# TCDS P-857: McCauley Propeller Systems - Type: Type certificate data sheet - Status: Current - Holder: McCauley Propeller Systems - Revision: 24 - Revised: November 2, 2009 - Product: Propeller - Certification basis: Part 14, Part 21, Part 35, CAR 14 - Data sheet PDF: https://openairdocs.org/files/sha256/97/89/978917087269b557d1211da0a28564de8408b198e08d183de1bffd078b76fd9c - FAA DRS: https://drs.faa.gov/browse/excelExternalWindow/BEA3A1655EFBDF3486257666004A73FE.0001 - Page: https://openairdocs.org/tcds/P-857 ## Models (4) As the data sheet lists them. - 1A170 - 1B175 - 1A162 - 1A175 ## 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 4 5 6 Rev. No. 24 24 24 24 24 24 DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION P-857 Revision 24 McCauley 1A162 1A170 1A175 1B175 November 02, 2009 TYPE CERTIFICATE DATA SHEET NO. P-857 Propellers of models described herein conforming with this data sheet (which is part of Type Certificate No. 857) and other approved data on file with the Federal Aviation Administration, meet the minimum standards for use in certificated aircraft in accordance with the 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: McCauley Propeller Systems 7751 East Pawnee Wichita, KS 67207 Type: Fixed pitch metal Material: Aluminum Alloy No. of Blades: Two Takeoff & Hub Drilling Model Max. Cont. Diameter Standard No. Di a. Dia. Bolt Hub Dimensions Weight (lb.) (See NOTE 2) HP RPM Limits Pitch Holes Ho les Circle Dia. Thickness (Max. Dia.) 1A162/TCD 100 2750 69”-66” 80”-40” 6 25/64” 4” 5-1/16” 5-55/64” 24.4 1A170/DF 165 2800 82”-70” 80”-40” 8 25/ 64” 5-1/4” 6-1/4” 3-7/16” 33 1A170/DM 165 2800 82”-70” 80”-40” 8 25/ 64” 5-1/4” 6-1/4” 3-7/16” 33 1A170/L 165 2800 82”-70” 80”-40” 8 25/ 64” 5-1/4” 6-1/4” 3-7/16” 33 1A170/LL 165 2800 82”-70” 80”-40” 8 25/ 64” 5-1/4” 6-1/4” 3-7/16” 33 1A175/DM 165 2800 82”-70” 80”-40” 8 25/ 64” 5-1/4” 6-1/4” 3-7/16” 33 1A170/BMS 180 2700 78”-70” 80”-40” 6 33/ 64” 4-3/4” 5-3/32” 4-13/16” 36* 1A170/GM 165 2800 82”-70” 80”-40” 6 25/ 64” 4-3/4” 6-1/4” 3-7/16” 33 1A170/CFA 180 2700 78”-70” 80”-40” 6 33/64” 4-3/4” 6” 7-7/16” 40* 1A170/EFA 180 2700 78”-70” 80”-40” 6 33/ 64” 4-3/4” 5-3/32” 4-15/16” 36* 1A170/FFA 180 2700 78”-70” 80”-40” 6 33/ 64” 4-3/4” 5-3/32” 6-3/32” 38* 1A170/JFA 180 2700 78”-70” 80”-40” 6 33/ 64” 4-3/4” 6-1/4” 4-15/16” 40.75* 1A170/JHA 180 2700 78”-70” 80”-40” 6 33/ 64” 4-3/4” 6-1/4” 4-15/16” 40.75 1A170/KFA 180 2700 78”-70” 80”-40” 6 33/ 64” 4-3/4” 6-1/4” 6-3/32” 41.25* 1A170/SFA 180 2700 78”-70” 80”-40” 6 33/ 64” 4-3/4” 5-3/4” 3-7/16” 33 1A170/SFC 165 2800 82”-70” 80”-40” 6 33/64” 4” 5-1/4” 3-7/16” 33 1A175/FC 175 2400 84”-70” 80”-40” 6 33/64” 4” 6-1/2” 3-7/16” 33 1A175/GM 165 2800 82”-78” 80”-40” 6 25/ 64” 4-3/4” 6-1/4” 3-7/16” 33 P-857 2 Rev. 24 Takeoff & Hub Drilling Model Max. Cont. Diameter Standard No. Di a. Dia. Bolt Hub Dimensions Weight (lb.) (See NOTE 2) HP RPM Limits Pitch Holes Ho les Circle Dia. Thickness (Max. Dia.) 1A175/GMA 165 2800 82”-78” 80”-40” 6 25/ 64” 4-3/4” 6-1/4” 5-7/16” 37.5* 1A175/SFC 165 2800 82”-70” 80”-40” 6 33/64” 4” 5-1/4” 3-7/16” 33 1B175/MFC 185 2500 84”-78” 80”-40” 6 33/64” 4” 5-1/4” 3-7/16” 33 1A175/ATM 165 2800 82”-78” 80”-40” 6 29/ 64” 4-3/4” 5-63/64” 6-13/16” 39.25* 1A175/ETM 165 2800 82”-78” 80”-40” 6 29/ 64” 4-3/4” 5-63/64” 6-13/16” 39.0* * Includes doweled spacer Certification Basis: Propeller Certification Basis Method of Approval Approval Date 1A162/TCD 14 CFR Part 35, Amdt 35-1 to 35-6 