TCDS P37EA

DEPARTMENT OF TRANSPORTATION P37EA FEDERAL AVIATION ADMINISTRATION Revision 13 Hartzell HC-J2Y, BHC-J2Y TYPE CERTIFICATE DATA SHEET NO. P37EA December 12, 2025 Propellers of models described herein conforming with this data sheet (which is part of Type Certificate No. P37EA) and other approved data on file with the Federal Aviation Administration meet the minimum standards for use in certificated aircraft in accordance with pertinent aircraft data sheets and applicable portions of the Federal Aviation Regulations provided they are installed, operated and maintained as prescribed by the approved manufacturer’s manuals and other approved instructions. Type Certificate Holder Hartzell Propeller LLC Piqua, OH 45356 Type Certificate Holder Record Hartzell Propeller Inc. Piqua, OH 45356 Type Constant speed; hydraulic (See NOTES 3 and 4) Engine shaft Special flange (See NOTE 1) Hub material Aluminum Alloy Blade material See Below Number of blades Two Hub models BHC-J2YF-1, -2; HC-J2YF-1 Maximum Diameter Approx. Max. Wt. Complete Blade Blades Continuous Takeoff Limits (For Reference Only) Construction (See NOTE 2) HP RPM HP RPM (See NOTE 2) (See NOTES 3 and 7) (See NOTE 10) Non-Counterweighted Propellers - Hub models HC-J2YF-1 and BHC-J2YF-1 7280+ 1/2 250 2700 250 2700 72 1/2” to 65” 55.0 lb. Aluminum Alloy to 7280-7 (+1/2 to -7) 7663-0 210 2800 210 2800 76” to 68” 50.0 lb. Aluminum Alloy to 7663-8 (-0 to -8) 7666-0 180 2900 180 2900 76” to 68” 55.0 lb. Aluminum Alloy to 7666-8 or or (-0 to -8) 250 2700 250 2700 7681-0 250 2700 250 2700 76” to 68” 55.0 lb. Aluminum Alloy to 7681-8 (-0 to -8) 7694-0 210 2800 210 2800 76” to 66” 53.5 lb. Aluminum Alloy to 7694-10 (-0 to -10) 7694-4 310 2700 310 2700 72” to 66” 53.5 lb. Aluminum Alloy to 7694-10 (-4 to -10) 8068-0 285 2700 285 2700 80” to 72” 54.0 lb. Aluminum Alloy to 8068-8 (-0 to -8) 8459-0 260 2800 260 2800 84” to 66” 52.0 lb. Aluminum Alloy to 8459-18 (-0 to -18) 8465-0 315 2575 315 2575 84” to 70” 54.0 lb. Aluminum Alloy to 8465-14 (-0 to -14) 8465-6 260 2700 260 2700 78” to 70” 53.0 lb. Aluminum Alloy to 8465-14 (-6 to -14) 8467-0 285 2700 285 2700 84” to 72” 56.0 lb. Aluminum Alloy to 8467-12 (-0 to -12) 8468-0 260 2700 260 2700 84” to 72” 54.0 lb. Aluminum Alloy to 8468-12 (-0 to -12) P37EA, Revision 13 Page 2 of 6 Maximum Diameter Approx. Max. Wt. Complete Blade Blades Continuous Takeoff Limits (For Reference Only) Construction (See NOTE 2) HP RPM HP RPM (See NOTE 2) (See NOTES 3 and 7) (See NOTE 10) 8470-0 260 2700 260 2700 84” to 76” 53.0 lb. Aluminum Alloy to 8470-8 (-0 to -8) 8475-0 310 2575 310 2575 84” to 80” 56.0 lb. Aluminum Alloy to 8475-4 or or (-0 to -4) 260 2700 260 2700 8475-4 350 2700 350 2700 80” to 78” 55.0 lb. Aluminum Alloy to 8475-6 (-4 to -6) 8475-6 310 2700 310 2700 78” to 70” 54.0 lb. Aluminum Alloy to 8475-14 or (-6 to -14) 300 2850 8477-0 260 2700 260 2700 84” to 72” 53.0 lb. Aluminum Alloy to 8477-12 (-0 to -12) B7421 241 2343 241 2343 74” 43.0 lb. Aramid Composite 8849-0 300 2700 300 2700 88” to 81” 57.8 lb. Aluminum Alloy 8849-7 (-0 to -7) Counterweighted Propellers: Hub Model BHC-J2YF-2 C7663-0 210 2800 210 2800 76” to 68” 56.5 lb. Aluminum Alloy to C7663-8 (-0 to -8) C7666-0 180 2850 180 2850 76” to 68” 61.5 lb. Aluminum Alloy to C7666-8 or or (-0 to -8) 250 2700 250 2700 C7681-0 250 2700 250 2700 76” to 68” 61.5 lb. Aluminum Alloy to C7681-8 (-0 to -8) C8459-0 260 2800 260 2800 84” to 72” 58.5 lb. Aluminum Alloy to C8459-12 (-0 to -12) C8465-0 315 2575 315 2575 84” to 70” 60.5 lb. Aluminum Alloy to C8465-14 (-0 to -14) C8465-6 260 2700 260 2700 78” to 70” 59.5 lb. Aluminum Alloy to C8465-14 (-6 to -14) C8467-0 285 2700 285 2700 84” to 72” 62.5 lb. Aluminum Alloy to C8467-12 (-0 to -12) C8468-0 260 2700 260 2700 84” to 72” 60.5 lb. Aluminum Alloy to C8468-12 (-0 to -12) C8470-0 260 2700 260 2700 84” to 76” 59.5 lb. Aluminum Alloy to C8470-8 (-0 to -8) C8475-0 310 2575 310 2575 84” to 80” 62.5 lb. Aluminum Alloy to C8475-4 or or (-0 to -4) 260 2700 260 2700 C8475-4 350 2700 350 2700 80” to 78” 61.5 lb. Aluminum Alloy to C8475-6 (-4 to -6) C8475-6 310 2700 310 2700 78” to 70” 60.5 lb. Aluminum Alloy to C8475-14 or (-6 to -14) 300 2850 C8477-0 260 2700 260 2700 84” to 72” 59.5 lb. Aluminum Alloy to C8477-12 (-0 to -12) Page 3 of 6 P37EA, Revision 13 Certification Basis: 14 CFR Part 35 effective February 1, 1965 with amendments 35-1 