DASSAULT AVIATION Proprietary Data
|
|
- Trevor Blake
- 5 years ago
- Views:
Transcription
1 F2000EX EASY CODDE 1 PAGE 1 / 2 TABLE OF CONTENTS TABLE OF CONTENTS GENERAL Introduction Sources Equipment location DESCRIPTION Introduction Description Operating principle APU systems Distribution CONTROL AND INDICATION Control Indication SYSTEM PROTECTION Circuit breakers APU ECU protections NORMAL OPERATION Starting sequence Shutdown Limitations ABNORMAL OPERATION APU start with GPU APU starting sequence failed APU normal shutdown failed APU overspeed APU fire CAS messages
2 F2000EX EASY PAGE 2 / 2 CODDE 1 TABLE OF CONTENTS INTENTIONALLY LEFT BLANK
3 F2000EX EASY CODDE 1 PAGE 1 / 4 GENERAL INTRODUCTION The Auxiliary Power Unit (APU) allows the Falcon 2000EX airplane to be self-supported (providing electrical power and bleed air) during ground operations especially at remote locations where ground servicing equipment may not be compatible or available. It also provides backup electrical power and main engine starting bleed air in flight.
4 F2000EX EASY PAGE 2 / 4 CODDE 1 GENERAL APU circuit breaker APU fire DC supply overhead panel APU control panel CAS window ENG synoptic ENG-TRIM-BRK window FIGURE FLIGHT DECK OVERVIEW
5 F2000EX EASY CODDE 1 PAGE 3 / 4 GENERAL SOURCES The APU inputs are independent of all installed airplane systems except for the electrical power source used during starting and fuel supply from the airplane fuel tanks. ELECTRICAL POWER APU starting requires electrical power supplied either: - by battery 1 through the battery bus, - by a Ground Power Unit via the ESSential bus. FUEL Fuel is supplied to the APU by the No. 2 engine fuel feed line. Refer to CODDE 1 / Chapter 02 / ATA 28 EQUIPMENT LOCATION FIGURE APU LOCATION The APU is longitudinally mounted underneath the fin, inside the tail cone.
6 F2000EX EASY PAGE 4 / 4 CODDE 1 GENERAL INTENTIONALLY LEFT BLANK
7 F2000EX EASY CODDE 1 PAGE 1 / 4 DESCRIPTION INTRODUCTION The Falcon 2000EX incorporates an APU model GTCP (F2M) manufactured by Honeywell. The unit is longitudinally mounted in the tail cone within a carbon fireproof compartment. The APU is certified for both ground and in-flight operations. DESCRIPTION The APU consists of an air intake, located in the middle of the unit, a centrifugal compressor and its discharge port for bleed air, a combustion chamber, a single stage turbine, an exhaust duct and an accessory section. The accessories include the APU fuel control unit, the fuel pump, the oil pump and the starter-generator. Air intake door APU bleed air valve Upper left compartment inlet ventilation Gearbox Exhaust duct Generator inlet ventilation Compressor Lower right compartment inlet ventilation Firewall Starter generator Generator outlet ventilation FIGURE APU LAYOUT
8 F2000EX EASY PAGE 2 / 4 CODDE 1 DESCRIPTION Air inlets are located on the right and left hand side of the tail cone. Two air scoops on tail cone (upper LH and lower RH sides) provide APU compartment ventilation. The engine air intake door is located on the right hand upper side of the APU compartment. The APU exhaust duct for engine gases and ventilation circulation is located at the rear of the cone. The APU generator has its own ventilation system. The air flows through a duct from the LH inlet ahead of the tail cone. The RH outlet below the APU air intake allows for exhaust of APU generator ventilation system. A door opens on LH side for APU oil filling. LH ventilation scoop APU engine exhaust APU air intake door APU generator inlet Oil filler door APU generator exhaust outlet RH ventilation scoop FIGURE EXHAUST OUTLET AND AIR INLET The hot bleed air necessary for main engine start and air conditioning is tapped from compressor discharge.
9 F2000EX EASY CODDE 1 PAGE 3 / 4 DESCRIPTION OPERATING PRINCIPLE The starter-generator first drives the APU. Once APU speed has reached 5.6% N1, the fuel induction begins and ignition is turned on. At 50% N1, energy extracted from exhaust gases is sufficient to drive the compressor and the starter operation is terminated. When the engine reaches 99% N1, ignition is terminated. APU stabilizes to regulated N1 (below 106%). The stabilized exhaust gas temperature (EGT) may vary depending on whether hot air is taken or not for air conditioning and on the ambient air temperature. The engine then operates on a cycle of continuous induction, compression, combustion and exhaust at a constant rpm. In flight, airbrakes extension (position 2) may induce an increase of around 20 C EGT. When APU BLEED AIR is selected, bleed air is available for engine start or air conditioning. The APU generator self-connects to the ESS bus. When the APU generator is on line, LH, ESS and battery buses are powered, BAT 1 is charging. Depending on bus tied rotary switch position, the same applies to right side buses and BAT 2. If the start relay fails to open, the amber STARTER APU message appears in the CAS message window. If APU generator fails to connect, the amber APU GEN displayed in the CAS message window. message is then APU SYSTEMS OIL SYSTEM The oil system provides cooling and lubrication of the main rotor bearings and accessory gearbox. A switch located downstream from the oil system indicates when oil pressure decreases below the minimum operating value. If so, the APU is automatically shut down. A thermostat, inside the oil sump, controls the temperature. If oil temperature exceeds the maximum operating value, the APU is automatically shut down. An electrical level measuring plug is fitted on the APU oil tank filler cap. The APU OIL status can be checked on the TEST synoptic before APU start. Measuring plug Filler cap FIGURE APU OIL FILLER PORT
10 F2000EX EASY PAGE 4 / 4 CODDE 1 DESCRIPTION FUEL SYSTEM Fuel is supplied to the APU by the No 2 engine fuel feed line through the fuel supply shut-off valve. The APU fuel system features a bypass filter and a high pressure gear pump. A solenoid shut-off valve permits the system to command APU shut-off in case of failure detected by the APU Electronic Control Unit (APU ECU). The fuel flow is controlled by the ECU to fit the different APU operation phases and loads. IGNITION SYSTEM The APU incorporates a high-energy ignition system consisting of a two-way exciter box, and dual cable and dual igniter plug in the combustion chamber. The ignition system is entirely controlled by the APU ECU. The ignition is started at 5.6% N1 and continues until N1 reaches 99%. APU ELECTRONIC CONTROL UNIT (APU ECU) The APU Electronic Control Unit (APU ECU) is located in the forward servicing compartment. It provides for automatic management of APU performance and safeties during starting, operation and shutdown phases. APU ECU monitoring uses N1 signal generated by a magnetic sensor mounted on the accessory gearbox and an EGT signal generated by the single thermocouple probe installed in the APU exhaust duct. The speed governing loop continuously monitors N1 and modulates fuel flow (timedacceleration during starting of the engine or control during self-sustaining operation). The control speed is 105% N1 in flight above 6,000 ft for main engine starting, otherwise 102% N1. The temperature loop is not active during APU starting or normal operation unless EGT exceeds the maximum operating value. DISTRIBUTION APU GENERATOR The starter-generator of the APU is rated at 9 kw (300A) to supply the airplane systems with 28.5 V DC and is regulated by an associated Generator Control Unit (GCU) mounted in the forward servicing compartment. Its excitation circuits are fed when APU generator trip magnetic switch is set to upward position. It is capable of supplying the entire DC electrical system in addition to charging batteries. BLEED AIR The APU bleed air is driven through a BLEED AIR valve to the pneumatic system. For main engine starting, the valve is fully open. When used for air conditioning, the APU ECU controls the valve to obtain the desired cabin temperature. for more information, refer to CODDE 1 / Chapter 02 / ATA 21.
