# TCDS TC 2-576: Douglas Aircraft Co. Inc. - Type: Type certificate data sheet - Status: Current - Holder: Douglas Aircraft Co. Inc. - Revision: 0 - Revised: November 28, 1945 - Product: Aircraft, Small Airplane - Certification basis: CAR 4a - Registered aircraft: 2, by the registry models matched to it (OpenAirDocs) - Data sheet PDF: https://openairdocs.org/files/sha256/d1/12/d1128952cc1d02128c58adcd47c7fe12a53aa9a586a5642a5c224d9359e1248e - FAA DRS: https://drs.faa.gov/browse/excelExternalWindow/9270E69E3D0E1ED685256735004C7121.0001 - Page: https://openairdocs.org/tcds/TC%202-576 ## Models (2) As the data sheet lists them. - UC-67 - B-23 ## What the data sheet says This is OCR from the scanned FAA data sheet. OCR can misread letters and numbers. ```text MODELS: Douglas UC-67 and B-23, 5 PGIM T.C. NUMBER: 2-576 (Approved 11/28/45) Engines 2 gie are equipped with to Speed perchargers. The supercharger speed controls must be positively safetied for operation in lowgear ratio only.) fuel 100 minimum octane aviation gasoline Engine limits Maximum, except takeoff (low blower) 35.8 in. Y9.. 2300 rpm (1200 hp) (Straight line manifold pressure variation altitude to 5500 ft.) 35.8 in. Ho.. 2300 rp.m Takeoff (five minutes) 43 in. Hg.. 2400 Ipm (1500 hp) except takeoff (low blower) 34.6 in. Hg., 2300 Ipm (1290 hp) (Straight line manifold pressure variation with altitude to 6500 ft.) 34.f in. Hg.. 2300 rpm Takeoff (five minutes) 43 in. Hg.. 2400 rp.m (1600 hp) Maxinum, except takeoff (low blower) (Sea level) 38.5 in. H.., 2300 rpm (1350 hp) (Straight line manifold pressure variation with altitude to 5800 ft.) 36.5 in. Hg.. 2300 Ipm Takeoff (five minutes) 44.0 in. Hg., 2400 rpm (1600 hp) Airspeed limits climb. - 2+1 mph True Ind. Glide or dive - 28? mph True Ind. Flaps extended - 131 mph Irue Ind. C.G. range (+55.3) (18.65 percent MAC) to (+62.3) (24.0 percent 1AT) (gear extended) Datun Leading edge ot certer section #inq MAC 141 in. L.E. of MAC at (+20) Leveling means Leveling lugs at Stations 301 and 315 in fuselage (See NOTE 5) Maximum weights (takeoff and landing) 27,500 (cargo) : 26,000 (passenger) (See NOTE 3) BaqJage NO. seats Fuel capacity A14 gallons (four tanks in center section wing with front and rear tauks on each side connected to form one right and one left hand tank of 407 gallons each (+66)) Oil capacity 66 gallons (two 33 gallon tanks) (+2.0) Control surface Aileron movements (5/8" droop) 24 degrees up 11 degrees down Aileron tab 11 degrees up 1¼ degrees down Elevator 30 degrees up 16 legrees down Elevator tab 10 degrees up 9 degrees down Rudder 23 degrees right 20 dearees left Rudder tab 15 degrees right 15 degrees left Wing flaps 55 degrees down Serial Nos. eligible All AAF numbers Certification basis Airworthiness Certificate only (C4D Q4 prior to 11/9/45) Required equipment Itens 1, 2, 65 6 2 20 301 32, 5031 202. 203, 301. 302. 505 Export eligibility tlinible for export as follows subject to inspectior specified in Chapter XII of Manual of Procedure: (a) Canada - Landplane - Skiplane - not eligible (b) All other countries except Great Britain, Australia, and Wew Zealand Propeller and Propeller Accessories (Except De-Icing Equipment): Hamilton Standard propellers, hubs 23550, blades 6159A-6 to 6159A-9 Diameter 13'6-3/8" maximum, blade models see Propeller Spec. 23 degrees at 42" station; teachered 93 degrees at 42" (-106) 2. Two Hamilton Standard governors (Model 4K11-B1B) (-102) 3. Two propeller feathering pumps (Pesco R-280-BE) 4 _ Hamilton Standard propellers, hubs 23E50, blades 6359A-12 to -14. Diameter 13'1/4i maximum, 12'9-1/8" minimum. Minimum low pitch setting 24 degrees at 42 station, feathered 93 degrees at 42" station. (-106) Michigan Ave., Chicago 5, FAte, Shicago S, iL, holds approved single engine performance data. Engine and Engine Accessories (Except De-Icing Equipnent): 101. TWO vacuum pumps (Pesco 207-D) 10 1bs. (-24) 102. Two starters (Eclipse Model 18) (-46) 103. Two oil coolers (U.A.P. U-5013) 87 lbs. (-40) 104. Two cylinder head temperature gauges (-44) 105. IWO fuel pumps (Thompson Prod. 4101) (-49) 106. Two hydraulic pumps (Pesco 214MA) 8 1bs. (-48) 107. Two auxiliary fuel pumps (Thompson IFD6400) 10 1bs. Landing Gear and Floats: 201. Two 45x20:00-18 Bendix wheels with duo servo brakes (Bendix 56478) (+28) 202. Two 45x20:00-13 tires (Goodrich 12 ply) (+28) 203. Two 45x20:00-18 (Goodrich tubes) (+28) 204. 22x: tail wheel (Bendix B-1) (+443) 205. 22x9:00x6 tail wheel tire (Goodyear 8 ply) +443 206. 