CIRRUS AIRPLANE MAINTENANCE MANUAL
|
|
- June Barker
- 5 years ago
- Views:
Transcription
1 ANALYZERS - ENGINE MONITORING. DESCRIPTION This section describes that portion of the engine indicating system which is used to analyze engine performance, temperature, and condition. Serials 00 thru 8 w/ EMax Engine Monitoring: Engine instrumentation is displayed on the Multi-Function Display (MFD). The Sensor Interface Unit (SIU), mounted above the RH kickplate, converts analog signals from the engine and fuel sensors to digital format, which is then transmitted to the MFD. The MFD displays fuel flow, nautical miles per gallon, fuel remaining, fuel-to-waypoint, fuel-to-destination, cylinder head temperatures (CHT), exhaust gas temperatures (EGT), engine crankshaft speed, manifold pressure, percent power, oil temperature, oil pressure, outside air temperature (OAT), and electrical bus voltages. EGT and CHT sensors are mounted to all six exhaust pipes and cylinder heads respectively. MFD functionality is enhanced by displaying six channels of EGT and CHT data. 8 VDC for system operation is suppled through the -amp ENGINE INST circuit breaker located on Main Bus. Serials 8 thru 0, 06 & subs w/o Perspective Avionics: Engine instrumentation is displayed on the Primary Flight Display (PFD) and Multi-Function Display (MFD). The Data Acquisition Unit (DAU), mounted above the RH kickplate, converts analog signals from the engine and fuel sensors to digital format, which is then transmitted to the MFD and PFD. The PFD displays percent power, engine crankshaft speed, manifold pressure, fuel flow, and oil pressure. The MFD displays fuel flow, nautical miles per gallon, fuel remaining, fuel-to-waypoint, fuel-to-destination, cylinder head temperatures (CHT), exhaust gas temperatures (EGT), engine crankshaft speed, manifold pressure, percent power, oil temperature, oil pressure, outside air temperature (OAT), and electrical bus voltages. The DAU replaces all of the signal conditioning, sensor excitation and warning light outputs that had been a function of the engine gages. 8 VDC for the digital instrument operation is supplied through the -amp ANNUN / ENGINE INST circuit breaker on the Essential Bus. Serials 8 thru 0, 06 & subs w/ EMax Engine Monitoring and w/o Perspective Avionics: EGT and CHT sensors are installed to each exhaust pipe and cylinder head respectively. MFD functionality is enhanced by displaying six channels of EGT and CHT data. Serials 06 & subs w/ Perspective Avionics: Engine instrumentation is displayed on the Primary Flight Display (PFD) and Multi-Function Display (MFD). The GEA 7 engine airframe unit, mounted behind the MFD, converts analog signals from the engine and fuel sensors to digital format, which is then transmitted to the MFD and PFD. The PFD displays percent power, engine crankshaft speed, manifold pressure, fuel flow, and oil pressure. The MFD displays fuel flow, nautical miles per gallon, fuel remaining, fuel-to-waypoint, fuel-to-destination, cylinder head temperatures (CHT), exhaust gas temperatures (EGT), engine crankshaft speed, manifold pressure, percent power, oil temperature, oil pressure, outside air temperature (OAT), and electrical bus voltages. The GEA 7 engine airframe unit replaces all of the signal conditioning, sensor excitation and warning light outputs that had been a function of the Data Acquisition Unit (DAU). 8 VDC for the digital instrument operation is supplied through the -amp ENGINE INSTR circuit breaker on Essential Bus. The GEA 7 engine airframe unit is integral to the Perspective Integrated Avionics system. For an overview of the Perspective Avionics system, refer to Chapter, Integrated Modular Avionics. (Refer to -00) For maintenance practices pertinent to the engine crankshaft speed and manifold pressure sensors, see the Power section of Engine Indicating. (Refer to 77-0) For maintenance practices pertinent to the CHT and EGT sensors, see the Temperature section of Engine Indicating. (Refer to 77-0) For maintenance practices pertinent to the oil temperature and oil pressure sensors, see the Indicating section of Oil. (Refer to 79-0) For maintenance practices pertinent to the OAT sensor, see the Flight Environment Pitot-Static Systems section of Navigation and Pitot-Static Systems. (Refer to -0) All Page Jun 00