11 F2000EX EASY CODDE 1 PAGE 1 / 8 CONTROL AND INDICATION CONTROL Pushbuttons Status lights FIGURE APU CONTROL PANEL Two-position APU generator trip magnetic switch FIGURE OVERHEAD PANEL DURING NORMAL IN-FLIGHT CONFIGURATION
12 F2000EX EASY PAGE 2 / 8 CODDE 1 CONTROL AND INDICATION CONTROL FUNCTION TO ACTIVATE TO DEACTIVATE SYNOPTIC - powers the APU if the ON light is off (APU not running and not powered) push to power before start-up Empty windows - deactivates the APU if the ON light only is on (APU only powered and not running) push to deactivate or stop APU N1 and EGT values (ENG synoptic and ENG window of PDU) - abnormal APU stop ON flashing - initiates APU starting sequence when the ON light only is on push to start - initiates APU shutdown when both ON and RUN lights are on (APU running) push to stop
13 F2000EX EASY CODDE 1 PAGE 3 / 8 CONTROL AND INDICATION CONTROL FUNCTION TO ACTIVATE TO DEACTIVATE SYNOPTIC contactor closed (Z< 35,000) - connects the APU generator to the ESS bus - allows excitation of APU generator Connected contactor closed (Z> 35,000) - trips automatically to down position when the GCU detects an over-voltage - acts as a reset switch when the fault is cleared (only one reset attempt is allowed) contactor open (APU stopped or GPU is on) Disconnected Abnormal situation: contactor open with APU running and no GPU
14 F2000EX EASY PAGE 4 / 8 CODDE 1 CONTROL AND INDICATION INDICATION As the APU supplies electrical power to the airplane, APU electrical indications can be displayed in the ELEC synoptic of the lower 2/3 MDU window. This page indicates APU generator status and the corresponding ammeter measurement. FIGURE ELECTRICAL SYNOPTIC INDICATION, APU RUNNING FIGURE APU GENERATOR SYMBOL
15 F2000EX EASY CODDE 1 PAGE 5 / 8 CONTROL AND INDICATION The ammeter indicates normal operating values or abnormal values using the following rules. Normal values appear in green Abnormal values appear in amber Invalid data FIGURE APU GENERATOR AMMETER For the APU generator, the analog ammeter and digital readout are only displayed when the APU is running. The amber scale and associated indication range depend on the airplane altitude. APU engine parameters are only displayed when APU MASTER is ON, at the top RH corner of the ENG synoptic and at the bottom of the ENG-TRM-BRK window. N1 (%) and EGT ( C) are displayed as digital readouts. In case of failure, amber labels are displayed near APU parameters: OVSP, OIL, BLEED and DOOR. FIGURE ENG SYNOPTIC
16 F2000EX EASY PAGE 6 / 8 CODDE 1 CONTROL AND INDICATION FIGURE ENG-TRM-BRK WINDOW
17 F2000EX EASY CODDE 1 PAGE 7 / 8 CONTROL AND INDICATION In the TEST synoptic of the MDU lower 2/3 window, APU OIL status can be obtained. The system indicates: - if APU OIL level is ok ( LEVEL OK message, see figure below), or - if APU OIL level is too low ( ADD APU OIL ), or - if the oil data is invalid ( TEST FAIL ). FIGURE LOWER MDU TEST SYNOPTIC An hourmeter, located in the aft servicing compartment, records APU operating time. It automatically begins to record 4 sec after the APU engine N1 reaches 99%.
18 F2000EX EASY PAGE 8 / 8 CODDE 1 CONTROL AND INDICATION INTENTIONALLY LEFT BLANK
19 F2000EX EASY CODDE 1 PAGE 1 / 2 SYSTEM PROTECTION CIRCUIT BREAKERS APU ECU circuit protection is provided by a conventional trip-free circuit breaker located above the overhead panel. FIGURE OVERHEAD CIRCUIT BREAKER PANEL APU ECU PROTECTIONS The APU ECU incorporates comprehensive protection, which automatically shuts down the unit and triggers the APU FAULT CAS message when any of the following conditions is met: - overspeed (110% ± 1%), - loss of N1 signal, - wrong position of APU air intake door, - APU ECU failure, - loss of DC power, - slow start (starting phase control), - speed drop. The extra following conditions are also activated providing that in-flight dual engine failure does not occur (in order to keep APU running in such an event): - EGT overheat (see next section, LIMITATIONS), - loss of EGT signal, - low oil pressure (below 31 psi though N1 above 99% for more than 10 sec), - high oil temperature (oil temperature in the sump above 163 C), - electrical fuel flow regulator failure, - APU fire, - air conditioning overheat.
