# TCDS A00068CE: Harbin Hafei Aviation Industry Co. Ltd. - Type: Type certificate data sheet - Status: Current - Holder: Harbin Hafei Aviation Industry Co. Ltd. - Revision: 2 - Revised: July 30, 2021 - Product: Aircraft, Small Airplane - Certification basis: Part 21, Part 23, Part 34, Part 36 - Data sheet PDF: https://openairdocs.org/files/sha256/09/a4/09a481317d80d8ef5c28a3a36b8e732d3c5108006415235d5ca9da03c08e1e11 - FAA DRS: https://drs.faa.gov/browse/excelExternalWindow/AD036A2C2F749CF5862587220062AADE.0001 - Page: https://openairdocs.org/tcds/A00068CE ## Models (1) As the data sheet lists them. - Y12F ## What the data sheet says From the PDF's text layer, line by line; tables lose their columns. The PDF is the record. ```text DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION Page No. 1 2 3 4 5 6 7 Rev. No. 2 0 0 2 1 1 0 A00068CE Revision 2 Harbin Hafei Aviation Industry Co., Ltd. (HAIC) Y12F July 30, 2021 TYPE CERTIFICATE DATA SHEET No. A00068CE This data sheet, which is part of Type Certificate No. A00068CE, prescribes conditions and limitations under which the product meets the airworthiness requirements of the Federal Aviation Regulations. Type Certificate Holder: Harbin Hafei Aviation industry Co., Ltd. Northeast side of Jiangnanzhonghuan Road, Nancheng second road of Hanan Industrial Park, Harbin, Heilongjiang, China. Post Code: 150060 I. Model Y12F (Commuter Category), Approved February 22, 2016 Engine 2 Pratt & Whitney Canada PT6A-65B FAA Engine Type Certificate: E4EA Fuel Commercial grades: International ............................................ Jet A, Jet A-1 and Jet B, Chinese ....................................................................... No.3 Jet fuel Military grades: International ............................................................ JP-4,JP-5,JP-8 Emergency commercial aviation gasoline: specification ...................... All usable aviation gasoline (NOTE 4) other approved fuel see P&WC S.B. N0.13044 Oil Follow P&WC SB 13001: Mobil Jet Oil TypeⅡand Mobile Jet Oil 254 (Engine & Gearbox) Engine Limitations Operating Conditions Time Limits Power TRQ(1) ITT Ng NP SHP lb·ft ℃ % rpm Take off 5 1000 3090 820 104 1700 Max. Continuous 1000 3090 810 104 1700 Max. Climb /Normal Cruise 1000 3090 750 104 1700 (1)Torque limit applies within range of 1000 to 1700 rpm propeller shaft; below 1000 rpm torque is limited to 2000 lb. ft. Other Engine Limitations refer to AFM Page 2 of 7 A00068CE Propeller And Propeller Limitation 2 (two) Hartzell Propeller HC-B5MP-3D/M10876ANSK FAA Propeller Type Certificate: P44GL Hartzell five bladed aluminum constant speed, full feathering reversible propeller with electric deice boots  Diameter: 2824mm(111.2 inches);  Minimum Allowable For Repair 2812mm(110.7 inches);  Pitch Setting: With respect to 42 inches radius (75.54% radius); Reverse: -11°±0.5°; Feather: +79°±0.5°; Low pitch: +14.5°±0.1°;  Rotate speed: Maximum operation speed: 1700rpm; Maximum over-speed :1870 rpm; Ground taxi: 900～1170rpm; Feather: less than or equal to 400rpm. Airspeed limits VO(Operation Maneuvering Speed) 144 knots(267 km/h)(CAS) VFE(Flap Extended Speed) 130 knots (241 km/h)(CAS) VLO(Maximum Speed For Landing Gear Operation) 137 knots (254 km/h)(CAS) VLE(Maximum Speed For Landing Gear Extension) 137 knots (254 km/h)(CAS) VMCA(Minimum Control Speed In The Air) 87 knots (161 km/h)(CAS) VMO(Maximum Operating Speed) 209 knots (387 km/h)(CAS) Center of Gravity Range 7800mm(307.09 inches) to 8007mm (315.24 inches)(25.00%～35.00%MAC)at 8400kg(18,520 