TCDS ATC 579

DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION ATC 579 Revision 1 Hawker Beechcraft B17R (Army UC-43H) 5 PCLB September 1, 2010 AIRCRAFT SPECIFICATION NO.579 Type Certificate Holder Hawker Beechcraft Corporation 9709 East Central Wichita, Kansas 67201 Type Certificate Holder Record: Beech Aircraft Corporation transferred to Raytheon Aircraft Company on April 15, 1996 Raytheon Aircraft Company transferred to Hawker Beechcraft Corporation on March 26, 2007 MODELS: Beechcraft B17R (Army UC-43H), 5 PCLB T.C. NUMBER: ATC 579 Wright R-975E-3 or R-9758-2 Placard limits (See NOTE 4) With fixed metal or adj. metal propeller Maximum, except take-off 33.0 in. Hg.. or 31.5 in.Hg-, or 29.5 in. Hg.. or 28.5 in. Hg.. 2100 Take-off (one minute) -- in. Hg., or 35.0 in. Hg.. 2200 rpm (420 hp) With controllable metal propeller (Below 4000 ft.) 28.5 in.Hg.. 2200 rpm (330 hp) 27.0 in. Hg., 2200 rpm (330 hp) (one minute) 35.0 in. Hg.. 2200 rpm (420 hp) Propeller Maximum permissible diameter 102 in. Placard speeds Level flight or climb - 206 mph True Ind. Glide or dive - 225 mph True Ind. Flaps extended - 100 mph True Ind. Fuel 70 gallons (two tanks: fuselage front 28 gallons fuselage rear 42 gallons (+55) oil 6 gallons (-13) No. passengers 4 (maximum (front +19, rear +60.5) (See NOTE 3) Baggage 125 1bs. (maximum) (+36) (See NOTE 3) Standard weight 3615 1bs. C. G. limits (+16.6) and (+29.0) Spec. basis Approved Type Certificate No. 579 Serial Nos. B17F-39, B17R-50 and up manufactured prior to 9/30/39 and all AAF Nos. eligible. Approval expired as of 9/30/39. EQUIPMENT: (Datum is lower wing leading edge) (* Means net increase) Page No. 1 2 Rev. No. 579 2 Rev. 1 Class I: 101. Engine ring cowl 28 1bs. 102- Battery (Exide 6TS-13-1) (under baggage compartment) 36 1bs. 103- Starter 25 1bs. 104- Generator 15 1bs. 105. Control column (a) Swing-over or (b) "T" type (Inspector should verify type installed) 106. 24 in. streamline wheels (Hayes ATC 23) with H.D. tires. Wheels must be placarded for these tires. 107- 10x3 tail wheel 108- Fixed metal propeller (Curtiss 55503) 109- Oil radiator (Harrison) 110- Cabin heater Class II: 200. Miscellaneous items as noted in approved weight and balance report 201. Miscellaneous extra instruments 202. Controllable deal proper Men fantason 90 1bs. 203. Standard hub 2D30 and blades 6101A or 6095A series Use actual weight 204- Camera installation (Drawings B17E015, B17E106, and B17E902) - Camera and viewfinder 110 1bs. (+51); operator's stool 4 1bs. (+65); 25 gallons fuel tank in baggage compartment 15 1bs. (+86) - Remove rear seat 31 lbs. (+62); cover plates for camera and viewfinder 3 lbs• (+51) and rear fuselage fuel tank (+55) . 205. Landing lights (a) (Grimes) - under Lower wing 3.5 1bs. each (+19) (b) (Hall) - in wheel well 3.5 1bs. each (+37) (c) (S & M) Use actual weight 206. Flares (Drawing No. I-17004) 207- Radio, variable (location and actua. eight of installation includin‹ controls, etc., or name of manufac- curer and model if already installed and included in the empty weight should be noted on inspection report) (Drawing I-17002 shows approved locations) . 208- (a) Breeze 15 1bs. 10 1bs. 209. Extra door on right side 6 1bs.* 210. fuel tanks in wings 23 gallons or 25 gallons each, upper (+45.5) 20 1bs. each. of fuel tanks including removal of the fuselage tanks may be used subject to inspector's approval and provided weight and balance accounts for actual installation. Rev. 1 3 579 (a) 7.5 gallons (-13) (b) 8.5 gallons (-13) (c) 10.3 gallons (-13) (Eclipse 25 amp) 20 1bs. Golf bag compartment (Drawing I-17006). In bay aft of, and opens into, baggage compartment. Maximum capacity 70 1bs. golf bag and clubs only. Parachutes or parachute type chairs Seaplane corrosion protection 20 1bs. 216- Pressure fire extinguisher (Drawing I-17001) (Container at +14) 217. Metal tank cover (Drawing I-17003) 218. Camera well (Drawing I-17005) 219. Ballast installation (+210) Maximum 25 1bs. 220. Special tool compartment in tail 25 lbs. including tools (+218) Class III: 24 in. streamline wheels (Hayes AIC 23) with 6-ply tires 75 1bs. (wheels must be placarded for 6-ply tires) proof tubes 7-50-10 8 lhs.* 24 in. streamline 5 1bs.* 303. Tail wheel steering device No change in weights 304. Electric motor and installation for auxiliary to manually operated retracting gear (25 ampere fuse required) 8 1bs.* The following placards were required on certain airplanes when originally certificated: At the fuel valve: "USE MAIN FUSELAGE TANKS FOR TAKE-OFF AND USE FUEL OUT OF AUXILIARY LOWER WING TANKS BEFORE EMPTYING MAIN TANKS.'® at rear fuselage tank, 'AS 4-PLACE 47 GALS., AS 5-PLACE 22 GALS." Baggage placarded to 75 lbs. Similar instructions must be placed in subsequent airplanes when the weight and balance report is based on any but the most adverse (from balance standpoint) use of the fuel. Inspector's report and actual weight and balance report should specify restrictions applicable. NOTE 2. Eligible for export as follows subject to inspection for equipment specified in Chapter XII of Inspection handbook: (6-9-38) (a) Canada - Landplane - Skiplane - not eligible (b) All other countries except Australia NOTE 3. Five place type must be placarded for 75 1bs. when 3 passengers occupy rear seat unless more is substantiated in actual veight and balance report. NOTE 4. Eligible for certification with placard limits of 420 hp. 2200 Ipm and manifold pressure of 34.5 in. Hg., for all operations. A weight and balance report must be made accounting for increase in thè reguired minimum fuel affected by the 420 METO hp rating. ** END **