TCDS R00008LA

Page No. 1 2 3 4 5 6 Rev. No. 2 - 2 2 2 2 DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION TY PE CERTIFICATE DATA SHEET NO. R00008LA Thi s data sheet, which is a part of the Type Certificate R00008LA, prescribes conditions and limitations under which the product for which the type certificate was issued meets the airworthiness requirements of the Federal Aviation Regulations. Ty pe Certificate Holder: Siller Helicopters 1250 Smith Road Yuba City, CA 95991 Ty pe Certificate Ownership Record: N/A I - Mo del SH-3A (S-61A) (Restricted Category Military Surplus Rotorcraft) Approved July 21, 2000 (See NOTES Section). Engi nes (2) General Electric T58-GE-100. (Optional Engines See Note 12) Fue l Aviation Kerosene, JP4 or JP5 ( General Electric Co. Spec. No. D50T1011 or subsequent revisions thereto). Engi ne Limits Sea Level Static - Standard Day (See Note 13) ENGINE LIMITS: (T58-GE-100) Torque (%Q) Power Turbine Speed (%Nf) Gas Generator Speed (% Ng) Power Turbine Inlet Temp (T5) Takeoff (5 Min) 103 112 103.4 721 OEI (30 min) 123 112 103.4 721 OEI (2-1/2 min) 123 112 103.4 745 Maximum Continuous 86 112 101.8 685 Max Transient (2 Sec.) NA NA NA 840 Starting Allowable Max (2 Sec) NA NA NA 949 Overspeed (15 Sec.) Note 15 122 105 NA ENGINE LIMITS: (CT58-140-2) Torque (%Q) Power Turbine Speed (%Nf) Gas Generator Speed (% Ng) Power Turbine Inlet Temp (T5) Takeoff (5 Min) 103 112 100 696 OEI (30 min) 123 112 100 696 OEI (2-1/2 min) 123 112 103.4 758 Maximum Continuous 86 112 100 660 Max Transient (2 Sec.) NA NA NA 840 Starting Allowable Max (2 Sec) NA NA NA 949 Overspeed (15 Sec.) Note 15 122 105 NA ENGINE LIMITS: (CT58-140-1, T58-GE-5, T58-GE-10) Torque (%Q) Power Turbine Speed (%Nf) Gas Generator Speed (% Ng) Power Turbine Inlet Temp (T5) Takeoff (5 Min) 103 112 100 696 OEI (30 min) 123 112 100 696 OEI (2-1/2 min) 123 112 102 721 Maximum Continuous 86 112 100 660 Max Transient (2 Sec.) NA NA NA 840 Starting Allowable Max (2 Sec) NA NA NA 949 Overspeed (15 Sec.) Note 15 122 105 NA R00008LA Revision 2 Siller Helicopters SH-3A August 07, 2026 Page 2 R00008LA Rotor Limits Max. 225 r.p.m. (112%) Min. 184 r.p.m. ( 91%) Transmission Torque Limits Single Engine Operation Transient torque meter readings from 112% to 130%, not to exceed 5 seconds. Transient torque meter readings above 130% are not permissible. Dual Engine Operation Transient torque meter readings from 95% to 112%, not to exceed 5 seconds. Transient torque meter readings above 112% are not permissible. Airspeed Limits Vne (Never exceed) speed 155 m.p.h. (130 knots) CAS. C.G. Range (+258.0) to (+259.6) at 19,100 lbs. to 22,000 lbs., Forward Limit (+276.0) to (+275.2) at 19,100 lbs. to 22,000 lbs., Aft Limit (+254.0) to (+280.0) at 16,000 lbs. or less. Straight Line Variation Between Points Given. (See chart.) 22,000 - GROSS WEIGHT 19,100 - (LBS.) 16,000 - Empty Weight C.G. Range None 254 258 276 280 Stations - Inches Datum 267.4 in. forward of main rotor centroid. Leveling Means Leveling plates on sill and upper frame of cargo door. Maximum Weight 19,100 lbs., see Note 18. Minimum Crew 2 - Pilot and Copilot. Number of Seats 2 - 2 at (+149.0) Maximum Cargo See Note 17. Fuel Capacity 700 gal. (347 gal. at 215.3, 353 gal. at 317.3). Oil Capacity 6.0 gal. (2 tanks 3 gal. each at 181.0). Rotor Blade & Control For rigging information, see Note 3. Movements Serial No.’s Approved Refer to Siller Helicopters Serial Numbers Eligible Report No. SH61001, NC, dated July 21, 2000, or later FAA approved revision. A current copy is on file at the Los Angeles ACO. Certification Basis FAR 21.25(a)(2) effective February 1, 1965, with Amendments 21-1 through 21-42. Type Certificate No. R00008LA issued July 21, 2000 for the Special Purpose(s) of: Page 3 R00008LA Certification Basis (cont’d) (1) Agricultural Operations under FAR 21.25(b)(1). Note: In accordance with FAR 36.1(a)(4), compliance with the noise requirements was not shown. Therefore, aircraft certificated under this type certificate are only eligible for agricultural operations excepted by FAR 36.1(a)(4) and defined under FAR 137.3 (2) Forest and Wildlife Conservation Operations under FAR 21.25(b)(2). Note: In accordance with FAR 36.1(a)(4), compliance with the noise requirements was not shown. Therefore, aircraft certificated under this type certificate are only eligible for dispensing fire fighting materials excepted by FAR 36.1(a)(4) and defined under FAR 137.3 (3) External Load Operations under FAR 21.25(b)(7). Note: In accordance with FAR 36.1(a)(4), compliance with the noise