# TCDS ATC 657: Lockheed Aircraft Corporation - Type: Type certificate data sheet - Status: Current - Holder: Lockheed Aircraft Corporation - Revision: 0 - Product: Aircraft, Small/Large Airplane - Registered aircraft: 1, by the registry models matched to it (OpenAirDocs) - Data sheet PDF: https://openairdocs.org/files/sha256/8c/b9/8cb9f204dd4687b2515ad810df53ad47fe2f4e9f9b8b52892bba9d11d2488e33 - FAA DRS: https://drs.faa.gov/browse/excelExternalWindow/9CEDD6C09D8217A085256738006D8A28.0001 - Page: https://openairdocs.org/tcds/ATC%20657 ## Models (2) As the data sheet lists them. - 14-H2 - 14-H ## What the data sheet says This is OCR from the scanned FAA data sheet. OCR can misread letters and numbers. ```text MODELS: Iockheed 14-H, 14-H2, 14 PCLM T.C. NUMBER: ATC 657 I - Specifications Pertinent to All Models: Propellers 2 controllable metal, constant speed (Hamilton Standard hubs 3150, blades 6111-12; low pitch setting 18 degrees) 695 1bs. (-110) Placard speeds Level flight or climb - 240 mph True Ind. Glide or dive - 284 mph True Ind. Flaps extended - 115 mph True Ind. Placard ceiling (a) 9350 ft. (usable) in standard air (See Item 243 and indicated airspeed of 113 mch at 15650 1bs. NOTE 10) with either engine inoperative and the inoper- ative propeller idling in high pitch. ft. (usable) in standard air at an indicated airspeed of 118 mch at 15650 1bs. with either engine inoperative and the inoperative propeller fully feathered. Fuel capacity 644 gallons (4 tanks in center section wing; 2 front tanks at 150 gallons each (-20.5) and 2 rear tanks not including fuel system at 172 gallons each oil capacity 44 gallons (1 tank in each nacelle at 22 gallons each (-52.5) not including capacity of oil No. passengers 11 (See Item 114) (Standard crew 2, pilots at (See Item 210 Baggage Maximum capacity of compartments (See NOTES 1 and 9) No. 1 - Nose compartment 1500 1bs. No. 2 - Forward belly compartment 800 lbs. (-68.5) 3 - Mid. belly compartment 400 1bs. (-20.5) 4 - Rear celly compartment 700 Ibs. (+30.5) Ballast compartment 350 1bs. (+230.5) C.G. limits (-0.3) and (+6.6) level for weighing floor or window line. MAC is 115.84 in. (L.E. MAC is 32.75 in forward of spar center line. Certification basis Approved Type Certificate No. 657 Serial Nos. 1416 and 1503 only eligible. Approval expired eligible under the terms of this Army surplus Hudson type are specification. EQUIPMENT: (Datum is spar center line on under side of wing) (* Means net increase) Class I: Two engine ring cowls (Lockheed 54022) (-89) Two exhaust collector rings (-60) Two oil radiators (UAP 9) (-41) Two vacuum pumps (Pesco 207, Type B-3) (-76) Two starters (Eclipse E-160) (-68) Generator (Eclipse E-5) (-75) (-47) Pressure fire extinguisher (Lux type 36-1) (-58) (+977) (-28.5) (-28.5) 15.00-16 tires (Goodyear) 8-ply HD (-28.5) 15.00-16 tire tubes, plain (-28.5) 18 in. streamline tail wheel and 6-ply tire (Goodyear) (+327) Tail wheel shock strut (Aerol B250L) (+314) Eleven standard passenger chairs 53 lbs. 006.51 homan humerals in parenthesis +65.5, +96.5, following item number signify number of seats removed) (See NOTE 9) 115. Ventilating system 57 1bs. (+57) 116- Instruments and panel (Refer to West Coast Branch for itemized list dated 3/1/38) 56 lbs. (-83 117. Heating system (Lockheed 57005) 61 1bs. 1+57 118- Constant speed propeller control (Type 1A1) 20 1ks. (-60) 119- Automatic mixture control (NAY-9C, G or H-23) 40 1bs. (-70) Class II: 200. Miscellaneous items as noted in approved weight and balance report. 