TCDS A-2-569

Page No. 1 2 3 Rev. No. 5 5 4 DEPARTMENT OF COMMERCE CIVIL AERONAUTICS ADMINISTRATION A-2-569 Revision 5 NAVY N3N-3 December 21, 1950 AIRCRAFT SPECIFICATION NO. A-2-569 Manufacturer Naval Aircraft Factory Philadelphia, Penn. I - Model N3N-3, 2 POLB Engine Wright R-760-2, -4 or -8 built by Naval Aircraft Fact. (Equivalent to Wright R-760E-T) (See NOTE 2 for Lycoming engines and NOTE 3 for P & W TIB-3 engine) Fuel 73 min. octane aviation gasoline Engine limits For all operations, 2000 rpm (235 hp) (See NOTE 1(g) for placard) Airspeed limits Level flight or climb 126 mph True Ind. Glide or dive 152 mph True Ind. (Glide or dive speed may be increased to 180 mph True Indicated if Max. Weight is restricted to 2800 lbs.) Propeller limits Diameter - not over 102 in. (See NOTE 1(g) for additional limitations). not under 100 in. (additional limitations. C.G. range (-1.6) to (+7.0) at 3200 lbs. or less (-1.6) to (+4.9) at 3400 lbs. Straight line variation between points given. 3000 3100 3200 3300 3400 -2 -1 0 1 2 3 4 5 6 7 FRONT LIMIT REAR LIMIT INCHES LBS. Empty weight C.G. range None Datum Leading edge of lower wing Leveling means Top surface of upper longerons in either cockpit. Maximum weight 3200 lbs. (See NOTES 2 and 3 for 3400 lbs.) No. seats 2 (one at +28 and one at +75) Maximum baggage 20 lbs. (+100) Fuel capacity 45 gals. (-11) Oil capacity 3-3/4 gals. (-31) Control surface movements Elevators Up 35° Down 25° Elevator tab Up 15° Down 15° Rudder Right 30° Left 30° Aileron Up 30° Down 18° Certification basis CAR 4a.031 Serial Nos. All eligible per NOTES 1 AND 2 Required equipment Items 1, 101, 102, 103, 201, 202, and 403. Propellers and Propeller Accessories 1. Propeller - adj. metal - Navy 5406AL or 5406AR hub 86 lbs. (-80) and 4350F blades (See NOTE 1(e) for restrictions) A-2-569 2 Engines and Engine Accessories (Fuel and Oil System) 101. Carburetor air heater assy. (See NOTE 1(b) for modifications) 13 lbs. 102. Engine-driven fuel pump - Pesco R-400 103. Hand fuel pump 104. Fire ext. press. type (engine section) ( -9) 105. Carburetor air cleaner 106. Starter - hand cranking 107. Engine primer Landing Gear 201. Bendix 30x5 fabricated wheels (-19.5) 202. 10x3 tail wheel (+183.5) Electrical Equipment 301. Batter (See NOTE 1(c) for modifications) (-29) 302. Swivel panel light (front and rear) 303. Anchor (turtle back) light 304. Wing position lights 305. Tail light (See NOTE 1 (c) for modifications) Interior Equipment 401. First-aid kit 402. Fire extinguisher - portable 403. Safety belts (two) - NAF 39941 (+28) & (+75) 404. Venturi tube NOTE 1. Prior to certification, each aircraft must comply with the following: (a) Firewall. Firewall either to be completely replaced by, or covered or backed by, one of the following materials: (1) Stainless steel - 015 in. thick (2) Nickel-chromium-iron alloy sheet - .015 in. thick (3) Low carbon steel - .018 in. thick (aluminum coated or otherwise protected against corrosion) (4) Monel metal - .018 in. thick (5) Terne plate - .018 in. thick (b) Carburetor Air Heater. Carburetor air heater to be modified in accordance with Airworthiness Bulletin No. 83. (c) Electrical System. Battery and battey supports to be removed or, if battery is retained, a master switch, approved type tail light, and battery to be installed and structure adjacent to battery to be painted with acid-proof paint. (d) Cockpit Air Contamination. The fuselage skin openings around landing gear members and any other openings leading through the bottom of the fuselage or lower wing into the cockpits to be sealed with suitable boots or skin patches to prevent engine exhaust from entering the cockpits and contaminating the air with carbon monoxide. (e) Propeller. If 9 ft. dia. propeller is installed, it should be reduced to 8 ft. 6 in. diameter. Pitch setting at 42 in. sta. for 8 ft. 6 in. dia. blades - 11°. Setting may be 14.6° if max. weight is restricted to 2800 lbs. Propeller to be indexed so that blades are 45° ahead of the locating screw on the propeller shaft (in the direction of rotation). (f) Spin Placard. Placards reading "Intentional Spinning Prohibited" to be installed in both cockpits. (g) Engine Operation Placard. Placards reading "Avoid Continuous Operation above 1800 rpm or below 1680 rpm" to be installed in both cockpits. (h) Solo Flying Placard. Placard reading "Fly Solo from Front Cockpit Only" to be installed in rear cockpit unless complete set of engine controls are installed in rear cockpit. (i) Instrument Marking. Tachometer to be marked at 2000 rpm. Airspeed indicator to be marked at 126 mph and 152 mph. (j) Fuel and oil Markings. The words "Fuel", "73 octane", and "45 gallons" to be marked on or adjacent to fuel filler cap. The words "Oil" and "3-3/4 gallons" to be marked on or adjacent to oil filler cap. NOTE 2. Eligible for installation of Lycoming R-680-E3, -E3A, or -E3B engine (military designation R-680-9 or R-680-13). The following are applicable to this installation: (a) Fuel - min. 