requirements was not shown. Therefore, aircraft certificated under this type certificate are only eligible for external load operations excepted by FAR 36.1(a)(4) and defined under FAR 133.1(b). Any alteration to the aircraft for Special Purposes not identified above require further FAA approval and in addition may require noise and / or flight testing. General Note: Any subsequent modifications to the helicopters type certified under this Type Certificate are to have the certification basis for that modification established under 14 CFR 21.101 published June 7, 2000 which became effective June 10, 2003. Otherwise non-significant modifications are to meet the requirements of CAR 7 airworthiness standards, transport category, including Amendment 7-4, effective October 1959, plus special conditions for turbine engine installations and 14 CFR 29.1529, Instructions for Continued Airworthiness, Amendment 20, effective September 11, 1980. Date of Application August 18, 1997 Production Basis None. No helicopter may be produced under this approval. Prior to adding serial numbers to this Type Certificate, each candidate helicopter must undergo a conformity inspection. The conformity inspection will be conducted in accordance with a Type Inspection Authorization, Part 1, or request for conformity that will include as a minimum, the inspections contained in the FAA Rotorcraft Directorate Restricted Category conformity document dated September 25, 2001 or later FAA approved revisions. Equipment Equipment necessary for the particular special purpose operation must be installed. NOTES NOTE 1 A current weight and balance report including a list of equipment included in the certificated empty weight, and loading instructions when necessary, must be provided for each aircraft at the time of original certification. Refer to Siller Helicopters RFM Document No. SH61005, “Rotorcraft Flight Manual for Model SH-3A Helicopter,” dated June 16, 2026 or later FAA approved revisions for C.G determination. Page 4 R00008LA NOT E 2 The following placards must be prominently displayed in the cockpit in full view of the pilots. P lacard No. 1 " THIS ROTORCRAFT MUST BE OPERATED IN ACCORDANCE WITH THE RESTRICTED CATEGORY OPERATING LIMITATIONS OF FAR 91.313." P lacard No. 2 “ THIS HELICOPTER MUST BE OPERATED IN COMPLIANCE WITH THE OPERATING LIMITATIONS SPECIFIED IN THE APPROVED HELICOPTER OPERATORS MANUAL. REFER TO RFMS #SH6I005 CHAPTER 4 FOR OPERATING LIMITS AND RESTRICTIONS.” P lacard No. 3 " VFR OPERATIONS ONLY." T he builder’s data plate required by FAR 45.13 must be installed in accordance with drawing SH-76, N.C., dated April 21, 1998 or later FAA approved revisions. NOT E 3 The helicopter(s) must be serviced, maintained, inspected, repaired, and overhauled in accordance with the documents specified in Siller Helicopters Instructions for Continued Airworthiness Maintenance Report No. SH61006, Revision 2, dated January 24, 2023, or later FAA accepted revisions or inspected in accordance with other FAA accepted inspection programs. The TC holder’s Instructions for Continued Airworthiness Report is part of the TC holder’s Instructions for Continued Airworthiness. NOT E 4 Prior to obtaining an original Airworthiness Certificate: ( A) Each helicopter must pass a conformity inspection in accordance with S iller Helicopters Engineering Report No. SH61002, NC, dated January 7, 1998, or later FAA approved revision. The Engineering R eport also identifies the special purpose modification(s) accomplished o n that particular helicopter. The Engineering Report identifies military airframe changes (AFC) accomplished on the helicopter. In addition, each helicopter must pass an inspection for any possible hidden damage and the military records reviewed for acceptability of any repairs or alterations. Navy Airframe Change 450 (or equivalent work instructions outlined in the Instructions for Continued A irworthiness) must be accomplished on the aircraft prior to c ertification. (B) The maintenance, overhaul and modification records of each helicopter must be reviewed for military changes that may affect the airworthiness of the helicopter. ( C) After the required inspections, the aircraft must be found to be in a good state of preservation, repair, and in a condition for safe operation. Page 5 R00008LA NOTE 5 This aircraft is prohibited from carrying cargo for compensation or hire. Carriage of cargo is limited to such cargo that is incidental to the aircraft owner/operator’s business which is other than air transportation. NOTE 6 Restricted