TCDS A46EU

Page No. 1 2 3 4 5 6 7 8 9 10 11 12 13 14 15 16 17 18 Rev. No. 23 8 10 13 13 24 9 10 10 12 9 10 22 22 14 20 24 20 Page No. 19 20 21 22 23 24 Rev. No. 21 23 23 22 22 22 DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION A46EU Revision 24 DASSAULT AVIATION MYSTERE-FALCON 50 MYSTERE-FALCON 900 FALCON 900EX September 5, 2026 TYPE CERTIFICATE DATA SHEET No. A46EU This data sheet which is part of Type Certificate No. A46EU 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 8) 9 Rond Point des Champs Elysees 75008 Paris France The U.S. airworthiness certification basis for aircraft type certificated under FAR Section 21.29 and exported by the country of manufacture is FAR Sections 21.183(c) or 21.185(c). The U.S. airworthiness certification basis for aircraft type certificated under FAR Section 21.29 exported from countries other than the country of manufacture (e.g. third party country) is FAR 21.183(d) or 21.185(b). Notwithstanding that the FAR referenced in the above paragraph does not specifically address or require a foreign civil airworthiness authority certification, such certification is the only practical way for an applicant to show, and the Federal Aviation Administration (FAA) to find conformity to the FAA -approved type design and conditions for safe operation. Additional guidance is contained in FAA Advisory Circular 21-23, Airworthiness Certification of Civil Aircraft, Engines, Propellers, and Related Products Imported into the United States. I. Model MYSTERE-FALCON 50 (Transport Category Airplane), approved March 7, 1979. (a) Basic Model Definition Engines. 3 engines - Allied Signal Engines, Model TFE 731-3-1C (see Note 3b). Engine Limits. Static, Standard Sea level Takeoff (5 min) lb 3,700 Maximum Continuous lb 3,700 Maximum normal operating rotor speeds Low pressure rotor (N1) RPM 21,000 percent 101.5% High pressure rotor (N2) RPM 29,692 percent 100% Transient Conditions* 1 Minute 5 Seconds Low pressure rotor (N1) 101.5% to 103% 103% to 105% High pressure rotor (N2) 100% to 103% 103% to 105% *(See NOTE 7) Interstage turbine temperature (ITT): During starting 907ºC (1,665ºF) A46EU 2 of 24 Rev. 24 Starting (10 sec. transient) 927ºC (1,700ºF)* Takeoff (5 minutes) 907ºC (1,665ºF) Takeoff (10 sec. transient) 939ºC (1,722ºF) Maximum Continuous 885ºC (1,625ºF) *(See NOTE 7) Oil temperature at fan gearbox inlet: Maximum (sea level to 30,000 ft) 127ºC (260ºF) Maximum (above 30,000 ft) 140ºC (284ºF) Maximum (2 minutes transient) 149ºC (300ºF) Minimum Continuous 30ºC ( 86ºF) Fuel Pressure Minimum fuel pressure warning, psig 4.5 Oil pressure limits: At idle, psig 25 to 46 Takeoff & maximum continuous, psig 38 to 46 APU (optional). Allied Signal Engines GTCP 36-100(A) (See NOTE 6) Limitation - Not operable in flight RATED MAX. ALLOWABLE EGT 680ºC 732ºC RP 100% 109% Fuel: See NOTE 4, and Airplane Flight Manual Oil: See NOTE 5b, and GTCP 36-100 Maintenance Manual. Airspeed Limits (IAS). Unless otherwise indicated, speeds are indicated airspeeds. VMO (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 24,000 ft. MMO (Maximum Operating) M = 0.86 above 24,000 ft. VA (Maneuvering) 210 kts VFE (Slat and Flap Speeds) Slats 200 kts Slats + flaps 20º 190 kts Slats + flaps 48º 175 kts VLO (Landing Gear Operation) 190 kts MLO 0.70 VLE (Landing Gear Extended) 220 kts MLE 0.75 Windshield Wiper Operation 205 kts Cockpit Window Opening 180 kts VMC (Minimum Control Speed) In flight 82.5 