20 F2000EX EASY PAGE 2 / 2 CODDE 1 SYSTEM PROTECTION INTENTIONALLY LEFT BLANK
21 F2000EX EASY CODDE 1 PAGE 1 / 4 NORMAL OPERATION STARTING SEQUENCE The APU can be started using either airplane battery 1 or an external ground power unit. On ground, the battery start is the usual operating mode. GPU start is detailed in the ABNORMAL OPERATION sub-section. Prior to starting the APU, the oil level must be checked as well as the security area. Pushing the APU MASTER pushbutton turns the ON light on (steady green once air intake door is open). APU ECU is powered. Pushing the START / STOP pushbutton initiates the automatic start sequence and automatically starts the stand-by No 2 booster pump. The RUN light then illuminates for approximately 5 sec to indicate that the command is taken into account (steady green). It extinguishes during APU starting (about 20 sec; BAT 2 symbol is displayed in gray on the ELEC synoptic). When APU start is successful (generator on line), it illuminates again and remains illuminated until the APU is stopped. As long as the RUN remains illuminated, the starting sequence is successful. The engine parameters can be monitored on the ENG-TRM-BRK window. N1 and EGT can be checked while increasing up to approximately 101% for N1 and 400 C for EGT. The electrical parameters can be checked on the ELEC synoptic before connecting equipment. The following examples show controls and indications displayed to the pilots during normal ground operation of the APU. FIGURE APU CONTROL PANEL
22 F2000EX EASY PAGE 2 / 4 CODDE 1 NORMAL OPERATION FIGURE ELEC SYNOPTIC FIGURE LOWER ENG-TRM-BRK WINDOW FIGURE ENG SYNOPTIC
23 F2000EX EASY CODDE 1 PAGE 3 / 4 NORMAL OPERATION SHUTDOWN The APU incorporates an automatic and manual shutdown system that is controlled by the APU ECU and corresponds to the abnormal conditions detailed in the SYSTEM PROTECTION section. Pushing the START / STOP pushbutton closes the APU fuel shut-off valve, the APU START- STOP green RUN light flashes for 2 sec then extinguishes. Pushing the APU MASTER pushbutton while ON light is steady green stops electrical power to the APU ECU. The ON light extinguishes when the air intake door is closed. NOTE 1 When the APU is shut down using the STOP pushbutton, or if automatic shutdown occurs, the APU cannot be restarted unless the MASTER pushbutton is momentarily unlatched and latched again (pushed twice). NOTE 2 Due to APU ECU shutdown logic, a transient amber OVSP label is displayed.
24 F2000EX EASY PAGE 4 / 4 CODDE 1 NORMAL OPERATION LIMITATIONS The APU is certified for in-flight and ground use. Operation of the APU is not authorized without supervision. Maximum N1 speed : 110%. Exhaust gas temperature limit (EGT): - Starting: o below 50% N1: between 870 C and 988 C, less than 10 sec, o above 50% N1: between 690 C and 870 C, less than 10 sec, - Stabilized: 690 C. EGT. NOTE The duration of operation on amber range (690 C to 746 C) must be as short as possible. Maximum generator output: - transient: 350 A, less than 60 sec, - stabilized (amber range display automatically changes): o 300 A below 10,000 ft, o 250 A between 10,000 ft and 25,000 ft, o 200 A above 25,000 ft.
25 F2000EX EASY CODDE 1 PAGE 1 / 4 ABNORMAL OPERATION APU START WITH GPU Prior to initiating the APU start cycle, the GPU must be plugged in and operating. When the EXT POWER light pushbutton is illuminated, the following occurs: - batteries No.1 and 2 are isolated, - the battery bus, the ESS, right and left buses are powered by the GPU (buses are automatically tied), - APU generator is inhibited. Pushing APU MASTER pushbutton powers the APU ECU, opens the air intake door, opens APU fuel supply valve and illuminates the ON light. Pushing APU START / STOP pushbutton initiates the starting sequence. This sequence is the same as the battery starting sequence except for BAT 1 contactor which close during the sequence, its symbol turning from gray to green on ELEC synoptic. Until EXT POWER is depressed, GPU generator continues to power the distribution system, inhibiting all generators, including APU, BAT 1 and BAT 2 (gray symbols). Since the engine speed is above 99% N1, APU bleed air is available for the air conditioning system. APU STARTING SEQUENCE FAILED If the APU fails to start when the START / STOP pushbutton is used, the RUN light does not illuminate and the ON light of the MASTER pushbutton flashes. APU NORMAL SHUTDOWN FAILED If the APU fails to shut down when the START / STOP pushbutton is pushed, an alternate method is also available. Pushing the APU MASTER pushbutton turns off the ON light and cuts off power to the APU ECU causing the APU fuel shut-off valve to close. NOTE This condition should be written up as a maintenance follow-up action. This problem may be associated with the APU ECU automatic shutdown logic.
26 F2000EX EASY PAGE 2 / 4 CODDE 1 ABNORMAL OPERATION APU OVERSPEED In case of APU overspeed, the APU shuts down automatically. FIGURE ENG SYNOPTIC FIGURE ENG-TRM-BRK WINDOW
27 F2000EX EASY CODDE 1 PAGE 3 / 4 ABNORMAL OPERATION APU FIRE The fire warning activates the warning horn, causes the illumination of the corresponding guarded FIRE APU message. pushbutton on the overhead control panel and displays the CAS Pressing the FIRE APU pushbutton automatically shuts down the APU and shuts off the APU fuel valve. Pressing the DISCH pushbutton causes discharge of the single APU fire extinguisher cylinder dedicated to this area. For more information, refer to CODDE 1 / Chapter 02 / ATA 26. CAS MESSAGES CAS MESSAGE FIRE APU APU CMPTR FAULT CODE APU FAULT APU FIRE DETECT FAIL APU GEN STARTER APU APU CMPTR FAULT CODE APU GEN FAIL DEFINITION Fire detected on APU APU ECU fault (parking) APU fault detected by APU ECU APU fire detection system failure APU generator not connected with APU running APU on and starter still active APU ECU fault (cruise) On ground, APU contactor failed to open
28 F2000EX EASY PAGE 4 / 4 CODDE 1 ABNORMAL OPERATION INTENTIONALLY LEFT BLANK
ATA 49 AUXILIARY POWER UNIT
F900EX EASY 02-49-00 CODDE 1 PAGE 1 / 2 TABLE OF CONTENTS 02-49 02-49-00 TABLE OF CONTENTS 02-49-05 GENERAL Introduction Sources APU location 02-49-10 DESCRIPTION Introduction Description Operating principle
More informationATA 36 PNEUMATIC TABLE OF CONTENTS DGT ATA 36 PNEUMATIC TABLE OF CONTENTS GENERAL Introduction Sources