DOA under 14 CFR Part 21, Subpart J October 6, 2009 1A170/DF Civil Air Regulations (CAR) Part 14 Oct 19, 1945 Amendment (Amdt) 14-1 April 23, 1947 1A170/DM CAR Part 14 Oct 19, 1945 Amdt 14-1 April 23, 1947 1A170/L CAR Part 14 Oct 19, 1945 Amdt 14-1 October 17, 1950 1A170/LL CAR Part 14 Oct 19, 1945 Amdt 14-1 October 17, 1950 1A175/DM CAR Part 14 Oct 19, 1945 Amdt 14-1 July 9, 1959 1A170/BMS 14 Code of Federal Regulations (CFR) Part 35, Amdt 35-1 & 35-2 14 CFR Part 21, Subpart J, and 14 CFR Part 35 May 29, 1990 1A170/GM CAR Part 14 Oct 19, 1945 Amdt 14-1 October 9, 1956 1A170/CFA 14 CFR Part 35, Amdt 35-1 & 35-2 Delegation Option Authorization (DOA) under 14 CFR Part 21, Subpart J August 19, 1967 1A170/EFA 14 CFR Part 35, Amdt 35-1 & 35-2 14 CFR Part 21, Subpart J, and 14 CFR Part 35 June 14, 1968 1A170/FFA 14 CFR Part 35, Amdt 35-1 & 35-2 DOA under 14 CFR Part 21, Subpart J, and 14 CFR Part 35 August 2, 1974 1A170/JFA 14 CFR Part 35, Amdt 35-1 & 35-2 14 CFR Part 21, Subpart J, and 14 CFR Part 35 October 4, 1982 1A170/JHA 14 CFR Part 35, Amdt 35-1 to 35-6 DOA under 14 CFR Part 21, Subpart J March 27, 1998 1A170/KFA 14 CFR Part 35, Amdt 35-1 & 35-2 14 CFR Part 21, Subpart J, and 14 CFR Part 35 October 4, 1982 1A170/SFA 14 CFR Part 35, Amdt 35-1 & 35-2 DOA Part 410 of the Regs of the Admin. October 25, 1963 1A170/SFC CAR Part 14 Oct 19, 1945 Amdt 14-1 DOA under 14 CFR Part 21, Subpart J July 1, 1966 1A175/FC CAR Part 14 Oct 19, 1945 Amdt 14-1 June 24, 1957 1A175/GM CAR Part 14 Oct 19, 1945 Amdt 14-1 December 6, 1960 1A175/GMA 14 CFR Part 35, Amdt 35-1 & 35-2 DOA under 14 CFR Part 21, Subpart J August 19, 1967 1A175/SFC CAR Part 14 Oct 19, 1945 Amdt 14-1 July 9, 1959 P-857 3 Rev. 24 Certification Basis: (cont’d) Propeller Certification Basis Method of Approval Approval Date 1B175/MFC (175 hp at 2400 rpm) CAR Part 14 Oct 19, 1945 Amdt 14-1 Civil Aeronautics Manual (CAM) 14.16-3b October 17, 1958 1B175/MFC (185 hp at 2500 rpm) CAR Part 14 Oct 19, 1945 Amdt 14-1 CAM 14.16-3b December 30, 1958 1A175/ATM 14 CFR Part 35, Amdt 35-1 & 35-2 DOA unde r 14 CFR Part 21, Subpart J January 5, 1968 1A175/ETM 14 CFR Part 35, Amdt 35-1 & 35-2 DOA under 14 CFR Part 21, Subpart J, and 14 CFR Part 35 April 16, 1973 Date of Application for Ty pe Certificate January 27, 1947 Production Basis: Production Certificate No. 3 NOTE 1. Installation . These propellers are for installation on flanged propeller shaft ends (See NOTE 2). The front plate supplied by the engine manufacturer is not to be used. Installation is to be made with special alloy steel bolts which are either furnished or specified by the propeller manufacturer. Propeller model 1A170/CFA is for use on modified SAE #2 flanged propeller shaft with McCauley P/N B-3637 spacer and must be installed in accordance with McCauley Drawing C-3883. Propeller models 1A170/DF, 1A170/DM a nd 1A175/DM are for use on SAE #3 flanged propeller shaft and must be installed in accordance with McCauley Drawing C-1177. Propeller models 1A170/L and 1A170/LL are for use on the modi fied SAE #3 flanged propeller shaft with special 2-3/16 pilot diameter and must be installed in accordance with McCauley Drawing C-1203. Propeller models 1A170/GM and 1A175/GM are for use on SAE #2 flanged propeller shaft and must be installed in accordance with McCauley Drawing C-1968. Propeller model 1A170/SFA is for use on modified SAE #2 flanged propeller shaft and must be installed in accordance with McCauley