# TCDS TC 551: Lockheed Aircraft Corporation - Type: Type certificate data sheet - Status: Current - Holder: Lockheed Aircraft Corporation - Revision: 0 - Product: Aircraft, Small Airplane - Registered aircraft: 2, by the registry models matched to it (OpenAirDocs) - Data sheet PDF: https://openairdocs.org/files/sha256/d7/30/d730779e2f6ccad522f0a8b80891572ca03375a941b5a7a9e6a85420817b3486 - FAA DRS: https://drs.faa.gov/browse/excelExternalWindow/EC97F3714C5CD88D85256738006D53A8.0001 - Page: https://openairdocs.org/tcds/TC%20551 ## Models (1) As the data sheet lists them. - Electra 10-A (Army UC-36A; Navy R-20; and XR-20-1) ## What the data sheet says This is OCR from the scanned FAA data sheet. OCR can misread letters and numbers. ```text MODEIS: Lockheed Electra 10-A (Army UC-36A, Navy R-20, XR-20-1), 12 PCIM I-C. NUMBER: 551 Ergines 2 P&W Wasps Jr. SB (See Item 119) Placard limits Maximum, except takeoff (87 minimum octane fuel) 33-1/2 in. Hg., 2200 rpm (400 hp) (80 minimum octane fuel) 33-1/2 in. Hg., 2200 rpm Takeoff (one minute) (87 minimum octane fuel) 36-1/2 in. Hg., 2300 rpm (80 minimum octane fuel) 34-1/2 in. Hg.. 2200 rpm Propellers Hamilton Standard hubs 2D30, blades 5095A-6 to 6095A-8, inclusive. Diameter 9'1/8l maximum, 819-3/4" minimum; low pitch setting 14 degrees] 157 1bs. each (-90) (See NOTE 6 and Items 116 and 118) 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) :E2/0S *NOTE: Best one-engine inoperative; rate or climb at sea level for this condition is 8 ft. per minute. Additional conditions Standard air Either engine inoperative (3) Carburetor intake on "cold air" (4) Leading edge de-icers installed rut not operating Fuel capacity 194 gallons standard (4 tanks in wing - 2 main at 81 gallons each (-21); 2 auxiliary tanks forward of oil capacity 14 gallons (2 tanks at 7 gallons each in each No. passengers Baggage Maximum capacity of compartments; compartment in nose (-97-1/2); compartment in each stub wing Maximum weight (See NOTES 3 and 5) C.G. limits (-10.1) and (+6.1) (Base line of cabin windows level) Spec. basis Type Certificate No. 551 (Aero. Bulletin 7A Serial Numbers 1001 and up eligible per NOTE A EQUIPMENT: (Datum is centerline of the center section wing spar) (* Means net increase) Class I: 2 Engine ring cowls 61 lbs. (-70) 2 Exhaust collector rings 60 lbs. (-60) 2 Oil radiators (UAP 5") 28 1bs. (-54) 2 Landing and 1 warning light (in nose) 15 1bs. (-126) Position lights Flares (two 3 minute and trackets 5 lbs.) 50 1bs. (-851 8- 2 Starters (electric) 64 1bs. (-58) 9- Battery (Exide 6XT-13-12V) 65 1bs. (-32) 10- Generator (50 amp) 36 1bs. (-61) 11. Pressure fire extinguisher system 35 1bs. (-45) 12. 35x15-6 wheels (Goodyear 6HBM) 68 lts. (-23) 13- 35x15-6 (Goodyear) H.D. 6-ply tires and plain tubes (wheels must be placarded for these tires) 109 1bs. (-23) 14- Retracting landing gear, elec. worm drive (100 amp. fuse required) 269 lbs. (-20) 15. Shock struts (Aerol SP-400E) 96 1bs. (-23) 16- Wing split trailing edge flaps elec. operated (60 amp. fuse required) 75 1bs. (+55) 17. Rudder equipped with trailing edge tab (single) and spring type bungee 3 lrs. 18. Elevator equipped with balance weight (external 12 lbs.; auxiliary flap 3 1bs.; tabs ¿ ibs. (+310) total 17 1bs, 20. Ventilating system 20 1bs. (+85) 21. Cabin heaters 40 1bs. (+45) 22. Toilet equipment 15 1bs. (+180) 23. Container and 1 gallon water 12 lbs. (+168) 24- Cabin Deluxe equipment 19 1bs. (+60)) 25. 