ROTAX Aircraft Engines SB-912 i-013_915 i A-012 Replacement of electrical fuel pump

ROTAX Aircraft Engines SB-912 i-013_915 i A-012 Replacement of electrical fuel pump
ROTAX Aircraft Engines Replacement of electrical fuel pump

Replacement of electrical fuel pump(s) for ROTAX® Aircraft Engines
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.

Applicability
NOTE: Make sure to check the whole set of criteria mentioned in this section. The following single fuel pumps (with S/N listed below) may be installed in all versions of ROTAX® engine types 912 i and 915 i A Series and/or accessory/spare parts/fuel pump modules.
Fuel pump serial number:

Fuel pump Description Serial number
Part no. 889694* Fuel pump from S/N 180500 up to S/N 203724 inclusive

Concurrent ASB/SB/SI and SL
In addition to this Service Bulletin the following documents must be observed and complied with:

  • in general all relevant Alert Service Bulletins (ASB), Service Bulletins (SB), Service Instructions (SI), Service Letters (SL), Service Instruction Parts and Accessories (SI-PAC) with relevance to perform this maintenance, repair or overhaul task.
  • Alert Service Bulletin ASB-915 i-008/ASB-912 i-011, title “Replacement of fuel pump assy.”, current issue.
  • Alert Service Bulletin ASB-912 i-010/ASB-915 i-006, title “Inspection and/or replacement of fuel pump assy.”, current issue.
  • Service Instruction SI-912 i-019/SI-915 i-005, title “Introduction of revised fuel pump assy.“, current issue.
  • Service Instruction SI-912 i-025, title ”Fuel pump assembly”, current issue.
  • Service Instruction Parts and Accessories SI-PAC-016, title ”Fuel pump assembly”, current issue.

Reason
Due to deviations in the manufacturing process of the electric fuel pump, a malfunction of fuel supply may occur. Possible effect in flight might be a loss of the redundancy within the fuel pump system. On ground the failure might be detected during the run-up check.

References
In addition to this technical information refer to current issue of

  • in general Illustrated Parts Catalog (IPC) and in particular: Chapter 73-10-00
  • in general Operators Manual (OM)
  • in general Installation Manual (IM)
  • in general Maintenance Manual Line (MML)
  • in general Maintenance Manual Heavy (MMH) and in particular: Chapter 73-10-00