2 . TROUBLESHOOTING Serials 06 & subs w/ Perspective Avionics: Trouble Probable Cause Remedy Engine airframe sensors not receiving valid data. Software or configuration error. GEA 7 is offline. Check PFD Alert Window for GIA, GIA, or GEA configuration, software or failed data path error messages. Correct any errors before proceeding. On PFD in Configuration Mode, turn to GEA STATUS page and verify that GEA internal power supply, configuration, and calibration status boxes are green.. If internal power supply box is red, check for shorted engine airframe sensors that receive V, 0V or V power from GEA (tach sensor, MAP sensor, fuel flow sensor, oil pressure sensor, and pitot heat sensor).. The configuration and calibration boxes should be green. If calibration status boxes are red, replace GEA 7. Verify internal, external, and reference voltages listed in the Main Analog and I/O A Analog boxes are not dashed out (does not include Aircraft Power and ). If any voltages are dashed out, replace GEA 7. On MFD AUX SYSTEM STATUS page, verify GEA is online (green checkmark is present). If GEA is not online (Red-X is present), verify the unit is receiving power at GEA rack connector. Faulty GEA 7. Replace GEA 7. Faulty wiring and connectors. Check GIA and GEA interconnect wiring and unit connector pins for faults. Page Jun 00 All
3 . MAINTENANCE PRACTICES A. Sensor Interface Unit (SIU) - Serials 00 thru 8 w/ EMax Engine Monitoring (See Figure 77-0) () Removal - Sensor Interface Unit (a) Set BAT, BAT, and AVIONICS switches to OFF positions. (b) Pull ENGINE INST circuit breaker. (c) Remove RH kick plate. (Refer to -0) (d) Disconnect electrical connectors from SIU. (e) Remove screws, washers, and nuts securing SIU to kick plate. Remove SIU from airplane. () Installation - Sensor Interface Unit (a) Perform Adjustment/Test - Sensor Interface Unit. (Refer to ) (b) Position SIU to kick plate and secure with screws, washers, and nuts. (c) Connect electrical connectors to SIU. (d) Install RH kick plate. (Refer to -0) (e) Reset ENGINE INST circuit breaker. () Adjustment/Test - Sensor Interface Unit CAUTION: DIP switches must be set to the proper configuration or the Sensor interface unit could send inaccurate data to the MFD. Exercise caution when setting DIP switches. Sensor interface units installed in accordance with Service Bulletin SB use different DIP switch settings than sensor interface units installed during airplane production. The sensor interface unit is considered non-adjustable, once the unit has the switches set to the proper configuration, no further adjustment is required. (a) Remove screws securing DIP switch cover to SIU. (b) Reset DIP switches in accordance with Figure (See Figure ) (c) Position DIP switch cover to SIU and secure with screws. Serials 00 thru 8 w/ EMax Engine Monitoring Page Jun 00
4 DIP SWITCH SETTINGS SR0 AIRPLANE SERIALS SW SW SW SW SW SW6 SW7 SW8 SW9 SW after SB DIP SWITCH SETTINGS SR0 AIRPLANE SERIALS SW SW SW SW SW SW6 SW7 SW8 SW9 SW0 8 - after SB ON () ON () OFF (0) OFF (0) DIP SWITCH SETTINGS SR0 AIRPLANE SERIALS SW SW SW SW SW SW6 SW7 SW8 SW9 SW0 and subsequent ON () OFF (0) KICK PLATE (REF) Serials 00 thru 8 w/ EMax Engine Monitoring. LEGEND. Sensor Interface Unit. Screw. Washer. Nut. Nylon Washer 6. DIP Switch Cover 7. Connector SR0_MM77_9 Page Jun 00 Figure Sensor Interface Unit Installation - Serials 00 thru 8 w/ EMax Engine Monitoring Serials 00 thru 8 w/ EMax Engine Monitoring
5 B. Data Acquisition Unit - Serials 8 thru 0, 06 & subs w/o Perspective Avionics (See Figure ) () Removal - Data Acquisition Unit (DAU) (a) Set BAT, BAT, and AVIONICS switches to OFF positions. (b) Pull ANNUN / ENGINE INST circuit breaker. (c) Remove RH kick plate. (Refer to -0) (d) Disconnect electrical connectors from DAU. (e) Remove screws, washers, and nuts securing DAU to kick plate. Remove DAU from airplane. () Installation - Data Acquisition Unit (DAU) (a) Position DAU to kick plate and secure with screws, washers, and nuts. (b) Connect electrical connectors to DAU. (c) Install RH kick plate. (Refer to -0) (d) Reset ANNUN / ENGINE INST circuit breaker. Serials 8 thru 0, 06 & subs w/o Perspective Avionics Page Jun 00
