TCDS TC 719

MODELS: Boeing S-307 T.C. NUMBER: 719 I - Model S-307, 39 PCIM (Approved 3/13/40) Engines 4 Wright Cyclones GR-1820G-102 with two 4-1/2 N dampers and either 16:11 or 3:2 reduction Fuel 90 minimum octane aviation gasoline Engine limits Maximum continuous, 36.7 in. Hg.. 2200 pm (900 hp) (To 6000 ft.) 35.0 in. Bg., 2200 rpm (900 hp) Take-off (one minute), in. Hg., 2350 rpm (1100 bp) or 43. in. Hg., 2200 rpm (1100 hp) Airspeed limits Level flight or climb - 230 mph (200 knots) (T. I.A.S.) Glide or dive - 262 mph Flaps extended - 126 mph C.G. range (321.4) (21.0 percent MAC) to (336.1) (29.2 percent (See NOTE 4.) Weight limits Landing 41,000 1bs. (See NOTE 2) Take-off 45,000 1bs. (See NOTE 2) Both may be increased 246 1bs. when complete de-icer installed. No. seats 39 maximum day type, 31 maximum sleeper type (16 pilots at and 1 flight engineer at (147)). Maximum baggage Maximum capacity of compartments: Cu. Ft. Rear main cargo compartment 200 Forward main cargo compartment 168 Forward auxiliary cargo Linen closet - forward - L.H. side 7.7 Coat compartment - aft center 3 compartments at 20 1bs. (9 kgs.) each between passenger seats on R.H. side of 60 27 5 compartments aft of seats on R. H. side of cabin: 25 1bs. (11 kgs.) each in fore and aft ments and 50 1bs. (23 kgs.) each in 200 91 Puel capacity 1700 gallons (two tanks at 425 gallons each and four tanks at 212.5 gallons each in oil capacity 100 gallons (four tanks at 25 gallons each, one in each nacelle) Control surface movements Not available Serial Nos. eligible 1995 and up Required equipment Items 101. 102 (a) and 103 II - Model S-307 Conversion in accordance with Airline Training, Inc., Homestead, FL, data or equivalent, PCLM (Approved 4/6/50) Engines 4 Wright Cyclones GR-1820G-102 with two 4-1/2 N dampers and Fuel 90 minimum octane aviation gasoline Engine limits Maximum continuous, (30 6000 ft.) 35.0 in. 09. 2200 km (900 kp Take-off (one minute), 43 in. Hg.. 2350 Ipm (1100 bp) oI 43 in. Hg.. 2200 pin (1100 hp) Airspeed limits Maximum - never exceed 256 mph (I. I.A.S.) climb or level flight - 192 mph (167 knots) Maneuvering 137.5 mph (119.5 Flaps extended - 126 mph (110 knots) C.G. range (Flight) (321.4) (21.0 percent MAC) to (336.1) (See NOTE 4) (29.2 percent (322.7) (21.7 percent MAC) to (332.8) (27.4 percent MAC) Usable ceiling See approved Flight Manual Weight limits Landing 45,000 1bs. (See NOTE 2) Take-off 50,000 1bs. (See NOTE 2) No. seats Minimum crew 3 (two pilots at (113) and one flight engineer at (147)). Maximum baggage Forward belly compartment 2690 1bs. Rear belly compartment 2400 1bs. (465) Fuel capacity 1700 gallons total (2 main tanks in wing 425 (331.6), 2 inboard auxiliary tanks in wing 212.5 gallons each (341.6), 2 outboard auxiliary tanks in wing 212.5 gallons each oil capacity 200 gallons total (1 50 gallon tank in each inboard nacelle (276), 1 50 gallon tank in each outboard Control surface Wing flaps - 43.5 degrees movements Aileron - up 15 degrees, down 12 degrees up elevator - 1-1/4" displacement Rudder - 25-1/4 right, Rudder trim tab - 4" right, 4" left Serial Nos. eligible 2002 and 2003 Required equipment Items 101, 102 (b), 103, 104, 105, 601 Specifications Pertinent to All Models: MAC 179.5 in. L.E. MAC (283.66) Leveling means Lugs on left-hand compression strut in accessory compartment under cabin floor between spars Datum 50 in. forward of nose of fuselage Certification basis Type Certificate No. 719 Production basis Export eligibility Eligible for export to all countries except as follows, subject to the provisions of ASR 312 (MOP 2-4) : Canada Landplane - eligible Skiplane - not eligible Propellers and Propeller Accessories (except De-Icing Equipment) Propellers - Hamilton Standard hubs blades 6153A-18 to 6153A-20 Diameter 11'6-3/8' maximum, 11'3-3/8" minimum. For interchange- able blade models see Prop. Spec. No. 603 (NOTE 6) - Minimum low pitch setting Engines and Engine Accessories - Fuel and oil System dump valve installation per Fuel dump installations which provide for complete dumping of right and left main tank fuel installed in accordance with Airline Training, Inc. approved data. 104. Four electrically driven Chandler-Hill Model AN-4101CH or equivalent, installed in accordance with Airline Training, Inc. approved Residual fuel and oil for Model S-307. Weight and arm not determined. Necessary to fill all oil and fuel operate all engines and drain tanks before weighing. Interior Equipment (Propeller, Wing and Windshield) 103. CAA Approved Flight Manual (current issue) (Airplane Operating Manual De-Icing Equipment (Propeller, Wing and Windshield) De-Icer instailation and control surface - Boots and attachments - wing (removable) (303) and attachments - empennage (removable) (788) Valves, fittings, etc. (removable) 16 1bs. (292) lines, vales, and energ (fixed) 95 1bs. (367) Propeller 4 slinger rings (Hamilton Standard 52903) (removable) 12 1bs. (191) 2 motor driven pumps (Eclipse M3454) (removable) 0 1DS (315) One 10 gallon tank (removable) (332) 2 fuselage ice protection plates 27 1bs. (180) (5) 10 gallons de-icer fluid (removable) 75 1bs. (332) (6) Miscellaneous lines, fittings, brackets and valves (fixed) 7 1bs. (229) Miscellaneous (Not listed above) 601. Wing slots in accordance with BAC Drawings 15-6395 and 15-6396 NOTE 1. Current weight and balance report including list of equipment included in certificated weight empty, and loading instructions, in each aircraft at the time of original certification and at all times thereafter. If provisions other than Item 102(a) or (b) are made for dumping, the fuel dump valves shall be made positively inoperative. If Item 102(a) or (b) is installed, the aircraft operation record shall incorporate one of the following statements, as the case may Non-Air Carrier. "Fuel shall not be dumped except in accordance with the provision of CAR 60.900 and with flaps retracted«' Air Carrier. With authorized weight in excess of maximum landing weight: 'Landing shall not be made at a weight in excess of maximum landing weight except in accordance with CAR 61.7811. be dumped except in accordance and with flaps retracted, and then only if the pilot deems it safer than landing at a weight in excess of maximum With authorized weight not in excess of maximum landing weight: Fuel shall not be dumped except in accordance with CAR 61.7811 and with flaps retracted. wOe the pite plans pined thated in act dance with "This airplane shall be operated in accordance with the CAA Approved Operating Manual for Boeing Model S-307 which shall be carried in the pilot's compartment at all times." NOTE 4. When elevator hydraulic boost is disconnected, the forward landin limit shall be 24.3 percent (25 percent, wheel down) for take-off and and 21 percent in flight.