# STC SA1-607

- Type: Supplemental type certificate
- Status: Current, Reissued
- Holder: BF Goodrich Aerospace, United States
- Description: Electrothermal propeller deicing system.
- Applied: July 6, 1961
- Status date: March 1, 1996
- Product: Aircraft, Small Multi-Engine
- Data sheets: [TCDS 6A1](https://openairdocs.org/tcds/6A1)
- Certificate PDF: https://openairdocs.org/files/sha256/6b/ee/6bee1bbf179ce8f6da98827cc956f0d5155ad8409b741414434a49a93c9f6274
- FAA DRS: https://drs.faa.gov/browse/excelExternalWindow/DRSDOCID147692149520230519171415.0001
- DRS record last changed: December 6, 2025
- Page: https://openairdocs.org/stc/SA1-607

## ADs that name it (1)

- [AD 2005-18-20](https://openairdocs.org/ad/2005-18-20): "FASTprop" propeller de-icers · Hartzell PHC-C3YF-1RF/F8468A(B,K)-8R constant speed propeller (STC SA00718LA or 17 others). Effective Oct 14, 2005. Named in the applicability

## Approved models (1)

- Twin Commander Aircraft Corporation 500-A ([TCDS 6A1](https://openairdocs.org/tcds/6A1))

## 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: SA1-607 This certificate issued to: BFGoodrich De-Icing Systems 1555 Corporate Woods Pkwy.

Uniontown, OH 44685 Part 3 of the CiVi I Air Regulalions: (See Type Certificate Data Sheet 6A1 for complete Original Product -Type Cerificate Number 6A1 certification basis).

Make Twin Commander Model: 500-A Description of Type Design Change:

Install Electrothermal Propeller De-Icing System in accordance with Installation Manuals (BFG Reports) 61-703, dated 3/15/61 and 59-728, dated 12/31/59.

Limitations and Conditions: Airplane Flight Manual Supplement No. 1 (BFG Report 61-719) dated 5/1/61, is required on board for operation.

2. This installation is applicable only to aircraft which have generator capacity sufficient to allow the addition of 12 amps for continuous prop de-icing. This is to be determined by electrical load analysis in accordance with CAM 18, Section 18, 30-12(1).

Compatibility of this design change with previously approved i fitzone desting ete mined be the install remain in effed until surrendered, suspended, revoked, or a termination date is sherwise established by the Administrater of the Federal Aviation Administration .

Date of Application: JUly 6, 1961 Jule wissued: March 1, 1996 Date of Issuance: August 23, 1961 Date Amended:

EDERAL AVIATIO By Direction of the Administrator Charles L. Smalley, Mattager<) Systems & Flight Test Branch Chicago Aircraft Certification Office (Title) 47 FAA FORM 8110-2 (10-68)

## Every issue (1)

- March 1, 1996: Reissued, Current. [certificate](https://openairdocs.org/files/sha256/6b/ee/6bee1bbf179ce8f6da98827cc956f0d5155ad8409b741414434a49a93c9f6274)

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