TCDS R00003AC

Page No. 1 2 3 4 5 6 7 8 9 Rev. No. 3 3 3 3 3 3 3 3 3 DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION TYPE CERTIFICATE DATA SHEET R00003AC This data sheet, which is a part of Type Certificate No. R00003AC 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 (TC) HOLDER RECORD: N/A I – MODEL NUMBER: EH-60A (Restricted Category Military Rotorcraft) Approved May 13, 2019 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 16 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 R00003AC Pickering Aviation, Inc. EH-60A UH-60A UH-60L Revision: 3 Date: January 24, 2025 Pickering Aviation, Inc. 3825 Market St. Suite# 121 Denton, Texas 76209 Page 2 of 9 TCDS No. R00003AC 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: 110% Sin gle Engine (No Time Limit) 100% Dual Engine (No Time Limit) *See NOTE 1 7 ROTOR LIMITS: POWER OFF: Max. 26 5 RPM (110%) Min. 217 RPM (90%) POWER ON: Max. 258 RPM (107%) Min. 219 RPM (91%) AIRS PEED LIMITS: Vne POWER ON: 193 knots IAS, (221 MPH). Refer to PA-1-1 520-237-10, Operator’s Manual for the Restricted Category Aircraft Model EH -60A, UH-6 0A, UH-6 0L Helicopter Rev. 3.0, Dated September 06, 2024, or later FAA approved revisions, for variations of Vne with gross weight, pressure altitude, and temperature. Refer to PA-1-1 520-237 -10, Operator’s Manual for the Restricted Category Aircraft Model EH -60A, UH-6 0A, UH-6 0L Helicopter Rev. 3.0, Dated September 06, 2024, or later FAA a pproved revisions, for additional limitation data. C.G . RANGE: EMPTY WEIGHT C.G. RANGE: DATUM: LEVELING MEANS: None. 341.2 inches forward of the ma in rotor c entroid. Plumb bob in L/H cabin door frame to leveling plate on cabin floor or electronic leveling means in accordance with PA-1-1520-237-10, Operator’s Manual for the Restricted Category Aircraft Model EH-6 0A, UH-6 0A, UH-6 0L Helicopter Rev. 3.0, Dated September 06, 2024, or later FAA approved revisions. C.G.RANGE AIRCRAFT WEIGHT LBS INCHES AFT OF DATUM 347.7 360.2 22,000 13,400 13,050 366.3 11,500 358.1342.6 345.5 13,700 15,900 Page 3 of 9 TCDS No. R00003AC MAXIMUM WEIGHT: 22,000 lbs. *See NOTE 15 MINIMUM CREW: 2 (Pilot in Command and Second in Command) both located at aircraft station 227.1. *See NOTE 14 NUMBER OF SEATS: OEM established locations: 2 at Sta. 227.1; 2 at Sta. 282.0; 3 at Sta. 320.7; 4 at Sta. 339.8; 4 at Sta. 387.2. No Passengers permitted. *See NOTE 11 MAX COMPARTMENT WEIGHT: Compartment C Compartment D Compartment E Sta. 247 to Sta. 288 5460 lbs. Sta. 288 to Sta. 343 8370 lbs. Sta. 343 to Sta. 398 8370 lbs. FUE L CAPACITY: OIL CAPACITY: OTHER LIMITS: Main Tanks usable U.S. Gallons of fuel are: 360 (gravity), 359 (pressure), and 356 (closed circuit). 7 quarts each engine at STA. 375.0 Refer to PA-1-1520-237-10, Operator’s Manual for the R estricted Category Aircraft Model EH-60A, UH-6 0A, UH-6 0L Helicopter Rev. 3.0, Dated September 06, 2024, or later FAA approved revisions. Reference the Note Section for additional limitations. II – MODEL NUMBER: UH-60A (Restricted Category Military Rotorcraft) Approved February 11, 2021 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 16 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 44,700 775 º 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 EN GINE 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 Page 4 of 9 TCDS No. R00003AC 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: 110% Sin gle Engine (No Time Limit) 100% Dual Engine (No Time Limit) *See NOTE 17 ROTOR LIMITS: POWER OFF: Max. 265 RPM (110%) Min. 217 RPM (90%) POWER ON: Max. 258 RPM (107%) Min. 2 19 RPM (91%) AIR SPEED LIMITS: Vne POWER ON: 193 knots IAS, (221 MPH). Refer to PA-1-1 520-237-10, Operator’s Manual for the Restricted Category Aircraft Model EH-60A, UH-6 0A, UH-6 0L Helicopter Rev. 3.0, Dated September 06, 2024, or later FAA approved revisions, for v ariations of Vne with gross weig ht, p ressure altitude, and temper ature. Refer to PA-1-1 520-237-10, Operator’s Manual f or th e Restricted C ategory Aircraft Model EH-60A, UH-6 0A, UH-6 0L Helicopter Rev. 3. 