TCDS 7A10

FEDERAL AVIATION AGENCY 7A10 Revision 2 de HAVILLAND D.H. 106 Comet 4C August 8, 2003 TYPE CERTIFICATE DATA SHEET NO. 7A10 This data sheet which is a part of ty pe certificate No. 7A 10 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 The de Havilland Aircraft Co., Ltd. Hatfield, Hertz, England I - Model D.H. 106 Comet 4C (Transport Category), Approved December 21, 1960 Engines 4 Rolls Royce Avon 525B turbojets Fuel The following Aviation Kerosene Specifications are approved: British: D.Eng. RD 2482, 2488 and 2494 Canadian: 3-GP-23C Type 1 American: A.S.T.M. D.1655-59 T Type A or Type A-1 and United Airlines Specification UA-1 I.A.T.A.: Kerosene Type Fuel The following departures from Specification D.Eng. RD 2494 are acceptable: Flash point Minimum 70°F Mercaptan Sulphur Maximum 0.016% by weight Oil D.Eng. RD 2487 (Type RD E/O/463) or Esso Aviation Turbo Oil 35 Engine limits Static Sea Level Ratings Rating Minimum Thrust (Lb.) Maximum RPM Max. Turbine Exhaust Gas Temp, °C Maximum takeoff (5 min.) 10250 8050 625 Maximum continuous 8765 7600 570 Airspeed limits (I.A.S.) Vne (never exceed) 305 kt. or Mach 0.79, whichever is the lesser Vno (normal operating) 275 kt. or Mach 0.76, whichever is the lesser Va (maneuvering) 199 kt. Vfe (flaps down 0° to 20°) 210 kt. Vfe (flaps down 20° to 30°) 190 kt. Vfe (flaps down 30° to 40°) 170 kt. Vfe (flaps down 40° to 60°) 150 kt. Vfe (flaps down 60° to 80°) 140 kt. Vlo (landing gear operation) 185 kt. Vle (landing gear extended) 210 kt. air brake operation 305 kt. or Mach 0.79, whichever is lesser air brake extended 305 kt. or Mach 0.79, whichever is lesser Vmc (minimum control) Less than the stalling speed Elevator Gear Change Limitations: Minimum airplane speed in 'fine gear' 170 kt. Maximum airplane speed in 'coarse gear' 200 kt. Page No. 1 2 3 4 5 Rev. No. 2 - - - - 7A10 Page 2 of 5 C.G. range (Landing The nose gear retraction moment is 27,000 in.lb. gear extended) Main gear retraction has no effect on the airplane C.G. -35 -30 -25 -20 -15 -10 -5 0 +5 60 80 100 120 140 160 170 79,000 -28.9 79,000 -13.3 95,000 +4.0 162,000 +4.1 162,000 -8.3 118,150 -17.7 108,700 -23.5 102,500 -28.8 107,300 -25.3 113,300 -22.7 Datum 702 in. aft of the fuselage nose Standard mean chord 222 in. (L.E. of S.M.C. is 640.8 in. aft of fuselage nose). (S.M.C.) Leveling means Fuselage sighting rods and microptic level for longitudinal leveling. Leveling bar and spirit level in conjunction with datum sockets in rear freight hold for lateral leveling. Maximum weight Maximum taxi 162,000 lb. Maximum takeoff 162,000 lb. Maximum landing 120,000 lb. Maximum zero fuel 102,500 lb. Minimum crew 3. Pilot and copilot (-628.8), flight engineer (-582) Maximum passengers 107 passengers. (See approved weight and balance report for actual number and location.) Maximum baggage Compartment Maximum Total Floor Load (lb.) Maximum Floor Loading (lb. sq. ft.) Moment Arm (In.) Freight Compartments Forward Hold Fwd. of Datum A (Frame 17) 783 75 -426.6 Between Datums A & B 257 75 -372.6 Frames 17 & 19 Aft of Datum B (Frame 19) 1,971 75 -271.2 Center Hold Fwd. of Datum A (Frame 42) 1,296 75 +144.0 Between Datum A & B 257 75 +212.4 (Frames 42 & 44) 1,512 75 +290.4 Rear Cabin Hold 3,140 150 +434.4 Page 3 of 5 7A10 Fuel capacity (See NOTE 1(b) for data on system fuel.) TANK