Rotax 914 F Installation Manual
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Rotax 914 F Installation Manual

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See also: Maintenance Manual
Installation Manual
Installation Manual
ROTAX Engine
ROTAX Engine
Before starting with the engine installation, please, read the Installation Manual completely as
it contains important safety-relevant information. Failure to do so may result in personal
injuries including death.
These technical data and the information contained therein are property of BOMBARDIER-
ROTAX GmbH and must not be reproduced, neither in entirety nor partially, and passed on to
third parties without previous consent in writing by BOMBARDIER-ROTAX GmbH. This text
must be written on every complete or partial reproduction.
Approval of translation to best knowledge and judgement - in any case the original text in German language is authoritative.
Recommended price:
Part no.: 897 816
AIRCRAFT ENGINES
Type 914 F
Type 914 F
Copyright - BOMBARDIER - ROTAX GmbH
ATS 200,--
DM
28,--
f o r
f o r
WARNING
Edition: 0 of 1996 05 10

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Summary of Contents for Rotax 914 F

  • Page 1 These technical data and the information contained therein are property of BOMBARDIER- ROTAX GmbH and must not be reproduced, neither in entirety nor partially, and passed on to third parties without previous consent in writing by BOMBARDIER-ROTAX GmbH. This text must be written on every complete or partial reproduction.

  • Page 2: Table Of Contents

    12.6) Feasible location of radiator ..................35 12.7) General directives for the cooling system ............... 36 12.8) Cooling air ducting ....................38 12.8.1) General directives for ducting of the cooling air ............ 38 Date Install Page Reference Modification-No. 1996 05 10 914 F - 0 -...
  • Page 3 16.3) Notes to employment of the air filter ............... 65 17) Pressure sensors ....................67 17.1) Static pressure sensor .................... 68 17.2) Airbox pressure sensor ................... 69 17.2.1) Water trap ......................69 18) Servo motor ......................70 Modification-No. Reference Install Date Page - 0 - 1996 05 10 914 F...
  • Page 4 23.5) Monitoring of the intake manifold pressure ............. 97 23.6) Air temperature in the airbox ................... 97 24) Preparations for trial run of engine ..............98 AUTHORIZED DISTRIBUTORS for Aircraft Engines ........99 Date Install Page Reference Modification-No. 1996 05 10 914 F - 0 -...
  • Page 5 Blank page Modification-No. Reference Install Date Page - 0 - 1996 05 10 914 F...

  • Page 6: Index

    Engine speed 20 Propeller drive 90 Engine suspension 24, 28 Protective covering 23 Engine views 18 Exhaust gas temperature 31 Exhaust system 30 Expansion tank 33 External alternator 87 Date Install Page Reference Modification-No. 1996 05 10 914 F - 0 -...
  • Page 7 Turbo Control Unit (TCU) 76, 84 Vacuum pump 91 Venting line of oil tank 42 Warning light 86 Water inlet bend 34 Water trap 69 Weights 21 Wiring diagram (electric) 74 Modification-No. Reference Install Date Page - 0 - 1996 05 10 914 F...

  • Page 8: Preface

    If any passages of the Manual are not completely understood or in case of questions, please, contact an authorized Distribution- or Service Partner for ROTAX engines. We wish you much pleasure and satisfaction flying your aircraft powered by this ROTAX engine.

  • Page 9: Repeating Symbols

    Due to the varying designs, equipment and types of aircraft, BOMBARDIER-ROTAX makes no warranty or representation on the suitability of its engine’s use on any particular aircraft.
  • Page 10 Since special tools and equipment may be required, engine servicing should only be performed by an authorized BOMBARDIER-ROTAX engine dealer or a qualified trained mechanic approved by the local airworthiness authority.

  • Page 11: Instruction

    This engine must only be operated with accessories supplied, recommended and released by ROTAX. Modifications are only allowed after consent by the engine manufacturer. ATTENTION: Spare parts must meet with the requirements defined by the engine manufacturer.

  • Page 12: Technical Documentation

    The fast technical progress and variations of installation might render present laws and regulations inapplicable or inadequate. Date Install Page Reference Modification-No. 1996 05 10 914 F - 0 -...
  • Page 13 Blank page Modification-No. Reference Install Date Page - 0 - 1996 05 10 914 F...

