# TCDS A40EU: Dassault Aviation - Type: Type certificate data sheet - Status: Historical - Holder: Dassault Aviation - Revision: 2 - Revised: March 2, 2010 - Product: Aircraft, Large Airplane - Certification basis: Part 21, Part 25, Part 36 - Data sheet PDF: https://openairdocs.org/files/sha256/16/7e/167e6ee6e80be052d1ad445751b89b2c5bd7d4d1d2231b4d53b1c6fddd4ccc01 - FAA DRS: https://drs.faa.gov/browse/excelExternalWindow/34484151C7D737A2862576E9004A4E87.0001 - Page: https://openairdocs.org/tcds/A40EU ## Models (1) As the data sheet lists them. - Mercure 100C (Falcon 100) ## What the data sheet says From the PDF's text layer, line by line; tables lose their columns. The PDF is the record. ```text Surrendered July 15, 2002 DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION A40EU Revision 2 DASSAULT AVIATION Mercure 100C March 2, 2010 TYPE CERTIFICATE DATA SHEET NO. A40EU This data sheet, which is a part of type certificate No. A 40EU prescribes conditions and lim itations under which the product fo r which the type certificate was issued meets the airworthiness requirements of the Federal Aviation Regulations. Type Certificate Holder DASSAULT AVIATION (Formerly known as AVIONS MA RCEL DASSAULT - BREGUET AVIATION) (1) This TC was surrendered for cancellation on July 15, 2002. Only standard airworthiness certificates issued prior to July 15, 2002 are valid. (2) Future unsafe conditions existing in the aircraft may result in the revocation of the airworthiness certificates of the aircraft if there is no entity to comply with 14 CFR § 21.99(a), “Required design changes.” (3) Replacement parts may not be available in the future. I - Model MERCURE 100C (Transport Aircraft), approved May 30, 1975. Engines 2 Pratt & Whitney JT 8D-15 turbofan engines. Fuel JP1 (MIL-J-5616 - ASTMD 1655) JP4 (MIL-T-5624) Fuels conforming with PW specification No. 522. Engine oil MIL-L-23699 - P&WA Turbojet Engine Service Bulletin No. 238 lists approved brand oils. Synthetic type conforming to P&WA Specification 521 as revised. Engine limits Takeoff static thrust standard day, sea level JT8D-15 conditions (5 min.), lb. 15,500 Maximum continuous static thrust, standard day, sea level conditions, lb. 13,750 Maximum permissible engi ne rotor operating speeds: low pressure compressor (N 1), rpm 8,800 high pressure compressor (N 2), rpm 12,250 Maximum permissible turb ine outlet gas temperature: Takeoff (5 min.) (620°C) 1148°F Maximum continuous (580°C) 1076°F Maximum for acceleration (2 min.) (630°C) 1166°F Starting (510°C) 950°F ground Maximum permissible oil inlet temperature: Continuous operation (130°C) 266°F Transient operation (is limited to (165°C) 329°F 15 min. above 130°C) Maximum permissible air bleed extraction: Percent of Primary Engine Airflow 1. High Pressure Bleed : Normal Emergency * (a) At 70% maximum continuous thrust and below 6.7 8.0 (b) From 70% maximum continuous thrust to maximum continuous thrust 3.5 5.5 (c) Above maximum continuous thrust 2.8 3.0 Maximum permissible air bleed extraction: Percent of Primary (cont'd) Engine Airflow N o r m a l Emergency * 2. Eight (8th) Stage Bleed : (a) At and below maximum con tinuous thrust 4.0 4.0 (b) Above maximum continous thrust 2.75 3.25 3. Low Pressure Bleed : (a) At 20% maximum continous thrust 5.0 5.0 (b) Below 20% maximum continous thrust 4.0 4.0 4. Fan Air Bleed : (a) At and below maximum con tinuous thrust 3.0 5.0 (b) Above maximum continous thrust 2.0 2.0 Thrust Setting: The appropriate thrust setting curve (APR or P t7), in the Airplane Flight Manual must be used for control of engine thrust. *Usable only when malfunction re quires and only until next landing. Airspeed limits Vmo/Mm o (Maximum Operating) 380 kts EAS/0.85 Mach. (whichever is lower) See FIGURE 1 Va (Maneuvering) 256 kts IAS at sea level (for altitude see FIGURE 1) Vfe (Flap Speeds): Deflection Speed Takeoff slats position and flaps de flection 0° to 12° 225 Kts IAS Landing slats position and fl aps deflection 25° 200 Kts IAS Landing slats position and fl aps deflection 37° 178 Kts IAS Vlo (Landing Gear Operation) Retract 200 Kts IAS Extend 250 Kts IAS Vle (Landing Gear Extended) 300 Kts IAS Mle .8 Mach Vllo (Landing Lights Operation) 225 Kts IAS Vlle (Landing Lights Extended) 225 Kts IAS Vabo (Airbrake Operation) Extended Vmo/Mmo Retracted Vmo/Mmo Vabe (Airbrake Extended) Vmo/Mmo Vmc (Minimum Control Speed) Vmca 99 Kts IAS Vmcg 108 Kts IAS 0 5 10 15 20 25 30 35 200 300 400 kiasV256 380 397 K 20000 ft 290 K 35000 ft MMO -. 8 5 VMO VA Altitude X1000 ft Maximum weights Ramp 54,500 Kg. 120,150 lb. Takeoff (brake release) 54,000 Kg. 119,048 lb. Landing 49,800 Kg. 109,789 lb. Zero fuel 46,000 Kg. 101,411 lb. Minimal 29,100 Kg. 64,154 lb. Fuel capacity (See NOTE 1 (c) for in formation relative to unusable fuel NOTE 2 (b) on use of fuel anti-icing additive and NOTE 2 (c) on use of fuel anti-static additive) The following data is given for full fuel tanks. Usable Fuel Arm Tank U.S. Gals. Liters Meters Inches Left Wing 1,637 6,200 - 0.173 - 6.8 Aft of Datum Right Wing 1,629 6,168 - 0.173 - 6.8 Aft of Datum Center Wing 1,585 6,050 +1. 270 +50.0 Fwd of Datum Total 4,851 18,418 Oil capacity Engine tank oil is the engine oil that is required for circulation in the system. Volume Arm Location U.S. Gals Meters Inches Left engine 4.0 + 2.97 + 116.9 Right engine 4.0 + 2.97 + 116.9 Total 8.0 Stabilizer movements Nose-Down Nose-Up Electrical stops + 1° - 11 ° Mechanical stops + 1° 30' - 11 ° 30' Cruise limit, droop L.E., retracted idem - 4° 30' Control surface Left and right elevator Up - 20° Down + 15° movements Lower and higher rudder Left - 22° Right + 22° Aileron Up - 25° Down + 25° Flaps (total) Down 37° Maximal Movements Flight spoilers Airbrakes Ground Spoilers Spoilers No. 1, 2, and 3 (right and left) 25° 35° 45° Airbrakes No. 1 and 2 (right and left) 25° 32° 30' Wing droop leading edges down : 17°48' internal slats No. 1 (right and left) 30°25' external slats No. 2 and 3 For detail rigging and toleran ces consult Maintenance Manual. C.G. range Weight/C.G. Envelope (Gear down) - FIGURE 2 - 30 40 50 60 10 15 20 25 30 35 132.2 Weight X 1000 lb.Weight X1 0 0 0k g 110.2 16.0 16.0 32.0 Taxi 33.026.0 66.1 11.5 88.2 Z.F.W. Flight and landing Takeoff C.G. location (% AMC) The airplane is normally weighed with wing flaps retracted, landing gear extended and thrust reversers retracted. - Gear retraction moment is - 175 mKg/1265 ft-lb (moves CG forward) - Flaps extension moment is + 40 mKg/1013 ft-lb (flaps 37°) (moves CG rearward) - Reversers extension moment is + 20 mKg/1447 ft-lb (moves CG rearward) Forward Limit % MAC Aft Limit % MAC Weight -1000 Kg Flight Zero Fuel Flight and Landing Takeoff 29.1 11.5 12 33 26 ) linear 40 11.5 12 33 33 ) variation between these points 43.2 11.5 12 33 33 46 11.5 16 33 ) linear 33 ) linear 49 11.5 ) For ) variation ) variation 51.5 13 ) variation ) between ) between 53 14.6 ) see ) these ) these 54 16 ) figure 2. 32 ) points 32 ) points Ramp 54.5 - Forward Limit 16% - Aft Limit 32% Datum Datum (origin of moments) is located at 25% of MAC and placards on the keel at fuselage main frame No. 30. Mean Aerodynamic 4,315 meters/169.9 inches (leading edge at 1.079 meters/42.5 inches forward of datum). Chord Leveling means A leveling facility is provided in the left ma in landing gear well. It features a support, a plumb line and sliding rod system designed to record the airplane longitudinal and lateral attitude. The airplane is leveled when the end of plumb lin e reads the zero on the sliding rod with the pointer of this sliding rod sets on the zero marking on the fi xed rod. This item of equipment is part of the airplane flyaway kit. NOTE : A means for airplane quick leveling but less accurate with two spirit levels is installed on cockpit wall at the crew side: one spirit level in longitudinal plane and the other in lateral plane. Minimum crew Pilot and Copilot. Maximum passengers 162 in accordance with Arrangement General Specifications AMD/BA D 113 and Emergency Evacuation Demonstration per FAR 25. 