6 KICK PLATE (REF) LEGEND. Data Acquisition Unit. Screw. Washer. Connector. Model Identification Jumper Serials 8 thru 0, 06 & subs w/o Perspective Avionics SR0_MM77_A Figure Data Acquisition Unit Installation - Serials 8 thru 0, 06 & subs w/o Perspective Avionics Page 6 Jun 00 Serials 8 thru 0, 06 & subs w/o Perspective Avionics
7 C. GEA 7 Engine Airframe Unit - Serials 06 & subs w/ Perspective Avionics (See Figure ) () Removal - GEA 7 Engine Airframe Unit (a) Set BAT, BAT, and AVIONICS switches to OFF positions. (b) Pull ANNUN / ENGINE INST circuit breaker. (c) Remove MFD. (Refer to -60) (d) Loosen screw securing handle-lock mechanism to engine airframe unit. (e) Lift handle-lock mechanism to disengage engine airframe unit from connectors. (f) Remove engine airframe unit from mounting rack. () Installation - GEA 7 Engine Airframe Unit (a) Position engine airframe unit to mounting rack, ensuring handle-lock mechanism engages slot on side of rack. (b) Using handle-lock mechanism, gently push engine airframe unit into mounting rack to engage connectors. (c) Tighten screw securing handle-lock mechanism to engine airframe unit. (d) Install MFD. (Refer to -60) (e) Reset ANNUN / ENGINE INST circuit breaker. (f) If GEA 7 has been replaced with a new or different unit, or original unit has been repaired, perform Adjustment/Test - Component Software and Configuration Loading. (Refer to -00) Serials 06 & subs w/ Perspective Avionics Page 7 9 Sep 07
8 CONSOLE (REF) LEGEND. GEA 7 Engine Airframe Unit. Rack. Screw. Washer. Nut SR0_MM77_70 Page 8 9 Sep 07 Figure GEA 7 Engine Airframe Unit Installation - Serials 06 & subs w/ Perspective Avionics Serials 06 & subs w/ Perspective Avionics
9 D. Engine Monitoring Recording System - Serials 00 & subs w/ EMax Engine Monitoring The engine monitoring recording system records and stores engine data on the MFD. () Functional Test - Engine Monitoring System - Serials & subs w/ EMax Engine Monitoring (a) Acquire necessary tools, equipment, and supplies. Description P/N or Spec. Supplier Purpose USB Flash Drive - Any Source Record data. Computer with USB Port - Any Source View data. (b) (c) (d) (e) (f) (g) (h) (i) (j) Connect blank flash drive to USB port on MFD bezel. Set BAT, BAT, and AVIONICS switches to ON positions. Pull STARTER RELAY and FUEL PUMP RELAY circuit breakers. On MFD, when READY TO WRITE ENGINE DATA TO REMOVABLE MEDIA is displayed, press [Proceed]. On MFD, verify the following: ENGINE DATA LOG TRANSFER IN PROGRESS is displayed. Status Bar displays as data is written. LOG TRANSFER SUCCEEDED is displayed. CONTINUE... is displayed. Remove data storage device from USB port on MFD. Reset STARTER RELAY and FUEL PUMP RELAY circuit breakers. Set BAT, BAT, and AVIONICS switches to OFF positions. Verify engine data was written to flash drive. Connect flash drive to USB port on computer. Navigate to flash drive and open EngineLog folder. Note: The engine log files use the following naming convention: Engine_07007_007_out.log where indicates the date (February 07, 007) and 007 indicates the time (0:0:7). Open engine log file corresponding to date of functional test and verify engine data exists for the expected times. If data exists, the engine monitoring recording system is functioning properly. If no data exists, the engine monitoring recording system is malfunctioning. Contact Cirrus Design for disposition. Serials 00 & subs w/ EMax Engine Monitoring Page 9 9 Sep 07
10 Intentionally Left Blank Page 0 9 Sep 07 All
INTEGRATED ENGINE INSTRUMENT SYSTEMS
All INTEGRATED ENGINE INSTRUMENT SYSTEMS. DESCRIPTION This section describes that portion of the engine indicating system which is used to analyze engine performance, temperature, and condition. Serials
More informationCIRRUS AIRPLANE MAINTENANCE MANUAL
INDICATING 1. DESCRIPTION This section describes that portion of the oil system which is used to indicate the quantity, temperature, and pressure of the oil. Components included are the oil filler cap/dipstick,
More informationAttitude And Direction
CIRRUS AIRPLANE MAINTENANCE MANUAL Attitude And Direction CHAPTER 34-20: ATTITUDE AND DIRECTION GENERAL 34-20: ATTITUDE AND DIRECTION 1. General This section contains information pertaining to those portions
More informationSTALL WARNING SYSTEM 1. DESCRIPTION A.
