TCDS TT00001AK

DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION TT00001AK C-1 Aero Fuel Grumman Navy C-1A November 19, 1993 TYPE CERTIFICATE DATA SHEET NO. TT00001AK This data sheet, which is a part of Type Certificate No. TT00001AK describes the 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 C-1 Aero Fuel P.O. Box 81464 Fairbanks, Alaska 99708 I - Grumman Aerospace Corporation U.S. Navy Model C-1A (Restricted Category), Approved November 19, 1993 (See NOTES 2, 3, and 4) Engines 2 Curtiss-Wright “Cyclone” R-1820-82B with ignition timing reset to produce spark 20° before top dead center Fuel Minimum Grade 100LL Aviation Gasoline Oil Esso 100 or equivalent; 3-GP-100, MIL-L-6082 Grade 1100 Engine Limits Takeoff (5 Minutes) 1475 BHP @ 2800 RPM and 54.5 in. Hg MAP @ S.L. density altitude, full throttle 1475 BHP @ 2800 RPM and 54.0 in. Hg MAP @ 1600 ft. density altitude, full throttle Normal Rated (METO) 1275 BHP @ 2500 RPM and 47.0 in Hg MAP @ S.L. density altitude, full throttle 1275 BHP @ 2500 RPM and 46.0 in. Hg MAP @ 3600 ft. density altitude, full th rottle Propellers 2 Hamilton Standard 3-Bladed Hydromatic Model 43D conforming to Propeller Type Certificate No. 851 Hub Model 43D51-303, 43D51-329, 43D51-341, 43D51-343, or 43D51-355 Blades Model 6915B-7, 6915C-7, 6915E-7, 6985B-7, or 6985C-7 Diameter 11 ft. 0 in. Low pitch setting 18.5 degrees Airspeed Limits (IAS) : VMO (Maximum Operating) 222 knots (255 mph) Page No. 1 2 3 4 5 6 Rev. No. - - - - - - TT00001AK 2 Airspeed Limits VA (Maneuvering) 156 knots (180 mph) (IAS) VFE (Flaps Extended) 150 knots (172 mph) VLE (Landing Gear Extended) 150 knots (172 mph) VLO (Landing Gear Operating) 150 knots (172 mph) VMC (Minimum Control Speed) 85 knots ( 98 mph) Maximum Speed for Full Lateral Control Displacement 200 knots (230 mph) Above 200 knots (230 mph) lateral control displacement is limited to one-half of full displacement. Maximum Speed for Skidding or Sideslipping (Rudder Assist OFF) 155 knots (178 mph) Maximum Speed for Skidding or Sideslipping (Rudder Assist ON) 130 knots (150 mph) Maximum Speed with Flaps Extended by Emergency System 130 knots (150 mph) Maximum Nose Wheel Ground Roll Speed 115 knots (132 mph) Maximum Crosswind Component for Takeoff or Landing 15.5 knots (With No Headwind) (17.8 mph) Maximum Crosswind Component for Takeoff or Landing (With 55 knots (63.3 mph) 30.0 knots Headwind) (34.5 mph) Maximum crosswind component for takeoff or landing varies linearly between specified values. See Figure 5-7 on Page 5-34 of the FAA approved Airplane Flight Manual for maximum engaging speeds approved for field arrested landings and aborted takeoffs, and for approved types of arresting gear. Mean Aerodynamic Chord (MAC) 88.61 in. MAC Leading Edge Location (in. aft of reference datum ‘0’) +194.80 C. G. Range (in. aft of reference datum ‘0’ and % MAC) +213.85 (21.5% MAC) to +220.32 (28.8% MAC), Landing Gear Extended +215.27 (23.1% MAC) to +221.83 (30.5% MAC), Landing Gear Retracted Landing Gear Retraction Moment (in. - lbs./1000) = +32.0 Retracting landing gear moves C.G. AFT. 3 TT00001AK Datum Reference Datum ‘0’ is 94.64 in. forward of jig point on forward face of nose landing gear uplock bulkhead located at reference station +96.0. Reference stations are distances in inches aft of reference datum ‘0’. Leveling Means Plumb bob and scribed scale in main entrance and cargo door frame on left side of airplane, at reference station +330.125. Plumb bob suspension p oint is located on fuselage interior structure above top of door frame. Scale is located at edge of cargo deck in bottom of door opening. Maximum Weights Takeoff 24,500 lbs. Normal Landing 24,500 lbs. Arrested Landing 24,200 lbs. Minimum Crew For flight in visual meteorological conditions 1 (Pilot) at ref. station +111.0 Number of Seats 2 at reference station +110.9 Cargo Capacity Cargo compartment length 208.75 in. Cargo compartment forward end location (ref. station) +129.25 Cargo compartment aft end location (ref. station) +338.0 Maximum distributed loading allowed on cargo floor 220 psf Cargo floor crushing strength 90 psi Main cargo compartment is divided into five smaller compartments for cargo loading purposes, as follows: Compartment C (ref. stations +129.25 to +182.0) Average arm (ref. station) +156.0 Maximum cargo weight (lbs.) 4790 Floor area (sq. ft.) 