TCDS 7A6

Page No. 1 2 3 4 5 6 7 Rev. No. 7 - - - - - 7 Surrendered October 27, 2009 FEDERAL AVIATION AGENCY 7A6 Revision 8 SUD AVIATION Caravelle SE 210 Model I Model III Model VIR November 24, 2009 TYPE CERTIFICATE DATA SHEET NO. 7A6 This data sheet which is a part of type certificate No. 7A 6 prescribes conditions and limita tions under which the product for which the type certificate was issued meets the airworthiness requirements of the Civil Air Regulations. Type Certificate Holder SUD AVIATION (1) This TC was surrendered for cancellation on October 27, 2009. Only standard airworthiness certificates issued prior to October 27, 2009 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 - SUD AVIATION Caravelle SE 210 Model I (T ransport Category), approved April 8, 1959 Engines 2 Rolls-Royce Avon 522 turbojets Fuel French: TRO (AIR 3405) British: Aviation Kerose ne D.Eng. RD 2482 (AVTUR) or D.Eng. RD 2494 (AVTUR/50) American: JP-1 (MIL-F-5616) Canadian: 3-GP-23B Oil British: D.Eng. RD 2487 American: ESSO Aviation Turbo oil 35 Engine limits Static Sea Level Ratings Rating Minimum Thrust (lb.) Maximum R.P.M. Max. Turbine Gas Temp., °C Maximum takeoff (5 min.) 10,500 8,050 625 Maximum continuous 9,125 7,650 575 Airspeed limits (CAS) Knots Vne (Never exceed) 325 or Mach 0.81 whichever is the lesser Vno (Normal operation) 300 or M ach 0.77 whichever is the lesser Va (Maneuvering) 174 Vfe (Flaps down 0° to 10°) 258 Vfe (Flaps down 10° to 20°) 202 Vfe (Flaps down 20° to 35°) 190 Vlo (Landing gear operation) 180 Vle (Landing gear extended) 218 Vllo (Landing light extension 215 Air brake operation 306 or Mach 0.81 Air brake extended 306 or Mach 0.81 Vmc (Minimum control) Less than the stalling speed C.G. range (Landing Landing gear retraction moment -79,860 in.-lb. (moves the C.G. forward) gear extended) Weight Forward Aft (Pounds) % S.M.C. Aft of datum (in. ) % S.M.C. Aft of datum (in.) Up to 81,600 25 623.18 39.0 648.54 95,900 25 623.18 35.8 642.75 Straight line variation between weights. Maximum weights Taxi 96,500 lb. Takeoff 95,900 lb. Landing 91,335 lb. Zero fuel 77,160 lb. Minimum crew 3. Pilot and copilot at (77), flight engineer at (102). Maximum passengers 90. (See a pproved weight and balance report for actual number and location) Maximum luggage Volume Maximum floor Capacity (Cu.ft.) loading (p.s.f.) (lb.) Upper aft hold 212 82 2,120 (948) Lower forward hold 194 62 1,940 (372) Lower aft hold 88 62 880 (800) Fuel capacity (See NOTE 1(b) for data on system fuel and oil) Total Usable (U.S. gal.) (U.S. gal.) 2 inboard wing tanks 2,141.0 each 2,140 each (621) 2 outboard wing tanks 372.5 each 370 each (729) Oil capacity (See NOTE 1(b) for data on system fuel and oil) 1.05 U.S. gal. per engine Total oil 2.1 U.S. gal. (886) II - SUD AVIATION Caravelle SE 210 Model III (Transport Category), approved July 12, 1960 Same as SE 210 Model I except for maximum weights, stabilizer se tting 1° up, engine installation, engine silencer and wheels and brakes. Engines 2 Rolls-Royce Avon 527 turbojets Fuel French: TRO (AIR 3405) British: Aviation Kerose ne D.Eng. RD 2482 (AVTUR) or D.Eng. RD 2494 (AVTUR) 50 American: JP-1 (MIL-F-5616) Canadian: 3-GP-23B or For aircraft on which modifi cation No. 227 has been applied: French: (AIR 3407) British: D.Eng. RD 2486 American: JP-4 (MIL-F-5624/C) Canadian: 3-GP-22B Oil British: D.Eng. RD 2487 American: ESSO Aviation Turbo oil 35 Engine limits Static Sea Level Ratings Rating Minimum Thrust (lb.) Maximum R.P.M. Max. Turbine Gas Temp., °C Maximum takeoff (5 min.) 11,400 8,050 675 Maximum continuous 9,500 7,750 580 3 7A6 Airspeed limits (CAS) Knots Vne (Never exceed) 325 or Mach 0.81 whichever is the lesser Vno (Normal operation) 300 or M ach 0.77 whichever is the lesser Va (Maneuvering) 174 Vfe (Flaps down 0° to 10°) 258 Vfe (Flaps down 10° to 20°) 202 Vfe (Flaps down 20° to 35°) 190 Vlo (Landing gear operation) 180 Vle (Landing gear extended) 218 Vllo (Landing light extension) 215 Brake parachute (Normal operation) 115 (Never exceed) 130 Air brake operation 325 or Mach 0.81 Air brake extended 325 or Mach 0.81 Vmc (Minimum control) Less than the stalling speed C.G. range (Landing Landing gear retraction moment -79,860 in.-lb. (moves the C.G. forward) gear extended) Weight Forward Aft (Pounds) % S.M.C. Aft of datum (in. ) % S.M.C. Aft of datum (in.) Up to 81,600 25 623.18 39 648.54 101,400 25 623.18 35 641.29 Straight line variation between weights. Maximum weights Taxi 102,500 lb. Takeoff 101,400 lb. Landing 96,570 lb. Zero fuel 78,260 lb. Minimum crew 3. Pilot and copilot at (77), flight engineer at (102). Maximum passengers 90. (See a pproved weight and balance report for actual number and location) Maximum luggage Volume Maximum floor Capacity (Cu.ft.) loading (p.s.f.) (lb.) Upper aft hold 212 82 2,120 (948) Lower forward hold 194 62 1,940 (372) Lower aft hold 88 62 880 (800) Fuel capacity (See NOTE 1(b) for data on system fuel and oil) Total Usable (U.S. gal.) (U.S. gal.) 2 inboard wing tanks 2,141.0 each 2,140 each (621) 2 outboard wing tanks 372.5 each 370 each (729) Oil capacity (See NOTE 1(b) for data on system fuel and oil) 1.05 U.S. gal. per engine Total oil 2.1 U.S. gal. (886) III - SUD AVIATION Caravelle SE 210 Model VIR (Transport Category), approved June 5, 1961 Same as SE 210 Model III except for maximum weights, engine installation, reversers, spoilers, windshield and cockpit, artificial feel (elevator and rudder control systems). Vortex generators, and wheels and brakes. Engines 2 Rolls-Royce Avon 532R or Avon 533R turbojets Fuel American: JP-1 (MIL-F-5616) JP-4 (MIL-F-5624C) Canadian: 3-CP-23B, 3-CP-22B British: D.Eng. RD 2482, 2494, 2486 French: TRO AIR 3405, AIR 3407 Oil ESSO Aviation Turbo Oil 35 ESSO Turbo Oil 35 (Also known as Penola Turbo Oil 35 or Humble Turbo Oil 35) Castrol 98 Gas Turbine Oil Texaco Synthetic Aircraft Turbo Oil 15 Engine limits Static Sea Level Ratings Rating MinimumThrust (lb.) Maximum R.P.M. Max. Turbine Gas Temp.,°C 532R 533R 532R 533R 532R 533R Maximum takeoff (5 min.) 12,080 12,600 8,050 8,150 670 685 Maximum continuous 10, 710 10,710 7,900 7,900 595 595 EXCEPT WHEN: Knots Mod. 1122 Mod. 1042 installed installed Airspeed limits (CAS) Vne (Never exceed) 350 325 345 or Mach .81 whichever is the lesser Vno (Normal operation) 325 300 320 or Mach .77 whichever is the lesser Va (Maneuvering) 190 (Sea Level) 213 (H = 39,300 ft.) Vfe (Flaps down 0° to 5°) 270 (Flaps down 5° to 10°) 258 (Flaps down 10° to 20°) 202 (Flaps down 20° to 35°) 190 Vlo (Landing gear operation) 180 Vle (Landing gear extended) 245 Vllo (Landing light extension 215 Airbrake operation 350 325 345 or Mach .81 Airbrake extended 350 325 345 or Mach .81 Vmc (Minimum control) Less than the stalling speed C.G. range (Landing Landing gear retraction moment -85,930 in.