TCDS H2EA

Page No. 1 2 3 4 5 6 Rev. No. 4 4 4 4 3 3 DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION H2EA Revision 4 SIKORSKY S-61A (U.S. Navy SH-3A, HSS-2) (USAF CH-3B) S-61D (U.S. Navy SH-3D) S-61E (U.S. Navy RH-3A) S-61V (U.S. Navy VH-3A, HSS-22) December 7, 2012 TYPE CERTIFICATE DATA SHEET NO. H2EA This data sheet which is a part of type certificate No. H2EA prescribes 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 Sikorsky Aircraft Corporation 6900 Main Street Stratford, Connecticut 06615-9129 I - Model S-61A (Restricted Category), approved April 13, 1967. Engine 2 General Electric T 58-GE-8B (for SH-3A and HSS-2) 2 General Electric T58-GE-1 (for CH-3B) Fuel Aviation Kerosene JP4 or JP5 (General Electric Co. Spec. No. D50TF2 or subsequent revisions thereto.) Engine limits Shaft Power Gas Power Turbine H P T u r b i n e R . P . M . Gen. R.P.M. Inlet (T5) Military Power 1250 21275 26300 677°C (1250°F) (30 min.) Normal Cont. 1050 21275 26300 635°C (1175°F) Cruise Rotor Limits Maximum 238 r.p.m. (117%) Minimum 184 r.p.m. (91%) Airspeed limits Never exceed 144 knots IAS C.G. range 258.0 to 276.0 Maximum weight 19,100 lb. Maximum Crew 2 (pilot, co-pilot) Fuel capacity 698 gal. (345 gal. fwd. tank, 353 gal. aft tank for Models SH-3A and HSS-2) 1,141 gal. (347 gal. fwd. tank, 353 gal. aft ta nk, 441 gal. auxiliary tank for CH-3B) Oil capacity 6 gal. (two tanks, 3 gal. each) H2EA Page 2 of 6 I - Model S-61A (Restricted Category), approved April 13, 1967. (Cont'd) Other operating Models SH-3A and HSS-2: Naval Air Training and Operating Procedures limitations Standardization ( NATOPS) Flight Manual, Navy Model SH-3A Helicopters, NAVAIR 01-230HLC-1, dated 15 September 1966. Mode l CH- 3B: USAF Flight Manual, USAF Series CH-3B Helicopter, T.O. 1H- 3(C)B-1, dated 30 August 1966. Serial Nos. eligible See latest revi sion of FAA-approved Sikorsky Report SER-611975 II - Model S-61D (Restricted Category), approved April 13, 1967. Engine 2 General Electric T58-GE-10 Fuel Aviation Kerosene JP4 or JP5 (General Electric Co. Spec. No. D50TF2 or subsequent revisions thereto.) Engine limits Shaft Power Gas Power Turbine H P T u r b i n e R . P . M . Gen. R.P.M. Inlet (T5) Military Power 1400 21275 26300 696°C (1285°F) (30 min.) Normal Cont. 1250 21275 26300 660°C (1220°F) Cruise Rotor Limits Maximum 238 r.p.m. (117%) Minimum 184 r.p.m. (91%) Airspeed limits Never exceed 144 knots IAS C.G. range 258.0 to 276.0 Maximum weight 19,100 lb. Minimum Crew 2 (pilot, co-pilot) Fuel capacity 848 gal. (347 gal. fwd. ta nk, 148 gal. center tank, 353 gal. aft tank) Oil capacity 6 gal. (two tanks, 3 gal. each) Other operating Naval Air Traini ng and Operating Procedures Standardization (NATOPS) Flight limitations Manual, Navy Model SH-3D Helicopt ers, NAVAIR 01-230-HLE-1, dated 15 September 1966 Serial Nos. eligible See latest revi sion of FAA-approved Sikorsky Report SER-611975 III - Model S-61E (Restricted Category), approved April 13, 1967. Engine 2 General Electric T58-GE-8B Fuel Aviation Kerosene JP4 or JP5 (General Electric Co. Spec. No. D50TF2 or subsequent revisions thereto.) Page 3 of 6 H2EA III - Model S-61E (Restricted Category), approved April 13, 1967. (Cont'd) Engine limits Shaft Power Gas Power Turbine H P T u r b i n e R . P . M . Gen. R.P.M. Inlet (T5) Military Power 1250 21275 26300 677°C (1250°F) (30 min.) Normal Cont. 1050 21275 26300 635°C (1175°F) Cruise Rotor Limits Maximum 238 r.p.m. (117%) Minimum 184 r.p.m. (91%) Airspeed limits Never exceed 144 knots IAS C.G. range 258.0 to 276.0 Maximum weight 19,100 lb. Minimum Crew 2 (pilot, co-pilot) Fuel