# TCDS A14IN: Avions Jodel - Type: Type certificate data sheet - Status: Current - Holder: Avions Jodel - Revision: 0 - Revised: August 1, 1963 - Product: Aircraft, Small Airplane - Certification basis: Part 3, CAR 3, CAR 10 - Data sheet PDF: https://openairdocs.org/files/sha256/18/e5/18e5ee2af169f652026e7235c6ee318de50a6860360899100e7e129d308e29b8 - FAA DRS: https://drs.faa.gov/browse/excelExternalWindow/BB63CBF7D8B2A86D8525673800629DAE.0001 - Page: https://openairdocs.org/tcds/A14IN ## Models (1) As the data sheet lists them. - 150 ## 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 Rev. No. - - FEDERAL AVIATION AGENCY A14IN JODEL 150 August 1, 1963 TYPE CERTIFICATE DATA SHEET NO. A14IN This data sheet which is a part of type certificate No. A14IN prescribes conditions 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 Avions Jodel Route de Seurre Beaune (Cote d'Or), France I Model 150, 2 PCLM (Normal and Utility Category), Approved June 18, 1963 Engine Continental O-200-A Fuel 80/87 minimum grade aviation gasoline Engine limits For all operations 2750 r.p.m. (100 hp.) Propeller and propeller limits McCauley 1A100 MCM 69-56 or any approved fixed pitch wood propeller which is eligible for the engine power and speed and which meets the following limits: Static r.p.m. at maximum permissible throttle setting: Not over 2400, not under 2300. No additional tolerance permitted. Diameter: Maximum 70 in., minimum allowable for repairs 68 in. No further reduction permitted. Airspeed limits (TIAS) Never exceed 174 m.p.h. (151 knots) Maximum structural cruising 131 m.p.h. (113 knots) Maneuvering 109 m.p.h. ( 95 knots) Maximum speed, flap extended 94 m.p.h. ( 81 knots) C.G. range (+12) to (+21.5) normal category (+12) to (+18) utility Empty weight C.G. range None Datum Leading edge of wing (section perpendicular to center line) Leveling means Upper longeron of fuselage Maximum weight 1590 lb. (normal), 1450 lb. (utility) No. seats 2 at +24 Maximum baggage See NOTE 2(b) Fuel capacity Two tanks: 10 1/2 gal. Usable (+4) One tank: 29 gal. usable (+47) Oil capacity 5 qt. (-27) Control surface movements Aileron Up 12° Down 12° Tolerance Rudder Right 30° Left 30° Elevator trim tab (measured +3°, -0° with elevator at 0°) Up 13° Down 0° Elevator Up 12° Down 11° +0°, -0.5° Flap Full travel 50° +2° Serial Nos. eligible The S.G.A.C. Certificate of Airworthiness for export endorsed as noted below under "Certification basis" must be submitted for each individual airplane for which application for certification is made. Certification basis CAR 10. Type Certificate No. A14IN issued June 18, 1963. Application for Type Certificate dated May 20, 1963. Each aircraft and any replacement parts manufactured in France must be identified as imported. A14IN Page 2 A U. S. Airworthiness Certificate may be issued on the basis of a Certificate of Airworthiness for Export signed by a representative of the French Secretariat General a l'Aviation Civile (SGAC) containing the following statement: "The airplane covered by this certificate has been examined and found to comply with U.S. Civil Air Regulations Part 3 dated May 15, 1956, including amendments 3-1 through 3-8 and conforms to T.C. A14IN." Equipment The basic required equipment as prescribed in the applicable airworthiness regulations (see Certification Basis) must be installed in the aircraft for certification. The following additional item must be installed: Pre-stall warning indicator, Safe Flight Instrument Corporation 164. NOTE 1. Current weight and balance report including list of equipment included in certificated empty weight, and loading instructions when necessary, must be provided for each aircraft at the time of original certification. The certificated empty weight and corresponding center of gravity location must