# TCDS P27EA: Hartzell Propeller LLC - Type: Type certificate data sheet - Status: Current - Holder: Hartzell Propeller LLC - Revision: 15 - Revised: April 2, 2025 - Product: Propeller - Certification basis: Part 35 - Data sheet PDF: https://openairdocs.org/files/sha256/ca/3d/ca3da8f5cf1641059d833f2725626e30e39546c1f1029fd204aa79a569988875 - FAA DRS: https://drs.faa.gov/browse/excelExternalWindow/DRSDOCID164052437020250403142746.0001 - Page: https://openairdocs.org/tcds/P27EA ## Models (5) As the data sheet lists them. - DHC-F2YR-1 - HC-F2YL-2 - HC-F2YR-1 - HC-F2YR-2 - HC-F2YL-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 P27EA FEDERAL AVIATION ADMINISTRATION Revision 15 Hartzell HC-F2Y, DHC-F2Y TYPE CERTIFICATE DATA SHEET NO. P27EA April 2, 2025 Propellers of models described herein conforming with this data sheet (which is part of Type Certificate No. P27EA) 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 HC-F2YL-1,2, HC-F2YR-1,2, DHC-F2YR-1 (see Notes 1 and 4) 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 & 7) (See Note 10) Non-Counterweighted Propellers - Hub models HC-F2YR-1, DHC-F2YR-1, HC-F2YR-2 7068-0 300 2700 300 2700 70” to 60” 64.0 lb.* Aluminum Alloy to 7068-10 (-0 to -10) 7280+ 1/2 250 2700 250 2700 72 1/2” to 65” 58.0 lb.* Aluminum Alloy to 7280-7 (+1/2 to -7) 7479-0 380 2900 380 2900 74” to 68” 59.0 lb.* Aluminum Alloy to 7479-6 (-0 to -6) 7497-0 250 2700 250 2700 74” to 68” 63.8 lb.* Aluminum Alloy to 7497-6 (-0 to -6) 7663-0 210 2800 210 2800 76” to 68” 57.0 lb.* Aluminum Alloy to 7663-8 (-0 to -8) 7666-0 180 2900 180 2900 76” to 68” 63.0 lb.* Aluminum Alloy to 7666-8 or or (-0 to -8) 250 2700 250 2700 7681-0 250 2700 250 2700 76” to 68” 58.0 lb.* Aluminum Alloy to 7681-8 (-0 to -8) 7694-4 310 2700 310 2700 72” to 66” 56.5 lb.* Aluminum Alloy to 7694-10 (-4 to -10) 8068-0 285 2700 285 2700 80” to 72” 63.0 lb.* Aluminum Alloy to 8068-8 (-0 to -8) 8459-0 260 2800 260 2800 84” to 66” 58.0 lb.* Aluminum Alloy to 8459-18 (-0 to -18) 8465-0 315 2575 315 2575 84” to 70” 59.0 lb.* Aluminum Alloy to 8465-14 (-0 to -14) 8465-6 260 2700 260 2700 78” to 70” 58.0 lb.* Aluminum Alloy to 8465-14 (-6 to -14) 8467-0 285 2700 285 2700 84” to 72” 63.0 lb.* Aluminum Alloy to 8467-12 (-0 to -12) P27EA, Revision 15 Page 2 of 7 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 & 7) (See Note 10) 8468-0 260 2700 260 2700 84” to 72” 61.0 lb.* Aluminum Alloy to 8468-12 (-0 to -12) 8470-0 260 2700 260 2700 84” to 76” 56.0 lb.* Aluminum Alloy to 8470-8 (-0 to -8) 8475-0 310 2575 310 2575 84” to 80” 62.0 lb.* Aluminum Alloy to 8475-4 or or (-0 to -4) 260 2700 260 2700 8475-4 350 2700 350 2700 80” to 78” 61.0 lb.* Aluminum Alloy to 8475-6 (-4 to -6) 8475-6 310 2700 310 2700 78” to 70” 60.0 lb.* Aluminum Alloy to 8475-14 (-6 to -14) 8477-0 260 2700 260 2700 84” to 72” 65.0 lb.* Aluminum Alloy to 8477-12 (-0 to -12) Non-Counterweighted Propellers: Hub Models HC-F2YL-1, HC-F2YL-2 7663-0 160 2700 160 2700 76” to 66” 57.0 lb.* Aluminum Alloy to 7663-10 (-0 to -10) 7692-0 180 2900 180 2900 76” to 68” 57.0 lb.* Aluminum Alloy to 7692-8 or or (-0 to -8) 250 2700 250 2700 8468-0 160 2700 160 2700 84” to 70” 61.0 lb.* Aluminum Alloy to 8468-14 (-0 to -14) Counterweighted Propellers: Hub Models HC-F2YR-2 C7479-0 380 2900 380 2900 74” to 68” 63.0 lb. Aluminum Alloy to C7479-6 (-0 to -6) C7497-0 250 2700 250 2700 74” to 68” 67.8 lb. Aluminum Alloy to C7497-6 (-0 to -6) C7663-0 210 2800 210 2800 76” to 68” 61.0 lb. Aluminum Alloy to C7663-8 (-0 to -8) C7666-0 180 2700 180 2700 76” to 68” 67.0 lb. Aluminum Alloy to C7666-8 or or (-0 to -8) 250 2700 250 2700 C7681-0 250 2700 250 2700 76” to 68” 62.0 lb. Aluminum Alloy to C7681-8 (-0 to -8) C8459-0 260 2800 260 2800 84” to 72” 62.0 lb. Aluminum Alloy to C8459-12 (-0 to -12) C8465-0 315 2575 315 2575 84” to 70” 63.0 lb. Aluminum Alloy to C8465-14 (-0 to -14) C8465-6 260 2700 260 2700 78” to 70” 62.0 lb. Aluminum Alloy to C8465-14 (-6 to -14) C8467-0 285 2700 285 2700 84” to 72” 67.0 lb. Aluminum Alloy to C8467-12 (-0 to -12) C8468-0 