TCDS H15NM

Torque Pressure (PSI) Output Horsepower (HP) Output (RPM) Exhaust Gas Temp. (C°) Gas Gen Speed N1(%) Takeoff (30 min.) 50.0 1100 6600 610 - 625 101.5 Max. Cont. 50.0 1100 6600 400 –610 101.5 DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION H15NM Revision 4 Hagglund Helicopters, LLC UH-1H January 7, 2022 TYPE CERTIFICATE DATA SHEET NO. H15NM This data sheet, which is part of Type Certificate No. H15NM, prescribes conditions and limitations under which the product for which the type certificate was issued meets the airworthiness requirements of the 14 Code of Federal Aviation Regulations (14 CFR). Type Certificate Holder: Hagglund Helicopters, LLC 5101 NW A Avenue Pendleton, OR 97801 Type Certificate Holder Record: Western International Aviation, Inc. transferred ownership of TC H15NM to Hagglund Helicopters, LLC on January 24, 2001 I - Model UH-1H, (Restricted Category Rotorcraft) Approved March 25, 1994 Engine 1 - Lycoming T53-L-13B (See Note 10 For Alternative Engines) Fuel ASTM-D1655 (Jet A, Jet A-1, Jet B) (See Note 12 For Alternative Fuels) Engine Limits Refer to TM55-1520-210-10 for additional limitation data. Rotor Limits Power Off Power On Maximum r.p.m. 339 324 Minimum r.p.m. 294 294 Airspeed Limits Roof-mounted pitot static: VNE (never exceed speed) 124 knots up to 7500 lbs. Gross Weight, sea level to 2000 feet. Never exceed 113 knots up to 9500 lbs. Gross Weight, seal level to 2000 feet. Refer to TM55-1520-210-10, Chapter 5, Section V, for specific operating airspeed limitations. See Note 2 for specific operation airspeed limitation placards. Nose-Mounted Pitot static: Never exceed 112 knots up to 7500 lbs. Gross Weight, sea level to 2000 feet. Never exceed 103 knots up to 9500 lbs. Gross Weight, sea level to 2000 feet. Refer to TM55- 1520-210-10, Chapter 5, Section V, for specific operating airspeed limitations. See Note 2 for specific operation airspeed limitation placards. Page No. 1 2 3 4 5 Rev. No. 4 4 4 2 4 H15NM Page 2 of 5 C.G. Range Longitudinal C.G. Limits (+130.0) to (+144.0) at 7000 lbs. (+130.0) to (+144.0) at 8600 lbs. (+130.0) to (+134.0) at 9500 lbs. (+134.0) to (+143.0) at 9500 lbs. Straight line variation between points given. GROSS WEIGHT 9500 - (LBS.) 8600 - 7000 - 128 130 132 134 136 138 140 142 144 Station – Inches Lateral C.G. Limits Plus or Minus 7.5 in. Empty Weight C.G. Range (+130.0) to (+144.0) Datum Station 0, datum is 7.6 inches aft of the most forward point of the fuselage nose section. Leveling Means Plumb line from top of left main door frame to index plate on cabin floor. See Note 1. Maximum Weight 9500 lbs. Minimum Crew 1 (Pilot) at (+46.7) No. of Seats See Note 15 Maximum Baggage 100 lbs. per sq. ft. of cargo area. (See U.S. Army TM55-1520-210-10.) Fuel Capacity 208.5 U.S. gallons (+151.6) Crashworthy system. 220.0 U.S. gallons (+151.6) Non-crashworthy system. Oil Capacity 3.25 gallons (+173.0) Rotor Blade and For rigging information, refer to U.S. Army TM55-1520-210-23 (Maintenance Manual). Control Movements Serial No.’s Approved U.S. Military Surplus UH-1H Helicopters as identified in Hagglund Helicopters, LLC Report No. HH-200 dated March 28, 2001, or later FAA approved revisions. Current copy on file at the Los Angeles Aircraft Certification Office. Certification Basis Part 21 § 21.25(a)(2), effective February 1, 1965, including Amendments 21-1 through 21-42. Type Certificate No. H15NM, for the special purpose of: 1) Agricultural Operations under § 21.25(b)(1). Note: In accordance with § 36.1(a)(4), compliance with the noise requirements was not shown. Therefore, aircraft certified under this type certificate are only eligible for agricultural operations excepted by § 36.1(a)(4) and defined under § 137.3. 