# TCDS A26CE: Textron Aviation Inc. - Type: Type certificate data sheet - Status: Current - Holder: Textron Aviation Inc. - Revision: 11 - Revised: November 27, 2017 - Product: Aircraft, Small Airplane - Certification basis: Part 21, Part 23, Part 91 - Registered aircraft: 12, by the registry models matched to it (OpenAirDocs) - Data sheet PDF: https://openairdocs.org/files/sha256/e6/83/e68385cf06358da06a2cea2d54a10419ababa3606050e2ab3ecb98a9ebf3d983 - FAA DRS: https://drs.faa.gov/browse/excelExternalWindow/EF9A96630D975A85862581EF0060D1D0.0001 - Page: https://openairdocs.org/tcds/A26CE ## Models (1) As the data sheet lists them. - T-34C ## What the data sheet says From the PDF's text layer, line by line; tables lose their columns. The PDF is the record. ```text Page No. 1 2 3 4 Rev. No. 11 6 4 9 `DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION A26CE Revision 11 Textron Aviation T-34C (T-34C-1, 34C) November 27, 2017 TYPE CERTIFICATE DATA SHEET A26CE This data sheet which is a part of Type Certificate No. A26CE prescribes conditio ns and limitations under which the product for which the Type Certificate was issued meets the airworthiness requirements of the Civil Air Regulations. Type Certificate Holder Textron Aviation Inc. One Cessna Boulevard Wichita, KS 67215 Type Certificate Holder Record Beech Aircraft Corporation transferred to Raytheon Aircraft Company on April 15, 1996 Raytheon Aircraft Company transferred to Hawker Beechcraft Corporation on March 26, 2007 Hawker Beechcraft Corporation transferred to Beechcraft Corporation on April 12, 2013 Beechcraft Corporation transferred to Textron Aviation Inc. on October 12, 2016 I. Model T-34C, Turbine-Mentor (Foreign Government T-34C-1), 2-PCLM (Acrobatic Category), Approved December 17, 1976 Model T-34C, Turbine-Mentor (Foreign Government 34C), 2-PCLM (Acrobatic Category), Approved August 25, 1978 Engine Pratt & Whitney Aircraft of Canada, LTD., of United Technologies Corp., Pratt & Whitney Division PT6A-25 (turboprop) per Beech Specification BS 22599 (T-34C) GL-1 and On or BS 22814 (T-34C-1) effective GM-1 through GM-71, GM-78 through GM-98 and (34C) effective GP-1 through GP-6. Pratt & Whitney Aircraft of Canada, Ltd., of United Technologies Corp., Pratt & Whitney Division PT6A-25A (turboprop) per Beech Specification BS 23784 (T-34C-1) effective GM-143 and On and (34C) effective GP-7 and On. Fuel JP-4, JP-5, JP-8, commercial kerosene, Jet A, Jet A-1, Jet B, and fuels conforming to P&W Specification 522, or ASTM Spec. No. ES2-74 (fuels shall conform to the specifications as listed or to subsequent revisions thereto). Fuels must contain anti-icing additives conforming to PFA 55MB (MIL-I-27686). Oil (Engine & Gearbox) UACL PT6 Engine Service Bulletin No. 1001 lists approved brand oils. Rev. 11 2 A26CE I. Model T-34C (Foreign Government T-34C-1), Model T-34C (Foreign Government 34C) (cont’d) Engine Limits Maximum Permissible Turbine N1 Gas Interstage Shaft Generator Prop Shaft Temperature Horsepower Speed (%) Speed (R.P.M.) (Deg. C.) Takeoff 425 101.5 2,200 695 Max. Continuous 425 101.5 2,200 695 Starting Transient - - - 1,090 (two seconds) R.P.M. overspeed limits (see NOTE 4) Oil temperatures: Minus 40° C. minimum starting Minus 40° C. to 99° C. idle 10° C. to 99° C. max. continuous Inverted flight limits (See NOTE 6) Propeller and Hartzell HC-B3TN-3H hubs with Hartzell T10173-11R blades propeller limits Diameter: 90.5 in. (maximum), minimum allowable for repair: 88.0 in. No further reduction permitted. Pitch settings at: (measure at 30 inch station) Flight idle stop (See NOTE 5) Max. low