TCDS R00035LA

DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION TYPE CERTIFICATE DATA SHEET R00035LA This data sheet, which is a part of Type Certificate No. R00035LA prescribes conditions and limitations under which the product for which the type certificate was issued meets the airw orthiness requirements of the 14 Code of Federal Aviation Regulations (14 CFR). TYPE CERTIFICATE (TC) HALLUX AEROSPACE LLC HOLDER: 4147 Corporate Way Missoula, MT 59808 I - MODEL: UH-60A (Restricted Category Military Surplus Rotorcraft) Approved December 23, 2024. ENGINES: (2) General Electric T700-GE-700 Original (2) General Electric T700-GE-701C (Alternate) (2) General Electric T700-GE-701D/CC (Alternate) FUEL: Aviation Kerosene JP-4, JP-5, JP-8, Jet A, Jet A-1 or Jet B. *See NOTE 8 for alternate and emergency fuels. ENGINE LIMITS: (T700-GE-700) SHAFT HP POWER TURBINE RPM GAS GEN RPM POWER TURBINE INLET (TGT) Military Power (30 min.) 1,561 20,900 44,700 850º C Normal Cont. Cruise 1,318 20,900 44,700 775º C ENGINE LIMITS: (T700-GE-701C) SHAFT HP POWER TURBINE RPM/% GAS GEN RPM/% POWER TURBINE INLET (TGT) Contingency Rated Power (CRP) (2 1/2 min. OEI) 1,940 20,900/100 44,700/102 903º C Maximum Rating (10 Min. dual) 1,890 20,900/100 44,700/102 878º C Intermediate Rated Power (IRP) (30 min dual) 1,800 20,900/100 44,700/102 851º C Maximum Continuous Power (MCP) 1,662 20,900/100 44,700/102 810º C ENGINE LIMITS: (T700-GE-701D/CC) SHAFT HP POWER TURBINE RPM/% GAS GEN RPM/% POWER TURBINE INLET (TGT) Contingency Rated Power (CRP) (2 1/2 min. OEI) 1,940 20,900/100 44,700/102 903º C Maximum Rating (10 Min. dual) 1,890 20,900/100 44,700/102 878º C Intermediate Rated Power (IRP) (30 min dual) 1,800 20,900/100 44,700/102 851º C Maximum Continuous Power (MCP) 1,662 20,900/100 44,700/102 810º C Page No. 1 2 3 4 5 6 7 Rev. No. - - 1 - - - - R00035LA Revision 1 HALLUX AEROSPACE LLC UH-60A UH-60L January 6, 2025 Page 2 of 7 R00035LA Revision 1 TRANSMISSION LIMITS: TORQUE: (UH-60A) 110% Single Engine (No time limit) 100% Dual Engine (No time limit) ROTOR LIMITS: Max. 258 RPM Min. 232 RPM AIRSPEED LIMITS: V ne Power on: 193 knots IAS, (221 MPH). See document RFM-H1-001 “Rotorcraft Flight Manual for UH-60A & UH-60L Blackhawk Helicopter”, Revision IR, Dated November 8 2024, or later FAA-approved revision for variations of Vne with gross weight, pressure altitude, and temperature and for additional data. EMPTY WEIGHT C.G. RANGE: None DATUM: 341.2 inches forward of the main rotor centroid. LEVELING MEANS: Plumb bob in L/H cabin door frame to le veling plate on cabin floor. Ref. TM 1-1570-237-23. MAXIMUM WEIGHT: 22,000 lbs. MINIMUM CREW: 2 (pilot, copilot) NUMBER OF SEATS: 2 at Sta. 227.1; 1 at Sta. 262.0; 3 at Sta. 282.0; 3 at Sta. 320.7; 4 at Sta. 339.8; 4 at Sta. 387.2. Refer to RFM-H1-001 “Rotorcraft Flight Manual for UH-60A & UH-60L Blackhawk Helicopter”, Revision IR, Dated November 8 2024, or later FAA-approved revision for seat configuration and loading information. FUEL CAPACITY: 361.5 gallons; 2 tanks (LH & RH interchangeable). 359.7 gallons; 2 tanks (LH &RH interchangeable) (with fuel boost pumps installed). OIL CAPACITY: 7 quarts each engine. OTHER LIMITS: Refer to Hallux Aerospace LLC. document no. RFM-H1-001 “Rotorcraft Flight Manual for UH-60A & UH-60L Blackhawk Helicopter”, Revision IR, Dated November 8 2024, or later FAA approved revisions. Flight hours are counted from takeoff to landing. Page 3 of 7 R00035LA Revision 1 II – MODEL: UH-60L (Restricted Category Military Surplus Rotorcraft) Approved December 23, 2024. ENGINES: (2) General Electric T700-GE-701C (Original) (2) General Electric T700-GE-701D/CC (Alternate) FUEL: Aviation Kerosene JP-4, JP-5, JP-8, Jet A, Jet A-1 or Jet B. ENGINE LIMITS: (T700-GE-701C) SHAFT HP POWER TURBINE RPM/% GAS GEN RPM/% POWER TURBINE INLET (TGT) Contingency Rated Power (CRP) (2 1/2 min. OEI) 1,940 20,900/100 44,700/102 903º C Maximum Rating (10 Min. dual) 1,890 20,900/100 44,700/102 878º C Intermediate Rated Power (IRP) (30 min dual) 1,800 20,900/100 44,700/102 851º C Maximum Continuous Power (MCP) 1,662 20,900/100 44,700/102 810º C ENGINE LIMITS: (T700-GE-701D/CC) SHAFT HP POWER TURBINE RPM/% GAS GEN RPM/% POWER TURBINE INLET (TGT) Contingency Rated Power (CRP) (2 1/2 min. OEI) 1,940 20,900/100 44,700/102 903º C Maximum Rating (10 Min. dual) 1,890 20,900/100 44,700/102 878º C Intermediate Rated Power (IRP) (30 min dual) 1,800 20,900/100 44,700/102 