# STC SA65NW

- Type: Supplemental type certificate
- Status: Current, Amended
- Holder: Madras Air Service, United States
- Description: Installation of fiberglass wing tips.
- Applied: July 19, 1973
- Status date: April 26, 1981
- Product: Aircraft, Single-Engine
- Certification basis: Part 21
- Data sheets: [TCDS A4CE](https://openairdocs.org/tcds/A4CE)
- Certificate PDF: https://openairdocs.org/files/sha256/95/0b/950bffdc13283e34579e7ca9874dc354f381d248cb385ffca1ef7c3bb0b7fbf4
- FAA DRS: https://drs.faa.gov/browse/excelExternalWindow/CDBCFB33FF0E2D60862578F600755D24.0001
- DRS record last changed: December 5, 2025
- Page: https://openairdocs.org/stc/SA65NW

## ADs that name it (0)

None.

## Approved models (26)

- Cessna Aircraft Company 206 ([TCDS A4CE](https://openairdocs.org/tcds/A4CE))
- Cessna Aircraft Company P206 ([TCDS A4CE](https://openairdocs.org/tcds/A4CE))
- Cessna Aircraft Company P206A ([TCDS A4CE](https://openairdocs.org/tcds/A4CE))
- Cessna Aircraft Company P206B ([TCDS A4CE](https://openairdocs.org/tcds/A4CE))
- Cessna Aircraft Company P206C ([TCDS A4CE](https://openairdocs.org/tcds/A4CE))
- Cessna Aircraft Company P206D ([TCDS A4CE](https://openairdocs.org/tcds/A4CE))
- Cessna Aircraft Company P206E ([TCDS A4CE](https://openairdocs.org/tcds/A4CE))
- Cessna Aircraft Company TP206A ([TCDS A4CE](https://openairdocs.org/tcds/A4CE))
- Cessna Aircraft Company TP206B ([TCDS A4CE](https://openairdocs.org/tcds/A4CE))
- Cessna Aircraft Company TP206C ([TCDS A4CE](https://openairdocs.org/tcds/A4CE))
- Cessna Aircraft Company TP206D ([TCDS A4CE](https://openairdocs.org/tcds/A4CE))
- Cessna Aircraft Company TP206E ([TCDS A4CE](https://openairdocs.org/tcds/A4CE))
- Cessna Aircraft Company TU206A ([TCDS A4CE](https://openairdocs.org/tcds/A4CE))
- Cessna Aircraft Company TU206B ([TCDS A4CE](https://openairdocs.org/tcds/A4CE))
- Cessna Aircraft Company TU206C ([TCDS A4CE](https://openairdocs.org/tcds/A4CE))
- Cessna Aircraft Company TU206D ([TCDS A4CE](https://openairdocs.org/tcds/A4CE))
- Cessna Aircraft Company TU206E ([TCDS A4CE](https://openairdocs.org/tcds/A4CE))
- Cessna Aircraft Company TU206F ([TCDS A4CE](https://openairdocs.org/tcds/A4CE))
- Cessna Aircraft Company U206 ([TCDS A4CE](https://openairdocs.org/tcds/A4CE))
- Cessna Aircraft Company U206A ([TCDS A4CE](https://openairdocs.org/tcds/A4CE))
- Cessna Aircraft Company U206B ([TCDS A4CE](https://openairdocs.org/tcds/A4CE))
- Cessna Aircraft Company U206C ([TCDS A4CE](https://openairdocs.org/tcds/A4CE))
- Cessna Aircraft Company U206D ([TCDS A4CE](https://openairdocs.org/tcds/A4CE))
- Cessna Aircraft Company U206E ([TCDS A4CE](https://openairdocs.org/tcds/A4CE))
- Cessna Aircraft Company U206F ([TCDS A4CE](https://openairdocs.org/tcds/A4CE))
- Cessna Aircraft Company U206G ([TCDS A4CE](https://openairdocs.org/tcds/A4CE))

## 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.

tiniud ~tQru of S!mnicQ flrpartmrnt of 1Cransportation - lrdrral aniation adminiStration ~llpplcmcntal 1:~pc <tcrtificatc SA65NW ~~~~~ Madras Air Service ~./k- Ci vi 1 Ai r ~, effective May IS, 1956, as amended by 3-1 through 3-8.

~~_~~~ .. A4CE uItak· Cessna ~: 206, P206, P206A thru P206E, U206, U206A thru U206G, TP206A thru TP206E, TU206A thru TU206F.

Installation of fiberglass wing tips in accordance with Madras Air Service Drawing and Installation Instruction Number MAS-102-l and Drawing No. MAS-102, Sheet 2.

~~tf~' Approval of this change in type design applies to the above model aircraft only. This approval should not be extended to aircraft of this model on which other previously approved modifications are incorporated unless it is deter­ mined that the relationship 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. A copy of this Certificate and Addendum No. SA65NW shall be maintained as part of the permanent records for the m~~~~~~~~~./k-~fo~..MaII~.Mv#'d~~ ~~~~-O/~~~~~-7~~¥'~ ~~~ ~~-¥'~: July 19, 1973 September 20, 1973 ~~~April 26, 1981 !!l::ZLk~ ( Signature) Acting Chief, Seattle Area Aircraft Certification Office (Tit le )

fAA fOIM 8110-2 (10-68)

tln1tt4 ~ttJ of S!mtrica

f)tpartmtnt of 'nal1.Sportation-.froual 5lbiation 5ldministration ~upplcmcntal 1ICypc Q:crtificatc (iontinuation ~httt) April 26, 1981 J1/~ SA65NW SUPPLEMENTAL TYPE CERTIFICATE ADDENDill1 NO. SA65NW The conditions and limitations of Type Certificate Data Sheet Number A4CE apply except Where superseded by the following:

This Supplemental Type Certificate Data Sheet, which is part of STC SA65NW, prescribes the conditions and limitations under which the STC was issued meets the airworthiness requirements of the Civil Air Regulations.

