Shock Mount Set for ROTAX® Aircraft Engines ATA System: 71-20-00 Engine suspension frame
What’s this about?
This document advises of the availability of a shock mount set (P/N 860695) and provides some installation-related information.
How does this affect me?
If your aircraft is equipped with a 912/914/912i/915i (series) ROTAX® aircraft engine, you may be interested in obtaining one of these shock mount sets. This document contains essential information about the P/N 860695 shock mount set.
What do I do about it?
Download and review this Service Instruction. If your aircraft has (or you plan to use) any of the listed parts or accessories covered by this SI-PAC, you and/or your aircraft maintenance provider should carefully review the document before installation or maintenance.
1) Planning information “PAC” Service Instruction Documents provide detailed information on non-certified ROTAX® Aircraft Engine Parts and Accessories. Referenced parts and accessories are provided without EASA certification or ASTM compliance. Certification / Compliance of referenced Parts and Accessories must be completed by the aircraft OEM. To obtain satisfactory results, procedures specified in this publication must be accomplished with accepted methods in accordance with prevailing legal regulations. BRP-Rotax GmbH & Co KG cannot accept any responsibility for the quality of work performed in accomplishing the requirements of this publication.
1.1) Applicability Refer to the latest issue of the relevant Illustrated Parts Catalog.
1.2) Concurrent ASB/SB/SI and SL None.
1.3) Reason In the course of continued development and our commitment to product improvement, a shock mount set has been introduced.
1.4) Subject Shock mount set for ROTAX® Aircraft Engines.
1.5) Compliance NONE – For Information Only.
1.6) Approval None.
1.7) Labor time and credit Estimated labor hours: Engine installed in the aircraft – – – labor time will depend on airframe installation and therefore no estimate is available from the engine manufacturer.
1.8) Mass data Change of weight – – – none. Moment of inertia – – – unaffected.1.9) Electrical load data No change.
1.9) Electrical load data No change.
