TCDS P-892

DEPARTMENT OF TRANSPORTATION P-892 FEDERAL AVIATION ADMINISTRATION Revision 20 Hartzell HC-92Z, BHC-92Z March 28, 2006 TYPE CERTIFICATE DATA SHEET NO. P-892 Propellers of models described he rein conforming with this data sheet (which is part of Type Certificate No. P-892) 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 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 Two Hub models HC-92ZF-1, -2, -6; HC-92ZK-1, -2, -6, -8; HC-92ZL-2; BHC-92ZF-1, -3, -8 (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) HUB MODELS HC-92ZF-1, -2, -6; HC-92ZK-1; BHC-92ZF-1, -3, -8 8447-0 280 2800 280 2800 84” to 78” 73.0 lb. to 8447-6 (-0 to -6) 8847-0 280 2600 280 2600 88” to 82” 78.0 lb. to 8847-6 (-0 to -6) 9349-0 280 2400 280 2400 92 5/8” to 77 5/8” 82.0 lb. to 9349-15 (-0 to -15) 9350-0 280 2400 280 2400 92 5/8” to 87 5/8” 82.0 lb. to 9350-5 (-0 to -5) 9350-5 280 2600 280 2600 87 5/8” to 77 5/8” 81.0 lb. to 9350-15 (-5 to -15) HUB MODEL HC-92ZL-2 8447-0 180 2800 180 2800 84” to 78” 73.0 lb. to 8447-6 (-0 to -6) 8447-8 180 2700 180 2700 76” to 70” 72.0 lb. to 8447-14 (-0 to -14) P-892, Revision 20 Page 2 of 6 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) HUB MODELS HC-92ZK -2, -6, -8 8447-8 250 2800 250 2800 76” to 70” 72.0 lb. to 8447-14 (-8 to -14) 8447A-8 250 2800 250 2800 76” to 70” 72.0 lb. to 8447A-14 (-8 to -14) 8447-12A 250 2800 250 2800 72” to 68” 72.0 lb. to 8447-16A (-12 to -16) 8447A-12A 250 2800 250 2800 72” to 68” 72.0 lb. to 8447A-16A (-12 to -16) * Weights apply to -2 and -3 hub models. Subtract 8 lb. for -1 hubs, 6 lb. for -6 hubs and 9 lb. for -8 hubs. Certification Basis: CAR 14 effective May 18, 1954 with Amendments 14-1 and 14-2. Type Certificate No. P-892 issued July 22, 1955. Models approved to the original certification basis include the following: HC-92ZF-1, -2, -6; HC-92ZK-1, -2, -6, -8; HC-92ZL-2; BHC-92ZF-1, -8 The following models were approved under Delegated Option Authorization Procedures of 14 CFR Part 21, Subpart J. Models added, updated or revised in accordance with 14 CFR Part 35 effective April 3, 1967 with amendments 35-1 and 35-2 include the following: BHC-92ZF-3 Date of application for Type Certificate: April 15, 1955. Production Basis: Production Certificate no. 10 NOTE 1: Hub Model Designation B HC- 9 2 Z F - 2 A L denotes left hand rotation Any other character denotes a minor change not affecting eligibility Denotes specific design features (see NOTE 4) -1: constant speed with counterweighted blades and 11.2 sq. in. piston area -2: constant speed and feathering with counterweighted blades and 11.2 sq. in. piston area -3: constant speed and reversing with counterweighted blades and 11.2 sq. in. piston area -6: constant speed with non-counterweighted blades and 23.0 sq. in. piston area -8: constant speed with non-counterweighted blades and 11.2 sq. in. piston area F denotes special flange with six 1/2” bolts and two 1/2” dowels on a 4” bolt circle K denotes SAE no. 2 flange with six 1/2” bolts and four 3/4” bushings on a 4-3/4” bolt circle L denotes SAE no. 2 flange with six 7/16” bolts and four 3/4” bushings on a 4-3/4” bolt circle Hartzell blade shank size (see NOTE 6) Number of blades Identifies basic design Hartzell Controllable Indicates dowel location with respect to centerline through blade sockets when viewing hub from flange mounting face (“F” flange hubs only) Blank: 90 and 270 deg. clockwise B: 30 and 210 deg. clockwise Page 3 of 6 P-892, Revision 20 NOTE 2: Blade Model Designation L 84 47 A - 3Q Number of inches cut off from basic diameter Q when used denotes special 1” x 90 deg. factory-bent tip for cutoff diameter A when following the dash number indicates a thinner and narrower tip R when used denotes specifically rounded tip for cutoff diameter * A denotes 0° sweepback * B or K denotes deicing boots N denotes shank modification (see NOTE 6) Any other character denotes a minor change not affecting eligibility Basic model or template Basic diameter in inches L when used denotes left hand blade * Some blades which use square or rounded tip shapes may not contain the letters “S” or “R” in their model designation. These characters are used to distinguish blades when two or more tip shapes are available at the dame diameter. Blades identified with an “A” following the model designation denote 0° sweepback (otherwise sweepback is 1°). Diameter limits shown are nominal diameters of the assembled propeller and do not include the + 1/8 inch manufacturing tolerance permissible