851º C Maximum Continuous Power (MCP) 1,662 20,900/100 44,700/102 810º C TRANSMISSION LIMITS: TORQUE: (UH-60L) 135% Single Engine (No time limit) 120% Dual Engine, at or below 80 KIAS (No time limit) 100% Dual Engine, above 80 KIAS (No Time Limit) ROTOR LIMITS: Max. 258 RPM Min. 232 RPM AIRSPEED LIMITS: V ne Power on: 193 knots IAS, (221 MPH). See document RFM-H1-001 “Rotorcraft Flight Manual for UH-60A & UH-60L Blackhawk Helicopter Revision IR, Dated November 8 2024, or later FAA-approved revision for variations of Vne with gross weight, pressure altitude, and temperature. OTHER LIMITS: Refer to RFM-H1-001 “Rotorcraft Flight Manual for UH-60A & UH-60L Blackhawk Helicopter”, Revision IR, Dated November 8 2024, or later FAA approved revisions for additional limitation data. Page 4 of 7 R00035LA Revision 1 DATUM: 341.2 inches forward of the main rotor centroid. MAXIMUM WEIGHT: 22,000 lbs. MINIMUM CREW: 2 (pilot, copilot) NUMBER OF SEATS: 2 at Sta. 227.1; 1 at Sta. 262.0; 3 at Sta. 282.0; 3 at Sta. 320.7; 4 at Sta. 339.8; 4 at Sta. 387.2. Refer to RFM-H1-001 “Rotorcraft Flight Manual for UH-60A & UH-60L Blackhawk Helicopter”, Revision IR, Dated November 8 2024, or later FAA-approved revision for seat configuration and loading information. FUEL CAPACITY: 361.5 gallons; 2 tanks (LH & RH interchangeable). 359.7 gallons; 2 tanks (LH &RH interchangeable) (with fuel boost pumps installed). OIL CAPACITY: 7 quarts each engine. DATA PERTINENT TO ALL MODELS SERIAL NO. APPROVED: U.S. military surplus, UH-60A and UH-60L Blackhawk helicopters as identified in Hallux Aerospace’ Serial Number Approved Report Number RPT-H1-102, Rev. IR dated October 3, 2024, or later FAA approved revision. CERTIFICATION BASIS: Part 21 § 21.25(a)(2) effective February 1, 1965, including Amendments 21-1 through 21-42 for the special purposes listed in FAR 21.25 (b)(1)(2)(7). § 21.25(b) (1) Agriculture Operations § 21.25(b) (2) Forest & Wildlife Conservation § 21.25(b) (7) External Loads Note: In accordance with § 36.1(a) (4), compliance with the noise requirements was not shown. Therefore, aircraft certificated under this type certificate are limited to dispensing of firefighting materials when performing the special purpose listed in FAR 21.25(b)(2) Forest & Wildlife Conservation. Page 5 of 7 R00035LA Revision 1 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. This aircraft approved for Day or Night VFR operations only. Flight into known icing conditions is prohibited 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 part 21 § 21.101 published June 7, 2000 which became effective June 10, 2003. Otherwise non-significant modifications are to meet the requirements of 14 CFR 29 airworthiness standards, transport category, Amendment 1, effective August 12, 1965 and 14 CFR part 29 § 29.1529, Instructions for Continued Airworthiness, Amendment 20, effective September 11, 1980. DATE OF APPLICATION: September 6, 2023 PRODUCTION BASIS: None. No helicopters may be produ ced under this approval. No helicopter serial number may be added to this type certificate unless approved by the cognizant Aircraft Certification Office. EQUIPMENT: The basic required equipment necessary for the particular special purpose operation must be installed for certification. In addition, the following items of equipment must be on board the helicopter and available to the crew: Model UH-60A and UH-60L “Rotorcraft Flight Manual for UH-60A & UH-60L Blackhawk Helicopter:”, Document number RFM-H1-001, Revision IR, Dated November 8 2024, or later FAA-approved revision. NOTE 1: A current weight and balance report in cluding a list of equipment included in the certified empty weight, and loading instructions when necessary, must be provided for each helicopter at the time of original airworthiness certification. NOTE 2: All placards required by either the FAA-approved Rotorcraft Flight Manual, the applicable operating rules, or the Type Certification Data, must be installed on the helicopter. Required placards are contained in Hallux Aerospace LLC. Engineering Configuration Report RPT-H1-100, Rev. A dated September 30, 2024, or later FAA-approved revision, or any applied technical bulletins. NOTE 3: The helicopter(s) must be serviced, main tained, inspected, repaired and overhauled in accordance with the requirements specified in Hallux Aerospace LLC. document ICA- H1-001 “Instructions for Continued Airworthiness” Rev. B dated