lb); 7766mm(305.76 inches)to 8007mm (315.24 inches)(23.36%～35.00%MAC)at 8000kg(17,640 lb); 7613mm(299.72 inches) to 8007mm (315.24 inches)(16.00%～35.00%MAC)at 6200kg (13,668 lb); 7593mm(298.94 inches) to 8007mm (315.24 inches)(15.00%～35.00%MAC) below 5700kg (12,566 lb). Straight line variation between points given. Datum Located at 1000mm(39.37 inches)in front of the airplane nose in forward and rear directions Located at the symmetric center line of airplane in left and right directions Located at horizontal plane, 750mm(29.53 inches) above cabin floor, in up and down directions Empty Weight C.G. Range None. Mean Aerodynamic Chord (MAC) 2074 mm (81.65 inches) Page 3 of 7 A00068CE The horizontal dimension of MAC leading edge to Datum : 7282mm (286.69 inches) Leveling Means See Leveling Diagram:YF082101H003151 Maximum Weights Max Ramp Weight 8450 kg (18,630 lb ) Max Take-off Weight 8400 kg (18,520 lb ) Max Landing Weight 8000 kg (17,640 lb ) Minimum Flight Crew Two (2) pilots. Pilot-in-Command is on the left viewed looking forwards except for training and checking Number of Seats Maximum Compartment Weights Maximum 21 seats(Including pilot and copilot seats) Item Arm mm(inches) Quantity Crew 4052(159.5) 2 Passengers Row 1 6082(239.4) 3 Passengers Row 2 6892(271.3) 3 Passengers Row 3 7702(303.2) 3 Passengers Row 4 8512(335.1) 3 Passengers Row 5 9322(367.0) 3 Passengers Row 6 10132(398.9) 2 Passengers Row 7 10942(430.8) 2 Front baggage compartment 50 kg (110 lb) 2420 mm (95.3 inches) Rear baggage compartment 250 kg (550 lb) 12760 mm (502.4 inches) Fuel capacities Left fuel tank 1252kg (1584.5 L,418.6 gal) at 8110mm (319.3 inches ) Right fuel tank 1252kg (1584.5 L,418.6 gal) at 8110mm (319.3 inches ) Each tank unusable fuel 25kg (31.5L, 8.3 gal). (Fuel Density:0.79kg/l) Oil capacities 11.7 L(12.3 US quart) each engine at 6843mm (269.41 inches ) Each engine unusable oil 4.08L (4.3 US quart) Maximum Operating Altitude 7000 m(23000 ft) Control movement Flaps Positions: 0°(±0.5°) 10°(±0.5°) 20°(±0.5°) Elevator Up 24°(+2°,0°) Down 15°(+1°,-0.5°) Elevator Trim Tab Up 16(+1,0°) Down 11.5(+2,0°) Rudder Left 20 °(0,-0.5) Right 20 °(0,-0.5) Rudder Trim Tab Left 12 °(±1) Right 12°(±1) Aileron Up 30(±1) Down 20(±1) Aileron Trim Tab Up 20(±1) Down 20(±1) Serial Nos. Eligible Y12F Serial Number: 001 and on. The CAAC Certificate of Airworthiness for Export must be submitted for each Page 4 of 7 A00068CE individual airplane. See "Import Requirements." Import Requirements A United States Certificate of Airworthiness may be issued on the basis of a CAAC Certificate of Airworthiness for Export, signed by a representative of the CAAC Authority, containing the following statement: "The airplane covered by this certificate has been examined, tested and found to conform to the type design approved under FAA Type Certificate A00068CE, and is in a condition for sa fe operation." Instructions for Continued Airworthiness (ICA) complying with FAR 23.1529, must be furnished before delivery of the first airplane or issuance of a US standard certificate of airworthiness, whichever occurs later. Refer to the applicable bilateral agreement to verify eligibility for import into the United States of both new and used aircraft based on the scope of the agreement, to identify any required statements by the exporting authority on the export certificate of airworthiness (or equivalent document), and for procedures for coordinating exceptions to conformity statements on these documents. Refer to FAA Order 8130.2, Airworthiness Certification of Aircraft, for requirements for issuance of an airworthiness certificate for imported aircraft Certification Basis The regulations (unless otherwise stated) are Title 14 of the Code of Federal Regulations (14 CFR): 1) FAR 21.29, 21.183(c) and FAR 23, effective February 1, 1965, including Amendments 23-1 through 23-61for Commuter Category. 