STALL WARNING SYSTEM 1. DESCRIPTION A. Stall Warning System - Serials w/o Perspective Avionics The airplane uses an electro-pneumatic stall warning system. As the angle of attack increases and the airplane
More informationCIRRUS AIRPLANE MAINTENANCE MANUAL
All INDICATING. DESCRIPTION A. Fuel Quantity Serials 005 thru 885: A fuel quantity gage is installed in the center console directly forward of the fuel selector valve. The fuel quantity gage indicates
More informationA. Stall Warning System - Serials w/o Ice Protection
Stall Warning System GENERAL 27-31: STALL WARNING SYSTEM 1. General A. Stall Warning System - Serials w/o Ice Protection The airplane uses an electro-pneumatic stall warning system. As the angle of attack
More informationCIRRUS AIRPLANE MAINTENANCE MANUAL
PASSENGER COMPARTMENT 1. DESCRIPTION This section covers the passenger compartment lighting. A. Passenger Eyeball Lights Individual eyeball-type reading lights are installed in the headliner above each
More informationSR22 Airplane Flight Manual (AFM) Temporary Change
Cirrus Design TPOH Airplane Flight Manual (AFM) Temporary Change Information in this Temporary Change adds to, supersedes, or deletes information in the basic Pilot s Operating Handbook. Affected Publications:
More informationCIRRUS AIRPLANE MAINTENANCE MANUAL
STALL WARNING SYSTEM 1. DESCRIPTION A. Stall Warning System - Serials 05 thru 2015, 2016 & subs w/o Perspective Avionics The airplane uses an electro-pneumatic stall warning system. As the angle of attack
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 information33-10 FLIGHT COMPARTMENT
FLIGHT COMPARTMENT. DESCRIPTION Flight compartment interior lighting consists of instrument lights, glareshield flood lights, overhead dome light, individual reading lights, pilot control lights, CAPS
More informationCIRRUS AIRPLANE MAINTENANCE MANUAL
MODEL SR0 INSTRUMENT AND CONTROL PANEL. DESCRIPTION Serials 00 thru 336, 337 thru w/o PFD: The airplane uses standard flight instruments arranged in the basic-six pattern. The airspeed indicator, attitude
More informationCIRRUS AIRPLANE MAINTENANCE MANUAL
MODEL SR0 FLIGHT ENVIRONMENTAL SYSTEMS. DESCRIPTION This section covers that portion of the system which senses environmental conditions and uses the data to influence navigation of the airplane. This
More informationCIRRUS AIRPLANE MAINTENANCE MANUAL
MODEL SR FLIGHT ENVIRONMENTAL SYSTEMS. DESCRIPTION This section covers that portion of the system which senses environmental conditions and uses the data to influence navigation of the airplane. This includes
More informationIndicating. 1. General. A. Fuel Quantity. B. Fuel Flow
Indicating GENERAL 28-40: INDICATING. General A. Fuel Quantity A dual reading fuel quantity indicator is displayed in the Fuel Qty block of the ENGINE page along calibrated vertical bars. The fuel quantity
More informationATTITUDE AND DIRECTION
All ATTITUDE AND DIRECTION 1. DESCRIPTION This section contains information pertaining to those portions of the system which use magnetic, gyroscopic, and inertia forces. Included is the magnetic compass,
More informationC I R R U S CONTROLLING DESCRIPTION
CONTROLLING 1. DESCRIPTION Serials 22-0002 & subs: An electric two-speed fuel pump provides boost (low speed) and prime (high speed) for the engine. A console mounted rocker switch located on the center
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 informationCIRRUS AIRPLANE MAINTENANCE MANUAL MODELS SR22 AND SR22T CHAPTER 28-00: FUEL GENERAL. Fuel 28-00: FUEL. 1. General
CIRRUS AIRPLANE MAINTENANCE MANUAL Fuel CHAPTER 28-00: GENERAL 28-00: 1. General This chapter contains information on the storage, distribution, and indicating components of the fuel system. The engine
More informationCIRRUS AIRPLANE MAINTENANCE MANUAL
All ATTITUDE AND DIRECTION 1. DESCRIPTION This section contains information pertaining to those portions of the system which use magnetic, gyroscopic, and inertia forces. Included is the magnetic compass,
More informationCIRRUS AIRPLANE MAINTENANCE MANUAL
1. GENERAL This chapter contains information on the storage, distribution, and indicating components of the fuel system. The engine is supplied with fuel drawn out of the left or right integral fuel tank
More informationFlight Environmental Systems
CIRRUS AIRPLANE MAINTENANCE MANUAL Flight Environmental Systems CHAPTER 34-0: FLIGHT ENVIRONMENTAL SYSTEMS GENERAL 34-0: FLIGHT ENVIRONMENTAL SYSTEMS. General This section covers that portion of the system
More information33-40 EXTERIOR LIGHTING
EXTERIOR LIGHTING. DESCRIPTION This section covers that portion of the system which provides illumination outside of the aircraft. This includes the landing light, anti-collision strobe light, and recognition
More informationCIRRUS AIRPLANE MAINTENANCE MANUAL
ELEVATOR AND PITCH TRIM SYSTEM 1. DESCRIPTION This section describes that portion of the flight control system which controls the position and movement of the elevator. Included are; elevator system torque
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 informationCIRRUS AIRPLANE MAINTENANCE MANUAL
AUXILIARY STRUCTURE 1. DESCRIPTION The leading edge of the wing is manufactured from composite materials. This airplane has a one-piece wing with individual wing tips. The wing tips are manufactured from
More informationFLIGHT SIMULATOR SYSTEMS
FLIGHT SIMULATOR SYSTEMS 1. GENERAL This section describes systems required for simulator operation. This equipment includes the Cirrus Landing Gear Simulator (CLGS). 2. DESCRIPTION The intent of the CLGS
More information22-11 SYSTEM 55 AUTOPILOT
SYSTEM 55 AUTOPILOT 1. DESCRIPTION This section covers those systems and components which use inputs to the system to automatically control the flight path of the aircraft through adjustment to the pitch/roll
