# STC SA03549NY

- Type: Supplemental type certificate
- Status: Current, Reissued
- Holder: Kuerzi Avionics Deutschland GmbH, Germany
- Description: Installation of Garmin G950 with LNAV/VNAV and LPV capability
- Applied: May 4, 2011
- Status date: September 1, 2015
- Product: Aircraft, Small Airplane
- Certification basis: Part 21, Part 23
- Data sheets: [TCDS 7A15](https://openairdocs.org/tcds/7A15)
- Certificate PDF: https://openairdocs.org/files/sha256/b3/6e/b36e64ab51efd27feec6f7a05ac2db91fe983f6fc77dadaab6f21fb577731874
- FAA DRS: https://drs.faa.gov/browse/excelExternalWindow/5A3195AFCB14F02186257EC10068D716.0001
- DRS record last changed: December 6, 2025
- Page: https://openairdocs.org/stc/SA03549NY

## ADs that name it (0)

None.

## Approved models (2)

- Pilatus Aircraft Limited PC-6/B-H2 ([TCDS 7A15](https://openairdocs.org/tcds/7A15))
- Pilatus Aircraft Limited PC-6/B2-H4 ([TCDS 7A15](https://openairdocs.org/tcds/7A15))

## 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.

FAA Form 8110-2 (5/14) Page 1 of

Part of the

Signature

Title SA03549NY Kuerzi Avionics Deutschland GmbH Moltkestrasse 4 78464 Konstanz Germany Federal Aviation Regulations.

1. Installation of Garmin G950 with LNAV/VNAV and LPV capability in accordance with Kuerzi Avionics Master Document List, MDL-200830764, revision I, dated June 19, 2015, or later EASA approved revisions.

2. Aircraft is to be maintained in accordance with Kuerzi Avionics Instructions for Continued Airworthiness, ICA-200830764, revision F, dated November 20, 2014, or later EASA accepted revisions.

1. The installer must determine whether this design change is compatible with previously approved modifications.

2. If the holder agrees to permit another person to use the certificate to alter the product, the holder must give the other person written evidence of that permission.

3. Required pre-modifications:

- Pilatus PC-6 pitch trim warning system according SB-180

(See Limitations and Conditions continued on page 3 of 3) Gaetano Sciortino Manager New York Aircraft Certification Office Pilatus Aircraft Ltd.

PC-6/B2-H2, PC-6/B2-H4 September 1, 2015 May 4, 2011 July 17, 2015 IMPORT 7A15 3

FAA Form 8110-2 (5/14) Page 2 of

To (Name and address of transferee)

From (Name and address of grantor)

3 SA03549NY

FAA Form 8110-2 (5/14) Page 3 of

3 Date Reissued: September 1, 2015

- Electrical stall warning system, type Safe Flight 1-02-0005 No. 164 (Transmitter) and C-73113(Buzzer)

- Electrical power distribution system (MCA 06/24/130)

- Electrical flap control according SB-95 (plus-difference)

- Two motor trim actuator system

- Rudder trim (electrical)

- Aileron trim system (electrical) for PC-6/B2-H4, (optional for PC-6/B2-H2)

Certification Basis:

Based on 14 CFR § 21.115 and § 21.101, and the FAA Order 8110.48, the certification basis for the Pilatus PC-6/B2- H2 and PC-6/B2-H4 is as follows:

a. For areas not affected by the change, the type certification basis for the Pilatus PC-6/B2-H2 and PC-6/B2-H4 is shown on TCDS 7A15.

b. For areas affected by the change, the type certification basis for the Pilatus PC-6/B2-H2 and PC-6/B2-H4 is 14CFR Part 23, Amendments 23-1 through 23-55 except the regulations listed below:

Section Title Amendment §23.1306 Indirect Effects of Lightning 23-61 §23.1308 Protection from Effects of HIRF 23-57 ----------END---------- SA03549NY

## Every issue (2)

- September 1, 2015: Reissued, Current. [certificate](https://openairdocs.org/files/sha256/b3/6e/b36e64ab51efd27feec6f7a05ac2db91fe983f6fc77dadaab6f21fb577731874)
- July 17, 2015: Issued, Historical. [certificate](https://openairdocs.org/files/sha256/40/c7/40c71e0b7be948a9cf769bd124de4323ffe8a1b8c8f688a5aedc1ad981befeaf)

---
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.