# TCDS H1EU: Eurocopter France - Type: Type certificate data sheet - Status: Current - Holder: Eurocopter France - Revision: 2 - Revised: February 15, 2007 - Product: Aircraft, Rotorcraft - Certification basis: Part 21, Part 29 - Data sheet PDF: https://openairdocs.org/files/sha256/51/16/5116188d97fcda589f26aa72e2f324939084f1af378a3f02ceec8813433fd1e9 - FAA DRS: https://drs.faa.gov/browse/excelExternalWindow/DF992A9E573DF613862572880073F4DF.0001 - Page: https://openairdocs.org/tcds/H1EU ## Models (1) As the data sheet lists them. - SA 321 F ## 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 Rev. No. 1 2 2 DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION H1EU Revision 2 SUD-AVIATION SA 321 F February 15, 2007 TYPE CERTIFICATE DATA SHEET NO. H1EU This data sheet which is a part of type certificate No. H1EU prescribes conditions and limitations under which the product for which the type certificate was issued meets the airworthiness requirements of the Federal Air Regulations. Type Certificate Holder EUROCOPTER FRANCE Aeroport International Marseille Provence 13725 - Marignane - Cedex France I - Model SA 321 F (Transport Helicopter - Category A), Approved August 29, 1968 Engines 3 Turbomeca TURMO III C5 Fuel Aviation Kerosene - JP4 or JP5 Approved fuels and anti-icing additives limitati ons are specified in the Rotorcraft Flight Manual (See NOTE 5). Engine Limits Sea level sta tic - standard day conditions. Shaft Power Gas Power HP Turbine Generator Turbine RPM RPM Inlet temp °C Takeoff (5 min) 1350 5915 33.150 745 One engine inoperative ( 30 min) 1350 5915 33.150 745 One engine inoperative (2 1/2 min) 1450 5915 33.550 775 (See NOTE 3) Maximum continuous 1230 5915 32.500 720 Maximum transient (30 seconds) - - - 800 Starting (30 seconds) - - - 750 Allowable maximum overspeed - 6344 33.700 - Takeoff and maximum continuous horsepower ratings are normally obtained at a power turbine speed of 5915 rpm. Total power for three engine operation is limited to 3750 HP for takeoff and 3380 HP maximum continuous. Rotor Limits Maximum 232 rpm. Minimum 180 rpm. Airspeed limits Never exceed 130 knots CAS at max. weight. Variation of V ne with weight and altitude is in the Rotorcraft Flight Manual. C.G. Range (+244.09) to (+259.84) Empty Weight C.G. Range None 2 H1EU Datum 255.905 inches forward of main rotor centroid. Leveling Means Leveling plates on left side of front fuselage. Maximum weight 27,560 lb. Minimum Crew Two (2) Maximum Passengers 39 limited by emergency exit requirements. Maximum Baggage 2320 lb (1160 lb in each external side sponsons). The cabin floor area between station +95.67 and +464.96 is structurally satisfactory for an uniformly distributed loading of 143.5 p.s.f. when used for cargo purposes. Fuel capacity 618 gallons. 206 gal. at (+ 190.31) 206 gal. at (+ 224.53) 206 gal. at (+ 302.79) Unusable fuel 28 gal. (9.4 gal. for each tank) Oil capacity 9.51 gallons (2 tanks 3.17 gal. each at (+ 145.00) (1 tank 3.17 gal. at (+ 361.06) Rotor Blade and Control Movements For rigging inform ation, refer to Maintenance Manual. Serial Nos. Eligible The French Government Certifi cate of Airworthiness for Export endorsed as noted below under "Import Requirements" must be subm itted for each individual aircraft for which application for FAA certification is made. Certification Basis FAR 21.29 - FAR 29 effective February 1, 1965, including Amendments 29-1 and 29.1323 of Amendment 29-3, plus Special C onditions notified by the U.S. Government to the Government of France in FAA le tters of January 29, 1968 and June 4, 1968. Type Certificate No. H1EU issued August 29, 1968. Date of Application for Type Certificate: September 28, 1966. The French Direction Generale de l’Aviation Civile (DGAC) originally type certificated this rotorcraft under its type certificate TC 46. The FAA validated this product under U.S. Type Certificate Number H1EU. Effective September 28, 2003, the European Aviation Safety Agency (EASA) began oversight of this product on behalf of the DGAC. Import Requirements The FAA can issue a U.S. airworthiness certificate based on a National Aviation Authority (NAA) Export Certificate of Airworthiness (Export C of A) signed by a representative of the French Generale de l’Aviation Civile (DGAC) on behalf of the European Community. The Export C of A should contain the following statement: “The aircraft covered by this certificate has been examined, tested, and found to comply with the type design approved under U.S. Type Certificate Number H1EU and to be in a condition for safe operation.” 3 H1EU Service Information Each of the documents listed below must state that it is approved by the European Aviation Safety Agency (EASA) or – for approvals made before September 28, 2003 – by the French Generale de l’Aviation Civile (DGAC). Any such documents are accepted by the FAA and are considered FAA approved. • Service Bulletin, • Structural repair manuals, • Vendor manuals, • Aircraft flight manuals, and • Overhaul and maintenance manuals. This applies only to the acceptance of the type design data. Equipment The basic required equipm ent as prescribed in the applicable airworthiness regulations (See Certification Basis) must be installed in the helicopter for certification. In addition the following items of equipment are required: (a) S.G.A.C. approved Ro torcraft Flight Manual. (b) Dual body control system hydr aulic servos S.A.M.M. Co. P/N 7112. NOTE 1. (a) Current weight and balance report including lis t of required equipment included in certificated empty weight, and loading instructions when necessary, must be provided for each helicopter at the time of original certification. (b) Unusable fuel, oil and all hudraulic fluid mu st be included in the certificated empty weight. NOTE 2. The following placard must be displayed in front and in clear view of the pilot. "THIS HELICOPTER MUST BE OPERATED IN COMPLIANCE WITH THE OPERATING LIMITATIONS SPECIFIED IN THE A PPROVED ROTORCRAFT FLIGHT MANUAL". NOTE 3. Engine controls must be set fo r these ratings for vertical operation. NOTE 4. Information essential to the proper maintneance of the helicopter is contained in the Manufacturer's Maintenance Manual provided with each helicopter, which specifies that service life limited parts be retired in accordance with its S.G.A.C. approved Chapter 5. NOTE 5. To prevent icing of fuel system components, all fuel in the tanks before takeoff must contain anti-icing additives in accordance with Flight Manual, when route forecast air temperatures are less than 5°C. ...END... ``` ## ADs None name its models. ## Registered aircraft by registry model (OpenAirDocs) - [Sud SA 321F](https://openairdocs.org/model/sud-sa-321f): 0 aircraft (registry code 8680824) ## STCs approved under this data sheet (2) - [STC SH3319NM](https://openairdocs.org/stc/SH3319NM): Installation of Precise Flight Pulselite Control Unit in the Landing /Taxi Recognition Visual Control Light system,. Precise Flight Inc - [STC SA4302NM](https://openairdocs.org/stc/SA4302NM): Installation of Electronics Int'l digital automatic engine analyzer.. Electronics International --- 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.