TCDS ATC 683

MODELS: Lockheed 14-11, 14-N2, 14-N3, 14 PCIM ISL MOMBER: ATC 683 I - Specifications Pertinent to All Models Placard speeds level flight or climb - 240 mph True Ind. Glide or dive - 284 mph True Ind. Flaps extended - 115 mph True Ind. Fuel capacity 544 gallons (4 tanks in center section wings; 2 front tanks at 150 gallons each (-20.5 and 2 rear tanks not including fuel system at 172 gallons each (+22.5) (See NOTE 4) 0il capacity 44 gallons (1 tank in each nacelle at 22 gallons each (-52.5) not including capacity of oil No. passengers 11 (see Item 119 for location) (Standard crew 2, pilots at (-52.5) (See Item 222) Baggage Maximum capacity of compartments: (See NOTE 1) No. 1 - Nose compartment 1500 1bs. No. 2 - Forward belly compartment 800 1bs. No. 3 - Mid belly compartment 400 lts. (-20.5) 4 - Rear belly compartment 700 lbs. (+30.5] Ballast compartment 350 1bs. C.G. limits (-0.3) and (+6.6) Level for weighing on main cabin floor or window line. MAC is 115.84 in. MAC is 32.75 in. forward of spar center line) Certification basis Approved Type Certificate No. 683 Serial Nos. 1416 and 1503 only eligible. Approval expired Wigible under the terms of thie space Army surplus Hudson type are not EQUIPMENT: (Datum 18 spar center line on under side of wing) (* Means net increase) class 1. 101. Two engine ring cowls (Lockheed Drawing 54022-4) 112 1bs. (-89) 10 117 1bs. 10: 50 1ks. 104- 10 1bs. 105. (exhaust gas) 12 1bs. 106. 60 lbs. 107. control 20 lbs. 108. Generator 36 1bs. 109- 75 1bs. 110. (a) (Lux type 25 lbs. (b) 8 lbs. 111. 123 1bs. 112. (a) duty tires 171 lbs. (b) 29 1bs. 113. 277 1bs. 114. 17 1bs. 115. 27 lbs. 116. 61 1bs. 117- 57 1bs. 118. 3/1/38) 56 1bs. 119- 53 1bs. each Class II: 200- 201. in wing 11 Ibs. 202. 122 1bs. 203. a1) 50 lbs. 204. 62 lbs. 205. 3 lbs. 206. 80 lbs. 207. and ines 6 lbs. nti -1 cer pump 5 1bs. sli nger rings 24 1bs. nd anti-icer fluid 24 1bs. (Eclipse E-5) 36 1bs. xide 6-FHM-13) 75 lbs. fir extinguishers 10 1bs. tin guisher hand type 8 1bs. 16 1bs. re ers 25 1bs.* wheel 5 1bs. strut: • 1bs.* (dural 5 1bs.* cordan ICE 58019 and 18 1bs.* 1tg 40 1bs. RA-2A 23 1bs. 43 1hs. fin der 10 1bs. share control 19 1bs. 6 1bs. unit, wiring, etc. 137 1bs. ver RA-4) 15 1bs. unit. wiring. etc. 114 1bs. in stallat ion (with t) 16 lbs. 217. (Servi ce) 36 1bs. (D) Cabin carpet (special heavy type, replacing standard) 19 lbs.* (+65 (0) Leather lavatory bench covering 5 1bs. (+232) (d) Cabin upholstery (Laidlow replacing linen) 20 1bs.* (+50) (e) Cabin carpet (shorter than service) 28 1bs. (+55) (£) cabin mat, rubber 17 Its. (+166) 218. (a) Extra airspeed installation 4 lhs. (-123) (b) Special instruments replacing some of standard instruments West Coast Branch for itemized list dated 3/18/38) Net decrease 3 lts. 219.(a) Two passenger divan (Lockheed Drawing 50383) 104 1bs. (+29.5) (b) Chart table 46 1bs. (+29.5) (c) Card table and clamps 13 lbs. (+172) (a) Blue denim chair covers 6 1bs. (+65) (e) Three-passenger divan (Lockheed 59 303) (+17.5, +40-5, +6305) 93 1bs. (£) c1 othes bench 2 lbs. (g) Map case (Lockheed 59293) 33 lbs. (h) Oxy gen supply cabinet Lockheed 59320 11 1bs. 220- (a) Two passenger foot stools (Drawing 59315) 19 1bs. (b) Passenger loading step 4 1bs. (c) Passenger interphone 2 1bs. (a) Passenger oxygen installation Lockheed 58328) 5 lbs. (e) Passenger oxygen installation (Lockheed 58329) 64 1bs. 221. (a) Deicer boot and removable equipment (wing) (See NOTE 8) 44 1bs. (b) Deicer boot and removable equipment (stabilizer) (See NOTE 8) 11 Ibs. (C) Deicer boot and removable equipment (fin) (See NOTE 8) 11 1bs. 222. Folding type stewardess chair (See NOTE za) 16 1bs. 223. Plexiglass nose replacing metal nose 5 1k8.