capacity 852 gal. (345 gal. fwd. tank, 353 gal. aft tank, 154 gal. auxiliary tank) Oil capacity 8.6 gal. (two tanks, 3 gal. each plus one auxiliary tank, 2.6 gal.) Other operating Naval Air Traini ng and Operating Procedures Standardization (NATOPS) Flight limitations Manual, Navy Model RH-3A Helicopt ers, NAVAIR 01-230-HLCA-1, dated 1 November 1966 Serial Nos. eligible See latest revi sion of FAA-approved Sikorsky Report SER-611975 IV - Model S-61V (Restricted Category), approved April 13, 1967. Engine 2 General Electric T58-GE-8C Fuel Aviation Kerosene JP4 or JP5 (General Electric Co. Spec. No. D50TF2 or subsequent revisions thereto.) Engine limits Shaft Power Gas Power Turbine H P T u r b i n e R . P . M . Gen. R.P.M. Inlet (T5) Military Power 1250 21275 26300 677°C (1250°F) (30 min.) Normal Cont. 1050 21275 26300 635°C (1175°F) Cruise Rotor Limits Maximum 238 r.p.m. (117%) Minimum 184 r.p.m. (91%) Airspeed limits Never exceed 144 knots IAS C.G. range 258.0 to 276.0 Maximum weight 19,100 lb. Maximum Crew 2 (pilot, co-pilot) Fuel capacity 698 gal. (345 gal. fwd. tank, 353 gal. aft tank) Oil capacity 6 gal. (two tanks, 3 gal. each) H2EA Page 4 of 6 IV - Model S-61V (Restricted Category), approved April 13, 1967. (Cont'd) Other operating Supplemental Handbook of Operation, Maintenance, and Repair Instructions with Parts limitations Breakdown, Navy Models VH-3A and SH-3A (BuNos 147145 and 148037) Helicopters, NAVAIR 01-230HLY-23, dated 15 January 1967 and Naval Air Training and Operating Procedures Standardization (NATOPS) Fli ght Manual, Navy Model SH-3A Helicopters, NAVAIR 01-230-HLC-1, dated 15 September 1966 Serial Nos. eligible See latest revi sion of FAA-approved Sikorsky Report SER-611975 Data Pertinent to All Models Datum 267.4 inches forward of the main rotor centroid Certification Basis FAR 21.25 (a ) 2 effective February 1, 1965 Type Certificate No. H2EA issued April 13, 1967, for the special purpose of transportation of cargo in the furtherance of the operator's or lessee's business only. Date of Application for Type Certificate: February 27, 1967. Production Basis None. No helicopters may be produced under this approval. Equipment Equipment necessary for the particular special purpose operation must be installed (See NOTE 3). NOTE 1. Current weight and balance report including a list of equipment included in the certificated empty weight, and loading instructions when necessary, must be in each helicopter at the time of original airworthiness certification and all times thereafter. Refer to Handbook of Weight and Balance NAVAIR 01-1B-40 for Models S-61D and S-61E and to Handbook of Weight and Balance NAVAIR 01-1B-50 for Models S-61A and S-61V. NOTE 2. These helicopters must be serviced and maintained in compliance with Periodic Maintenance Requirements Manual NAVWEPS 01-230HLC-6 and with the following handbooks: Model S-61A: Handbook of Maintenance Instructions NAVAIR 01-230HLC-2; Mode l S-61D: Handbook of Maintenance Instructions 01-230HLE-2; Model S-61E: Handbook of Maintenan ce Instructions 01-230HLCA-2; Model S-61V: Handbook of Maintenance Instructions 01-230HLC -2 and Supplemental Handbook of Operation, Maintenance, and Repair Instructions with Parts Breakdown NAVAIR 01-230HLY-23. NOTE 3. Modifications to these rotorcra ft or special equipment will be necessary, reference FAR 21.25(a)(2), prior to civil airworthiness certification for th e special purpose of transportation of cargo. NOTE 4. See latest revision of F AA-approved Sikorsky Report SER-611975 for S-61A serial number eligibility information. NOTE 5. Prior