TCDS R00024AT

Page No. 1 2 3 4 5 6 7 8 Rev. No. - - - - - - - - DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION R00024AT Revision IR BHI Productions, LLC UH-60A UH-60L February 12, 2026 TYPE CERTIFICATE DATA SHEET R00024AT This data sheet, which is a part of Type Certificate (TC) No. R00024AT, 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 (TC) BHI Productions, LLC HOLDER: 10100 Aileron Ave Pensacola, FL 32506 I -MODEL UH-60A (Restricted Category Rotorcraft) Approved February 12, 2026 ENGINES: (2) General Electric T700-GE-700 Original (2) General Electric T700-GE-701C Alternate (2) General Electric T700-GE-701D/CC Alternate *See NOTE 9 for alternate engine information. FUEL: Aviation Kerosene JP-4, JP-5, JP-8, Jet A, Jet A-1 or Jet B. *See NOTE 12 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 Maximum Cont. Power 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 R00024AT Rev. IR Page 2 of 8 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) (30b 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-60A) 110% Single Engine (No time limit) 100% Dual Engine (No time limit) ROTOR LIMITS: Power On Maximum 107% (258 RPM) Minimum 91% (219 RPM) Power Off Maximum 110% (265 RPM) Minimum 90% (217 RPM) AIRSPEED LIMITS: Vne Power on: 193 knots IAS, (221 MPH). See document BHIP-200-210 “BHIP Rotorcraft Flight Manual” (UH-60A & UH-60L) for variation of Vne with gross weight, pressure altitude and temperature. Refer to document no. BHIP-200-210, “BHIP Rotorcraft Flight Manual”, Rev. IR, dated August 30, 2025, or later FAA approved revisions for additional limitation data. R00024AT Rev. IR Page 3 of 8 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 leveling plate on cabin floor. Ref. TM 1-1570-237-23. MAXIMUM WEIGHT: 22,000 lbs. MINIMUM CREW: 2 (pilot, copilot) location at aircraft station 227.1 for both pilot and co-pilot NUMBER OF SEATS: OEM established locations: 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. Ref. BHIP-200-210 “BHIP Rotorcraft Flight Manual” Rev. IR, dated August 30, 2025, or lates FAA-approved revision. No passengers permitted. *See NOTE 11 for information on personnel carrying restrictions. MAX COMPARTMENT WEIGHT: Compartment C Compartment D Compartment E Sta 247 to Sta 288 Sta 288 to Sta 343 Sta 343 to Sta 398 6460 lbs. 8370 lbs. 8370 lbs. FUEL CAPACITY: 361.5 gallons gravity; 2 tanks (LH & RH interchangeable) STA. 420.75 359.7 gallons; 2 tanks (LH &RH interchangeable) (with fuel boost pumps installed) STA. 420.75 OIL CAPACITY: 7 quarts each engine. OTHER LIMITS: Refer to BHI Productions LLC documents no. BHIP-200-210 “Rotorcraft Flight Manual” Rev. IR, dated August 30, 2025, or later FAA-approved revision. R00024AT Rev. IR Page 4 of 8 II -MODEL NUMBER: UH-60L (RESTRICTED CATEGORY MILITARY SURPLUS) Approved February 12, 2026 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. *See NOTE 12 for alternate and emergency fuels. . 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: Power On Maximum 107% (258 RPM) Minimum 91% (219 RPM) Power Off Maximum 110% (265 RPM) Minimum 90% (217 RPM) AIRSPEED LIMITS: Vne Power on: 193 knots IAS, (221 MPH). See document BHIP-200-210 “BHIP Rotorcraft Flight Manual” (UH-60A & UH-60L) for variation of Vne with gross weight, pressure altitude and temperature. Refer to document no. BHIP-200-210, “BHIP Rotorcraft Flight Manual” Rev. IR, dated August 30, 2025, or later FAA approved revisions for additional limitation data. R00024AT Rev. IR Page 5 of 8 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 leveling plate on cabin floor. Ref. TM 1-1570-237-23. MAXIMUM WEIGHT: 22,000 lbs. MINIMUM CREW: 2 (pilot, copilot) location at aircraft station 227.1 for both pilot and co-pilot NUMBER OF SEATS: OEM established locations: 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. Ref. BHIP-200-210 “BHIP Rotorcraft Flight Manual” Rev. IR, dated August 30, 2025, or later FAA-approved revision. No passengers permitted. *See NOTE 11 for information on personnel carrying restrictions. MAX COMPARTMENT WEIGHT: Compartment C Compartment D Compartment E Sta 247 to Sta 288 Sta 288 to Sta 343 Sta 343 to Sta 398 6460 lbs. 8370 lbs. 8370 lbs. FUEL CAPACITY: 361.5 gallons gravity; 2 tanks (LH & RH interchangeable) STA. 420.75 359.7 gallons; 2 tanks (LH &RH interchangeable) (with fuel boost pumps installed) STA. 420.75 OIL CAPACITY: 7 quarts each engine. OTHER LIMITS: Refer to BHI Productions LLC documents no. BHIP-200-210 “Rotorcraft Flight Manual” Rev. IR, dated August 30, 2025, or later FAA-approved revision. R00024AT Rev. IR Page 6 of 8 DATA PERTINENT TO ALL MODELS SERIAL NO. APPROVED: U.S. military surplus UH-60A & UH-60L Blackhawk helicopter as identified in Serial Number Approved Report Number BHIP-200-204 Rev. IR, dated February 12, 2026, or later FAA approved revision. CERTIFICATION BASIS: Title 14 CFR Part 21 § 21.25(a)(2) effective February 1, 1965, including Amendments21- 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 14 CFR §36.1(a)(4), compliance with the noise requirements was not shown. Therefore, aircraft certificated under this Type Certificate are only eligible for (1) agricultural operations as defined in § 137.3; (2) aerial dispensing of fire fighting materials excepted by § 36.1(a) (4), and (3) external loads as defined in §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. 