2 Baggage straps (nose compartment) 4 1bs. (-98) 26- 16x7-3 tail wheel (Goodyear 3TW) with 4-ply tire 12 Its. (+313) 27. Tail wheel strut (Aerol 300ET) 17 1bs. (+300) 28. Instruments with panel 56 1bs. (-74) class II: 2 Wheel fenders (12 1bs. on serials 8 1bs. (-20) Rudder lock in cockpit 1 1b. (-65) Control wheel lock 2 1bs. (-29) Tail wheel centering lock control 3 1bs. (-70) Abrasion strips on lower fins 2 1bs. (+284) Abrasion strips on tail surface (complete) 5 1bs. (+270) 37. De-icer installation (fixed portion 56 lbs., removable 55 1bs.) (See NOTE 5) 111 Its.* (-24) 38- Small type generator (25 amp.) 28 1bs. (-61) 39• 40- 41. 2 cactus proof tire liners Oil radiator (UAP 6") Heavy duty battery (replaces UAP 5") 70 39 1bs. 22 lbs. 1bs. (-32) (-23) (-54) 48- Fuel capacity increase 51 gallons, forward fuselage tank 40 1bs. (-17) 49- Fuel capacity increase 90 gallons, two 45-gallon fuselage tanks 60 1hs. (+33) 50- 28-gallon wing tanks Fuel capacity increase 56 gallons, two 62 1bs. (+17) 51. oil capacity 28 gallons - 14 gallon 52. tank in each nacelle, replacing standard 7 gallon tank Couch (2-place) 30 1bs.* 55 1bs. (+40) (-49) 53. Couch (1-place) and pillows cloth covered 115 1bs. (+40) 54- couth covered (2-place and pillows cloth 115 1bs. (+40) 55. Couch (3-place) and pillows cloth covered 115 Its. (+40) 56. 57. covered Couch (3-place) and pillows leather Arm chair 130 1ks. 26 lts. (+40) (-17) 58. Standard passenger seats removed, deduct 20 1bs. each (Roman numerals in parenthesis signify number of seats removed) 74. 79- 80. Robot pilot installation Light weight sound proofing, deduct Heavier type inner cowling 120 1bs. 30 1bs. 15 1bs. (-65) (-80) (+60) 84- Revised landing gear retracting mechanism with 12.5:1 gear ratio and EDC No. 45040 electric motor (100-amp. fuse required) 6 1bs. (-20) 85. Oil capacity 19 gallons (9.5 gallon tank in each nacelle, replacing standard 7-gallon tank) 4 1bs. (-49) 86. Oil capacity 17 gallons tanks in each nacelle) (two 8.5 gallon 2 lts. (-49) 87- 88. Cactus proof liner in tail wheel tire Pratt & Whitney oil regulator 3 Ibs. 1bs. (+313) (-54) 91. 2 Batteries (Exide 6TS-13-1) and box, 93. 94- 95. 96. 7 lcs. Heavy type landing gear yoke Carburetor induction system Double filler neck and plumbing Heavy type engine mount fittings 81 1bs. 14 1bs. 10 1bs. 15 1DS. 7 1bs. (-28) (-65) (-45) (-32) (-23) 97. Electric system 24-volt wiring jights 3 1bs (knuckle type) retracting 10 lbs. and extra weight landing 13 1bs. (0) 99. Landing gear mechanism with 12.5:1 gear ratio and EDC No. 45040 electric motor (140-amp. fuse required) (replaces standard worm and sector type) 275 1bs. (-20) 100. Rudders equipped with fixed trimming tabs (replacing adjustable tars) and 3 lbs. spring type bungee No weight change 202. Constant speed propeller control installatior 20 1bs. (-64) (a) When installed with 6095A-6 blades, low pitch setting 10 degrees (b) When installed with 6101A-12 blades, low pitch setting 9 102. Exhaust gas analyzer (Cambridge) degrees 12 lbs. (-40) 103. 