TCDS P00040BO

TCDS NUMBER: P00040BO REVISION: ORIGINAL U.S. DEPARTMENT OF TRANSPORTATION SOCIETE DUC FEDERAL AVIATION ADMINISTRATION t/a DUC Hélices Propellers TYPE CERTIFICATE DATA SHEET P00040BO MODEL: FLASH H-FSH_3-D-R_I_()_C Series DATE: December 16, 2021 Propellers of models described herein confirming with this data sheet (which is part of this Type Certificate No. P00040BO) and other approved data on file with the Federal Aviation Administration, meet the minimum standards for use in certified 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 approved manufacturer’s manual and other approved instructions. TYPE CERTIFICATE HOLDER SOCIETE DUC t/a DUC Hélices Propellers Aérodrome de Villefranche-Tarare 289 Avenue Odette et Edouard Durand 69620 Frontenas France TYPE Ground-adjustable ENGINE MOUNTING See Note 1 of this TCDS HUB MATERIAL Carbon fiber reinforced composite BLADE MATERIAL Carbon fiber reinforced composite, nickel sheath leading edge HUBS: See Note 1 of this TCDS NUMBER OF BLADES 3 (three) DESIGN SERIES H-FSH_3-D-R_I_AN6_C, H-FSH_3-D-R_I_AN8_C, H-FSH_3-D-R_I_RX_C MODELS BLADES See Notes 2 & 6 MAXIMUM CONTINUOUS MAXIMUM <TAKE OFF> NOMINAL DIAMETER Max Min APPROXI- MATE WEIGHT HP(kW) RPM HP(kW) RPM inch (cm) inch (cm) lbs. (kg) H-FSH_3-D-R_I_RX_C FSH-D-R_I_C 160 (120) 2700 160 (120) 2700 59.8 152 74.8 190 12.3 5.6 H-FSH_3-D-R_I_AN6_C FSH-D-R_I_C 160 (120) 2700 160 (120) 2700 59.8 152 74.8 190 12.3 5.6 H-FSH_3-D-R_I_AN8_C FSH-D-R_I_C 160 (120) 2700 160 (120) 2700 59.8 152 74.8 190 13.2 6.0 The propeller pitch angle is measured at 9.8 inches (25 cm) from the blade tip. Page No. 1 2 3 4 Rev. No. basic basic basic basic TCDS P00040BO Page 2 of 4 CERTIFICATION BASIS: TC (IMPORT) NO. TC APPLICATION DATE: TC ISSUED PRODUCTION BASIS: IMPORT REQUIREMENTS: Pursuant to 14 CFR 21.29(a)(1)(ii), the Type Certificate was issued in validation of the European Aviation Safety Agency (EASA) Certification Standards CS-P, amendment 1 effective November 16, 2006, which was found to provide a level of safety equivalent to that provided by 14 CFR part 35 effective February 1, 1965, as amended by 35-1 through 35-9. EASA issued Type Certificate P.038 for the FLASH H-FSH_3-D-R_I_()_C series propeller. P00040BO November 24, 2021 December 16, 2021 EASA To be considered eligible for installation on U.S. registered aircraft, each propeller imported into the United States must be accompanied by a certificate of airworthiness for export or certifying statement endorsed by the exporting cognizant civil airworthiness authority. Include the following language in the certifying statement: (1) This propeller conforms to its United States type design (Type Certificate Number P00040BO) and is in a condition for safe operation; and (2) This propeller has been subjected by the manufacturer to a final operational check and is in a proper state of airworthiness. Reference 14 CFR 21.500, which provides for the airworthiness acceptance of 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. TCDS P00040BO Page 3 of 4 NOTES NOTE 1: HUB MODEL DESIGNATION: Model Half Hubs H-FSH_3-D-R_I_RX_C DMFSH-3-AV_RX_C DMFSH-3-AR_RX_C H-FSH_3-D-R_I_AN6_C DMFSH-3-AV_AN6_C DMFSH-3-AR_AN6_C H-FSH_3-D-R_I_AN8_C DMFSH-3-AV_AN8_C DMFSH-3-ARV_AN8_C H-FSH_3-D-R_I_RX_C for BRP-Rotax 912 and 914 engine flange H-FSH_3-D-R_I_AN6_C engine SAE flange with AN6 bolts or AN7 bolts (with adaptor spacer) H-FSH_3-D-R_I_AN8_C engine SAE flange with AN8 bolts NOTE 2: BLADE MODEL DESIGNATION: FSH-D-R_I_C NOTE 3: Pitch Control: Pitch control is accomplished by ground adjustment. NOTE 4: (a) Feathering: Model incorporates no feathering feature. (b) Reversing: Model incorporates no reversing feature. NOTE 5: Direction of Rotation: Right, viewed in the flight direction. NOTE 6: Interchangeability: The blades of a propeller ar e part of a whole. DO NOT INTERCHANGE with other similar blades from propeller. The propeller blades are manufactured to their application. Their structure, weight and balance are different from a propeller to another. NOTE 7: Accessories: The propeller is optionally equipped with a carbon and glass fiber reinforced composite cone, and/or a spacer. . NOTE 8: Shank fairings: Not applicable NOTE 9: Special limits: The FAA approved Airworthiness Limitations Section of the Instructions for Continued Airworthiness is published in the applicable "Instruction manual 3-blade propeller Certified FLASH-R" document number DH_FSH-R_BE_04_B, chapter 7.1 "Airworthiness Limitations Section”. The suitability of a propeller for a given aircraft/engine combination must be demonstrated within the scope of the type certification of the aircraft. TCDS P00040BO Page 4 of 4 NOTES CONTINUED NOTE 10: Special notes: (a) Aircraft installations must be approved as part of the aircraft type certificate and demonstrate compliance with the applicable aircraft airworthiness requirements. The propeller CMACO must evaluate the propeller installation for each new aircraft installation to assess possible changes in airworthiness limitations. NOTE 11: Service Information: Each of the documents listed below must state that it is approved by the European Aviation Safety Agency (EASA) . 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 --