  • Page 14: List Of The Current

    96 05 10 96 05 10 96 05 10 96 05 10 96 05 10 96 05 10 96 05 10 96 05 10 53 blank 96 05 10 Date Install Page Reference Modification-No. 1996 05 10 914 F - 0 -...

  • Page 15: Table Of Amendments

    0 - 2 5 1996 05 10 not required 1996 05 10 KD/Me 1 - 1 0 1 Modification-No. Reference Install Date Page - 0 - 1996 05 10 914 F...

  • Page 16: Description Of Design

    7.1) Designation of type Basic type e.g. ROTAX 914 F2: F2: with prop flange for fix pitch propeller F3: with prop flange with drive of hydraulic governor for constant speed propeller F4: with prop flange for fix pitch propeller, but prepared for retro-fit of hydraulic...
  • Page 17 Components especially developed and tested for this en- gine are readily available at BOMBARDIER-ROTAX. WARNING: This equipment has not been tested for safety and durability to the standards of aviation. The user assumes all risks possibly arising by utilizing auxiliary equipment.

  • Page 18: Engine Components, Engine Views, Numbering Of Cylinders, Definition Of Main Axes

    F sensor for oil pressure f oil tank u expansion tank G sensor for oil temperature g external alternator i 2 separate oil pumps H sensor for cylinder head temperature Date Install Page Reference Modification-No. 1996 05 10 914 F - 0 -...
  • Page 19 Ill. 3 Ill. 5 Cyl. 4 Cyl. 3 Cyl. 2 Cyl. 1 Ill. 4 Ill. 6 Modification-No. Reference Install Date Page - 0 - 1996 05 10 914 F...

  • Page 20: Technical Data

    See ill. 7. max........40° NOTE: Up to this inclination the dry sump lubrication system warrants adequate lubrication in every flight situation. Ill. 7 Date Install Page Reference Modification-No. 1996 05 10 914 F - 0 -...

  • Page 21: Installation Dimensions (All Dimensions In Mm)

    - x1 moment of inertia around 24 560 25 450 axis y1 - y2 moment of inertia around 26 520 27 480 axis z1 - z3 Modification-No. Reference Install Date Page - 0 - 1996 05 10 914 F...

  • Page 22: Preparations For Engine Installation

    12 month after date of delivery from BOMBARDIER-ROTAX. This warranty is subject to the following conditions: the engine has to be stored in the packing as supplied by ROTAX. the covers on various openings must not be removed (see chapter of protective covering) engine has to be stored in a suitable place.

  • Page 23: Protective Covering

    WARNING: The maximum storage period is limited to 24 month! Preservation for periods of longer than 24 months is only possible after a written permission of BOMBARDIER-ROTAX. Should the situation arise send engine for inspection to ROTAX. NOTE: No trouble to put engine back into operation after preservation.

  • Page 24: Engine Suspension And Position

    WARNING: If the engine suspension frame supplied by ROTAX is not used or if modified, certification to the latest requirements such as FAR or JAR has to be conducted by the aircraft builder.

  • Page 25: Definition Of Attachment Points

    (limit load) in (Nm) 1 0 0 and z axis in x, y and z axis WARNING: Tighten all engine suspension screws as specified by the aircraft builder. Modification-No. Reference Install Date Page - 0 - 1996 05 10 914 F...

  • Page 26: Permissible Fitting Positions

    To prevent a possible hydraulic shock at engine start, ensure proper closing of float valves. If in doubt, park the aircraft with rising propeller shaft axis. 6° 6° L(T)2 R(T)2 30° Ill. 11 Date Install Page Reference Modification-No. 1996 05 10 914 F - 0 -...
  • Page 27 Tolerated roll deviation of parallelism: ......± 5°. (see ill. 12) Vertical axis: y-axis must be square to the longitudinal axis of the aircraft. Ill. 13 10° 10° Yaw tolerance: ± 10° (see ill. 13) Modification-No. Reference Install Date Page - 0 - 1996 05 10 914 F...