More informationCIRRUS AIRPLANE MAINTENANCE MANUAL
POWER CONTROL. DESCRIPTION This section describes those components which furnish a means of controlling engine power. Engine controls for the airplane include the following: control quadrant, throttle
More informationDC Generation. 1. General. A. DC Generation
CIRRUS AIRPLANE MAINTENANCE MANUAL DC Generation CHAPTER -0: DC GENERATION GENERAL -0: DC GENERATION 1. General (See Figure -0-1) This section covers the systems to generate, regulate, control, and indicate
More informationCIRRUS AIRPLANE MAINTENANCE MANUAL
CENTRAL WARNING SYSTEMS 1. GENERAL This section describes the Central Warning Systems which consists of a Crew Alerting System (CAS) and related sensors and switches. A. Crew Alerting System Aircraft annunciations
More information57-20 AUXILIARY STRUCTURE
AUXILIARY STRUCTURE 1. DESCRIPTION The leading edge of the wing is manufactured from composite materials. This airplane has a one-piece wing with individual wing tips. The wing tips are manufactured from
More informationCIRRUS AIRPLANE MAINTENANCE MANUAL
MODEL SR0 EXTERIOR LIGHTING. DESCRIPTION This section covers that portion of the system which provides illumination outside of the aircraft. This includes the landing light, anti-collision strobe light,
More informationALT #2 fail light on but Alternator is still charging (MCU 100/120):
ALT #2 fail light on but Alternator is still charging (MCU 100/120): We have seen this happen a lot. The good news is there is probabl nothing wrong with the aircraft. Basic MCU Function: The MCU has a
More informationFlaps System. 1. General
CIRRUS AIRPLANE MAINTENANCE MANUAL Flaps System CHAPTER 27-50: FLAPS SYSTEM GENERAL 27-50: FLAPS SYSTEM 1. General This section describes that portion of the flight control system which controls the position
More informationC I R R U S DISTRIBUTION DESCRIPTION
MODELS SR AND SRT DISTRIBUTION. DESCRIPTION This section contains information on the distribution system. The fuel distribution system consists of electric and mechanical (engine-driven) fuel pumps, fuel
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 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 informationCIRRUS AIRPLANE MAINTENANCE MANUAL
SPECIAL PURPOSE EQUIPMENT 1. GENERAL This section describes special purpose equipment on the airplane. This equipment includes the Cirrus Airplane Parachute System (CAPS) and the aft tiedown ballast bracket.
More informationNOTE: SB is a WAAS only supported build. If the autopilot is not WAAS equipped, the unlock card cannot be used at this time.
Single Engine Service Bulletin July 22, 2011 TITLE GARMIN G1000 / FLINT AERO, INC AUXILIARY FUEL GALLON REMAINING ENABLEMENT EFFECTIVITY The following airplanes equipped with the Garmin G1000 Nav III Avionics
More informationCIRRUS AIRPLANE MAINTENANCE MANUAL
SYSTEM 55 AUTOPILOT 1. DESCRIPTION The S-TEC System 55 is a dual axis autopilot system that provides roll stability, heading hold, NAV/GPS tracking, altitude hold, vertical speed selection, automatic glideslope
More informationSPECIAL PURPOSE EQUIPMENT
All SPECIAL PURPOSE EQUIPMENT 1. GENERAL This section describes special purpose equipment on the airplane. This equipment includes the Cirrus Airplane Parachute System (CAPS) the aft tiedown ballast bracket,
More informationLOG OF REVISIONS. Model G58 Baron (Serials TH-2125 and After) Pilot s Operating Handbook and FAA Approved Airplane Flight Manual
LOG OF REVISIONS Model G58 Baron (Serials TH-2125 and After) Pilot s Operating Handbook and FAA Approved Airplane Flight Manual Revision A12 - May, 2015 Title Page LOEP LOR Section 1 All Reformatted to
More informationCIRRUS AIRPLANE MAINTENANCE MANUAL
AIR INTAKES 1. DESCRIPTION This section describes that portion of the power plant which directs mass air flow to the engine. Induction air enters the engine through a filter mounted on the left, forward
More informationCHAPTER 24 - ELECTRICAL POWER TABLE OF CONTENTS
ELECTRICAL POWER 24-00 General 1 Electrical Power - Serials w/o Perspective Avionics 1 Electrical Power - Serials w/ Perspective Avionics 1 Troubleshooting 2 DC GENERATION 24-30 Description 1 DC Generation
More informationCIRRUS SR2X SB 2X Service Bulletin. Issued: February 27, SNS SUBJECT: TEMPERATURE CONTROL - Cabin Air Coupler Actuator Rigging
CIRRUS SR2X Service Bulletin Number: Issued: February 27, 2012 SNS SUBJECT: 21-60 TEMPERATURE CONTROL - Cabin Air Coupler Actuator Rigging 1. COMPLIANCE Recommended, On Condition: Accomplish this Service
More information53-40 ATTACH FITTINGS
ATTACH FITTINGS. DESCRIPTION Attach fittings are provided for attachment of the seats (Refer to -0), baggage straps (Refer to -0), rear seat harnesses (Refer to -0), cargo net straps (Refer to -0), cabin
More informationService Bulletin No.: D42L Rev 0 Date Issued: 06 June 2016 Title: GTX 33ES Installation Page: 1 of 6
Title: GTX 33ES Installation Page: 1 of 6 1. ATA Code: 3450 2. Effectivity: All DA42 aircraft with TCCA STC SA09-54 or FAA STC SA02725NY installed with Garmin GIA 63W (WAAS). 3. General: This Service Bulletin
More informationC I R R U S BRAKES DESCRIPTION
BRAKES. DESCRIPTION The brake system consists of a single disc brake assembly on each main landing gear wheel, master cylinder for each rudder pedal, hydraulic fluid reservoir, parking brake, and associated
More informationC I R R U S COLLECTOR DESCRIPTION
COLLECTOR 1. DESCRIPTION This section describes the portion of the exhaust system which collects the exhaust gases from the cylinder and conducts them overboard. Included are the exhaust headers and collector
More informationAll KODIAK 100 Series Aircraft; see Compliance section below for details of applicability.
