# STC SA4293WE - Type: Supplemental type certificate - Status: Current, Reissued - Holder: Turbine Conversions Int, United States - Description: Removal of original equipment engines and propellers and installation of two Lycoming LTP101-600A-1A turbo-propeller engines and two three-bladed Hartzell HC-B3TN-3C/T10173-13Q propellers and controls including a major fuel system modification. - Applied: November 1, 1977 - Status date: September 6, 1996 - Product: Aircraft, Small Multi-Engine - Certification basis: Part 3, Part 21, Part 23, Part 27, Part 36, Part 91 - Data sheets: [TCDS A7CE](https://openairdocs.org/tcds/A7CE) - Certificate PDF: https://openairdocs.org/files/sha256/c7/70/c77038067920d440b16ae2fd8f1cec52728c7f1e9ec618bf49eff8dd66acfbe5 - FAA DRS: https://drs.faa.gov/browse/excelExternalWindow/DB82FE284616CC5F85256CC2000E3B4D.0001 - DRS record last changed: December 6, 2025 - Page: https://openairdocs.org/stc/SA4293WE ## ADs that name it (0) None. ## Approved models (2) - The Cessna Aircraft Company 421B ([TCDS A7CE](https://openairdocs.org/tcds/A7CE)) - The Cessna Aircraft Company 421C ([TCDS A7CE](https://openairdocs.org/tcds/A7CE)) ## What the certificate says This is OCR from the scanned FAA certificate. OCR can misread letters and numbers. United States of America 8103 Department of Transportation Federal Aviation Administration Supplemental Type Certificate Number: SA4293WE This certificate issued to: TURBINE CONVERSIONS, INT. 2016 Palomar Airport Road Carlsbad, California 92008 Certifies that the change in the type design for the following product with the limitations and conditions therefor as sperified hereon meets the airoorthiness requirenents of Part + of the + Roegulations. *See Continuation Sheet Pages 5 & 6 Original Product • Type Certificato Number : A7CE Make: Cessna Model. : 421B and 421C Description of Type Design Change: ; Removal of original equipment engines and propellers and installation of two Lycoming LTP101-600A-1A turbo-propeller engines and two three-bladed Hartzell HC-B3TN-3C/T10173-13Q propellers and controls including a major fuel system modification in accordance with Riley Aircraft Corporation FAA sealed Master Drawing List R421000, Rev. S, and/or later sealed revisions plus appropriate Riley Aircraft Corporation Airplane Flight Manual Cessna 421B FAA approved July 29, 1981 or Cessna 421C FAA approved January 22, 1982 or later approved revisions. Limitations and Conditions: . The approval of this change in type design applies basically to the Cessna Models 421B and 421C. 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 by the installer that the interrelationship between this change and any of those other previously approved modifications will introduce no adverse effect upon the airworthiness of the aircraft. Date of Application: November 1, 1977 Date Reissued: April 14, 1983, May 26, 1989, September 6, 199€ Date of Issuance: January 30, 1981 Date Amended: January 22, 1982 FEDERAL AVIATION By Direction of the Administrator Michala. Durgly (Signature) Manager, Technical and Administrative TOMINISTRATIO Support Staff, ANM-103L (Title) FAA Form 8110-2-1(10-68) Page 1 of 8 TRANSFER ENDORSEMENT Transfer the ownership of Supplemental Type Certificate Number to (Name of transferee) (Address of transferee) (Number and street) from (Name of grantor) (Print or type) - (Address of grantor) (Number and street) (City, Stale, and ZIP code) Extent of Authority (if licensing agreement): Signature of grantor (In ink): - United States of America Department of Transportation Federal Aviation Administration Supplemental Type Certificate (Continuation Sheet) Number: SA9293HE These continuation sheets are a part of Supplemental Type Certificate NO. SA4293WE. Limitations and Conditions: of Type Certificate No. ACE apply except as outlined below: VI - Model 421B and 421C (Normal Category) Modified by STC SA4293WE Engines: Two Lycoming STP101-600A-1A turboprop Fuel: Kerosene Fuels: MIL-T-5624, JP-5 (NATO Code F42, F44). ASTM D1655-70, Jet A, Jet A-1 (NATO Code F34, F35) . See NOTE 4 for fuel additives Engine Limits: Operating Limits Shaft N Gas Indicated Prop Measured Horse Generator Torque Shaft Gas Temp. Power Speed Pressure Speed Limit (br. p.m.) (psi) (r. p.m.) MGT (°C) Takeoff (5 min) 475* 103.2 51.3 1924 782 Max. Continuous 475* 101.7 51.3 1924 763 Starting .... 