September 30, 2024, or later FAA accepted revision, or inspected in accordance with other FAA accepted inspection programs. The service life limited parts overhaul and retirement intervals for these helicopters is specified in the FAA-Approved airworthiness limitation sections of the ICA-H1-001. An FAA approved/accepted copy must accompany each helicopter on delivery. General Electric (GE) Aviation Unit and T 700 Intermediate Maintenance Manual SEI 671 Change 4, dated July 16, 2021 and General Electric (GE) T700 Depot Maintenance Manual SEI 676 Change 14 dated February 17, 2023 or later FAA-accepted revision, are an acceptable alternate method for servicing, maintaining, inspecting, repairing and overhauling General Electric GE T700-GE-700, T700-GE-701C and T700-GE-701D engines. Revisions to the above listed manuals must be submitted to the FAA Boston Aircraft Certification Office for review and concurrence before being submitted to the FAA Fort Worth Aircraft Evaluation Group for FAA-acceptance Page 6 of 7 R00035LA Revision 1 NOTE 4: This helicopter must be operated in accordance with the Operator Manual comprised of the following: “Rotorcraft Flight Manual for UH-60A and UH-60L Blackhawk Helicopter:”, Document number RFM-H1-001, Revision IR, Dated November 8 2024, or later FAA-approved revision. NOTE 5: This aircraft is prohibited from carryi ng cargo for compensation or hire. Carriage of cargo is limited to such cargo that is required to support the approved special purpose. NOTE 6: A Restricted Category helicopter may not be operated in a foreign country without the express written approval of that country. NOTE 7: This helicopter 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: Installation of T-700-GE-701D engine s in accordance with MWO: 1-1520-237-20-3, Modification Instructions for The Installation of T700-GE-701D Engines and Support Components On UH-60A Aircraft, and MWO: 1-1520-237-30-3, Modification Instructions for The Installation of the Auto Relight and Transient Droop Improvement For T700-GE-701D Engines On UH-60A Aircraft, is approved for the helicopter models: UH-60A helicopters under this type certificate. Performance information and limitations with T700-GE-701C or T700-GE-701D/CC engines are contained in Chapter 7A of “Rotorcraft Flight Manual for UH-60A and UH-60L Blackhawk Helicopter:”, Document number RFM-H1-001 Revision IR, Dated November 8 2024, or later FAA-approved revision. NOTE 9: The US Army Safety Messages that must be complied with for the helicopter and engine prior to certification are contained in Hallux Aerospace LLC Airworthiness Directives, Military Message, & Technical Publications Listing document RPT-H1-104, Revision A dated October 3, 2024, or later FAA-approved revision. NOTE 10: Alternative and emergency fuels are listed in document no: RFM-H1-001, “Rotorcraft Flight Manual for UH-60A and UH-60L Blackhawk Helicopter:”, Revision IR, Dated November 8 2024, or later FAA-approved revision. NOTE 11: No person may be carried onboard this aircraft unless that person is a flight crewmember: is a flight crewmember trainee: performs an essential function in connection with a special purpose operation for which the aircraft is certificated: or is necessary to accomplish the work activity directly associated with that special purpose. Reference 14 CFR §91.31(d). NOTE 12: Any alteration to the type design of this aircraft may require Instructions for Continued Airworthiness. Changes to the type design by means of a Supplemental Type Certificate requiring ICAs or changes to existing ICAs must be submitted and received by the Fort Worth Aircraft Evaluation Group (FTW-AEG). Type design changes by means or an FAA field approval that require ICAs must have those ICAs reviewed by the Flight Standards District Office managing the field approval or the FTW-AEG. NOTE 13: No helicopter may obtain a Restricted Category Airworthiness Certificate under this type certificate unless it is included in the "Approved Serial Number List ", Hallux Aerospace LLC Report Number RPT-H1-102 Revision A dated October 3, 2024, or later FAA approved revision. NOTE 14: The Type Certificate holder’s data plat e must be installed in accordance with Hallux Aerospace LLC Drawing H1-001-101, Rev. NC dated September 21, 2023, as approved by the Engineering Configuration Report RPT-H1-100, Rev. A dated September 30, 2024, or later FAA-approved revision. END