Category aircraft may not be operated in a foreign country without the express written approval of that country. NOTE 7 This aircraft has not been shown to meet the requirements of the applicable comprehensive and detailed airworthiness code as provided by Annex 8 to the Convention on International Civil Aviation. NOTE 8 Engine changes are allowed provided the replacement engine is of the same make and model as identified in this TCDS. The replacement engine must have proper records and have the applicable FAA Airworthiness inspection accomplished. Installed engines must be of the same make and model as approved on the TCDS. NOTE 9 The Airworthiness Directives for the helicopter and engines contained in Siller Helicopters Airworthiness Directives Compliance Report No. SH61007 dated January 7, 1998, or later FAA approved revisions, must be complied with prior to original airworthiness certification. NOTE 10 The service life limited parts overhaul and retirement intervals for these helicopters is specified in Siller Helicopters Instructions For Continued Airworthiness Report, Report No. SH61006, Revision 2, dated January 24, 2023, or later FAA approved revisions. NOTE 11 The helicopter must be operated in accordance with a Flight Manual comprised of the following: 1) NOTE DELETED. 2) Siller Helicopters RFM Document No. SH61005, “Rotorcraft Flight Manual for Model SH-3A Helicopter.”, dated June 16, 2026 or later FAA approved revision. NOTE 12 Optional Engine Installation: (2) General Electric CT58-140-1 (with Hamilton Standard Fuel Control JFC-26). (2) General Electric T58-GE-5. (2) General Electric T58-GE-10. (2) General Electric CT58-140-2 (with Hamilton Standard Fuel Control JFC-26.) NOTE 13 Installation of all engine models require: a. NOTE DELETED. b. Main gearbox part number S6135-20600-27, -33, -39 and subsequent installed. c. Left engine cowl inst., part number S6130-80050 modified for increased cooling provisions per Sikorsky Service Instructions No. 61-3A. d. Tail pipe assembly, part number S6130-80169-1, installed (bolt on versus clamp). e. Tube installation - air bleed dump RH, part number S6120-62342-6, installed. f. Engine Inlet Duct Assy. S6130-80165 installed. g. Installation of Naval Airframe Change 450 (or equivalent work instructions outlined in the Instructions for Continued Airworthiness) Page 6 R00008LA NOTE 14 Maximum continuous total power for two-engine operation is limited to 2100 hp. NOTE 15 With two engines operating take-off power may exceed torque = 103% on one engine to a maximum of torque = 123% provided that the torque on the other engine is less than 103% and the sum of the individual torque values does not exceed 206%. Transient operation between 206% and 230% total torque is permitted for periods of not over 5 seconds for each occurrence. Operation between 206% and 230% total torque for more than 5 seconds or over 230% total torque for any period requires removal and overhaul of the main gearbox. With one engine operating transitory over-torque on the order of 150% Q is permissible provided the over-torque period does not exceed 20 seconds per application and the cumulative time above 135% Q does not exceed 30 minutes during the transmission overhaul period. Torque values and duration above 135% must be recorded. . NOTE 16 If takeoff power (CT58-140-1 or CT58-140-2) is used in cumulative excess of 5 minutes during any one emergency, the engine must be inspected in accordance with GE Commercial Maintenance Manual SEI-182, Revision 8 dated December 31, 1996 or later FAA approved revision. NOTE 17 Provisions for the carriage of external loads are available in the form of structural hard points on the fuselage and single point hook. Information concerning the operating limitations with this equipment is contained in the Flight Manual. NOTE 18 Maximum takeoff and landing weight is 19,100 lbs., except in FAR 133 rotorcraft-external load operations where the maximum rotorcraft-load combination weight is 22,000 lbs. The external load must be jettisonable so that the rotorcraft weight is not more than 19,100 lbs. NOTE 19 Any alteration to the type design of this aircraft may require Instructions for Continued Airworthiness. These instructions must be submitted and accepted by AED, Aircraft Evaluation Division, prior to approval for return to service. NOTE 20 NOTE DELETED. NOTE 21 NOTE DELETED.. NOTE 22 NOTE DELETED. NOTE 23 NOTE DELETED. NOTE 24 No Person may be carried in this helicopter during flight unless that person is essential to the purpose of the flight. END