TCDS A4NW

Page No. 1 2 3 4 Rev. No. 5 3 1 1 DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION A4NW Revision 5 BLANCHAIR (EAGLE) DW-1 July 8, 2010 TYPE CERTIFICATE DATA SHEET NO. A4NW This data sheet, which is part of Type Certificate No. A4NW, prescribes conditions and limitations under which the product, for which the Type Certificate was issued, meets the airworthiness requirements of the Federal Aviation Regulations. Type Certificate Holder BlanchAir LLC 942 Windemere Dr. NW Salem, OR 97304-2722 Type Certificate Holder Record Eagle Aircraft Company transferred TC A4NW to Bellanca, Inc. on October 22, 1984 Bellanca, Inc. transferred TC A4NW to Alexandria Aircraft LLC on May 30, 2002 Alexandria Aircraft LLC transferred to BlanchAir LLC on July 8, 2010 I. Model EAGLE DW-1 (Restricted Category), approved November 17, 1978 (See Note 5 for Restricted Categor y Airworthiness Certificate Eligibility) Engine Jacobs R 755 B2 Fuel 80 minimum octane aviation gasoline Engine limits For all operations 2200 rpm (275 hp) Max cylinder head temperature 500 F Propeller Grumman (Sensenich) ground adjust able Model J-5404, SR-5404, SR-5404/MA96K Pitch setting at 36 in. STA is 15.0 . Static RPM at maximum permissible throttle setting (not over 2090, not under 1990). The propeller must be indexed in the zero degree position, (Blades in line with crank throw). NOTE: Blade angle adjustment must be with  1/2 degree allowable tolerance to result in never exceeding the maximum rated RPM at rated power in a full throttle climb at 75 mph CAS. Airspeed limits (CAS) Never exceed 113 mph Dive 126 mph C.G. Range 13.5 to 18.75 aft of datum Empty weight C.G. range None Datum Landing gear axle center line. Leveling means Top fuselage longeron at cockpit opening. Maximum weight 3860 lbs. A4NW Page 2 of 4 Number of seats 1 Hopper capacity 250 U.S. gallon Fuel capacity 40 U.S. gallon Oil capacity 4.4 U.S. gallon Control surface movements Aileron Up 28  Down 8  Elevator Up 30  Down 25  Rudder Left 25  Right 25  Spoilers Up 90  Serial numbers eligible DW-1-0001 See Note 5 for restricted Categor y Airworthiness Certification Eligibility. Certification basis FAR 21.25(a)(1) Using the ai rworthiness requirement of Appendix B of CAM 8. Production basis None Exterior finish The wings, aileron and center s ection must be painted white to reflect heat. II. Model EAGLE DW-1 (Restricte d Category), approved April 25, 1980 Engine Continental W670-6N (R-670-4) Continental W670-6A (R-670-5) (with dual magnetos) (new, newly overhauled, or rebuilt) Lycoming IO-540-M1B5D Fuel 80 minimum octane av iation gasoline (W670 series) 100/130 mininum octane avia tion gasoline (IO-540 series) Engine limits For all operations 2075 rpm (220 hp) (W670) For all operations 2700 rpm (300 hp) (IO-540) Propeller Hartzell HA 2V20-1B/V10133N (W670) Pitch setting at 30 in. sta. is 17 . Static RPM at maximum permissible throttle setting (not under 1800, not over 1950). Hartzell HC-C3YR-1RF/F8468-2R (IO-540) Pitch setting at 30 in. sta. is 10.5  (lo pitch) 37  (hi pitch) Diameter: not over 82 in., not under 78 in. Hartzell 49F4-11B governor Airspeed Limits (CAS) Never exceed 130 mph Dive 150 mph C.G. range 13.5 to 18.75 aft of datum Empty weight C.G. range None Datum Landing gear axle center line. Leveling means Underneath surface of the top wing near the wing root. Maximum weight 4000 lbs. Number of seats 1 Page 3 of 4 A4NW Hopper capacity 2082 lbs. Fuel capacity 40 U.S. gal. (opt. 65 U.S. gal.) Oil capacity 4.4 U.S. gal. (W670) 3.0 U.S. gal. (IO-540) Control surface movements Aileron Up 24  Down 8  Elevator Left Up 16  Down 10 ; Right Up 15  Down 11  (Min) Rudder Left 23  Right 23  Spoilers Up 90  Serial numbers eligible DW-1-0002 and up Certification basis FAR 21.25(a)(1) Using