TCDS H1EA

Page No. 1 2 3 Rev No. 4 4 4 DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION H1EA Revision 4 ERICKSON AIR-CRANE INCORPORATED S-64A March 28, 2007 TYPE CERTIFICATE DATA SHEET NO. H1EA This data sheet, which is a part of Type Certificate Number H1EA, prescribes conditions and limitations under which the product for which the Type Certificate was issued meets the airworthiness requirements of the Civil Air Regulations. Type Certificate (TC) Holder: Erickson Air-C rane Incorporated, DBA Erickson Air-Crane 3100 Willow Springs Road P. O. Box 3247 Central Point, Oregon 97502 Type Certificate Holder Record. Sikorsk y Aircraft transferred TC H1EA to Erickson Air-Crane on February 13, 1992. I - Model S-64A (Restricted Category), approved 30 July 1965. (See NOTE 5 for modified version.) Engine 2 Pratt & Whitney JFTD12A-1 (with Hamilton Standard Fuel Control JFC56-1). Fuel Aviation Kerosene JP-4 or JP-5 (m ilitary specification MIL-J-5624 or subsequent revisions thereto). Engine limits Sea Level Sta tic, Standard Day Conditions Shaft Power Gas Power Turbine HP Turbine R.P.M. Gen. R.P.M. Inlet (T5) Takeoff (30 min) 4050 9500 (105.5%N2) 16,700 (104%N1) 650°C Maximum continuous 3200 9500 (105.5%N2) 16,700 (104%N1) 565°C Allowable maximum - - 10,350 (115%N2) 16,700 (104%N1) - - overspeed Accelerated limit - - - - - - 665°C (2 min.) Starting limit - - - - - - 525°C (2 min.) Takeoff and Maximum continuous horsepower ratings are normally obtained at a power turbine speed of 9000 r.p.m. (100%N2). Total power for two-engine operation is lim ited to 5400 s. hp. for takeoff and 4800 s. hp. maximum continuous. Rotor limits Maximum 204 r.p.m. (110%Nr) Minimum 167 r.p.m. (90%Nr) Airspeed limits Never exceed 132 m.p.h. (115 knots) IAS, zero instrument error. H1EA 2 C.G. range (+328.0) to (+357.0) at 38,000 lb. (+324.0) to (+357.0) at 30,000 lb. (+328.0) to (+357.0) at 23,000 lb. 324 328 23,000 30,000 38,000 357Station--Inches Gross Weight (Pounds) Empty weight None. C.G. range Datum 336 inches forward of main rotor centroid. Leveling means Plumb line from top level plate inside cockpit aft door. Maximum weight 38,000 lb. Maximum crew 2 (pilot, observer). Number of seats 5: 2 at (+94.0), 1 at (+108.5), 1 at (+127.0), 1 at (+130.0). Maximum cargo See NOTE 3. Fuel capacity 1356 gal. (454 gal. at (+280.0) , 454 gal. at (+397.3), 448 gal. at (+461.3)). Oil capacity 2.6 gal. (+234.0) (2 tanks 1.3 gal. each). See NOTE 1 for data on system fuel and oil. Rotor blade and control movements For rigging informa tion, refer to Maintenance Manual. Serial numbers eligible There are no e ligible serial numbers at this time. Certification basis CA R 8, October 11, 1950. Type Certificate H1EA issued July 30, 1965, for the purpose of feasibility studies by the U.S. Army related to the heavy-lift helicopt er development project. Aircraft produced under this type certificate are not eligible for civil certification. Date of Application for Type Certificate - June 25, 1963. Production basis None. Equipment The basic required equipm ent as prescribed in the applicable airworthiness regulations (see certification basis) must be installed in th e aircraft for certification. In addition, the following items of equipment are required: (a) FAA Approved Roto rcraft Flight Manual. NOTE 1. Current weight-and-balance report including list of required equipment and equipment included in certificated empty weight, and loading instructions, when necessary, must be provided for each helicopter at the time of original certification. The certificated empty weight and corresponding C.G. locations must include undrainable oil of 5 lb. (+234.0) and unusable fu el of 26 lb. (10 lb. at (+290.0), 9 lb. at (+370.0), 7 lb. at (+461.0)). NOTE 2. The following placard must be displayed in front of and in clear view of the pilot: "THIS HELICOPTER MUST BE OPERATED IN COMPLIANCE WITH THE OPERATING LIMITATIONS SPECIFIED IN THE FAA APPROVED ROTORCRAFT FLIGHT MANUAL" 3 H1EA NOTE 3. Provisions for the carriage of external loads are av ailable in the form of structural hard points on the fuselage and main landing gear; single and four-point hoists; and a four-point load-leveler suspension system. Information concerning the operating limitations with this equipment is contained in the Rotorcraft Flight Manual. NOTE 4. Information essential to the proper maintenance of the helicopter is contained in the manufacturer's Maintenance Manual provided with each helicopter which sp ecifies that service Life-Limited parts be retired according to the following schedule: Component Part No. Service Life (Hours) Upper plate S6410-23011-101 1650 Lower plate S6410-23009-101 1650 Spacer S6410-23006-011 250 S6410-23006-012 1650 Hub S1510-23001-4 500 Sleeve S1510-23351 7300 Vertical hinge S1510-23022 500 Horizontal hinge pin S1510-23099-1 1550 Scissors bracket, rotating S6410-24069-011 4950 Upper link, rotating S6410-24056-101 17,000 Lower link, rotating S6410-24052-101 17,000 Damper assembly (less cylinder housing) S6410-26200-043 500 Cylinder housing, damper S6410-26001-103 400 Attachment brackets, damper S6410-26208-101 500 102 500 Main rotor blade S6415-20101-041 5000 Spindle S65112-07002-041, -044 2600 Main rotor shaft S6435-20078-014 1000 Splice installation, S6420-60211 2750 rotary rudder boom and pylon NOTE 5. Model S-64A modified as described in Sikorsk y Engineering Report No. SER-64182, approved June 27, 1968, for the purpose of United States Army use of a cr ane-type helicopter as a vehicle to transport cargo and equipment, with or without combat crews, in a field Army. Included among the modifications are changes to structure, systems and equipment, extern al cargo carrying provisions, and the incorporating of two Pratt and Whitney JFTD 12A-4A engines w ith Hamilton Standard Fuel Control JFC56-4. Engine limits Sea Level Sta tic, Standard Day Conditions Shaft Power Gas Power Turbine HP Turbine R.P.M. Ge n. R.P.M. Inlet (T5) Takeoff (5 min.) 4500 9500 (105.5%N2) 16,700(104%N1) 688°C Maximum continuous 4000 9500 (105.5%N2) 16,700(104%N1) 655°C Allowable maximum - - 9500 (105.5%N2) 16,700(104%N1) - - overspeed Acceleration limit - - - - - - 688°C (2 min.) Starting limit - - - - - - 525°C (2 sec.) Takeoff and maximum continuous hor sepower ratings are normally obtained at a power turbine speed of 9000 r.p.m. (100%N2). Total power for twin-engine operation is limited to 6600 s. hp. for takeoff and 5400 s. hp. maximum continuous. ...END...