201. Two retracting landing lights (in wing) 11 1bs. 202. Two flares and brackets (International) 50 lbs. 203. Two retractable oil radiator scoops (includes thermostatic control) 9 1bs. 204. (a) Lavatory equipment including 3 62 lbs. gallons water (b) 1/2 gallon water, bottle, and brackets 205. (a) Two flashlights in cockpit (b) Extra cabin door lock 206. (a) Automatic pilot lines and brackets and (b) Automatic pilot mechanism 207. (a) 2-1/2 gallon propeller anti-icer fluid tank and lines (P) Propeller anti-icer pump (c) Spinners and slinger rings (a) Propeller anti-icer fluid 13 gallons) (e) Slinger rings (for hydromatic propeller) 208. (a) Extra, two, "pint" fire extinguishers (Pyrene) (b0) Extra "quart" fire extinguisher (Pyrene) 209. Landing gear strut recess flaps 210. Folding type stewardess chair (See NOTE 2a) 211. 15.00-16 cactus proof tire liners 212. 18 in. cactus proof tail wheel tire liner 213. Plexiglass fuselage nose replacing standard metal nose * 214. Ten standard passenger chairs 53 1bs each (replacing Item 114) 1-16.50 - 16.5. *104.5. *2143.5. +143.51 (oman numerals +65.5, +104.5, in parenthesis following the iten lumber signify number of seats removed.) 215. Dump valve installation (Lockheed Drawings 58019 and 58077) (See NOTE 7) 216. (a) Radio compass (RCA AVR8E) (b) Hand reel and antenna (trailing) (c) Radio receivers (RA2) (2) (RA4) (3) (WE17A) (a) Radio transmitters (TA2) (e) Radio power units (JBX-3) 49 (‡) Wiring, etc., and compass loop (g) Dipole antenna (h) Vee antenna (1) Two spare trailing type antenna (5) Radio receivers (1) (RAZ) (2) (RA4) 15 (3) (RA6) 217. (a) Cabin carpet (Beluxee) (b) neavy type) 57 (C) Leather lavatory bench covering (d) Leather upholstery on interior cabin tulkheads (e) Upholstery (Laidlow replacing linen) (İ) Four blankets in cabin parcel nets 218. (a) Auxiliary instruments and panel (refer to West Coast Branch for 10 1bs. (D) 5 1bs. 219- 5 lbs.* 220- (a) 3 lbs. 221. (a) 44 1bs. (b) 11 1bs. (C) 11 1bs. 222- TOO1 17 1bs. 223. 12 1bs. 224. 29 lbs. 225. (Lockheed 53525 103 1bs. 226- (a) 13 1bs. (b) 1 1b. (C) 18 1bs. 227. (Lockheed 53506B) 14 1bs.* 228. installation, 145 1bs.* 229. (a) 39 1bs. (b) 3 lbs. 230. 5 lbs.* 231. fuselage station 12 1bs. 232. 7 lbs.* 233. (Drawing 42402) 2 1bs. 234- 55560) 10 1bs. 235. Ibs - 1041 236- Auxiliary battery 1 1b8 (-32) 237. drag 55053D and 55008C: bulkhead fitting 56 1bs. (ž0) 238. 20 1bs. 239- maximum Drawing 4 lbs.* (+6705) 240. NO. 14-38) 6 1bs. (-104) 241- 21 1bs. (-30-5) 242- Drawing 55380) 38 lbs.* (-88) 243. 25 lbs. (-7) (a) De-icer installation (wing and tail fixed portion) (See NOTE 8) (0) 302. Emergency wheel lowering device (independent oildraulic system manually operated) (0) 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. Stewardess' seat not to be occupied by passengers. Placard accordingly. Placard lavatory door as follows: "This room not to be occupied during take-off and landing.m Eligible for export, at standard weight, as follows subject to inspection for equipment specified in Chapter XII of Inspection Handbool - Skiplane - not eligible. However, structure complies with Canadian ski gear requirements provided that the geometry of the ski gear is in accordance with Lockheed Report No. 954. (b) All other countries. NOTE (In lieu of posting such placards, and subject to the approval of the chief, The following placards must be installed in locations noted: Air Carrier inspection Section, definite instructions must be issued by the operator to assure compliance therewith.) At fuel selector valve: "All fuel (to within 2 or 3 gallone) shall be used from each tank in the order listed below before using fuel from succeeding tank: win filling fuel tanks, care must be observed Right Front, Left Rear, Left Front, Right Rear." to ascertain that tanks are full in the following order: rear, left front, left rear, right front." Tab ranges are limited as follows: Rudder tab, trim travel move to ab only) up 26 degrees; down 24 degrees 30 feet as measured from ¿ eutral position 5 degrees down from chord plane of aileron. Serv travel down 17 degrees. servo travel up 1 degres. NOt from al. in the 00 pron fee must tent tobeen 239 is installed. 