# TCDS TC 584: Lockheed Aircraft Corporation - Type: Type certificate data sheet - Status: Current - Holder: Lockheed Aircraft Corporation - Revision: 0 - Product: Aircraft, Small Airplane - Data sheet PDF: https://openairdocs.org/files/sha256/bc/ba/bcbadfba06b38d8384c0bfb514f6bc5cd71aee7e620ebf245d560388f4681ffd - FAA DRS: https://drs.faa.gov/browse/excelExternalWindow/D2643643D6FD285185256738006D5EC5.0001 - Page: https://openairdocs.org/tcds/TC%20584 ## Models (1) As the data sheet lists them. - Electra 10-B (Navy R-30-1) ## What the data sheet says This is OCR from the scanned FAA data sheet. OCR can misread letters and numbers. ```text MODELS: Lockheed Electra 10-B (Navy R-30-1), 12 PCLM I_C._NUMBER: 584 (Same as Model 10-A except engines and racelles.) Engines 2 Wrights R975E-3 Placard limits Maximum except takeoff 34-1/2 in. Hg.. 2200 rpm (420 hp) Takeoff (one minute) Propellers Hamilton Standaa. 2250s 2030, 0 ad 2D30, blades 6095A-6 maximum, 8'9-3/4м minimum low pitch setting 13 degrees, 152 1bs. each (-90) (See Item 57, Placard speeds Level flight or climb - 210 mph True Ind. Glide or dive - 261 mph True Ind. Flaps extended - 125 mph True Ind. Usable ceiling (May be realized under conditions shown) Ceil (£t.) 1800 700 rpm Additional conditions Standard air Either engine inoperative Carburetor intake on "cold air" leading edge de-icers installed but not Fuel capacity 94 gallons (4 tanks in wings - 2 at 81 gallons each (-21); 2 forward of spar at 16 gallons oil capacity 15 gallons (2 tanks at 7-1/2 gallons each) (-49) No. passengers Baggage Maxime 00 1c. (7.5); cemeartmente in each stub wing 250 1bs. each Maximum weight 10200 1bs. (See NOTES 2 and q) CaG. limits (-9.75) and (+6.1) (Base line of cabin windows level) Spec. basis Type certificate No. 584 (Aero. Bulletin 7A requirements) Serial Numbers 1036 and up eligible per NOTE A EQUIPMENT: (Datum is centerline of the center section wing spar) (* Means net increase) Class 1: 2 Engine ring cowls 61 1bs. (-70) 2 Exhaust collector rings 60 1bs. (-60) 2 Oil radiators (UAP 6") 38 lbs. (-54) 4. 2 Landing lights and 1 warning light 22 1bs. (-10) 5. Plater 20) Position lights 3-minute and brackets 5 lbs.) 50 Ibs. (-85) 3. 2 Starters (Electric) 6q 1b8. (-58) 9. Battery (Exide 6XHS-13-1) (-32) 10- Generator (-61) 11• Pressure fire extinguisher system (-45) 36x15-6 wheels (Goodyear 6HBM) (-23) 13- 35x15-6 6-ply tires and plain tubes (wheels must be placarded for these tires) (-23) 14. Retracting landing gear (Electric worm drive 100-amp fuse (-20) 15- Shock struts (Aerol SP-400E) (-23) 16- Wiectrieat y operated (so fimp. fuse required) (+55) 17. Rudder equipped with trailing edge tab bingle and spring typ 18- levator equipped with (externa] balance weights 12 lbs.; 3 lbs.: trailing edge tabs 2 lbs. Total (+310) 20. Ventilating system (+85) 21- Cabin heaters (+45) 22- Toilet equipment (+180) 23- Container and 1 gallon water (+168' 25. 2 Baggage straps (-98 26. 16x7-3 tail wheel (Goodyear 3 TW) with 4-ply tire (+313) Tail wheel strut (Aerol 30021) 17 lbs. (+300) Instruments (complete with panel) 56 1bs. (-74) class I]: 2 Wheel fenders 8 lbs. (-20) 32- Rudder lock in cockpit 1 1b. (-65) 33- Control wheel lock 2 1bs. (-29) 34. Tail wheel centering lock control 3 lbs. (-70) 35. Abrasion strips on lower fins 2 1bs. (-84) 36. 230 gallon fuel capacity (with 2 extra 18 gallon tanks in wing - rear of spar) 45 1bs. (-17) 37. Deicer installation (fixed portion 56 1bs. removable 55 1bs.) (See NOTE 4) 111 1bs.* (-24) 38. 35x15-6 cactus proof tire liners (two) 22 lbs.* (-23) 39. Landing gear retracting mechanism with 12.5:1 gear ratio and EDC No. 45040 electric motor (100 amp. fuse required) 6 1bs. (-20) 40- Heavy type landing gear yoke 14 1Łs. (-23) 41- Double filler neck and plumbing 15 1bs. (-28) 42. Heavy type engine mount fittings 7 1bs. (-45) 44. Higher seat backs 30 1bs.