TCDS P6EA

DEPARTMENT OF TRANSPORTATION P6EA FEDERAL AVIATION ADMINISTRATION Revision 13 Hartzell HC-A3V, HC-A3MV PHC-A3V, PHC-A3MV EHC-A3V, EHC-A3MV December 16, 2002 TYPE CERTIFICATE DATA SHEET NO. P6EA Propellers of models described herein conforming with this data sheet (which is part of Type Certificate No. P6EA) 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 Inc. Piqua, OH 45356 Type Constant speed; hydraulic (see NOTES 3 and 4) Engine Shaft Spline shaft, special flange (see NOTE 1) Hub material Alloy steel Blade material Aluminum alloy Number of blades Three Hub models ( )HC-A3(M)VF-(2,3,4,5,7), HC-A3(M)VF-1, HC-A3(M)VK-(1,2,4), HC-A3(M)V20-(1,2,3,5), HC-A3(M)V21-2, EHC-A3(M)VF-2 (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) V7636D-0 336 2850 336 2850 76 5/8” to 70 5/8” 90.0 lb. to V7636D-6 (-0 to -6) V8433-0 400 2650 400 2650 84 5/8” to 72 5/8” 94.0 lb. to V 8433-12 (-0 to -12) V8485-0 346 2030 400 2030 84 5/8” to 72 5/8” 94.0 lb. to V8485-12 (-0 to -12) V8833-0 380 2450 380 2450 88 3/8” to 78 3/8” 97.0 lb. to V8833-10 (-0 to -10) V9333C-0 340 2200 340 2200 93 5/8” to 80 5/8” 100.0 lb. to V9333C-13 (-0 to -13) V9333D-0 340 2400 340 2400 93 5/8” to 80 5/8” 100.0 lb. to V9333D-13 (-0 to -13) V10133-0 390 2180 390 2180 101 5/8” to 88 5/8” 103.0 lb. to V10133-13 (-0 to -13) V10133D-0 390 2180 390 2180 101 1/2” to 98 1/2” 103.0 lb. to V10133D-3 (-0 to -3) V10133D-3 420 2180 420 2180 98 1/2” to 88” 103.0 lb. to V10133D-12.5 (-3 to -12.5) For #20 or #21 spline shaft add 3 lb. For HC-A3(M)V(F,K)-4 subtract 7 lb. P6EA Page 2 of 7 Certification Basis: ( )A3V( ) models: CAR Part 14 with amendment 14-1 effective Dec. 15, 1956. ( )A3MV( ) models: FAR Part 35 with amendments 35-1 through 35-6 effective Aug. 18, 1990 Type Certificate No. P6EA issued Aug. 15, 1962 Date of application for Type Certificate: July 27, 1962 Models certificated on or subsequent to March 7, 1967 are certified under Delegation Option Authorization provisions of FAR Part 21 Subpart J. Production Basis: Production Certificate no. 10 NOTE 1. Hub Model Designation ( ) HC A 3 V ( ) - ( ) ( ) L denotes left hand rotation Any other character denotes a minor change not affecting eligibility Denotes specific design features (see NOTE 4) F denotes special flange with six 1/2” bolts and two 1/2” dowels on a 4” bolt circle K denotes SAE # 2 flange with six 1/2” bolts and four 3/4” drive bushings on a 4-3/4” bolt circle 20 denotes SAE #20 spline 21 denotes SBAC #2 spline V denotes a double shoulder blade retention system MV denotes a single shoulder blade retention system Number of blades Identifies basic design Hartzell Controllable Dowel location with respect to blade centerline when viewing hub from flange mounting face Blank: 90 and 270 deg. clockwise E,P Align T/C marks on propeller and engine flange NOTE 2: Blade Model Designation L V 84 33 ( ) - ( )Q Number of inches cut off from basic diameter Q when used denotes special 1” x 90 deg. factory-bent tip. No cutoff permitted. R when used denotes specifically rounded tip for cutoff diameter. * C or D denotes a dimensional modification from the original design B denotes deicing boots A when used with 8433 blades denotes 1 deg. of sweepback in lieu of the standard 2 deg. R or S when used denote round or square tips respectively for the basic diameter * N denotes a shank modification (see NOTE 6) Note: one or more letters may be used as appropriate Basic blade model Basic diameter in inches V denotes a double shoulder blade shank with internal needle bearing MV denotes a single shoulder blade shank with internal needle bearing L when used denotes left hand blade * Some blade designs incorporate round or square tip shapes, yet have no “R” or “S” in their model designation. This character is used to distinguish blades when two or more tip shapes are available at the same diameter. P6EA Page 3 of 7 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 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) Approved with Hoof model 1-000-007 series Wt.: 3.5 lb. (c) Approved with Hamilton Standard models 