TCDS P00120IB

U.S. DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION P00120IB REVISON Initial Avia Propeller S.R.O. AV-804 Series Model: AV-804-1 July 2, 2025 TYPE CERTIFICATE DATA SHEET P00120IB Propellers of models described herein conforming with this data sheet (which is part of Type Certificate No. P00120IB) and other approved data on file with the Federal Aviation Administration (FAA) 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 Avia Propeller S.R.O. Beranovych 65/666 199 00 Prague 9 - Letnany Czech Republic TYPE Hydraulic variable pitch, constant speed, feather, reverse propeller Engine Flange See Note 1 Hub Material Aluminum Alloy Blade Material Aluminum Alloy Number of blades 4 (Four) Hub Models see NOTE 1 Design Series AV-804 Hub- Type BLADES (see NOTES 2 & 6) Maximum Continuous HP (kW) RPM <Takeoff> HP (kW) RPM Diameter Limits Inch (cm) Approx. Max Wt. Complete (For Reference Only) AV-804-1 ( ) - 441 850 (635) 1950 867 (647) 1900 750 (560) 2200 850 (635) 1950 867 (647) 1900 750 (560) 2200 98.43 (250) 195.1 lb. (88.5) kg AV-804-1 ( ) - 446 850 (635) 1950 867 (647) 1900 750 (560) 2200 850 (635) 1950 867 (647) 1900 750 (560) 2200 108.27 (275) 198.4 lb. (90) kg Certification Basis: The United States (U.S.) certification basis determined under Title 14 CFR §21.29 and Bilateral Airworthiness Agreement between the U.S. and the European Aviation Safety Agency (EASA) is 14 CFR Part 35, effective December 23, 2008, Amendments 35-1 to 35-8, inclusive. TC (Import) No: EASA Type Certificate EASA.P.020 TC Application Date: April 23, 2025 TC Issued: July 2, 2025 Approval Basis: Title 14, CFR §21.500 gives information on the airworthiness acceptance of aircraft propellers manufactured outside the U.S. These propellers must have a U.S. Type Certificate. The FAA offers more guidance in Advisory Circular 21 -23B (or later revision), A irworthiness Certification of Civil Aircraft, Engines, Propellers, and Related Products Imported to the United States . P00120IB 2 of 4 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 or certifying statement endorsed by the exporting cognizant civil airworthiness authority (EASA) which contains the following language: (1) This propeller conforms to its U.S. type des ign (Type Certificate Number P00120IB) 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. NOTES NOTE 1: Hub Model Designation A V – 804 – 1 – E – ( ) – ( ) – ( ) – ( ) – ( ) 1 2 3 4 5 6 7 8 9 10 11 Hub 1 Avia Propeller (manufacturer) 2 V – Variable Pitch Propeller 3 Blade Root Type 4 Number of Blade 5 Number of variant of the propeller model 6 Code letter for flange type B = AS 127D, SAE No. 2 mod., ½ inch-20 UNF bolts D = ARP 502 E = ARP 880 K = M14 Flange 7 Code letter for counterweights blank = no or small counterweights for pitch change forces to decrease pitch C = counterweights for pitch change forces to increase pitch 8 Code letter for feather provision blank = no feather position possible F = feather position installed 9 Code letter for reverse provision blank = no reverse position possible R = reverse position installed 10 Code letter for reverse system W = System Walter P = System Pratt & Whitney 11 Code letter for design changes small letter for changes which do not affect interchangeability capital letter for changes which restrict or exclude interchangeability NOTE 2: Blade Model Designation ( ) ( ) 275 – 446 ( ) 1 2 3 4 5 Blade 1 Code letter for position of pitch change pin blank = pitch change pin position for pitch change forces to decrease pitch C = pitch change pin position for pitch change forces to increase pitch CF = pitch change pin position for feather provision; pitch change forces to increase pitch CR = pitch change pin position for reverse provision; pitch change forces to increase pitch CFR = pitch change pin position for feather and reverse provision; pitch change forces to increase pitch P00120IB 3 of 4 2 Code letter for blade design and Installation blank = right-hand tractor RD = right-hand pusher L = left-hand tractor LD = left-hand pusher 3 Propeller diameter in cm Diameter limits are nominal diameters of the assembled propeller. They do not include the + or - 1/8-inch manufacturing tolerance the FAA allows for propellers with basic diameters of less than 14 feet. 4 Number of blade type (contains design configurations and aerodynamic data) according to the certified hub/blade - combinations 5 Code letter for design changes small letter for changes which do not affect the interchangeability of blade set capital letter for changes which restrict or exclude interchangeability of the blade set Note 3: Pitch Control (a) The propellers are approved for flight operation with the propeller speed governors which are listed in Avia Propeller Service Bulletin No. 3 (b) The propellers are approved for flight operation with the propeller overspeed governors which are listed in the appropriate propeller, engine or aircraft parts list. (c) The AV-804-1 propeller model covers the following design configurations. Each design configuration is defined by a main assembly drawing and an appropriate parts list: AV-804-1-E-C-F-R(W) Design Configuration “Constant Speed, Feather, Reverse (System Walter)” Drawing No. 117-0000 dated May 5, 2015 (*1) Parts List No. R-117-0000 dated May 5, 2015 (*1) AV-804-1-E-C-F-R(P) Design Configuration “Constant Speed, Feather, Reverse (System Pratt and Whitney)” Drawing No. 117-0001 dated August 7, 2023 (*1) Parts List No. R-117-0001 dated December 9, 2024 (*1) (*1) effective is the declared issue or a later EASA approved revision. Note 4: Feathering and Reversing (a) The propellers incorporate feathering and unfeathering features when equipped with appropriate mounted instruments (see Note 3 and 7). Blade Feathering is accomplished by: (1) by oil pressure (2) by outweighing moment of counterweights (3) by springs (b) The propellers incorporate reversing feature when equipped with appropriate mounted instruments (see Note 3). Note 5: Left-hand Models The left-hand version of the approved propeller model is eligible at the same rating and diameter limitations as listed for the right-hand model. Note 6: Interchangeability Not applicable Note 7: Accessories (a) Propeller spinners: According to the FAA-approved list published in Avia Propeller Service Bulletin No.2. (b) Propeller accessories including governors: According to the FAA-approved list published in Avia Propeller Service Bulletin No. 3. (c) Propeller de-icing: According to the FAA-approved list published in Avia Propeller Service Bulletin No. 4. Note 8: Shank Fairings Not applicable P00120IB 4 of 4 Note 9: Special Limits Not applicable Note 10: Special Notes (a) The propeller installation must be approved as part of the aircraft type certificate to demonstrate compliance with the applicable aircraft airworthiness requirements. (b) All AV-804 propellers are to be operated within the limits of Avia Propeller Operation and Installation Manual No. EN-1320 and adhere to the TBO limits shown in Service Bulletin No. 1. (c) Propeller maintenance, overhaul, and airworthiness limitations shall be accomplished in accordance with Avia Propeller Overhaul Manuals No. EN-1291 and EN-1370 latest revision. Note 11: Special Limits Airworthiness Limitations shall be complied with as given in the approved Airworthiness Limitation Section of the Avia Operation and Installation Manual EN-1320, Overhaul Manual EN-1291 and Overhaul Manual for Metal Blades EN- 1370. The propeller Certificate Management Certification Branch must evaluate the propeller installation for each new aircraft installation to assess possible changes in the airworthiness limitations. -- END --