KODIAK MANDATORY SERVICE BULLETIN SB12-04 NUMBER: SB12-04 REVISION: 00 DATE: May 31, 2012 SUBJECT: KODIAK 100 Fuel Quantity Calibration *MANDATORY SERVICE BULLETIN* EFFECTIVITY: All KODIAK 100 Series Aircraft;
More informationService Bulletin. ATA 27-00: Flight Controls Rudder-Aileron Interconnect Modification
Service Bulletin Issued: 09 May 2007 Models SR20 and SR22 ATA 27-00: Flight Controls Rudder-Aileron Interconnect Modification COMPLIANCE Mandatory: Accomplish this Service Bulletin within 25 Flight Hours
More informationPitch Control and Trim
Pitch Control and Trim GENERAL 27-30: PITCH CONTROL AND TRIM. General This section describes that portion of the flight control system which controls the position and movement of the elevator. This includes
More informationCIRRUS AMM TEMPORARY REVISION
CIRRUS AMM TEMPORARY REVISION MODEL SF50 SF50 AMM Temporary Revision --01 Brakes Affected Manuals: SF50 Airplane Maintenance Manual (18-001, Revision 1) Serial Numbers: SF50 Serials 0005 & subs Filing
More informationSERVICE BULLETIN NAVIGATION - GARMIN G1000 SYSTEM UPGRADES INCLUDING TERRAIN AWARENESS AND WARNING SYSTEM (TAWS-B) FUNCTION PER STC SA01725SE
Beechcraft TITLE: NAVIGATION - GARMIN G1000 SYSTEM UPGRADES INCLUDING TERRAIN AWARENESS AND WARNING SYSTEM (TAWS-B) FUNCTION PER STC SA01725SE SYNOPSIS OF CHANGE This Service Bulletin (SB) has been revised
More informationCIRRUS AIRPLANE MAINTENANCE MANUAL
POWER PLANT 1. GENERAL This chapter describes maintenance practices for the airplane systems which provide the means to induce and convert fuel-air mixture into power such as the engine, baffling, cowling,
More informationATP Aircraft Registration Profile
ADs Aircraft Registration Profile 10/21/2014 Profile ID: Created: 10/7/2014 Changed: 10/21/2014 Owner/Operator: KILO ECHO LLC Contact: Address: 341 Raven Circle, Wyoming, Delaware 19934-4033 USA Phone:
More informationG1000 / GFC 700. Diamond DA 40 & DA 40 F. Instructions for Continued Airworthiness May, 2006 Revision A
G1000 / GFC 700 Instructions for Continued Airworthiness Diamond DA 40 & DA 40 F 190-00492-03 May, 2006 Revision A Copyright 2006 Garmin Ltd. or its subsidiaries All Rights Reserved Except as expressly
More informationYaw Control and Trim. 1. General. A. Yaw Control System. B. Yaw Trim System
CIRRUS AIRPLANE MAINTENANCE MANUAL MODELS SR AND SRT Yaw Control and Trim CHAPTER 7-0: YAW CONTROL AND TRIM GENERAL 7-0: YAW CONTROL AND TRIM. General This section describes that portion of the flight
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 informationPASSENGER AND CREW DOORS
MODELS SR AND SRT PASSENGER AND CREW DOORS. DESCRIPTION AND OPERATION Serials -000 thru -00: The two crew/passenger doors incorporate a flush-mount outside door handle, key-operated door lock, and a conventional
More informationCHAPTER 13 INSTRUMENTS
CHAPTER 13 INSTRUMENTS Section Title Page 13.000 Description.............................................. 13.1 13.100 Pitot-Static System......................................... 13.3 13.200 Primary Instruments........................................