2 Heavy gage 81 gallon fuel tanks standard 81-gallon fuel tanks (Lockheed No. 45732), replacing 26 Its. * (-21) 104. Oil capacity 16 gallons (8 gallon tank in each nacelle replacing standard 7 gallon tank) No change in weights 105. Lockheed Model 10 ski and ski gear (Iockheed Drawing 45204) 624 1bs.; tail ski and gear (Lockheed Drawing 45205) 51 1bs.; and original portion of landing gear structure retained 11 1bs.: total 686 1bs. Lockheed Drawing 45378 must be used when ski are installed with knuckle landing gear. 106. Landing lights (in wing) 11 1bs. (-10) 107. Oil capacity 23 gallons (11.5 gallon tank in each nacelle) (Lockheed Drawing 45889 or 45906), replacing standard 7 gallon tank) 6 lbs.* (-49) 108- Oil immersion heaters 6 1bs. (-49) 109. Radio compass (RCA, AVR-8) 63 Its. (-46) 111- 15.5 inch streamline tail wheel 12 1bs. (+313) 112- Oil radiator (UAP 7") UAP 5MJ 42 1ks. (-54) 113- Hamilton Standard blades 6101A-12 to 6101A-14 inclusive. Diameter 9'1/8" aximum, 8'9-3/4" minimum, replacing 6095A-6 blades (Item 101 (b) must be installed with this item (See NOTE 6) 5 lks.* (-90) 114. New bladed (hydropressed type main wing ribs) (Drawing 40200K) No weight change 115.. 2 Engine ring cowls (Engel Parts No. 1110: 1112 and 11 4) 1105, 1106, 1108, 1110. 61 lbs. (-70) 116. Hamilton Standard propeller blades 6167A-6 to 6167A-8 inclusive (same diameter limits as 6095A) No weight change 117. 256 gallon fuel capacity installation replacing standard (in accordance with Northwest Airlines Drawing No. 40012-A) 59 Ibs. (+17) 118. 2 Full feathering hydromatic (Hamilton Standard hubs 22D30, blades 6186A-6, 6 18 1A-7, 6183A-12, Or 6185A-13. Diameter 9'3/8" maximum, 8'10" minimum; low pitch setting 10 degrees) (North- west Airlines Drawing 107411) use abtual weight change 88 lbs.* 119. Engines (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 gasoline Limits: махітит, except takeoff (Sea level) 34.2 in. Hg.. 2300 1pm (400 hp) (Straight line manifold pressure variation with altitude to 5400 Takeoff (one minute) 37.5 in. Hg., 2300 rpm (450 hp) (d) Pratt & Whitney Wasp Jr. T1B2 (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) Military 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) (5) Military R-985-AN-1 or -AN-3 (limits same as T1B3) (k) -48, -50, -AN-2, -AN-6 (limits -23, -48, -50, same as SB) (1) Military R-985-27 (limits same as T1B3) 120. Automatic pilot (а) Lear Model I-2B installation in accordance with Lear Drawing 95625A 54 1bs. (+71) (T) Servo Slip Clutch Settings: Aileron 75+5 in. 1bs. Elevator 60+5 in. 1bs. Rudder 60+5 in.lbs. (2) Pilots Operating Instructions, dated 1/31/52 should be attached for Aircraft Form ACA-309. The following placard should be installed in full view of pilot below 300 feet above the terrain in the cruise configuration. 'Do not use autopilot below 300 feet above the terrain in the approach configuration." Minimum altitude for each case does not override any higher minimum operational altitude. Do not override the auto- to increase angle of Do not use autopilot turn control with one engine inoperative." Toe brakes installed in accordance with Purdue Aeronautics Corp., Drawing 60574-41- Each aircraft manufactured after 10/7/41 must, prior to original certification, satisfactorily pass: An inspection for workmanship, materials and conformity before any covering, metal priming or final finish is applied. All woodwork may be varnished. A final inspection of the completed aircraft. A check of