# STC SA936NW - Type: Supplemental type certificate - Status: Current, Reissued - Holder: Milo DeAngelis, Canada - Description: Lycoming O-360-A1A, McCauley1A200-FA8248 propeller spinner, engine mount, exhaust system, modified landing gear or Edo248-2440 floats, modified cowl. - Applied: April 29, 1980 - Status date: February 6, 2006 - Product: Aircraft, Single-Engine - Certification basis: Part 3, Part 21 - Data sheets: [TCDS 1A6](https://openairdocs.org/tcds/1A6) - Certificate PDF: https://openairdocs.org/files/sha256/30/4f/304f94dd63b0e082380e88f4f8af0b612075e1f853efc2a5e8272b0eda8bcec0 - FAA DRS: https://drs.faa.gov/browse/excelExternalWindow/FF364D66555E6DAC8625711700502F41.0001 - DRS record last changed: December 6, 2025 - Page: https://openairdocs.org/stc/SA936NW ## ADs that name it (0) None. ## Approved models (3) - The New Piper Aircraft Inc. PA-22-150 ([TCDS 1A6](https://openairdocs.org/tcds/1A6)) - The New Piper Aircraft Inc. PA-22-160 ([TCDS 1A6](https://openairdocs.org/tcds/1A6)) - The New Piper Aircraft Inc. PA-22S-160 ([TCDS 1A6](https://openairdocs.org/tcds/1A6)) ## 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 (This STC is a duplicate original to replace the original which was lost. Issued 2/06/06) Number SA936NW This certificate, issued to Milo DeAngelis 6665 Old Kamloops Rd Vernon, B.C. V1H 1P8 Part 3 of the Civil Air Regulations, effective November 1, 1949. Original Product⎯Type Certificate Number: 1A6 Make: Piper Model: PA-22-150, -160, and PA-22S-160 Description of the Type Design Change: Installation of a Lycoming 0-360-A1A, engine, McCaul 1A200-FA82XX propeller, spinner, engine mount, exhaust, modified landing gear or Edo 248-2440 or PK 2300 floats, modified cowling, and associated systems in accordance with Simpson Aviation Company Drawings Number SAC-5000, Sheets 1 and 2, SAC-5100, SAC-6100, and SAC-6200. Limitations and Conditions: Approval of this change in type design applies basically to the above model aircraft only. This approval is limited to the installation in the above models modified with extended wings and fuselage in accordance with STC SA819SW and should not be extended to other aircraft of this model on which other previously approved modifications are incorporated unless it is determined that the interrelationship 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 aircraft. See “Continuation Sheet” Page 2 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. Date of application: April 29, 1980 Date reissued: July 30, 1980, February 6, 2006 Date of issuance: May 16, 1980 Date amended: July 30, 1980, August 22, 1980 (Signature) Acting Manager, Seattle Aircraft Certification Office (Title) Number SA936NW Reissued: July 30, 1980, February 6, 2006 Amended: July 30, 1980, August 22, 1980 Limitations and Conditions: (cont’d) A copy of this Certificate and Addendum No. SA936NW shall be maintained as part of the permanent records for the modified aircraft. **SUPPLEMENTAL TYPE CERTIFICATE ADDENDUM NO. SA936NW** The conditions and limitations of Type Certificate Data Sheet No. 1A6 apply except where superseded by the following: This Supplemental Type Certificate Data Sheet, which is part of the STC SA936NW, 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: Milo DeAngelis **I. PIPER PA-22-150, -160, AND 22S-160 (NORMAL CATEGORY) AS MODIFIED BY STC SA936NW** Engine: Lycoming 0-360-A1A Fuel: 91/96 minimum grade aviation gasoline Engine Limits: For all operations 2700 rpm (180 Hp) Propeller and Propeller Limits: McCauley 1A200-FA8248 (landplane); 1A200-FA8243 (seaplane) Diameter: 82” maximum; 78” minimum Static Limits: 2275 rpm maximum; 2175 rpm minimum Powerplant Instrument Markings: Tachometer: 2700 rpm (red line) maximum Oil Temperature Gauge: 245ºF (red line) maximum Oil Pressure Gauge: 25 psi (red line) minimum 100 psi (red line) maximum 60 to 90 psi (green arc) normal operating range Fuel Pressure Gauge: .5 psi (red line) minimum 8.0 psi (red line) maximum 3 to 5 psi (green arc) normal operating range - END – - **FAA FORM 8110-2- 1 (10-69)** ## Every issue (1) - February 6, 2006: Reissued, Current. [certificate](https://openairdocs.org/files/sha256/30/4f/304f94dd63b0e082380e88f4f8af0b612075e1f853efc2a5e8272b0eda8bcec0) --- 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.