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 airworthi- ness certificate shall incorporate one of the following statements, as the case may be: on-Airline Carrier. Fuel shall not be dumped except ir accordance 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 excese With authorized weight not in excess of standard - Fuel shall not be dumped except in accordance with CAR 61.7811." NOTE 8. Standard (and provisional) weight may be increased 93 1bs. when complete de-icer is installed. when airplanes of the subject models are operated as cargo carriers, If no passenger seats are installed, the cabin may be divided into baggage compartments having a combined maximum total capacity of 2700 lbs. provided each compartment is conspicuously placarded as follows: Load cargo so that its center of gravity rests directly over the gravity of the compartment." "The maximum permissible load density is 145 lbs. per linear foot When Goodrich propeller deicing strips are installed (the strips must not extend beyond the outside diameter of the engine cowl) the placard ceilings are reduced 1000 feet below the usable ceilings shown. II - Model 14-H, Designation 14 PCIM Engines 2 Pratt & Whitney Hornets S1EG Placard limits Fuel (See NOTE 4) aximum, except takeoff 87 minimum octane Below 1000 ft. 36.0 in. Hg.. 2275 rpm (800 hp) Below 3000 ft. 35.5 in. Hg., 2275 rpm (800 hp) Above 3000 ft. 35.0 in. Hg.. 2275 rpm (800 hp) Takeoff (one minute) 87 minimum octane 40.5 in. Hg.. 2500 rpm (850 hp) Weights Empty - Use actual (approximately 10270 1bs. (-4.65) as 13 PCLM with Class I items only) Standard - 15650 1bs. (See NOTE 7) Standard (as cargo carrier airplane) - 17500 lbs. (See NOTE 9) Provisional - 17500 1bs. (See NOTE 7) III - Model 14-H2, Designation 14 PCIM (Same as Model 14-H except engines 12 lbs.* (-89) when S1E2-G engines are installed and 36 lbs.* (-88) when S1E3-G engines are installed.) Engines 2 Pratt & Whitney Hornets S1E2-G or S1E3-G Placard limits Fuel (See NOTE 4) Maximum, except takeoff 87 minimum octane Sea level 36.5 in. Hg.. 2250 rpm (800 hp) Straight line manifold pressure variation with telenge to 5500 ft. 34.5 in. #g.. 2250 rpm Takeoff (one minute) 87 minimum octane Sea level 41.0 in.Hg.. 2300 Ipm (900 hp) or 39.5 in.Hg., 2500 rpm (885 hp) Weights With S1E2-G engines Standard (as cargo carrier airplane) - 17500 1bs. Provisional - 17500 1bs. (See NOTE 7) 892 50 - 15630 50 10 02 4 1 0 (1)) Standard (as cargo carrier airplane) - 17500 lbs. (See NOTE 9) 17500 1bs. (See NOTE 7) ``` ## ADs (3, in force first) - [AD 99-19-08](https://openairdocs.org/ad/99-19-08): AFM - Deicing · Lockheed 14-H, 14-H2, 14-N and 3 more. Effective Dec 27, 1999 - [AD 98-04-32](https://openairdocs.org/ad/98-04-32): AFM - Limitations Section - Icing · Lockheed 14-H, 14-H2, 14-N and 3 more. Effective Mar 25, 1998 - [AD 93-14-12](https://openairdocs.org/ad/93-14-12): Crewmember Protective Breathing Equipment Units · Airbus A300 B2-1A, A300 B2-1C, A300 B2-203 and 201 more. Effective Sep 2, 1993 ## Registered aircraft by registry model (OpenAirDocs) - [Lockheed 14-H](https://openairdocs.org/model/lockheed-14-h): 1 aircraft (registry code 5261502) - [Lockheed 14-H2](https://openairdocs.org/model/lockheed-14-h2): 0 aircraft (registry code 5261504) ## STCs approved under this data sheet (2) - [STC SA04652CH](https://openairdocs.org/stc/SA04652CH): To allow use of 100R grade aviation fuel meeting Swift Fuel, LLC specification. Swift Fuels LLC - [STC SA01282NY](https://openairdocs.org/stc/SA01282NY): Installation of Airwolf remote mounted engine oil filter kit AFC-K015 on aircraft powered by Pratt & Whitney radial reciprocating engine Series R-985, R-1340 and R-1830.. Airwolf Filter Corporation --- OpenAirDocs.org is an independent research project of [Contrail Labs](https://contraillabs.com/). It is not affiliated with the FAA or the NTSB. Source documents are U.S. government works in the public domain.