0, Dated September 06, 2024, or later FAA a pproved revisions, for additional limitation data. C .G. RANGE: EMPTY WEIGHT C.G. RANGE: DATUM: LEVELING MEANS: MAXIMUM WEIGHT: MINIMUM CREW: None. 341.2 inches forward of the main rotor centroid. Plumb bob in L/H cabin door frame to leveling plate on cabin floor or electronic leveling means in accordance with PA-1-1520-237-10, Operator’s Manual for the Restricted Category Aircraft Model EH-6 0A, UH-6 0A, UH-6 0L Helicopter Rev. 3.0 , Dated September 06, 2024 or l ater FAA approved rev isions. 22,000 lbs. *See NOTE 15 2 (Pilot in Command and Second in Command) both located at aircraft station 227.1. *See NOTE 14 C.G.RANGE AIRCRAFT WEIGHT LBS INCHES AFT OF DATUM 347.7 360.2 22,000 13,400 13,050 366.3 11,500 358.1342.6 345.5 13,700 15,900 Page 5 of 9 TCDS No. R00003AC NUMBER OF SEATS: OEM established locations: 2 at Sta. 227.1; 2 at Sta. 282.0; 3 at Sta. 320.7; 4 at Sta. 339.8; 4 at Sta. 387.2. No Passengers permitted. *See NOTE 11 MAX COMPARTMENT WEIGHT: Compartment C Compartment D Compartment E Sta. 247 to Sta. 288 5460 lbs. Sta. 288 to Sta. 343 8370 lbs. Sta. 343 to Sta. 398 8370 lbs. FUEL CAPAC ITY: OIL CAPACITY: OTHER LIMITS: Main Tanks usable U.S. Gallons of fuel are: 360 (gravity), 359 (pressure), and 356 (closed cir cuit). 7 quarts each engine at STA. 375.0 Refer to PA-1-1 520-237-10, Operator’s Manual for the Restricted Category Aircraft Model EH-60A, UH-60A, UH-6 0L Helicopter Rev. 3.0, Dated September 06, 2024, or later FAA approved revisions. Reference the Note Se ction f or additional limitations. FUEL: III – MODEL NUMBER: UH-60L (Restricted Category Military Rotorcraft) Approved January 24, 2025 ENGINES: (2) General Electric T700-GE-701C Original (2) General Electric T700-GE -701D/CC Alternate *See NOTE 9 for al ternate engine information. Aviation Kerosene JP-4, JP-5, JP-8, Jet A, Jet A-1, or Jet B *See NOTE 16 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 Page 6 of 9 TCDS No. R00003AC TRANSMISSION LIMITS: TORQUE: 135% Single Engine (No Time Limit) 120% Dual Engine; 80 KIAS or below (No Time Limit) 100% Dual Engine; Above 80 KIAS (No Time Limit) *See NOTE 17 ROTOR LIM ITS: POWER OFF: Max. 265 RPM (110%) Min. 217 RPM (90%) POWER ON: Max. 258 RPM (107%) Min. 2 19 RPM (91%) AIR SPEED LIMITS: Vne POWE R ON: 193 knots IAS, (221 MPH). Refer to PA-1-1 520-237-10, Operator’s Manual for the Restricted Category Aircraft Model EH-60A, UH-6 0A, UH-6 0L Helicopter Rev. 3.0, Dated September 06, 2024, or later FAA approved revisions, for variations of Vne with gross weight, pressure altitude, and temperatur e. Refer to PA-1-1 520-237-10, Operator’s Manual fo r th e Restricted Catego ry Aircraft Model EH-60A, UH-6 0A, UH-6 0L Helicopter Rev. 3.0, Dated September 06, 2024, or later FAA approved revisions, for additional limitation data. C.G. R ANGE: EMP TY WEIGHT C.G. RANGE: DATUM: LEVELING MEANS: MAXIMUM WEIGHT: MINIMUM CREW: NUMBER OF SEATS: None. 341.2 inches forward of the main rotor centroid. Plumb bob in L/H cabin door frame to leveling plate on cabin flo or or electronic leveling means in accordance with accordance with PA -1-1520-237-10, Operator’s Manual for the Restricted Category Aircraft Model EH-6 0A, UH-60A, UH-60L Helicopter Rev. 3.0, Dated September 06, 2024, or later FAA approved revisions. 22,000 lbs. *See NOTE 15 2 (Pilot in Command and Second in Command) both located at aircraft station 227.1. *See NOTE 14 OEM established locations: 2 at Sta. 227.1; 2 at Sta. 282.0; 3 at Sta. 320.7; 4 at Sta. 339.8; 4 at Sta. 387.2. No Passengers permitted. *See NOTE 11 MAX COMPARTMENT WEIGHT: Compartment C Compartment D Compartment E Sta. 247 to Sta. 288 5460 lbs. Sta. 288 to Sta. 343 8370 lbs. Sta. 343 to Sta. 398 8370 lbs. C.G.RANGE AIRCRAFT WEIGHT LBS INCHES AFT OF DATUM 347.7 360.2 22,000 13,400 13,050 366.3 11,500 358.1342.6 345.5 13,700 15,900 Page 7 of 9 TCDS No. R00003AC FUEL CAPACITY: OIL CAPACITY: OTHER LIMITS: Main Tanks usable U.S. Gallons of fuel are: 360 (gravity), 359 (pressure), and 356 (closed circuit). 