 1 2 3 4 5 6 7 AviationLearning net 01 07 2018 REV 1 These n...

Page 684: ... DME or RNV waypoints will be presented on the MAP display VOR RNV 1 is displayed in blue VOR RNV 2 is displayed in green WPT DGR alerting WPT illuminates amber when approaching a waypoint DGR illuminates amber when the UNABLE RNP message is displayed on the MCDU TO FROM indicator magenta Drift angle indicator magenta Radar s range selector may be used to select the distance scale DME 1 2 Indicate...

Page 685: ... by GPS to the next waypoint Ground speed indicator Indicates the ground speed calculated by the GPS Desired track indication Lateral deviation to the track WPT DGR alerting WPT illuminates amber when approaching a waypoint DGR illuminates amber when the UNABLE RNP message is displayed on the MCDU TO FROM annunciator RADAR status APP OFS APP illuminates cyan when in approach phase Not applicable O...

Page 686: ...ection and the velocity in kt of the wind VOR symbols Only VOR DME will be presented on the MAP display VOR 1 is displayed in blue VOR 2 is displayed in green WPT or DGR alerting WPT illuminates amber when approaching a waypoint DGR illuminates amber when the integrity is lost TO FROM indicator magenta Drift angle indicator magenta Radar s range selector may be used to select the distance scale AA...

Page 687: ...r when both Capt and F O use GPS as navigation source Distance counter Indicates the distance computed by GPS to the next waypoint Ground speed indicator Indicates the ground speed calculated by the GPS Desired track indication Lateral deviation to the track WPT alerting Illuminates amber when approaching a waypoint TO FROM annunciator AA 1 2 3 4 5 6 7 AviationLearning net 01 07 2018 REV 1 These n...

Page 688: ...e presented on the MAP display VOR RNV 1 is displayed in blue VOR RNV 2 is displayed in green WPT DGR alerting WPT illuminates amber when approaching a waypoint DGR illuminates amber when the UNABLE RNP message is displayed on the MCDU TO FROM indicator magenta Drift angle indicator magenta Radar s range selector may be used to select the distance scale DME 1 2 Indicates the distance given by DME ...

Page 689: ...by GPS to the next waypoint Ground speed indicator Indicates the ground speed calculated by the GPS Desired track indication Lateral deviation to the track WPT DGR alerting WPT illuminates amber when approaching a waypoint DGR illuminates amber when the UNABLE RNP message is displayed on the MCDU TO FROM annunciator RADAR status APP OFS APP illuminates cyan when in approach phase OFS illuminates c...

Page 690: ... when both Capt and F O use GPS as navigation source Distance counter Indicates the distance computed by GPS to the next waypoint Ground speed indicator Indicates the ground speed calculated by the GPS Desired track indication Lateral deviation to the track WPT alerting Illuminates amber when approaching a waypoint TO FROM annunciator AA 1 2 3 4 5 6 7 AviationLearning net 01 07 2018 REV 1 These no...

Page 691: ...SYSTEM P 8 MAY 98 080 1 15 60 GPS RAIM FAULT lights RAIM Receiver Autonomous Integrity Monitoring FAULT illuminate amber when RAIM function is lost AA R AviationLearning net 01 07 2018 REV 1 These notes are not revised after issue For Training Purposes Only Page 663 of 764 ...

Page 692: ... when both Capt and F O use GPS as navigation source Distance counter Indicates the distance computed by GPS to the next waypoint Ground speed indicator Indicates the ground speed calculated by the GPS Desired track indication Lateral deviation to the track WPT alerting Illuminates amber when approaching a waypoint TO FROM annunciator AA 1 2 3 4 5 6 7 AviationLearning net 01 07 2018 REV 1 These no...

Page 693: ...NV MSG illuminates amber on EADI when a message appears on the GPS screen or when RAIM function is lost RNV MSG will extinguish when these cases are taken into account MSG pb on GPS control panel AA AviationLearning net 01 07 2018 REV 1 These notes are not revised after issue For Training Purposes Only Page 665 of 764 ...

Page 694: ...by GPS to the next waypoint Ground speed indicator Indicates the ground speed calculated by the GPS Desired track indication Lateral deviation to the track WPT DGR alerting WPT illuminates amber when approaching a waypoint DGR illuminates amber when the UNABLE RNP message is displayed on the MCDU TO FROM annunciator RADAR status APP OFS APP illuminates cyan when in approach phase Not applicable OF...

