TCDS TC 616

MODEIS: Lockheed 12-A (Army UC-40, UC-40A; Navy JO-1, J0-2), 8 PCIM I.C. NUMBER: 616 (Approved 10/14/36) Engines Pratt & Whitney Wasp Jr. SB with one 4-1/2M ard one 9N damper (See also Item 89) Fuel 80 minimum octane aviation gasoline (87 minimum Engine limits Maximum, except takeoff 34.5 in. Hg., 2200 rpm (400 hp) (Straight line manitold pressure variation with altitude to 5000 ft.) 33.5 in. Hg.. 2200 rpm Takeoff (one minute) 36.5 in. Hg.. 2300 rpm (450 hp) Airspeed limits Level flight or climb - 240 mph True Ind. Glide or dive - 275 mph True Flaps extended- 125 mph True Ind. Propellers Controllable metal (Hamilton Standard hubs 2D30, 6095A-12 inclusive. 9'1/8" maximum, 8'6-1/2l minimum) (Low pitch setting 16 degrees.) (See Items 24, 65, 88 and 90) Usable ceiling (May be realized under the following conditions) Ceiling Weight Prop (1bs.) Pressure Octane Item Full throttle 98 Standard pitch 7700 8650 2200 Full throttle 98 80 or 87 Fully 90 feathered Additional conditions (1) Standard air (Z) Either engine inoperative (3) Carburetor air intake on "cold air" (4) Wing de-icers installed but not operating C.G. range (-16.3) to (+1.6) Datum Spar center line on under side of wing Leveling means Base line of main cabin windows weight limits Landing 8650 1bs. (See NOTES 3 and 4) Takeoff 9200 lbs. (Item 79 required) (See NOTES 3 and 4) No. seats 8 (See Item 19 for location of passenger seats), Crew 2 (-43) Faggage 450 lts. maximum (nose compartment, 200 1bs. (-101; aft of cabin compartment 250 1bs. (+111) Fuel capacity 200 gallons (4 tanks in wing; 2 forward of spar 49 gallons each (-15) : 2 aft of spar at 51 gallons each (+17)) (See NOTES 2 and oil capacity 14 gallons (2 tanks at 7 gallons each) (-37) Control surface movements Not available Serial Nos. eligible 1201 and up per NOTE A Required equipment 4, 15. 16, 17, 18 and i 8, 9. 10. 11. 12, 13. Specifications Pertinent to All Models: Certification basis Type Certificate No. 616 (Aero. Bulletin 7A requirements) Production basis None (See NOTE A) Export eligibility Eligible for export, at Maximum landing weight, as follows subject to provisions of MOP 2-4: (a) Canada - Landplane - eligible. - Skiplane - not eligible. (b) All other countries except New Zealand. EQUIPMENT: A plus (+) or minus (-) sign preceding the weight of an optional iten indicates the net weight change when that item is installed. Propeller and Propeller Accessories (Except De-Icing Equipment) constant speed propeller control pitch setting 11 degrees OI 11-1/2 degrees for 6095A-8 and 9 degrees for 6101A-12 blades) 20 1ks. -64 Propeller spinners 16 Its. -84 Propeller blades 6101A-12 replacing standard blades 6095A-8 *12 1bs. (-84) Propeller spinners (heavier type) 22 1ks. (-84) Propel here ade models (for interchangeable to change in weight, low piech beting replacing 6095A-6, or pertinent notations. Propellers - full feathering hydro- matic - Hamilton Standard hubs 22D30, blades 6181A-6 or 6181A-7. pitch etting 10 degrees at "2 in. pitch setting propeller station 392 lbs. (-84) Engine and Engine Accessories - Fuel and Oil System Two engine ring cowls 75 1bs. (-63) Two exhaust collector rings 99 1bs. (-44) Two oil radiators (UAP 6") 28 1bs. (-41) 64 lbs. (-48) Residual fuel and oil in system 18 1bs. (-25) Old type dump