# TCDS P7EU: Hoffmann GmbH & Co. KG - Type: Type certificate data sheet - Status: Current - Holder: Hoffmann GmbH & Co. KG - Revision: 3 - Revised: March 12, 2007 - Product: Propeller - Certification basis: Part 21, Part 35 - Data sheet PDF: https://openairdocs.org/files/sha256/89/c1/89c1dce3fcaf8a2d0950230a16d9d9a5b7de401efe845bc57d0c9b9e5686bbd0 - FAA DRS: https://drs.faa.gov/browse/excelExternalWindow/9D6BECE0B6FC01D28625729F006C39CD.0001 - Page: https://openairdocs.org/tcds/P7EU ## Models (2) As the data sheet lists them. - HO-V 62-R - HO-V 62 ## What the data sheet says From the PDF's text layer, line by line; tables lose their columns. The PDF is the record. ```text U.S. DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION TYPE CERTIFICATE DATA SHEET P7EU TCDS NUMBER: P7EU REVISION: 3 HOFFMANN HO-V 62 HO-V 62-R March 12, 2007 Propellers of models described herein conforming with this data sheet (which is part of type certificate no. P7EU) 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 Hoffmann GmbH & Co.KG Kuepferlingstr. 9 D-83022 Rosenheim Federal Republic of Germany Type M echanically variable pitch (see NOTES 3 and 4) Engine shaft Mounting flange 3.20" diameter bolt circle, 6 bolts 7/16 - 20 UNF, center bore 1.88" Dia. Hub material Aluminum alloy Blade material Laminated wood composite structure, epoxy fiber glass cover, with metal tipping. Number of blades 2 Hubs eligible HO-V 62, HO-V 62-R Propeller Blades Maximum Continuous Takeoff Blade Diameter Limits Blade twist limits in degrees* Min. max. Approx. max. wt. lbs. reference only (See NOTES 3 & 7) Note 2 & 6 HP/KW RPM HP/KW RPM English (in.) Metric/ (cm) 150 A 57/42.6 3200 67/50 3600 59 (± 2) 150 (± 5) 5 50 18.7 160 G 57/42.6 3200 67/50 3600 63 (+ 2) 160 (± 5) 5 50 18.7 160 T 160 T 65/48.5 71/53 3200 3000 71/53 79/59 3600 3400 63 (± 2) 160 (± 5) 63 (+2) 160 (+5) (-4) 160 (-10) 5 50 5 50 18.7 18.7 160 BT 160 BT 65/48.5 88.5/66 3200 3000 71/53 95/71 3600 3400 63 (±2) 160 (±5) 63 (±2) 160 (±5) 50 5 50 18.7 18.7 170 Y 100/75 2750 100/75 2750 67 (-4) 170 (-10) 5 50 19.8 170 DX 88.5/66 2540 95/71 2875 64 (-4) 170 (-10) 5 50 19.8 170 FA 100/75 2700 100/75 2700 67 (-4) 170 (-10) 5 50 19.8 *The data for blade twist limits is valid for the blade radius of 0.2 through 1.0. Certification basis FAR 21.29, FAR 35 effective September 1968 with amendments 35-1 and 35-2. Luftfahrt-Bundesamt (LBA) originally type certificated this propeller under its type certificate Number 32.130 / 013. The FAA validated this product under U.S. Type Certificate Number P7EU. Effective September 28, 2003, the European Aviation Safety Agency (EASA) began oversight of this product on behalf of the Federal Republic of Germany. TC (IMPORT) NO. LBA-Data Sheet No. 32.130 / 013 Edition 12 dtd. 28 Aug. 1992. TC APPLICATION DATE: April 7, 1978 Page No. 1 2 3 4 5 Rev. No. 3 3 3 3 3 P7EU Page 2 of 5 TC ISSUED August, 1978, Revised January 30, 2003. IMPORT REQUIREMENTS: To be considered eligible for installation on U.S. registered aircraft, each propeller to be exported to the United States shall be accompanied by a Certificate of Airworthiness for export endorsed by the LBA on behalf of the European Community which contains the following language: (1) This propeller conforms to its United States type design (Type Certificate Number P7EU) and is in a condition for safe operation. (2) This propeller has been subjected by the manufacturer to a final operational check and is in a proper state of airworthiness. Reference FAR Section 21.500 which provides for the airworthiness acceptance of aircraft engines or propellers manufactured outside the U.S. for which a U.S. type certificate has been issued. Additional guidance is contained in FAA Advisory Circular 21-23, Airworthiness Certification of Civil Aircraft, Engines, Propellers and Related Products, imported into the United