TCDS A33EU

Page No. 1 2 3 4 5 Rev.No. 4 2 2 3 3 DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION A33EU Revision 4 DASSAULT AVIATION Falcon 10 March 2, 2010 TYPE CERTIFICATE DATA SHEET NO. A33EU This data sheet which is a part of Type Certificate No. A33EU prescribes conditions and limitations under which the product for which the Type Certificate was issued meets the airworthiness requirements of the Federal Aviation Regulations. Type Certificate Holder: DASSAULT AVIATION (See NOTE 6) 9 Rond Point des Champs Elysees 75008 Paris France I - MODEL FALCON 10 (Transport Category Airplane), Approved September 20, 1973 Engines 2 - Airesearch Manufacturing Company of Arizona, Model TPE731-2-1C (FAA Engine Type Certificate E6WE-1) Fuel Fuels conforming to Airesearch Manuf acturing Company of Arizona specifications: EMS 53111 (Type JET A) EMS 53112 (Type JET A 1) EMS 53113 (Type Jet B and JP4) EMS 53116 (Type JP5) Aviation gasoline, MIL-G-5572D, grades 80/87, 100/130 and 115/145, not in excess of 500 gallons per 100 hours of operation, may be used in emergencies. Shall ASA-3, anti-static additive, or e quivalent, in amounts to bring fuel up to 300 conductivity units, is permissible except that in no event shall the additive exceed 1 ppm. MIL-I-27686E inhibitor, icing, fuel system, or equivalent, is approved for use in fuel in amounts up to 0.15 percent by volume. If a different type of fuel is used, or a mixt ure of fuels is used, the engine computer must be adjusted (to adapt the computer to the de nsity of the fuel used) in order to preserve both the starting characteristics and the acceleration and deceleration characteristics of the engine. Oil Oils conforming to Airesearch Manufact uring Company of Arizona Specification EMS 53110, Class B. (Service Information letters of the Aires earch Manufacturing Company of Arizona give brand names of oils conforming to the above specification). A33EU 2 Engine Limits Maximum take off static thrust, up to 86°F Sea level conditions (5 minutes) lb. 3,230 Maximum continuous static thrust, up to 86 °F Sea level conditions lb. 2,966 Maximum permissible engine operating speeds (Takeoff and maximum continuous) Low pressure rotor (N 1) RPM 20,688 Percent 100% High pressure rotor (N 2) RPM 29,692 Percent 100% Maximum permissible interstage turbine temperature (ITT) During starting 860 °C (1,580°F) Takeoff (5 minutes) 860 °C (1,580°F) Maximum continuous 832 °C (1,530°F) Oil pressure limits At idle, psig 25 to 46 Takeoff and maximum continuous psig 38 to 46 Oil temperature Maximum from sea level up to 30,000 ft. 113 °C (235°F) Maximum above 30,000 ft. 132 °C (270°F) Minimum -40 °C ( -40°F) Fuel pressure Minimum fuel pressure warning, psi 4.5 Airspeed Limits V MO (Maximum Operating 350 kts at sea level; 370 kts at 10, 000 ft., with straight line variation between those points. 370 kts from 10,000 ft. to 25,000 ft. M MO (Maximum Operating) M = 0.87 above 25,000 ft. V A (Maneuvering) 220 kts V FE (Slat and Flap Speed) Slats 200 kts Slats + Flaps 15 ° 190 kts Slats + Flaps 30 ° 165 kts Slats + Flaps 52 ° 165 kts V LO (Landing Gear Operation) 190 kts V LE (Landing Gear Extended) 220 kts Windshield Wiper Operation 190 kts V MC (Minimum Control Speed) In flight 97 kts On ground 100 kts C.G.Range (Gear Extended) Forward limit % MAC Weight(lb) Takeoff En Route Landing Aft limit % MAC 18,300 25 25 -- 31 17,200 21.2 21.2 21.2 31 15,720 16 16 16 31 13,230 16 14 14 31 9,920 16 14 14 31 Straight-line variation between points shown. Gear retraction moment is + 1750 in.lb. 3 A33EU Datum Datum is 25% of mean aerodynamic chor d (MAC) which is marked on aircraft and coincides with Fuselage Station (FS) + 268.28 inches. (Fuselage station +0 is the forward end of the aircraft nose cone.) Mean Aerodynamic Chord. Length 80.54 in. Zero % MAC is at FS +248.15 in. Leveling Means A bubble-type level, when placed on the top of bolt heads (with locknuts) on the floor of the fuselage rear compartment, facilitates le veling of the airplane in the longitudinal and lateral directions. Weight Limitations Maximum Weights Maximum ramp 18,300 lb. Maximum takeoff (brake rel ease) 18,300 lb.