valves and controls (Lockheed Drawings 68002, 68004) Exhaust gas analyzer (Cambridge) 12 1bs. (-45) Pesco vacuum pumps (two) 10 1bs. (-59) Eclipse vacuum pumps (two) 14 1bs. (-59) Fuel capacity increased 49 gallons fuselage tank Lockheed No. 69300) 40 lbs. (-16) oil capacity 19 gallons (9-1/2 gallon tan nicene, replacing standard, in gallon tanks) No change in weight 46. Oil immersion heaters 6 lbs. (-37) Fuel capacity increased 98 gallons 80 1bs. (-16) Two oil radiators (UAP 7") 40 lbs. (-41) Automatic rocker oiling (SB engines only) 11 lbs. (-64) Arens control to rocket oiling 2 1bs. (-64) 79. Closeable dump valves, controls and discharge chutes (See NOTE 4) +14 1bs. (+8) Wing fuel tank installation (Lockheed Drawing No. 68007) (four tanks in wing; 2 forward of spar at 49 gallons and 2 aft of spar at 50 gallons) 62 1bs. (+0.5) 89- Engines (must have one 4-1/2N and one 9N damper) Use actual weight change (a) Pratt & Whitney Wasp Jr. SB-2 (limits same as for SB) (b) Pratt & Whitney Wasp Jr. SB-3 (limits same as for SB) (c) Pratt & Whitney Wasp Jr. T1B3 Fuel, 87 minimum octane aviation Limits: aximum, except takeoii (Sea level) 34.2 in. Ng., 2300 xEm (400 hp) (Straight line manifold pressure variation with altitude to 5400 ft.) 32.5 in. Hg.. 2300 rpm (400 hp) Takeoff (one minute) 37.5 in. Hg.. 2300 rpm (450 hp) (d) Pratt & Whitney Wasp Jr. (limits same as T1B3) (e) Military R-985-AN-4 (limits same as SB) (£) Military R-985-AN-6 or -AN-6B (limits same as SB) (g) M1litary R-985-AN-12 or -AN-12B (limits same as SB) (h) Military R-985-AN-14B (limits same as SB) (İ) Military R-985-25 (limits same as T1B3) (3) Military R-985-AN-1 or -AN-3 (limits same as T183) (ж) Military R-985-13, -17, -19. -23. -48. (1) military 85-27 it a (limits same as T1B3) Landing Gear and Floats 31 in. streamline wheels (Hayes 3100M) 66 Ibs. (-28) 11. 81 in. streamline tires, General Special 8-ply (wheels must be placarded for these tires, 43 lbs. pressure inflation) 84 lbs. 1-28 12- Shock struts (Aerol SP350L) 95 lbs. (-28) 13- 13-1/4 in. streamline tail wheel and tire 10 Ibs. (+290) 14. Tail wheel shock strut (Aerol 300L) 20 1bs. (+282) 16. Wheel fenders 5 lbs. (-20) 31- Cactus proof tubes (replacing standard tubes) +14 1bs. (-28) 42- 31 in. streamline wheels (Hayes 3100A) 82 lbs. (-28) 43. 11.00-12 wheels (Hayes 1101A or 1102A) 64 1bs. (-28) 44- 11.00-12 tires (Goodrich) 8-ply and plain tubes 86 1bs. (-28) 45- 11.00-12 cactus proof tubes 10 1bs. (-28) 59. Brake controls (dual set-copilot) 4 lbs. (-74) 60- 30x13-6 wheels (Goodyear 6HBM) 62 1bs. (-28) 61- 30x13-6 tires (HD 6-ply) and plain tubes 86 lbs. (-28) 62. 30x13-6 cactus proof tire liners 20 lbs. (-28) 63. Chock strut (Aerol SP 3501-13) -6 lbs. (-28) 64- Tail wheel lock 3 lbs. (-50) 70. Cactus proof tail wheel tire liner 3 lbs. (+290) 76- Revised brake control system in accordance with data submitted No change in weight 6/18 and 6/21/37. Electrical Equipment Two retractable landing lights in wing (one warning light in nose) (-133) 8 1ks. (-19) Battery (Exide 6-FHM-13-1) 75 1bs. (-81) Generator, 25 amp. 21 1bs. (-54) 33. Generator, 50 amp. 36 1bs. (-54) 34. (a) Antenna reel (H & K) 10 1bs. (+290) Antenna 5 1bs. (+20) 36. Battery (Prestolite R-1213-G) 91 1bs. (-81) Interior Equirment Two flares and brakets (3 minute) 50 