899** Transient 104.8 2112 843** * • Flat hated the airple powerplant Flat rated: The engines may be capable of producing more power than that for which the airplane has been certificated. Under these conditions the limits marked on the powerplant instruments shall not be exceeded. ** MGT time limit is 12 seconds above 782°C during starting and transients. FAA FORM 8110-2-1 (10-69) PAGE OFf PAGES FAA AC 73-2631 Enited States of Scrico Department of Transportation Federal Aviation Administration Supplemental Type Certificate (Continuation Sheet) Numbex SAA2934E Propeller and Two Hartzell constant speed, full feathering, Propeller reversible, three-bladed Limits Hub: HG-B3TN-3C Blade: T10173-130 Diameter: 88 inches Pitch at 30-inch station: Feathered +87.0° + .5° Hydraulic Low Pitch Stop +20.2° · .1° Reverse - 11.0° · .4° Model 421B 421C Airspeed Limits VMU (Maneuvering) (Max Operating) 198 knots 203 knots (IAS) 151 knots 152 knots (Flaps Extended) (Takeoff & Approach) 168 knots 176 knots 45° (Landing) 137 knots 140 knots YMCA (Min. Control Speed) Air 94 knots 97 knots (Inoperative Engine Feathered) VLE (Landing Gear Extended) 142 knots 176 knots C.G. Range Aft Limit (Landing Gear 421B - 6, 7 or 8 Place Seating Configuration Extended) 156.4 in. aft of Datum at 7579 lbs. 156.7 in. aft of Datum at 7050 lbs. 421B - 10 Place Seating Configuration and all 421C 157.7 in. aft of Datum at 7579 lbs. 158.0 in. aft of Datum at 7050 lbs. Forward Limit for 421B and 421C 6 thru 10 Place Seating Configuration 153.1 in. aft of Datum at 7579 1bs. 147.1 in. aft of Datum at 6100 1bs. Empty Wt. C.G. None Range Leveling Means Same as ACE Maximum Weight Takeoff 7579 1bs. Landing 7200 1bs. Zero Fuel 6957 lbs. for 4218 6606 lbs. for 421C No. of Seats Same as A7CE Maximum Baggage Same as ACE 47 PAGEA OF8 PAGES FAA AC 73-2651 United States of America Department of Transportation Federal Aviation Administration Supplemental Type Certificate (Continuation Sheet) Number SA4293WE Fuel Capacity Capacity Usable (U.S. gal) (U.S. gal) Model 421B Main Tanks (2) 102 100 Wing Aux (2) 100 96 Nacelle Aux (2) 77 75 Total 279 271 Model 421C Main Tanks (2) 213.4 206 Nacelle Tank (2) 77 75 Total 290.4 281 Oil Capacity 7.0 quarts per engine Maximum Operating Altitude 27,000 ft. Control Surface Movements Same as ACE Serial Numbers 421B0301 and subsequent Eligible Certification Basis Model 421B Modified by STC SA4293WE Part 3 of the Civil Air Regulations dated May 15, 1956 including amendments 3-1 thru 3-5 and 3-8 as follows: Paragraphs: all of Subpart A; 3.171 thru 3.183, 3.185 thru 3.194 and 3.197 thru 3.265 of Subpart C; 3.291 thru 3.307 and 3.317 thru 3.401 of Subpart D; 3.651, 3.780 of Subpart G; all of Subpart H. The following ortions of FAR 23 dated February 1, 1965, as amended by 23-1 thru 23-7 as follows: Paragraphs 23.21, 23.23, 23.29, 23.31, 23.33, 23.141 thru 23.147, 23.161 thru 23.207 and 23.231 thru 23.253. Amendments 23-. thru **FAA FORM 8110-2-1 (10-69) PAGE 50F 8PAGES C FAA AC 73-2651** United States of America Department of Transportation Federal Aviation Administration Supplemental Type Certificate (Continuation Sheet) Number: SA4293NE 23.-14 FAR 23.1419 when the ice protection equipment is installed in accordance with the FAA Approved Airplane Flight Kit (FK) No. 194. FAR 23 Amendments 23-1 thru 23-21 Paragraphs 23.25, 23.45 thru 23.