# STC SA1155CE - Type: Supplemental type certificate - Status: Current, Reissued - Holder: Staggerwing Museum Foundation Inc., United States - Description: Install crack detection system. - Applied: August 12, 1975 - Status date: September 3, 2004 - Product: Aircraft, Single-Engine - Certification basis: Part 21 - Data sheets: [TCDS 770](https://openairdocs.org/tcds/770) - Certificate PDF: https://openairdocs.org/files/sha256/12/6e/126ee6ae50fd9a8dcb184b0e151a89ba7a09403e3e3679650a1a48333201d548 - FAA DRS: https://drs.faa.gov/browse/excelExternalWindow/B756B903DE8BB9E2862570BA0052E985.0001 - DRS record last changed: December 6, 2025 - Page: https://openairdocs.org/stc/SA1155CE ## ADs that name it (1) - [AD 75-27-09 R2](https://openairdocs.org/ad/75-27-09-R2): Wing Structure · Textron 18A, 18D, 18S (Army C-45C) and 27 more. Effective Aug 21, 1980. Cited in the text ## Approved models (1) - Beech Aircraft Corporation D18C-T ([TCDS 770](https://openairdocs.org/tcds/770)) ## 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 Staggerwing Museum Foundation, Inc. 560 Old Shelbyville Highway Tullahoma, TN 37388 Part 4a-T of the Civil Air Regulations. 770 BEECH D18C-T Description of Type Design Change: Install crack detection system in accordance with Hamilton Aircraft Company Drawing No. 454-000 and data referenced thereby. FAA Approved Airplane Flight Manual Supplement dated December 23, 1975, and FAA Approved Maintenance Instructions dated December 23, 1975, are required. Limitations and Conditions: This approval should not be extended to other specific airplanes 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 will introduce no adverse effect upon the airworthiness of that airplane. Parts manufactured under this STC may have been produced without an FAA approved quality control procedure. Prior to installation, such parts must be inspected for conformity and airworthiness in accordance with FAR’s 21 and 43. 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 : August 12, 1975 Date of issuance : December 23, 1975 Date reissued: September 3, 2004 ( Signature) Manager, Technical & Administrative Support Staff, Los Angeles Aircraft Certification Office ( Title) ## Every issue (1) - September 3, 2004: Reissued, Current. [certificate](https://openairdocs.org/files/sha256/12/6e/126ee6ae50fd9a8dcb184b0e151a89ba7a09403e3e3679650a1a48333201d548) --- 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.