F900EX EASY 02-36-00 CODDE 1 PAGE 1 / 2 TABLE OF CONTENTS 02-36 02-36-00 TABLE OF CONTENTS 02-36-05 GENERAL Introduction Sources 02-36-10 DESCRIPTION Introduction Main sub-systems Distribution 02-36-15
More informationDASSAULT AVIATION Proprietary Data
F2000EX EASY 02-28-00 CODDE 1 PAGE 1 / 2 TABLE OF CONTENTS 02-28 ATA 28 - FUEL SYSTEM 02-28-00 TABLE OF CONTENTS 02-28-05 GENERAL Introduction Sources Fuel tank location 02-28-10 DESCRIPTION Sub-systems
More informationCanadair Regional Jet 100/200 - Auxiliary Power Unit
1. INTRODUCTION The auxiliary power unit (APU) is installed within a fireproof titanium enclosure in the aft equipment compartment. The APU is a fully automated gas turbine power plant which drives an
More informationDASSAULT AVIATION Proprietary Data
F900EX EASY 02-30-00 CODDE 1 PAGE 1 / 2 TABLE OF CONTENTS 02-30 02-30-00 TABLE OF CONTENTS 02-30-05 GENERAL Introduction Anti-icing protection sources Anti-ice system location overview 02-30-10 DESCRIPTION
More informationBombardier Challenger Auxiliary Power Unit
GENERAL A Honeywell 36 150(CL) constant-speed gas turbine auxiliary power unit (APU) is installed within a fire-resistant compartment in the aft equipment bay. The APU drives a generator, providing AC
More informationGeneral. APU Control System. APU Door System
.10 -Description and Operation General The Auxiliary Power Unit () provides electrical and pneumatic power for engine start and air conditioning, and supplies ground and in-flight electrical power. Pneumatic
More informationDASSAULT AVIATION Proprietary Data
F2000EX EASY 02-70-00 CODDE 1 PAGE 1 / 2 TABLE OF CONTENTS 02-70 02-70-00 TABLE OF CONTENTS 02-70-05 GENERAL Introduction Sources Engine location 02-70-10 DESCRIPTION Introduction Major components Operating
More informationDASSAULT AVIATION Proprietary Data
F2000EX EASY 02-24-00 CODDE 1 PAGE 1 / 2 TABLE OF CONTENTS 02-24 02-24-00 TABLE OF CONTENTS 02-24-05 GENERAL Introduction Sources Equipment location 02-24-10 DESCRIPTION Generation Distribution Operation
More informationIntroduction. APU Location
B737 NG APU Introduction The auxiliary power unit (APU) is a self contained gas turbine engine installed within a fireproof compartment located in the tail of the airplane. The APU supplies bleed air for
More informationDash8 - Q400 - Pneumatics
12.19.1 Introduction The Auxiliary Power Unit (APU) replaces the standard composite tailcone with a titanium tailcone and firewall. The APU is accessed by two clamshell type doors on the bottom of the
More informationDASSAULT AVIATION Proprietary Data
F2000EX EASY 02-27-00 CODDE 1 PAGE 1 / 2 TABLE OF CONTENTS 02-27 02-27-00 TABLE OF CONTENTS 02-27-05 GENERAL Introduction Flight control sources Primary and secondary flight controls 02-27-10 DESCRIPTION
More informationDASSAULT AVIATION Proprietary Data
FALCON 7X 02-28-05 CODDE 1 PAGE 1 / 4 GENERAL ACRONYMS APU BP CAS CB CCD CG ECP FCP FLCU FMS FQMC FQ FQMS FR Fuel SOV IRS LP OP PCB PDU POF PPH RCP SSPC Auxilary Power Unit Booster Pump Crew Alerting System
More informationDASSAULT AVIATION Proprietary Data
F900EX EASY 02-27-00 CODDE 1 PAGE 1 / 2 TABLE OF CONTENTS 02-27 02-27-00 TABLE OF CONTENTS 02-27-05 GENERAL Introduction Flight control sources Primary and secondary flight controls 02-27-10 DESCRIPTION
More informationDASSAULT AVIATION Proprietary Data
FALCON 7X 02-70-05 CODDE 1 PAGE 1 / 6 GENERAL ACRONYMS LIST ACOC AGB APU A/T ATSV BOV CAS CB CL CMC CR DC DCU ECS EEC FADEC FBW FCU FF FOHE FSOV HP HPC HPT IGV ITT LP LPC LPT LRU MV N1 N2 PDU PLA PMA PMU
More informationATA 24 ELECTRICAL POWER
F900EX EASY 02-24-00 CODDE 1 PAGE 1 / 2 TABLE OF CONTENTS 02-24 02-24-00 TABLE OF CONTENTS 02-24-05 GENERAL Introduction Sources Equipment location 02-24-10 DESCRIPTION Generation Distribution 02-24-15
More informationCHAPTER 4 ---AUXILIARY POWER UNIT
Table of Contents Vol. 1 04--00--1 CHAPTER 4 ---AUXILIARY POWER UNIT Page TABLE OF CONTENT 04-00 Table of Contents 04--00--1 INTRODUCTION 04-10 Introduction 04--10--1 POWER PLANT 04-20 APU Power Plant
More informationDASSAULT AVIATION Proprietary Data
F2000EX EASY 02-33-00 CODDE 1 PAGE 1 / 2 TABLE OF CONTENTS 02-33 02-33-00 TABLE OF CONTENTS 02-33-05 GENERAL Introduction Sources 02-33-10 DESCRIPTION General Cockpit lights Cabin lights Servicing lights
More informationDASSAULT FALCON 900EX EASY SYSTEMS SUMMARY
DASSAULT FALCON 900EX EASY SYSTEMS SUMMARY Electrical The material contained on this site is to be used for training purposes only. Do not use it for flight! Please note that this document is not affiliated
More informationcanadair chzflleriqer OPERATING MANUAL PSP 601A-6 SECTION 5 AUXILIARY POWER UNIT (APU)
OPERATING MANUAL. AUXILIARY POWER UNIT (APU) 1.. 3. 4. 5. 6. GENERAL APU CONTROL START SYSTEM SHUTDOWN BLEED AIR SYSTEM OIL SYSTEM TABLE OF CONTENTS Page 1 3 3 Figure Number LIST OF ILLUSTRATIONS Title
More informationcanaaair chaiiencjer
canaaair chaiiencjer AUXILIARY POWER UNIT (APU) TABLE OF CONTENTS Subject Page GENERAL APU CONTROL START SYSTEM SHUTDOWN I BLEED AIR SYSTEM OIL SYSTEM 1 1 3 5 5 7 Figure Number LIST OF ILLUSTRATIONS Title
More informationDash8-200/300 - Auxiliary Power Unit APU CONTROLS AND INDICATORS. Page 1
APU CONTROLS AND INDICATORS Page 1 APU control and indicators Page 2 closed APU controls and indicators Page 3 SYSTEM DESCRIPTION General The auxiliary power unit (APU) is a gas turbine engine, located
More informationCessna Citation XLS - Electrical
GENERAL Electrical power for the Citation XLS comes primarily from DC sources originating with the starter/ generators, the Auxiliary Power Unit (APU) or the battery. A receptacle below the left engine
More informationCHAPTER 4 ---AUXILIARY POWER UNIT
Vol. 1 04--00--1 AUXILIARY POWER UNIT Table of Contents REV 3, May 03/05 CHAPTER 4 ---AUXILIARY POWER UNIT Page TABLE OF CONTENT 04-00 Table of Contents 04--00--1 INTRODUCTION 04-10 Introduction 04--10--1
More informationCHAPTER ICE AND RAIN PROTECTION SYSTEM
15--00--1 ICE AND RAIN PROTECTION SYSTEM Table of Contents REV 3, May 03/05 CHAPTER 15 --- ICE AND RAIN PROTECTION SYSTEM Page TABLE OF CONTENTS 15-00 Table of Contents 15--00--1 INTRODUCTION 15-10 Introduction
More informationGENERAL The Honeywell model TFE731-40AR turbofan engine is a lightweight, two-spool, geared-stage, front-fan, jet engine.