2) Forest and Wildlife Conservation under § 21.25(b)(2) Certificaton Basis (cont’d) Note: In accordance with § 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 § 36.1(a)(4) and defined under §137.3. H15NM Page 3 of 5 Certification Basis (cont’d) 3) External Load Operation under § 21.25(b)(7) Note: In accordance with part § 36.1(a)(4), compliance with the noise requirements was not shown. Therefore, aircraft certificated under this type certificate are only eligible for external loads operations excepted by § 36.1(a)(4) and defined under §133.1(b). General Note: 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. Date of Application: November 5, 1993. Production Basis None. Prior to original certification of each aircraft, a FAA representative must perform a detailed inspection for workmanship, materials, and conformity with the approved technical data following a check, by the type certificate holder, of the flight characteristics in accordance with all applicable portions of Section II of the U.S. Army Technical Manual TM55-1520-242-MTF Maintenance Test Flight Manual, Army Model UH-1, EH-1 Helicopter, Change 1, dated December 19, 1986, as appropriate for each aircraft, or other FAA approved manual. Equipment Equipment necessary for the particular special purpose operation must be installed. Each helicopter is required to incorporate modifications as specified in Hagglund Helicopter, LLC’s Special Purpose Modifications, Report No. HH-600, N.C., dated October 22, 2001, or later FAA approved revisions. 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 helicopter at the time of original airworthiness certification. Refer to Chapter 6 of Operator’s Manual, TM55-1520-210-10 and Maintenance Manual TM55-1520-210-23, Paragraph 1-36 for leveling means and weight and balance determination. NOTE 2. The following placards must be prominently displayed in the cockpit in full view of the pilots as appropriate: Placard No. 1: CALIBRATED AIRSPEED-KNOTS With Roof Mounted Pitot Static LIMITS AIRCRAFT WT/KIAS GROSS WEIGHT Density Alt. (Ft.) To 7500 lbs. 8500 lbs. 9500 lbs. SL to 2000 124 118 113 3000 121 115 110 6000 112 106 101 9000 103 97 92 12000 94 88 83 15000 82 76 - 18000 70 - - UNDER 7500 LBS. GW USE 6000 TO 6600 RPM RANGE OVER 7500 LBS. GW USE 6400 TO 6600 RPM RANGE POWER OFF 294 TO 339 ROTOR RPM REDUCE SPEED WHEN VIBRATION IS EXCESSIVE H15NM Page 4 of 5 NOTE 2 (Cont’d) CALIBRATED AIRSPEED-KNOTS With Nose Mounted Pitot Static LIMITS AIRCRAFT WT/KIAS GROSS WEIGHT Density Alt. (Ft.) To 7500 lbs. 8500 lbs. 9500 lbs. SL to 2000 112 107 103 3000 109 104 100 6000 100 95 91 9000 91 86 82 12000 82 77 73 15000 70 65 - 18000 58 - - UNDER 7500 LBS. GW USE 6000 TO 6600 RPM RANGE OVER 7500 LBS. GW USE 6400 TO 6600 RPM RANGE POWER OFF 294 TO 339 ROTOR RPM DECREASE AIRSPEED IF VIBRATION IS EXCESSIVE Placard No. 2: “THIS ROTORCRAFT MUST BE OPERATED IN ACCORDANCE WITH THE RESTRICTED CATEGORY OPERATING LIMITATIONS OF 14 CFR part 91 § 91.313.” Placard No. 3: “THIS HELICOPTER MUST BE OPERATED IN COMPLIANCE WITH THE OPERATING LIMITATIONS SPECIFIED IN THE APPROVED HELICOPTER OPERATORS MANUAL. REFER TO TM55-1520-210-10, CHAPTER 5, FOR OPERATING LIMITS AND RESTRICTIONS.” Placard No. 4: “VFR OPERATIONS ONLY.” The Builder’s Data Plate required by § 45.13 must be installed in accordance with Drawing HH-001, dated June 12, 2001, or later FAA approved revisions. NOTE 3. The helicopter(s) must be serviced, maintained, inspected, repaired, and overhauled in accordance with the documents specified in Hagglund Helicopters, LLC Instructions For Continued Airworthiness Report No. HH-300, dated April 4, 2001, or later FAA accepted revision, or inspected in