TCDS P40EA

DEPARTMENT OF TRANSPORTATION P40EA FEDERAL AVIATION ADMINISTRATION Revision 17 Hartzell HC-B4T TYPE CERTIFICATE DATA SHEET NO. P40EA September 27, 2024 Propellers of models described herein conforming with this data sheet (which is part of Type Certificate No. P40EA) 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 Alloy Steel Blade material Aluminum Alloy Number of blades Four Hub models HC-B4TN-3, HC-B4TW-3, HC-B4TN-5 (see Notes 1 and 4) Maximum Diameter Approx. Max. Wt. Complete Blades Continuous Takeoff Limits (For Reference Only) (see Note 2) HP RPM HP RPM (see Note 2)* (see Notes 3 and 7) HC-B4TN-3, HC-B4TN-5 T9212-0 850 2000 850 2000 93” to 83” 158 lb. to T9212-10 (-0 to –10)* T9216-0 850 2000 850 2000 93” to 83” 158 lb. to T9216-10 (-0 to –10)* T10574-0 950 1620 950 1620 106” to 90” 165 lb. to T10574-16 (-0 to –16)* T10574A-0 950 1620 950 1620 106” to 90” 168 lb. to T10574A-16 (-0 to –16)* T10576-0 950 1591 950 1591 106” to 90” 170 lb. to T10576-16 (-0 to –16)* T10173+1 900 2200 900 2200 103.5” to 81.5” 155 lb. to T10173-21 (+1 to –21)** T10173AN-12.5 750 2200 900 2200 90” to 81.5” 157 lb. to T10173AN-21 (-12.5 to –21)** T10173F-10.5 750 2200 950 2200 92” to 81.5” 153 lb. to T10173F-21 (-10.5 to –21)** T10176+1 900 2200 900 2200 103.5” to 81.5” 155 lb. to T10176-21 (+1 to –21)** T10178-0 950 2200 950 2200 102.5” to 81.5” 165 lb. to T10178-21 (-0 to –21)** T10282-0 950 2200 950 2200 103” to 81” 165 lb. to T10282-22 (-0 to –22)* P40EA, Revision 17 Page 2 of 5 Maximum Diameter Approx. Max. Wt. Complete Blades Continuous Takeoff Limits (For Reference Only) (see Note 2) HP RPM HP RPM (see Note 2)* (see Notes 3 and 7) HC-B4TN-3, HC-B4TN-5 T10282+6 950 1591 950 1591 109.25" to 103" 166 lb. to T10282-0 or or (+6 to –0)*** 800 2000 800 2000 T10890N-0 950 1591 950 1591 109.5" to 103.5" 186 lb. to T10890N-6 (-0 to –6)** HC-B4TN-5 T10891N-0 950 1591 950 1591 109.5" to 103.5" 186 lb. to T10891N-6 (-0 to –6)** HC-B4TW-3 T10282N-0 950 2200 950 2200 103” to 81” 166 lb. to T10282N-22 (-0 to –22)* HC-B4TN-3, HC-B4TW-3 T10702N-0 950 2080 950 2080 108” to 98” 172 lb. to T10702N-10 (-0 to –10)* Certification Basis: 14 CFR Part 35 effective April 3, 1967 with amendments 35-1 and 35-2 thereto. Type Certificate no. P40EA issued April 27, 1971 under Delegation Option Authorization procedures of 14 CFR Part 21 Subpart J. Date of application for T.C.: April 6, 1971 The following models were included under the original certification basis: HC-B4TN-3, HC-B4TN-5 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-B4TN-3, HC-B4TN-5 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-B4TN-3, HC-B4TN-5 The following models were added, updated or revised in accordance with 14 CFR Part 35 with amendments 35-1 through 35-8 effective October 24, 2008: HC-B4TW-3, HC-B4TN-5 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-B4TN-3, HC-B4TW-3 The following models were added, updated or revised in accordance with 14 CFR Part 35 with amendments 35-1 through 35-9A effective July 26, 2013: HC-B4TW-3 Production Basis: Production Certificate no. 10 Note 1: Hub Model Designation (See Notes 4 and 5) Page 3 of 5 P40EA, Revision 17 HC – B 4 T N - 3 A L when used denotes left hand rotation Any other character denotes minor change not affecting eligibility Denotes specific design features -3: external beta feedback mechanism -5: start locks, internal beta feedback mechanism N denotes special flange with 8 – 9/16” bolts and 2 dowels on a 4 1/4” B.C. W denotes special flange with a 3/8” spacer, 8 – 9/16” studs and 2 dowels on a 4 1/4” B.C. Hartzell blade shank size Number of blades Identifies basic design Hartzell Controllable Note 2: Blade Model Designation (See Notes 5 and 6) L T 101 73 FHB-2Q Number when used indicates