  • Page 28: General Directives For Engine Suspension

    NOTE: The engine suspension has to be designed to prevent any excessive engine movement and to minimize noise emission and vibration on air frame side. Date Install Page Reference Modification-No. 1996 05 10 914 F - 0 -...
  • Page 29 Blank page Modification-No. Reference Install Date Page - 0 - 1996 05 10 914 F...

  • Page 30: Exhaust System

    The complete exhaust system is in the volume of supply and is certified together with the engine. WARNING: If the ROTAX exhaust system is not employed or if modified, certification to the latest requirements such as FAR or JAR has to be conducted by the aircraft builder.

  • Page 31: Operating Limits

    Exhaust gas temperature: (1740 ° F) max................. 950° C (1650 ° F) normal ..............900° C Reading taken approx. 70 mm ( 2,75 in.) after exhaust flange. Modification-No. Reference Install Date Page - 0 - 1996 05 10 914 F...

  • Page 32: Cooling System

    12.1) Description of the system See ill. 16. The cooling system of the ROTAX 914 F is designed for liquid cooling of the cylinder heads and ram-air cooling of the cylinders. The cooling system of the cylinder heads is a closed circuit with an expansion tank.

  • Page 33: Requirements On The Cooling System

    WARNING: The size and layout of the cooling system must be designed to keep the operating temperatures within the specified limits. To minimize flow resistance employ radiator with low flow resistance and parallel flow as realized on the original BOMBARDIER-ROTAX radiator and use short hoses and pipelines. Coolant hoses: temperature durability: min.

  • Page 34: Coolant Capacity

    250 cm 2 m coolant hose (18 mm inside dia.) : ........500 cm total coolant quantity in engine: approx. 1410 cm (3/8 gal (us)) Date Install Page Reference Modification-No. 1996 05 10 914 F - 0 -...

  • Page 35: Feasible Location Of Radiator

    WARNING: Ensure that the overflow bottle will never be empty, otherwise air will be sucked into cooling circuit with ill effect to safe operation of the engine. Modification-No. Reference Install Date Page - 0 - 1996 05 10 914 F...

  • Page 36: General Directives For The Cooling System

    12.7) General directives for the cooling system See illustration 21. BOMBARDIER-ROTAX offers essential parts of the cooling system for this engine such as radiator, overflow bottle etc. (see spare parts list) in the non-certified state. Certification to the latest requirements to FAR or JAR has to be conducted by the aircraft builder.
  • Page 37 Blank page Modification-No. Reference Install Date Page - 0 - 1996 05 10 914 F...

  • Page 38: Cooling Air Ducting

    For front installation in a closed fuselage, ducting of cooling air to the cylinders is recommended. In this case a costly horizontal partitioning can be avoided. BOMBARDIER-ROTAX developed especially for this application a non-certified cooling air ducting. WARNING: Certification to the latest requirement like FAR or JAR has to be conducted by the aircraft builder.
  • Page 39 Blank page Modification-No. Reference Install Date Page - 0 - 1996 05 10 914 F...

  • Page 40: Lubrication System

    13) Lubrication system 13.1) Description of the system See Ill. 22. The BOMBARDIER-ROTAX 914 F engine is provided with a dry sump forced lubrication system with a main oil pump with integrated pressure regulator and a n additional suction pump.

  • Page 41: Limits Of Operation

    ......ca. 90 ÷ 110 C (190 - 250 ° F) WARNING: At operation below nominal oil temperature formation of condensate in the lubrication system might influence oil quality. Modification-No. Reference Install Date Page - 0 - 1996 05 10 914 F...

  • Page 42: Requirements On The Oil- And Venting Lines

    Protection by insulation, or routing in a hose with hot air flow or by furnishing venting line with a bypass opening Q before passing through cowling W. See ill. Ill. 23 Date Install Page Reference Modification-No. 1996 05 10 914 F - 0 -...

  • Page 43: Connecting Dimensions And Location Of Connections

    ....... 8 mm (0,31 in.) slip-on length ......max. 20 mm (0,79 in.) Tightening torque of banjo bolt T M10x1x19: 17 Nm (150 in.lb) Ill. 26 Modification-No. Reference Install Date Page - 0 - 1996 05 10 914 F...