-lb. (moves the C.G. forward) gear extended) Weight Forward Aft (Pounds) % S.M.C. Aft of datum (in. ) % S.M.C. Aft of datum (in.) Up to 110,200 25 623.18 39 648.54 Maximum weights Taxi 111,300 lb. Takeoff 110,200 lb. Landing 105,000 lb. Zero fuel 79,400 lb. 81,570 lb. (Mod. 1042 installed) Minimum crew (See NOTE 4) All operations except training, test and ferry flights 3. Pilot and copilot at (77), flight engineer at (102). Training, test and ferry flights 2. Pilot and copilot at (77) Maximum passengers 90. (See a pproved weight and balance report for actual number and location) 5 7A6 Maximum luggage UAL Version Mod. 712 installed Maximum luggage Volume Maximum floor Capacity (Cu.ft.) loading (p.s.f.) (lb.) Left upper aft hold 120 122 1,200 (954) Right upper aft hold 81 122 810 (950) Lower forward hold 194 61 1,940 (372) Lower aft hold 88 61 880 (800) Mod. 998, 1188 Installed Lower forward hold 222.5 61 3,065 (374) Lower aft hold 116.5 61 1,575 (798) Fuel capacity (See NOTE 1(b) for data on system fuel and oil) Total Usable (U.S. gal.) (U.S. gal.) 2 inboard wing tanks 2,141.0 each 2,140 each (621) 2 outboard wing tanks 372.5 each 370 each (729) Oil capacity (See NOTE 1(b) for data on system fuel and oil) 1.05 U.S. gal. per engine Total oil 2.1 U.S. gal. (886) Data Pertinent to All Models Datum Zero moment datum is located on the center lin e of the aircraft at the vertical line tangent to the aircraft theoretical nose, i.e., 82.8 inch es forward of frame No. 7. Horizontal arms to the rear of the datum are positive (+). Standard Mean chord 181.42 inches The leading e dge of the standard mean chord is at+577.8 in. (S.M.C.) Leveling means Leveling plates in fo rward lower hold at Frames 22 and 25. Control surface movements Elevator Up 30° Down 12° Rudder Right 25° Left 25° Aileron Up 21° Down 21° Flaps 35° Total angle of travel Upper airbrake Up 70° Lower airbrake Down 75° Spoilers Up 60° (for Model VIR only) Maximum operating altitude 39,300 ft. Other operating Aircraft shall be operated in compliance with the operating limitations specified limitations in the S.G.A.C. approved Airplane Flight Manual. Serial Nos. eligible The French Government Certifi cate of Airworthiness for export endorsed as noted under "Certification basis" must be submitted for each individual aircraft for which application for certification is made. Certification basis CAR 10. Type Ce rtificate No. 7A6 dated April 18, 1959. Date of application for Type Certificate September 30, 1955. Each aircraft and any replacement part manuf actured in France must be clearly identified as imported. A U.S. Airworthiness Certificate may be issued on the basis of Certificate of Airworthiness for Export signed by a repr esentative of the Secretariat General a l'Aviation Civile (S.G.A.C.) containing the following statement: "The aeroplane covered by this certificat e has been examined and found to comply with U.S. Civil Air Regulation Part 4b, effective December 31, 1953, including amendments 4b1, 4b2, 4b4, 4b7, 4b9 a nd SR 422 A (Models I and III), SR 422 B (Model VIR) and with the Special Require ments notified by the U.S. Government to the French Government