inches cut off from (or added to if preceded by ‘+’) basic diameter Q when used denotes special 1” x 90 deg. factory-bent tip. R when used denotes round blade tip shape B, E or K denotes deicing boots H denotes hard alloy N denotes shank modification S denotes shot peened surface Any other character denotes a minor modification not affecting eligibility Basic blade model Basic diameter in inches for a three blade propeller. Corrections are as follows: * Add 1.0 inch. ** Add 1.5 inches. *** Add 1.25 inches for T10282+6 only. Add 1.0 inch for all others. Denotes needle bearing installation in blade shank L when used denotes left-hand rotation Note 3: Pitch Control (weight of pitch control extra) (See Notes 4 and 10) (a) All models have counterweighted blades and use governor oil to decrease pitch. (b) All governors and propeller control systems must be approved as part of the aircraft installation regardless of manufacturer. (c) Maximum control pressure for all models: 500 psig (d) General Electric Czech Aviation H80-100 series engine has an option to use either a hydro-mechanical or electronically integrated propeller pitch control. Hartzell propeller model HC-B4TW-3( ) is approved for use with either option, and complies with the propeller airworthiness requirements when used with either. Any change to the engine, including its control system, which affects or may affect the propeller approval must be substantiated to demonstrate that the propeller, as integrated with the changed engine, including its control system, still complies with the propeller certification basis. Also, any change to the engine resulting from a change to the propeller must be substantiated to demonstrate that the changed engine still complies with the engine certification basis. P40EA, Revision 17 Page 4 of 5 Note 4: Feathering (a) The -3 and -5 models incorporate feathering and unfeathering features. Reversing (a) The -3 and -5 models are approved for installation as reversing propellers with reversing controls. 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 Note 2) (a) Hard and soft alloy blades of the same model designation are interchangeable. (b) Blades with the suffix “N” in the basic model number may replace those without an “N” either individually or as a set. Likewise, blades with the suffix “S” in the basic model number may replace those without an “S” either individually or as a set. When the aircraft Type Certificate or Supplemental Type Certificate specifies blades with the letters “N” or “S” in the basic model number, those characters must be retained in all replacement blade models. For example: Blades with neither “N” nor “S” may be replaced by “N”, “S” or “NS” blades, “N” blades may be replaced by “NS” blades, “S” blades may be replaced by “NS” blades. (c) Refer to Hartzell Service Letter HC-SL-30-260 for ice protection system component interchangeability. Note 7: Accessories (a) 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) (b) Propeller deice (weight of deice 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) Note 8: Shank Fairings Not applicable. Note 9: Special Limits Not applicable. Note 10: The propeller installation must be approved as part of the aircraft type certificate to 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. Note 11: Retirement Time (a) Life limits and mandatory inspections. (1) Airworthiness limitations, if any, are specified in Hartzell Owner’s Manual 139. (2) The propeller Certification Branch Office must evaluate the propeller installation for each new aircraft installation to assess possible changes in the airworthiness limitations. Page 5 of 5 P40EA, Revision 17 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 recommended overhaul periods. END