TCDS P10NE

DEPARTMENT OF TRANSPORTATION P10NE FEDERAL AVIATION ADMINISTRATION Revision 41 Hartzell HC-D4, HC-E4 TYPE CERTIFICATE DATA SHEET NO. P10NE August 13, 2024 Propellers of mod els described herein conforming with this data sheet (which is part of Type Certificate No. P10NE) 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 Four Hub models HC-D4N-(2,3,5); HC-D4P-5; HC-E4N-(2,3,5); HC-E4A-(2,3); HC-E4P-(3,5), HC-E4W-(3,5) 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) HC-D4N-(2,3) D9383 950 2000 950 2000 94” to 84” 152 lb. Aluminum Alloy to D9383-10 (-0 to -10) D9512 950 2040 950 2040 96” to 86” 152 lb. Aluminum Alloy to D9512-10 (-0 to -10) HC-D4N-3 D9083 950 2000 950 2000 91” to 81” 145 lb. Aluminum Alloy to D9083-10 (-0 to -10) D9290 750 2200 750 2200 93” to 83” 136 lb. Aluminum Alloy to D9290-10 (-0 to -10) D9510 750 2200 750 2200 96” to 86” 146.5 lb. Aluminum Alloy to D9510-10 (-0 to -10) D9511 850 2200 850 2200 96” to 86” 152 lb. Aluminum Alloy to D9511-10 (-0 to -10) D9515 850 2000 850 2000 96” to 86” 152 lb. Aluminum Alloy to D9515-10 (-0 to -10) D9901 750 2200 750 2200 100” to 90” 152 lb. Aluminum Alloy to D9901-10 (-0 to -10) HC-D4N-5 D9327 1100 2000 1100 2000 94” to 84” 151 lb. Aluminum Alloy to D9327-10 (-0 to -10) D8501 800 2000 800 2000 86” to 76” 130 lb. Aluminum Alloy To D8501-10 (-0 to -10) P10NE, Revision 41 Page 2 of 7 Maximum Diameter Approx. Max. Wt. Complete Blades Continuous Takeoff Limits (For Reference Only) Notes (see Note 2) HP RPM HP RPM (See Note 10) (see Notes 3 and 7) (See Note 10) HC-D4P-5 D10541 1000 1700 1000 1700 106” to 96” 165 lb. Aluminum Alloy to D10541-10 (-0 to -10) HC-E4P-5 E11990 1000 1540 1000 1540 120” 132 lb. Aramid Composite HC-E4A-3 E10477 1200 1700 1200 1700 105” to 95” 160 lb. Aluminum Alloy to E10477-10 (-0 to -10) E10478 1200 1700 1200 1700 105” to 95” 168.5 lb. Aluminum Alloy to E10478-10 (-0 to -10) E10479 1200 1700 1200 1700 105” to 97” 156 lb. Aluminum Alloy to E10479-8 (-0 to -8) E10950 1400 1735 1400 1735 110” 132 lb. Aramid Composite HC-E4A-2 E9612 1300 2000 1300 2000 97” to 87” 155 lb. Aluminum Alloy to E9612-10 (-0 to -10) E9673 1600 2000 1600 2000 97” to 87” 155 lb. Aluminum Alloy to E9673-10 (-0 to -10) HC-E4N-(2,3,5); HC-E4A-(2,3); HC-E4P-,5 D9390 950 2000 950 2000 94” to 84” 145 lb. Aluminum Alloy to D9390-10 (-0 to -10) HC-E4N-(3,5); HC-E4A-3; HC-E4P-5 D9391 950 2000 950 2000 94” to 84” 145 lb. Aluminum Alloy to D9391-10 (-0 to -10) HC-E4N-3 E8190 750 2200 750 2200 81.75” 120 lb. Aramid Composite D8292 800 2000 800 2000 82.5” to 76.5” 121 lb. Aluminum Alloy to D8292-6 or or (-0 to -6) 680 2200 680 2200 D8295 550 2200 550 2200 82.5” to 72.5” 122 lb. Aluminum Alloy to D8295-10 (-0 to -10) D8990 750 2200 750 2200 90” to 80” 142 lb. Aluminum Alloy to D8990-10 (-0 to -10) E9083 950 2000 950 2000 91” to 81” 145 lb. Aluminum Alloy to E9083-10 (-0 to -10) D9290 750 2200 750 2200 93” to 83” 136 lb. Aluminum Alloy to D9290-10 (-0 to -10) D9511 850 2200 850 2200 96” to 86” 152 lb. Aluminum Alloy to D9511-10 (-0 to -10) Page 3 of 7 P10NE, Revision 41 Maximum Diameter Approx. Max. Wt. Complete Blades Continuous Takeoff Limits (For Reference Only) Notes (see Note 2) HP RPM HP RPM (See Note 10) (see Notes 3 and 7) (See Note 10) HC-E4N-3 (cont’d) E9512 950 2040 950 2040 96” to 86” 155 lb. Aluminum Alloy E9512-10 (-0 to -10) D9900 900 2000 900 2000 100” to 90” 145 lb. Aluminum Alloy to D9900-10 (-0 to -10) D9901 750 2200 750 2200 100” to 90” 154 lb. Aluminum Alloy to D9901-10 (-0 to -10) NC9208+2 850 2000 850 2000 95” to 83” 115 lb. Carbon Composite to NC9208-10 (+2 to -10) E10703 900 2000 900 2000 108” to 98” 153 lb. Aluminum Alloy to E10703-10 (-0 to -10) GC11114 900 1900 900 1900 110” to 100” 122 lb. Carbon Composite to GC11114-10 (-0 to -10) HC-E4P-3 E10479 1200 1700 