TCDS TC 704

MODELS: Boeing 314 and A-314 T.C. NUMBER: 704 I - Model 314, 89 PCFOM (Approved 1/25/39) Engines 4 Wright Double Row Cyclones GR-2600-A2, geared 16.9 Fuel 95 minimum octane aviation gasoline Engine limits Maximum, except take-off (See NOTE 9) (Straight line manifold pressure variation with altitude to 5400 ft.) 33.2 in. Hg.. 2100 Ipm (Sea level) 35.0 in. Hg.. 2100 Ipm (1200 hp) Take-off (two minutes) 42.5 in. Hg.. 2400 pm (1550 hp) Airspeed limits Level flight or climb - 178 mph (155 knots) Glide or dive - 212 mph (184 knots) True Ind. Flaps extended (40 degrees or less) (105 knots) True Ind. Flaps extended (more than 40 degrees) - 105 mph Usable ceiling (May be realized under conditions shown) True Ind. Prop. Celling Weight lanifol Airspeed Blades Flap De-Icers (Ft.) (Lbs.) RPM Pressur (Knots) Model Opening Installed 8,900 80,000 2100 Full 100 6159A-0 throttle 7,500 84,000 2100 Full 102 6159A-0 throttle 10,000 80,000 2100 Full 100 6243A-3 5 degrees Yes throttle 9,000 84,000 2100 Full 102 6243A-3 5 degrees Yes throttle Additional Conditions Standard air One engine inoperative Inoperative propeller fully feathered Carburetor air intake on "cold air" De-icers not operating C.G. range In Plight: (See NOTE 7) loaded weights of 80,000 1bs. or more (455.6) (22 percent MAC) (30.7 percent MAC) At loaded weights less than 80,000 lbs. (444.3) (17.65 percent MAC) to (478.2) (30.7 percent MAC) At loaded weights of 70,330 1bs. or more (463.4) At loaded weights less than 70,330 1bs. (455.6) (28 percent MAC) to (478.2) (30.7 percent MAC) (22 percent MAC) to (478.2) (30.7 percent MAC) Datum Nose of hull MAC Leaveling means Weight limits Landing 80,000 lbs. (See NOTES 2 and 3) Take-off 84,000 1bs. No. seats 89 maximum (variable) Maximum baggage 10,826 1bs. (See NOTE 4) Fuel capacity 5448 gallons or 32688 lbs. (2 tanks at 600 gallons each in wing stubs, 1 tank 960 gallons or 5760 1bs. (inboard) and 1 at 1164 gallons or 6984 Ibs. (outboard) in each hydro- oil capacity 300 gallons (4 tanks at 75 gallons each in wing leading edge inboard of each engine) Control surface movements Not available Serial Nos. eligible Required eguipment Items 101, 102, and 103 1992 and 1993 1988, 181, 102, and 103 992 and 1993 1990. II- Model A-314 89 PCFOM (Approved 5/2/41) (Same as Model 314 except for engine, powerplane installation, engine mount, and inner structural details.) Engines 4 #right Double Row CyClones 709C14AC1 or 579C14AC1, Fuel 95 minimum octane aviation gasoline Engine limits except take-off (Straight line manifold pressure variation with altitude to 6200 ft.) 35.8 in. Hg.. 2300 Ipm (Sea level) 37.5 in. Hg., 2300 rpm (1350 hp) Take-off (two minutes) 43.5 in. Hg.. 2400 Ipm (1600 hp) Airspeed limits Level flight or climb - 178 (155 knots) True Ind. Glide or dive - 212 mph (184 knots) True Ind. Flap extended (40 degrees or less) 121 mph (105 knots) Ture Ind. Flaps extended (more than 40 degrees) 105 mph (91 knots) True Ind Usable ceiling (May be realized under conditions shown) True Ind. Prop. COMI Ceiling Weight Manifold Airspeed Blades Flap De-Icers (Ft.) (Lbs.) RPM Pressure (Knots) Model Opening Installed 10,000 80,000 2300 Full 100 6243A-3 5 degrees Yes throttle 9,000 84,000 2300 Full 102 6243A-3 5 degrees Yes throttle Additional Conditions (1) Standard Air (2) One engine inoperative (3) Inoperative propeller fully feathered (4) Carburetor air intake or "cold air" (5) De-icer's not operating C. G. range In Flight: (See NOTE 7) At 12 ped eat MA) t (478.2) (30.7 mOC (455.6) loaded weights of less than 80,000 1bs. (444.3) (17.65 percent MAC) to (478.2) (30.7 percent MAC) At loaded weights of 70.330 lbs. or more (463.+) (25 percent MAC) to (478.2) At loaded weihgts less than 70,330 1bs. (455.6) (22 percent MAC) to (478.2) (30.7 percent MAC) Datum Nose of hull MAC 258.79 in. Leading edge of MAC at (398.66) Leveling means Lugs on rear spar in center section Weight limits Landing 40015 See 3) Take-off 84,000 1bs. (See NOTES 2 and No. seats 89 maximum (variable) Baggage Fuel capacity each in wing stubs, 1 tank 960 Jallons or 5760 1bs. (inboard) and 1 at 116 gallons or 6984 Ibs. (outboard) in each hydro- oil capacity 206 gallons (2 outboard tanks at 50 gallons each 2 inboard tanks at 53 gallons each and in wing leading edge inboard of each engine) Control surface movements Not available Serial Nos. eligible 2081 and up (See NOTE A) Required equipment Items 101, 102 and 103 Specifications Pertinent to All Models: Certification basis Type Certificate No. 704 (Aero. Bulletin 7A requirements) Production basis None (See NOTE A) Export eligibility Eligible for export to all countries except Australia and New Zealand, subject to the provisions of MOP 2-4 EQUIPMENT: Propellers and Propeller Accessories (except propeller de-icer 101. Propellers - Hamilton Standard 3 blade metal constant speed hydromatic full feathering hubs to 6243A-6 inclusive. 