TCDS P17B0

U.S. DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION TYPE CERTIFICATE DATA SHEET P17BO TCDS NUMBER P17BO REVISION: 1 DOWTY PROPELLERS MODEL/S: (c)R408/6-123-F/17 February 27, 2007 Propellers of models described herein conforming with this data sheet (which is part of TC No. P17BO) 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 and other approved instructions. Type Certificate Holder Dowty Propellers Anson Business Park Cheltenham Road East Gloucester, GL2 9QH, England Type Constant speed; hydraulic (See: Notes 3 and 4) Engine flange Special flange with 15 studs, nuts, and 3 dowels at 9.8125 inches P.C.D. Hub material Aluminum alloy Blade material: Composite glass and carbon re-inforced plastic, polyurethane coated and fitted with nickel leading edge sheath for erosion protection with electric deicer boots. Number of blades 6 Design series (c)R408/6-123-F/17 BLADES (See Note 2 ) MAXIMUM CONTINUOUS SHP RPM KW <TAKE OFF> SHP RPM KW NOMINAL DIAMETER APPROXIMATE PROPELLER WEIGHT* Part No. 697071002 5071 1020.0 3782 5071 1020.0 3782 162 inches 555 lbs. *Includes Spinner Weight CERTIFICATION BASIS: FAR 21.29 and FAR 35 effective February 1, 1965, Amendments 35-1 through 35-7. Compliance established by equivalence to British Civil Airworthiness Requirements JAR-P Change 7 dated 22 October 1987. Orange Paper P/96/1 effective 8 August 1996 and special requirements detailed in CAA letter dated 21 April 1999 (Ref: 9/80/Dowty/Dash 8/CO2/1-A) Civil Aviation Authority (UKCAA) originally type certificated this propeller under its Type Certificate Number 117. The FAA validated this product under U.S. Type Certificate Number P17BO. Effective September 28, 2003, the European Aviation Safety Agency (EASA) began oversight of this product on behalf of the United Kingdom of Great Britain and Northern Ireland. TC (IMPORT) NO: UKCAA Type Certificate Number 117 TC APPLICATION DATE: October 18, 1996 TC ISSUED: July 29, 1999 Page No. 1 2 3 4 5 Rev. No. 1 1 1 1 1 PAGE 2 T CDS NUMBER P17BO 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 UKCAA on behalf of the European Community which contains the following language: (1) This propeller conforms to its United States type design (TC No. P17BO) 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. NOTES NOTE 1. Propeller Model Designation The model designation of a complete Dowty Aerospace Propeller assembly consists of the basic model designation with prefix and suffix letters and numbers as shown below: Prefix Basic model designation Suffix (c) R 408 / 6 -123 -F / -17 Suffix number denotes interchangeable design standard Engine Flange mounted Blade Shank size No. 123 Number of blades - 6 Prefix number denotes non-interchangeable design standard Dowty Aerospace Civil (non-military) The prefix number indicates the design series, and propellers with different prefix numbers are not generally interchangeable. Certain models may be interchanged as complete aircraft sets on the advice of the propeller manufacturer only. The suffix number is used to record minor alterations which do not affect interchangeability. NOTE 2. Blade Model Designation Dowty Aerospace propeller blades are identified by a serialized part number only, which does not constitute a model designation. A dash number following the part number indicates the type of finish. Only blades with a serial number prefix may be used on this model propeller. NOTE 3: Pitch control: Normal pitch control from feather to full-reverse by pitch control unit (PCU). NOTE 4: (a) Feathering: (b) Reversing: Model incorporates auxiliary feathering and unfeathering features by means of counterweights and motor/pump unit, Model incorporates reversing feature. NOTE 5: Right-hand model: (c) R408 These propellers are designed and manufactured for right-hand tractor only. (clockwise when viewed from rear). NOTE 6: Interchangeable blades: All of the blades are fully interchangeable with each other, and a propeller may contain blades with different approved part numbers. TCDS NUMBER P17BO PAGE 3 NOTE 7: Equipment: The propeller equipment set, comprising the propeller itself and the units itemized below which are approved for use with the propeller are defined by Equipment Set Drawing 697070002-010 or subsequent approved issue and published in Aircraft Maintenance Manual (AMM) 1096. Item Part No. - Propeller comprising 697070002 - Hub, Actuator & Backplate Assembly 697071234 - Blade & Bearing Assembly 697071002 - Beta Tubes 697074004 - Spinner 697069001 697069002 - Brush Block Bracket Unit 