# STC SE1657NM - Type: Supplemental type certificate - Status: Current, Amended - Holder: Machen Inc, United States - Description: Installation of Rotomaster3AU2ME60H3 (or H2) and3AV2ME60H3 (or H2), turbo- chargers, optional intercooler and associated systems. - Applied: January 26, 1982 - Status date: November 1, 1998 - Product: Engine - Certification basis: Part 21 - Data sheets: [TCDS 1E4](https://openairdocs.org/tcds/1E4) - Certificate PDF: https://openairdocs.org/files/sha256/df/76/df76a18eb25c37ea5245e660d8c948f22131fa58087d0aafad4d36c0b10be7d1 - FAA DRS: https://drs.faa.gov/browse/excelExternalWindow/AEB5A4440D6DFD8985256CC2005A746B.0001 - DRS record last changed: December 6, 2025 - Page: https://openairdocs.org/stc/SE1657NM ## ADs that name it (1) - [AD 2002-19-03](https://openairdocs.org/ad/2002-19-03): Crankshaft ยท Lycoming Engines IO-540-A1A5, IO-540-AA1A5, IO-540-AA1B5 and 81 more. Effective Sep 20, 2002. Named in the applicability ## Approved models (2) - Lycoming Engines IO-540-AA1A5 ([TCDS 1E4](https://openairdocs.org/tcds/1E4)) - Lycoming Engines IO-540-S1A5 ([TCDS 1E4](https://openairdocs.org/tcds/1E4)) ## What the certificate says This is OCR from the scanned FAA certificate. OCR can misread letters and numbers. United States of America Department of Transportation Federal Aviation Administration Supplemental Type Certificate Number: SE1657NM This certificate issued to: Machen, Inc. 10555 Airport Drive Coeur d'Alene Airport Hayden Lake, ID 83835 Certifies that the change in the type design for the following product with the limitations and conditions therefor as specified hereon meet's the airworthiness requirement's of Part 13 of the Civil Air Regulations. Original Product -Type Certificate Number: 1E4 Make: AVCO Lycoming Model: IO-540-S1A5 and IO-540-AA1A5 Description of Type Design Change: Installation of Rotomaster 3AU2ME60H3 (or H2), and 3AV2ME60H3 (or H2), turbochargers, optional intercooler and associated systems in accordance with Machen, Inc. Report No. 65-2, dated June 12, 1982 or later FAA approved revisions. Limitations and Conditions: . Approval of this change in type design applies to the above model engines only, and is limited to the Piper Aerostar 600, 601, 601P and 602P aircraft modified per STC SA1658NM. This approval should not be extended to other engines of this model on which other previously approved modifications are incorporated unless it is determined that the relationship between this change and any of those other previously approved modifications, including changes in type design, will introduce no adverse effect upon the airworthiness of that engine. A copy of this Certificate must be maintained as part of the permanent records for the modified engine. If the holder agrees to permit another person to use this certificate to alter the product, the holder shall give the other person written evidence of that permission. (See "Continuation Sheet" Page 3) Date of Application: January 26, 1982 Date Reissued: Date of Issuance: August 11, 1982 Date Amended: April 24, 1985, March 18, 1988, November 1, 1998 EDERAL AVIATION direc (Signature) ISTRATION Acting Manager, Seattle Aircraft Certification Office (Title) United States of America Department of Transportation Federal Aviation Administration Supplemental Type Certificate (Continuation Sheet) Number: SE1657NM Machen, Inc. Reissued: Amended: November 1, 1998 Limitations and Conditions: continued: Supplemental Type Certificate (STC) ADDENDUM NO. SE1657NM The conditions and limitations of Type Certificate Data Sheet (TCDS) 1E4 apply except where superseded by the following: Supplemental Type Certificate Data Sheet, which is part of STC SE1657NM prescribes the conditions and limitations under which the product for which the STC was issued meets the airworthiness requirements of the Civil Air Regulations. Supplemental Type Certificate HOLDER: Machen, Inc. AVCO Lycoming IO-540-S1A5-MM or IO-540-AA1A5-MM as modified by STC SE1657NM Non-Intercooled Installation Full power manifold pressure and rpm shall be set within the following limits for 325 hp maximum power continuous operation: Max MAP = 41" Hg Max RPM = 2500 Decrease MAP 1/2" Hg per 1,000 feet altitude above 15,000 feet altitude operation. Intercooled Installation Full power manifold pressure and rpm shall be set within the following limits for 340 hp maximum power continuous operation: Max MAP = 41" hg Max RPM = 2500 Full power manifold pressure and rpm shall be set within the following limits for 350 hp maximum power continuous operation: Max MAP = 42" Hg Max RPM = 2500 - END - **FAA FORM 8110-2-1 (10-69) PAGE 3 OF 3 PAGES** ## Every issue (1) - November 1, 1998: Amended, Current. [certificate](https://openairdocs.org/files/sha256/df/76/df76a18eb25c37ea5245e660d8c948f22131fa58087d0aafad4d36c0b10be7d1) --- OpenAirDocs.org is an independent research project of [Contrail Labs](https://contraillabs.com/). It is not affiliated with the FAA or the NTSB. Source documents are U.S. government works in the public domain.