and conforms to T.C. 7A6." Compliance with the ditching re quirements has been demonstrated. Compliance with the ice protection require ments of CAR 4b.640 has been demonstrated. Equipment The basic required equipm ent as prescribed in the applicable airworthiness regulations (see Certification Basis) must be installed in the aircraft for certification. The following additional equipment is required: Weight (lb.) (a) Stall warning, 1 horn SANOR Model TR 2 2 (59) (b) High speed warning according to SR 450A 1 horn SANOR Model J8 AV or 1 cling bell 2 (59) BONVOISIN 4003/AF/G - (Mod. 1132 installed) 1 (59) (c) Artificial feel device, Elevator Control System SUD AVIATION drawing No. 27 06 003 51 (932) (Models I and III) SUD AVIATION drawing No. 27 06 801 (Model VIR) 69 (932) Aileron Control System SUD AVIATION drawing No. 17 50 425 17 (772) Rudder Control System SUD AVIATION drawing No. 27 07 003 44 (932) (Models I and III) SUD AVIATION drawing No. 27 07 295 (Model VIR) 60 (932) (d) Control surface positions Elevator: 1 transmitter AIR EQUIPEMENT Model 11501 1 (1145) 1 indicator AIR EQUIPEMENT Model 12504.01 1 (49) Aileron: 1 transmitter AIR EQUIPEMENT Model 11501 1 (739) 1 indicator AIR EQUIPEMENT Model 12504.02 1 (49) Rudder: 1 transmitter AIR EQUIPEMENT Model 11501 1 (1160) 1 indicator AIR EQUIPEMENT Model 12504.03 1 (49) NOTE 1. (a) Current weight and balance report including list of equipment included in the certificated empty weight, and loading instructions when necessary, must be provided for each aircraft at the time of original certification. (b) "Unusable Fuel and System Oil " and all hydraulic fluid must be included in the certificated empty weight. "Unusable Fuel is that quantity of fuel in the system and in the tanks which is unavailable to the engine under critical flight conditions as defined in CAR 4b.416. This unusable fuel includes "system fuel" which is defined as the quantity required to fill the system and tanks to the tank outlet level when the airplane is on the ground level attitude. The fuel gauges are calibrated with the unusable fuel as the zero datum. 7 7A6 The total amount of fuel is as follows: Usable fuel Unusable fuel 5020 U.S. gal. 7 U.S. gal. System oil is that amount of oil required to fill the oil system and tanks and is completely contained within the engine. System oil weight is 31 lb. The oil tank capacity shown in the da ta sheet includes only the usable oil. A sight glass allows to check the oil level. NOTE 2. The following is a list of aircraft parts which are critical from the fatigue standpoint and must be replaced at the times specified: 2 Pressure regulators, LOCKH EED-ENGLAND Model AIR 43444 6,000 hours NOTE 3. All aircraft must be maintained and repaired in accordance with the French Government approved Maintenance and Structural Repair Manuals. NOTE 4. Aircraft incorporating SUD Mod. 1126 may be flown with a minimu m crew as shown on page I.4.1 of S.G.A.C. approved Airplane Flight Manual SE 210 655. NOTE 5. Sud/Lear Autoland Installation - SE 210 Model VI R. If Sud Modifications Nos. 1186, 1357 and 1358 have been incorporated in accordance with Caravelle Service Bulletin No. 22.33, operation of the autopilot is author ized down to 50 feet. (The above equipment complies with FAA Advisory Circular A.C. 20-31). .....END.....