ENGINE GENERAL The Honeywell model TFE731-40AR turbofan engine is a lightweight, two-spool, geared-stage, front-fan, jet engine. The cross section of the engine is shown in Figure 7-71-1, page VII-71-3.
More informationDornier 328Jet - Pneumatic
ECS Control Panel Page 1 MESSAGE (SYNOPTIC) WARN INHIBIT CONDITION Location (COLOR) TONE 1 2 3 APU BLEED LEAK CAS Field (AMBER) X X LEAK (APU BLEED) Bleed air leak in APU bleed air duct. ECS Page (AMBER)
More informationB777. Electrical DO NOT USE FOR FLIGHT
B777 Electrical DO NOT USE FOR FLIGHT 6.10 Electrical-Controls and Indicators Electrical Panel [IFE/PASS SEATS and CABIN/UTILITY switches basic with C/L 350] 1 2 IFE/PASS CABIN/ SEATS UTILITY 3 11 APU
More information24-00 ELECTRICAL POWER
ELECTRICAL POWER 1. GENERAL This chapter contains information on DC Generation, External Power, and Electrical Load Distribution. The airplane is equipped with a two-alternator, two-battery, 28-volt direct
More informationSECTION IV ELECTRICAL & LIGHTING
SECTION IV ELECTRICAL & LIGHTING TABLE OF CONTENTS Electrical Power Systems... 4-1 Introduction... 4-1 General... 4-1 Main Batteries... 4-2 Emergency Battery... 4-3 Generators... 4-4 Generator Control
More informationSECTION 5 AUXILIARY POWER UNIT (APU) TABLE OF CONTENTS LIST OF ILLUSTRATIONS. Title
BOMBARDIER AUXILIARY POWER UNIT (APU) TABLE OF CONTENTS Subject GENERAL APU CONTROL START SYSTEM SHUTDOWN BLEED AIR SYSTEM OIL SYSTEM Page 1 1 4 6 8 8 LIST OF ILLUSTRATIONS Figure Number 1 APU Control
More informationCHAPTER 6 ELECTRICAL SYSTEMS
CHAPTER 6 ELECTRICAL SYSTEMS Page TABLE OF CONTENTS 06-00-01/02 DESCRIPTION General 06-10-01 Description 06-10-01 Controls and Indicators 06-10-02 COMPONENTS Circuit Breaker Panel Locations 06-20-01/02
More informationPneumatic Air Conditioning System Citation, Citation I
Pneumatic Air Conditioning System Citation, Citation I COCKPIT VENT FOOT WARMER OVERHEAD COCKPIT WINDSHIELD WEMAC OPTIMAL VENT OVERHEAD CONDITIONED AIR DUCTS BLOWER SIDE WINDOW UNDER FLOOR CONDITIONED
More informationAUXILIARY POWER UNIT. Table of Contents. May 06/2005 Flight Crew Operating Manual Volume 2 REV 2 CSP REV 2
Table of Contents EV 2 Introduction... 05-01-01 Compartment... 05-01-01 APU Access Panel Locations... 05-01-02 APU Schematic... 05-01-03 Power Section and Gearbox... 05-01-04 Description... 05-01-04 Components
More informationAIRCRAFT SYSTEMS PNEUMATIC
Intentionally left blank PRELIMINARY PAGES - TABLE OF CONTENTS DSC-36-10 Description DSC-36-10-10 General GENERAL... A DSC-36-10-20 Engine Bleed System GENERAL... A Architecture... B Air Bleed Selection...C
More informationBombardier Global Express - Hydraulics
INTRODUCTION Hydraulic power is provided by three independent and isolated systems designated 1, 2 and 3 and operate at a nominal pressure of psi. SYSTEM 1 AND 2 Systems 1 and 2 are each powered by an
More informationDESCRIPTION AND OPERATION ICE DETECTION SYSTEM
ICE DETECTION SYSTEM 2.23. ICE DETECTION SYSTEM The ice detection system consists of an ice detector located on the right side of the airplane nose and two ICE amber caution lighted pushbuttons on both
More informationAUXILIARY POWER UNIT TABLE OF CONTENTS CHAPTER 5
TABLE OF CONTENTS CHATER 5 age TABLE OF CONTENTS DESCRITION General AU Access and Component Location AU Compartment AU General Arrangement AU System Schematic Lubrication Oil ressure Gravity Oil Fill Oil
More informationENGINE GROUND RUNNING
B737 600/700/800/900 (CFM 56) ENGINE GROUND RUNNING Guide and Reference Sheets This publication is for TRAINING PURPOSES ONLY. This information is accurate at the time of completion. No update service
More informationThis chapter contains information on DC Generation, External Power, and Electrical Load Distribution.