pitch (ground) - Minus 5° ± .4° Feathered - 87.0° ± .5° Propeller blade life limit - 9,634 hours Spinner: Hartzell C 3065-6 Airspeed Limits (CAS) Max. operating speed 195 knots (224 mph) up to 20,000 ft. Max. operating Mach No. .43 Maneuvering speed 172 knots (198 mph) Max. flap extension speed 100% position 30° 120 knots (138 mph) Max. landing gear extended and extension speed 150 knots (173 mph) Max. landing gear retraction speed 120 knots (138 mph) C.G. range (Landing (+86.0) to (+89.5) at 4,300 lb. Gear Extended) (+84.8) to (+89.5) at 4,000 lb. or less Straight line variation between points given Moment change due to retracting landing gear +831 in.-lb. Empty weight C.G. range (+85.5) to (+85.9) When empty weight C.G. falls within the range given, complete computations of critical fore and aft C.G. positions are unnecessary. Range is not valid for nonstandard arrangements. Maximum weight Ramp 4,325 lb. Takeoff 4,300 lb. Landing 4,300 lb. Zero fuel 3,580 lb. (See NOTE 1) Minimum Crew One pilot Number of seats One crew (+86.1) One crew (+137.1) Maximum baggage None Rev. 11 3 A26CE I. Model T-34C (Foreign Government T-34C-1), Model T-34C (Foreign Government 34C) (cont’d) Fuel Capacity Tank Cap. Gal. Usable Gal. Arm Main 134.7 130 87.5 See NOTE 1(a) for data on unusable fuel Oil capacity 16 qt. total at +31.6 See NOTE 1(b) for data on undrainable oil Maximum Operating 25,000 ft. Altitude For FAR 91 Operations: As limited by FAR 91.211 Control Surface Wing flap Maximum 30° Movements Aileron tabs Up 10° Down 10° *Aileron Up 20° Down 21° Elevator tabs Up 10° Down 20° Elevator Up 20° Down 15° Rudder tab Right 11½° Left 11½° Rudder Right 28° Left 28° *Neutral is defined as 2° down with respect to travel board zero reference. Serial Nos. eligible GL-1 and On (T-34C) GM-1 and On (T-34C-1) GP-1 and On (34C) Datum Located 88.0 inches forward of the wing main (forward) spar centerline. Leveling Means Two external screws located on left side of fuselage at station 186.7. Certification Basis FAR 23, effective February 1, 1965, as amended by 23-1 through 23-13 and FAA Special Conditions 23-56-CE-7 issued June 27, 1974. FAR 36 dated December 1, 1969, as amended by 36-1 through 3-5. Equivalent Safety Findings: FAR 23.621, 23.689(b), 23.777(d)(1), 23.777(e). Application for Type Certificate dated March 28, 1973. Type Certificate No. A26CE issued December 17, 1976, obtained by the manufacturer under delegation option procedures. Production basis Production Certificate No. 8. Delegation Option Manufacturer No. CE-2 authorized to issue airworthiness certificates under delegation option provisions of Part 21 of the Federal Aviation Regulations. Equipment The basic required equipment as prescribed in the applicable regulations (see Certification basis) must be installed in the aircraft for certification. In addition, the following items of equipment are required: 1. Pre-stall warning system consisting of: a. P/N 12K (Rosemount) sensor b. P/N 20U-1 (Rosemount) computer c. P/N C-04002 (Safe-Flight) shaker 2. Maximum allowable airspeed indicator, P/N 104-384056-3, front and rear cockpits. Rev. 11 4 A26CE Data Pertinent to All Models NOTE 1. Current weight and balance data, loading information and a list of equipment included in empty weight must be provided for each aircraft at the time of original certification. (a) Basic empty weight includes unusable fuel of 31 lb. at (+91.3 in.) with 2.2 lb. being undrainable. (b) Basic empty weight includes engine oil of 32 lb. at (+31.6 in.) with 6.3 lb. being undrainable. NOTE 2. All placards required in the FAA Approved Airplane Flight