* 224- Addition of bronze and steel plates to Goodyear brake assembly 7 1bs.* 225- Bulkhead reinforcement, fuselage Station 456 (Lockheed Drawing 50124E) 12 1bs. 226. Brake fluid gravity tank and fluid (Drawing 42402) 2 lbs. 227. Fuselage structural changes to accommodate camera (lockheed Drawing 55560) 10 lbs. 228. Auxiliary battery 11 1bs. 229. Structural increase (consisting of changes in shock strut, side strut an d ara 55008C: also tail bulkhead fitting strut per Drawings 55007D, 55053D 50460A, stringer 19A and 20A extended per Drawing 50050G, windshield revisions per Drawing 50565A and 50801, window frame gussets per Drawing 50050G, new emergency exit per Drawing 50063, and miscellaneous center section and wing increases per Drawing 51000F) 56 1DS. 230- Zinc chromate primer (Interior) 20 Ibs. 231. operating Drawing 51851) 4 lbs.* (+6705) 232. W.A.C. dynamic suspension engine mount Stand Make Drawing 2510.1 used in conjunction with Hamilton blades 6111-12 11 1bs.* (-77) 233. Fuselage reinforcements in No. baggage compartment (lockheed Service Bulletin No. 14-38) 6 lbs. (-104) 234. Radio operator's seat installation (Lockheed Drawing 55450) 21 1bs. (-30-5) 235. Toe brake installation (Lockheed Drawing 55380) 38 1bs.* (-88) 236- Fixed wing-slots installation (All placard ceilings reduced 130 ft. when this item is installed) 25 1bs. (-7) Hamilton Standard Hydromatic propeller installation (replacing controllable constant speed propeller) hubs 23E50, blades 6139A-12, low pitch setting 22 degrees at propeller station 42 (in accordance with Lockheed Drawing 54270 and Hamilton Standard wiring diagram No. SK 3676) (For Model 14-N) 141 Ibs.* (-81) Class III: (a) Deicer installation (wing and tail) fixed portion (See NOTE 8) 25 1bs. (0) Emergency wheel lowering device (independent oil-draulic system, manually operated) 8 lbs. (0) NOTE 1. 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 equipment. NOTE 2. Stewardess' seat limited to 130 lbs., not to be occupied by passengers. Placard accordingly. (b) Placard lavatory door as follows: "This room not to be occupied during take-off and landing. NOTE 3. Eligible for export, at standard weight, as follows subject to inspection for equipment specified in Chapter XII of Inspection Handbook (7/19/39): (a) - landplane - Skiplane - not eligible. However, structure complies with the ski gear (b) All other countries except Australia. The following placards must be installed in locations noted: (In lieu of posting such placards, and subject to the approval Chief, Air Carrier Inspection Section, definite instructions must be issued by the operator to assure compliance therewith.) At the fuel tank selector valve: "All fuel (to within 2 or 3 shall be used from each tank in the order listed below before using fuel from succeeding tank: Right Front, Left Rear, Left Front, Right Rear.' At fuel tank filler caps: "In filling fuel tank, care must be observed to ascertain that tanks are full in the following order: Right Rear, left Front, Left Rear, Right Front." Tab ranges are limited as follows: to Right 6 degrees 10 feet. Trim Travel Move to Right 25 degrees. Servo Travel Move Rudder Tab, trim Travel Move to left 25 degrees. Servo Travel Move to Leit 6 degrees 5 feet. Elevator Tab, Trim Travel Up 25 degrees. Servo Travel Down 11 degrees Elevator Tab, Trim Travel Down 25 degrees. Servo Travel Up 5 degrees Aileron, Trim Travel (I.H. tab only) Up 26 degrees, Down 24 degrees As measured from a neutral position 5 degrees down from chord plane Servo Travel Down 17 degrees. Servo Travel Up 1 degree. Relief valve in hydraulic flap operating system must be set to unless Item