TYPE CERTIFICATE DATA SHEET NO. A00010WI

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Page No. 1 2 3 4 5 6 Rev. No. 8 4 5 4 7 6 DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION A00010WI Revision 8 | Hawker Beechcraft 390 March 26, 2007 | TYPE CERTIFICATE DATA SHEET NO. A00010WI This data sheet, which is part of Type Certificate No. A00010WI, 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: Hawker Beechcraft Corporation 9709 East Central Wichita, Kansas 67201 Type Certificate Holder Record: Raytheon Aircraft Company transferred to Hawker Beechcraft Corporation on March 26, 2007 I. MODEL 390 (PREMIER I) (NORMAL CATEGORY) APPROVED MARCH 23, 2001 Engine Two Williams-Rolls, Inc. International FJ44-2A Turbofans Fuel Commercial kerosene JET A, JET A-1, per ASTM -D-1655, or JP-8 per MIL-T-83133 (Limited use Av-gas 100LL per ASTM D910. Limited to 5,000 gallons per engine between major periodic inspections. Operation is limited to 10,000 feet and below with the electric boost pumps on per AFM procedures). Fuels not containing icing inhibitors must have MIL-I-27686 or MIL-I-85470 fuel system icing inhibitor added in amounts of not less than 0.10% nor more than 0.15% by volume. Minimum fuel icing inhibitor content during refueling is 0.10% by volume. Dupont Stadis 450 anti-static additive or equivalent is permitted to bring fuel up to 300 conductive units, but not to exceed 1 part per million. SOHIO Biobor JF biocide additive or equivalent is permitted at a concentration not to exceed 20 parts per million (270 ppm total additive) of elemental boron. Engine Limits Static, Sea Level, Standard Day Takeoff (5 minutes) static thrust, sea level 2300 lbs. Maximum Continuous static thrust, sea level 2300 lbs. Maximum permissible engine rotor (Operating speed) Low pressure rotor, N1 (30 seconds) 106.4% Low pressure rotor, N1 105.2% High pressure rotor, N2 98.8% Maximum permissible Interstage Turbine Temperature (ITT) Take-off (10 second) 835°C Take-off (5 minutes) 820°C Maximum Continuous 805°C Engine Starting 805°C Engine Starting (30 second) 900°C Engine Starting (15 seconds) 1000°C All other engine limits as noted in engine TCDS E3GL. A00010WI, Rev. 8 2 Airspeed Limits (KCAS) Vmo (Maximum Operating Speed) Sea Level to 27,600 feet 320 Mmo (Maximum Operating Mach No.) (above 27,600 feet) .80 VF (Flap Extension Speed) Flaps 10 ° 200 Flaps 20° RB-4 thru RB-69 and aircraft not modified per kit 390-3203 RB-2, RB-3, RB-70 and after and aircraft modified per kit 390-3203 200 201 Flaps 30° 170 VLO (Retraction) 180 VLO (Extension) RB-4 thru RB-69 and aircraft not modified per kit 390-3203 RB-2, RB-3, RB-70 and after and aircraft modified per kit 390-3203 200 201 VLE RB-4 thru RB-69 and aircraft not modified per kit 390-3203 RB-2, RB-3, RB-70 and after and aircraft modified per kit 390-3203 200 201 VO Operating Maneuvering Speed 200 VMCA (Min. Control Speed ) Flaps UP 102 Flaps 10° 97 Flaps 20° 93 VMCL (Flaps 30°) 91 Datum F.S. 0.00 is located 34.00 inches forward of the nose of the aircraft. Mean Aerodynamic Chord 66.24 inches. The leading edge of the mean aerodynamic chord is 278.471 inches aft of the datum. C.G. Range (Gear and Flaps Extended) Allowable Forward C. G. Up To 12,500 lbs Aft C. G. Up To 10,000 lbs Aft C. G. Up To 12,500 lbs Straight line variation between given points F.S. 294.37 F.S. 303.97 F.S. 300.14 Leveling Means Level is determined with a level gauge placed on the cabin door floor longeron. Maximum Weights Ramp 12,591 LBS Takeoff 12,500 LBS Landing 11,600 LBS Zero Fuel 10,000 LBS Minimum Crew One Pilot No. of Seats 2 Crew 6 Passengers Maximum Baggage Nose Baggage 150 lb. Aft Cabin Baggage 140 lbs. Aft Fuselage Baggage –Forward 200 lbs. Aft Fuselage Baggage –Aft 200 lbs. A00010WI, Rev. 8 3 Fuel Capacity (Total Airplane) U.S. CAP. GAL. U.S. USABLE GAL. ARM Gravity Fill 552.8 539 290.8 Single Point 541.8 528 289.8 For aircraft serial numbers RB-75 and after, or prior aircraft that embody Kit No. 390-9200: Gravity Fill 552.8 547.8 290.5 Single Point 541.8 537.0 289.5 See Note 1. for data on unusable and undrainable fuel Oil Capacity 2.5 Quarts usable per engine - ARM 390.5 See Note 1. for data on undrainable oil. Maximum Operating Altitude 41,000 feet Serial Numbers Eligible RB-2 and after Control Surface Movements Rudder Right Left 25° +1°/-0° 25° +1°/-0° Rudder Trim Right Left 20° +1°/-0° 20° +1°/-0° Elevators Up Down 20° +1°/-0° 9.6° +1°/-0° Horiz. Tail Incidence Leading Edge Up Leading Edge Down 1.4° ± 0.2° 7° ± 0.2° Elevator Trim Up Down 3.06° ± 0.5° 12.6° ± 0.5° Ailerons Up Down 15.5° +0.5°/-0° 12.5° + 0°/-0.5 Aileron Trim LH Up Down RH Up Down 20° ± 1° 20° ± 1° 20° ± 2° 20° ± 2° Wing Flap Takeoff Landing 0º, 10º, 20° *Multiple tolerances 30° *Multiple tolerances Roll Spoiler- flaps > 20° Outboard Panels Mid panels 9.0º ± 0.7º 8.05º ± 1.05° Roll Spoiler- flaps down Outboard Panels Mid panels 4.3º ± 0.4° 3.55º ± 0.75° Deleted: Page Break A00010WI, Rev. 8 4 Control Surface Movements (cont’d) Speedbrake Outboard Panels Mid panels 23° ± 0.3° 23° + 0°/-1.8° Lift Dump Inboard Panels Outboard Panels Mid Panels 60° ± 4° 45° +1°/-1.5° 45° +0°/-3.1° *See Specification BS25190, BS25191 and BS25192 or maintenance manual for rigging tolerances. Certification Basis (1) 14 CFR part 23, effective February 1, 1965, as amended by Amendments 23-1 through 23-52. (2) 14 CFR part 36 effective December 1, 1969, as amended by 36-1 through 36-22. (3) 14 CFR part 34 as amended by Amendments 34-1 through 34-3. (4) Title 49 U.S.C. Section 44715: (5) Special Conditions as follows: (a) 23-096-SC and 23-096A-SC-additional requirements for: Performance, stalling speed, takeoff speeds, takeoff performance, accelerate-stop distance, takeoff path, takeoff distance and takeoff run, takeoff flight path, climb, climb