24 Volt electric starter assy for ROTAX Aircraft Engines

24 Volt electric starter assy for ROTAX Aircraft Engines
24 Volt electric starter assy for ROTAX Aircraft Engines

SERVICE INSTRUCTION
The 24 Volt electric starter assy. and its connectors may be declared as part of the starting system on aircraft-side and so might not be a part of the Engine Type Design. Such a PAC part has been then tested and released by BRP-Rotax, but it might not be certified for the relevant engine type. In such a case the correct function in conjunction with the entire system is the responsibility of the aircraft manufacturer and must be carried out jointly with the aircraft.

Concurrent ASB/SB/SI and SL
In addition to this Service Instruction- PAC the following Service Instruction- PAC should be considered: SI-PAC-017, title “Starter relay assy. for ROTAX® Aircraft Engines“, current issue.

Subject
24 Volt electric starter assy. for ROTAX® Aircraft Engines.

Parts requirement for installation

for further material and procedures to install starter assy. on the engine and in the aircraft check with aircraft manufacturer´s instructions for continued airworthiness.

Operating limits
Refer to the latest issue of the Operators Manual (OM).

Ambient temperatures
System limit Min. Max.
Electric starter - 40 °C (- 40 °F) 80 °C (176 °F)

Thermal durability
Suitable for short starting periods only. Activate starter for max. 10 seconds (without interruption), followed by a cooling period of 2 minutes.

Aircraft ground
The engine block must be connected to the aircraft using a properly sized ground strap (minimum the same cable cross section as starter supply), to provide the required starter current and to avoid static electricity between the engine and the aircraft.

Negative terminal:
The engine block must be connected to the airframe using a properly sized ground strap (minimum the same cable cross section as the starter supply), for carrying the starter current and to avoid static electricity between the engine and the airframe.

Installation notes
The representation of components in this chapter which are not within scope of the delivery is only symbolic. The design shown in this chapter does not represent a specified execution but should support the understanding of the system.

The final design, the selection and specification of parts according to the respective applicable regulations, the consideration of the system limitations and interface description as well as the comprehension of the operating limits in every operational state is in the responsibility of the aircraft manufacturer. The aircraft manufacturer has to make sure that the operating limits given in the Operators Manual (OM) can be supervised by the pilot. The execution of the installation must allow the operation of the engine according to the Operators Manual (OM).

Installation overview

Wiring
The engine block must be connected to the airframe using a properly sized ground strap for carrying the starter current and to avoid static electricity between the engine and the airframe. The minimum cable cross-section for the line from the battery to the starter relay and from there to the electric starter and for the ground line (start system) depends on the cable length “I“(= Sum of the supply line and ground line of the electric starter) and has to be calculated according to the following table.

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