2) FAR 36, effective December 1969, including Amendments 36-1 through 36-29. 3) FAR 34,effective September 10, 1990. including Amendments 34-1 through 34-5. 4) Equivalent Level of Safety per 21.21(b)(1): a) ACE-15-16 of July 21, 2015, landing gear handle location, § 23.777(g) at amendment 23-51; b) ACE-13-04 of December 7, 2012, Engine Display Requirements, § 23.1305(a)(2), (a)(3), (c)(2) and (c)(5) at amendment 23-52 and § 23.1549 (a), (b) and (c) at amendment 23-45; c) ACE-13-07 of March 18, 2013, Storage Battery, § 23.1353(h) at amendment 23-49; d) ACE-10-13 of July 23, 2010, Circuit Protective Devices, § 23.1357(b) at amendment 23-43; e) ACE-10-12 of July 23, 2010, ASI Flap Markings, § 23.1545(b)(4) at amendment 23-50. f) AT00787CE-A-S-1 dated Feb. 11, 2019, Pitot Heat Indication System, § 23.1326(b)(1) at amendment 23-49. 5) No Exemptions 6) No Special Conditions 7) The airplane is approved for ditching. 8) Only airplanes with Harbin HAEFI modification YF-MOD-2 installed are Page 5 of 7 A00068CE Validation Basis approved for flight into known or forecasted icing. Compliance has been demonstrated in accordance with §23.1416 and §23.1419. (Note 6) 9) The Civil Aviation Administration of China (CAAC) issued CAAC Type Certificate No. TC0024A on December 10, 2015. Date of application for original Type Certificate: August 30, 2006 The applicable airworthiness requirements for a U.S. certification under14 CFR 21 section 21.29 identified above were established considering the airworthiness requirements applied by the responsible exporting Civil Aviation Administration of China (CAAC) under the Bilateral Aviation Agreement (BAA) - Schedule of Implementation Procedures (SIP), between the United States (U.S.) and the People’s Republic of China (P.R.C.) dated March 23, 1995. Equipment The basic required equipment prescribed in the applicable airworthiness regulations (see Certification Basis) must be installed in the airplane. In addition, the following equipment is also required: FAA approved Aircraft Flight Manual Y12F, Document No. Y12FTP-AFM, revision RN003 dated Nov. 20, 2018 or later approved revision. Service Information Each of the following service information documents must state that it is approved and/or accepted by the Civil Aviation Administration of China (CAAC). In accordance with the US/People’s Republic of China Bilateral Airworthiness Agreement and the associated Schedule of Implementation Procedures (BAA-SIP) paragraph 226, any future changes that affect the US type design, including but not limited to, the following documents must be coordinated with the FAA through the CAAC for direct FAA approval or acceptance as required. These documents will show this FAA approval and/or acceptance along with the CAAC approval and/or acceptance:  Y12F Aircraft Flight Manual Y12FTP-AFM  Y12F Aircraft Scheduled Maintenance Requirements Y12FTP-SMR  Y12F Aircraft Maintenance Manual Y12FTP-AMM  Y12F Aircraft Airworthiness Limitations Y12FTP-ALS Additional changes that must be coordinated with the FAA includes any other service documents that:  make changes to any other FAA approved limitations  requires a US type design change  