# TCDS P-206: Hamilton Standard Division - Type: Type certificate data sheet - Status: Current - Holder: Hamilton Standard Division - Revision: 6 - Revised: December 1, 1970 - Product: Propeller - Data sheet PDF: https://openairdocs.org/files/sha256/0f/96/0f961c2897d65c53229b9bfb4c6d6ecb938ab665c11e4ba0099015ebffcf1c77 - FAA DRS: https://drs.faa.gov/browse/excelExternalWindow/9FB43AAACD797B958525670F0066C154.0001 - Page: https://openairdocs.org/tcds/P-206 ## Models (2) As the data sheet lists them. - 2DX - 2D30 ## What the data sheet says From the PDF's text layer, line by line; tables lose their columns. The PDF is the record. ```text Page No. 1 2 3 Rev. No. 6 6 6 Reformatted 7/94. DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION P-206 Revision 6 Hamilton Standard 2D December 1, 1970 TYPE CERTIFICATE DATA SHEET NO. P-206 Propellers of models described herein conforming with this data sheet (which is part of type certificate no. 206) 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 Civil Air Regulations/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 Hamilton Standard Division United Aircraft Corporation Windsor Locks, Connecticut 06096 Type Hydraulically controllable (see NOTES 3 and 4) Engine shaft SAE No. 30 or X (X indicates special shaft sizes for foreign engines are eligible.) Hub material Steel Blade material Aluminum alloy Number of blades 2 Hubs eligible 2D30, 2DX, 8345, 8363, 8460, S-8460 and 50040 (see NOTES 1 and 4) Blade Eligible Maximum Continuous Takeoff Diameter Limits Hub and Blade Weight (See Note 2) HP RPM HP RPM (See Note 2) (Max Diameter) NOTES 6095-0 to 6095-24 550 2400 605 2640 9' 6"- 7' 6" 160 lbs. (-0 to -24) 6096 is the left-hand version of 6095. 5 6101-0 to 6101-24 550 2300 605 2420 10' 0" - 8' 0" 165 lbs. 8 (-0 to -24) 6102 is the left-hand version of 6101. 5 6127-0 to 6127-21 550 2200 605 2420 10' 9"- 9' 0" 179 lbs. (-0 to -21) 6128 is the left-hand version of 6127. 5 6167-0 to 6167-24 550 2400 605 2640 9' 6 - 7' 6" 160 lbs. (-0 to -24) 6168 is the left-hand version of 6167. 5 6237-0 to 6237-24 550 2400 605 2640 9' 6 - 7' 6" 160 lbs. (-0 to -24) 6238 is the left-hand version of 6237. 5 Certification basis Type Certificate No. 206 issued 20 June 1941. P206 Page 2 Production basis Production Certificate No. 14 NOTE 1. Hub Model Designation Minor change not affecting eligibility SAE propeller shaft size Blade shank size Number of blades 2 D 30 101- NOTE 2. Blade Model Designation If used, indicates telescoped; "S," square cutoff Nominal reduction from basic diameter in inches Operational features (may indicate particular deicing assembly), does not affect eligibility. Aerodynamic and structural features If used, indicates shank fairing design. A 6101 C 18 T- - The blade model designation suffixed with "T" indicates a diameter reduction by telescoping. Blade models with square cutoffs in accordance with Hamilton Standard blade drawings are suffixed with "S." Telescoped blades and blades with a square cutoff are eligible at the same ratings and diameter limits as blades with standard cutoff. 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 or ± 1/4 inch permissible for propellers with basic diameter 14 feet or larger. NOTE 3. Pitch Control. Eligible with Hamilton Standard manual control or constant speed governor only. NOTE 4. Feathering. Not applicable. NOTE 5. Left-Hand Models. The left-hand version of an approved model propeller is eligible at the same rating and diameter limitations as listed for the right-hand model. NOTE 6. Interchangeable Blades. Blades with an "S" or "T" (see NOTE 2) are not interchangeable aerodynamically or vibrationwise with each other or with blades having normal round cutoffs. Only blades listed in the same group of the following groups are aerodynamically similar. Only blades listed under the same type in any one group are structurally similar. A higher type number implies a higher strength. This is due to difference in alloys and in cold working of the blade surface. Type 1 includes standard alloy non-surface treated blades; Type 2, hard alloy non-surface treated blades; Type 3, hard alloy blades with cold worked shanks; Type 4, hard alloy blades with cold worked shanks and shot peened surfaces. Page 3 P-206 The following defines the degree to which these blades may be used interchangeably in the same diameter without a flight performance test and without a vibration survey: Type 2 blades may replace Type 1 blades in the same group, but not vice-versa. Type 3 blades may replace either Type 1 or Type 2 blades in the same group, but not vice-versa. Type 4 blades may replace either Type 1, Type 2, or Type 3 blades in the same group, but not vice-versa. Reference should always be made to the ratings of the blades, and blades with different model numbers cannot be incorporated in the same propeller unless the aircraft type certificate data sheet specifically permits this. Group Type 1 Type 2 (1) 6167 6237 NOTE 