# TCDS P36EA: Hartzell Propeller LLC - Type: Type certificate data sheet - Status: Current - Holder: Hartzell Propeller LLC - Revision: 29 - Revised: November 26, 2024 - Product: Propeller - Certification basis: Part 35 - Data sheet PDF: https://openairdocs.org/files/sha256/24/d9/24d9af0a2ac0194351d3e254dafaf69b2ae6f41b6a9da56a78d772bc2f6724c5 - FAA DRS: https://drs.faa.gov/browse/excelExternalWindow/DRSDOCID127858074120241127174756.0001 - Page: https://openairdocs.org/tcds/P36EA ## Models (6) As the data sheet lists them. - HC-J3YF-1 - HC-J3YF-2 - PHC-J3YF-1 - PHC-J3YF-2 - HC-J3Y1F-1 - PHC-J3Y1F-1 ## 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 P36EA FEDERAL AVIATION ADMINISTRATION Revision 29 Hartzell HC-J3Y, PHC-J3Y TYPE CERTIFICATE DATA SHEET NO. P36EA November 26, 2024 Propellers of models described herein conforming with this data sheet (which is part of Type Certificate No. P36EA) 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 “Notes” column in table below Number of blades Three Hub models HC-J3YF-1, -2; PHC-J3YF-1, -2; HC-J3Y1F-1; PHC-J3Y1F-1 Maximum Diameter Approx. Max. Wt. Complete Blades Continuous Takeoff Limits (For Reference Only) Notes (See NOTE 2) HP RPM HP RPM (See NOTE 2) (See NOTES 3 and 7) (See NOTE 10) Non-Counterweighted Propellers HC-J3YF-1, PHC-J3YF-1 7391-0 350 2700 350 2700 75” to 65” 80.2 lb. Aluminum Alloy to 7391-10 (-0 to -10) 7392-0 350 2850 350 2850 75” to 65” 75.5 lb. Aluminum Alloy to 7392-10 (-0 to -10) 7479-2 380 2900 380 2900 74” to 68” 78.0 lb. Aluminum Alloy to 7479-8 (-2 to -8) 7498-0 350 2700 350 2700 76” to 66” 72.5 lb. Aluminum Alloy to 7498-10 (-0 to -10) N7605-0 350 2700 350 2700 78” to 68” 62.5 lb. Composite to N7605-10 (-0 to -10) 7663-0 350 2800 350 2800 78” to 68” 73.0 lb. Aluminum Alloy to 7663-10 (-0 to -10) 7666-0 310 2700 310 2700 78” to 68” 77.0 lb. Aluminum Alloy to 7666-10 (-0 to -10) 7691-0 350 2850 350 2850 78” to 68” 71.0 lb. Aluminum Alloy to 7691-10 (-0 to -10) 7691+2 350 2700 350 2700 80” to 78” 71.0 lb. Aluminum Alloy to 7691-0 (+2 to -0) 7693+2 350 2700 350 2700 80” to 68” 77.0 lb. Aluminum Alloy to 7693-10 or (+2 to -10) 330 2850 7694-0 310 2700 310 2700 78” to 68” 76.0 lb. Aluminum Alloy to 7694-10 (-0 to -10) N7893-0 350 2700 350 2700 80” to 70” 63.0 lb Composite to N7893-10 (-0 to -10) P36EA, Revision 29 Page 2 of 9 Maximum Diameter Approx. Max. Wt. Complete Blades Continuous Takeoff Limits (For Reference Only) Notes (See NOTE 2) HP RPM HP RPM (See NOTE 2) (See NOTES 3 and 7) (See NOTE 10) 8068+2 350 2700 350 2700 84” to 72” 81.0 lb. Aluminum Alloy to 8068-10 (+2 to -10) 8068-2 350 2700 310 2850 80” to 72” 81.0 lb. Aluminum Alloy to 8068-10 (-2 to -10) NG8301-0 350 2850 250 2850 85” to 78” 62.8 lb. Carbon Composite to NG8301-7 (-0 to -7) NG8304-0 350 2850 350 2850 85” to 78” 63.9 lb. Composite to NG8304-7 (-0 to -7) NM8410-0 350 2850 350 2850 86” to 79” 62.5 Carbon Composite to NM8410-7 (-0 to -7) NM8411-0 350 2850 350 2850 86” to 79” 62.5 Carbon Composite to NM8411-7 (-0 to -7) 8429-0 350 2850 350 2850 86” to 76” 69.3 Aluminum Alloy to 8429-10 (-0 to -10) 8459-0 400 2700 400 2700 86” to 72” 75.0 lb. Aluminum Alloy to 8459-14 (-0 to -14) 8465-0 400 2700 400 2700 86” to 72” 78.0 lb. Aluminum Alloy to 8465-14 (-0 to -14) 8467-0 400 2575 400 2575 86” to 