87 octane aviation gasoline. (b) Engine limits: Maximum continuous, 2200 rpm (285 hp) Take-off (one minute), 2300 rpm (300 hp) (c) Airspeed limits: Level flight or climb 126 mph True Ind. Glide or dive 164 mph True Ind. (d) Propeller - Ham. Std. Constant Speed, 2B20 Hub, 6135A-9 Blades, 1012-A1 Governor. (e) Propeller limits: Pitch settings at 42 in. sta. -Low 9°, high 19°; dia. 8'3" max., 8'1" min. (f) Powerplant installation - AT-10 exhaust, carburetor heater muff, and oil tank (6 gals.) may be installed without modification. No cowling or engine baffles may be used unless flight tested by CAA representatives. (g) Maximum weight - 3400 lbs. provided that wheels and tires having an approved rating of 1700 lbs. each (or greater) are installed. (BT-13 or BT-15 wheels, tires, and axles are satisfactory.) (h) Engine mount - Satisfactory engine mounts have been substantiated by the following modifiers: Brandt, Perkins, and Brandt, Marysville, Calif., Drawing No. 1. Rankin Aivation Industries, Tulare, Calif., Drawing dated February, 1947. South Delta Aviation Service, Rolling Fork, Miss., Original R-760 mount modified for Lycoming R-680 engine. 3 A-2-569 (i) Fuel pumps - Wobble (U.A.P. Type D-2) Engine Driven (AN 4100 CE) (j) NOTE 1, parts (b), (e), (g), (i) and (j) are not applicable to this installation. Required equipment items 1, 101, 102, 103, and 201 should be replaced by corresponding items specified in this note. NOTE 3. Eligible for installation of Pratt and Whitney T1B-3 (R-985-AN-1 or -AN-3) engine. The following are applicable to this installation: (a) Fuel - minimum 87 octane aviation gasoline (b) Engine limits - Maximum continuous, 37.5 in. Hg., 2300 rpm (450 hp) Take-off (one minute), 37.5 in. Hg., 2300 rpm (450 hp) With these power ratings, a minimum of 67 1/2 gals. of fuel capacity must be provided except in Restricted Category aircraft (certificated prior to October 11, 1950) in which case the airplane must be placarded to be re-fueled for each hour of operation. (c) Airspeed limits - Level flight or climb 100 mph True Ind. Glide or dive 120 mph True Ind. (d) Propeller (1) Ham. Std., two-position, 2D30 hub, 6101A-12 to -18 blades Diameter - not over 108 in., not under 102 in. Low pitch limit at 42 in. R. 13.5° High pitch limit at 42 in. R. 18.0° (2) Western Propeller Co. model W2-1-9'-0" (ground adjustable) Diameter - not over 108 in., not under 106 in. Pitch setting at 42 in. R. 12.5° (3) Ham. Std., 5406 hub with 1945-6 blades, 1C1-12 blades, 33C1 blades or A3A1-12 blades Diameter with 1C1-12 blades - not over 108 in., not under 100 in. Pitch setting at 42 in. R. 12.5° Diameter with 1945-6, 33C1 or A3A1-12 blades - not over 108 in., not under 106 in. Pitch setting at 42 in. R. (33C1 blades) 12.5° Pitch setting at 42 in. R. (A3A1-12 blades) 12.5° Index A3A1-12 propeller at 0° to crank throw Pitch setting at 42 in. R. (1945-6 blades) 13.3°. (e) C.G. range - (-1-6) to (+4.9) at 3400 lbs. (f) Powerplant installation: BT-13 exhaust collector, carburetor heater muff, oil tank, oil cooler (Model U.A.P. U-3170-W-D5) and air cleaner may be installed provided the heater muff is suitable modified to insure adequate heat rise. No outside cowling or engine baffle may be used unless flight tested by CAA representatives. (g) Maximum weight - 3400 lbs. provided that wheels and tires having an approved rating of 1700 lbs. each (or greater) are installed. (BT-13 or BT-15 wheels, tires and axles are satisfactory.) (For Restricted Category take-off weight for airplanes certificated prior to October 11, 1950, see NOTE 4.) (h) Engine mount - Satisfactory engine mounts have been substantiated by the following modifiers: (1) Marsh Aviation Co., P.O. Box 1031, Phoenix, Arizona. Dwg. No. MA-3. (2) Albert D. Waite, 3133 McKinley Blvd., Sacramento, Calif. Dwg. No. 1 (3) Quick Flying Service, 2427 E. Buchanan St., Phoenix, Arizona. Dwg. No. Q985N3 (4) Goettl's Metalcraft Co., 2431 E. Buchanan St., Phoenix, Arizona Dwg. No. G2352M (i) Fuel pumps - (1) Engine-driven Chandler Evans, Type F (AN4100) (2) Hand wobble model U.A.P. D-3 (j) NOTE 1 parts (b), (e), (g), (h), (i) and (j) are not applicable to this installation. NOTE 4. Model N3N-3 aircraft which are eligible for 3400 lbs. and were certificated in the Restricted Category prior to October 11, 1950, may continue to be operated with the following limitations with the engines listed in NOTES 2 or 3: (a) Maximum take-off weight 3740 lbs. Maximum landing weight 3400 lbs. *Maneuvering speed at maximum weight 114 mph C.G. range (-1.6) to (+4.9) (b) The following placards must be in full view of the pilot: (1) *"Maneuvering speed at maximum weight not to exceed 114 mph." (2) "Intentional spins prohibited." All original certification in the Restricted Category after October 11, 1950, must be in accordance with CAR and CAM 8. *Airplanes with "Level flight or climb" speed less than 114 mph should have "maneuvering" speed reduced to correspond with "level flight or climb" speed. .....END.....