to the civil airworthiness certification, co mpliance with the latest revision of FAA-approved Sikorsky Report SER-611974 must be accomplished. Page 5 of 6 H2EA NOTE 6. Service life limited parts must be retir ed in accordance with the following schedule: Part No. Service Life (Hours ) Main Rotor Blades S6115-20101 2000 Tail Rotor Blades S6115-30001 3000 S6115-30001-1 3000 Tail Rotor Hub S6110-33003 2200 Tail Rotor Spindle S6110-33006 850 Primary Servo Trunnion Assembly S6165-20232 7700 Swashplate Guide S6135-20553-1 5200 Main Transmission S6135-20011-1 3600 Upper Housing S6135-20011-6 3600 Primary Servo Housing Assembly S6165-20202 8100 Rotary Wing Head Damper S6110-26019-0 3400 Piston Rod Assembly S6110-26019-1 3400 NOTE 7. The following placard must be prominently disp layed in the cockpit in full view of the pilots: "This rotorcraft must be operated in accordance with the restricted category operating limitations of FAR 91.39." NOTE 8. Certain serial number airc raft listed in Sikorsky Report SER-611975 are also eligible with the accomplishment of certain applicable fuselage modifications (NOTE 5) and installation of optional engines listed below. Optional engines eligible for installation and the applicable limitations: (See NOTE 12) Engines (2): (a) General Electric CT58-140-1 (w ith Hamilton Standard Fuel Control JFC-26). Engines Limits: Sea Level Static - Standard Day Shaft Power Gas Power Turbine H P T u r b i n e R . P . M . Gen. R.P.M. Inlet (T5) Takeoff (5 min.) 1400 21275 (112%Nf) 26300(100%Ng) 1285°F(696°C) One Engine Inoperative 1400 21275 (112%Nf) 26300(100%Ng) 1285°F(696°C) (30 min.) (See NOTE 11) One Engine Inoperative 1500 21275 (112%Nf) 26800(102%Ng) 1330°F(721°C) (2 1/2 min.) Maximum Continuous 1250 21275 (112%Nf) 26300(100%Ng) 1220°F(660°C) Maximum Transient 1545°F(840°C) (2 sec.) Starting (2 sec.) 1740°F(950C) Allowable Maximum Overspeed (15 sec.) 23100(122%Nf) 27600(105%Ng) Takeoff and Maximum continuous horsepower ratings are normally obtained at a power turbine speed of 18,966 r.p.m. (100%Nf). Total power for two engine operation is limited to 2,500 hp. for takeoff. Maximum continuous total power for two engine operation is limited to 2100 hp. See NOTE 9 for variations of sea level static power limit below 59°F. The use of engine Model CT58-140-1 is permitted only when: a. Main gearbox part number S6135-20600-27, -3, or -39 is installed. b. Left engine cowl inst., part number S6130-80140-3, is used. c. Tail pipe assembly, part number S6130- 80169-1, is installed (bolt-on versus clamp). d. Tube installation - air bleed dump R. H., part number S6120-62342-6, is installed. e. Engine Inlet Duct Assy. S6130-80179-2 is installed. H2EA Page 6 of 6 NOTE 9. Below 59°F the sea level sta tic power limits vary as follows: CT58-140-1 2 1/2 Min. Helicopter Increases linearly from 1500 hp. at 59°F to 1545 hp. at -65°F. Takeoff and 30 Min. Increases linearly from Helicopter 1400 hp. at 59°F to 1510 hp. at 22°F and to 1540 hp. at -65°F. Max. Continuous Increases linearly from 1250 hp. at 59°F to 1390 hp. at 39°F and flat rated at 1390 hp. at 39°F and below. NOTE 10. Tail rotor blade S6117-30101-041, -042, and -043 are not usable on these models. NOTE 11. If takeoff power is used in cumu lative excess of five minutes during any one emergency, the engine must be inspected in accordance with G.E. Commercial E ngine Service Memorandum CT58-110-1, Maintenance No. 19, April 17, 1962. NOTE 12. If any ratings on the CT58-140 series engines are ex ceeded refer to G.E. Engine Maintenance Manual No. SEI-182, Revision 7, November 1979. ...END...