More informationSYSTEM LOAD CHARTS AND BUS SCHEMATICS
SYSTEM LOAD CHARTS AND BUS SCHEMATICS 1. GENERAL The airplane is equipped with a two alternator system, with each alternator operating continuously. Serials 22-0002 thru 22-1601, 22-1603 thru 22-1820,
More informationIssue 2.0 December EPAS Midi User Manual EPAS35
Issue 2.0 December 2017 EPAS Midi EPAS35 CONTENTS 1 Introduction 4 1.1 What is EPAS Desktop Pro? 4 1.2 About This Manual 4 1.3 Typographical Conventions 5 1.4 Getting Technical Support 5 2 Getting Started
More informationCIRRUS AIRPLANE MAINTENANCE MANUAL
MODEL SR PASSENGER AND CREW DOORS. DESCRIPTION AND OPERATION Serials 000 thru 00: The two crew/passenger doors incorporate a flush-mount outside door handle, key-operated door lock, and a conventional
More informationCIRRUS SR2X SB 2X R2. Service Bulletin. Issued: Revised: June 26, 2012 July 31, 2012
CIRRUS SR2X Service Bulletin Number: Issued: Revised: June 26, 2012 SNS SUBJECT: 57-40 ATTACH FITTINGS - Lower Landing Gear Attach Bracket Torque 1. COMPLIANCE Mandatory: Cirrus Design considers this Service
More informationSERVICE INFORMATION NO. SI
Diamond Aircraft Industries G.m.b.H. N.A. Otto-Straße 5 A-2700 Wiener Neustadt Austria DAI SI 42-141 Page 1 of 1 25-Aug-2010 FT SERVICE INFORMATION NO. SI-42-141 : SI s are used only: 1) To distribute
More informationCHAPTER 27 - FLIGHT CONTROLS TABLE OF CONTENTS
FLIGHT CONTROLS 27-00 General 1 Troubleshooting 2 AILERON AND ROLL TRIM SYSTEM 27-10 Aileron System Cables 2 Removal - Aileron System Cables 2 Installation - Aileron System Cables 2 Adjustment/Test - Aileron
More informationCIRRUS AIRPLANE MAINTENANCE MANUAL
PROPELLER 1. GENERAL The airplane employs a 3 blade, constant speed, non-feathering propeller. The blades (composite or aluminum) are mounted in an aluminum hub which contains the pitch changing mechanism
More informationCIRRUS AIRPLANE MAINTENANCE MANUAL
MODEL SR0 YAW CONTROL AND TRIM. GENERAL This section describes that portion of the flight control system which controls the position and movement of the rudder. Included are; rudder system rigging, rudder
More informationCIRRUS AIRPLANE MAINTENANCE MANUAL
NOISE SUPPRESSOR 1. DESCRIPTION Noise suppression is accomplished through use of a heat exchanger (Serials 0002 thru 019) or a heat exchanger and muffler (Serials 020 & subs) connected to the exhaust header
More informationPropeller Assembly. 1. General
Propeller Assembly GENERAL 61-10: PROPELLER ASSEMBLY 1. General The propeller assembly consists of a hollow aluminum hub which supports the propeller blades and also houses the pitch changing mechanism.
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 informationCIRRUS AIRPLANE MAINTENANCE MANUAL
MODEL SR0 All PASSENGER AND CREW DOORS. DESCRIPTION AND OPERATION Serials 005 thru 4: The two crew/passenger doors incorporate a flush-mount outside door handle, key-operated door lock, and a conventional
More informationCIRRUS AIRPLANE MAINTENANCE MANUAL
BRAKES. DESCRIPTION The brake system consists of single disc brake assembly on each main landing gear wheel, master cylinder for each rudder pedal, hydraulic fluid reservoir, parking brake, and associated
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 informationService Bulletin. ATA 52-10: Passenger and Crew Doors Door Latching Assembly Upgrade
Service Bulletin Issued: 5 Oct 00 Models SR0 and SR ATA 5-10: Passenger and Crew Doors Door Latching Assembly Upgrade COMPLIANCE Optional: Accomplishment of this Service Bulletin is at the owner s option.
More informationCHAPTER 22 AUTOPILOT
Section Title CHAPTER 22 AUTOPILOT 22-00 Description............................................... 22.1 22-10 (Pitch) Servo Assembly...................................... 22.3 22-20 (Roll) Servo Assembly.......................................
More informationG1000 Synthetic Vision & Pathways Option
G1000 Synthetic Vision & Pathways Option Activation Instructions For G1000 Installations in Diamond DA40 / DA40 F Aircraft Contains Instructions for Continued Airworthiness for STC #SA01480WI-D 190-00545-10
More information*MANDATORY SERVICE BULLETIN*
NUMBER: SB11-12 REVISION: 00 DATE: 08/05/2011 EFFECTIVITY: KODIAK 100 Series Aircraft Serial Numbers: 100-0001 through 100-0054. KO D I A K SUBJECT: FUEL QUANTITY CALIBRATION PROCEDURES SUMMARY: It has
More information57-50 FLIGHT SURFACES
FLIGHT SURFACES 1. DESCRIPTION The flaps are mounted to the trailing edge of each wing between the inboard end of the ailerons and the fuselage. The ailerons are located near the wing tips and hinge to
More informationEPAS Desktop Pro Software User Manual
Software User Manual Issue 1.10 Contents 1 Introduction 4 1.1 What is EPAS Desktop Pro? 4 1.2 About This Manual 4 1.3 Typographical Conventions 5 1.4 Getting Technical Support 5 2 Getting Started 6 2.1
More informationPassenger And Crew Door
CIRRUS AIRPLANE MAINTENANCE MANUAL Passenger And Crew Door CHAPTER 5-10: PASSENGER AND CREW DOOR GENERAL 5-10: PASSENGER AND CREW DOOR 1. General The two crew/passenger doors incorporate a flush-mount
More informationCIRRUS AIRPLANE MAINTENANCE MANUAL
FLIGHT SURFACES. DESCRIPTION The flaps are mounted to the trailing edge of each wing between the inboard end of the ailerons and the fuselage. The ailerons are located near the wing tips and hinge to the
More informationCIRRUS AIRPLANE MAINTENANCE MANUAL
AIR INTAKES 1. DESCRIPTION This section describes that portion of the power plant which directs mass air flow to the engine. Induction air enters the engine through a filter mounted on the right, aft side
More informationSERVICE NOTICE. 1. The configuration of each Garmin LRU specific to the KODIAK The Garmin LRU software.