260 2700 260 2700 84” to 72” 65.0 lb. Aluminum Alloy to C8468-12 (-0 to -12) Page 3 of 7 P27EA, Revision 15 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 & 7) (See Note 10) C8470-0 260 2700 260 2700 84” to 76” 60.0 lb. Aluminum Alloy to C8470-8 (-0 to -8) C8475-0 310 2575 310 2575 84” to 80” 66.0 lb. Aluminum Alloy to C8475-4 or or (-0 to -4) 260 2700 260 2700 C8475-4 350 2700 350 2700 80” to 78” 65.0 lb. Aluminum Alloy to C8475-6 (-4 to -6) C8475-6 310 2700 310 2700 78” to 70” 64.0 lb. Aluminum Alloy to C8475-14 or or (-6 to -14) 300 2850 300 2850 C8477-0 260 2700 260 2700 84” to 72” 69.0 lb. Aluminum Alloy to C8477-12 (-0 to -12) Counterweighted Propellers: Hub Models HC-F2YL-2 C7663-0 160 2700 160 2700 76” to 66” 61.0 lb. Aluminum Alloy to C7663-10 (-0 to -10) C7692-0 180 2900 180 2900 76” to 68” 61.0 lb. Aluminum Alloy to C7692-8 or or (-0 to -8) 250 2700 250 2700 * Weights shown are for non-counterweighted -2 models only. Subtract 3 lb. for -1 model. Certification Basis: 14 CFR Part 35 effective February 1, 1965 with amendments 35-1 thereto. Type Certificate No. P27EA issued December 8, 1966. Models added on or after September 27, 1967 were approved under Delegation Option Authorization provisions of 14 CFR Part 21 Subpart J. Date of application for Type Certificate: December 5, 1966. The following models were included under the original certification basis: HC-F2YR-2 The following models were added, updated or revised in accordance with 14 CFR Part 35 with amendments 35-1 and 35-2 effective April 3, 1967: HC-F2YR-1, HC-F2YR-2 The following models were added, updated or revised in accordance with 14 CFR Part 35 with amendments 35-1 through 35-5 effective October 14, 1980: HC-F2YL-1, HC-F2YL-2 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: HC-F2YL-1, HC-F2YL-2, HC-F2YR-1, HC-F2YR-2 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 35-9 effective March 19, 2013: HC-F2YR-1, DHC-F2YR-1 Production Basis: Production Certificate no. 10 P27EA, Revision 15 Page 4 of 7 NOTE 1: Hub Model Designation (See Notes 4, 5 and 6) D HC - F 2 Y R - 2 UF A when used indicates one-piece shaft extension L when used denotes left hand rotation F when used denotes modified pitch change system P when used denotes a hub unit with a “B” suffix serial number U denotes spring kit (package) in propeller dome Any other character denotes a minor change not affecting eligibility Denotes specific design features -1: non-feathering, no counterweights, governor oil pressure increases pitch -2: feathering with or without counterweights, governor oil pressure decreases pitch L denotes SAE # 2 flange with 6 7/16” bolts and 4 5/8” drive bushings on a 4-3/4” B.C. R denotes SAE # 2 flange with 6 1/2” bolts and 5 3/4” drive bushings on a 4-3/4” B.C. Hartzell blade shank size Number of blades Identifies basic design - “F” denotes 3 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 Blank 0 and 180 degrees Non counter bored hole R Blank 0 and 180 degrees Dowel Pins L D 60 and 240 degrees Non counter bored hole R NOTE 2: Blade Model Designation (See Notes 5 and 6) L C 76 63 D - 3R Number of 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 or template Basic diameter in inches 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 * Blades may incorporate either round or square tips, yet may not be marked with an “R” or “S” in the 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. Page 5 of 7 P27EA, Revision 15 NOTE 3: Pitch Control (See Notes 4, 6 and 10) (a) Approved with Hartzell governors per drawings C-4770 and C-4772. 