CIRRUS AIRPLANE MAINTENANCE MANUAL Electrical Power CHAPTER 24-00: ELECTRICAL POWER GENERAL 24-00: ELECTRICAL POWER 1. General This chapter contains information on DC Generation, External Power, and Electrical
More informationCanadair Regional Jet 100/200 - Fuel System
1. INTRODUCTION The fuel system consists of three integral tanks within the wing box structure. Ejector pumps and electrical boost pumps supply fuel to each engine. The fuel system also provides facilities
More informationSECTION 2-05 ELECTRICAL
SECTION 2-05 TABLE OF CONTENTS Block General...2-05-05...01 DC System...2-05-05...02 DC System Protection...2-05-05...04 External Power Source...2-05-05...05 Batteries...2-05-05...06 Backup Battery...2-05-05...07
More informationCHAPTER FUEL SYSTEM
Vol. 1 13--00--1 FUEL SYSTEM Table of Contents REV 3, May 03/05 CHAPTER 13 --- FUEL SYSTEM Page TABLE OF CTENTS 13-00 Table of Contents 13--00--1 INTRODUCTI 13-10 Introduction 13--10--1 FUEL STORAGE 13-20
More informationOVERHEAD PANEL PROCEDURES FLASH CARDS
OVERHEAD PANEL PROCEDURES FLASH CARDS Boeing 737-800 A supplement to the procedures and checklists publication, Flying the Boeing 737-800 NG Greg Whiley Aussie Star Flight Simulation ELECTRICAL POWER UP
More informationOperation of the FFBH is enabled and disabled by the Automatic Temperature Control Module (ATCM).
Page 1 of 8 Published : Apr 22, 2004 Auxiliary Heater COMPONENT LOCATIONS Item Part Number Description 1 - Fuel line connection with fuel tank 2 - Auxiliary fuel pump 3 - Fuel fired booster heater GENERAL
More informationSection of 14. Ice and Rain Protection
Ice & Rain Protection 1 of 14 WINDSCREEN WIPERS General The aircraft is fitted with two windscreen wipers, one on each pilots side windscreen, which are controlled by a 3-position (FAST, SLOW and MANUAL)
More informationDASSAULT FALCON 7X SYSTEMS SUMMARY
DASSAULT FALCON 7X SYSTEMS SUMMARY Airframe & Doors This material is to be used for training purpose only Do not use it for flight! Please note that this document is not affiliated in any way with any
More informationTHOMSON AIRWAYS LIMITED DISCREPANCY SHEET
IPC REF FIG ITEM DESCRIPTION FROM 72.35.01 01 085/220 ROTATING FAIRINGS 72.31.11 01 280 LP BLADES (22 OFF) 73.11.07 01 645/725 MAIN FUEL INLET TUBE 29.11.03 02 100 HYD. SUPPLY,RIGID TUBE 29.11.03 02 200
More informationGPU Equipment Operating Instructions Table of Contents
GPU Equipment Operating Instructions Table of Briggs & Stratton Model: 30439 Davco Model: GP28R under construction Foxtronics Model: PR-2000-T7S GUINAULT MODEL: GA90V133 HOBART MODEL: JET EX-2, EX-3, EX-4,
More informationCessna Citation XLS - Environmental & Temperature Control
GENERAL Environmental and temperature control on the Citation XLS is provided by pre-cooled engine and/or APU bleed air. The conditioned bleed air is distributed in a series of ducts and vents. The primary
More informationUnited States Army Aviation Center of Excellence. Fort Rucker, Alabama JULY 2011 STUDENT HANDOUT
United States Army Aviation Center of Excellence Fort Rucker, Alabama JULY 2011 STUDENT HANDOUT TITLE: AH-64D INTEGRATED PRESSURIZED AIR SYSTEM (IPAS) FILE NUMBER: 011-0910-1.5 (LOT13) PROPONENT FOR THIS
More informationSection 13 - E. 1 of 18. Engine Systems
Engine Systems 1 of 18 ENGINE FUEL SYSTEM Introduction The fuel system uses electronic, hydraulic and mechanical functions to regulate the power and adapt it to the requirements at any one time. Air pressure
More informationFuel Fired Booster Heater
Page 1 of 15 Published: Mar 31, 2009 Fuel Fired Booster Heater COMPONENT LOCATION - VEHICLES WITHOUT FFBH REMOTE CONTROL Item Part Number Description 1 Automatic Temperature Control (ATC) module 2 Fuel
More informationModulating Furnace Information. Warning on Meter Setting - Read First!
Modulating Furnace Information Pressure Transducer Pressure DC Volts 0.00" 0.25 0.20" 0.63 0.25" 0.72 0.30" 0.82 0.35" 0.91 0.40" 1.00 0.45" 1.09 0.50" 1.19 0.55" 1.28 0.60" 1.38 0.65" 1.47 0.70" 1.56
More informationSurface and Brakes Anti-Ice Systems
Surface and Brakes Anti-Ice Systems WING DEICE DISTRIBUTOR VALVE TAIL DEICE R BLEED FAIL VDC FROM RIGHT ENGINE P3 PNEUMATIC AIR SHUTOFF VALVE N.O. R BK DEICE ON Ice and Rain Protection N.C. TO DOOR SEAL
More informationFUEL MODEL 750 BAGGAGE COMPARTMENT SMOKE DETECTION
MODEL 750 SECTION II AIRPLANE AND SYSTEMS System test is accomplished by turning the cockpit rotary test switch to FIRE WARN. Proper system operation is indicated by illumination of the APU FIRE indicating
More informationDEEP SEA ELECTRONICS PLC
COMPLEX SOLUTIONS MADE SIMPLE DEEP SEA ELECTRONICS PLC DSE704 AUTOSTART CONTROL MODULE OPERATING MANUAL 057-042 704 Operating Instructions Issue 2.1 18/06/2007 11:27:00 JR - 1 - Deep Sea Electronics Plc
More informationWIRELESS CONTROL MODULE (WCM)
42C-1 GROUP 42C WIRELESS CONTROL MODULE (WCM) CONTENTS GENERAL INFORMATION 42C-2 42C-5 KEYLESS ENTRY FUNCTION 42C-5 IMMOBILIZER FUNCTION 42C-9 TIRE PRESSURE MONITORING SYSTEM (TPMS) FUNCTION 42C-10 WARNINGS/ALARMS
More informationFokker 50 - Ice & Rain Protection. Controls and indicators of the AIRFRAME DE-ICING system are located at the ice protection panel.