Number 231per square inch to 1000 1bs. per square inch, from 850 1bs. is installed. If provisions other than Item 215 are made for dumping, the fuel dump valves shall be made positively inoperative. If Item 215 (which complies with EI-11c) is installed, the air- worthiness certificate shall incorporate one of the following statements, as the case may be: Non-Airline Carrier. Fuel shall not be dumped except 1 ccordance with the provisions of CAR 60.900. With Authorized weight in excess of standard - "Landing shall not be made at a weight in excess of standard except in accordance with CAR 61.7811. 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 standard." With authorized weight not in excess of standard - 'Fuel shall not be dumped except in accordance wit! CAR 61.7811." NOTE 8. Standard (and provisional) weight may be increased 93 1bs. when complete de-icer is installed. II - Model 14-N, Designation 14 PCIM: Engines 2 Wright Cyclones GR-1820G-105 Placard limits Fuel: 90 minimum octane laximum, except take-off (CFR) it sea level 36.7 in. Hg., 2200 rpm (900 hp (Low impeller ratio) 90 minimum octane At 6000 ft. 35.0 in. Hg.. 2200 rpm (900 hp) (CFR) (low impeller ratio) 95 minimum octane At 11000 ft. 36.0 in. Hg.. 2200 rpm (750 hp) (CFR) (High impeller ratio) 95 minimum octane At 17000 ft. 33.0 in. Hg.. 2200 Ipm (750 hp) (CFR) (High impeller ratio) Takeoff (one minute) : 90 minimum octane 43.0 in. Hg.. 2200 rpm (1100 hp) (CFR) Propellers 2 controllable metal, constant speed (Hamilton Standard hubs 3250 695 1bs. (-107.5) (See blades 6111-12, Placard ceiling usable, in standard air, at 16650 lbs. at an indicated airspeed of 110 mph with either engine inoperative, the inoperative propeller fully feathered and the remaining engine operating at full throttle at 2200 rpm (See items 236 and 237) Weights Standard - 15650 1bs. (See NOTE 7) Provisional - 17500 1bs. (See NOTE 7) III - Model 14-N2 - Designation 14 PCIM (Same as Model 14-N except for change in engines 16 lbs. net decrease) Engines 2 Wright Cyclones GR-18200-102 Placard limits fuel: 90 minimum octane Men teste the variation teen 10 de to (CFR) 6000 ft. 35.0 in. Hg., 2200 rpm (900 hp) 90 minimum octane (CFR) At sea level 43.0 in. Ng., 2200 rpm (1100 hp) Propellers 2 controllable metal, constant speed (Hamilton staring 1 deg 295) 655 les. 6(1107.5, 10w pitch setting 18 degrees) Placard ceiling 10500 ft. usable, in standard air, at 15650 1bs. at an indicated airspeed of 110 mph with either enging open at to netle we 2200 faining (See Item 236) Weights 15650 1bs. (See NOTE 7) Provisional - 17500 1bs. (See NOTE 7) IV - Model 14-N3 - Designation 14 PCIM (Same as Model 14-N except for change in engines 0 lbs.* and propellers 145 1b8.*) Engines 2 Wright Cyclones GR-1820G-105A Placard limits Fuel: 90 minimum octane Maximum, except takeoff: (CFR) At sea level 37.5 in. Hg.. 2300 rpm (900 hp) (Low impeller ratio) At 6700 ft. 35.4 in. Hg.. 2300 rpm (900 hp) (Iow impeller ratio) At 11000 ft. 36 in. Hg.. 2300 Ipm (775 hp) (High impeller ratio) At 17300 ft. 33.6 in. Hg.. 2300 rpm (775 hp) (High impeller ratio) 90 minimum octane Takeoff (one minute) (CFR) 43.5 in. Hg., 2350 rpm (1100 hp) Propellers 2 Constant speed full feathering hydromatic (Lockheed Drawing 54270) hubs 23E50, blades 6139A-12; low pitch setting 840 1bs. (-104) Placard ceiling 160 an aged ver the ped re speller fully feathered and the remaining engine operating at 2300 rpm and 34 in.Hg.. manifold pressure (with supercharger operating in high impeller 10.1 gear ratio Weights mpty - Use actual (approximately 11085 lrs -7.18) as 13 PCLM with Class I items only Standard - 15650 1bs. Provisional - 17500 1bs. (See NOTE 7)