kts (CAS) On ground 87.5 kts (CAS) C.G. Range. Weight (lb) Forward Limit (% MAC) Aft Limit (% MAC) (Gear Extended) 38,800 22.3 32 35,715 19.8 32 30,203 14 32 18,959 14 32 For aircraft incorporating AMD-BA Modification 1230 (Falcon 50 Service Bulletin Number 161), C.G. Range is modified as follows: Weight (lb) Forward Limit (% MAC) Aft Limit (% MAC) A46EU 3 of 24 Rev. 24 40,780 23.3 29.6 40,255 22.8 32 35,715 19.2 32 30,640 14 32 18,959 14 32 For aircraft incorporating AMD-BA Modification 1430 (Falcon 50 Service Bulletin Number 191), C.G. Range is modified as follows: Weight (lb) Forward Limit (% MAC) Aft Limit (% MAC) 40,780 20.9 29.6 40,255 20.6 32.0 35,715 17.3 32.0 32,624 14.0 32.0 18,959 14.0 32.0 Gear retraction has negligible effect on C.G. Range. Datum. Datum is 25% of mean aerodynamic chord (MAC) which is marked on aircraft and coincides with fuselage Station (FS) + 382.83 inches. (Fuselage Station + 0 is the forward end of the aircraft nose cone). Mean Aerodynamic Chord. Length 111.77 in. Zero % MAC is at FS + 354.89 in. Leveling Means. A bubble-type level, when placed on a special leveling rule which in turn is placed on the tops of 3 specific leveling pins on the floor of the fuselage rear compartment, facilitates leveling of the airplane in the longitudinal and lateral directions. Weight Limitations. Maximum Weights Maximum ramp 38,800 lb. Maximum takeoff (brake release) 38,800 lb. Maximum landing 35,715 lb. Maximum zero fuel 25,570 lb. Minimum weight 18,959 lb. For aircraft incorporating AMD-BA Modification 1230 or modification 1430 (Falcon 50 Service Bulletin Number 161 or 191), weight limitations are modified as follows: Maximum ramp 40,780 lb. Maximum takeoff (brake release) 40,780 lb. Maximum landing 35,715 lb. Maximum zero fuel 25,570 lb. Minimum weight 18,959 lb. Maximum Passengers. 19 maximum - limited by emergency exit requirement of FAR 25.807(c) (AMD memo DTM 800 identifies approved cabin interior for 8 or 9 passenger seats). 12 maximum - limited by cabin air ventilation requirements of FAR 25.831 when operated above 45,000 feet (AMD Falcon 50 Service Bulletin No. F50-0163 is applied (or AMD Mod. M17). 0 - Without passenger provision but incorporating Dassault Ferry flight configuration : M2133. Crew Seats. Third crew seat, installed in accordance with Option No. 25-11-02, may be occupied for takeoff and landing. Maximum Baggage. 2,200 lb in rear baggage compartment. Fuel Capacity. Nominal - (refer to weight and balance report of each individual airplane for exact capacity). A46EU 4 of 24 Rev. 24 Usable Fuel US Gallons Pounds Arm (in) Left wing 559 3,748 -0.94 Center wing 410 2,749 -38.82 Right wing 559 3,748 -0.94 Left fuselage 210 1,404 +51.3 Center fuselage 367 2,461 +51.85 Right fuselage 210 1,404 +51.3 TOTAL USABLE 2,315 15,514 TOTAL FUEL 2,329 15,607 Pressure Fueling 50 psi maximum. Oil Capacity. Usable, 0.5 US Gallons (Each Engine) Unusable, 2.25 US Gallons (drainable, and trapped oil) side engine arm + 80.9 in., center engine arm + 225.8 in. Maximum Operating Altitude. 