Drawing C-3343. Propeller models 1A170/SFC, 1A175/SFC, and 1B175/MFC are for use on the special Continental Motors Corporation propeller flange and must be installed in accordance with McCauley Drawing C-2359. Propeller models 1A175/FC is for use on the special Continental Motors Corporation propeller flange and must be installed in accordance with McCauley Drawing C-2125. Propeller model 1A175/GMA is for use on SAE #2 flanged pr opeller shaft with McCauley P/N B-3515 spacer and must be installed in accordance with McCauley Drawing C-3518. Propeller model 1A175/ATM is for use on modified SAE #2 flanged propeller shaft with McCauley P/N B-3898 spacer and must be installed in accordance with McCauley Drawing C-3900. Propeller model 1A170/EFA is for use on modified SAE #2 flanged propeller shaft with McCauley P/N B-4020 spacer and must be installed in accordance with McCauley Drawing C-4018. Propeller model 1A170/BMS is for use on modified SAE #2 flanged propeller shaft with McCauley P/N B-6627 spacer and must be installed in accordance with McCauley Drawing C-6626. Propeller model 1A175/ETM is for use on SAE #2 flanged propeller shaft with McCauley P/N C-4516 spacer and must be installed in accordance with McCauley Drawing B-4518. Propeller model 1A170/FFA is for use on modified SAE #2 flanged propeller shaft with McCauley P/N B-4273 spacer and must be installed in accordance with McCauley Drawing C-4280. Propeller models 1A170/JFA and 1A170/JHA are for use on m odified SAE #2 flanged propeller shaft with McCauley P/N C-5464 spacer and must be installed in accordance with McCauley Drawing C-5465. P-857 4 Rev. 24 NOTE 1. Installation (cont’d). Propeller model 1A170/KFA is for use on modified SAE #2 flanged propeller shaft with McCauley P/N B-4273 spacer and must be installed in accordance with McCauley Drawing C-5448. Propeller model 1A162/TCD is for use on TCM O200D flange d propeller shaft with McCauley P/N B-7925 spacer and must be installed in accordance with McCauley Drawing 1A162/TCD6754. NOTE 2. Propeller Model Designation . The propeller model designation consists of a series of numbers suffixed to the basic design number to indicate propeller diameter and geometric pitch at the .75 radius. Basic Model Designation Suffix * 1A170E/ DF 76 48 Inches pitch at .75 radius Propeller diameter in inches CFA denotes SAE No. 2 flange m odified (six ½” mounting bolts); 4” integral doweled spacer DF denotes SAE No. 3 flange; elliptical tips LM denotes SAE No. 3 flange; square tips L denotes SAE No. 3 flange with 2.188” diameter pilot; elliptical tips LL denotes SAE No. 3 flange with 2.188” diameter pilot; square tips GM denotes SAE No. 2 flange; square tips SFA denotes SAE No. 2 flange modified (six ½”mounting bolts) SFC denotes special flange 4” B.C.; square tips FC denotes special flange 4” B.C.; square tips GMA denotes SAE No. 2 flange with 2” integral doweled spacer; square tips MFC denotes special flange 4” B.C.; square tips ATM denotes SAE No. 2 flange m odified (six 7/16”mounting bolts); 3.5” integral doweled spacer; square tips EFA denotes SAE No. 2 flange m odified (six 7/16”mounting bolts); 1.5” integral doweled spacer; square tips ETM denotes SAE No. 2 flange with 3.5” integral doweled spacer; square tips FFA denotes SAE No. 2 flange m odified (six ½”mounting bolts); 2.65” integral doweled spacer; square tips BMS denotes SAE No. 2 flange m odified (six 7/16” mounting bolts); 1.375” integral