SUPPLEMENTAL TYPE CERTIFICATE HOLDER: Madras Air Service I. MODELS 206, U206, AND P206 AS MODIFIED BY STC SA65NW Airspeed Limits:

Landplane: Never Exceed 206 mph 079 knots) Maximum Structural Cruising 167 mph 045 knots) Maximum Maneuvering 136 mph 018 knots) Floatplane: Never Exceed 206 mph 079 knots) Maximum Structural Cruising 167 mph 045 knots) Maximum Maneuvering 136 mph (118 knots) Skiplane: Not applicable II. MODELS U206A, U206B, P206A, AND P206B AS MODIFIED BY STC SA65NW Airspeed Limits:

Landplane: Never Exceed 206 mph 079 knots) Maximum Structural Cruising 167 mph 045 knots) Maximum Maneuvering 142 mph 023 knots) Floatplane: Never Exceed 206 mph 079 knots) Maximum Structural Cruising 167 mph 045 knots) Maximum Maneuvering 136 mph ( 118 knots) Skiplane: Never Exceed 206 mph 079 knots) Maximum Structural Cruising 167 mph 045 knots) Maximum Maneuvering 136 mph ( 118 knots) Any alteration oj this certificate is punishable by afine oj not exceeding 11,000, or imprisonment not exceeding 3 years, or both.

FAA FORM 811()'2-1 (t()'69) This certificate may be transferreri in Q&corriame with FAR 21.47.

**PAGE 3 OF 5 PAGES C FAA AC73-2651**

**III.**

IV.

April 26, 1981 STC ADDENDUM SA65NW MODELS TU206A, TU206B, TP206A, AND TP206B AS MODIFIED BY STC SA65m~ Airspeed Limits:

Landplane: Never Exceed: 206 mph 079 knots) Maximum Structural Cruise 167 mph 045 knots) Maximum Maneuvering 142 mph 023 knots) Floatplane: Never Exceed: 206 mph 079 knots) Maximum Structural Cruise 167 mph 045 knots) Maximum Maneuvering 136 mph ( 118 knots) Skiplane: Never Exceed 206 mph 079 knots) Maximum Structural Cruise 167 mph 045 knots) Maximum Maneuvering 136 mph ( 118 knots) MODELS P206C, P206D, P206E, TP206C, TP206D, AND TP206E AS MODIFIED BY STC SA65NW Airspeed Limits:

Landplane:

Floatplane:

Skiplane:

MODELS U206C THRU Airspeed Limits:

Landplane:

Floatplane:

Never Exceed 206 mph (179 knots) Maximum Structural Cruise 167 mph (145 knots) Maximum Maneuvering 142 mph (123 knots) Not applicable Never Exceed 206 mph 079 knots) Maximum Structural Cruise 167 mph 045 knots) Maximum Maneuvering 136 mph ( 118 knots) U206F, AND TU206C THRU TU206F AS MODIFIED BY STC SA65NW Never Exceed Maximum Structural Cruise Maximum Maneuvering Never Exceed Maximum Structural Cruise Maximum Maneuvering 206 mph (179 knots) 167 mph (145 knots) 142 mph (123 knots) for Serial Numbers U206-09l5 thru U206-l444 137 mph (119 knots) for Serial Numbers U2060l445 thru U2060l700 206 mph (179 knots) 167 mph (145 knots) 136 mph (118 knots) for Serial Numbers U206-0915 thru U206-1444 137 mph (119 knots) for Serial Numbers U2060l445 thru U2060l700 Page 4 of 5 Pages

tlnlttd .statts of S!maica lacpartmtnt of 1J:ransportation-,ftdcral ;Amation :administration ~upplcmcntGI 1[ypc (tcftifiCGtc April 26, 1981 V. (CONTINUED):

Skiplane:

(Q:ontinuation ~httt) J1I~ Never Exceed Maximum Structural Cruise Maximum Maneuvering STC ADDENDUM SA65NW 206 mph (179 knots) 167 mph (145 knots) 136 mph (118 knots) for Serial Numbers U206-0915 thru U206-1444 132 mph (114 knots) for Serial Numbers U20601445 thru U2060l700 VI. MODEL U206G AS MODIFIED BY STC SA65NW Airspeed Limits:

Landplane: Never Exceed 181 knots Maximum Structural Cruise 148 knots Maximum Maneuvering 118 knots Floatplane: Never Exceed 181 knots Maximum Structural Cruise 148 knots Maximum Maneuvering 118 knots NOTE 1 . In addition to the changes required above, the aircraft Weight and Balance Report must be revised as follows at the time of modification.

Weight of the wing tips is 9.5 pounds total; deduct the weight of the tip being removed and add the difference to the aircraft empty weight. The moment change is negligible.

NOTE 2. All of the maximum maneuvering speed placards called for by NOTE 2 of Type Certificate Data Sheet No. A4CE must be revised to show the maximum maneuverin l speeds specified in Sections I through VI above.

- END - Any alteration oj this certificate is punisha,ble by a fine oj not exceeding 11,000, or imprisonment not exceeding 3 years, or both.

FAA FORM 811()'2 - 1 (I ()'69) This certifoate may be transferred in accordance with FAR 21.17.

**PAGE 5 OF 5 PAGES C FAA AC73-2651**

## Every issue (1)

- April 26, 1981: Amended, Current. [certificate](https://openairdocs.org/files/sha256/95/0b/950bffdc13283e34579e7ca9874dc354f381d248cb385ffca1ef7c3bb0b7fbf4)

---
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.