Page 695: ...iated when the pilot entered RNP is greater than default current RNP VERIFY RNP POS REF message annunciated when flight phase changes and current pilot entered RNP is greater than the default RNP for new flight mode UNABLE APPROACH message annunciated when within 2 NM from the FAF and RAIM prediction at FAF MAP fails or navigation source is not GPS In addition there are some advisory messages such...

Page 696: ... when both Capt and F O use GPS as navigation source Distance counter Indicates the distance computed by GPS to the next waypoint Ground speed indicator Indicates the ground speed calculated by the GPS Desired track indication Lateral deviation to the track WPT alerting Illuminates amber when approaching a waypoint TO FROM annunciator AA 1 2 3 4 5 6 7 AviationLearning net 01 07 2018 REV 1 These no...

Page 697: ...hts RNV MSG illuminates amber on EADI when a message appears on the GPS screen or when RAIM function is lost RNV MSG will extinguish when these cases are taken into account MSG pb on GPS control panel AA AviationLearning net 01 07 2018 REV 1 These notes are not revised after issue For Training Purposes Only Page 669 of 764 ...

Page 698: ...y GPS to the next waypoint Ground speed indicator Indicates the ground speed calculated by the GPS Desired track indication Lateral deviation to the track WPT DGR alerting WPT illuminates amber when approaching a waypoint DGR illuminates amber when the UNABLE RNP message is displayed on the MCDU TO FROM annunciator RADAR status APP OFS APP illuminates cyan when in approach phase OFS illuminates cy...

Page 699: ...G message annunciated when NAV source becomes dead reckoning GPS and DME modes are lost VERIFY RNP ENTRY message annunciated when the pilot entered RNP is greater than default current RNP VERIFY RNP POS REF message annunciated when flight phase changes and current pilot entered RNP is greater than the default RNP for new flight mode UNABLE APPROACH message annunciated when within 2 NM from the FAF...

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Page 701: ...YSTEM GLOBAL POSITIONING SYSTEM P 10 NOV 00 080 1 15 60 60 4 LATERAL MAINTENANCE PANEL This jack enables to connect a computer to update the data base AA AviationLearning net 01 07 2018 REV 1 These notes are not revised after issue For Training Purposes Only Page 673 of 764 ...

Page 702: ...EM GLOBAL NAVIGATION SATELLITE SYSTEM P 9 NOV 00 090 1 15 60 60 3 ELECTRICAL SUPPLY EQUIPMENT DC BUS SUPPLY GNSS DC STBY BUS on overhead panel GPS AA AviationLearning net 01 07 2018 REV 1 These notes are not revised after issue For Training Purposes Only Page 674 of 764 ...

Page 703: ...Model 400 500 GNSS NAVIGATION SYSTEM GLOBAL NAVIGATION SATELLITE SYSTEM P 10 NOV 00 090 1 15 60 LEFT INTENTIONALLY BLANK AA AviationLearning net 01 07 2018 REV 1 These notes are not revised after issue For Training Purposes Only Page 675 of 764 ...

Page 704: ...liability One of the received and used satellites is not valid The position is erroneous If a local message or a system failure are detected There are no priority of displayed message for RAIM function D RNV MSG light illuminates amber The crew can find the right origin of the alert by viewing the MESSAGE page of the GPS In that case the crew may consider GPS information but must crosscheck with u...

Page 705: ...YSTEM GLOBAL POSITIONING SYSTEM P 10 NOV 00 080 1 15 60 60 4 LATERAL MAINTENANCE PANEL This jack enables to connect a computer to update the data base AA AviationLearning net 01 07 2018 REV 1 These notes are not revised after issue For Training Purposes Only Page 677 of 764 ...

Page 706: ...T RAIM POS REF message annunciated within 30 NM of destination airport if active route contains approach and approach RAIM predicted to be non available for some period of time within 15 minutes of destination ETA RNV MSG will extinguish when the associated MCDU message is cancelled 60 3 ELECTRICAL SUPPLY EQUIPMENT DC BUS SUPPLY GNSS DC STBY BUS on overhead panel GPS AA R R R R R R R R AviationLea...

Page 707: ...Model 400 500 GNSS NAVIGATION SYSTEM GLOBAL NAVIGATION SATELLITE SYSTEM P 10 NOV 00 090 1 15 60 LEFT INTENTIONALLY BLANK AA AviationLearning net 01 07 2018 REV 1 These notes are not revised after issue For Training Purposes Only Page 679 of 764 ...

