TCDS H6EA

DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION TYPE CERTIFICATE DATA SHEET NO H6EA This data sheet, which is part of Type Certificate Number H6EA, prescribes conditions and limitations under which the product for which the Type Certificate was issued meets the airworthiness requ irements of the Federal Aviation Regulations. Type Certificate (TC) Holder: Type Certificate Holder Record Erickson Incorporated, DBA Erickson Air-Crane 3100 Willow Springs Road Central Point, Oregon 97502-0010 Erickson Air-Crane Incorporated, DBA Erickson Air-Crane transferred TC H6EA to Erickson Incorporated, DBA Erickson Air-Crane on August 13, 2014 Erickson Air-Crane Co., L.L.C. transferred TC H6EA to Erickson Air-Crane Incorporated, DBA Erickson Air-Crane on February 14, 2001 Erickson Air-Crane Co. transferred TC H6EA to Erickson Air-Crane Co., L.L.C. on August 22, 1997 Sikorsky Aircraft transferred TC H6EA to Erickson Air-Crane Co. on February 13, 1992. I. MODEL NUMBER: S-64E (Transport Category Rotorcraft) (See ALL MODEL Section) (See NOTES Section) Approved: 08 /21/69 Engines: Fuel: Engine Limits: 2 Pratt & Whitney JFTD12A-4A (with Hamilton Standard Fuel Control JFC56-4) Aviation Kerosene Jet A or Jet A-1 or Jet B or JP-4 or JP-5 or JP-8 or JP-8 +100 (conforming to Pratt & Whitney Aircraft SB 2016) Sea Level Static, Standard Day Conditions SHAFT HP POWER TURBINE RPM GAS GEN POWER TURBINE RPM INLET TEMP (TS) Takeoff (5 min) 4,500 9,500(105%N2) 16,700(104.2%N1) 688° C One engine inoperative (30 min) 4,500 9,500(105%N2) 16,700(104.2%N1) 688° C Maximum continuous Allowable maximum overspeed Acceleration limit (2 min) 4,000 -- -- 9,500(105%N2) 10,350(114%N2) -- 16,700(104.2%N1) 16,700(104.2%N1) -- 655° C -- 688° C Takeoff and maximum continuous horsepower ratings are normally obtained at a power turbine speed of 9,000 rpm (100%N2) Total power for two-engine operation is limited to 6,600 s.hp. for takeoff, and 5,400 s.hp. maximum continuous. Revision 18 Erickson Air-Crane S-64E H6EA 2 of 6 Rotor Limits: Power Off Max 110% Nr (204 r.p.m.) Min 89% Nr (165 r.p.m.) Power On Max 104% Nr (193 r.p.m.) Min 100% Nr (185 r.p.m.) Airspeed Limits: V NE (never exceed) 114 m.p.h. (99 knots) at 42,000 lb gross weight. For increased airspeed limits at lower gross weights and variation of V NE with altitude refer to Rotorcraft Flight Manual. C.G. Range: (+328.0) to (+353.0) at 23,000 lb (+324.0) to (+353.0) at 30,000 lb (+328.0) to (+353.0) at 38,000 lb (+328.0) to (+346.0) at 38,000 lb 42,000 GROSS WEIGHT (POUNDS) 38,000 30,000 23,000 324 328 Station--Inches 346 353 (+328.0) to (+346.0) at 42,000 lb Empty Weight C.G. Range: Datum: Leveling Means: Maximum Weight: Number of Seats: Maximum Baggage: None 336 inches forward of main rotor centroid Plumb line from top level plate inside cockpit aft door 42,000 lb 5. 2 at (+94.0), 1 at (+108.5), 1 at (+127.0), 1 at (+130.0). 500 lb at (+124.0) Two baggage compartments with a maximum allowable floor loading of 300 p.s.f. and a total allowable load of 250 lb each compartment. See NOTE 3 for information pertaining to the carriage of external loads. Fuel Capacity: Oil Capacity: 1356 gal. (454 gal. at (+280.8), 454 gal. at (+397.3), 448 gal. at (+461.3)). 2.6 gal. (+234.0) (2 tanks 1.3 gal. each). See NOTE 1 for data on system fuel and oil. Rotor Blade & Control Movements: For rigging information, refer to Maintenance Manual. Serial Numbers Eligible: 64002,64003,64015,64016,64017,64018,64019,64022,64025,64027, 64028,64033,64034D,64037,64038,64042,64043,64050,64052,64058, 64061,64064,64065,64066,64079,64099,64101,641001,64E3001, and subsequent. 