Manual (AFM) must be installed in the appropriate location. NOTE 3. Mandatory retirement times for all structural components are contained in the AFM (P/N 104-590024) Limitation Section. These limitations may not be changed without FAA Approval. NOTE 4. One hundred percent propeller shaft speed is defined as 2,204 rpm, and is the normal steady state operating limit. Gas generator speeds up to 102.7 percent are permissible for 10 seconds and to 101.6 percent for unlimited periods, subject to applicable temperature and other limits. One hundred percent gas generator speed is defined as 37,468 rpm . NOTE 5. Flight idle propeller low pitch is set so that at 2,000 rpm, there shall be an indicated 300 + 25 ft.-lb. torque corrected to sea level standard day. NOTE 6. Inverted flight (less than "0" g) limited to a maximum of 15 seconds. NOTE 7. Prior to issue of a Standard Airworthiness Certificate, the T-34C must be modified in accordance with Beech Drawing 104-005000. Prior to issue of a Standard Airworthiness Certificate, the T-34C-1 and 34C must be modified in accordance with Beech Drawing 104-005001. ---- END ---- ``` ## ADs (7, in force first) - [AD 2023-10-02](https://openairdocs.org/ad/2023-10-02): Indicating/Recording System, Navigation · Boeing 18, 23, 35 and 1,060 more. Effective May 26, 2023 - [AD 2001-23-10](https://openairdocs.org/ad/2001-23-10): Flap Flex Shaft Assemblies · Textron 35, 35-33, 35-A33 and 60 more. Effective Dec 13, 2001 - [AD 95-04-10](https://openairdocs.org/ad/95-04-10): Wing Attach Bolts · Textron T-34C. Effective Apr 7, 1995 - [AD 94-04-18](https://openairdocs.org/ad/94-04-18): Elevator Arm Assembly · Textron T-34C. Effective Apr 12, 1994 - [AD 91-17-01](https://openairdocs.org/ad/91-17-01): Elevator Trim Tab Actuators · Textron 35-33, 35-A33, 35-B33 and 40 more. Effective Nov 25, 1991 - [AD 85-22-05](https://openairdocs.org/ad/85-22-05): Nuts and Bolts Replacement · Textron 100, 200, 200C and 60 more. Effective Nov 12, 1985 - [AD 80-07-05](https://openairdocs.org/ad/80-07-05): Bolt and Nut, Wing Section · Textron 200, 200C, 200T and 10 more. Effective Apr 3, 1980 ## Registered aircraft by registry model (OpenAirDocs) - [Beech T-34C](https://openairdocs.org/model/beech-t-34c): 10 aircraft (registry code 1152015) - [Beechcraft T-34C TURBO MENTOR](https://openairdocs.org/model/beechcraft-t-34c-turbo-mentor): 2 aircraft (registry code 4210111) ## STCs approved under this data sheet (44) - [STC SA04837NY](https://openairdocs.org/stc/SA04837NY): Installation of AeroLED's Holdings, LLC., position lights, navigation lights, strobe lights and beacon lights. AeroLED's Holdings, LLC - [STC SA12406WI](https://openairdocs.org/stc/SA12406WI): Installation of a Garmin AXIS Flight Display System. Garmin International Inc. - [STC SA02636SE](https://openairdocs.org/stc/SA02636SE): Installation of Garmin GPS 175 Navigation System and GNX 375 Navigation System with ADS-B In/Out Transponder.. Garmin International Inc. - [STC SA02019SE-D](https://openairdocs.org/stc/SA02019SE-D): Installation of Garmin Model GTN 625/635/650; 725/750 Navigation System. Garmin International Inc. - [STC SA02738CH](https://openairdocs.org/stc/SA02738CH): Installation of L-3 Communications Avionics Systems. Acron Aviation Inc. - [STC SA04046CH PAGE 1](https://openairdocs.org/stc/SA04046CH%20PAGE%201): Installation of L-3 GENESIS (TM) Electronic Standby Instrument System (ESI-500/MAG-500). Acron Aviation Inc. - [STC SA02658SE](https://openairdocs.org/stc/SA02658SE): Installation of Garmin GI 275 Multi-Function Display System. Garmin International Inc. - [STC