21.8 Volume (cu. ft.) 130.8 Compartment D (ref. stations +182.0 to +219.0) Average arm (ref. station) +200.0 Maximum cargo weight (lbs.) 2990 (1760 within cargo cage) Floor area (sq. ft.) 13.6 Volume (cu. ft.) 68.0 Compartment E (ref. stations +219.0 to +255.0) Average arm (ref. station) +237.0 Maximum cargo weight (lbs.) 2990 (1705 within cargo cage) Floor area (sq. ft.) 13.6 Volume (cu. ft.) 68.0 Compartment F (ref. stations +255.0 to +291.0) Average arm (ref. station) +273.0 Maximum cargo weight (lbs.) 2810 (1705 within cargo cage) TT00001AK 4 Cargo Capacity Floor area (sq. ft.) 12.8 Volume (cu. ft.) 64.0 Compartment G (ref. stations +291.0 to +338.0) Average arm (ref. station) +314.0 Maximum cargo weight (lbs.) 3120 (1200 aft of cargo cage) Floor area (sq. ft.) 14.2 Volume (cu. ft.) 71.0 Maximum cargo weight in each compartment is weight that can be carried in that compartment when cargo cage is not installed, based on maximum distributed floor loading. Maximum cargo weight that can be carried within cargo cage in compartments D, E, and F is based on maximum distributed floor loading on floor area between sides of cage. Maximum cargo weight that can be carried aft of cargo cage in compartment G is based on strength of cargo cage aft stanchions and horizontal beams under forward loading. Maximum weights cannot be carried in all compartments simultaneously. Total cargo weight capacity is limited by airplane maximum weight and C.G. range. Fuel Capacity Total 521 gal. (2 wing tanks, 260.5 gal. each) Usable 518 gal. (2 wing tanks, 259 gal. each) Reference station of fuel weight varies with fuel quantity according to the following table: Fuel Quantity in Tank Reference Station 1/4 Full +233.15 1/2 Full +230.60 3/4 Full +229.40 Full +227.25 Oil Capacity 27 gal. total (one 13.5 - gal. tank in each engine nacelle) at reference station +192.5 Maximum Operating Altitude 12,000 ft. Control Surface Movements Ailerons, measured at outboard end Up 20° +/- 1°, or 3 -29/32 in. +/- 1/16 in. Down 15° +/- 1°, or 2 -29/32 in. +/- 1/16 in. Elevators, measured at inboard end (on rudder trimmer) Up 25° +/- 1°, or 6 -5/16 in. +/- 1/4 in. Down 15° +/- 1°, or 3 -3/4 in. +/- 1/4 in. Rudder, measured at any station Right 24° +/- 1° or 8 -5/16 in. +/- 11/32 in. Left 24° +/- 1° or 8 -5/16 in. +/- 11/32 in. Rudder Trimmer, measured at lower end (combined electric and hydraulic actuation) Right 25° Ref.*, or 10 -7/32 in. Ref* Left 25° Ref.*, or 10 -7/32 in. Ref.* *Tolerances for rudder trimmer movements are defined only for hydraulic actuation alone and for electric actuation alone. Movements for combined hydraulic and electric actuation are given for reference only. 5 TT00001AK Rudder Trimmer, measured at lower end (hydraulic actuation only) Right 20° ± 1°, or 8 -5/32 in. ± 13/32 in. Left 20° ± 1°, or 8 -5/32 in. ± 13/32 in. Rudder Trimmer, measured at lower end (electric actuation only) Right 5° ± 0° -10’, or 2 -1/16 in. ± 1/16 in. Left 5° ± 0° -10’, or 2 -1/16 in. ± 1/16 in. Elevator Trim Tabs, measured at inboard end (from trailing edge of elevator) Up 20° ± 1°, or 1 -3/8 in. ± 1/16 in. Down 20° ± 1°, or 1 -3/8 in. ± 1/16 in. Aileron Trim Tab (on left aileron only), measured at outboard end of spring tab, 4 in. from hinge centerline Up 20° ± 1°, or 1 -3/8 in. ± 1/16 in. Down 20° ± 1°, or 1 -3/8 in. ± 1/16 in. Rudder Tab, measured at upper or lower end (from trailing edge of rudder, with 0° rudder and 25° rudder trimmer) Right 27° ± 2°, or 2 -3/8 in. ± 3/16 in. (with rudder trimmer 25 ° left) Left 23° ± 2°, or 2 in. ± 3/16 in. (with rudder trimmer 25 ° right) Elevator Geared Tabs, measured at outboard ends (from trailing edge of elevator) Down 5° ± 1°, or 11/32 in. ± 1/16 in. (with elevator 0° to 15° down) Down 20° ± 2°, or 1 -3/8 in. ± 1/8 in. (with elevator 25° up) Aileron Spring Tabs, measured at outboard ends (at trim tab on left aileron), 4 in. from hinge centerlines Up 15° ± 1°, or 1-1/32 in. ± 1/16 in. Down 20° ± 1°, or 1 -3/8 in. ± 1/16 in. Outboard Flaps, measured at engine nacelles Down 27-1/2° ± 2°, or 11-13/32 in. ± 27/32 in. Inboard Flaps, measured at engine nacelles Down 40° ± 2°, or 17-11/16 in. ± 29/32 in. Outboard Spoilers, measured at wing station 317 spoiler hinges Up 58° ± 3°, or 6-3/16 in. ± 5/16 in. Inboard Spoilers, measured at wing station 233 spoiler hinges Up 38-1/2° ± 2°, or 