TCDS R00005RC

DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION TYPE CERTIFICATE DATA SHEET R00005RC This data sheet, which is a part of Type Certificate No. R00005RC 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) ACE Aeronautics, LLC. HOLDER: 105 Buck Island Road Guntersville, AL 35976 I - MODEL: UH-60A (Restricted Category Military Surplus Rotorcraft) Approved October 21, 2016 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. 3 2 3 3 3 3 3 R00005RC Ace Aeronautics, LLC. UH-60A UH-60L Revision 3 February 19, 2025 Page 2 of 7 R00005RC TRANSMISSION LIMITS: TORQUE: (UH-60A) 110% Single Engine (No time limit) 100% Dual Engine (No time limit) ROTOR LIMITS: Power Off: Max. 265 RPM Maximum 110% Max. 217 RPM Minimum 90% Power On Max. 258 RPM Maximum 107% Max. 232 RPM Minimum 96% AIRSPEED LIMITS: Vne Power on: 193 knots IAS, (221 MPH). See document ACE-210 “Rotorcraft Flight Manual for UH-60A & UH-60L Helicopter” for variations of Vne with gross weight, pressure altitude, and temperature and for additional data OTHER LIMITS: Refer to document no. ACE-210 “Rotorcraft Flight Manual (RFM) for the UH-60A Helicopter, Rev. IR, Dated 30 September, 2016 or later FAA approved revisions for additional limitation 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 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. note 11 for applicability 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 at STA 375 Page 3 of 7 R00005RC OTHER LIMITS: Refer to ACE-210, Rotorcraft Flight Manual (RFM) dated 30 September, 2016 or later FAA approved revision for additional limitations II – MODEL: UH-60L (Restricted Category Military Surplus Rotorcraft) Approved February 19, 2025. 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 (No time limit) at or below 80 KIAS (No time limit) 100% Dual Engine, above 80 KIAS (No Time Limit) ROTOR LIMITS: Power Off: Max. 265 RPM Maximum 110% Max. 217 RPM Minimum 90% Power On Max. 258 RPM Maximum 107% Max. 232 RPM Minimum 96% AIRSPEED LIMITS: Vne Power on: 193 knots IAS, (221 MPH). See document ACE-210 “Rotorcraft Flight Manual for UH-60A & UH-60L Helicopter” for variations of Vne with gross weight, pressure altitude, and temperature and for additional data OTHER LIMITS: Refer to ACE-210, Rotorcraft Flight Manual (RFM), Revision A, dated 17 January, 2025 or later FAA approved revision for additional limitations Page 4 of 7 R00005RC DATUM: 341.2 inches forward of the main rotor centroid. 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. note 11 for applicability 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 at STA 375 DATA PERTINENT TO ALL MODELS SERIAL NO. APPROVED: U.S. military surplus UH-60A & UH-60L Blackhawk helicopters as identified in ACE Aeronautics, LLC Report Number ACE-204, Approved Serial Number List, Rev. IR dated March 31, 2016, 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: Compliance with the noise requirements in part 36 was not shown. Therefore, aircraft certificated under this type certificate are eligible only for operations excepted from noise compliance by § 36.1, including agricultural uses under part 137, aerial dispensing of fire fighting materials, and external loads under part 133. Page 5 of 7 R00005RC Approval of any Special Purpose Operations not identified above (and their accompanying modifications) requires further FAA approval and in addition, may require noise and/or flight testing. Aircraft is 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 12, 2016 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 Office. 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 the Maintenance Test Flight also known as Functional Check Flight List manual ACE-208, Dated May 03, 2016 or later approved revision for model UH-60A helicopters. EQUIPMENT: The basic required equipment necessary for the particular special purpose operation must be installed for certification. In addition, the following item of equipment must be on board the helicopter and available to the flight crew. Model UH-60A “Rotorcraft Flight Manual” no. ACE-210, Rev. IR, Dated 30 September, 2016, or later FAA approved Revision. Model UH-60L “Rotorcraft Flight Manual” no. ACE-210, Rev. A, Dated 17 January, 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: 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. Page 6 of 7 R00005RC NOTE 3: The helicopter(s) must be serviced, maintained, inspected, repaired and overhauled in accordance with the requirements specified in ACE Aeronautics, LLC document no. ACE-202 “Instructions for Continued Airworthiness” Rev. IR dated September 13, 2016 or later FAA accepted revision, or inspected in accordance with any other FAA accepted maintenance program. The service life limited parts overhaul and retirement intervals for these helicopters is specified in ACE Aeronautics, LLC document no. ACE-202 “Instructions for Continued Airworthiness” Rev. IR dated September 13, 2016. 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 ACE Aeronautics, LLC Drawing no. 40002, Rev. - dated April 04, 2016 or later FAA approved revisions. NOTE 5: This helicopter must be operated in accordance with the operator manual comprised of the following: Model UH-60A “Rotorcraft Flight Manual” no. ACE-210, Rev. IR, Dated 30 September, 2016, or later FAA approved Revision. Model UH-60L “Rotorcraft Flight Manual” no. ACE-210, Rev. A, Dated 17 January, 2025, or later FAA approved Revision. NOTE 6: Prior to obtaining an original Airworthiness Certificate: A. Each helicopter must pass a conformity inspection in accordance with ACE Aeronautics, LLC document no. ACE-201 “Engineering Configuration” Rev. IR dated April 25, 2016 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. NOTE 9: Military to Military engine changes are allowed provided the replacement engine is conformed to ACE Aeronautics, LLC document no. ACE-202 “Instructions for Continued Airworthiness” Rev. IR, dated September 13, 2016 or later approved FAA revision. The military or civil replacement engine must have proper military or civil records and have the applicable FAA Airworthiness Inspection accomplished and is in an airworthy condition. NOTE 10: The Safety of Flight Compliance Report for the helicopter contained in ACE Aeronautics, LLC, document no. ACE-205 “Airworthiness & Military Safety Messages”, Rev. D, dated December 6, 2024 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 Page 7 of 7 R00005RC necessary to accomplish the work activity directly associated with that special purpose. Reference 14 CFR §91 .3I 3(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: 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 it’s safe for intended use requirement, cycle counting and operational time tracking is required on certain critical components. Ref. ACE Aeronautics, LLC document no. ACE-202, “Instructions for Continued Airworthiness” Rev. IR, dated September 13, 2016, or later FAA approved revisions. NOTE 15: 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, 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 ACE-210 “Rotorcraft Flight Manual (RFM) for the UH-60A Helicopter”, Rev. A, Dated 30 17 January, 2025 or later FAA approved revisions. NOTE 16: The US Army Safety Messages that must be complied with for the helicopter and engine prior to certification are contained in Airworthiness Directives, Military Message, & Technical Publications Listing document ACE-205, Revision D dated December 6, 2024, or later FAA-approved revision. NOTE 17: Alternative and emergency fuels are listed in document no: ACE-210 “Rotorcraft Flight Manual (RFM) for the UH-60A Helicopter”, Rev. A, Dated 30 17 January, 2025 or later FAA approved revisions. END