72” 82.0 lb. Aluminum Alloy to 8467-14 (-0 to -14) 8468-0 400 2700 400 2700 86” to 72” 79.0 lb. Aluminum Alloy to 8468-14 (-0 to -14) 8468-6 310 2850 310 2850 80” to 72” 79.0 lb. Aluminum Alloy to 8468-14 (-6 to -14) 8470-0 400 2700 400 2700 86” to 72” 78.0 lb. Aluminum Alloy to 8470-14 (-0 to -14) 8475+2 435 2266 435 2266 88” to 72” 82.0 lb. Aluminum Alloy to 8475-14 (+2 to -14) 8475-0 400 2650 400 2650 86” to 72” 78.0 lb. Aluminum Alloy to 8475-14 (-0 to -14) 8477-0 400 2575 400 2575 86” to 72” 81.0 lb. Aluminum Alloy to 8477-14 (-0 to -14) Non-Counterweighted Propellers HC-J3Y1F-1, PHC-J3Y1F-1 N7605-0 350 2700 350 2700 78” to 68” 57.7 lb. Composite to N7605-10 (-0 to -10) NG8301 350 2850 250 2850 85” to 78” 58.0 lb. Carbon Composite to NG8301-7 (-0 to -7) NG8304 350 2850 350 2850 85” to 78” 58.7 Composite to NG8304-7 (-0 to -7) Page 3 of 9 P36EA, Revision 29 Maximum Diameter Approx. Max. Wt. Complete Blades Continuous Takeoff Limits (For Reference Only) Notes (See NOTE 2) HP RPM HP RPM (See NOTE 2) (See NOTES 3 and 7) (See NOTE 10) Counterweighted Propellers HC-J3YF-2, PHC-J3YF-2 C7391-0 350 2700 350 2700 75” to 65” 90.7 lb. Aluminum Alloy to C7391-10 (-0 to -10) C7479-2 380 2900 380 2900 74” to 68” 86.0 lb. Aluminum Alloy to C7479-8 (-2 to -8) C7663-0 350 2800 350 2800 78” to 68” 81.0 lb. Aluminum Alloy to C7663-10 (-0 to -10) C7666-0 310 2700 310 2700 78” to 68” 85.0 lb. Aluminum Alloy to C7666-10 (-0 to -10) C7691-0 350 2850 350 2850 78” to 68” 79.0 lb. Aluminum Alloy to C7691-10 (-0 to -10) C8459-0 400 2700 400 2700 86” to 72” 83.0 lb. Aluminum Alloy to C8459-14 (-0 to -14) C8465-0 400 2700 400 2700 86” to 72” 86.0 lb. Aluminum Alloy to C8465-14 (-0 to -14) C8467-0 400 2575 400 2575 86” to 72” 90.0 lb. Aluminum Alloy to C8467-14 (-0 to -14) C8468-0 400 2700 400 2700 86” to 72” 87.0 lb. Aluminum Alloy to C8468-14 (-0 to -14) C8468-6 310 2850 310 2850 80” to 72” 87.0 lb. Aluminum Alloy to C8468-14 (-6 to -14) C8470-0 400 2700 400 2700 86” to 72” 86.0 lb. Aluminum Alloy to C8470-14 (-0 to -14) C8475+2 435 2266 435 2266 88” to 72” 90.0 lb. Aluminum Alloy to C8475-14 (+2 to -14) C8475-0 400 2650 400 2650 86” to 72” 90.0 lb. Aluminum Alloy to C8475-14 (-0 to -14) C8477-0 400 2575 400 2575 86” to 72” 93.0 lb. Aluminum Alloy to C8477-14 (-0 to -14) P36EA, Revision 29 Page 4 of 9 Certification Basis: 14 CFR Part 35 effective February 1, 1965 with amendments 35-1 and 35-2 thereto. Type Certificate No. P36EA issued March 1, 1971 under Delegated Option Authorization procedures of 14 CFR Part 21 Subpart J. Date of application for Type Certificate: February 5, 1971. The following models were approved to the original certification basis: HC-J3YF-1,2; PHC-J3YF-1,2 Models added, updated or revised in accordance with 14 CFR Part 35 effective August 18, 1990 with amendments 35-1 through 35-6 include the following: HC-J3YF-1,2; PHC-J3YF-1,2 The following models added in accordance with 14 CFR Part 35 effective August 18, 1990 with amendments 35-1 through 35-6 and reference to special conditions 35-002-SC dated October 3, 2001 for bird impact and lightning strike qualification: HC-J3YF-1 and PHC-J3YF-1 hubs with N7605 and N7893 blade models HC-J3Y1F-1 and PHC-J3Y1F-1 hubs with N7605 blade model 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 