# TCDS A3IN: Avions Jodel - Type: Type certificate data sheet - Status: Current - Holder: Avions Jodel - Revision: 0 - Revised: February 3, 1964 - Product: Aircraft, Small Airplane - Certification basis: Part 3, CAR 3, CAR 10 - Data sheet PDF: https://openairdocs.org/files/sha256/89/1f/891f4f142115f4e8608e2b08d0e36af88a2e834f541cb661b7d1b796844b1fd8 - FAA DRS: https://drs.faa.gov/browse/excelExternalWindow/69444B376BFBB64F852567380062746C.0001 - Page: https://openairdocs.org/tcds/A3IN ## Models (1) As the data sheet lists them. - D-140-B ## 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 A3IN JODEL D-140-B February 3, 1964 TYPE CERTIFICATE DATA SHEET NO. A3IN This data sheet which is a part of type certificate No. A3IN 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 Avion Jodel Route de Seurre Beaune (Cote d'Or) France I - Model D-140-B, 4 or 5 PCLM, (Normal Category) Approved July 1, 1963 Engine Lycoming O-360-A2A Fuel 91/96 Octane Minimum grade aviation gasoline Engine limits For all operations 2700 rpm (180 hp) Propeller and propeller limits McCauley, 1A200-FA, Fixed Pitch Metal Static rpm at maximum permissible throttle setting: Not over 2250, not under 2100. No additional tolerances permitted. Diameter: Maximum 80 in., minimum allowable for repairs 78 1/2 in. (No further reduction permitted) Airspeed limits Never exceed 178 mph (155 knots) Maximum structural cruising 159 mph (138 knots) Maneuvering 121 mph (105 knots) Maximum speed with flaps extended 97 mph ( 84 knots) C.G. range +14" to +24" Empty weight C.G. range None Datum Leading edge of wing Leveling means Upper longeron of fuselage Maximum weight 2650 lbs. No. of seats 4 or 5 (2 at +18") (2 or 3 at +50") See note 3 for rear seat occupancy. Maximum baggage Forward compartment 130 lbs (-21) Rear compartment 200 lbs (+51) Fuel capacity Two tanks: 24 gallons usable (-22") 33 gallons usable (+52") Oil capacity 8 quarts (-45") Control surface movements Aileron Up 12° Down 12° Tolerance Elevator Up 25° Down 20° permitted Elev. Trim tab Up 20° Down 25° on all surface Flaps Take Off 20° Landing 50° travels Rudder Right 25° Left 25° +3°, -0° 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 is made. Certification basis CAR 10. Type Certificate No. A3IN issued July 1, 1963. Date of Application for Type Certificate February 1, 1962. Each aircraft and any replacement part manufactured in France must be identified as imported. A3IN 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 Secrtariat 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 3-6 and conforms to T.C. A3IN". 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 No. 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. NOTE 2. (a) The following placards must be displayed in front and in clear view of pilots: "THIS AIRPLANE MUST BE OPERATED IN NORMAL CATEGORY IN COMPLIANCE WITH THE OPERATING LIMITATIONS STATED IN THE FORM OF PLACARDS, MARKINGS AND MANUALS, NO ACROBATIC MANEUVERS, INCLUDING SPINS, APPROVED". (b) The following placard must be displayed in the rear seat: "MAXIMUM WEIGHT ON REAR SEATS 460 LBS." (c) The following placard must be displayed in the forward luggage compartment: "MAXIMUM WEIGHT 130 LBS.". (d) The following placard must be displayed in the rear luggage compartment: "MAXIMUM WEIGHT 200 LBS. Refer to weight and balance" NOTE 3. Rear seat may be occupied by three persons provided: (a) The total weight on the rear seats is under 460 lbs. (b) The rear seat is equipped with three separate safety belts. (c) Aircraft weight and C.G. position is within limits. - END - ``` ## ADs None name its models. ## Registered aircraft by registry model (OpenAirDocs) - [Jodel Avion D-140-B](https://openairdocs.org/model/jodel-avion-d-140-b): 0 aircraft (registry code 47004RB) ## STCs approved under this data sheet (12) - [STC SA03898NY](https://openairdocs.org/stc/SA03898NY): Installation and maintenance of ORATEX covering and coating material. Aircraft Design & Certification Ltd - [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 SA5159NM](https://openairdocs.org/stc/SA5159NM): Installation of chip detector system.. Northwest Aircraft 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.