accordance with other FAA accepted inspection program. The TC Holder’s Instructions For Continued Airworthiness Report is part of the TC Holder’s Instructions For Continued Airworthiness. NOTE 4. In addition to the standard helicopter requirements, the following additional data and/or helicopter configuration requirements must be met for each individual model UH-1H helicopter upon application for an original Special Airworthiness Certificate: A. Each helicopter must pass a conformity inspection in accordance with Hagglund Helicopters, LLC Engineering Configuration Report No. HH-100, dated September 10, 2001, or later FAA approved revision. The Configuration Report identifies any military Maintenance Work Orders accomplished on that particular helicopter, and a description of the modification(s) accomplished on that particular 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. B. The maintenance, overhaul and modification records of each helicopter must be reviewed for military changes that may affect the airworthiness of the helicopter. H15NM Page 5 of 5 NOTE 4 (Cont’d) 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. D. An FAA representative must perform a detailed inspection for workmanship, materials, and conformity with the approved technical data following a check, by the type certificate holder, of the flight characteristics in accordance with all applicable portions of Section II of the U.S. Army Technical Manual TM55 - 1520-242-MTF Maintenance Test Fligh t Manual, Army Model UH -1, EH-1 Helicopter, Change 1, dated December 19, 1986, as appropriate for each aircraft, or other FAA approved manual. 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 owners/operator’s business which is other than air transportation. NOTE 6. This helicopter must be operated in accordance with a Flight Manual comprised of the following: (1) Department of the Army Technical Manual No. TM55-1520-210-10, “Operator’s Manual, Army Model UH-1H/V Helicopters”, dated 15 February 1988, with Changes 1-19. NOTE 7. Restricted category aircraft may not be operated in a foreign country without express written approval of that country. NOTE 8. 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 9. E ngine 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 military records and have the applicable FAA Airworthiness inspections accomplished. NOTE 10. Alternative approved engines are: 1 – Lycoming T53-L-13; 1 – Lycoming T53-L-13BA NOTE 11. An acceptable method of determining engine cycles from engine total operating time is contained in Hagglund Helicopters, LLC Report No. HH-500, dated December 6, 2001, or later FAA approved revision. This may be used when converting military operating hours to commercial equivalent cycles at the time of initial airworthiness conformity. NOTE 12. Alternative and emergency fuels are listed in TM55-1520-210-10, Operators Manual Army Model UH-1H/V Helicopters, Chapter 2, Section XVL. Some limitations apply for the use of certain alternate and emergency fuels. These limitations are listed in this section. NOTE 13. The Airworthiness Directives for the helicopter(s) and engine(s) are contained in Hagglund Helicopters, LLC Report No. HH-400, dated March 28, 2001, or latest FAA approved revision must be complied with prior to original certification. NOTE 14. Any alteration to the type design of this aircraft may require Instructions For Continued Airworthiness. These instructions must be submitted to and accepted by the FTW-AEG, Aircraft Evaluation Group Office prior to approval for return to service. NOTE 15. No Person may be carried in this helicopter during flight unless that person is essential to the intended purpose of the flight. END