dowe led space; square tips TCD denotes TCM O200D flange Basic design number: “E” when present is a minor change letter that indicates elliptical tips and does not effect interchangeability or eligibility. * Some propellers of these models may have been marked with a hyphen following the basic design number in lieu of a diagonal line (i.e. 1A170-DF7648) NOTES 3, 4, and 5. Not applicable. NOTE 6. Interchangeable Propellers . Propellers of the same basic design number with square or elliptical tips are sufficiently similar aerodynamically and vibrationwise to permit interchangeability in the same diameter and static r.p.m. without a flight test. NOTE 7. Accessories. (a) Spinners. (1) Model 1A170/CFA eligible with McCauley spinner consisting of D-3876 dome, C-3877 front bulkhead and C-3878 rear bulkhead assembled and installed in accordance with McCauley Drawing D-3875. NOTE 8. Not applicable. P-857 5 Rev. 24 NOTE 9. 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. Propeller Model Engine Model Max. Dia. Min. Dia. Placards 1A170/DM Continental C-125-2 73” 71-1/2” None 1A170/DF Continental C-145 Series and 80” 73” None 1A170/DM Continental O-300 Series up to 1A170/SFC 145 hp. and 2700 r.p.m. or 1A175/DM 1A170/DF Franklin 6A4-150-B3 76 74 Avoid continous engine operation or 1A170/DM between 2100 and 2300 r.p.m. 1A170/SFC Franklin 6A-150-B4 76 74 Avoid continous engine operation between 2100 and 2300 r.p.m. 1A170/DF Franklin 6A-165-B3 76 74 Avoid continous engine operation or 1A170/DM between 2150 and 2250 r.p.m. 1A170/SFC Franklin 6A4-165-B4 76 74 Avoid continous engine operation between 2150 and 2250 r.p.m. 1A170/DF Lycoming O-290 Series up to 76 70 None 1A170/DM 135 hp. and 2600 r.p.m. 1A170/GM 1A170/L or 1A170/LL 1A170/GM Lycoming O-320 Series up to 78 70 None 160 hp. and 2700 r.p.m. 1A170/CFA Lycoming O-360 Series up to 78 74 None 1A170/EFA 180 hp. and 2700 r.p.m. or 1A170/SFA 1A175/GM Lycoming O-290 Series up to 82 78 None 135 hp. and 2600 r.p.m. 1A175/GM Lycoming O-320 Series up to 82 78 None or 1A175/GMA 160 hp. and 2700 r.p.m. 1A175/SFC Continental C-145 Series and 80 73 None Continental O-300 Series up to 145 hp. and 2700 r.p.m. 1A175/FC Continental GO-300-A 84 78 None 1A175/GMA Lycoming O-320 and IO-320 82 78 None 1A175/ATM Series up to 160 hp. and or 1A175/ETM 2700 r.p.m. 1A170/FFA Lycoming O-360 Series 75 74.5 “Avoid continuous operations Up to 180 hp. and 2700 r.p.m. while descending between 1850 and 2250 r.p.m.” 1B175/MFC Continental GO-300-A 84 78 None NOTE 10. The word “eligible” as used herein does not signify appr oval. For approval, compliance with the applicable aircraft airworthiness requirements is necessary. ... END ... ``` ## ADs (3, in force first) - [AD 2005-14-11](https://openairdocs.org/ad/2005-14-11): Failed propeller blade · Hartzell Propeller BHC-92W, BHC-92ZF-1, BHC-92ZF-3 and 391 more. Effective Aug 17, 2005 - [AD 2003-13-17](https://openairdocs.org/ad/2003-13-17): Propeller blade · Hartzell Propeller BHC-A2V, BHC-C2Y, EHC-G3YF-2 and 81 more. Effective Jul 18, 2003 - [AD 82-27-01](https://openairdocs.org/ad/82-27-01): Hub · McCauley Propeller Systems 1A170. Effective Dec 30, 1982 ## STCs approved under this data sheet (3) - [STC SP26CH](https://openairdocs.org/stc/SP26CH): Modification of a McCauley 1A170-BMS76 model propeller. Pegasus Innovations, LLC - [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. --- 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.