the ai rworthiness requirements of Appendix B of CAM 8. Production basis None. Prior to original certifica tion of each aircraft, an FAA representative must perform a detailed inspection for workmans hip, materials, and conformity with the technical data, and a check of the flight characteristics. Exterior Finish The wings, aileron, and center section must be painted white to reflect heat. NOTE 1. Current weight and balance report together with list of equipment included in certificated empty weight, and loading instructions, when necessary, must be provided for each aircraft at the time of original certification. NOTE 2. The following placard must be displayed in front of, and in clear view of, the pilot on airplane serial no. DW-1-0001: EAGLE AIRCRAFT CO. AIRPLANE MOD EL DW-1 TYPE CERTIFICATE NO. A4NW "THIS AIRCRAFT IS CERTIFIED UNDER CA R 8, AS A SPECIAL PURPOSE AGRICULTURAL AIRCRAFT AND MUST BE OPERATED IN COMPLIANCE WITH OPERATING LIMITATIONS STATED IN THE FORM OF PLACARDS AND MARKINGS. THIS AIRCRAFT APPROVED FOR DAY, VFR FLIGHT ONLY. NO INVER TED OR ACROBATIC MANEUVERS INCLUDING SPINS APPROVED. MAXIMUM MANEUVERING SPEED (Vm) 90 mph CAS MAXIMUM OPERATING SPEED (Vne) 113 mph CAS MAXIMUM POSITIVE LOAD FACTOR 4.2 G MAXIMUM NEGATIVE LOAD FACTOR -1.0 G DESIGN GROSS WEIGHT 3860 LBS. CENTER OF GRAVITY LIMITS ARE FROM 13.5 INCHES TO 18.75 INCHES AFT OF DATUM. DATUM IS THE MAIN LANDING GEAR AXLE. SULPHUR DUSTING AND FLAMMABLE LIQUID SPRAYING IS PROHIBITED UNLESS SPECIAL FIRE PREVENTION MEASURES HAVE BEEN INCORPORATED IN THIS AIRCRAFT. THE ALTERNATOR IN THIS ELECTRICAL SYSTEM HAS BEEN TESTED TO 45 AMPS MAXIMUM." The following placard must be displayed in front of a nd in clear view of the pilot on airplane serial no. DW-1-0002 and up: A4NW Page 4 of 4 EAGLE AIRCRAFT CO. AIRPLANE MOD EL DW-1 TYPE CERTIFICATE NO. A4NW "THIS AIRCRAFT IS CERTIFIED UNDER CA R 8, AS A SPECIAL PURPOSE AGRICULTURAL AIRCRAFT AND MUST BE OPERATED IN COMPLIANCE WITH OPERATING LIMITATIONS STATED IN THE FORM OF PLACARDS , MARKINGS, AND AIRPLANE FLIGHT MANUAL. THIS AIRCRAFT APPROVED FOR DAY AND NIGHT VFR FLIGHT ONLY. NO INVERTED OR ACROBATIC MANEUVERS INCLUDING SPINS APPROVED. MAXIMUM MANEUVERING SPEED (Vm) 107 mph CAS MAXIMUM OPERATING SPEED (Vne) 130 mph CAS MAXIMUM POSITIVE LOAD FACTOR 4.2 G MAXIMUM NEGATIVE LOAD FACTOR -1.0 G DESIGN GROSS WEIGHT 4000 LBS. CENTER OF GRAVITY LIMITS ARE FROM 13.5 INCHES TO 18.75 INCHES AFT OF DATUM. DATUM IS THE MAIN LANDING GEAR AXLE. SULPHUR DUSTING AND FLAMMABLE FL UID SPRAYING IS PROHIBITED UNLESS SPECIAL FIRE PREVENTION MEASURES HAVE BEEN INCORPORATED IN THIS AIRCRAFT. THE TYPE CERTIFICATE REQUIRES THAT THE WINGS, AILERON, AND CENTER SECTION BE PAINTED WHITE. (Continental W670) THE ALTERNATOR IN THIS ELECTRICAL SYSTEM HAS BEEN TESTED TO 40 AMPS MAXIMUM." NOTE 3. Reserved. NOTE 4. The DW-1 (serial numbers DW-1-0002 and up) has demonstrated satisfactory operation at 5400 pounds gross weight in the restricted category envelope at sea level under standard day conditions. Further weight increases should not be accomplished in the field. The design maximum takeoff a nd landing weight is 4000 pounds. Since the hopper load is disposable, landings in excess of this weight should not be requi red. If it is necessary to make a landing weight over 4000 pounds, the pilot must exercise caution to prevent structural damage to the landing gear and airframe. The takeoff weight should be adjusted also, to suit the runway surface to prevent over-stressing the structure. NOTE 5. Airplane Serial No. DW-1-0001 was extensively damaged and cannot be rebuilt to the original certified configuration due to insufficient type design data. This airplane is no longer eligible for a Restricted Category Airworthiness Certificate. .....END.....