using 14 CFR Part 21.101 for paragraphs 35.15, 35.35(c), 35.36, 35.38, 35.41 and 35.43. HC-J3YF-1 and PHC-J3YF-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-J3YF-1; PHC-J3YF-1; HC-J3Y1F-1; PHC-J3Y1F-1 Models added after August 31, 2009 are approved in accordance with Organization Designation Authorization procedures of 14 CFR Part 183 Subpart D The following models were added, updated or revised in accordance with 14 CFR Part 35 with amendments 35-1 through 35-10 effective August 30, 2017: HC-J3YF-1, PHC-J3YF-1, HC-J3Y1F-1, PHC-J3Y1F-1 Production Basis: Production Certificate no. 10 Page 5 of 9 P36EA, Revision 29 NOTE 1: Hub Model Designation P HC - J 3 Y 1 F - 1 RF F when used denotes modified pitch change system L denotes left hand rotation M when used denotes 21.6 sq. in. piston area and large return spring N indicates compatibility with N shank blades (See NOTE 2) R when used denotes 21.6 sq. in. piston area 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 1 when used denotes hub design modification compatible only with blade models listed in the front of this Data Sheet Hartzell blade shank size Number of blades 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 & 270 degrees Dowel Pin F P 0 & 180 degrees Dowel Pin F NOTE 2: Blade Model Designation L C 76 63 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 C when used with N7605 blades denotes material modification (See NOTE 6) 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 for a two blade propeller.** Add two inches for three blade propellers. Denotes counterweighted blades Denotes blade configuration: right-hand tractor unless otherwise noted F denotes a large pitch change knob H denotes right-hand pusher J denotes left-hand tractor L denotes left-hand pusher N or NG denotes carbon composite construction * 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) ** Diameter limits are nominal diameters of the assembled propeller. They do not include the + or – 1/8 inch manufacturing tolerance the FAA allows for propellers with a basic diameter of less than 14 feet. P36EA, Revision 29 Page 6 of 9 NOTE 3: Pitch Control (See Notes 4 and 10) (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 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 (See Notes 2 and 3) (a) 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) (b) 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. (c) Blades (1) Shot-peened blades may replace non shot-peened blades either individually or as a set (See NOTE 2) (2) N7605C( ) blades may replace N7605( ) blades either individually or as a set. N7605( ) blades may not replace N7605C( ) blades. (d) Ice Protection Systems Refer to Hartzell Service Letter HC-SL-30-260 for ice protection system component interchangeability. Page 7 of 9 P36EA, Revision 29 NOTE 7: Accessories (See Note 10) (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. P36EA, Revision 29 Page 8 of 9 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 HC-J3YF PHC-J3YF F7391D TCM IO-550-N, -P, -R TCM IOF-550-N, -P, -R 75 72 none HC-J3YF 7663 TCM IO-520-A, -J, TCM TSIO-520-A, -C, -H 76 74 none PHC-J3YF 7663 TCM IO-520-B, -C, TCM TSIO-520-B, -D 76 74 none PHC-J3YF F7663 TCM TSIO-360-GB, -LB, -MB 76 74 none PHC-J3YF F7663-2Q TCM TSIO-520-R, -C, -H, -M, -P, -AF, -CE 