# STC SA64NW - 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: September 18, 1986 - Product: Aircraft, Single-Engine - Certification basis: Part 21 - Data sheets: [TCDS 3A21](https://openairdocs.org/tcds/3A21) - Certificate PDF: https://openairdocs.org/files/sha256/e2/f9/e2f9f908a8cea3cf84b585f8f161935073c6e94af98b280cd7e51a4db00382ea - FAA DRS: https://drs.faa.gov/browse/excelExternalWindow/CDADC954C0914841862578F600746549.0001 - DRS record last changed: December 6, 2025 - Page: https://openairdocs.org/stc/SA64NW ## ADs that name it (0) None. ## Approved models (15) - Cessna Aircraft Company 210 ([TCDS 3A21](https://openairdocs.org/tcds/3A21)) - Cessna Aircraft Company 210-5 (205) ([TCDS 3A21](https://openairdocs.org/tcds/3A21)) - Cessna Aircraft Company 210-5A (205A) ([TCDS 3A21](https://openairdocs.org/tcds/3A21)) - Cessna Aircraft Company 210A ([TCDS 3A21](https://openairdocs.org/tcds/3A21)) - Cessna Aircraft Company 210B ([TCDS 3A21](https://openairdocs.org/tcds/3A21)) - Cessna Aircraft Company 210C ([TCDS 3A21](https://openairdocs.org/tcds/3A21)) - Cessna Aircraft Company 210D ([TCDS 3A21](https://openairdocs.org/tcds/3A21)) - Cessna Aircraft Company 210E ([TCDS 3A21](https://openairdocs.org/tcds/3A21)) - Cessna Aircraft Company 210F ([TCDS 3A21](https://openairdocs.org/tcds/3A21)) - Cessna Aircraft Company 210G ([TCDS 3A21](https://openairdocs.org/tcds/3A21)) - Cessna Aircraft Company 210H ([TCDS 3A21](https://openairdocs.org/tcds/3A21)) - Cessna Aircraft Company 210J ([TCDS 3A21](https://openairdocs.org/tcds/3A21)) - Cessna Aircraft Company 210K ([TCDS 3A21](https://openairdocs.org/tcds/3A21)) - Cessna Aircraft Company 210L ([TCDS 3A21](https://openairdocs.org/tcds/3A21)) - Cessna Aircraft Company T210F ([TCDS 3A21](https://openairdocs.org/tcds/3A21)) ## 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. tiJId £Uo II S!mD BqJartmmt of ~n.sportation - .ftdttal g\liation ggmjstr9tion ~upplrmrntal 1Cypr Madras Air Service ~~d~~g~~r~fo1k~~·u'iddk~~~ ~~~~nnedv./k~~~¥,9~ 3 ~~ Civil Air ~ (See Type Certificate Data Sheet No. 3A21) ~~~~Jt;nz/-. . · vIIak : Jtx.u : 3A21 Cessna 210 through 210F, T210F, (205)210 - 5, (205A) 210 - 5A, 210G, 21 0B , 210J, 210K & 210L. Installation of fiberglass wing tips in accordance with FAA Sealed Madras Air Service Drawing No. MAS- 102-1 dated July 3, 1973 and Drawing No . MAS- 102, Sheet 2, Revision B dated July 11, 1972, or later FAA Approved Revisions. This approval should not be extended to other airplanes of these models on which other previously approved modifications are incorporated unless it is determined that the i nterrelationship between this change and any of those other previously approved modifications will introduce no adverse effect upon the ai rworthiness of this airplane. A copy of this certificate and Addendum No . SA64NW shall be maintained as part of t he permanent records for this modified aircraft . ~~..auu:I./k~.dakAu~.