requires an ELOS, Special Condition or Exemption  makes an acoustical or emissions changes to this product’s U.S. type certificate as defined in 14 CFR § 21.93 Any other service documents that do not affect changes to US type design (such as customer unique designs, service bulletins and product improvements) that are not dealt with by the BAA-SIP paragraph 226(a) will be accepted by the FAA and will be Page 6 of 7 A00068CE considered FAA approved data upon the CAAC approval statement. Available Documents for the Y12F are: (Note 5) FAA approved Aircraft Flight Manual Y12F, Document No. Y12FTP-AFM, revision RN003 dated Nov. 20, 2018 or later CAAC/FAA approved revisions.(Note 2)(Note 6) Y12F Aircraft Scheduled Maintenance Requirements Y12FTP-SMR, Revision Initial dated Dec. 15, 2015 or later CAAC accepted revisions. Y12F Aircraft Maintenance Manual Y12FTP-AMM, Normal Revision RN001 dated Jan. 30, 2016 or later CAAC/FAA accepted revisions. Y12F Aircraft Airworthiness Limitations Y12FTP-ALS, Initial Issue dated Dec.22, 2015 or later CAAC/FAA approved revisions. The ALS dated Dec. 22, 2015 is Chapter 4 of Y12FTP-AMM Normal Revision RN001. (See Note 3) NOTES Note 1 Note 2 Note 3 Note 4 Note 5 Note 6 Current weight and balance data, loading information, and a list of equipment included in empty weight must be provided for each airplane at the time of original certification. (a) Basic empty weight includes unusable fuel of 50kg (110 lb ) at 8110mm (319.3 inches ) (b) Basic empty weight includes engine oil of 22.3kg (49.2 lb ) with 3.9 kg (8.6 lb.) being unusable. Airplane operation must be in accordance with the CAAC-approved Aircraft Flight Manual Y12FTP-AFM listed above. All placards listed in Section 2 of the FAA approved AFM must be displayed in the appropriate locations. The US versions of the Y12F AFM limitations may not be changed without CAAC and direct FAA approval. Y12F mandatory retirement times for all structural components are contained in Aircraft Airworthiness Limitation Section document Y12FTP-ALS Initial Issue (or later versions). The US versions of the Y12F limitations may not be changed without CAAC and direct FAA approval. Emergency AVGAS Limitations: a)Operation is limited to 150 hours between engine overhauls; b)The fuel system must be flushed after using the 80 aviation gasoline; c) Before the flight, make sure that all the fuel booster pumps are operative. Master Manual Document Number: Y12FTP-MTM Normal Revision RN001 dated Jan. 30, 2016 (or later revisions) lists all the Y12F technical publications and their corresponding revision (version) levels that are delivered to the customer with each airplane. This includes all the ICA documents. FAA validation project A T00787CE-A approved Flight Into Known Icing (FIKI) for Page 7 of 7 A00068CE Note 7 Y12F airplanes equipped with Harbin HAFEI modification YF-MOD-2, which requires AFM revision RN003 dated Nov. 20, 2018 and AFMS No. 7 dated Nov. 20, 2018 or later CAAC/FAA approved revisions. FAA validation project A T00807CE-A approved the optional Honeywell Automatic Flight Control System (AFCS) that includes: Autopilot, Yaw Damper and Flight Director. This design change is identified YF-MOD-1 and requires AFMS No. 9 dated Nov. 20, 2018 or later CAAC/FAA approved revisions. – END – ``` ## ADs None name its models. --- OpenAirDocs.org is an independent research project of [Contrail Labs](https://contraillabs.com/). It is not affiliated with the FAA or the NTSB. Source documents are U.S. government works in the public domain.