SUBJECT: G1000 Configurations and Updates EFFECTIVITY: As required BACKGROUND This Service Notice is to make customers aware of the different software configurations available for their G1000-equipped
More informationDASSAULT AVIATION Proprietary Data
F2000EX 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 Equipment location 02-49-10 DESCRIPTION Introduction Description Operating
More informationCHAPTER 13 INSTRUMENT SYSTEM
CHAPTER 13 INSTRUMENT SYSTEM Section Title 13-00 Description............................................... 13.1 13-10 Pitot-Static System......................................... 13.3 13-20 Primary Instruments.........................................
More informationTHE SOFTWARE WILL BE AVAILABLE ON TechCONNECT ON FEBRUARY 3, 2004.
NUMBER: 18-002-04 GROUP: Vehicle Performance DATE: February 3, 2004 This bulletin is supplied as technical information only and is not an authorization for repair. No part of this publication may be reproduced,
More informationSB SWITCH CONTROL BOX
Carson Manufacturing Co., Inc. 5451 North Rural Street Indianapolis, IN 462 Phone: (888) 577-6877 Fax: (317) 254-2667 www.carsonsirens.com SB-008-25 SWITCH CONTROL BOX INSTALLATION AND OPERATING INSTRUCTIONS
More informationTroubleshooting Procedure for Discharged Battery
MBE 900 SERVICE MANUAL 14.6 NO START (ENGINE WILL NOT ROTATE) There are several causes for the engine to not start. These probable causes are: Discharged Battery Defective Magnetic Switch Defective Starter
More informationPRODUCT INFORMATION BULLETIN #3365 DIGITAL MOTOR CONTROL PLATTER SYSTEMS For Serial Number and After
PRODUCT INFORMATION BULLETIN #3365 DIGITAL MOTOR CONTROL PLATTER SYSTEMS For Serial Number 28640996 and After Record Platter System Identification Numbers Here: Model # Serial # Table of Contents Program
More informationSECTION 3 ENGINE INDICATION SYSTEM (EIS)
ENGINE INDICATION SECTION ENGINE INDICATION () NOTE: Refer to the Pilot s Operating Handbook (POH) for limitations. The Engine Indication System () displays critical engine, electrical, fuel, and other
More informationMini-Lab Gas Turbine Power System TM Sample Lab Experiment Manual
Mini-Lab Gas Turbine Power System TM Sample Lab Experiment Manual Lab Session #1: System Overview and Operation Purpose: To gain an understanding of the Mini-Lab TM Gas Turbine Power System as a whole
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 informationC I R R U S CABIN 1. DESCRIPTION A. Cabin Seats B. Radio Module Assembly
CABIN. DESCRIPTION This section covers cabin compartment seats, seat harnesses, trim, cabin headliner, floor covering, sunvisors, grab handles, headset hooks, coat hooks, drink holders, storage pockets,
More informationSERVICE BULLETIN TITLE ENGINE CONTROLS - FULL AUTHORITY DIGITAL ENGINE CONTROL (FADEC) SOFTWARE UPGRADE VERSION C10
Citation SB750-76-12 TITLE ENGINE CONTROLS - FULL AUTHORITY DIGITAL ENGINE CONTROL (FADEC) SOFTWARE UPGRADE VERSION C10 EFFECTIVITY REASON MODEL SERIAL NUMBERS 750 (Citation X) -0001 thru -0313 NOTE: Airplanes
More informationSNS SUBJECT: NOSE GEAR - Nose Landing Gear Assembly Inspection and Reinforcement
CIRRUS SR22 Service Bulletin Number: Issued: SNS SUBJECT: 32-20 NOSE GEAR - Nose Landing Gear Assembly Inspection and Reinforcement 1. COMPLIANCE Mandatory: Cirrus Design considers this Service Bulletin
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 informationINTECH Micro 2300-RTD6
INTECH Micro 2300-RTD6 6 Channel RTD Input Station Overview. The Intech Micro 2300 Series is a system of modular I/O Remote Stations, that add an even lower cost option to Intech s already extensive intelligent
More information