3 of 6 H6EA Certification Basis: FAR 29, 1 February 1965, including Amendments 29-1 and 29-2 except FAR 29.855(d), and Special Conditions No. 29-014-SC. For S-64E models incorporating Composite Main Rotorblades, §29.571 amendment 29-55 has been added in addition to the above certification basis. Type Certificate Application Date: 11/27/67. Type Certificate Issued: 08/21/69 The S-64E is designed and intended to be operated as an industrial flying crane. It is primarily intended to carry cargo in external load operations and the certification basis has been developed for that purpose. Special Conditions No. 29-014-SC include modifications to sections of FAR 29 considered appropriate for industrial flying crane operation without external loads under FAR 91 and for rotorcraft-load combinations meeting the requirements of Subpart D of FAR 133. II. MODEL NUMBER: Approved: Engines: S-64F (Transport Categorv Rotorcraft) (See ALL MODEL Section) (See NOTES Section) 11/25/70 2 Pratt & Whitney JFTDl2A-5A (with Hamilton Standard Fuel Control JFC56- 6) Fuel: Engine Limits: Aviation Kerosene Jet A or Jet A-1 or Jet B or JP-4 or JP-5 or JP-8 or JP-8+100 (conforming to Pratt & Whitney Aircraft SB 2016). Sea level static, standard day conditions SHAFT HP POWER TURBINE RPM GAS GEN RPM POWER TURBINE INLET TEMP (T5) Takeoff (5 min) One engine imperative (30 min) Maximum continuous Allowable maximum overspeed Acceleration limit (2 min) Starting limit (2 sec) 4,800 4,800 4,430 -- -- -- 9,500(105%N2) 9,500(105%N2) 9,500(105%N2) 10,350(114%N2) -- -- 16,700(104.2%N1) 16,700(104.2%N1) 16,700(104.2%N1) 16,700(104.2%N1) -- -- 720° C 720° C 675° C -- 720° C 525° C Takeoff and maximum continuous horsepower ratings are normally obtained at a power turbine speed of 9,000 rpm (100%N2) Total power for two-engine operation is limited to 7,900 s.hp. for takeoff, and 6,600 s.hp. maximum continuous. Rotor Limits: Power Off Max 110% Nr (204 r.p.m.) Min 95% N r (176 r.p.m.) Power On Max 104% Nr (193 r.p.m.) Min 100% Nr (185 r.p.m.) Airspeed Limits: VNE (never exceed) 120 m.p.h. (104 knots) at 47,000 lb gross weight. For airspeed limits at lower gross weights and variation of VNE with altitude refer to Rotorcraft Flight Manual. H6EA 4 of 6 C.G. Range: (+323.0) to (+349.0) at 23,000 lb (+323.0) to (+349.0) at 30,000 lb (+326.4) to (+349.0) at 38,000 lb (+326.4) to (+346.0) at 38,000 lb (+328.0) to (+346.0) at 42,000 lb (+328.0) to (+346.0) at 47,000 lb 47,000 - 42,000 GROSS WEIGHT (POUNDS) 30,000 23,000 323 328 346 349 Station--lnches Empty Weight C.G. Range: Datum: Leveling Means: Maximum Weight: Number of Seats: Maximum Baggage: None 336 inches forward of main rotor centroid Plumb line from top level plate inside cockpit aft door 47,000 lb 5. 2 at (+94.0). 1 at (+108.5), 1 at (+127.0), 1 at (+130.0). 500 lb at (+124.0). Two baggage compartments with a maximum allowable floor loading of 300 p.s.f. and a total allowable load of 250 lb each compartment. See NOTE 3 for information pertaining to the carriage of external loads. Fuel Capacity: Oil Capacity: 1,356 gal. (454 gal. at (+280.8), 454 gal. at (+397.3), 448 gal. at (461.3)). 