(See NOTE 3 and 4) Maximum landing 17,200 lb. Maximum zero fuel 12,460 lb (See NOTE 3) Minimum weight 9,920 lb Minimum Crew 2 - Pilot and co-pilot Maximum Passengers 9 with appr opriate approved passenger provisions for cabin interior and approved seating arrangement. (AMD Production Memo No. 1908 iden tifies approved passenger provisions and seating arrangement fo r a maximum of 7 passengers). 0 - without passenger provisions for cabin interior but incorporating AMD Ferry Kit per Production Memo No. 751. Maximum Baggage Compartment Weight (lb) Arm*(in) In the coat rack - without galley, with retainer 180 -110.0 - with galley 90 -102.5 On the rear tank 500 +44.5 On the folded back of the three-people divan 500 + 9.5 * Arm is taken from 25% MAC. Fuel Capacity (Average - Refer to weight and balan ce report of each individual airplane for exact capacity). U.S. Gallons Pounds Arm (in) USABLE FUEL in both wings 470.0 3,150 -7 in both fuselage tanks 412.0 2,762 +47 TOTAL USABLE 882.0 5,912 +18 UNUSABLE FUEL - Drainable unusable fuel in both wings 1.0 7 -7 in both fuselage tanks 3.5 24 -47 - Tank trapped fuel in both wings 1.0 7 -7 in both fuselage tanks - - - - Line trapped fuel 0.5 4 +50 - Engine trapped fuel 1.5 10 +55 TOTAL FUEL in both wings 472 3,164 -7 in both fuselage tanks 415.5 2,786 +47 in lines and engines 2.0 14 +54 TOTAL 889.5 5,964 +18 Pressure Fueling Maximum pressure for pr essure fueling is 50 psi. A33EU 4 Oil Capacity Usable, 0.5 U.S. gallon (at Arm + 75 in.) (each engine) Unusable, 2.25 U.S. gallon (at Arm + 75 in.) Maximum Operating Altitude 45,000 feet Control Surface Movements (Control Stops) Elevator Up 18 °30’(±10’) Down 12 ° (± 10’) Rudder Right 35 ° (± 10’) Left 35 ° (± 10’) Aileron Up 15 °30’ (+0°10’ -0°30’) Down 13 °30’(+0°10’-0°30’) Flaps Down 52 ° (±30’) Airbrakes Up 50 ° Wing slats Internal 20 ° (+30’ -0) External 31 °10’ (+30’ -0) Stabilizer: Electrical stops: Nose down 0 °14’ (±10’) Nose up 12 °16’ (±10’) Mechanical stops: Nose down (max) 0 °35’ Nose up (max) 12 °55’ Structural stops: Nose down (min) 1 ° Nose up (min) 13 °15’ Serial Numbers Eligible A French “Certificat de navi gabilite pour Exportation” endorsed as noted under “Import Requirements”, must be submitted for each i ndividual aircraft for which application for U.S. Certification is made. Import Requirements The FAA can issue a U.S. airwor thiness certificate based on an NAA Export Certificate of Airworthiness (Export C of A) signed by a representative of the Direction Générale de l'Aviation Civile (DGAC) of France 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 conform with Type Design approved under U.S. Type Certificate No. A33EU and to be in a condition for safe operation.’ Certification Basis FAR Part 25 dated February 1, 1964, including Amendment Nos. 25-1 through 25-20. FAR Part 36, including Amendment 36-1. FAA Special Conditions No. 25-49-EU-14, dated April 16, 1973. Type Certificate A33EU issued September 20, 1973. Date of Application for Type Certificate: June 18, 1969. The Direction Générale de l'Aviation Civile (DGAC) of France originally type certificated this aircraft under its type certificate Number 142. The FAA validated this product under U.S. Type Certificate Number A33EU. Effective September 28, 2003, the European Aviation Safety Agency (EASA) began oversight of this product on behalf of the Direction Générale de l'Aviation Civile (DGAC) of France. Equipment The basic required equipm ent as prescribed in the applicable airworthiness regulations (see Certification Basis) must be installe d on the aircraft for Certification. The equipment list for Falcon 10 contains lists of all equipment as well