# STC SA2309NY

- Type: Supplemental type certificate
- Status: Current, Issued
- Holder: Standard Aero Inc, United States
- Description: Install Pratt & Whitney, Canada (P&WC) PT6A-135A engines (modified with a dual line start fuel system ) in place of PT6A-135 engine.
- Applied: September 8, 2006
- Status date: November 1, 2006
- Product: Aircraft, Single-Engine
- Certification basis: Part 3, Part 21
- Data sheets: [TCDS A8EA](https://openairdocs.org/tcds/A8EA)
- Certificate PDF: https://openairdocs.org/files/sha256/1d/0b/1d0bdba703d14c2cb74084d7cf2647b12bf6d29dd3f7971ad46ee2b56b020cdb
- FAA DRS: https://drs.faa.gov/browse/excelExternalWindow/C8454BF3A2FCE13B862572480078B3F9.0001
- DRS record last changed: December 6, 2025
- Page: https://openairdocs.org/stc/SA2309NY

## ADs that name it (0)

None.

## Approved models (1)

- Piper Aircraft Inc. PA-31T2 ([TCDS A8EA](https://openairdocs.org/tcds/A8EA))

## 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.

This certificate issued to Standard Aero Inc.

600 Hayden Circle Allentown, PA 18109

Part 3 of the Civil Air Regulations.

Original Product -- Type Certificate Number: A8EA

Make: Piper Aircraft, Inc.

Model: PA31T2, Cheyenne IIXL Description of Type Design Change:

Install Pratt & Whitney, Canada (P&WC) PT6A-135A engines (modified with a dual line start fuel system ) in place of PT6A-135 engine in accordance with Standard Aero Inc. Installation Instructions Report No. 55036-27 Rev. A, dated October 18, 2006.

1. You can not use descriptive data about this design change to duplicate other products. This approval is limited to only the installation made in Piper Aircraft, Inc., PA31T2l, Cheyenne IIXL, Serial Number 31T-116608. This STC does not permit manufacturing of parts for multiple installations.

2. Pratt & Whitney Canada PT6A-135 engines were modified and approved via 8110-3 to model PT6A-135A and returned to service via Form 337.

3. Reference Flight Manual Supplement 55036-25, Revision A.

4. The listed temperature for the PT6A-135A engine is 93 °F for maximum continuous and takeoff power compared to 85 °F for the PT6-135 engine. The engine ratings are based on static sea level condition 29.92 in. Hg pressure, compressor intake screen installed, no external accessory loads and no airbleed. These ratings are available up to the following compressor inlet air (dry) temperatures.

5. Reference P&WC Engine Maintenance Manual (Part no. 3043512) for instructions concerning lubrication of “wet spline” drive for the starter generator that is a feature of the PT6A-135A engine.

Date of application: September 8, 2006

Date of issuance: November 01, 2006 Date reissued:

( Signature) Anthony Socias Manager New York Aircraft Certification Office

(Title)

## Every issue (1)

- November 1, 2006: Issued, Current. [certificate](https://openairdocs.org/files/sha256/1d/0b/1d0bdba703d14c2cb74084d7cf2647b12bf6d29dd3f7971ad46ee2b56b020cdb)

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