and 35-2 thereto. Type Certificate No. P37EA issued February 26, 1971 under Delegated Option Authorization procedures of 14 CFR Part 21 Subpart J. Date of application for Type Certificate: February 9, 1971. The following models were approved to the original certification basis: BHC-J2YF-1,2 Models added, updated or revised in accordance with 14 CFR Part 35 effective October 14, 1980 with amendments 35-1 through 35-5 include the following: BHC-J2YF-1 The following models were added, updated or revised in accordance with 14 CFR Part 35 with amendments 35-1 through 35-8 effective December 23, 2008. HC-J2YF-1, BHC-J2YF-1 Production Basis: Production Certificate no. 10 NOTE 1: Hub Model Designation B HC - J 2 Y F - 1 BF L when used denotes left hand rotation F denotes modified pitch change system R when used denotes a large piston area (see NOTE 4) Any other character denotes a minor change not affecting eligibility Denotes specific design features (See NOTE 4) -1: non-feathering, no counterweights, governor oil pressure increases pitch -2: feathering with counterweights, governor oil pressure decreases pitch F denotes special flange with six 1/2” bolts and two 1/2” dowels on a 4” bolt circle Hartzell blade shank size Number of blades Identifies basic design - J denotes a 3.25 inch integral shaft extension Hartzell Controllable When used indicates Flange Angular Index with respect to #1 blade, viewed clockwise facing propeller flange Prefix Angular Index Clocking Feature Flange Blank 90 and 270 degrees Dowel Pins F B 30 and 210 degrees Dowel Pins F P37EA, Revision 13 Page 4 of 6 NOTE 2: Blade Model Designation FL C 76 66 D - 3R Number when used indicates inches cut off from (or added to if +) basic diameter Q when used denotes special 1” x 90 deg. factory-bent tip. No cutoff permitted. R when used denotes specifically rounded tip for cutoff diameter. Any other character in this location denotes tip shape D or F denotes a dimensional modification from the original design B or K denotes deicing boots R when used denotes a rounded tip for the basic diameter S when used denotes a square tip for the basic diameter * Any other character denotes a minor modification not affecting eligibility Basic blade model Basic diameter in inches Denotes counterweighted blades Denotes blade configuration: right-hand tractor unless otherwise noted B prefix only denotes a right-hand tractor composite blade F denotes a large pitch change knob H denotes right-hand pusher J denotes left-hand tractor L denotes left-hand pusher * Blades may incorporate either round or square tips, yet may not be marked with an “R” or “S” in their model designation. This character is used to distinguish between two or more tip shapes available at the same diameter. Certain blades use “S” to denote shot peening of the exterior surface. (See NOTE 6) NOTE 3: Pitch Control (a) Approved with Hartzell governors per drawings C-4770 and C-4772. Wt.: 4.5 lb. (See NOTE 10) D - 1 - 4 Z Governor Model Designation L when used indicates left hand rotation Z when used indicates drive coupling type Any other character denotes a minor change not affecting eligibility Minor adjustment not affecting eligibility Minor adjustment to obtain engine/propeller/governor compatibility Basic body and major parts modification (b) The -2 models have counterweighted blades and use oil to decrease pitch. The -1 models do not have counterweighted blades and use oil to increase pitch. (See NOTE 4) (c) Maximum governor output pressure: 350 psi for all propeller models (d) All governors must be approved as part of the aircraft installation regardless of manufacturer. (See NOTE 10) NOTE 4: Feathering The -1 models do not feather. The -2 models incorporate feathering and unfeathering features. Reversing Not applicable Piston size The -2R model differs from the -2 model in that the -2R model has a piston area of 20.2 sq. in. and the -2 has a piston area of 16.25 sq. in. Page 5 of 6 P37EA, Revision 13 NOTE 5: Left-Hand Models The left-hand version of an approved propeller model is approved at the same rating and diameter as listed for the right-hand model. (See NOTES 1 and 2) NOTE 6: Interchangeability (a) Blades (1) Blades with counterweights (having “C” prefix) can replace non-counterweighted blades on feathering propellers (hub model suffix -2 or -2R) only, provided the air charge is reduced to 80 psi at 