TOTAL USABLE MOMENT ARM (lb.) (in.) 1 center wing tank 16095 16031 (-26.5) (No. 1) 2 inner wing tanks 12639 12607 (-32.2) (No. 2) 2 middle wing tanks 22462 22398 (-49.4) (No. 3) 2 outer wing tanks 13409 13313 (+108) (No. 4) 2 external wing tanks 6944 6816 (- 7.2) (No. 4A) Oil capacity (See NOTE 1(b) for data on system oil.) 1.04 U.S. gal. per engine (-7.4) Max. operating altitude 40,000 ft. Other operating limitations Aircraft sha ll be operated in compliance with the operating limitations specified in the Air Registration Board approved Airplane Flight Manual. Control surface movements Elevator Coarse gear Up 23° Down 10° (From neutral trim Fine gear Up 12° minimum Down 5° minimum position) Elevator balance tab Up 13° 20' Down 30° 38' Rudder Left 28° Right 28° (From neutral trim position) Aileron Up 22° 30' Down 22° 30' (From neutral trim position) Aileron balance tab Up 6° 10' Down 6° 10' Flaps 2 inboard sections 80° Total angle of travel 2 outboard sections 58° Total angle of travel Airbrakes Inner Up 27° Outer Up 84° Down 72° Auto pilot limit Elevator movement from switches neutral trim position Coarse Up 2° 24' Down 1° 24' Fine Up 0° 30' Down 0° 30' Aileron movement from neutral trim position Coarse Up 15° Down 15° Fine Up 3° 45' Down 3° 45' Serial Nos. eligible 6424, 6425, and 6443 provided a United Kingdom Certificate of Airworthiness for export endorsed as noted under "Import Requirements" is submitted for each individual aircraft for which application for certification is made. Import requirements A U.S. Airworthiness Certificate may be issued on the basis of: a) A United Kingdom Certificate of Airw orthiness for Export which contains the following notation: "The aeroplane covered by this certificat e has been examined and found to comply with British Airworthiness Requirements (July 1, 1956) and the Special Conditions for the Comet notified by the U.S.A. Government of the United Kingdom and conforms to T.C. 7A10,: 7A10 Page 4 of 5 b) Satisfactory evidence that all applicable inspections and modifications classified as "Mandatory" by the U.K. Civil Aviation Authority, and compliance with all FAA Airworthiness Directives have been accomplished. (A current list of all CAA "Mandatory" modifications and inspec tions may be obtained upon request from the Chief, Aircraft Certification staff, FAA, c/o American Embassy, APO New York, N.Y. 09667); and, c) An FAA finding that the airplane conforms to T.C. 7A10 and is in a condition for safe operation pursuant to FAR 21.183(c). Certification basis CAR 10, equivalent to CAR 4b effective December 31, 1953, plus amendments 4b-1, 4b-2, 4b-3, 4b-4, 4b-5, 4b-6; except paragraphs 19 4b.358 (b)(5) and 47 4b.645(e); 4b-7, 4b-8; except paragraph 17 4b.612(b); 4b-9, 4b-11 and S.R.422B. Compliance with the ditching requirements has been demonstrated. Compliance with the icing protection requirements has been demonstrated. Type Certificate No. 7A10 issued December 21, 1960. Date of Application for Type Certificate June 11, 1956. Equipment The basic required equipment as prescribed in the applicable airworthiness regulations (see Certification basis) must be installed in the aircraft for certification. Approved equipment is shown on de Havilland Equipment Schedule M.31410. The following additional equipment is required: (a) Stall