2.6 gal. (+234.0) (2 tanks 1.3 gal. each). See NOTE 1 for data on system fuel and oil. Rotor Blade & Control Movements: For rigging information, refer to Maintenance Manual. Serial Numbers Eligible: 64081, 64084, 64085, 64086, 64091, 64093, 64097, 64067, 64078, 64080, 64088, 64089, 64090, 64095, 64098, 64F5001, and subsequent. Certification Basis: FAR 29 dated 1 February 1965 including Amendments 29-1 and 29-2 except FAR 29.855(d), and Special Conditions No. 29-014-SC. Type Certificate Application Date: 04/02/69 5 of 6 H6EA Type Certificate Amended: 11/25/70 The S-64F is designed and intended to be operated as an industrial flying crane. It is primarily intended to carry cargo in external load operations and the certification basis has been developed for that purpose. Special Conditions No. 29-014-SC include modifications to sections of FAR 29 considered appropriate for industrial flying crane operation without external loads under FAR 91 and for rotorcraft-load combinations meeting the requirements of Subpart D of FAR 133. THE FOLLOWING DATA IS PERTINENT TO ALL MODELS OF THIS SERIES: Production Basis: Production Certificate 716NM Equipment: The basic required equipment as prescribed in the applicable airworthiness regulations (see certification basis) must be installed in the aircraft for certification. In addition, the following items of equipment are required: (a) FAA Approved Rotorcraft Flight Manual and appropriate supplements. 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 fuel 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." NOTE3: NOTE4: Provisions for the carriage of external loads are available in the form of structural hard points on the fuselage and main landing gear; single point hoist; and a four point load leveler suspension system. Information concerning the operating limitations with this equipment is contained in the Rotorcraft Flight Manual. Information essential to the proper maintenance of the helicopter is contained in the manufacturer's Maintenance Manual provided with each helicopter. In addition to the maintenance manuals, the helicopters are to be serviced and maintained according to the following Service Bulletins: Model S-64E 1. Service Bulletin 64B General-2 for component maximum recommended time between overhaul. Model S-64F 1. Service Bulletin 64F General-2 for component maximum recommended time between overhaul. In addition, the following Airworthiness Limitations have been established for this Rotorcraft.: Model S-64E 1. Service Bulletin 64B General-1 for component retirement times. FAA approved by the Rotorcraft Certification Office (RCO). Model S-64F 1. Service Bulletin 64F General-1 Time Limits-Retirement Schedule. FAA approved. 2. Service Bulletin 64F General-3 Mandatory Structural Inspections. FAA approved. H6EA 6 of 6 NOTE 5: NOTE 6: NOTE 7: NOTE 8: Prior to Airworthiness certification as a Model S-64F helicopter, either a military Model CH-54B helicopter must be inspected and modified according to Erickson Air-Crane Document No. 1097 "Master Conversion Drawing List, CH-54B to S-64F ", or conforms to Erickson Air-Crane General Arrangement Drawing 6401-10015, Rev. D, or later FAA approved revision level. Prior to Airworthiness certification as Model S-64E helicopter , military Model CH-54A helicopters must be inspected and modified according to Erickson Air-Crane Document No. 1077, "Modification of CH-54A to S-64E Helicopter", or conforms to Erickson Air-Crane General Arrangement Drawing 6401-10021, Rev. IR, or later FAA approved revision level. Revision No. 5 to this TCDS was not published by the FAA. Both S-64E and S-64F models are also known as "Industrial Flying Crane Helicopters." ------END------