45,000 ft. 49,000 ft. for serial No. 156 and on, or for aircraft incorporating AMD-BA Modification M17 (Falcon 50 Service Bulletin Number F50-0163). Control Surface Movements. Elevator: Down 16º Up 20º (Control stops) Rudder: Right 23º Left 23º Aileron: Up 25º20' Down 24º50' Flaps: Down 48º Airbrakes: Up 68º Wing Slats: internal 20º external 30º Stabilizer: Electrical stops: Nose down 1º Nose up 11º Mechanical stops:Nose down (max) 1º30' Nose up (max) 11º30' Structural stops: Nose down (min) 2º Nose up (min) 12º Rigging tolerances are included in Maintenance Manual. (b) Falcon 50EX Definition EX designation for Mystère Falcon 50 does not correspond to a model designation. This is only a commercial designation for airplanes on which 6 Major modifications are embodied. Those 6 modifications, listed below, are basic on any aircraft from serial number 253 and subsequent. M1200: Increase of rudder control authority M1810: new engines - assembly line configuration - TFE 731-40 M1890: new avionics M1939: new engine control EIED M1940: Bleed Air System Computer M2159: ADC new calibration The following associated retrofit modifications are available: M2017: New engines – retrofit – TFE 731-40-1C M1924: New avionics – retrofit Other modifications, as retrofit, have the same modification numbers as for new build aircraft. Engines. 3 engines - Allied Signal Engines, Model TFE 731-40 (FAA Data Sheet EINM-1 July 13, 1995) Engine Limits. Static, Standard Sea level Takeoff (5 min) lb 3,700 Maximum Continuous lb 3,700 A46EU 5 of 24 Rev. 24 Maximum normal operating rotor speeds Low pressure rotor (N1) RPM 21,021 percent 100.1% High pressure rotor (N2) RPM 31,485 percent 101% Transient Conditions* 5 Seconds Low pressure rotor (N1) 100.5% High pressure rotor (N2) 102.5 *(See NOTE 7) Interstage turbine temperature (ITT): During starting 991ºC (1,815ºF) Takeoff (5 minutes) 1013ºC (1,855ºF) Maximum Continuous 991ºC (1,815ºF) Oil temperature at fan gearbox inlet: Maximum (sea level to 30,000 ft) 127ºC (261ºF) Maximum (above 30,000 ft) 140ºC (284ºF) Maximum (2 minutes transient) 149ºC (300ºF) Minimum Continuous 40ºC ( 104ºF) Fuel Pressure Minimum fuel pressure warning, psig 4.5 Oil pressure limits: At idle, psig 50 to 80 Takeoff & maximum continuous, psig 65 to 80 APU (basic). Unchanged. Included as basic equipment on serial number 253 and subsequent. Airspeed Limits (IAS). Unchanged C.G. Range. Weight (lb) Forward Limit (% MAC) Aft Limit (% MAC) (Gear Extended) 39,700 22.96 32 30,179 14 32 18,959 14 32 After incorporation of Falcon 50 Service Bulletin Number 161, C.G. Range is modified as follows: Weight (lb) Forward Limit (% MAC) Aft Limit (% MAC) (Gear Extended) 40,785 23.3 29.57 40,300 22.99 32 30,618 14 32 18,959 14 32 Datum. Unchanged Mean Aerodynamic Chord. Unchanged Leveling Means. Unchanged Weight Limitations. Maximum Weights Maximum ramp 39,700 lb. Maximum takeoff (brake release) 39,700 lb. Weight Limitation (cont’d) Maximum landing 35,715 lb.(unchanged) Maximum zero fuel 25,570 lb.(unchanged) Minimum weight 18,959 lb.(unchanged) After incorporation of Falcon 50 Service Bulletin Number 161, weight limitations are modified as follows: Maximum ramp 40,785 lb.(unchanged) A46EU 6 of 24 Rev. 24 Maximum takeoff (brake release) 40,785 lb.(unchanged) Maximum landing 35,715 lb. (unchanged) Maximum zero fuel 25,570 lb. (unchanged) Minimum weight 18,959 lb. (unchanged) Maximum Passengers. Unchanged, except Ferry kit definition and installation (0 passenger provisions) is covered by Dassault modification M2133 Crew Seats. Unchanged Maximum Baggage. Unchanged Fuel Capacity. Unchanged Oil Capacity. Usable, 1.01 US Gallons (Each Engine) Unusable, 0.31 US Gallons Maximum Operating Altitude. Unchanged Control Surface Movements. Unchanged ,except Rudder (M1200): Right 29º Left 29º II. Model MYSTERE-FALCON 900 (Transport Category Airplane), approved March 21, 1986. (a) Basic Model Definition Engines. 