1200 1700 105” to 97” 156 lb. Aluminum Alloy to E10479-8 (-0 to -8) HC-E4N-2 E9512 950 2040 950 2040 96” to 86” 152 lb. Aluminum Alloy to E9512-10 (-0 to -10) HC-E4N-5 E9327 1100 2000 1100 2000 94” to 84” 150 lb. Aluminum Alloy to E9327-10 (-0 to -10) D9690 950 2000 950 2000 97” to 87” 154 lb. Aluminum Alloy to D9690-10 (-0 to -10) E9782 750 1591 750 1591 97.7” to 87.7” 160 lb Aluminum Alloy To E9782-10 (-0 to -10) NC10904 1100 1591 1100 1591 110” to 100” 134 lb. Carbon Composite to NC10904-10 (-0 to -10) E10991 950 1591 950 1591 109.5” to 99.5” 172 lb. Aluminum Alloy to E10991-10 (-0 to -10) HC-E4N-(2,3,5) E8501 800 2000 800 2000 86” to 76” 130 lb. Aluminum Alloy to E8501-10 or or (-0 to -10) 680 2200 680 2200 P10NE, Revision 41 Page 4 of 7 Maximum Diameter Approx. Max. Wt. Complete Blades Continuous Takeoff Limits (For Reference Only) Notes (see Note 2) HP RPM HP RPM (See Note 10) (see Notes 3 and 7) (See Note 10) HC-E4W-3 D8990 777 2080 777 2080 90” to 80” 142 lb. Aluminum Alloy to D8990-10 (-0 to -10) D9290 750 2200 750 2200 93” to 83” 136 lb. Aluminum Alloy to D9290-10 (-0 to -10) E9083 950 2080 950 2080 91” to 81” 145 lb. Aluminum Alloy to E9083-10 (-0 to -10) D9900 850 2080 850 2080 100” to 90” 142 Aluminum Alloy to D9900-10 (-0 to -10) HC-E4W-5 E10305 1100 1591 1100 1591 104” to 94” 173 lb. Aluminum Alloy to E10305-10 (-0 to -10) Page 5 of 7 P10NE, Revision 41 Certification Basis: 14 CFR Part 35 effective October 14, 1980 with amendments 1 through 5 thereto. Type Certificate No. P10NE issued January 18, 1985 under Delegated Option Authorization procedures of 14 CFR Part 21 Subpart J. Models approved to the original certification basis include the following: HC-D4N-(2,3,5); HC-D4P-5; HC-E4N-3; HC-E4P-5 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-D4N-5; HC-E4A-(2,3); HC-E4N-(2,3,5); HC-E4P-5; HC-E4W-(3,5) 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-E4N-3; HC-E4A-3; HC-D4N-3 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-E4A-2, HC-D4N-3, HC-E4W-3, HC-E4P-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-E4N-3, HC-E4N-5, HC-E4A-3 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-E4W-3, HC-E4N-3, HC-D4N-3, E4N-5 Production Basis: Production Certificate no. 10 Note 1: Hub Model Designation HC – D 4 N - 2 A K when used denotes a through-bolt hub mounting scheme L when used denotes left-hand rotation V when used indicates a hub that accommodates a GC blade shank Y when used with -3 models indicates optional start locks Any other character denotes minor change not affecting interchangeability or eligibility Denotes specific design features (see Note 4) -2: no beta feedback mechanism -3: external beta feedback mechanism -5: start locks, internal beta feedback mechanism N denotes flange with eight 9/16” bolts and two ½” dowels on a 4.25” bolt circle P is identical to N flange except uses four ½” dowels A denotes flange with twelve 9/16” bolts and two 5/8” dowels on a 5.125” bolt circle W is similar to N except uses studs in place of bolts Number of blades D specifies basic hub and blade retention E specifies modified hub and blade retention Hartzell Controllable P10NE, Revision 41 Page 6 of 7 Note 2: Blade Model Designation D 90 83 A K - 2 Number of inches cut off from (or added to if +) basic diameter B or K denotes deicing boots S when used with aluminum blades denotes a shot-peened exterior (see Note 6) C when used with 10950 blade model indicates alternate counterweight (see Note 6) H when used designates a blade manufactured with erosion protection on the leading edge Any other character denotes a minor modification not affecting eligibility Basic blade model Basic diameter in inches.