* (+45) 47. Fuel capacity increased 56 gallons (two 28 gallon wing tanks aft of spar) 62 lbs. (+17) 49. Landing gear (knuckle type) retracting mechanism with 12-1/2 to 1 gear ratio and EDC No. 45040 electric motor amp fuse required) (replaces standard worm and sector type) 275 1bs. (-20) 50- Fuel capacity increased 4 gallons (two 83 gallon main wing tanks replacing standard 81 gallon tanks when Item 49 is installed) 20 1bs.* (-21) 51. Oil tanks (two heavy gauge 7-1/2 gallon capacity replacing standard 7-1/2 gallon tanks. Refer to Drawing No. 45650) 6 Ibs. * (-49) 52. Rudders equipped with fixed trimming tabs (replacing adjustable tats) and and 3 lbs. spring type bungee No change in weight 53- Standard passenger seats removed deduct 20 lts. each (Roman numberal in paren- thesis signify number of seats removed) 54. Fuel capacity increased 51 gallons (1 tank in fuselage, Lockheed No. 42505) 40 1bs.* (-18) 55. Fuel capacity increased 49 gallons (1 tank in fuselage Lockheed No. 43826) 40 lhs.* (+26) 56. Oil capacity 22 gallons (11 gallon tank, replacing Standard 71/2 in each nacelle gallon tanks) 10 1bs.* (-44) 57. Constant speed propeller control unit (low pitch setting 10 degrees) 20 1bs. (-70) 58. Abrasion straps on I.E. tail surfaces 5 1bs. (+264) 59. Couch - 3 place 115 1bs. (+39) 67. Two heavy gage 81 gallon fuel tanks (Lockheed No. 47534) replacing standard 81 gallon tanks 20 1bs.* (-21) 70- Automatic pilot 120 1bs. (-180) 71. Lockheed Model 10 ski and ski gear (Lockheed Drawing 45204) 624 1bs.; ski and gear (Lockheed Drawing 45205) 51 Ibs.; and original portion of landing gear structure retained, 11 Its.; total 686 1bs. Lockheed Drawing 45378 used when skis are installed with knuckle landing gear. 72- Exhaust gas analyzer (Cambridge) 12 1bs. (-40) 73- Cactus proof liner in tail wheel tire 3 1bs. (+313) 74- 15.5 inch streamline tail wheel 12 Ibs. (+313) 76- 2 Landing lights and 1 warning light (in nose) 15 1bs. (-126) 77. New Leaded (hydropressed) type main wing ribs (Lockheed Drawing 40200 K) No weight change 78. Hamilton Standard propeller blades 6167A-6 to 6167A-8 including replacing 6095A Series blades. Diameter 9'1/81 maximum, 8'9-3/4" minimum. No change in weight, low pitch setting or pertinent notations No weight change 79.. Hamilton Standard propellers, hubs 2D30, Llades 6101A-12 to 6101A-14. inclusive. Diameter 9'1/8" maximum, 819-3/4м minimum. Iow pitch setting 10 degrees. 7 1ts. each NOTE A. Each aircraft manufactured after 10/7/41 must, prior to original certification, satisfactorily pass: (a) p, materials and contormity before an All woodwork may be varnished. (b) A final inspection of the completed aircraft. (c) A check of flight characteristics. Weight and balance report including list of equipment instructions when necessary, must be submitted for each aircraft with original inspector's report and each subsequent report covering changes in equipment. NOTE 2. Maximum weight may be increased to 10500 lbs. provided Item 57 (constant speed propeller control is installed). NOTE 3. Eligible for export as follows, subject to provisions of MOP 2-4: Canada - landplane - eligible. - Skiplane - not eligible. However, structure complies with Canadian requirements for ski installation provided Item 71 is installed. (b) All other countries except New Zealand. NOTE 4. aximum weight may be increased an amount equal to .006 x maximur eight when complete de-icer is installed NOTE 5. Fuel dump valves must be made positively inoperative pending satisfactory completion of dump tests. NOTE 6. Placard lavatory door as follows: This room not to be occupied durint take-off and landing." ``` ## ADs (1, in force first) - [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 ELECTRA 10-B](https://openairdocs.org/model/lockheed-electra-10-b): 0 aircraft (registry code 5261310) ## 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 SA01828SE](https://openairdocs.org/stc/SA01828SE): Installation of J.P. Instruments (JPI) EDM-960 Primary Engine Data Management System. J. P. Instruments --- 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.