3 engines - Allied Signal Engines, Model TFE 731-5AR-1C (See NOTE 3b). MF900 aircraft incorporating M1200 and M1548 (Service Bulletin F900-100) are equipped with 3 engines Allied Signal Engines, Model TFE 731-5BR-1C. Commercial name of Myatere-Falcon 900 airplanses fitted with M1200 and M1548 modificatiions is F900B. Engine Limits. A/C without SB100 A/C with SB100 Static, Standard Sea Level Takeoff (5 min.) lb 4,500 lb 4,750 Maximum continuous lb 4,500 lb 4,634 Maximum normal operating rotor speeds Low pressure rotor (N1) RPM 21,000 RPM 100% High pressure rotor (N2) RPM 29,989 RPM 101% 30,540 RPM 100.8% Transient Conditions* 5 seconds Low pressure rotor (N1) 100% to 103% High pressure rotor (N2) 101% to 103% 100.8% to 103% * (See NOTE 7) A46EU 7 of 24 Rev. 24 Interstage turbine temperature (ITT): During starting 952ºC (1,746ºF) 978ºC (1,793ºF) Starting (10 sec. transient) 974ºC (1,785ºF)* 996ºC (1,825ºF) Takeoff (5 minutes) 974ºC (1,785ºF) 996ºC (1,825ºF) (5 sec. transient) 984ºC (1,803ºF) 1006ºC (1,842ºF) (2 sec. transient) 994ºC (1,821ºF) 1016ºC (1,861ºF) Maximum continuous 924ºC (1,696ºF) 968ºC (1,775ºF) * (See NOTE 7) Oil temperature at fan gearbox inlet: Maximum (sea level to 30,000 ft) 127ºC (260ºF) Maximum (Above 30,000 ft) 140ºC (284ºF) Maximum transient (2 minutes) 149ºC (300ºF) Minimum Continuous 30ºC ( 86ºF) Fuel pressure: Minimum fuel pressure warning psig 4.5 Oil pressure limits: At idle, psig psig 25 to 46 Takeoff and maximum continuous psig 38 to 46 APU. Allied Signal Engines Model GTCP 36-150(F) Limitation - Not operable in flight RATED MAX. ALLOWABLE EGT 720ºC 973ºC RPM 102% 110% Fuel : See NOTE 4, and Airplane Flight Manual Oil : See NOTE 5b. Airspeed Limits. Unless otherwise indicated, speeds are indicated airspeeds. VMO (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. MMO (Maximum Operating) - Weight below 35,000 lbs. M = 0.87 from 25,000 ft. to 38,000 ft. 0.87 at 38,000 ft. to 0.84 at 42,000 ft., with straight line variation between other points. 0.84 above 42,000 ft. - Weight above 35,000 lbs. M = 0.87 from 25,000 ft. to 33,000 ft. 0.87 at 33,000 ft. to 0.84 at 37,000 ft. with straight line variations between those points. 0.84 above 37,000 ft. A46EU 8 of 24 Rev. 24 Aircraft Aircraft Without SB100 With SB100 VA (Maneuvering) VFE (Slat and Flap Speeds) Flaps 7º + Slats Flaps 20º + Slats Flaps 40º + Slats VLO (Landing Gear Operation) MLO VLE (Landing Gear Extended) MLE Windshield Wiper Operation Cockpit Window Opening VMC (Minimum Control Speed) In flight On ground 228 kts 200 kts 190 kts 180 kts 190 kts 0.70 245 kts 0.75 215 kts 215 kts 83 kts (CAS) 85.3 kts (CAS) 83.6 kts (CAS) 86 kts (CAS) C.G. Range. Weight (lb) Forward Limit (% MAC) Aft (Gear Extended) 45,500 14 31 42,000 14 31 20,700 14 31 For aircraft incorporating Modification 1196, C.G. range is modified as follows: Weight (lb) Forward Limit (% MAC) Aft Limit (% MAC) 20,700 14 31 42,000 14 31 46,500 14 31 Gear retraction has negligible effect on C.G. Range. Datum. Datum is 25% of mean aerodynamic chord (MAC) which is marked on aircraft and coincides with fuselage Station (FS) + 420.43 inches. (Fuselage Station + 0 is the forward end of the aircraft nose cone). Datum is marked on fuselage of A/C S/N's 1 through 11 only. Mean Aerodynamic Chord. Length 113.69 in. Zero % MAC is at FS + 392 in. Leveling Means. Standard bubble-type level to be installed on the passengers seats tracks. Weight Limitations. Maximum Weights Maximum ramp 45,700 lb Maximum takeoff (brake release) 45,500 lb Maximum landing 42,000 lb Maximum zero fuel 28,220 lb Minimum weight 20,700 lb For aircraft incorporating DASSAULT Modification 1196, Weight limitations are modified as follows: Maximum ramp 46,700 lb Maximum takeoff 46,500 lb Maximum landing 42,000 lb Maximum zero fuel 30,865 lb Minimum weight 20,700 lb A46EU 9 of 24 Rev. 24 Maximum Passengers. 