  • Page 44: 3) Oil Tank

    This screw plug has to be removed and is replaced by the hose nipple P, sealing ring w 10x14 DIN 7603 and banjo bolt {. Ill. 28 Date Install Page Reference Modification-No. 1996 05 10 914 F - 0 -...
  • Page 45 Blank page Modification-No. Reference Install Date Page - 0 - 1996 05 10 914 F...

  • Page 46: Feasible Position And Location Of The Oil Tank

    Install the oil tank free of vibrations. Oil tank cover E and oil drain plug to be easily accessible. Ill. 29 Date Install Page Reference Modification-No. 1996 05 10 914 F - 0 -...

  • Page 47: Feasible Position And Location Of The Oil Cooler

    If need be, take appropriate measures like changing size of cooler, partial covering of cooler etc. 13.7) General notes on oil cooler BOMBARDIER-ROTAX offers for this engine a non-certified oil cooler (see spare parts list). WARNING: Certification of this cooler to the latest requirements such as FAR or JAR has to be conducted by the aircraft builder.

  • Page 48: Fuel System

    Feeding lines to suction side of the electric fuel pumps W lines from pressure side of the electric fuel pump to inlet of fuel pressure control Returnline from fuel pressure control to oil tank Date Install Page Reference Modification-No. 1996 05 10 914 F - 0 -...

  • Page 49: Operating Limits

    Fuel temperature: To prevent vapour locks temperatures in excess of 36°C (100°F) are not permis- sible in the vicinity of fuel lines, float chamber and such. Modification-No. Reference Install Date Page - 0 - 1996 05 10 914 F...

  • Page 50: Connecting Dimensions, Location Of Joints And Directives For Installation

    30 min. ø8 NOTE: A capacity increase of approx. 20% is feasible by running-in process. ø9 Date Install Page Reference Modification-No. 1996 05 10 914 F - 0 -...
  • Page 51 There is no need for a checkvalve for the operation of the two electric fuel pumps since the pump itself won't allow any passage against correct direction of flow ATTENTION: Employ GENUINE-BOMBARDIER-ROTAX fuel pumps only. Non-compliance will release BOMBARDIER-ROTAX from any liability.

  • Page 52: 2) Fuel Pressure Control

    1/3. The additional nipple can be fitted of course to any other connections with the exception of outlet T. All the necessary items are available as spare parts. Date Install Page Reference Modification-No. 1996 05 10 914 F - 0 -...
  • Page 53 Blank page Modification-No. Reference Install Date Page - 0 - 1996 05 10 914 F...

  • Page 54: Carburetor

    ATTENTION: With closed or blocked leakage piping, fuel could end up on exhaust system. RISK OF FIRE! Connecting nipple W for leakage line outside dia. ø ..6 mm (1/4") slip on lengthmax. 17 mm (11/16") Ill. 35 Date Install Page Reference Modification-No. 1996 05 10 914 F - 0 -...

  • Page 55: Connections For Bowden-Cable Actuation And Limit Load

    N (5,4 lb) limit load: 100 N (22 lb) Directive for choke actuation The choke shaft E is marked R. This mark has to point towards cable engagement Modification-No. Reference Install Date Page - 0 - 1996 05 10 914 F...

  • Page 56: Requirements On Cable Actuation

    Otherwise increase preten- sion of spring by bending lever flap Q or fit a stronger return spring, W or a cable with pull-push action would have to be used. Date Install Page Reference Modification-No. 1996 05 10 914 F - 0 -...

  • Page 57: Requirements On The Throttle Lever

    ATTENTION: Adjustable positive stops for idle- and full throttle position are of course required. These stops have to be designed such to render adjustibility and to prevent bending of the idle stop on the carburetor. Modification-No. Reference Install Date Page - 0 - 1996 05 10 914 F...

  • Page 58: Location And Determination Of The Throttle Position For Max. Continuous Power

    15.5.2) General information about the communication program The software is property of BOMBARDIER-ROTAX. Duplication is only permitted for transmission on a fixed disk or for back up and recording. The TCU must be switched on.
  • Page 59 If the bottom line Q displays "Error" instead of the sub NOTE: program, some connection between TCU and computer has been interrupted. Checking of all plug connections between TCU and computer is necessary. Ill. 41 Modification-No. Reference Install Date Page - 0 - 1996 05 10 914 F...