Page 708: ...e of the received and used satellites is not valid The position is erroneous If a local message or a system failure are detected There are no priority of displayed message for RAIM function D RNV MSG illuminates amber on EADI D DGR illuminates amber on EHSI The crew can find the right origin of the alert by viewing the MESSAGE page of the GPS In that case the crew may consider GPS information but ...

Page 709: ...YSTEM GLOBAL POSITIONING SYSTEM P 10 NOV 00 080 1 15 60 60 4 LATERAL MAINTENANCE PANEL This jack enables to connect a computer to update the data base AA AviationLearning net 01 07 2018 REV 1 These notes are not revised after issue For Training Purposes Only Page 681 of 764 ...

Page 710: ...odel 500 GPS NAVIGATION SYSTEM GLOBAL POSITIONING SYSTEM P 11 12 MAI 98 080 1 15 60 60 5 SCHEMATIC AA AviationLearning net 01 07 2018 REV 1 These notes are not revised after issue For Training Purposes Only Page 682 of 764 ...

Page 711: ...odel 400 500 GNSS NAVIGATION SYSTEM GLOBAL NAVIGATION SATELLITE SYSTEM P 11 12 NOV 01 090 1 15 60 60 4 SCHEMATIC AA R R R R AviationLearning net 01 07 2018 REV 1 These notes are not revised after issue For Training Purposes Only Page 683 of 764 ...

Page 712: ...42 Model 400 500 GPS NAVIGATION SYSTEM GLOBAL POSITIONING SYSTEM P 11 12 NOV 00 100 1 15 60 ă 60 5 SCHEMATIC AA AviationLearning net 01 07 2018 REV 1 These notes are not revised after issue For Training Purposes Only Page 684 of 764 ...

Page 713: ... ATR 42 Model 400 500 GNSS NAVIGATION SYSTEM GLOBAL NAVIGATION SATELLITE SYSTEM P 11 12 NOV 01 110 1 15 60 60 4 SCHEMATIC AA AviationLearning net 01 07 2018 REV 1 These notes are not revised after issue For Training Purposes Only Page 685 of 764 ...

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Page 721: ...ogging indicator is provided on pilot s panel The Hydro Mechanical Unit HMU which has two functions to meter the fuel flow delivery to the engine by a metering valve assembly 4 the excess being returned to HP pump inlet to provide the HP motive flow required by the fuel tank jet pump through an engine valve 5 A fuel flowmeter 6 A Fuel Cooled Oil Cooler FCOC 7 that provides cooling of the lubricati...

Page 722: ...7 bearing cavity and the reduction gear box on which gear pumps are used 20 4 IGNITION SYSTEM Each engine is equipped with a high energy ignition system It consists of two engine mounted ignition exciters A and B powered by the DC ESS BUS and two spark igniters one for each ignition exciter Ignition cycle includes two phases During 25 sec the intensity is 5 to 6 sparks sec and then the intensity b...

Page 723: ...ature indication is provided A HP pump 3 with a filter a clogging indicator is provided on pilot s panel The Hydro Mechanical Unit HMU which has two functions to meter the fuel flow delivery to the engine by a metering valve assembly 4 the excess being returned to HP pump inlet to provide the HP motive flow required by the fuel tank jet pump through an engine valve 5 A fuel flowmeter 6 A flow divi...

Page 724: ...g cavity and the reduction gear box on which gear pumps are used 20 4 IGNITION SYSTEM Each engine is equipped with a high energy ignition system It consists of two engine mounted ignition exciters A and B powered by the DC ESS BUS and two spark igniters one for each ignition exciter Ignition cycle includes two phases During 25 sec the intensity is 5 to 6 sparks sec and then the intensity becomes 1...

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Page 740: ...olled by the hydromechanical channel in accordance with commands transmitted by the EEC Ensures engine shutdown HP fuel S O Delivers a motive flow to the fuel tank jet pump ENGINE ELECTRONIC CONTROL EEC Regulates a given power by controlling the stepper motor to obtain a predicted torque as a function of D the power lever position D the PWR MGT selector position D flight conditions D the position ...