5-9/32 in. ± 9/32 in. Serial Numbers Eligible Grumman S/N 44 (U.S. Naavy Bureau of Aeronautics S/N 136791) The original Navy designation for the C-1A airplane was the TF-1 and this designation will appear on the manufacturer’s nameplate. In 1962, a new numbering system was established for all U.S. military airplanes and the TF-1 became the C-1A. Certification Basis FAR 21.25 (a) (2) and FAR 21.25 (b) (7) effective February 1, 1965 as amended by Amendment 21-42 effective February 7, 1975. Restricted Type Certificate TT00001AK issued November 19,1993 for the special purpose of carrying cargo. Application for Restricted Type Certificate dated April 20,1993. TT00001AK 6 Production Basis None. Prior to original airworthiness certification of each airplane, FAA personnel must perform an airworthiness inspection to verify that it is in a good state of preservation and repair and in a condition for safe operation, and must witness a satisfactory flight test. Equipment The basic required equipment as prescribed in the applicable airworthiness regulations (see Certification Basis) must be instal led in the airplane for airworthiness certification. In addition, the FAA approved C-1 Aero Fuel Airplane Flight Manual for Grumman C-1A Airplane dated November 19, 1993 and the FAA approved C-1 Aero Fuel Airplane Flight Manual Avionics Supplement for Grumman C-1A Airplane dated November 19,1993, or later FAA approved revisions, are required. NOTE 1 Current weight and balance report including list of equipment included in certificated empty weight, and Chart E for C-1A Airplane from Handbook of Weight and Balance Data, AN 01-1B-40, must be provided for each airplane at the time of original airworthiness certification. NOTE 2 A. This approval applies to Grumman Aerospace Corporation U.S. Navy Model C-1A airplanes incorporating modifications as described in C-1 Aero Fuel Master Descriptive Data List No. C-1A-1 dated June 17, 1993, or later FAA approved revisions. B. Airplanes eligible for original airworthiness certification under Type Certificate TT00001AK may be issued Certificates of Airworthiness in the Restricted Category for the special purpose of carrying cargo. Airplanes for which such Certificates of Airworthiness have been issued must be operated in compliance with the operating limitations for restricted category civil aircraft specified in FAR 91.313. C. The following placard must be displayed in front of and in clear view of the pilot(s): THIS AIRPLANE MUST BE OPERATED AS A RESTRICTED CATEGORY AIRPLANE IN COMPLIANCE WITH THE OPERATING LIMITATIONS STATED IN THE FORM OF PLACARDS, MARKINGS, AND MANUALS. All placards required in the FAA approved Airplane Flight Manual and in the FAA approved Airplane Flight Manual Avionics Supplement must be installed in the appropriate locations. NOTE 3 All U.S. Navy Airframe Bulletins applicable to the C-1A airplane must be complied with prior to original airworthiness certification of each airplane. Airplanes eligible for original airworthiness certification under Type Certificate TT00001AK must be inspected, serviced, and maintained in accordance with the Handbook of Inspection Requirements for Navy Model C-1A Aircraft, NAVAIR 01-85SAA-506, the Handbook of Maintenance Instructions for Navy Models TS2A, US2A, US2B, US2C, and C-1A Aircraft, NAVAIR 01-85SAA-2-2, and Navy letter entitled C-1A Aircraft Service Life, Recommendation On, Department of the Navy Letter No. 5302B/APC Ser 7.2600, dated January 11,1980. The service life limit of C-1A airplanes eligible for original airworthiness certification under Type Certificate TT00001AK has been established as 25,000 total flight hours including a maximum total of 3300 arrestments. NOTE 4 Upon completion of the special purpose modifications required to bring the airplane into compliance with the Restricted Category type design approved by Type Certificate TT00001AK, the manufacturer’s nameplate on the airplane must be altered to include the C-1A designation and to state that the airplane has been modified per TC TT00001AK. If the original nameplate is not large enough to include this additional information, a similar plate containing the additional information must be installed near the original plate. The original nameplate, and any other nameplate(s) subsequently installed, must be left on the airplane. .....END.....