SA02571SE](https://openairdocs.org/stc/SA02571SE): Installation of Garmin G500/G600 TXi Integrated Avionics System (Primary Flight Display, Multi-Function Display, and Engine Indicating System Display).. Garmin International Inc. - [STC SA02444AK](https://openairdocs.org/stc/SA02444AK): Approval of the L-3 Communications NGT 9000/9000R ADS-B system installed. ADS-B Technologies LLC - [STC SA02430SE](https://openairdocs.org/stc/SA02430SE): Fabrication and installation of a camera housing. Airborne Sensor LLC - [STC SA00401BO](https://openairdocs.org/stc/SA00401BO): Installation of a SkyTrax100B UAT receiver. Avidyne Corporation - [STC SA00692WI-D](https://openairdocs.org/stc/SA00692WI-D): Installation of Bendix/King KLN 900 GPS Navigation System for enroute and non-precision approach IFR operation.. Honeywell International Inc - [STC SA01714WI](https://openairdocs.org/stc/SA01714WI): Installation of a Garmin transponders: (a) GTX 330/330D/33/33D with ADS-B Out functionality; (b) GTX 335/335R/345/345R with ADS-B Out and In functionality; or (c) GTX 335R/345R with ADS-B Out functionality in select airplanes installed with G950/G1000 systems.. Garmin International Inc - [STC SA00344BO PAGE 1](https://openairdocs.org/stc/SA00344BO%20PAGE%201): Installation of Parmetheus Plus LED PAR36 and PAR46 taxi and landing lights.. Whelen Aerospace Technologies - [STC SA02153LA-D PAGE 1](https://openairdocs.org/stc/SA02153LA-D%20PAGE%201): Installation of Garmin G600 Primary Flight Display (PFD) and Multifunction Display (MFD) System. Garmin International Inc. - [STC SA02212AK](https://openairdocs.org/stc/SA02212AK): Replacement of existing landing and/or taxi light reflector and bulbs with high intensity discharge (HID) lighting systems. Seaplanes North LLC - [STC SA00382BO](https://openairdocs.org/stc/SA00382BO): Installation of Globalstar Antenna and Cradle provisions to support a Globalstar GPS-1700 in non-composite airplanes. Avidyne Corporation - [STC SA02428SE](https://openairdocs.org/stc/SA02428SE): Installation of an Air Stream Switch for an electric time recording device on non-pressurized aircraft. Henry F Rogers/David E Polley - [STC SA00343BO](https://openairdocs.org/stc/SA00343BO): Installation of a single configuration or a dual configuration Avidyne Corporation Integrated Flight Display, Model IFD540 loaded with Release 10.0 software (or later FAA approved release). Avidyne Corporation - [STC SA00352BO PAGE 1](https://openairdocs.org/stc/SA00352BO%20PAGE%201): Installation of an Avidyne Corporation Mode A/C/S Transponder with ADS-B Out capability, Model AXP340 loaded with Version 3.13 software (or later FAA approved version),. Avidyne Corporation - [STC SA02119SE PAGE 1](https://openairdocs.org/stc/SA02119SE%20PAGE%201): Installation of Garmin GDL 88 ADS-B UAT Transceiver System. Garmin International Inc - [STC SA02442AK PAGE 1](https://openairdocs.org/stc/SA02442AK%20PAGE%201): Approval of the L-3 Communications NGT 2000/2500 ADS-B system. ADS-B Technologies, LLC - [STC SA8446SW](https://openairdocs.org/stc/SA8446SW): Installation of Benz PCS-111A programmed continuity sensor in engine chip detector electrical circuit. Meggitt, Orange County, Inc. - [STC SA01085LA](https://openairdocs.org/stc/SA01085LA): Installation of the VNS 1000 Voice Navigation System.. VNS Incorporated - [STC SA015444WI-D](https://openairdocs.org/stc/SA015444WI-D): Modification of a Rockwell Collins, Inc. AFD-3010 and AFD-3010E Adaptive Flight Display Installation in Part 23 Aircraft.. Rockwell Collins Inc - [STC SA01198NY](https://openairdocs.org/stc/SA01198NY): Remove existing