# STC SA01439WI - Type: Supplemental type certificate - Status: Current, Amended - Holder: MT- Propeller Entwicklung GmbH - Description: Installation of MT-Propeller Model MTV-16-1-E-C-F-R(P)/CFR250-55 reversing and full feathering 4-blade constant speed propeller. - Status date: July 20, 2007 - Data sheets: A37CE, A37CE, A37CE - Certificate PDF: https://openairdocs.org/files/sha256/97/a6/97a6d9c8f745a8c08620617211bf3e1c930f1fe0f7768900f48f85e4e99d75ba - FAA DRS: https://drs.faa.gov/browse/excelExternalWindow/A2D0483614CEA5A88625733F004B0BAD.0001 - Page: https://openairdocs.org/stc/SA01439WI ## ADs that name it None. ## Approved models (3) - Cessna Aircraft Company 208 (TCDS A37CE) - Cessna Aircraft Company 208A (TCDS A37CE) - Cessna Aircraft Company 208B (TCDS A37CE) ## What the certificate says Read from the PDF's text layer, without the form's printed wording; the layout is lost and the order can differ. The PDF is the record. United States of America Department of Transportation -- Federal Aviation Administration Supplemental Type Certificate IMPORT FAA FORM 8110-2(10-69) Sheet 1 of 2 Number SA01439WI This certificate issued to: Part 23 of the Federal Aviation Regulations. Luftfahrt- Bundesamt (LBA) originally certificated this modification under German LBA EMZ (STC) No. EASA.A.S.01128. The FAA validated this modification under U.S. Supplemental Type Certificate No. SA01439WI. Effective September 28, 2003, the European Aviation Safety Agency (EASA) began oversight of this modification on behalf of Luftfahrt-Bundesamt. Original Product Type Certificate Number: A37CE Make: Cessna Model: 208, 208A, 208B Installation of MT-Propeller Model MTV-16-1-E-C-F-R(P)/CFR250-55 reversing and full feathering 4-blade constant speed propeller in accordance with MT-Propeller Installation Instructions Document No. E-1500, Revision (1), dated May 23, 2007, or later FAA approved revisions. Instructions for Continued Airworthiness Document No. E-1216, Revision (2), dated 23 May 2007, or later FAA approved revisions. FAA Approved Airplane Flight Manual Supplement E-1215 dated June 14, 2007, or later FAA approved revision. 1. Compatibility of this design change with previously approved modifications must be determined by the installer. 2. This STC is not to be transferred since its issuance was in accordance with 14 CFR§21.29 and based upon a validation of the German LBA EMZ No. EASA.A.S.01128. This certificate and the supporting data, which is the basis for approval, shall remain in effect until surrendered, suspended, revoked or a termination date is otherwise established by the Administrator of the Federal Aviation Administration. MT-Propeller Entwicklung GmbH Flugplatzstr. 1 94348 Atting Germany Date reissued: Date amended: July 20, 2007 Original signed by Grant E. Youngdahl ( Signature) Grant Youngdahl FAA Program Manager Wichita Aircraft Certification Office ( Title) Date of application: August 22, 2005 Date of issuance: June 14, 2007 FAA FORM 8110-2(10-69) Sheet 2 of 2 Number SA01439WI Date of issuance: June 14, 2007 DateAmended: July 20, 2007 Limitations and Conditions (continued): 3. If the holder agrees to permit another person to use this certificate to alter that product, the holder shall give the other person written evidence of that permission. 4. The Limitations and Conditions are as defined on this certificate. 5. A copy of the approved data shall be maintained in the airplane permanent records. 6. A copy of this certificate must be maintained as part of the permanent records for the aircraft. Certification Basis: Based on 14 CFR §§ 21.101 and 21.115, and the FAA policy for significant changes in FAA Order 8110.48, the certification basis for the MT-Propeller model MTV-16-1-E-C-F-R(P)/CFR250-55 reversing and full feathering 4-blade constant speed propeller as installed on the Cessna 208, 208A, 208B is as follows: a. The type certification basis for Cessna 208 Series airplanes is shown on TCDS A37CE for parts not changed or not affected by the change. b. The certification basis for parts changed or affected by the change since the reference date of application, August 22, 2005, is based upon Part 23 as amended by Amendment 23-45. Based on 14 CFR §§ 21.101 and 21.115, and the FAA policy for significant changes in FAA Order 8110.48, the certification basis for this modification was determined to be: Regulations at amendment 23-45 23.1, 23.21, 23.29, 23.33, 23.45, 23.51, 23.65, 23.75, 23.77, 23.201, 23.251, 23.629, 23.867, 23.901, 23.905, 23.907, 23.925, 23.929, 23.933, 23.1041, 23.1043, 23.1045, 23.1155, 23.1305, 23.1309, 23.1419, 23.1501, 23.1521, 23.1529, 23.1541, 23.1549, 23.1559, 23.1581, 23.1583, 23.1587 …END… ## Every issue (1) - July 20, 2007: Amended, Current. [certificate](https://openairdocs.org/files/sha256/97/a6/97a6d9c8f745a8c08620617211bf3e1c930f1fe0f7768900f48f85e4e99d75ba) --- From OpenAirDocs.org, an independent open copy of FAA data. Only the Federal Register edition on govinfo.gov is the official legal text of an AD.