flight characteristics. Weight and balance report including list of equipment included ir. certificated weight empty, and loading instructions when necessary, must be submitted for each aircraft with original inspector's report and each subsequent report covering changes in equipment. (a) The following placard must be conspicuously posted at the right outboard wing fuel tank filler cap: "FILL WITH 87 OCTANE FUEL ONLY." The following placard must be placed at the fuel selector valve: "USE RIGHT WING OUTBOARD TANK FUEL FOR TAKE-OFF AND LANDING." when 87 (or 80) octane fuel is used in all tanks, the above placards may be deleted and the operation limits placard should bear the notation 87 OCTANE FUEL ONLY USED IN ALL TANKS." NOTE 3. Maximum weight may be increased to 10,500 1bs. provided Item 101 (constant speed prop, control or propeller Item 118) is installed. NOTE 4. Eligible for export subject to the provisions of ASR 312 (MOP 2-4 contains same information) except as follows: - landplane - eligible. - Skiplane - not eligible. However, structure complies with Canadian requirements for ski installation when item 105 is installed. NOTE 5. Maximum weight may be increased an amount equal to .00€ × maximum weight when complete de-icer is installed. NOID! with dynamic damper tuned to both 4-1/2 and 9 times engine speed. Item 113 must be installed when engines are equipped with damper turned Propeller is eligible for use on engines without dynamic damper to 4-1/2 times only. When used on engines without dynamic dampers, the propeller shall not be operated in excess of 1500 hours and shall be operated in a cruising range of 1850 to 1950 rpm, taking every precaution to avoid nicks and eliminate them as soon as possible in the outer 14 inches of the blade. NOTE 7. Fuel dump valves must be made positively inoperative pending satisfactory completion of dump tests. NOTE 8. Placard lavatory door as follows: ạThis room not to be occupied during 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-A](https://openairdocs.org/model/lockheed-electra-10-a): 2 aircraft (registry code 5261302) ## STCs approved under this data sheet (7) - [STC SA04652CH](https://openairdocs.org/stc/SA04652CH): To allow use of 100R grade aviation fuel meeting Swift Fuel, LLC specification. Swift Fuels LLC - [STC SA01757WI](https://openairdocs.org/stc/SA01757WI): To allow the use of UL91 or UL94 (minimum) grade aviation fuel. Swift Fuels LLC - [STC SA01831WI](https://openairdocs.org/stc/SA01831WI): To allow the use of UL91 (minimum) grade aviation fuel. Petersen Aviation Inc - [STC SA01828SE](https://openairdocs.org/stc/SA01828SE): Installation of J.P. Instruments (JPI) EDM-960 Primary Engine Data Management System. J. P. Instruments - [STC SA6070NM](https://openairdocs.org/stc/SA6070NM): Installation of a 'quick-disconnect drain plug' on the engine rocker sump for the oil drain retrieval system after engine shutdown.. West Coast Air Creations - [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 - [STC SA1612WE](https://openairdocs.org/stc/SA1612WE): Installation of Hamilton Standard Hydromatic Full Feathering Propellers 22D30-213/6533A-12, Propeller feather system, BT-13 oil cooler and cowling and modified oil tank.. Walter E. Heller and Company --- 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.