TCDS P30EA

DEPARTMENT OF TRANSPORTATION P30EA FEDERAL AVIATION ADMINISTRATION Revision 4 Hartzell HA-B3P TYPE CERTIFICATE DATA SHEET NO. P30EA July 29, 2004 Propellers of models described herein conforming with this data sheet (which is part of Type Certificate No. P30EA) and other approved data on file with the Federal Avia tion 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 Inc. Piqua, OH 45356 Type Ground adjustable Engine shaft SAE Spline (see NOTE 1) Hub material Alloy Steel Blade material Aluminum Alloy Number of blades Three Hub models HA-B3P30-1 (See NOTE 1) 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) P10152-5 1/2 450 2300 450 2300 95 1/2” to 90” 120 lb. to P10152-11 (-5 1/2 to -11) P10160-6 450 2300 450 2300 95” to 90” 121 lb. to P10160-11 (-6 to -11) Certification Basis: 14 CFR Part 35 with amendment 35-1 effective February 1, 1965. Type certificate no. P30EA issued May 1, 1967 under Delegated Option Authorization procedures of 14 CFR Part 21 Subpart J. Date of application for Type Certificate: April 6, 1967 Production Basis: Production Certificate no. 10 NOTE 1. Hub Model Designation HA - B 3 P 30 - 1 D L denotes left hand rotation Any other character denotes minor change not affecting eligibility Denotes specific design features (see NOTE 4) SAE no. 30 spline Hartzell blade shank size Number of blades Identifies basic design Hartzell Ground Adjustable P30EA, Revision 4 2 of 3 NOTE 2. Blade Model Designation LP 101 52 N - 5 ½ Q Number of inches cut off from basic diameter Q when used denotes special 1” x 90 deg. factory-bent tip for cutoff diameter 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 P denotes enlarged shank with bronze sleeves NOTE 3. Pitch Control Not applicable NOTE 4. (a) Feathering Not applicable (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) Propellers Propellers listed in this data sheet are approved to replace corresponding propellers listed on TCDS P-914 provided the propeller designations are the same except that “Z” character is replaced by “P” and that the associated blades are prefixed by the letter “P”. (See NOTES 1 and 2) NOTE 7. Accessories Not applicable NOTE 8. Shank Fairings Not applicable 3 of 3 P30EA, Revision 4 NOTE 9. Special Limits Table of Propeller - Engine Combinations Approved Vibrationwise for Use on Normal Category Single Engine Tractor Aircraft The maximum and minimum propelle r 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 c onfigurations on the engine type certificat e unless specifically stated otherwise. Modifications to the engine or airframe that alter the power of the engine models listed be low during any phase of operation have the potential to increase propeller stresses and are not appr oved by this list. Such modi fications include, but are not limited to, the addition of a turbocharger or turbonormalizer, increased boost pressure, increas ed compression ratio, increased RPM, altered ignition timing, electronic ignition, full authority digital engine controls (FADEC), or tuned induction or exhaust. 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 HA-B3P30 P10152-5 ½ P&WA R-985 series, 6:1 compression ratio or less, 450 HP @ 2300 RPM or less, one 4 ½ order and one 9th order dampers 95 ½ 95 ½ none HA-B3P30 P10160-6 P&WA R-985 series, 6:1 compression ratio or less, 450 HP @ 2300 RPM or less, one 4 ½ order and one 9th order dampers 95 95 Avoid continuous operation between 1600 and 1800 RPM 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 Manual 108A or Service Letter 61( ). NOTE 12. Special Notes Refer to Hartzell Manual no. 202( ) for overspeed and overtorque limits. END