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: February 18, 2022 PRODUCTION BASIS: None. No helicopters may be produced under this approval. No helicopter serial number may be added to this type certificate unless approved by the cognizant Aircraft Certification Branch. Each helicopter must pass a conformity inspection in accordance with this TCDS, plus any additional special instructions attached to the Request for conformity, FAA 8120- 10. In addition, a check by the Type Certificate holder or its agent, of the flight characteristics in accordance with applicable portions of MTF -1- 1520-237-MTF Maintenance Test Flight Manual for UH -60A, UH-60L & EH -60A Helicopters, dated 31 January , 2019, or later approved revision for BHIP UH-60 helicopters. 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 BHI Productions LLC “BHIP Rotorcraft Flight Manual” document no. BHIP-200-210 Rev. IR, dated August 30, 2025, or later FAA approved revision NOTE 1: A current weight and balance report, including 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: The following placards must be prominently displayed in the cockpit in full view of the pilots: R00024AT Rev. IR Page 7 of 8 Placard No. 1 THIS HELICOPTER MUST BE OPERATED IN COMPLIANCE WITH THE OPERATING LIMITATIONS SPECIFIED IN THE APPROVED HELICOPTER OPERATIONS MANUAL. Placard No. 2 THIS ROTORCRAFT MUST BE OPERATED IN ACCORDANCE WITH THE RESTRICTED CATEGORY OPERATING LIMITATIONS OF 14 CFR PART 91.313. Placard No. 3 EXTERNAL LOADS OPERATIONS: Vne WILL BE DETERMINED FOR EACH PROPOSED EXTERNAL LOAD APPLICATION. NOTE 3: The helicopter(s) must be serviced, maintained, inspected, repaired and overhauled in accordance with the requirements specified in BHIP document no. BHIP-200-202 “Instructions for Continued Airworthiness” Rev. D dated February 14, 2025, or later FAA accepted revisions, 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 BHIP-200-202 document “Instructions for Continued Airworthiness” Rev. D, dated February 14, 2025, or later FAA approved revisions. A FAA approved/accepted copy must accompany each helicopter on delivery. NOTE 4: The builder’s data plate required by part 45 § 45.13 must be installed in accordance with document no. BHIP-200-300 Rev. B dated August 13, 2025 & drawing no. BHIP-001- 101 Rev. IR “Type Certificate Data Plate”, dated February 23, 2022 NOTE 5: This helicopter must be operated in accordance with the Rotorcraft Flight Manual comprised of the following: (1) BHIP-200-210 “BHIP Rotorcraft Flight Manual”, Rev. IR, dated August 30, 2025, or later FAA approved revisions. NOTE 6: Prior to obtaining an original Airworthiness Certificate: A. Each helicopter must pass a conformity inspection in accordance with document no. BHIP-200-203 “Engineering Configuration”, Rev. D dated February 7, 2025 or later FAA approved revision. The Engineering Configuration Report identifies the U.S. Army airframe changes, and special purpose modifications accomplished on that particular helicopter. B. Each helicopter must pass an inspection for any possible hidden damage and the military records reviewed for acceptability of any repairs or alterations. C. The maintenance, overhaul, and modification records of each helicopter must be reviewed for military changes that may affect the airworthiness of the helicopter. Modifications and changes of equipment that affect the safety or performance of the helicopter must be approved by the Federal Aviation administration. D. 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. NOTE 7: A Restricted Category helicopter may not be operated in a foreign country without the express written approval of that country. NOTE 8: 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. R00024AT Rev. IR Page 8 of 8 NOTE 9: Installation of T-700-GE-701D engines 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. MWO: 1-1520-237-30-3 modification instructions for the installation of the auto relight and transient droop improvement for T700-GE-701D engine on UH-60A aircraft is approved for the helicopter models: UH60A 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” document no. BHIP-200-210 Rev. IR dated August 30, 2025, or later FAA approved revision. NOTE 10: The Safety of Flight Compliance Report for the helicopter contained in BHI Productions LLC. document no. BHIP-200-205 “Airworthiness Directives & Military Safety Messages”, Rev. A, dated February 20, 2025, or later FAA Approved revision, must be complied with prior to original airworthiness certification. 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 §91.313(d). NOTE 12: Alternative and emergency fuels are listed in document no. BHIP-200-210 “BHIP Rotorcraft Flight Manual”, Rev. IR, dated August 30, 2025, or later FAA approved revision. NOTE 13: Any alteration to the type design of this aircraft may require Instructions for Continued Airworthiness. These instructions must be submitted and accepted by the Administrator, prior to approval for return to service. NOTE 14: The certification life limits for the helicopter, its engine and appliances were based on satisfactory service history as designed and operated by the military. Therefore, to operate and maintain the aircraft to the original acceptance criteria, and maintain its safe for intended use requirement, cycle counting and operational time tracking is required on certain critical components. Ref. Document no. BHIP-200-202, “Instructions for Continued Airworthiness” Rev. D, dated February 14, 2025, or later FAA approved revisions. END