# TCDS P41EA: Hartzell Propeller LLC - Type: Type certificate data sheet - Status: Current - Holder: Hartzell Propeller LLC - Revision: 14 - Revised: April 2, 2025 - Product: Propeller - Certification basis: Part 35 - Data sheet PDF: https://openairdocs.org/files/sha256/45/a3/45a30cd0b5dd9f36db1e63a81c52a8540492545c3647dacc31a29221dbdc8b17 - FAA DRS: https://drs.faa.gov/browse/excelExternalWindow/DRSDOCID122358187620250404133130.0001 - Page: https://openairdocs.org/tcds/P41EA ## Models (2) As the data sheet lists them. - PHC-L3Y - EHC-L3Y ## 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 P41EA FEDERAL AVIATION ADMINISTRATION Revision 14 Hartzell EHC-L3Y PHC-L3Y TYPE CERTIFICATE DATA SHEET NO. P41EA April 2, 2025 Propellers of models described herein conforming with this data sheet (which is part of Type Certificate No. P41EA) 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 Three Hub models EHC-L3YF-1, PHC-L3YF-1, PHC-L3Y1F-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) Hub models EHC-L3YF-1, PHC-L3YF-1 7392-0 350 2850 350 2850 75” to 65” 69.0 lb. Aluminum Alloy to 7392-10 (-0 to -10) 7663-0 310 2800 310 2800 78” to 68” 70.0 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” 68.0 lb. Aluminum Alloy to 7691-10 (-0 to -10) 8068+2 350 2700 350 2700 84” to 72” 78.5 lb. Aluminum Alloy to 8068-10 (+2 to -10) 8068-2 350 2700 310 2850 80” to 72” 78.5 lb. Aluminum Alloy to 8068-10 (-2 to -10) NM8410-0 350 2850 350 2850 86” t0 79” 58 lb. Composite NM8410-7 (-0 to -7) 8459-0 400 2700 400 2700 86” to 72” 73.0 lb. Aluminum Alloy to 8459-14 (-0 to -14) 8465-0 400 2700 400 2700 86” to 72” 75.0 lb. Aluminum Alloy to 8465-14 (-0 to -14) 8467-0 400 2575 400 2575 86” to 72” 79.0 lb. Aluminum Alloy to 8467-14 (-0 to -14) 8468-0 400 2625 400 2625 86” to 72” 76.0 lb. Aluminum Alloy to 8468-14 (-0 to -14) 8468-6 310 2850 310 2850 80” to 72” 76.0 lb. Aluminum Alloy to 8468-14 (-6 to -14) P41EA, Revision 14 Page 2 of 5 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) 8470-0 400 2700 400 2700 86” to 72” 75.0 lb. Aluminum Alloy to 8470-14 (-0 to -14) 8475-0 400 2575 400 2575 86” to 72” 79.0 lb. Aluminum Alloy to 8475-14 (-0 to -14) 8477-0 400 2575 400 2575 86” to 72” 82.0 lb. Aluminum Alloy to 8477-14 (-0 to -14) Hub models PHC-L3Y1F-1 N7605+2 350 2700 350 2700 80” to 68” 57.0 lb. Composite to N7605-10 (+2 to -10) NG8301-0 350 2850 350 2850 85” to 78” 57.0 lb. Composite to NG8301-7 (-0 to -7) Certification Basis: 14 CFR Part 35 with amendments 35-1 and 35-2 effective April 1, 1967. Type Certificate No. P41EA issued January 10, 1972 under Delegated Option Authorization provisions of 14 CFR Part 21 Subpart J. Date of application for Type Certificate: October 20, 1971. The following models were included under the original certification basis: EHC-L3YF-1, PHC-L3YF-1 The following models were added, updated or revised in accordance with 14 CFR Part 35 with amendments 35-1 through 35-6 effective August 1, 1990: EHC-L3YF-1, PHC-L3YF-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 35-8 effective December 23, 2008 using 14 CFR Part 21.101 for paragraphs 35.15, 35.35(c), 35.41 and 35.43: PHC-L3Y1F-1 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: PHC-L3Y1F-1 Production Basis: Production Certificate no. 10 Page 3 of 5 P41EA, Revision 14 Note 1: Hub Model Designation (See Notes 4 and 5) E HC - L 3 Y 1 F - 1 RF F when used denotes modified pitch change system L when used denotes left hand rotation 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 -1: non-feathering, no counterweights, governor oil pressure increases pitch F denotes 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 this data sheet Hartzell blade shank size Number of blades Identifies basic design. “L” denotes integral 0.5 inch 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 E, P 0 and 180 degrees Dowel Pins F Note 2: Blade Model Designation (See Notes 5 and 6) FL 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 for a two blade propeller. Add two inches for a three blade propeller. 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. P41EA, Revision 14 Page 4 of 5 Note 3: Pitch Control (See Notes 4, 6 and 10) (a) Approved with Hartzell governors per drawings C-4770. Wt.: 4.5 lb. 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 -1 models do not have counterweighted blades and use oil to increase pitch. (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. Note 4: Feathering The -1 models do not feather. Reversing Not applicable Piston size Piston area is 17.7 sq. in. except as noted in Note 1. Note 5: Left-Hand Models (See Notes 1 and 2) The left-hand version of an approved propeller model is approved at the same rating and diameter as listed for the right-hand model. 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 Shot-peened blades may replace non shot-peened blades either individually or as a set. (d) Ice protection systems Refer to Hartzell Service Letter HC-SL-30-260 for ice protection system component interchangeability. 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) Page 5 of 5 P41EA, Revision 14 Note 8: Shank Fairings Not applicable. 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, altered 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 PHC-L3YF F7691 TCM IO-520-A, B, BA, BB, D, F, J, L 78 77 Do not exceed 20” manifold pressure below 2250 RPM PHC-L3YF F7691 TCM IO-550-B, D, F 78 77 Do not exceed 20” manifold pressure below 2250 RPM PHC-L3YF F8468R TCM IO-470-C, J, K, L, N 80 77 none PHC-L3YF F8468-8Q TCM IO-470-C, J, K, L, N 80 77 none PHC-L3YF F8468A( ) TCM IO-520-D 80 78 none PHC-L3YF F8468A( ) TCM IO-550-D 80 78 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 113( ), 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 ``` ## ADs (5, in force first) - [AD 2008-13-28](https://openairdocs.org/ad/2008-13-28): Propeller · Hartzell Propeller CHC-C2Y, DHC-C2Y, DHC-E2Y and 14 more. Effective Jul 17, 2008 - [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 2001-07-03](https://openairdocs.org/ad/2001-07-03): Overhaul · Hartzell Propeller BHC-C2Y, BHC-G2YF-1, BHC-I2YF-1 and 62 more. Effective Jun 4, 2001 ## STCs approved under this data sheet (2) - [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. --- 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.