include unusable oil of 4 lb. at (-27). NOTE 2. (a) The following placard must be displayed in front and in clear view of pilots: (1) "This airplane must be operated as a Normal or Utility Category Airplane in compliance with the approved airplane flight manual. All markings and placards, on this airplane apply to its operation as a Normal Category airplane. For Utility Category operations, refer to the Airplane Flight Manual. No acrobatic maneuvers (including spins) are approved for Normal Category Operations." (2) "Do not place anything on the floor." (3) "Type of operation approved: DAY-VFR." (b) The following placard must be displayed on the baggage area behind the seat: "Maximum weight 130 lb." For additional loading instructions see weight and balance data. NOTE 3. This airplane is limited to DAY-VFR operations until compliance with appropriate sections of CAR 3 is demonstrated for other types of operation. Refer to CAR 3.750, 3.772 and 3.778(h). - END - ``` ## ADs None name its models. ## Registered aircraft by registry model (OpenAirDocs) - [Jodel Avion 150](https://openairdocs.org/model/jodel-avion-150): 0 aircraft (registry code 47008MO) ## STCs approved under this data sheet (13) - [STC SA03898NY](https://openairdocs.org/stc/SA03898NY): Installation and maintenance of ORATEX covering and coating material. Aircraft Design & Certification Ltd - [STC SA10077SC](https://openairdocs.org/stc/SA10077SC): Installation of push-button starter system.. Hartzell Engine Technologies, LLC - [STC SA10921SC](https://openairdocs.org/stc/SA10921SC): Installation of an alternator and regulator as a replacement to existing OEM generators and mechanical voltage regulators. Hartzell Engine Technologies, LLC - [STC SA02283SE PAGE 1](https://openairdocs.org/stc/SA02283SE%20PAGE%201): Installation of Electronics International Inc. Glass Panel Engine Monitor (with In Flight Data) CGR-30P. Electronics International Inc. - [STC SA02402SE PAGE 1](https://openairdocs.org/stc/SA02402SE%20PAGE%201): Installation of Electronics International Inc. Glass Panel Engine Monitor (with In-Flight Data) CGR-30C. Electronics International Inc. - [STC SA00068SE](https://openairdocs.org/stc/SA00068SE): Installation of fuel flow/pressure instruments. (W/TSIO-360-MB1). Electronics International Inc. - [STC SA01988SE](https://openairdocs.org/stc/SA01988SE): Installation of Electronics International Inc. Glass Panel Engine Monitor (with In-Flight Data) MVP-50P.. Electronics International Inc. - [STC SA593CH](https://openairdocs.org/stc/SA593CH): Install Champion SlickSTART magneto booster system.. Champion Aerospace LLC - [STC SA2683NM](https://openairdocs.org/stc/SA2683NM): Installation of Precise Flight, Inc. stand-by vacuum system (SVS). Precise Flight Inc - [STC SA01157LA](https://openairdocs.org/stc/SA01157LA): Installation of Electronics International Model FP-5 or FP-5L fuel flow/fuel pressure instrument as a replacement instrument.. Electronics International Inc. - [STC SA8075SW](https://openairdocs.org/stc/SA8075SW): Installation of fiberglass covering. (M-62 SERIES PT-19) (G-73 SCHWEIZER). Razorback Fabrics Inc - [STC SA489EA](https://openairdocs.org/stc/SA489EA): Installation of ARP Inc. carburetor ice detection system. Aircraft & Rotorcraft Products (ARP) Inc - [STC SA308EA](https://openairdocs.org/stc/SA308EA): Installation of carburetor ice detection system 105AP in single and twin engine aircraft and single engine helicopters powered by Continental, Franklin, and Lycoming type engines equipped with Marvel-Schebler MA-2, MA-3, MA-4, MA-4-5, MA-6 and HA-6 series carburetors. (Normal,Utility and Acrobatic Category airplanes and helicopters equipped with engines and carburetors as described.). Alfred R Puccinelli --- 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.