for propellers with basic diameter less than 14 feet. NOTE 3: Pitch Control (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 (see NOTE 6) 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, -2 and -3 models have counterweighted blades and use oil to decrease pitch. The -6 and -8 models do not have counterweighted blades and use oil to increase pitch. (See NOTE 4) (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. (see NOTE 10) NOTE 4: Feathering and Reversing (a) Feathering The -2 model incorporates feathering and unfeathering features. The -1, -3, -6 and -8 models do not feather. (b) Reversing The -3 model is approved for installation as a reversing propeller 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) P-892, Revision 20 Page 4 of 6 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) Only blades listed in the same groups of the following listed groups are sufficiently similar aerodynamically and vibrationwise to permit interchangeability in the same diameter without a flight test. Group (a) 8447(N)-8 to -14, 8447A(N)-8 to -14 Group (b) 8447(N)-12A to -16A, 8447A(N)-12A to -16A Group (c) 8447(N)-12R to -16R, 8447A(N)-12R to -13R (b) Governors (See NOTE 3) (1) 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. (2) The Hartzell B-0 is the only model which is interchangeable with the Hamilton Standard 1M12 and 1Q12. Other Hartzell models are not interchangeable with any Hamilton Standard model without modification of the latter. (c) Propellers (See NOTES 1 and 2) (1) The following propeller models may be replaced by corresponding propellers listed in Type Certificate Data Sheet P16EA as indicated below. Propellers listed in this data sheet are not approved to replace propellers listed in P16EA. For example (B)HC-92W( ) models using blades with a “W” prefix may replace corresponding (B)HC-92Z( ) models using blades with no prefix. TCDS P-892 TCDS P16EA HC-92ZK-1D HC-92WK-1D BHC-92ZF-1D1 BHC-92WF-1D1 HC-92ZK-2B HC-92WK-2B BHC-92ZF-3 BHC-92WF-3 BHC-92ZF-3LG BHC-92WF-3LG HC-92ZK-8D HC-92WK-8D HC-92ZK-8L HC-92WK-8L Page 5 of 6 P-892, Revision 20 NOTE 7: Accessories (a) Propeller anti-icing (weight of anti-icing system extra) (1) Approved with fluid feed boots listed on Hartzell approved type design data when installed in accordance with Hartzell specification H-S-2 or Hartzell Manual no. 133( ). (2) Approved with Hartzell fluid feed equipment on propeller models for which equipment is available. (b) Propeller deicing (weight of deicing system extra) (1) Approved with Goodrich electrical deicing kit 5EXXXX, 7EXXXX, 77-XXX, 67-XXX or 65-XXX when installed in accordance with Goodrich Report no. ATA 30-60-07. (2) Approved with Goodyear Ice Guards (electrical propeller deicer) when installed in accordance with instructions outlined in Goodyear Report no. AP-147 dated October 23, 1961. (3) Approved with ice protection equipment when listed on Hartzell type design data. (c) Propeller spinner (weight of spinner extra) Approved with Hartzell and other manufacturers’ spinners when listed on approved 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 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 approve d 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 HC-92Z 8447-( )R 8447A-( )R LYC O-360 and IO-360 series, 8.5:1 compression ratio or less, 180 HP at 2700 RPM or less 72 71 Do not exceed 23 inches manifold pressure below 2300 RPM HC-92Z 8447-( )A 8447A-( )A LYC O-360 and IO-360 series, 8.5:1 compression ratio or less, 180 HP at 2700 RPM or less 72 70 Do not exceed 23 inches manifold pressure below 2300 RPM HC-92Z 8447A-( ) LYC O-360-A1A, -A1D 76 72 Avoid continuous operation between 2250 and 2500 RPM BHC-92Z 8447 TCM IO-470-J 84 82 none P-892, Revision 20 Page 6 of 6 Hub Blade Max. Dia. Min. Dia. Model Model Engine Model (inches) (inches) Placards HC-92Z 8447 LYC O-540 series, two 6th order dampers, 8.5:1 compression ratio or less, 250 HP at 2575 RPM or less 84 82 none BHC-92Z 8847 TCM O-470-B, -M 88 88 none HC-92Z 8847 TCM IO-470 series, 8.6:1 compression ratio or less, 260 HP at 2625 RPM or less. Centerline of blades 60° and 240° clockwise from no. 1 crankthrow facing engine from propeller end. 88 88 none HC-92Z 8847 LYC O-540-A1A5 88 88 none 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 or STC 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 Manuals 105( ), 110( ), 114( ), 119( ) or Service Letter 61( ). NOTE 12: Special Notes Refer to Manual 202( ) for overspeed and overtorque limits. END