14'9-3/8" maximum, 14'5-5/8" minimum. For interchangeable blade models NOTE 6 of Propeller Spec. No. 603. pitch setting 10 degrees at propeller Sta. 72. (See NOTE 8) (276) 203. Propellers (for Model 314 only) Hamilton Standard 3-blade constant speed hydromatic full-feathering hubs 23E50, blades 6159A-0 to 6159A-3 inclusive. Diameter 14'3/8" maximum, 13'8-3/4" minimum. For interchangeable blade models see NOTE 6 of Propeller Spec. No. 603- (See NOTE 9) 1819 1bs- (276) Engines and Engine Accessories - Fuel and Oil System 102. Fuel dump valve installation per Drawing No. 15-5147 De-lcer ryuipment: 201. ne-icer installation (See NOTE 3) Wing and control surfaces - Goodrich Model C-140 Boots and attachments, pump, controls, valves, brackets (removable) (2) Miscellaneous brackets, fittings, valves, controls, wirings, switches, and conduit (tixed nsolage, and empennage A 15. (370) (3) Wing, lines (fixed) 199 1bs. (501) B- (1) Propeller (removable) 4 slinger rings (Hamilton Standard 52903) 14 1bs. (282) (2) 2 motor driven pumps (Eclipse M34541'ice protection plates 2-20 gallon tanks 38 1bs. (444 (3) 2 bu11 19 1bs. 1267 NOTE A. Each aircraft manufactured subsequent to 6/?1/44, must, prior to original certification, satisfactorily pass: (a) An inspection for workmanship, materials and conformity during construction. (b) A final inspection of the completed aircraft. (c) Check of flight characteristics. Weight and balance report including list of equipment included in certificated weight empty, and loading instructions when necessary, must be submitted for each aircraft with original inspector's report and each subsequent report covering change in effective If provisions other than Item 102 are made for dumping, the fuel dump valves shall be made positively inoperative. If Item 102 is installed, the aircraft operation record shall incorporate one of the following statements, Non-Air Carrier. "Fuel shall not be dumped except in accordance the provision of CAR 60.900." 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 Fuel shall not be dumped except in accordance with CAR 61.7811 and then only if the pilot deems it safer than landing at a weight in excess of maximum landing With authorized weight not in excess of maximum landing weight - "Fuel shall not be dumped except in accordance NOTE 3. Maximum landing or take-off weight may be increased 480 1bs. when complete de-icer is installed. NOTE 4. Allowable baggage Maximum loading apacit 1bs./sg. ft. Hold #1 (nose of hull) 826 62 Holds #2-P and 2-S (hull center section forward) 960 each 84 Holds #3-P and 3-S (hull center section aft) 1280 each 84 Holds #4-P and 4-5 (wing stubs) 1360 each 27 *Includes crew in berths when occupied and 226 lbs. of boat gear in forward end. NOTE 5. Airworthiness certiticate must be accompanied by an approved copy of the manufacturer's operating manual. NOTE 6. The following placards must le displayed in full view of the pilot: (a) Taxi in accordance with instructions in the approved operating manual." ®IMPORTANT To look rudders and elevator: Elevators must be fully down. (2) Rudders must be moved to neutral. (3) Raise look lever and engage socket. It should be noted that the forward C.G. limits shown for "landing" determine the most forward C.G. locations at which the airplane complies with the landing requirements of the Civil Air Regulations. "flight" limits may be used only under special conditions since the airplane must never be flown with its load arranged in such a manner that the approved forward "landing" limit cannot be realized readily by shifting passengers and available crew members in case an emergency In order to utilize the wide "flight" c.G. limits, it is necessary that the loading instruction referred to in NOTE 1 be prepared in such a manner that they satisfactorily provide for the following restrictions: Whenever the airplane C.G. is located ahead of the approved forward landing limit, a sufficient number of passengers and/or crew members must be available to be shifted in such a manner as a move the C.G. within the approved "landing" limits. At no time may the airplane C.G. be permitted to move outside the "flight" limits. NOTE 8. When Item 101 is installed, continuous operation between 1750 and 2050 engine rpm should be avoided. NOTE 9- When Item 203 is installed (Model 314), the placard "Take-off" limit must be reduced to 42 in. Hg.. 2300 rpm (1500 bp).