ICE AND RAIN PROTECTION AIRFRAME DE-ICING Description Controls and indicators of the AIRFRAME DE-ICING system are located at the ice protection panel. Airframe de-icing is accomplished by alternately inflating
More informationcanadair chaifenqer 14-CONTENTS Page 1 Feb 12/88 TABLE OF CONTENTS Subject Page GENERAL ICE DETECTION
chaifenqer ICE/RAIN PROTECTION TABLE OF CONTENTS Subject Page GENERAL ICE DETECTION WING ANTI-ICING General Operating Modes System Monitoring Lower Isolation Valve Operation ENGINE ANTI-ICING General Operation
More informationAIRCRAFT SYSTEMS FUEL
Intentionally left blank PRELIMINARY PAGES - TABLE OF CONTENTS DSC-28-10 Description DSC-28-10-10 General GENERAL... A DSC-28-10-20 Tanks Tanks...A DSC-28-10-30 Engine Feed GENERAL... A Main Components...B
More informationMODEL 520 REMOTE START ENGINE MANAGEMENT SYSTEM
MODEL 520 REMOTE START ENGINE MANAGEMENT SYSTEM DSE 520 ISSUE 4 4/4/02 MR 1 TABLE OF CONTENTS Section Page INTRODUCTION... 4 CLARIFICATION OF NOTATION USED WITHIN THIS PUBLICATION.... 4 1. OPERATION...
More informationSECTION 2-14 PNEUMATICS, AIR CONDITIONING AND PRESSURIZATION
AIRPLANE PNEUMATICS SECTION 2-14 PNEUMATICS, TABLE OF CONTENTS Block General... 2-14-05..01 Pneumatic System... 2-14-05..02 Pneumatic System Function Logic... 2-14-05..06 Cross Bleed Valve Operational
More informationTECHNICAL PAPER 1002 FT. WORTH, TEXAS REPORT X ORDER
I. REFERENCE: 1 30 [1] Snow Engineering Co. Drawing 80504 Sheet 21, Hydraulic Schematic [2] Snow Engineering Co. Drawing 60445, Sheet 21 Control Logic Flow Chart [3] Snow Engineering Co. Drawing 80577,
More informationAIRPLANE OPERATIONS MANUAL SECTION 2-15
SECTION 2-15 TABLE OF CONTENTS Block General... 2-15-05..01 Bleed Air Thermal Anti-Icing System... 2-15-10..01 Wing, Stabilizer and Engine Anti-icing Valves Operational Logic... 2-15-10..04 EICAS Messages...
More informationPilot's Operating Handbook Supplement AS-03
POH / AFM SECTION 9 Pilot's Operating Handbook Supplement ASPEN EFD1000 PFD This supplement is applicable and must be inserted into Section 9 of the POH when the Aspen Avionics Evolution Flight Display
More informationEC135 T2e/P2e Technical Data 2013
EC135 T2e/P2e Technical Data 2013 135 T2e/P2e Technical Data EC135 T2e/P2e (Civil Version) EC635 T2e/P2e (Military Version) Technical Data 3 Baseline Aircraft Definition GENERAL Energy absorbing fuselage
More informationSECTION 3 EMERGENCY PROCEDURES CONTENTS
CONTENTS Page Definitions.................................. 3-1 Power Failure - General......................... 3-1 Power Failure Above 500 feet AGL................ 3-2 Power Failure Between 8 and 500
More informationFlight Systems. Replacement for KASSEC DESCRIPTION
DESCRIPTION The is a universal generator controller that will start, stop, and provide engine protection for most generators. Universal replacement for both the 90353 and 90354 KASSEC Compatible with most
More informationKing Air B90. Speeds (KIAS)
King Air B90 Speeds (KIAS) V MCA 92 V SSE (101) Derived from C90 V X 101 V Y 114 Down to 103 @ 30 000 V XSE 101 V YSE 110 Down to 101 @ 24 000 V A 169 V R 92 V 1 101 V MO 208 V FE 174 35% 130 100% V LE
More information24 ELECTRICAL DC ELECTRICAL SYSTEM DESCRIPTION
24 ELECTRICAL DC ELECTRICAL SYSTEM DESCRIPTION The Direct Current electrical system provides power to most equipment through an electrical bus system. The power may be supplied from one of three sources:
More informationCHAPTER 21 ENVIRONMENT CONTROL. Section Title Page
CHAPTER 21 ENVIRONMENT CONTROL Section Title Page 21-00 Description........................................ 21.1 21-10 Ventilation........................................ 21.3 21-11 Nose Vent................................
More informationSECTION II ENGINES & FUEL
SECTION II ENGINES & FUEL TABLE OF CONTENTS Engines...2-1 Fuel Control Logic Diagram (Figure 2-1)... 2-2 Engine Fuel and Control System... 2-3 Thrust Levers... 2-3 Engine-Driven Fuel Pump... 2-4 Hydromechanical
More informationDEEP SEA ELECTRONICS PLC
DEEP SEA ELECTRONICS PLC 703 AUTOMATIC START MODULE OPERATING INSTRUCTIONS Author:- John Ruddock 703 Operating Instructions Issue Beta1 25/08/2003 2:45 PM JR - 1 - >
More informationUnited States Army Warfighting Center Fort Rucker, Alabama OCTOBER 2005
United States Army Warfighting Center Fort Rucker, Alabama OCTOBER 2005 STUDENT HANDOUT TITLE: CH-47D POWER PLANTS FILE NUMBER: 011-2107-5 PROPONENT FOR THIS STUDENT HANDOUT IS: 110 th Aviation Brigade
More informationSECTION 6-3 POWER PLANT
SECTION 6-3 SYSTEMS DESCRIPTION Index Page General Description... 6-3-3 Engine Features... 6-3-4 Engine Indication System... 6-3-6 Power Plant Control... 6-3-10 Power Plant System Control... 6-3-12 Power
More information5220 AUTOMATIC MAINS FAILURE MODULE OPERATING MANUAL
5220 AUTOMATIC MAINS FAILURE MODULE OPERATING MANUAL > Section DSE Model 5220 Automatic Mains Failure & Instrumentation System Operators Manual TABLE OF CONTENTS
More informationInstruction Manual. Q Series 2 Motor Control Modules - OEM
A382-21-880 Issue B Instruction Manual Q Series 2 Motor Control Modules - OEM Pump/ Q Motor Control Module Item Number pumping system Electrical supply 24 V d.c. control 24 V a.c. control QDP40 200-230
More informationCOMPONENT IDENTIFICATION
This CFMI publication is for Training Purpose Only. The information is accurate at the time of compilation; however, no update service will be furnished to maintain accuracy. For authorized maintenance
More informationSECTION III HYDRAULICS & LANDING GEAR
TABLE OF CONTENTS Pilot s Manual SECTION III HYDRAULICS & LANDING GEAR Hydraulic System... 3-1 Firewall Shutoff Valves... 3-2 Source Selector Valve... 3-2 AUX HYD Pump Control... 3-2 Main/Auxiliary System
More informationGENERAL The AuRACLE Engine Management System primary display provides a graphical representation of the following engine instrumentation:
GENERAL The AuRACLE Engine Management System primary display provides a graphical representation of the following engine instrumentation: o Manifold Pressure (MAP) o RPM o Fuel Flow (FF) o Turbine Inlet
More informationCRUISE CONTROL SYSTEM
CRUISE CONTROL CRUISE CONTROL SYSTEM CRUISE CONTROL SYSTEM PRECAUTION 1 1. HANDLING PRECAUTION FOR CRUISE CONTROL SYSTEM (a) Turn the cruise control main switch OFF when not using the cruise control system.