179 in accordance with emergency exits configuration. Maximum operating altitude The maximum operating altitude is 35,000 ft. Other operating See approve d Airplane Flight Manual. limitations Main cabin load Fuselage floor - Maximum Running Load 800 kg/m (44.8 lb/in) limitations Maximum Loading 375 kg/m² (76.8 lb/sq.ft) Passenger cabin floor extends into the fuse lage between frame No. 9 and frame No. 55. Lower Holds : Maximum Running Load Maximum Distributed Load Intensity Max Total Holds Fitted Cargo Kg/m lb/in Unfitted Cargo Kg/m lb/in Fitted Cargo Kg/m2 lb/ft2 Unfitted Cargo Kg/m2 lb/ft2 Load Kg / Lb Forward lower deck cargo hold 1 840 47.0 660 37.0 735 150.6 580 118.8 3,625 7,992 Aft lower deck cargo hold 3 840 47.0 660 37.0 735 150.6 580 118.8 2,900 6,393 4 630 35.3 630 35.3 600 122.9 600 122.9 1,800 3,968 Equipment The basic required equipm ent as prescribed in the applicable airworthiness regulations (see Certification Basis) must be insta lled in the aircraft for certification. The Equipment List for Mercure Doc. DGT 11 1211 contains list of all required equipment. DGT 11 1222 contains list of optional equipment a pproved by Secretariat General a l'Aviation Civil (SGAC) of France. In addition, the following is required: - MERCURE 100C Airplane Fli ght Manual SGAC-approved May 21, 1975. - Stall Warning System - Ref. AMD-BA-DED 062-115-04. Service information All Model MERCURE 100C Servi ce Bulletins published by Avions Marcel DASSAULT- BREGUET AVIATION (AMD/BA) will be S.G.A.C. ap proved, and will carry a statement to that effect. This statement may be interpreted, as "FAA APPROVED". Service Bulletins that are the subject matter of a French "Consigne de Navigab ilite" (Airworthiness Directive) will be so stated on the Bulletin. Maintenance Manual (which include s information essential to the proper maintenance of the aircraft and retirement times of parts with a predetermined service life). Other available service documents for Model MERCURE 100C are as follows: - Illustrated Parts Catalog - Wiring Diagram Manual, and - Structural Repair Manual. Certification basis FAR 25, Amendments 25-1 through 25-18 and Special Conditions No. 25-51-EU-15 issued on April 20, 1973. Date of Application for Type Certificate : October 25, 1968. Type Certificate No. A40EU issued May 30, 1975. Compliance with the following optional requirement s has been established: FAR 25, 25-20, 25-21, 25-22, portions of 25-23, 25-28, 25-32 as described in "Reglements de Certification de Type FAA de l'avion Dassault MERCURE 100C" Attach ment to SGAC letter dated May 26, 1975. - Ditching Provisions 25.801 (Overwater opera tion can be approved when the aircraft has been equipped and installation has been approved according to FAR 25.801). - Ice Protection Provisions 25.1419 (and Fren ch regulation STAe/Ab 36998 of June 20, 1968 for Mercure). Compliance has been shown with FAR 36.201 (c) (1) effective December 1, 1969. SFAR 27. Equivalent safeties found, in lieu of complian ce, with respect to the following requirements: - FAR 25.173(c) - Static longitudinal stability (Speed free return - stick force gradient) - FAR 25.777(e) - Cockpit controls Distance between wing flap control and landing gear control) Import requirements An FAA Sta ndard Airworthiness Certificate may be issued on the basis of a French "Certificat de Navigabilite pour Exportation" signed by a repres entative of the Secretariat General a l'Aviation Civile (S.G.A.C.) of France, containing the following statement: "The airplane covered by this certificate has been found to comply with Fr ench Airworthiness Regulations and conforms to Type Certificate No. A40EU." Serial Numbers eligible A French "Certificat de Navi gabilite pour Exportation" endorsed as noted under "Import Requirements" must be submitted for each indivi dual aircraft for which application for U.S. certification is made. NOTE 1. (a) Current weight and balance report, including loadi ng instructions and list of equipment in certificated empty weight, must be provided for each aircraft at the time of original certification. (b) The aircraft must be loaded in accordance with prescribed methods which conform with the overall loading instructions given in th e MERCURE Weight and Balance manual. (c) The "drainable unusable fuel" is that amount of fuel in the tank which is unavailable to the engine under critical flight conditions as defined in FAR 25.959. This drainable unusable fuel does not include the "tank trapped fuel" or "line unusable fuel" which is the unusable fuel retained in the fuel feed lines. The "total unusable fuel" and line unusable fuel must be included in the airplane empty weight or be suitably accounted for in the airplane weight and balance document. The volume weight and moments of the unusable fuel are listed in the following table: UNUSABLE FUEL QUANTITIES Drainable Trapped Location Volume li./qts. Weight kg / lb Arm m / in Moment m-kg/ft-lb Volume li. / qts. Weight kg / lb Arm m / in Moment m-kg/ft-lb Left wing + 27.4 20.8 +1.4 - 29.1 32 25.6 + 1.2 - 30.7 Right wing 26 (45.8) (55.1) -210.5 33.8 (56.4) 47.2 -222.1 Lines 12 9.6 + 0.6 12.7 (21.2) 23.6 - 5.9 Total 26 20.8 + 1.4 - 29.1 44 35.2 + 0.93 - 36.6 27.4 (45.8) (55.1) -210.5 46.5 (77.6) 36.6 -264.7 Center wing 5 4 + 0.2 - 0.8 5 4 + 0.1 - 0.4 5.3 (8.8) (7.9) - 5.9 5.3 ( 8.8) 3.9 - 2.9 Total 31 24.8 + 1.21 - 29.9 49 39.4 + 0.93 - 37 32.8 (54.7) (47.6) -216.3 51.8 (86.9) 36.3 -267.6 (d) Engine System Oil is the total engine oil less the quantity drainable from the tank. Location Volume li. / qts. Weight kg / lb Arm m / in. Moment m-kg / ft-lb Left engine 4.73 / 5.0 4.45 / 9. 8 +2.97 / 116.9 13.2 / 95.5 Right engine 4.73 / 5.0 4.45 / 9. 8 +2.97 / 116.9 13.2 / 95.5 * Total 9.46 /10.0 8.90/19.6 +2.97 / 116.9 26.4 / 191.0 * 1.25 gallons of residual oil in each engine is incl uded in the engine weight and is not in the engine oil values given above. (e) The maximum allowable lateral unbalance fuel for taxi, takeoff, ground roll and landing is 1000 kg. (2.205 lb) NOTE 2. (a) JP1 and JP4 fuels conforming to P&WA Specifications No. 522 and later revisions may be used separately or mixed in any proportions without adversely affecting the engine operation or power output. No fuel control adjustment is required when switching fuel types. (b) Phillips anti-icing fuel additive PFA-55MB may be used if concentration delivered to airplane does not exceed 0.15% by volume. No fuel system anti-icing credit is allowed. (c) Shell ASA 3 antistatic additive may be used at a concentration up to 0.0001% by volume (1 mg per liter) NOTE 3. The aircraft must be operated in accordance with the limitations presented in the MERCURE 100C Airplane Flight Manual approved by the Secretariat Gene ral a l'Aviation Civile (S.G.A.C.) of France. NOTE 4. Service Life Limits: Airplane components which are lif e limited are listed in the SGAC approved portion of Chapter 5 of the MERCURE Maintenance Manual (Section 5-40.00) and must be replaced as indicated therein. .....END..... ``` ## ADs (1, in force first) - [AD 79-18-12](https://openairdocs.org/ad/79-18-12): Auxiliary Power Units · Airbus BAC 1-11 200 Series, BAC 1-11 400 Series, Manufacturing Company Auxiliary Power Units and 46 more. 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