as optional equipment approved by Secretariat Gene ral a l’Aviation Civile (SGAC) of France. In addition, the following is required: (a) SGAC or FAA-approved Falcon 10 Airplane Flight Manual, approved October 17, 1973 (b) Nose wheel must be equipped with a chined tire. Service Information Each of the doc uments listed below that contain a statement that it is approved by the European Aviation Safety Agency (EASA) - or for approvals made before September 28, 2003 - by the Direction Générale de l'Aviation Civile (DGAC) of France, are accepted by the FAA and are considered FAA approved. Additionally, approvals issued by Dassault Aviation under the authority of EASA approved Design Organization EASA.21J.051 - or for approvals made before September 28, 2003 - under the authority of DGAC Design Organization Approval No. F.JA.03 are considered FAA approved. These approvals pertain to the type design only. • Dassault Aviation Service Bulletins, except as noted below, 5 A33EU • Structural repair manuals, • Vendor manuals referenced in Dassault Aviation service bulletins • Aircraft flight manuals, • Repair Instructions. Note: Design changes that are contained in Dassault Aviation Service Bulletins and that are classified as Level 1 Major in accordance with either the US/France or US/EASA Bilateral Aviation Safety Agreement Implementation Procedures for Airworthiness must be approved by the FAA. NOTES NOTE 1. Weight and Balance. a. Current weight and balance report, including list of equipment in certificated empty weight and loading instructions must be provided for each aircraft at delivery. b. The airplane must be loaded so that the CG is w ithin the specified limits at all times with the effect of fuel used and a movement of crew and pa ssengers from their assigned position being considered. c. The following must be included in the airplane empty weight: The total Unusable Fuel (52 lb.) listed unde r Fuel Capacity, plus unusable oil (36 lb. at +75 inches), plus hydraulic fluid (77 lb. at +45 inches). NOTE 2. Service Life Limits. Service life limits for airframe structural components wh ich are fatigue critical, if any, are listed in the FAA- approved Airplane Fli ght Manual for Falcon 10. NOTE 3. Airplane S/N 55 and subsequent , and prior serial numbers incorporating AMD/BA Modification No. 150 or Service Bulletin No. F10-0052, are eligible for ope ration at a maximum takeoff weight of 18,743 lbs. (8500 kg) in accordance with SGAC-approved Falcon 10 Airplane Flight Manual Revision No. 7 and at maximum zero fuel weight of 13,560 lbs (6150 kg) in accordance with DGAC-approved Falcon 10 Airplane Flight Manual Revision 10 on behalf of FAA. NOTE 4. Airplane S/N 212 and subsequent , and prior serial numbers incorporating AMD-BA Modification M151 or Service Bulletin No. F10-238, are eligible for opera tion with the following maximum weights, in accordance with DGAC-approved Falcon 10 Airplane Fli ght Manual Revision 23 on behalf of FAA. Maximum ramp 19,405 lb Maximum takeoff (brake release) 19,305 lb Maximum landing 17,640 lb Maximum zero fuel 14,420 lb Minimum flight weight 9,920 lb The associate CG range (gear extended) is then as follows: Forward limit % MAC Weight(lb) Takeoff En Route Landing Aft limit % MAC 9,920 16 14 14 31 13,230 16 14 14 31 15,720 16 16 16 31 17,640 21.8 21.8 21.8 31 19,305 26.6 26.6 31 19,405 27 31 NOTE 5. Airplanes incorporating AMD-BA Service Bulle tin No. F10-0082 are eligible for operation on unpaved runways in accordance with DGAC approved Falcon 10 Airplane Flight Manual Supplement No 1 and F10 Flight Manual Revision 9, on behalf of FAA. NOTE 6. Effective June 19, 1990 the name of AVI ONS MARCEL DASSAULT-BREGUET AVIATION changed to DASSAULT AVIATION. The new name will appear as of this date on all documents and nameplates. However, documents bearing the old name remain valid and will be updated when and where necessary. ...END...