7 quarts each engine at STA. 375.0 Refer to PA-1-1 520-237-10, Operator’s Manual for the Restr icted Category Aircraft Model EH-60A, UH-6 0A, UH-6 0L Helicopter Rev. 3.0, Dated September 06, 2024, or later FAA a pproved revisions. Reference the Note Section for additional limitations. DATA PERTINENT TO ALL MODELS SERIAL NO. APPROVED: Refer to the latest FAA approved revision of Pickering Aviation, Inc. Document No. PA-03 Approved Serial Numbers List for the listing of all EH-60A, UH-60A, and UH-60L serial numbers that are approved by the FAA to be conformed under this Restricted Category Type Certificate. CERTIFICATION BASIS: Title 14 CFR p art 21 §21.25(a)(2) effective February 1, 1965, including Amendments 21-1 through 21-42 for the special purposes listed in 14 CFR §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 EQUI PMENT: NO TE SECTION NOTE 1: NOTE 2: In accordance with 14 CFR §36.1(a)(4), compliance with the noise requirements as not sh own. Therefore, in accordance with section 36.1(a)(4), aircraft certificated under this Type Certificate are only eligible for (1) agricultu ral operations as defined in § 137.3; (2) aerial dispensing of liquids and firefighting materials; and (3) external loads as defined in § 133.1(b). Any a lteration to the aircraft f o r S pecial P urpose operations not i de ntifie d above requires further FAA approval an d in addition, m ay require noi se a nd/or flight testing. This aircraft is approved for D ay or N i ght V F R o perations only. Flight i nt o known icing conditions is prohibited. Any subsequent modifications to the helicopters type certified under this Type C ertificate are to have the certification basis for that modification established under 14 CFR §21.101. Ot herwise, non-significant modifications are to meet the requirements of 14 CFR part 29 a irworthiness standards, transport category rotorcraft and 14 CFR §29.1529, Instructions for C ontinued Airworthiness. The basic required equipment neces sary for t he particular special purpose ope ration m ust be installed for ce rtification. 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 a t the time of original airworthiness certification. The following placards must be prominently displayed in the coc kpit in full view of the pilots: P LACARD NO. 1 THIS HELICOPTER MUST BE OPERATED IN COMPLIANCE WITH THE OPERATING LIMITATIONS SPECIFIED IN THE AP PROVED HELICOPTER OP ERATIONS MANUAL. Page 8 of 9 TCDS No. R00003AC PLACARD NO. 2 NOTE 3 : NOTE 4: NOTE 5: NOTE 6: THIS HELICOPTER MUST BE OPERATED IN ACCORDANCE WITH THE RESTRICTED CATEGORY OPERATING LIMITATIONS OF 14 CFR PART 91.313 OR PART 133 FOR EXTERNAL LOAD OPERATIONS. PLACARD NO. 3 EXTERNAL L OADS OP ERATIONS: VNE W ILL BE DE TERMINED FOR E ACH PROPOSED EXTERNAL LOAD APPLICATION. PLACARD NO. 4 THIS AI RCRAFT I S APPROVED FOR DAY OR NIGHT VF R OP ERATIONS ONL Y. FLIGHT INTO KNOWN ICING CONDITIONS IS PROHIBITED. The helicopter(s) mu st be serviced, maintain ed, inspected, repaired, and overhauled in accordance with the requirements specified in Pickering Aviation, Inc. Document no. PA-04 Instructions for Continued Airworthiness Rev. 5.0, Dated December 19, 2024, or later FAA approved revisions, or inspected in accordan ce with other FAA approved inspection programs. The service life limited parts overhaul and retirement intervals for these helicopters are specified in Pickering Aviation, Inc. Document no. PA-04 Instructions for Continued Airworthiness Rev. 5.0, Dated December 19, 2024, o r later FAA approved revisions. The latest FAA approved ICA must be provided with each helicopter at delivery and all later FAA approved revisions must be provided to the helicopter owner and operator. The TC Holder’s data plate required by 14 CFR §45.13 must be installed in ac cordance with Pickering Aviation, Inc. Data Plate Drawing No. PA-H60-DP Rev. 1, Dated June 13, 2022, or later FAA approved revisions. The helicopter(s) must be operated in accordance with the Operator Manual comprised of the following: PA-1-1520-237-10, Operator’s Manual for the Restricted Category Aircraft Model EH-6 0A, UH-60A, UH-60L