Page 741: ...ndling Bleed valve HBV so as to ensure correct LP compressor operation PROPELLER VALVE MODULE PVM At high power controls the propeller maximum speed Np according to the PWR MGT selection Controls propeller pitch at low power and when using reverse Ensures low pitch through a solenoid when PLA are below FI position PWR MGT SELECTOR LINE A One engine out operation LINE B Normal TO or CLB LINE C CRZ1...

Page 742: ...ncelled out at FI In case of engine torque control failure In Hotel mode According to the rating selected on the PWR MGT rotary selector with the PL at a set point the EEC commands a determined engine power and therefore a torque value for a given propeller speed Thus the torque which is the engine control parameter is controlled with PLA constant in all ambient conditions AA 1 R AviationLearning ...

Page 743: ...f the Handling Bleed valve HBV so as to ensure correct LP compressor operation PROPELLER VALVE MODULE PVM At high power controls the propeller maximum speed Np according to the PWR MGT selection Controls propeller pitch at low power and when using reverse Ensures low pitch through a solenoid when PLA are below FI position PWR MGT SELECTOR LINE A One engine out operation LINE B Normal TO or CLB LIN...

Page 744: ...ncelled out at FI In case of engine torque control failure In Hotel mode According to the rating selected on the PWR MGT rotary selector with the PL at a set point the EEC commands a determined engine power and therefore a torque value for a given propeller speed Thus the torque which is the engine control parameter is controlled with PLA constant in all ambient conditions AA 1 R AviationLearning ...

Page 745: ...dling Bleed Valve HBV so as to ensure correct LP compressor operation PROPELLER VALVE MODULE PVM At high power controls the propeller maximum speed Np according to the PWR MGT selection Controls propeller pitch at low power and when using reverse Ensures low pitch through a solenoid when PLA are below FI position PWR MGT SELECTOR LINE A One engine out operation LINE B Normal TO or MCT LINE C CLB o...

Page 746: ...ncelled out at FI In case of engine torque control failure In Hotel mode According to the rating selected on the PWR MGT rotary selector with the PL at a set point the EEC commands a determined engine power and therefore a torque value for a given propeller speed Thus the torque which is the engine control parameter is controlled with PLA constant in all ambient conditions AA 1 R AviationLearning ...

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Page 758: ... for 2 15 seconds but uptrim is energized on the remaining engine This feature enables to perform an acceleration stop without having autofeather in order to benefit from some reversing action on the failed engine In this case the throttle reduction occuring within 2 15 seconds period automatically disarms the mode Once the mode has been triggered its cancellation can only result from either PWR M...

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Page 760: ... for 2 15 seconds but uptrim is energized on the remaining engine This feature enables to perform an acceleration stop without having autofeather in order to benefit from some reversing action on the failed engine In this case the throttle reduction occuring within 2 15 seconds period automatically disarms the mode Once the mode has been triggered its cancellation can only result from either PWR M...

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Page 767: ...ed dot 137 FDAU target Displays the maximum torque value computed by the FDAU depending on the PWR MGT selection except on the T O position where reserve T O torque is displayed Notes 1 In case of FDAU target failure associated with a pointer misfunctioning an AFU failure may be suspected see page 1 2 15 sec are necessary to obtain a valid FDAU target indication on non affected side after a rotary...

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Page 769: ...radial 114 2 Red dot 132 4 FDAU target Displays the maximum torque value computed by the FDAU depending on the PWR MGT selection except on the T O position where reserve T O torque is displayed Notes 1 In case of FDAU target failure associated with a pointer misfunctioning an AFU failure may be suspected see page 1 2 15 sec are necessary to obtain a valid FDAU target indication on non affected sid...

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Page 771: ...00 C Temperature limit in uptrim conditions Red point 840 C Temperature limit for 20 sec Red point S 950 C Temperature limit for 5 sec for start Alert It Illuminates amber and the CCAS is activated when ITT 800 C or 715 C in hotel mode Test pb Allows to test the ind During test both counter and pointer will displayed 1150 C Note A blue dot is provided on the ind scale to identify 1150 C AA 1 2 R 3...

Page 772: ...e to identify 115 OIL IND OIL PRESS indication Actual oil pressure is displayed Green sector 55 65 PSI Amber sector 40 55 PSI Red mark 40 PSI Dashed white red radial at 55 PSI OIL LOW PRESS lt Illuminates red when OIL PRESS indication drops below 40 PSI A separate pressure switch activates the CCAS at 40 PSI OIL TEMP indication Actual oil temperature is displayed Green sector 45 125_C Amber sector...

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