76 76 none PHC-J3YF F7691( ) TCM IO-520-A, -B, -BA, -BB, -C, -CB, -D, -E, -F, -J, -K, -L, -M, -MB 78 77 Do not exceed 20 inches MP below 2200 RPM PHC-J3YF F7691( ) TCM IO-550-A, -B, -C, -D, -F, -G, -L 78 77 Do not exceed 20 inches MP below 2200 RPM HC-J3YF PHC-J3YF F7693( ) TCM IO-550-A, -B, -C, -D, -E, -F, -G, -L, -N, -P, -R, TCM TSIO-550-B, -C, -E 78 75 none HC-J3YF PHC-J3YF F7693(D)F( ) TCM TSIO-520-C, G, M, P, R, AF 80 76 none PHC-J3YF F8068 TCM IO-520-A, -J IO-550-D, -E, -F, -L TSIO-520-C, -G, -H, -M, -R, -P, -AF, -CE 82 78 none PHC-J3YF F8068-2 TCM IO-520-D, -E, -F, -L 80 78 none PHC-J3YF F8468 TCM TSIO-520-L, -LB 80 76 none PHC-J3YF F8468A( ) TCM TSIO-520-C, -G, -H, -M, -N, -P, -R, -T, -AF 80 77 none Page 9 of 9 P36EA, Revision 29 NOTE 10: Propeller installation must be approved as part of the aircraft Type Certificate and demonstrate compliance with the applicable aircraft airworthiness standards. 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 113( ), 115N, 117( ) or 145( ). (2) The propeller Certification Branch Office 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 ``` ## ADs (6, in force first) - [AD 2007-26-09](https://openairdocs.org/ad/2007-26-09): Initial blade inspections · Hartzell Propeller BHC-C2Y, BHC-G2YF-1, BHC-I2YF-1 and 67 more. Effective Jan 30, 2008 - [AD 2005-14-11](https://openairdocs.org/ad/2005-14-11): Failed propeller blade · Hartzell Propeller BHC-92W, BHC-92ZF-1, BHC-92ZF-3 and 391 more. Effective Aug 17, 2005 - [AD 2003-13-17](https://openairdocs.org/ad/2003-13-17): Propeller blade · Hartzell Propeller BHC-A2V, BHC-C2Y, EHC-G3YF-2 and 81 more. Effective Jul 18, 2003 - [AD 94-17-13](https://openairdocs.org/ad/94-17-13): Grease Fitting Holes · Two Lycoming TIO-540-A2B, or N2BD turbocharged engines and two… (Javelin Conversions STC SA2082WE or 2 others). Effective Sep 15, 1994 - [AD 2002-09-08](https://openairdocs.org/ad/2002-09-08) (historical): Blade Shank Radius · Hartzell Propeller BHC-C2Y, BHC-G2YF-1, BHC-I2YF-1 and 45 more. Effective Jun 13, 2002 - [AD 77-12-06](https://openairdocs.org/ad/77-12-06) (historical): Blade Shank · Hartzell Propeller BHC-12YF-4, BHC-C2Y, BHC-G2YF-1 and 115 more. Effective Dec 21, 1977 ## STCs approved under this data sheet (7) - [STC SP01222WI](https://openairdocs.org/stc/SP01222WI): Installation of Aircraft Development propeller vortelators.. Aircraft Development Co - [STC SP00582NY](https://openairdocs.org/stc/SP00582NY): Installation of Prop-Guard Polyurethane Protective Tape on the leading edge of metal propellers.. McFarlane Aviation, Inc. - [STC SP00400SE](https://openairdocs.org/stc/SP00400SE): Installation of various propeller electrical de-icer models. SMR Technologies - [STC SA00823CH](https://openairdocs.org/stc/SA00823CH): Installation of various de-icer wire harnesses.. SMR Technologies - [STC SA01384CH](https://openairdocs.org/stc/SA01384CH): Installation of various de-icer harnesses.. SMR Technologies - [STC SP1964SO](https://openairdocs.org/stc/SP1964SO): Installation of replacement electrothermal type de-icing boots.. Thermodyne, Inc - [STC SP1318GL](https://openairdocs.org/stc/SP1318GL): Installation of replacement electrothermal type de-icing boots.. Rapco, Inc --- 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.