1A4, 1M12, 1P12, and 1Q12 Wt.: 4.5 lb. (d) Approved with Woodward model X210XXX Wt.: 3.5 lb 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. The HC-A3(M)V(F,K)-4 propeller has no counterweights, hence require a governor which supplies oil to increase pitch. Governors on drawing C-4770 meet this requirement. NOTE 4. (a) Feathering The -1 and -4 models do not feather. The -2, -3, -5 and -7 models incorporate feathering and unfeathering features. The -4 models do not have counterweights. (b) Reversing The -3, -5 and -7 models incorporate reversing when used with the appropriate 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) Blades (1) Blades with an “N” suffix, such as (M)V8433N, are interchangeable with corresponding blades without the “N” suffix, provided that all blades in the same propeller are identical. (2) Blades with “M” prefix, such as MV8433N, can be substituted for corresponding blades without the “M” prefix provided that all blades in the same propeller are identical and that the hub model also contains the characters “MV”. Blades without the “M” prefix cannot be substituted for those with the “M” prefix. (b) Propellers (1) Propellers listed in this data sheet may replace corres ponding propellers listed in Type Certificate Data Sheets P14EA, P-913 and P-884. (2) Propellers listed in T.C.D.S. nos. P14EA, P-913 and P-884 may not repl ace propellers listed in this data sheet. (3) In the model designation HC-A3(V,MV)( ), the “A” may be substituted for propeller models with “8” in the same location and “V” or “MV” may be substituted for propeller models with “X” in the same location as listed in T.C.D.S nos. P14EA, P-913 and P-884. (4) In the model designation HC-A3(V,MV)( ), the “M V” may be substituted for “V”, however “V” may not replace “MV”. (c) Governors 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. P6EA Page 4 of 7 NOTE 7. Accessories (a) Propeller anti-icing (weight of anti-icing equipment extra) (1) Approved with fluid feed boots listed in Hartzell approved type design data when installed in accordance with Hartzell specification H-S-2 or Manual 133( ). (2) Approved with fluid feed equipment listed in Hartzell approved type design data on propeller models (b) Propeller deicing (weight of deicing equipment extra) (1) Approved with Goodrich electrical deicing kit 5EXXXX-X, 7EXXXX-X, 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 Safeway deicing boot 6848 and 5735 kit when installed in accordance with manufacturer’s instructions. (c) Propeller spinner (weight of spinner extra) (1) Approved with Hartzell and other manufacturer’s spinners when listed in Hartzell approved type design data. NOTE 8. Shank Fairings Not Applicable NOTE 9. Special Limits Table of Propeller - Engine Combinations Approved Vibrationwise foe 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 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 ha ve the potential to increase propeller stresses and are not approved by this list. Such modifications include, but are not limite d to, the addition of a turbocharger or turbonormalizer, increased boost pressure, increased compression ratio, increased RPM, altere d 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 EHC-A3VF PHC-A3VF 7636-4Q TCM IO-520-A, -B, -C, -D, -E, -F, -J 72 72 none EHC-A3VF V7636D TCM IO-470-U; 8.6:1 compression ratio or less; two 6th order, one 5th order and one 4.5 order dampers; 260 HP at 2625 RPM or less. T/C marks must be aligned. 