70°F. Attached decal specifying air charge must be changed accordingly. (2) Shot-peened blades may replace non shot-peened blades either individually or as a set (See NOTE 2) (b) Propellers “F” type propellers with large pitch change knobs are interchangeable with corresponding propellers with the standard pitch change system. (See NOTES 1 and 2) (c) Ice Protection Systems Refer to Hartzell Service Letter HC-SL-30-260 for ice protection system component interchangeability. (d) Governors Hartzell governors with a “Z” suffix in their model designation may be used interchangeably with corresponding governors without the “Z”. For example, the F-6-24Z is a replacement for the F-6-24 and the F-6-24 is a replacement for the F-6-24Z. NOTE 7: Accessories (a) Propeller ice protection system (weight of ice protection equipment extra) (1) Propeller models listed in this data sheet are approved for use with propeller ice protection equipment listed in Hartzell Manual 159( ) or in other Hartzell type design data. (2) All propeller ice protection equipment must be approved as part of the aircraft installation regardless of manufacturer. (See NOTE 10) (b) Propeller spinner (weight of spinner extra) (1) Approved with Hartzell and other manufacturers’ spinners when listed on Hartzell type design data. (2) All propeller spinners must be approved as part of the aircraft installation regardless of manufacturer. (See NOTE 10) NOTE 8: Shank Fairings Not applicable. P37EA, Revision 13 Page 6 of 6 NOTE 9: Special Limits Table of Propeller - Engine Combinations Approved Vibrationwise for Use on Normal Category Single Engine Tractor Aircraft The maximum and minimum propeller diameters that can be used from a vibration standpoint are shown below. No reduction below the minimum diameter listed is permissible, since this figure includes the diameter reduction allowable for repair purposes. The engine models listed below are the configurations on the engine type certificate unless specifically stated otherwise. Modifications to the engine or airframe that alter the power of the engine models listed below during any phase of operation have the potential to increase propeller stresses and are not approved by this list. Such modifications include, but are not lim ited to, the addition of a turbocharger or turbonormalizer, increased boost pressure, increased compression ratio, increased RPM, alte red ignition timing, electronic ignition, full authority digital engine controls (FADEC), or tuned induction or exhaust. Also, a ny change to the mass or stiffness of the crankshaft/counterweight assembly is not approved by this list. Hub Blade Max. Dia. Min. Dia. Model Model Engine Model (inches) (inches) Placards BHC-J2YF F7663 TCM IO-360-A, -B, -C, -D, -E 76 72 none BHC-J2YF F7694-( )T TCM IO-550-N, -P, -R 72 70 Avoid continuous ground operation between 1850 and 2100 RPM BHC-J2YF F8459(A)- 11Q TCM TSIO-360-GB, -LB 73 73 none BHC-J2YF F8459A-11Q TCM TSIO-360-MB 73 73 none BHC-J2YF 8475 TCM IO-520-B, -C, TCM TSIO-520-B, -D 80 77 none BHC-J2YF 8475 TCM TSIO-520-E 78 77 none NOTE 10: Propeller installation must be approved as part of the aircraft Type Certificate and demonstrate compliance with the applicable aircraft airworthiness requirements. Propeller models listed herein consist of basic hub and blade models. Most propeller models include additional characters to denote minor changes and specific features as explained in NOTES 1 and 2. Refer to the aircraft Type Certificate Data Sheet for the specific propeller model applicable to the installation. Propellers with composite blades must be evaluated for bird impact resistance prior to approval on any type aircraft. Hartzell Propeller must perform tests and/or analyses based on aircraft configuration and operating conditions to determine the potential hazard as a result of a bird impact. NOTE 11: Retirement Time (a) Life Limits and Mandatory Inspections (1) Airworthiness limitations, if any, are specified in Hartzell Manuals 115N, or 145( ). (2) The propeller Certificate Management Certification Branch must evaluate the propeller installation for each new aircraft installation to assess possible changes in the airworthiness limitations. NOTE 12: Special Notes (a) Refer to Hartzell Manual no. 202( ) for overspeed and overtorque limits. (b) Refer to Hartzell Service Letter HC-SL-61-61( ) for overhaul periods. END