«k~Jk~fo~~~~#dAvn~:£UUl'­ ~~~R1"-O/~~~~~-7./k~~~ ~~~ g~..,t'~ . July 19, 1973 g;~..,t'~: September 13, 1973 Sept ember 18, 1986 ( Title ) A'9' alteration of this certificate is punishable by a fine of not exceeding 11,000, or impri.stnunent not exceeding 3 years, or both. This certificate may ~ /Tans/erred in accordanu with FAR 21.47. FAA fou< 8110-2 (10-6 8) tlIItd ~ II S!mtm Iltpartmmt of nansportation-,ftdaal abiation administration ~uppltl11rntal 1C~pt Q:trtificau ((tontinuation £'httt) JV~ SA64NW SUPPLEMEHTAL TYPE CERTIFICATE ADDENDUII 110. SA64D The conditions and limitations of Type Certificate Data Sheet No. 3A21 apply except as follows: This STC Addendum, which is a part of Supplemental Type Certificate No. SA64NW prescribes conditions and limitations under which the product for which the STC was issued meets the airworthiness requirements of the Civil Air Regulations. A copy of this STC Addendum is required to be maintained to as a part of the modified aircraft's permanent record. SUPPLEMENTAL TYPE CERTIFICATE HOLDER: MADRAS AIR SERVICE I & II. MODELS 210 AND 210A, AS MODIFIED BY STC SA64NW Airspeed L imi ts : Never exceed 197 mph (171 knots) Maneuvering 128 mph (111 knots) Maximum structural cruising 172 mph (149 knots) III. MODELS 210B AND 210C, AS MODIFIED BY STC SA64NW Airspeed Limits: Never exceed 221 mph (192 knots) Maneuvering 130 mph (113 knots) Maximum structural cruising 187 mph (145 knots) IV. MODELS 210-5(205) AND 210-5(205A), AS MODIFIED BY STC SA64NW Airspeed Limits: Never exceed 206 mph (179 knots) Maneuvering 136 mph (118 knots) Maximum structural cruising 167 mph (145 knots) V & VI. MODELS 210D AND 21 OE, AS MODIFIED BY STC SA64NW VII & VIII Airspeed Limits: Never exceed 221 mph (192 knots) Maneuvering 132 mph (114 knots) Maximum structural cruising 187 mph (162 knots) MODELS T-210F AND 210F, AS MODIFIED BY STC SA64NW Airspeed Limits: Never exceed 221 mph (192 knots) Maneuvering 129 mph (112 knots) Maximum structural cruising 187 mph (162 knots) 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 (1()'69) This ,,,tijieau ma.7 b, tTansjemti in QU/Wdan&, willa F.tR 21.47. X fl)DELS 210G AND 21 OH, AS fl)DIFIED BY STC SA64NW Airspeed Limits: Never exceed 221 mph (192 knots) Maneuvering 129 mph (112 knots) Maximum structural cruising 187 mph (162 knots) XII MODELS 21 OJ, AS MODIFIED BY STC SA64NW Airspeed Limits: (CAS) Never exceed 221 mph (192 knots) Maneuvering 129 mph (112 knots) Maximum Structural Cruising 187 mph (162 knots) XIII MODELS 210K & 210L, AS MODIFIED BY STC S!64NW Airspeed Limits: (CAS) Never exceed 221 mph (192 knots) Maneuvering 129 mph (112 knots) Maximum Structural Cruising 187 mph (162 knots) BOTE 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 wing tips 9.5 lb total; deduct weight of the tip being removed and add the difference to the aircraft empty weight. The moment change is negligible. BOTE 2: All of the maximum maneuvering speed placards called for by NOTE 2 of Type Certificate Data Sheet No. 3A21 must be revised to show the maximum maneuvering speeds specified in sections I through VIII & X. - END - Page 4 of 4 ## Every issue (1) - September 18, 1986: Amended, Current. [certificate](https://openairdocs.org/files/sha256/e2/f9/e2f9f908a8cea3cf84b585f8f161935073c6e94af98b280cd7e51a4db00382ea) --- 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.