* Add one inch correction for all blade models. Blade shank configuration: D or E denotes right-hand tractor NC denotes “N” shank right-hand tractor composite blade with counterweight GC denotes “G” shank right-hand tractor composite blade with counterweight HD or HE or HNC denotes right-hand pusher LD or LE or LNC denotes left-hand pusher JD or JE or JNC denotes left-hand tractor * Diameter limits are nominal diameters of the assembled propeller. They do not include the +/- one eighth inch manufacturing tolerance the FAA allows for propellers with basic diameter less than 14 feet. Note 3: Pitch Control (weight of pitch control extra) Maximum output pressure: HC-E4A-(2,3) models: HC-(D,E)4(N,P,W)-(2,5) models: HC-E4N-3KU model HC-(D,E)4(N,P,W)-3 models: 700 psig 610 psig 610 psig 500 psi (a) All propeller models have counterweighted blades and use governor oil to decrease pitch. (See Note 4) (b) The Hartzell propeller model HC-E4A-2( ) is controlled by an integrated control system which is part of the engine type design. The propeller model HC-E4A-2 complies with the propeller airworthiness requirements when used with the Pratt & Whitney PT6A-68 series engine only. 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. (c) All governors and propeller control systems must be approved as part of the aircraft installation regardless of manufacturer. (See Note 10) Note 4: Feathering The -2, -3 and -5 models incorporate feathering and unfeathering features. Reversing The -3 and -5 models are approved for installation as reversing propellers with appropriate reversing controls. 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 (a) Shot-peened blades may replace non shot-peened blades either individually or as a set. (see Note 2) (b) E10950()CB blades may replace E10950PB blades models either in pairs or as a set. Opposing pairs of blades in the hub must have the same designation. (see Note 2) (c) E10950PCK blades may replace E10950PK blades models either in pairs or as a set. Opposing pairs of blades in the hub must have the same designation. (see Note 2) Page 7 of 7 P10NE, Revision 41 (d) Refer to Hartzell Service Letter HC-SL-30-260 for ice protection system component interchangeability. Note 7: Accessories (See Note 10) (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 deicing (weight of deicing equipment extra) (1) Approved with Goodrich electrical deicing kit 5EXXXX-X, 7EXXXX-X, 65-XXX, 67-XXX, or 77-XXX when the specific kit number is listed on Hartzell type design data and installed in accordance with Goodrich Report no. ATA 30-60-07, Goodrich drawing no. 7E1284 or Beech installation drawing no. 50T-389045. (2) Approved with Safeway deice equipment when installed in accordance with Safeway Installation Manual no. 6927 or E-5735-14 and Hartzell Manual 133( ) for aluminum blades or Manual 135( ) for composite blades, and associated STC or PMA documents. (3) 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. (4) All propeller ice protection equipment must be approved as part of the aircraft installation regardless of manufacturer. (See NOTE 10) (c) Propeller pulley drive. (weight of pulley drive extra) (1) Propeller model HC-E4A-2( ) used on Beechcraft Models 3000 and AT-6( ) uses containment ring P/N 133-910029-11 and air conditioning system drive pulley P/N 133-910029-7 or 133-1400-1. (2) Propeller model HC-D4N-2( ) with blade model D9512( ) is approved with Pilatus Aircraft Ltd. air conditioning system pulley drive P/N PC-9-1401-1 and pulley centering ring P/N PC-9-1402-1. (3) Propeller model HC-D4N-2( ) with blade model D9512( ) is approved with EADS PZL air conditioning system pulley drive P/N 837.76.610-08-0. 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. 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 147( ) or 149( ). (2) The propeller CMACO 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 recommended overhaul periods. END