starter-generators and install Aircraft Parts Corporation starter-generator P/N 200SG116Q-1.. Skurka Aerospace Inc. - [STC SA01258AT-D](https://openairdocs.org/stc/SA01258AT-D): Installation of left-hand and right-hand box section fuel cell assemblies.. FFC Manufacturing - [STC SA01259AT-D](https://openairdocs.org/stc/SA01259AT-D): Installation of left-hand and right-hand box section fuel cell assemblies.. FFC Manufacturing - [STC SA01033WI](https://openairdocs.org/stc/SA01033WI): Replacement of original outboard main landing gear doors with a one-piece monolithic machined metal door.. Machining Programming Manufacturing Inc - [STC SA4005NM](https://openairdocs.org/stc/SA4005NM): Precise Flight Inc. Pulselite Control System. Precise Flight Inc - [STC SP00400SE](https://openairdocs.org/stc/SP00400SE): Installation of various propeller electrical de-icer models. SMR Technologies - [STC ST10827SC](https://openairdocs.org/stc/ST10827SC): Installation of HF comm, VHF comm, Flitefone, SELCAL, Cabin Interphone, PA amplifier, Comm/Nav Audio Control, Clock, captain's FD-112V Flight Director system, ADF, Radio Altitude, Transponder, DME, Altitude Encoder, ELT, Weather Radar, Strike Finder, PN-101 Pictorial Navigation system, 400/60 Hz inverters, cockpit lighting system, strobe lights, various cockpit indication & aural warnings and an engine pre-oil system. Spirit Wing Aviation LTD - [STC SA01158WI](https://openairdocs.org/stc/SA01158WI): Installation of Aero Enhancements UV250-1 Supplemental Instrument Panel Lightning System.. Aero Enhancements Inc. - [STC SA572EA](https://openairdocs.org/stc/SA572EA): Installation of Goodrich Model 5735K deicer kit (P/N 5735 deicer boot, P/N D-5735-1 cable, P/N 5735H hardware kit). Limited to aircraft which incorporate Goodrich Propeller Deicing Systems equipped with Goodrich Propeller Deicer Boot P/N 4E1185-5 on Hartzell propellers as listed on STC SA572EA eligibility list.. Goodrich Corp. - [STC SA01258AT](https://openairdocs.org/stc/SA01258AT): Installation of left hand and right hand box section fuel cell assemblies.. Floats & Fuel Cells - [STC SA01259AT](https://openairdocs.org/stc/SA01259AT): Installation of left hand and right hand box section fuel cell assemblies.. Floats & Fuel Cells - [STC SA812NE](https://openairdocs.org/stc/SA812NE): Installation of BF Goodrich Model 6975-1 De-Icer kit or BF Goodrich Model 6975-10 De-Icer kit.. BF Goodrich Aerospace - [STC SA01460AT](https://openairdocs.org/stc/SA01460AT): Installation of Becker AR-4201VHF Communications Transceiver.. Raytheon Aerospace Co - [STC SA00023WI](https://openairdocs.org/stc/SA00023WI): Installation of structural provisions for an anti- collision warning system.. BF Goodrich Flight Systems, Inc - [STC SA2540CE](https://openairdocs.org/stc/SA2540CE): The installation of provisions only for an anti-collision warning system.. BF Goodrich Flight Systems, Inc - [STC SA1455NM](https://openairdocs.org/stc/SA1455NM): Installation of a flame proof auxiliary heater-dryer, Model12-1600.. Thermal, Inc - [STC SA2943SW](https://openairdocs.org/stc/SA2943SW): Addition of Hydro Seal Fluid Additive to landing gear shock struts.. Granville Lasseter/dba Granville's Aircraft Strut Sealant - [STC SA02153LA-D](https://openairdocs.org/stc/SA02153LA-D) (historical): Installation of Garmin G600 Primary Flight Display (PFD) and Multifunction Display (MFD) System. Garmin International Inc - [STC ST01085LA](https://openairdocs.org/stc/ST01085LA) (historical): Installation of the VNS 1000 Voice Navigation System.. VNS Incorporated --- 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.