More informationUniversity of Houston Master Construction Specifications Insert Project Name SECTION ELECTRONIC VARIABLE SPEED DRIVES PART 1 - GENERAL
SECTION 23 04 10 ELECTRONIC VARIABLE SPEED DRIVES PART 1 - GENERAL 1.1 RELATED DOCUMENTS: A. The Conditions of the Contract and applicable requirements of Division 1, "General Requirements", and Section
More informationCommander 15i Container and Pallet Loader. Property of American Airlines
Commander 15i Container and Pallet Loader Section 2. Operation BEFORE ATTEMPTING TO OPERATE OR MAINTAIN THE VEHICLE, COMPLETELY READ AND UNDERSTAND THE OPERATION AND MAINTENANCE MANUAL, INCLUDING ALL DANGER,,
More informationCHAPTER 14 LANDING GEAR
CHAPTER 14 LANDING GEAR Page TABLE OF CONTENTS 14-00-01/02 DESCRIPTION General 14-10-01 Description 14-10-01 Controls and Indicators 14-10-04 COMPONENTS Nose Gear 14-20-01 Main and Center Gear 14-20-02
More informationDeep Sea Electronics Plc
Deep Sea Electronics Plc 5120 AUTOMATIC MAINS FAILURE MODULE OPERATING MANUAL Author: Anthony Manton Deep Sea Electronics Plc Highfield House Hunmanby North Yorkshire YO14 0PH England Tel: +44 (0) 1723
More information500 Series Troubleshooting Guide for C520 Alternators
500 Series Troubleshooting Guide for C520 Alternators Hazard Definitions These terms are used to bring attention to presence of hazards of various risk levels or to important information concerning product
More informationCentral Warning Systems
CIRRUS AIRPLANE MAINTENANCE MANUAL Central Warning Systems CHAPTER 31-50: CENTRAL WARNING SYSTEMS GENERAL 31-50: CENTRAL WARNING SYSTEMS 1. General This section describes the Indicating/Recording Systems
More informationRemote engine start. Function
Function Remote engine start is used to start the engine without turning the starter key to the start position, for example by using a switch outside the cab. Function There is also a function called Inhibit
More informationIn-Flight Entertainment System
GENERAL In-Flight Entertainment System 44-20: IN-FLIGHT ENTERTAINMENT SYSTEM 1. General This chapter describes the systems, units, and components which provide entertainment to the passengers with music,
More informationGENSET CONTROL MODULE A121H / A241H. User selectable time delays for engine start and engine stop (cool down).
Technical Data Sheet GENSET CONTROL MODULE A121H / A241H Features: Models for both 12V and 24V systems. One model for both spark ignition and diesel engines. 4-alarm light outputs with lamp-test provisions.
More information702 AUTOMATIC START MODULE OPERATING INSTRUCTIONS
702 AUTOMATIC START MODULE OPERATING INSTRUCTIONS > TABLE OF CONTENTS 1 DESCRIPTION OF OPERATION... 4 1.1 MANUAL MODE OPERATION... 4 1.2 AUTOMATIC MODE OF OPERATION...
More informationStarting System DS-102 Series 200. Elmatik AS P.O.Box 309 NO-3471, Slemmestad T F
Starting System DS-102 Series 200 Elmatik AS P.O.Box 309 NO-3471, Slemmestad T - +47 31 28 37 83 F - +47 31 28 37 93 www.elmatik.no post@elmatik.no CONTENT 1. INTRODUCTION 3 2. TECHNICAL SPECIFICATIONS
More informationCIRRUS AIRPLANE MAINTENANCE MANUAL
ELECTRICAL LOAD DISTRIBUTION. DESCRIPTION The power distribution system for this airplane consists of the main distribution bus and the essential distribution bus in the MCU along with the associated buses
More informationA AMM - ENGINE BLEED AIR SUPPLY SYSTEM - DESCRIPTION AND OPERATION
ENGINE BLEED AIR SUPPLY 1. General The system is designed to : - select the compressor stage from which air is bled, depending on the pressure and/or temperature existing at the last stage of the engine
More informationCHAPTER 96 ELECTRICAL SYSTEM
CHAPTER 96 ELECTRICAL SYSTEM Section Title Page 96-00 Description.............................................. 96.1 96-10 Battery................................................. 96.3 96-11 Lead-Acid
More informationEuropean Aviation Safety Agency
European Aviation Safety Agency EASA TYPE-CERTIFICATE DATA SHEET Number : E.036 Issue : 04 Date : 10 September 2013 Type : Rolls-Royce plc Trent 1000 series engines Models Trent 1000-A Trent 1000-A2 Trent
More informationAIRPLANE FLIGHT MANUAL AQUILA AT01 AIRPLANE FLIGHT MANUAL - SUPPLEMENT AVE28 GLASS COCKPIT. equipped with ASPEN EFD1000 PFD
SECTION 9 AIRPLANE FLIGHT MANUAL - SUPPLEMENT AVE28 GLASS COCKPIT equipped with ASPEN EFD1000 PFD This AFM supplement is applicable and must be inserted into Section 9 of the Airplane Flight Manual when
More informationPowertrain DTC Summaries EOBD
Powertrain DTC Summaries Quick Reference Diagnostic Guide Jaguar X-TYPE 2.0 L 2002.25 Model Year Refer to page 2 for important information regarding the use of Powertrain DTC Summaries. Jaguar X-TYPE 2.0
More informationLanding Gear & Brakes
EMBRAER 135/145 Landing Gear & Brakes GENERAL The EMB-145 landing gear incorporates braking and steering capabilities. The extension/retraction, steering and braking functions are hydraulically assisted,
More information