Helicopter Rev. 3.0, Dated September 06, 2024, o r later FAA approved revisions. Prior to obtaining an original Airworthiness Certificate: A. Each h elicopter must pass a conformity inspection in accordance with Pickering Aviation, Inc. Document no. PA-ACR, Aircraft Configuration Report, Rev. 1, Dated June 13, 2023, or later revisions. B. Each helicopter must complete t he Aircraft Configuration Report, Document no. PA - ACR, Rev. 1, Dated June 13, 2023, or later revisions. The ACR provides evidence of the aircraft’s critical historical records, at the time of TC conformity, to show it is safe for its attended use. C. Each helicopter must pass an inspection for any possible hidden damage and the Military records reviewed for acceptability of any repairs or alterations. D. 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 FAA. E. 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: Restricted Category helicopter may not be operated in a foreign country without the expre ss written approval of that country’s Civil Air Authority. 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. Page 9 of 9 TCDS No. R00003AC NOTE 9: NOTE 10: NOTE 11: NOTE 12: NOTE 13: NOTE 14: NOTE 15: NOTE 16: NOTE 17: The alternate engines T700-GE-701C and/or T700-GE-701D/CC were approved in accordance with Order 8110.56B, para 4-15, as modifications “previously qualified by the U.S. Armed Forces.” Installation of the approved alternate engines must be in accordance with MWO 1-1520-237-20-3. T700-GE-701C and T700-GE-701D/CC performance information and limitations are contained in Chapter 7A of PA-1-1520-237-10, Operator’s Manual for the Restricted Category Aircraft Model EH-60A, UH-60A, UH-60L Helicopter Rev. 3.0, Dated September 06, 2024, or later FAA approved revisions. All applicable FAA ADs and Military Safety Messages listed in Pickering Aviation, Inc. Document no. PA-ACR, Aircraft Configuration Report, Rev. 1, Dated: June 13, 2023, or later revisions, must be complied with prior to original airworthiness cer tification. No person may be carried on board this aircraft unless th at 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)(1)(2)(3)(4). Any alteration to the typ e design of this aircr aft may require FAA approved Instructions for Continued Airworthiness. These instructions must be submitted and accepted by the Administrator, prior to appr oval for return to service. The established life limits for the products and articles of the Pickering Aviation, Inc. EH-60A, UH-60A, and UH-60L are based on the satisfactory service history as designed and operated by the US Armed Forces. Therefore, it is mandatory to constantly track and comply with the current life limits of certain critical components as identified in the FAA approved Airworthiness Limitation Section of Pickering Aviation, Inc. Instructio ns for Continued Airworthiness Document no. PA-04, Rev. 5.0, Dated Decemebr 19, 2024, or later FAA approved revisions. Pilot in Command and Second in Command rating requirements: Pilot in Command must comply with 14 CFR § 61.31 Second in Command must comply with 14 CFR § 61.55. EH-60A, UH-60A, and UH-60L maximum gross weight can be exten ded from 20,250 pounds to 22,000 pounds only when wedge mounted pitot-static probes and either/or MWO 55-1520-237-50-58 or MWO 1-1520-237-50-73 are installed. Alternative and emergency fuels are listed in PA-1-1520-237-10, Operator’s Manual for the Restricted Category Aircraft Model EH-60A, UH-60A, UH-60L Helicopter Rev. 3.0, Dated September 06, 2024, or later FAA approved revisions. Helicopters prior to S/N 91−26354 that are not equipped with improved main rotor flight controls are further restricted above 80 KIAS to Dual−Engine Continuous Torque Limits as indicated by a placard on the instrument panel. Refer to figure 5−3 for placard “Dual- Engine Torque Limitations at Airspeeds Above 80 KIAS 701C - 701D/CC” of PA-1-1520-237-10, Operator’s Manual for the Restricted Category Aircraft Model EH-60A, UH-60A, UH-60L Helicopter Rev. 3.0, Dated September 06, 2024, or later FAA approved revisions. – END –