States. Page 3 of 5 P7EU NOTE 1. Hub Model Designation Minor change with no effect on airworthiness/interchangeability Propeller pitch Blank = Two position propeller R = Cruise position A = Automatic pitch change system H = Hydro mechanical pitch change mechanism HS = Hydro mechanical pitch change mechanism with feathering position C = Hydro mechanical pitch change mechanism by Model “C” HSC = Hydro mechanical pitch change mechanism with feathering by Model “C” Distance hub blade axis to flange in (mm). Designation of the flange Blank = basic model of flange Number of blades Number of basic design model Variable pitch Hoffmann GmbH & Co. KG HO – V 6 2 – ( ) ( ) ( ) ( ) P7EU Page 4 of 5 NOTE 2. Blade Model Designation L 150 ( ) ( ) ( ) ( ) ( ) Deviation from basic diameter in cm. Material of blade Blank = compreg (beech) and spruce P = compreg Information for additional equipment B = electrical deicing Designates blade twist (small letter) Designates blade design drawing. Basic diameter in (cm) Sense of rotation Blank = righthand, tractor D = righthand, pusher L = lefthand, tractor LD = lefthand, pusher NOTE 3. Pitch Control. Mechanically HO - V 62 has 2 positions HO - V 62-R has 3 positions Actuating mechanism is part of the airframe. Model HO-V 62: For propellers with hydro mechanical pitch change mechanism (HO-V62H; HO-V62HS) Amendment No. 1 to the 8th edition of Instruction Manual No. 0107.72 is required. For propellers with hydro mechanical pitch change mechanism model “C” (HO-V62 ()()-C-(); HO-V62()()- CS-()) Amendment No. 2 to the 8th edition of Instruction Manual No. 0107.72 is required. NOTE 4. (a) Feathering. Incorporates a mechanical feathering device. (b) Reversing. 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. See NOTES 1 and 2. NOTE 6. Interchangeable Blades. Not applicable. NOTE 7. Accessories. (a) The TCM/RR 0-200 engine installation must use spacer VP 20-580 for Model HO-V 62. (See Instruction Manual) (b) Hoffmann propeller spinners; VP 30-81, VP 30-82 weighing 2.6 lbs. are eligible/acceptable. NOTE 8. Shank Fairings. Not applicable. Page 5 of 5 P7EU NOTE 9. Special Limits. Table of Propeller-Engine Combinations Eligible 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 reductions below the minimum diameter listed is permissible since this figure includes the diameter reduction allowable for repair purposes. Hub Model Blade Model Engine Model Max. Dia. Min. Dia. Placards (inches) cm (inches) cm HO-V 62 and HO-V 62 R 170Y TCM/RR 0-200A, 67 170 63 160 None -B, -C NOTE 10. Special Notes. The word "eligible" as used herein does not signify full installation approval. Compliance with the applicable engine and aircraft FAR requirements is necessary before full approval for use on aircraft can be given. All Models: The permitted time between overhaul (TBO) for these propeller models is listed in Hoffmann GmbH & Co. KG Service Bulletin No. E1(). NOTE 11: Service Information. Each of the documents listed below must state that it is approved by the European Aviation Safety Agency (EASA) or – for approvals made before September 28, 2003 – by the LBA. Any such documents are accepted by the FAA and are considered FAA approved. • Service bulletins, • Structural repair manuals, • Vendor manuals, • Aircraft flight manuals, and • Overhaul and maintenance manuals. ....END.... ``` ## ADs (2, in force first) - [AD 2018-20-03 R1](https://openairdocs.org/ad/2018-20-03-R1): Propeller Assembly · Hoffmann HO-V 62. Effective Dec 12, 2018 - [AD 2018-20-03](https://openairdocs.org/ad/2018-20-03): Propeller Assembly · Hoffmann HO-V 62. Effective Nov 14, 2018 ## STCs approved under this data sheet (1) - [STC SP01222WI](https://openairdocs.org/stc/SP01222WI): Installation of Aircraft Development propeller vortelators.. Aircraft Development Co --- 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.