19 maximum - limited by emergency exit requirement of FAR 25.807(c) (AMD memo (See Note 9) DTM 20164 identifies approved cabin interior for 12 passenger seats). Ferry flight configuration (0 passenger provisions) is defined by Dassault modification M3115 Crew Seats. The optional third crew seat may be occupied for takeoff and landing. Maximum Baggage. 2,866 lb in rear baggage compartment. Fuel Capacity. Nominal - (refer to weight and balance report of each individual airplane for exact capacity). Usable Fuel US Gallons Pounds Arm (in) wing and center wing, LH 904 6,058 -12.1 wing and center wing, RH 904 6,058 -12.1 Forward and aft fuselage 1,037 6,949 -28.2 TOTAL USABLE FUEL 2,845 19,065 TOTAL FUEL 2,863 19,184 Pressure Fueling 50 psi maximum. Oil Capacity. Usable, 0.375 US Gallons (Each Engine) Unusable, 2.86 US Gallons (drainable, and trapped oil) side engine arm + 136.7 in., center engine arm + 272.5 in. Maximum Operating Altitude. 51,000 ft. Control Surface Movements. Elevator: down 16º up 20º (Control Stops) Rudder: right 29º left 29º Aileron: up 25º20' down 24º50' Flaps: down 40º Airbrakes: up 68º Wing Slats: internal 20º external 30º Stabilizer: Electrical stops: Nose down 2º Nose up 10º Mechanical stops:Nose down (max) 2º30' Nose up (max) 10º30' Structural stops: Nose down (min) 2º40' Nose up (min) 11º Rigging tolerances are included in Maintenance Manual. (b) Falcon 900C Definition The 900C designation for the Mystere-Falcon 900 does not correspond to a model designation. It is only a commercial designation for Mystere-Falcon 900 airplanes on which one of the following major modifications are incorporated: M1975: Avionics upgrade - production M2695: Avionics upgrade – retrofit The M1975 and M2695 modifications consists of a complete upgrade of the basic Mystere-Falcon 900 avionics, by installation of a variant of the Honeywell Primus 2000 suite. M1975 is basic on all Mystere-Falcon 900 aircraft produced from serial number 179 and subsequent. All parameters listed in the preceding sub-section (a) for the basic Mystere-Falcon 900 remain valid for airplanes which incorporate M1975 or M2695. III. Model FALCON 900EX (Transport Category Airplane), approved July 19, 1996. A46EU 10 of 24 Rev. 24 (a) Basic Model Definition The Falcon 900EX is defined by Dassault modification M3000 and differs from the Mystere-Falcon 900 in the following major respects: (i) Allied Signal Engines TFE 731-60 replace TFE 731-5AR-1C or TFE 731-5BR-1C engines; (ii) A new aft fuel tank is added, and the forward central fuel tank is increased in capacity; (iii) The instrument panel is changed by the installation of a new avionics suite, including Honeywell Primus 2000 five tube EFIS including autothrottle; (iv) bleed air system is modified by the addition of a Bleed Air System Computer (BASC) and modification of HP flow control; (v) relocation of electrical system components, and use of Falcon 2000 type electrical wires; (vi) an increase in maximum weights. Engines. 