1ks. (-88) fire extinguisher system (Alfite, 5 1b. bottle under copilot's seat, or at rear of nose baggage compartment) 23 lrs. (-43) 15. Instruments and panel 50 lts. (-72) 18. Heater and ventilator 32 1bs. (+35) 19- Six standard passenger seats at 20 ibs. each (-11, -11, +31, +31, +64, +64) See Items 21 and 77) 21. Standard passenger chair removed; deduct 20 1bs. each (Roman numerals in paren- thesis signify number of seats removed (See Items 19 and 77) 23. cockpit partition and door assembly 25 1bs. (-30) 28. couch - three-place 81 1bs. (+42) 35. Automatic pilot (Sperry) 100 1bs. (-64) 77. Standard model 14 chair installed (Add 53 1bs. each) (Roman numerals in parenthesis signify number of seats installed) (See Items 19 and 21) 80- Heavy type nose baggage compartment flooring +10 1bs. (-101) Zeiss special camera installation 10 1bs. (+57) Two flares and brackets (3 minute) 50 lbs. (+165) De-Icing Equipment De-icing equipment (fixed portion 30 Ibs. - removable 65 lbs.) (See NOTE 3) 95 lbs. (-13) Miscellaneous (not listed above) Abrasion strips (tail surfaces I.E.) (+250) Abrasion strips (on lower Ibs. (+270) 81. Revised empennage assembly with dynamically balanced rudders (Lockheed Drawing No. 63012) +55 1bs. (+273) 100 percent static balance (Lockheed Drawing No. 62002G) +23 1bs. (+26) Fuselage revised tail section, .032 replacing .025 skin (Lockheed Drawing No. 60060E) +6 lbs. (+187) NOTE A• Each aircraft manufactured after January 26, 1943 must, prior to original certification, satisfactorily pass: (a) An inspection for workmanship, materials and conformity during construction. 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, be submitted for each aircraft with original inspector's report and each subsequent report covering changes in equipment. NOTE 2. The following placard must be conspicuously posted at the righ rear main fuel tank (wing) filler cap: •FILL WITH 87 OCTANE FUEL ONLY. when Item 38 is installed, in lieu of above, a placard must be conspicuously posted at the fuselage fuel tank filler cap reading: The following placard must be placed at the fuel selector valve: "USE REAR WING MAIN TANKS (OR FUSELAGE TANK) FOR TAKE-OFF AND LANDING.i when 87 octane fuel is used in all tanks, the above placards must be deleted, the aircraft "Operation Limits" placard should bear the notation: "87 OCTANE FUEL ONLY USED IN ALL TANKS." NOTE 3. Maximum landing and takeoff weights may be increased 52 lbs. when complete de-icer is installed. If provisions other than Item 79 are made for dumping, the fuel shall be made positively inoperative. If Item 79 is installed and the aircraft is used for air carrier operation, the aircraft operation record shall incorporate the following statements: (T) with authorized weight in excess of landing weight - 'Landing shall not be made at a weight in excess of maximum landing weight except in accordance with CAR 61.7811. Fuel shall not be dumpe xcept in accordance with CAR 61.7811 and then only if the pilo deems it safer than landing at a weight in excess of maximum landing weight." (2) With authorized weight not in excess of maximum landing weight "Fuel shall not be dumped except in accordance with CAR 61.7811." NOTE 5. Placard lavatory door as follows: "This room not to be occupied during takeoff and landing."