warning stick shaker D.H. drg. 6-2 CF 1941 4 lb. (-645) (b) High speed warning, 1 horn KLAXON 2K 3 lb. (-606) (c) Artificial feel, 'q' pot elevator control system D.H. drg. 6-4B CF 313A 17 lb. (-653) (d) Rudder limiter D.H. drg. 6-4B CF 337A and 6-4 CF 1449 A/1 8 lb. (-669) (e) Rudder centralizer LOCKHEED part no. AIR 107270 2 ¼ lb. (+639) (f) Artificial feel, spring struts: Elevator control system 6-4B CF 779A/1 3 lb. (-636) Aileron control system 6-4C 10725 A.N.D. 3 lb. (-643) Rudder control system 6-4B CF 145/3 2 lb. (-669) (g) Yaw damper, rudder control system: 2 detector and amplifier SMITHS 300 EAP 23 lb. (+123) 2 actuator SMITHS 302 EAP 11 lb. (+403) (h) Control surface position indicators: Aileron: 2 transmitters SMITHS 875 F./BR 1 ½ lb. (+146) 1 indicator SMITHS PW 873/FL/BR 1 lb. (+654) Elevator: 1 transmitter SMITHS 875 FL/BR 3/4 lb. (+642) Rudder: 1 transmitter SMITHS 875 FL/BR 3/4 lb. (+646) Elevator/Rudder: 1 indicator SMITHS PW 873/FL/BR 1 lb. (-654) NOTE 1. (a) Current weight and balance report, including list of equipment included in certificated empty weight, and loading instructions when necessary, must be provide d for each aircraft at the time of original certification. (b) "Unusable fuel" is that amount of fuel in the tanks which is unavailable to the engines under critical flight conditions as defined in CAR 4b. 416. This unusable fuel includes the "system fuel" which is defined as the quantity required to fill the system and tanks to the tank outlet level when the airplane is in the ground level altitude. The "unusable fuel" must be included in the airplane empty weight or be suitably accounted for in the airplane weight and balance report. The total amount of fuel is as follows: Usable fuel (lb.) Unusable fuel (lb.) 71,165 384 Page 5 of 5 7A10 "System Oil" is that amount of oil required to fill the oil system and tanks and is completely contained within the engines. System oil weight is 58 lb. The oil tank capacity shown in this data 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 cr itical from the fatigue standpoint, and must be replaced at the times specified. Component Part No. Renewal Times No. 2 Aileron Hinge Bracket attachment bolts 6.4WE. 5085 12,000 hr. Nose Wheel Steering Jack 6.UN. 1087 attachment bolt (Pre.Mod.4/1095) 18,000 hr. 6.4UN. 273 (Post Mod.4/1095) 18,000 hr. Main Alighting Gear 6.3U. 39A Rocker Arm (Pre.Mod.4/1637C) 1,800 landings Elevator Primary ) 10,000 hr. Servodyne Valve ) AIR. 101014 Chest ) or ) Rudder Primary ) AIR. 104582 30,000 hr. Servodyne Valve ) Chest ) Aileron Primary AIR. 100930 15,000 hr. Servodyne Body Aileron Primary AIR. 100932 15,000 hr. Servodyne Connecting Block Aileron Secondary AIR. 100870 15,000 hr. Servodyne Body Outer Flap Servodyne AIR. 102358 or 15,000 hr. Body AIR. 103660 Outer Flap Servodyne AIR. 104654 15,000 hr. Valve Chest Main Undercarriage AIR. 104224 or 20,000 hr. Jack Eye End AIR. 58416 NOTE 3. All aircraft must be maintained and repaired in accordance with the Air Registration Board approved Maintenance and Structural Repair Manuals. NOTE 4. When thrust reversers are not installed throttle le vers conforming with de Havilland Comet modification 4/2395 must be installed. NOTE 5. A FAA Certificate of Airworthiness is not to be issued until compliance is found to SFAR 88. .....END.....