TCDS P10EA

DEPARTMENT OF TRANSPORTATION P10EA FEDERAL AVIATION ADMINISTRATION Revision 6 Hartzell HC-B4W TYPE CERTIFICATE DATA SHEET NO. P10EA April 2, 2025 Propellers of models described herein conforming with this data sheet (which is part of Type Certificate No. P10EA) 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 SAE Spline (see NOTE 1) Hub material Alloy Steel Blade material Aluminum Alloy Number of blades Four Hub models HC-B4W40-2 (see NOTES 1 and 4) Maximum Diameter Approx. Max. Wt. Complete Blades Continuous Takeoff Limits (For Reference Only) (See NOTES 2 and 6) HP RPM HP RPM (see NOTE 2) (See NOTES 3 and 7) W10160-6 ½ 550 2200 600 2250 96” to 91” 160 lb. to W10160-11 ½ (-6 ½ to -11 ½ ) Certification Basis: Civil Air Regulations Part 14 effective December 15, 1956 with amendment 14-1 thereto. Type certificate no. P10EA issued March 29, 1963. Date of application for Type Certificate: March 5, 1963. Production Basis: Production Certificate no. 10 NOTE 1. Hub Model Designation HC - B 4 W 40 - 2 D L denotes left hand rotation Any other character denotes minor change not affecting eligibility Denotes specific design features (see NOTE 4) SAE no. 40 spline Hartzell blade shank size Number of blades Identifies basic design Hartzell Controllable P10EA 2 of 3 Revision 6 NOTE 2. Blade Model Designation LW 101 60 B - 6 ½ Q Number of inches cut off from basic diameter (Add 1.5 inches to cutoff to determine the equivalent diameter) Q when used denotes special 1” x 90 deg. factory-bent tip for cutoff diameter B or K when used denotes deicing boots H denotes hard alloy (see NOTE 6) N denotes shank modification (see NOTE 6) Basic model or template Basic diameter in inches L when used denotes left hand blades W denotes needle bearing installation in blade shank NOTE 3. Pitch Control (a) Approved with Hartzell governors per drawings C-4770 and C-4772. Wt.: 4.5 to 6 lb. (see NOTE 10) B - 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 governor oil to decrease pitch. (see NOTE 4) (c) Governors must be approved as part of the aircraft installation regardless of manufacturer. (see NOTE 10) (d) Maximum control pressure for all models: 400 psig NOTE 4. (a) Feathering The -2 models incorporate feathering and unfeathering features. (b) Reversing Not applicable NOTE 5. Left-Hand Models The left-hand version of an approved model propeller 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 the suffix “N” in the basic model number may replace those without an “N” either individually or as a set. When the aircraft Type Certificate or Supplemental Type Certificate specifies blades with the letter “N” in the basic model number, the “N” character must be retained in all replacement blade models. For example: Blades without the “N” suffix may be replaced by “N” suffix blades. Blades with the “N” suffix may only be replaced by “N” suffix blades. (2) Hard and soft alloy blades of the same model designation are interchangeable. (See NOTE 2) (b) Governors (See NOTE 3) 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. 3 of 3 P10EA Revision 6 NOTE 7. Accessories (a) Propeller spinner (weight of spinner extra) Approved with Hartzell and other manufacturer's spinners when listed on Hartzell type design data. 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 limited to, the addition of a turbocharger or turbonormalizer, increased boost pressure, increased compression ratio, increas ed RPM, altered ignition timing, electronic ignition, full authority digital engine controls (FADEC), or tuned induction or exha ust. Also, any 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 None NOTE 10. The 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. NOTE 11. Retirement Time (a) Life Limits and Mandatory Inspections (1) Airworthiness limitations, if any, are stated in Hartzell Service Letter 61( ). (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 Refer to Hartzell Manual no. 202( ) for overspeed and overtorque limits. END