  • Page 60: 3) Checking Of The Throttle Position

    If the throttle position for idle and full throttle are not within the allowance variation or if not proceeding linear, then a new calibration of the throttle position is absolutely necessary. Refer to Maintenance Manual 914 F. Date Install...
  • Page 61 Blank page Modification-No. Reference Install Date Page - 0 - 1996 05 10 914 F...

  • Page 62: Air Intake System

    ø ..60 mm (2 3/8") slip-on length ..max. 25 mm (1") ATTENTION: Utilize the full slip-on length on all connection. Secure hoses by suitable screw clamps. Ill. 43 Ladeluftkühler (Intercooler) Date Install Page Reference Modification-No. 1996 05 10 914 F - 0 -...

  • Page 63: 1) Requirements On The Intake Air Ducting

    The pressure loss must not exceed 5 hPa. WARNING: Use only filter elements which will not tend to restrict the flow when in contact with water. Modification-No. Reference Install Date Page - 0 - 1996 05 10 914 F...

  • Page 64: 1) Airbox

    1/3 - 5 6 8 - 1 8 0 - 2 0 cylinder side 2/4 - 5 9 0 1 8 0 - 2 0 Date Install Page Reference Modification-No. 1996 05 10 914 F - 0 -...

  • Page 65: Notes To Employment Of The Air Filter

    16.3) Notes to employment of the air filter BOMBARDIER-ROTAX offers a dry type air filter. WARNING: The certification to the latest requirement such as FAR and JAR has to be conducted by the aircraft builder. The following points should assist the aircraft builder at the choice of a suitable filter.
  • Page 66 Blank page Date Install Page Reference Modification-No. 1996 05 10 914 F - 0 -...

  • Page 67: Pressure Sensors

    To avoid any mix-up of pressure sensor wiring, plug connections are colour coded. grey plug connection W static pressure sensor black plug connection E airbox pressure sensor Umgebungs-Drucksensor static pressure sensors Airbox-Drucksensor airbox pressure sensors Ill. 46 Modification-No. Reference Install Date Page - 0 - 1996 05 10 914 F...

  • Page 68: Static Pressure Sensor

    Location of installation is limited by the length of the wiring harness. length of cable assy.: approx. 250 mm (10 in) from TCU. ø3 ø4,7 60° 60° Ill. 47 Date Install Page Reference Modification-No. 1996 05 10 914 F - 0 -...

  • Page 69: Airbox Pressure Sensor

    W 4x7 of airbox and the airbox pressure sensor E. ATTENTION: Utilize full slip-on length on all connections. ø35 ø6 ø6 Ill. 49 ø30 Ill. 48 Modification-No. Reference Install Date Page - 0 - 1996 05 10 914 F...

  • Page 70: Servo Motor

    The correct adjustment of the servo cable Q and consequently the waste gate W was made already on the course of the testrun at ROTAX. Prior to engine operation check the position of the waste gate as follows: WARNING: Engine stop - ignition "OFF".
  • Page 71 Blank page Modification-No. Reference Install Date Page - 0 - 1996 05 10 914 F...

  • Page 72: Elektric System

    ATTENTION: An excess-voltage protection has to be realized by the aircraft builder in accordance to effective regulations. WARNING: The certification to the latest requirements such as FAR or JAR has to be conducted by the aircraft builder. Date Install Page Reference Modification-No. 1996 05 10 914 F - 0 -...

  • Page 73: 1) Electromagnetic Compatibility (Emc)

    RT CA DO-160C, sections 18, 20-22 and IEC 801-2. The following EMC/EMI tests were performed: Radio frequency Susceptibility (conducted) Radio frequency Susceptibility (radiated) Audio Frequency Susceptibility Lightning Susceptibility Conducted RF Interference Radiated RF Interference Modification-No. Reference Install Date Page - 0 - 1996 05 10 914 F...

  • Page 74: Wiring Diagram

    30-31 lamps isolating switch for servo motor 2 ignition switches master switch starter switch control lamp amperemeter battery relay battery bus bar capacitor 42-51 circuit breaker Date Install Page Reference Modification-No. 1996 05 10 914 F - 0 -...
  • Page 75 Verbraucher (consumer) Ill. 52 Modification-No. Reference Install Date Page - 0 - 1996 05 10 914 F...