7. Accessories. (a) Propeller Deicing (1) Eligible with Hamilton Standard deicing slinger ring assemblies. (2) Eligible with Goodrich No. 37572 propeller deicer fluid feed strips. (3) Eligible with Siebenthaler deicing slinger ring assembly 16 lbs. (includes spinner). NOTE 8. Shank Fairings. A letter and a dash prefix included in the blade model designation (as A-6101) indicates that the blade assembly includes molded shank fairing. Fairings are eligible only on those model blades specifically designated. The following procedure should be followed when determining if blades with molded shank fairings are eligible on a model aircraft. (a) Refer to the pertinent propeller type certificate data sheet and determine whether an assembly of the blade model in question is eligible to incorporate a molded shank fairing. (b) Refer to the pertinent aircraft type certificate data sheet and determine whether the same model blade with incorporated molded shank fairing is eligible in the propellers of that model aircraft. NOTE 9. Special Limits. Not applicable NOTE 10. Special Notes. The word "eligible" as used herein does not signify approval. For approval, compliance with the applicable aircraft airworthiness requirements is necessary. ....END.... ``` ## ADs None name its models. ## STCs approved under this data sheet (16) - [STC SP1408NW](https://openairdocs.org/stc/SP1408NW): Installation of Aircraft Propulsion Systems, Inc. rollers in place of the Hamilton Standard counterweight bearings. Canyon Oaks Propeller D/B/A H & Propeller Shop Inc. - [STC SP01222WI](https://openairdocs.org/stc/SP01222WI): Installation of Aircraft Development propeller vortelators.. Aircraft Development Co - [STC SP00582NY](https://openairdocs.org/stc/SP00582NY): Installation of Prop-Guard Polyurethane Protective Tape on the leading edge of metal propellers.. McFarlane Aviation, Inc. - [STC SP245NW](https://openairdocs.org/stc/SP245NW): Manufacture AG-100-4S blades and CF AG-100-4S blades with cooling fairing and use thereof in Hamilton 2D30 hubs of P&W R-985, 450 h.p. engine.. Pacific Propeller International LLC - [STC SP7WE](https://openairdocs.org/stc/SP7WE): Installation of Efficiency Aircraft Components, Inc. propeller blades in Hamilton Standard hubs as follows: 1. E.A.C.AG-100-2 propeller blades in 2D30 and 12D40 hubs in accordance with FAA sealed E.A.C. Installation Instructions No. 100 and in 3D40 hubs in accordance with FAA sealed E.A.C. Installation Instructions No. 400. 2. E.A.C. AG-200-2 propeller blades in 22D30, 22D40, and 23D40 hubs in accordance with FAA sealed E.A.C. Installation Instructions No. 200, 300, and 500 respectively.. Pacific Propeller International LLC - [STC SP362NW](https://openairdocs.org/stc/SP362NW): Installation of Pacific Propeller, Inc. chafing ring PP17010 in accordance with Pacific Propeller, Inc. FAA Sealed Drawing List 76005, dated September 27, 1976, or later FAA Sealed Revision thereto.. Pacific Propeller International LLC - [STC SP5WE](https://openairdocs.org/stc/SP5WE): Installation of Little Giant Propeller Seal.. Pacific Propeller International LLC - [STC SP1521SO](https://openairdocs.org/stc/SP1521SO): Install Northwest Propeller Service Counterweight Thrust Bearings in place of the Hamilton Standard Counterweight Thrust Bearings. Northwest Propeller Services Inc. - [STC SP1520SO](https://openairdocs.org/stc/SP1520SO): Install Memphis Prop. counterweight thrust bearings in place of the Hamilton Standard counterweight thrust bearings.. Northwest Propeller Services Inc. - [STC SP09390SC](https://openairdocs.org/stc/SP09390SC): Replace Hamilton Standard inboard and outboard piston gaskets and nut with RSW piston crown.. Schweis Robert W - [STC SP09397SC](https://openairdocs.org/stc/SP09397SC): Installation of a propeller blade seal.. Schweis Robert W - [STC SP8715SW](https://openairdocs.org/stc/SP8715SW): Installation of a 'R S W' blade thrust bearing assembly in all D-shank blades of counterweight type propellers. (2D 30) (23D 40) (12D 40) (22D 40) (3D 450) (24D 50). Schweis Robert W - [STC SP8467SW](https://openairdocs.org/stc/SP8467SW): Installation of counterweight bearings and shaft assembly kit C.P. 22000.. Schweis Robert W - [STC SP7836SW](https://openairdocs.org/stc/SP7836SW): Installation of Condor bushing, P/N C.P. 22001.. Schweis Robert W - [STC SP10WP](https://openairdocs.org/stc/SP10WP): Installation of greaseless counterweight bearings. (2D 30-227, -233, -235, -237, -243, -247, -249, -259, -261). American Propeller Service - [STC SP829SO](https://openairdocs.org/stc/SP829SO): Vibration approval for single engine tractor installations only, on P & W Model P985-AN-1, -AN-3, -AN-14B, -25, -27, -39A, T1B2 and T1B3 engines. (2D 30/6101A-10S). Metropolitan Propeller Repair, Inc --- OpenAirDocs.org is an independent research project of [Contrail Labs](https://contraillabs.com/). It is not affiliated with the FAA or the NTSB. Source documents are U.S. government works in the public domain.