76 5/8 74 none EHC-A3VF V7636N-2Q TCM IO-470-U 74 5/8 74 5/8 none P6EA Page 5 of 7 HC-A3VF PHC-A3VF V7636D TCM IO-470 series; 8.6:1 compression ratio or less; two 5th and two 6th order dampers; 260 HP at 2625 RPM or less 76 5/8 76 5/8 none PHC-A3VF EHC-A3VF V7636D TCM IO-520 series; two 6th, one 5th and one 4th order dampers; 8.5:1 compression ratio or less; 300 HP at 2850 RPM or less 76 5/8 74 none Hub Blade Max. Dia. Min. Dia. Model Model Engine Model (inches) (inches) Placards HC-A3VK V7636D LYC O-540 and IO-540 series; 8.5:1 compression ratio or less; two 6th order dampers; 250 HP at 2575 RPM or less; centerline of one blade must be in line with no. 1 crank throw facing engine from propeller end. 76 5/8 70 5/8 none HC-A3VK V7636D LYC O-540 and IO-540 series; 8.7:1 compression ratio or less; one 6th and one 5th order dampers; 290 HP at 2575 RPM or less; centerline of one blade must be in line with no. 1 crank throw facing engine from propeller end. 76 5/8 70 5/8 none HC-A3V21 LV7636D Bristol Siddeley Gypsy Queen 30 MK.2 series; 6.5:1 compression ratio or less; 250 HP at 2500 RPM or less 76 1/4 75 Maintain manifold pressure above 15” Hg for airspeeds above 140 MPH PHC-A3VF V8433 TCM IO-520-BB, NB TSIO-520-DB 84 1/4 74 1/4 none PHC-A3VF V8433 TCM IO-470 series; 7:1 compression ratio or less; one 5th and one 6th order dampers; 225 HP at 2600 RPM or less 80 5/8 78 5/8 none HC-A3VF PHC-A3VF EHC-A3VF V8433 TCM IO-470 series; four 6th order dampers; 8.6:1 compression ratio or less; 260 HP at 2625 RPM or less 84 5/8 80 none HC-A3VF PHC-A3VF V8433 TCM IO-520 series; 8.5:1 compression ratio or less; two 6th, one 5th and one 4th order dampers; 285 HP at 2700 RPM or less 84 1/4 78 1/4 none PHC-A3VF V8433 TCM IO-520-BA 82 5/8 78 1/4 none HC-A3V20 V8433 LYC GO-435, GO-435-C2B, -C2B1 84 5/8 84 5/8 none HC-A3V20 V8433 LYC GO-480-A1A, -D1A, B, -B1B, -B1C, -B1D 84 5/8 84 5/8 none HC-A3V20 V8433 LYC GO-480-B1A6 84 5/8 84 5/8 Avoid continuous operation on the ground between 1300 and 1650 RPM and between 2100 and 2500 RPM P6EA Page 6 of 7 Hub Blade Max. Dia. Min. Dia. Model Model Engine Model (inches) (inches) Placards HC-A3VK V8433 LYC O-540 and IO-540 series; 8.7:1 compression ratio or less; one 6th and one 5th order dampers; 290 HP at 2575 RPM or less; centerline of one blade must be in line with no. 1 crank throw facing engine from propeller end. 80 5/8 72 5/8 none HC-A3VK V8433 LYC O-540 and IO-540 series; 8.7:1 compression ratio or less; one 6th and one 5th order dampers; 290 HP at 2575 RPM or less; centerline of one blade must be in line with no. 1 crank throw facing engine from propeller end. 80 5/8 72 5/8 none HC-A3VK V8433 LYC IO-540-K1B5, -K1C5, -L1A5, -M1A5 77 5/8 76 5/8 none HC-A3VK V8433 LYC IO-720 series; 8.7:1 compression ratio or less; six 4th order, one 5th order and one 3.5 order dampers; 400 HP at 2650 RPM or less; centerline of one blade must be in line with no. 1 crank throw facing engine from propeller end. 77 5/8 75 5/8 Avoid continuous operation between 1800 and 2000 RPM when above 24” Hg M.P. HC-A3VK V8433 V8433S LYC IO-720 series; 8.7:1 compression ratio or less; six 4th order, one 5th order and one 3.5 order dampers; 400 HP at 2650 RPM or less; centerline of one blade must be in line with no. 1 crank throw facing engine from propeller end. 84 5/8 77 3/4 none HC-A3VF V8833 TCM GIO-470 series; 8.6:1 compression ratio or less; 0.75:1 reduction gear ratio; six heavy 3rd order dampers; 310 HP at 3200 RPM or less. 88 3/8 88 3/8 none HC-A3VF PHC-A3VF V8833 TCM GTSIO-520 series; 7.5:1 compression ratio or less; 0.75:1 reduction gear ratio; six 3rd order dampers; 340 HP at 3200 RPM or less. 88 3/8 86 3/8 none HC-A3V20 V8833 LYC GO-480-C1B6 86 3/8 82 3/8 Avoid continuous operation in flight below 2400 RPM HC-A3V20 V9333C LYC GO-435-C2B 93 5/8 87 5/8 none HC-A3V20 V9333C LYC GO-435-C2B1 90 5/8 90 5/8 none HC-A3V20 V9333C LYC GO-480-C1D6, -C2C6, -C2D6, -G2D6, -G2F6 93 5/8 89 5/8 none P6EA Page 7 of 7 Hub Blade Max. Dia. Min. Dia. Model Model Engine Model (inches) (inches) Placards HC-A3V20 V9333C LYC GO-480-F2A 90 5/8 87 5/8 none HC-A3V20 V9333C LYC GO-480-F2A6, -F4A6, -F4B6 93 5/8 87 5/8 none HC-A3V20 V9333C LYC GSO-480-A1A6, -B1A6, IGSO-480-A1C6 93 5/8 88 5/8 none HC-A3V20 V9333C LYC GSO-480-B2D6 93 5/8 91 5/8 Avoid continuous operation between 2800 and 3100 RPM NOTE 10. Special Notes Propeller installation must be approved as part of the aircraft Type Certificate and demonstrate compliance with the applicable aircraft airworthiness requirements. NOTE 11. Retirement Time (a) Life Limits and Mandatory Inspections (1) Airworthiness limitations, if any, are specified in Hartzell Manuals 114( ), 118( ) and 122( ). …..END…..