  • Page 76: Description Of The Turbo Control Unit (Tcu)

    19.3) Description of the Turbo Control Unit (TCU) See Ill. 53/54. The ROTAX 914 F engine is equipped with an exhaust gas turbo charger, making use of the energy in the exhaust gas for precompression of the intake air (boost pressure).
  • Page 77 The TCU registers the time of full throttle operation (boost pressure). Full throttle operation for longer than 5 minutes will make the red boost lamp blinking Modification-No. Reference Install Date Page - 0 - 1996 05 10 914 F...

  • Page 78: Technical Data And Connection Of The Electric Components

    Use cables in this area as short as possible and with adequate cross section. never sever connection between terminal C and +B of regulator e.g. by removal of a fuse Date Install Page Reference Modification-No. 1996 05 10 914 F - 0 -...
  • Page 79 ......max ± 5% Ill. 57 (1/min.) 1000 2000 3000 4000 5000 6000 A charge-indicating lamp 3W/12V (Ill. 52, pos. s) may be fitted on NOTE: the instrument panel. Modification-No. Reference Install Date Page - 0 - 1996 05 10 914 F...

  • Page 80: 3) Electronic Modules

    Min. section area: 2x 0,75 mm (shielded flexible cable, shielding braid on both ends grounded). ATTENTION: The metal base of each ignition switch must be grounded to air craft frame. Date Install Page Reference Modification-No. 1996 05 10 914 F - 0 -...

  • Page 81: 5) Electric Starter

    DIN 46247 grounding: via housing ATTENTION: Activation of start relay limited to short duration. Over a period of 4 min. operation, the duty cycle is 25%. Modification-No. Reference Install Date Page - 0 - 1996 05 10 914 F...

  • Page 82: 7) Electric Fuel Pumps

    FAR or JAR and the effective wiring diagram (Ill. 52). WARNING: An essential point is according to regulations, that the fuel pumps are connected on two completely independent power supplies. Date Install Page Reference Modification-No. 1996 05 10 914 F - 0 -...
  • Page 83 Blank page Modification-No. Reference Install Date Page - 0 - 1996 05 10 914 F...

  • Page 84: 8) Turbo Control Unit (Tcu)

    FAR or JAR has to be conducted by the aircraft builder. Ill. 63 WARNING: Choose place of installation such, that operation is within the specified temperature limits. Date Install Page Reference Modification-No. 1996 05 10 914 F - 0 -...

  • Page 85: 9) Isolating Switch For Servo Motor

    WARNING: The TCU comprises electronic components and is therefore completely sealed. The TCU is allowed to be opened only by persons authorized by BOMBARDIER-ROTAX! connections: + terminal: flexible cable 0,75 mm white No. 1* - terminal: flexible cable 0,75 mm white No.

  • Page 86: 10)Warning Light

    No. 35* * from the 36 pole plug receptacle of the TCU, plug 6,3 x 0,8 to DIN 46247 length approx. 600 mm (24 in) from TCU Date Install Page Reference Modification-No. 1996 05 10 914 F - 0 -...

  • Page 87: 12) Externernal Alternator (Optional Extra)

    2000 3000 4000 5000 6000 7000 8000 n Alternator NOTE: The speed of the auxiliary generator is 1,24 times crankshaft speed Ill. 65 or 3 times the prop speed. Modification-No. Reference Install Date Page - 0 - 1996 05 10 914 F...

  • Page 88: 13)Connection Of The Electric Rev-Counter

    * from the 36 plug receptacle of TCU without plug connection length approx. 1000 mm (40 in) from TCU. NOTE: BOMBARDIER-ROTAX developed especially for this application a non-certified electric rev-counter. Certification to the latest require- ments such as FAR or JAR has to be conducted by the aircraft builder.

  • Page 89: 14) Battery

    ....... approx.0,25 A ..........~ 8 A internal power consumption, without servo motor and lamps standard value, actual value up to aircraft builder without electric starter and start relay Modification-No. Reference Install Date Page - 0 - 1996 05 10 914 F...