3 engines - Allied Signal Engines TFE 731-60-1C (See Note 3b). Engine Limits. Static, Standard Sea Level Takeoff (5 min.) lb 5,000 Maximum Continuous lb 4,525 Maximum normal operating rotor speeds: Low pressure rotor (N1) rpm 21,000 percent 100% High pressure rotor (N2) rpm 31,485 percent 100% Transient conditions*: 1 second Low pressure rotor (N1) 100% to 100.5% High pressure rotor (N2) 100% to 101.5% * (See Note 7) Interstage Turbine Temperature (ITT): During starting 994C (1,821F) Takeoff (5 minutes) 1022C (1,872F) (10 sec. Transient*) 1032C (1,890F) Maximum Continuous 991C (1,816F) * (See Note 7) Oil temperature at fan gearbox inlet: Maximum: - Sea level to 30,000 ft 127C (260F) - Above 30,000 ft 140C (284F) Maximum transient (2 minutes) 149C (300F) Minimum Continuous 30C (86F) Fuel pressure: Minimum fuel pressure warning psig 4.5 Oil pressure limits: At idle psig 50 to 80 Takeoff and maximum continuous psig 65 to 80 Transient (3 minutes maximum) psig 100 APU. Allied Signal Engines GTCP 36-150(F) Limitation - Not operable in flight Rated Max.allowable EGT 720C 973C RPM 102% 110% Fuel: See NOTE 4, and Airplane Flight Manual Oil: See NOTE 5b Airspeed Limits. Unless otherwise indicated, speeds are indicated airspeeds. VMO (Maximum operating) Sea level 350 kt 10,000 ft 370 kt (linear variation from 0 to 10,000 ft) A46EU 11 of 24 Rev. 24 From 10,000 to 25,000 ft 370 kt MMO (Weight lower than 35,000 lb) From 25,000 to 38,000 ft Mach 0.87 From 38,000 to 42,000 ft Linear Variation from Mach 0.87 to 0.84 Above 42,000 ft Mach 0.84 MMO (Weight above 35,000 lb) From 25,000 to 33,000 ft Mach 0.87 From 33,000 to 37,000 ft Linear Variation from Mach 0.87 to 0.84 Above 37,000 ft Mach 0.84 VA (Maneuvering) 228 kt VFE (Slat and flaps speeds) flaps 7 + slats 200 kt flaps 20 + slats 190 kt flaps 40 + slats 180 kt Landing gear operation VLO 190 kt MLO Mach 0.70 Landing gear extended VLE 245 kt MLE Mach 0.75 Windshield wiper operation 215 kt Cockpit window opening 215 kt Minimum control speed In flight: VMCA 85.2 kt (CAS) On ground: VMCG 88.9 kt (CAS) Weight Limits & CG Range. Without M3020 (SB N 1) Weight Forward CG limit Rear CG limit kg lb % CMA % CMA Minimum weight Maximum zero fuel weight Maximum landing weight Maximum weight for 31% rear limit Maximum takeoff weight Maximum ramp weight 9 390 14 000 19 051 21 228 21 908 22 000 20 700 30 864 42 000 46 800 48 300 48 500 14 14 14 14 14 14 31 31 31 31 24,20 23,45 With M3020 (SB N 1) Weight Forward CG limit Rear CG limit kg lb % CMA % CMA Minimum weight Maximum zero fuel weight Maximum landing weight Maximum weight for 31% rear limit Maximum takeoff weight Maximum ramp weight 9 390 14 000 20 185 21 228 22 226 22 317 20 700 30 864 44 500 46 800 49 000 49 200 13 13 13 13 13 13 31 31 31 31 21,35 20,50 Datum. Datum is 25% of mean aerodynamic chord (MAC) and coincides with fuselage station +420.43 inches (Fuselage station +0 is the forward end of the aircraft nose cone). 13% MAC is 13.66 inches forward of the reference 14% MAC is 12.52 inches forward of the reference 31% MAC is 6.81 inches rear of the reference. A46EU 12 of 24 Rev. 24 Mean Aerodynamic Chord. Length 113.69 inches Zero % MAC is at FS + 392 inches Leveling Means. Standard bubble type level to be installed on the passengers seats tracks. Maximum Passengers. 19 maximum. (See Note 9) Ferry flight configuration (0 passenger provisions) is defined by Dassault modification