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. The -2 models may or may not have counterweighted blades and use oil to decrease 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: (a) Feathering The -1 models do not feather. The -2 models incorporate feathering and unfeathering features. (b) Reversing Not applicable NOTE 5: Left-Hand Models (See Notes 1 and 2) The left-hand version of an approved model propeller is approved at the same rating and diameter as listed for the right-hand model. NOTE 6: Interchangeability (See Notes 1 and 2) (a) Propellers “F” type propellers with large pitch change knobs are interchangeable with corresponding propellers with the standard pitch change system. Propeller models containing a “P” suffix, for example HC-F2YR-1FP, may replace corresponding models without the “P” suffix, for example HC-F2YR-1F. Propeller models without the “P” suffix may not replace those containing the “P” suffix. (b) Blades Shot-peened blades may replace non shot-peened blades either individually or as a set. Blades with provisions to attach counterweights (denoted by a “C” prefix) can replace non- counterweighted blades on feathering propellers (-2 suffix in hub model) only, providing the air charge is reduced to 80 psi at 70 deg. F. Attached decal specifying air charge must be changed accordingly. (c) 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. (d) Ice Protection Systems Refer to Hartzell Service Letter HC-SL-30-260 for ice protection system component interchangeability. P27EA, Revision 15 Page 6 of 7 NOTE 7: Accessories (See Note 10) (a) Propeller ice protection system (weight of ice protection system 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 manufacturer’s 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. 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-F2YR F7068 LYC IO-360-B1A, -B1B, -B1C, -B1D, -B1E, -B1F, -E1A, -F1A 68 67 Stabilized operation is prohibited above 25” manifold pressure between 2300-2500 RPM and below 15” manifold pressure above 2600 RPM. HC-F2YR F7068 LYC O-360-A1F6, -A1F6D, -A1G6, -A1G6D, -A1H6, -F1A6, -G1A6 LYC IO-360-A1B6, -A1B6D, -A1D6, -A1D6D, -B1F6, -C1C6, -C1D6, -C1E6, -C1E6D 68 66 none HC-F2YR-1FP F7497 LYC O-360-A1A, -A1C, -A1D, -A1F, -A1G, -A1H, -A1P 74 72 none HC-F2YR-1FP F7497 LYC IO-360-A1B6, -A1B6D, -A1D6, -A1D6D, -C1C6, -C1D6, -C1E6, -C1E6D, -B1A, -B1B, -B1D, -B1E, -B1F, -E1A, -M1A 74 72 none HC-F2YR-1FP F7497 LYC IO-360-A1A, -A1B, -A1C, -A1D, -C1A, -C1B, -C1C, -C1F, -D1A 74 72 Continuous operation is prohibited above 24” manifold pressure between 2350 and 2550 RPM. Page 7 of 7 P27EA, Revision 15 Hub Blade Max. Dia. Min. Dia. Model Model Engine Model (inches) (inches) Placards HC-F2YL 7663 LYC O-320 series with 8.5:1 compression ratio, rated 160 HP at 2700 RPM or less 73 72 none HC-F2YR F7694-( )T LYC IO-540-D4A5, -D4B5, -D4C5, -N1A5, -R1A5, -T4A5D, -T4B5(D), -T4C5D, -V4A5(D), -K1A5(D), -K1B5(D), -K1C5, -K1D5, -K1E5(D), -K1F5(D), -K1G5(D), -K1H5, -K1J5(D), -K1K5, -L1A5(D), -L1B5D, -L1C5, -AC1A5 72 70 Avoid continuous ground operation between 1750 and 2100 RPM. Do not operate above 24" manifold pressure at engine speeds below 2300 RPM. HC-F2YR F8468A-4R LYC IO-540-J3A5D 80 78 none HC-F2YR F8468A LYC IO-540-J1A5D 80 78 Avoid continuous operation below 2300 RPM above 25" Hg manifold pressure. HC-F2YR F8475D-4 LYC IO-540-K1A5 80 78 Do not exceed 23" Hg manifold pressure below 2250 RPM. 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 strike. 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 ``` ## ADs (10, in force first) - [AD 2009-22-03](https://openairdocs.org/ad/2009-22-03): Propeller hub · Hartzell Propeller BHC-C2Y, CHC-C2Y, DHC-C2Y and 8 more. Effective Nov 12, 2009 - [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 2006-24-07](https://openairdocs.org/ad/2006-24-07): Propeller blades · Hartzell Propeller BHC-C2Y, HC-A2V, HC-A3V and 52 more. Effective Jan 3, 2007 - [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 2001-23-08](https://openairdocs.org/ad/2001-23-08): Propeller Hubs · Hartzell Propeller BHC-C2Y, BHC-G2YF-1, BHC-I2YF-1 and 23 more. Effective Dec 24, 2001 - [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 - [AD 2006-18-15](https://openairdocs.org/ad/2006-18-15) (historical): Front cylinder half of the propeller hub · Hartzell Propeller BHC-C2Y, BHC-G2YF-1, BHC-I2YF-1 and 24 more. Effective Sep 25, 2006 - [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 (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.