697068002 - Pitch Control Unit 697073002 - Overspeed Governor Unit 697072003 - Feather Pump 697076004 - Propeller Electronic Controller 699008003 - Timer Monitor Control Unit 699009001 NOTE 8: Drawings & Specifications: Design Specification General Arrangement Drawing Installation Drawing 697070002-010 (Build Standard) or later approved issue. NOTE 9: The Dowty Aerospace Model (c)R408/6-123-F/17 propeller is controlled by an integrated electronic control system which is operationally compatible with the engine type design. This model propeller complies with the approved propeller airworthiness requirements when used with the Pratt & Whitney PW150A engine installed in the De-Havilland DHC-8 Model 400, Model 401 and Model 402 aircraft and meet the Dowty Aerospace Propeller Electronic Control (PEC) Software Standard, UD1079 (Strike 23). Later versions of the PEC Software Standards must comply with the following Dowty Aerospace control documents: Title Report No. RTCA DO-178B Document No. Software Accomplishment 699008957 11.2 Summary Software Configuration 699008956 11.15 and 11.16 Index Plan of Software 699008955 11.1 Aspects of Certification NOTE 10: Operational Limitations: 10.1 Crosswind and Tailwind Restrictions 10.1.1 Maintenance Ground Running All ground running with the aircraft static should normally be conducted with the aircraft pointed into wind ±30°. The following limitations apply when the aircraft is not pointed into the wind ±30°. For windspeeds less than or equal to 20 knots, maximum allowable torque is 15400 lbf ft (20882 Nm), e quivalent to 2990 SHP (2230 kW) at 1020 rpm. For windspeeds greater than 20 knots, maximum allowable torque is 2575 lbf ft (3492 Nm), equivalent to 500 SHP (373 kW) at 1020 rpm. PAGE 4 T CDS NUMBER P17BO NOTE 10 CONT’D: 10.1.2 Flight Operations- Take-off. Maintenance ground running limits (Section 10.1.1) normally apply until the aircraft speed is greater th an the windspeed. Alternatively, a rolling take-off procedure may be used as follows: For windspeeds less than or equal to 8 knots, maximum allowable torque with the aircraft static on the brakes is 15900 lbf ft (21560 Nm), equivalent to 3088 SHP (2303 kW) at 1020 rpm. As soon as the brakes are released, normaly take-off torque of 23583 lbf ft (31979 Nm), equivalent to 4580 SHP (3415 kW) at 1020 rpm, can be selected. For windspeeds above 8 knots and le ss than or equal to 20 knots, maximum allowable torque with the aircraft static on the brakes is 2575 lbf ft (3492 Nm), equivalent to 500 SHP (373 kW) at 1020 rpm. As soon as the brakes are released, normal take-off torque of 23583 lbf ft (31979 Nm), equivalent to 4580 SHP (3415 kW) at 1020 rpm, can be selected. 10.1.3 Ground Operation On landing and/or rejected take-offs, the Power Lever must be held at Flight Idle position for at least 1.5 seconds before selecting a Power Lever Angle (PLA) less than Flight Idle, or by an appropriate alternative approved procedure as detailed within the Aircraft Flight Manual. A PLA less than Flight Idle must not be selected at airspeeds greater than 150 knots Equivalent Airspeed (EAS). 10.1.4 Equipment Operation The Propeller is not to be operated with oil temperature below 0°F (-18°C). 10.2 The following declared limitations and ratings shall apply: Take-off Power, 100% 5071SHP 3782 KW Take-off Engine Torque, 100% 26110 lbf ft (35405 Nm) Take-off Propeller Speed, 100% 1020 rpm Maximum Continuous Power, 100% 5071 SHP (3782 KW) Maximum Continuous Propeller Torque, 26110 lbf ft (35405 Nm) 100% Maximum Continuous Propeller Overspeed, 1072 rpm ±10 rpm 105% ±1% Maximum Permitted Transient Propeller 29710 lbf ft (40287 Nm) Torque, 113% Maximum Transient Propeller Overspeed, 1173 rpm 115% TCDS NUMBER P17BO PAGE 5 NOTE 11: Approved installations: Propellers listed in this data sheet are approved from a vibration standpoint only for use on the engine-aircraft combinations shown below: PROPELLER MODEL AIRCRAFT MODEL ENGINE MODEL FAA SPECIFICATION OR TC DATA SHEET AIRCRAFT ENGINE (c)R408/6-123-F/17 DeHavilland DHC-8 Model 400, 401, and 402 Pratt & Whitney PW150A * E00062EN *The Type Certification program for the DeHavilland DHC-8 Model 400, 401, and 402 is incomplete as of this propeller type certificate approval date. Aircraft installations must be approved as part of the aircraft type certificate and demonstrate compliance with the applicable aircraft airworthiness requirements. NOTE 12: 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 UKCAA. 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......