  • Page 90: Propeller Drive

    2,4286 (51 T/21 T) max. torque: 340 Nm (103 ft.lb.) at propeller max. moment of inertia : 6000 kgcm max. permitted out-of-balance on a prop: max. 0,5 gm Ill. 68 Date Install Page Reference Modification-No. 1996 05 10 914 F - 0 -...

  • Page 91: Vacuum Pump

    0,54 of engine speed. WARNING: Certification to the latest requirements such as FAR or JAR has to be conducted by the aircraft builder. Ill. 69 Modification-No. Reference Install Date Page - 0 - 1996 05 10 914 F...

  • Page 92: Hydraulic Governor For Constant Speed Propeller

    1,44 kg (3,2 lb) 2,7 kg (6 lb) (inclusive drive unit) NOTE: Reduction ratio of crankshaft to governor is 1,842 e.g. the governor speed is 0,54 of the engine speed. Date Install Page Reference Modification-No. 1996 05 10 914 F - 0 -...

  • Page 93: Connections For Instrumentation

    20° C (68° F) ± 10% tolerance: NOTE: BOMBARDIER-ROTAX recommends the temperature indication VDO instrument “VDO 310.274/082/017“ with an indicating range of 50° to 150° C (120° F - 300° F). Modification-No. Reference Install...

  • Page 94: Sensor For Oil Temperature

    20° C (68° F) ± 10% tolerance: BOMBARDIER-ROTAX offers a non-certified temperature indicating instrument. Refer to current spare parts list. WARNING: Certification to the latest requirements such as FAR of JAR has to be conducted by the aircraft builder.

  • Page 95: Oil Pressure Sensor

    20° C (68° F) voltage: 12 V ± 5% tolerance: BOMBARDIER-ROTAX offers a non-certified pressure gauge. Refer to current spare parts list. WARNING: Certification to the latest requirements such as FAR of JAR has to be conducted by the aircraft builder. Modification-No.

  • Page 96: Mechanical Rev-Counter Or Hour-Meter

    = 4 i.e. 1/4 of engine speed NOTE: A flexible shaft for the mechanical rev-counter is readily available from BOMBARDIER-ROTAX. Date Install Page Reference Modification-No. 1996 05 10 914 F - 0 -...

  • Page 97: Monitoring Of The Intake Manifold Pressure

    To take air temperature readings in the airbox a connection is provided. This connection is closed on the standard engine by a plug screw. connection: tapping 1/8-27 NPT thread length approx. 9 mm (3/8") Ill. 80 Modification-No. Reference Install Date Page - 0 - 1996 05 10 914 F...

  • Page 98: Preparations For Trial Run Of Engine

    Performance check in accordance with Operator's Manual. If nominal performance won't be reached or is in excess of, examination of the installation and engine will be necessary. Consult Maintenance Manual 914 F. ATTENTION: Don't conduct any test flights before fault has been traced and found.

  • Page 99: Authorized Distributors For Aircraft Engines

    FRANZ AIRCRAFT ENGINES VERTRIEB GMBH Contact person: Volker Roßbach Kampenwandstr. 4 D-83135 SCHECHEN, GERMANY Tel.: 08039 / 1431/ 5555, Fax: 08039 / 4616 Contact person: Eduard Franz Modification-No. Reference Install Date Page - 0 - 1996 05 10 914 F...
  • Page 100 ISRAEL: CONDOR-AVIATION INDUSTRIES LTD. 34 Arlozorov St. IL-52481 RAMAT - GAN Tel.: 03 / 6 724 884; Fax: 03 / 6 723 753 Contact person: David Viernik Date Install Page Reference Modification-No. 1996 05 10 914 F - 0 -...
  • Page 101 Contact person: Kit Chong UNITED ARAB. EMIRATES: AL MOALLA P.O. Box 7787 ABU DHABI Tel.: 2 / 723 248, Fax: 2 / 788 073 Contact person: Hussain Al Moalla Modification-No. Reference Install Date Page - 0 - 1996 05 10 914 F...
  • Page 102 Leerseite Date Install Reference Page Modification-No. 914 F 1996 05 10 - 0 -...

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