TCDS R00020AT

Page No. 1 2 3 4 5 6 Rev. No. - - - - - DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION R00020AT Revision 1 Carson Helicopters, Inc. UH-60A TYPE CERTI FICATE DATA SHEET R00020AT This data sheet, which is a part of Type Certificate No. R00020AT 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) HOLDER: TYPE CERTIFICATE HOLDER RECORD MODEL NUMBER: Carson Helicopters, Inc. 952 Blooming Glen Road Perkasie, PA 18944 AAR Airlift Group transferred TC R00020AT t o Carson Helicopters on August 21, 2018 UH-6 0A - Restricted Category Rotorcraft Approved J une 26, 2017 ENGINE S: (2) General Electric T700-GE-700 Original (2) General Electric T700-GE-701C Alternate (2) General Electric T700-GE-701D Alternate FUEL: Aviation Kerosene JP-4, JP-5, JP-8, Jet A, Jet A-1 or Jet B. ENGINE LIMITS: (T700-GE-700) SHAFT HP POWER TURBINE RPM GAS GEN RPM POWER TURBINE INLE T (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 INLE T (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 R00020AT Revision 2 Carson Helicopters, Inc. UH-60A September 18, 2019 2 2 R00020AT Page 2 of 6 ENGINE LIMITS: (T700-GE- 701D) SHAFT HP POW ER TURBINE RPM/% GAS GEN RPM/% POW ER 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-60A) 110% Single Engine (No time limit) 100% Dual Engine (No time limit) ROTOR LIMITS: Power Off : Max. 265 RPM Maximum 110% M ax. 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 AAR-210 “Rotorcraft Flight Manual (RFM) for the UH-60A Helicopter for variation of Vne with gross weight, pressure altitude and temperature. Refer to document no. AAR-210 “Rotorcraft Flight Manual (RFM) for the UH-60A Helicopter, Rev. IR, Dated 5 June, 2017 or later FAA approved revisions for additional limitation data. Page 3 of 6 R00020AT 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. Work Package 1727 contained in TM 1-1520-237-23 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 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. 420.75 356.0 gallons closed circuit; 2 tanks (LH & RH interchangeable) STA. 420.75 OIL CAPACITY: 7 quarts each engine at STA.375.0 R00020AT Page 4 of 6 OTHER LIMITS: SERIAL NO. APPROVED: CERTIFICATION BASIS: § 21.25(b) (1) Agriculture Operations § 21.25(b) (2) Forest & Wildlife Conservation § 21.25(b) (7) External Loads This aircraft approved for Day or Night VFR operations only. Flight into known icing conditions is prohibited. 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 agricultural operations per §137.3 including aerial dispensing of liquids and forest conservation material excepted by §36.1(a) (4) and or external loads as defined §133.1(b). An y 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 part 21 § 21.101. Non-significant modifications shall have a certification basis of 14 CFR § 29 dated February q, 1965, including amendment 29-20, effective September 11, 1980. DATE OF APPLICATION: August 25, 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 co gnizant Aircraft Certification Office. Each helicopter must pass a conformity i nspection in accordance with this TCDS, plus any additional special instructions attach ed to the Request for conformity, FAA 8120-10. In addition, a check by the Type Cert ificate holder or its agent, of the flight characteristics in accordance with applica ble portions of the Maintenance Test Flight also known as Functional Check Flight List manual AAR-208, Dated January 29, 2017 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. “Rotorcraft Flight Manual” no. AAR-210, Rev. IR, Dated 05 June, 2017. 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: Refer to AAR - 210, Rotorcraft Flight Manual (RFM) d a ted 05 J une, 2017 or later FAA approved revision for additional limitations By AAR Airlift Group: U.S. military surplus UH-60A Blackhawk helicopter Serial Numbers 79-23293, 80-23430, 78-23004 . 14 CFR Part 21 § 21.25(a)(2) effective February 1, 1965, including Amendments 2 1-1 through 21-42 for the special purposes listed in FAR 21.25 (b)(1)(2)(7). Page 5 of 6 R00020AT 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 AAR Airlift Group document no. AAR- 202 “Instructions for Continued Airworthiness” Rev. IR dated March 13, 2017 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 AAR Airlift Group document no. AAR-202 “Instructions for Continued Airworthiness” Rev. IR dated March 13, 2017. 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 AAR Airlift Group drawing no. 16061-1006, Rev. A dated February 02, 2017 or later FAA approved revisions. NOTE 5: This helicopter must be operated in accordance with the operator manual comprised of the following: (1) AAR Airlift Group approved document no. AAR-210 “Rotorcraft Flight Manual (RFM) for the UH-60A Helicopter”, Rev. IR, Dated 05 June, 2017 or later FAA approved revisions. NOTE 6: Prior to obtaining an original Airworthiness Certificat e: A. Each helicopter must pass a conformity inspection in accordance with AAR Airlift Group document no. AAR-201 “Engineering Configuration” Rev. IR dated September 30, 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. R00020AT Page 6 of 6 NOTE 7: A restricted category heli copter 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 requirem ents 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 eng ine changes are allowed provided the replacement engine is conformed to AAR Airlift Group document no. AAR-202 “Instructions for Continued Airworthiness” Rev. IR, dated March 13, 2017 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 helicop ter contained in AAR Airlift Group, document no. AAR-205 “Airworthiness & Military Safety Messages”, Rev. IR, dated February 10, 2017 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 flight crewmember trainee, performs an essential function in connection with a special purpose operation for which the aircraft is certified; or is necessary to accomplish the work activity directly associated with that special purpose. Reference 14 CFR Part 91.313 (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 ICA, must be submitted and received by the Fort Worth Aircraft Evaluation Group (FTW-AEG). Type design changes by means of an FAA field approval that requires 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. AAR Airlift Group document no. AAR-202, “Instructions for Continued Airworthiness” Rev. IR, dated March 13, 2017, or later FAA approved revisions. END