// and 23.149, 23.335(b)(4) (i), 23.361, 23.367, 23.372 and 23.479(b), 23.629, 23.859, 23.863(a), 23.901 thru 23.1203, 23.1303(a) thru (d), 23.1305 thru 23.1309, 23.1323, 36, Appendix F, dated December 1, 1969, including Amendments 36-1 thru 36-11 and SFAR 27 dated February 1, 1974 including Amendments 27-1 and 27-2. Applicable portions of FAR 21 dated January 6, 1975 thru Amendment 21-42 plus Special Conditions No. 23-98-WE-29 datec October 10, 1980. Model 421C Modified by STC SA4293WE Part 3 of the Civil Air Regulations dated May 15, 1956 including amendments 3-1 thru 3-5 and 3-8 as follows: Paragraphs: all of Subpart A; 3.171 thru 3.183, 3.185 thru 3.194 and 3.197 thru 3.265 of Subpart C; 3.291 thru 3.307 and 3.317 thru 3.355, 3.361 thru 3.401 of Subpart 3.721 51d 3.926 thru 3.,28 of Subpart 3; 3.,3 t96 thru 3.743, 3.748 thru 3.758, 3.766, 3.769 thru 3.11, 3.19 and 3.780 of Subpart G; all of Subpart H. The following portions of FAR 23 dated February 1, 1965, as amended by 23-1 thru 23-7 as follows: Paragraphs 23.21, 23.23, 23.29, 23.31, 23.33, 23.141 thru 23.147, 23.161 thru 23.207 and 23.231 thru 23.253. Amendments 23-1 thru 23.-14 FAR 3.729, 23.1387 (e), 23.1435 and FAR 23.1419 when the ice protection equipment is installed in accordance with the FAA Approved Airplane Flight Kit (FK) No. 194. FAR 23 Amendments 23-1 thru 23-21 paragraphs 23.25, 23.45 thru 23.77 and 23.149, 23.335(b)(4) (1), 23.361, 23.367, 23.372 and 23.479(b), 23.629, 23.859, 23.863(a), 23.901 thru 23.1203, 23.1303(a) thru (d), 23.1305 thru 23.1309, 23.1323, 23.1325, 23.1329, 23.1335 thru 23.1367, 23.1431, FAA FORM 8110-2-1 (10-69) PAGE 6 OF g PAGES C FAA AC 73-2651 Eniced States of Sacrico Department of Transportation Federal Aviation Administration Supplemental Type Certificate (Continuation Sheet) Number: SA4293WE 23.1437, 23.1505(c), 23.1521, 23.1527, 23.152 'FAR Part 23.1545 (d), 23.1549 thru 23.1557 and 23.1583. 36, Appendix F, dated December 1, 1969, including Amendments 36-1 thru 36-11 and SFAR 27 dated February 1, 1974 including Amendments 27-1 and 27-2. Applicable portions of FAR 21 dated January 6, 1975 thru Amendment 21-42 plus Special Conditions No. 23-98-WE-29 dated October 10, 1980. NOTE 1 Current weight and balance report, based on actual weighing of aircraft, together with list of equipment included in certificated empty weight and loading instructions, must be provided. The certificated empty weight and center of gravity location must include unusable fuel as follows: Modified Model 421B Tip (main) tanks (2) - 13 lb. at (+152.0 in.) Wing (aux) tanks (2) - 27 lb. at (+164.0 in.) Nacelle (aux) tanks (2) - 13 lb. at (+202.0 in.) Modified Model 421C Main Wing Tanks (2) - 50 lbs. at (165.2 in.) Nacelle (aux) Tanks (2) - 13 1bs. at (+202.0 in.) NOTE 2 The placards specified in the FAA approved Airplane Flight Manual must be displayed. NOTE 3 Same as Note 3 ACE. In addition, inspection criteria established in compliance with FAR 23.1529 and Airframe Special Condition No. 2 are contained in Section 2, pages 30 and 31 of the Supplemental Maintenance Manual No. D817-13 dated December 31, 1980 or later revision. NUTE 4 Prist MIL-I-27686 (NATO S-748), Phillips PFA-55MB, or equivalent anti-icing additive at concentration not in excess of .15% by volume is approved for use with approved fuels. **FAA FORM 8110-2-1 (10-69) PAGE, OF 8 PAGES FAA AC 73-2651** United States of America Department of Transportation Federal Aviation Administration Supplemental Type Certificate (Continuation Sheet) Number: SA9293WE Production Basis: None. An inflight operational check must be conducted in accordance with FAR 91.167(a) for each aircraft modified in accordance with this Supplemental Type Certificate. When original airworthiness certification has not previously been accomplished, the applicant must also comply with FAR 21.130 and 21.183(d). Amendment Listing January 30, 1981(1) April 28, 1981(A) May 21, 1981(A) July 29, 1981(A) January 22, 1982(A) added Model 421C 47. PAGE g OF g PAGES C FAA AC 73-2651 ## Every issue (1) - September 6, 1996: Reissued, Current. 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