22x9:00x6 tail wheel tire tube +443 207. Four shockstruts (Douglas Drawing 5077049) (+29) 208. Tail wheel shockstrut (Douglas Drawing 5077046) (+426) 209. Two 17.00-16 Bendix wheels (Bendix B-3) 210. Two 17.00-16 tires (Bendix 10-ply rayon) Electrical Equipment: Two batteries (Fxide D-6) 142 1bs. (+45) Two generators 46 1bs. (-47) landing lights (AC-36D-3467 Type A-9) 7 1bs. (+30) Interior Equipment: 402. Seats (a) Pilot (Douglas Drawing 5083281) (-18) (b) Co-pilot (Douqlas Drawing 5082337) (-18) (c) Navigator (Douglas Drawinq 5032333) (+36) (a) Radio Operator Drawing 5082339) (Douglas (+36) Equipment (Propeller, Wing and Windshield): Propeller de-icer equipment inciuding windshield de-icer system (-36) Anti-icer tank 1-32 503. Windshield wipers (Acrotorque 17) (-42) Windshield Wipers (Kearfoot 5A-4) 539 wing and tail surface NOTE 1. Weight and balance report including list of equipment included in certificated weight empty, and loading instructions when nacessary, must be submitted for each aircraft with original inspection report and subsequent report covering change in equipment. Each airplane must be weighted to determine its weight and balance prior to original certifi- cation. Prior to certification as a civil aircraft, the following must be accomplished. Carbon Monoxide Elimitation in cabin. charges must be made to reduce the carbin monoxide concentration in the pilot and passender Emergency Exits (See CAP 04.462 for requirements). cabin to at least one part in 20,000 (or .015 percent). Present UC-67 airplanes can be certificated for carrying a maxinum of For more than five persons, changes must be made to comply with the exit requirements of CAR 04.462. If fuselage structural members are altered to provide for the required exits, the alteration and substantiating structural data should be forwarded P.O. Box 45007, Airport Station, Los Angeles, CA. at he necessite to a rev ponte in fish i circate Fuel booster pump protectors must be accessible in flight. Master Switch. A master switch arrangement accessible to a crew member in flight must be installed to provide disconnection of all electrical power at a point near the power source (batteries and generators) . The ignition switch and system must be made independent of the master switch and battery switch. Fuel Tank Sump Drains. Sump drains nust be modified so as to drain clear of the nacelle structure. Landing Flares. All airplanes certificated for night operation nust be provided with approved flares in accordance with cas J4.512 (c). Passenjer seats and safety belt installations other than originally provided by the manufacturer must he shown to neet the strenqth requirements of Car 04. In the event any tanks are renoved or not intended to be used, the fuel gauges should be checked for proper graduation and of the poppet type renoved or blocked open in order to preclude setting the valve in the "unused" position. tank filler caps or adjacent surfaces must be marked to indicate the minimun octane fuel and the tank capacity, and in the case of the the additional note "Fill rear fuel tanks first." tank capacitites also must be properly indicated at the fuel valve An oil level indicating device nust re provided in accordance with CAR 04.633. beane ani foing provide for such copistente anoid be caratio ¡ane placarded for the mit such otherts shaild be canatie the maximum perissible floor loadings. All cargo and baguare compartments of withstanding a limit load factor of 3.32 without undue permanent deformation and must have sufficient strength to withstand an ultimate load factor of 5.73. Adequate cargo tie-downs must be provided. plywood supported by four pine 2x4 inch transvers be 1600 Ibs. Some UC-67 airplanes have a bomb bay floor installation of 3/4 inch This floor is capable of supporting a uniformly distributed load of Instruments. Instruments must be marked for approved operation limitations. A cylinder head temperature gauge must be installed and marked to indicate a limiting temperature of 450 degrees F. Each aircraft must satisfactorily pass an inspection for conformity, possible hidden damage, and for workmanship and materials used in making any repairs and/or alterations. In making the inspection for hidden damage, the outer wing panels must be removed to permit the inspection of the doublers and attaching angles for defects and replacement thereof as needed in accordance with the Airworthi- Directives for Douglas DC-3 series aircraft as are pertinent to this aircraft. If any changes have been made which would adversely affect its flight characteristics, the particular airplane nust be Any interior or exterior changes made to the primary structure or equipment be either according to approved Douglas drawings or satis- factorily substantiated. Upon completion of the conversion to certificated status, the manu- facturer's nameplate on the aircraft should be altered to include the date of conversion. In some cases the original nameplate is not sufficiently large to include this additional information, a similar plate should be installed near the original plate. stances should the original or any succeeding nameplate be removed Fuel booster pump and propeller feathering pump circuits must incorporate circuit breakers. Approved position lights must be installed. NOTE 3. Eligible for certification at a takeoff weight of 27,500 lbs. with passengers, provided a satisfactory fuel dumping installation is made. Requests regarding approval of such an installation should be addressed to the FAA, P.O. Box 45007, Airport Station, Los Angeles, CA. NOTE 4. The following placards shall be placed on the instrument panel in full view of the pilot. The operating manual referred to in part (b) shall be in the pilot's compartment at all tines. (a) Use booster pumps for takeoff and for all operations above 10,000 ft. (b) This airplane shall be operated in accordance with Part I of the CAA approved operating manual for Douglas UC-67 airplanes. (c) Use fuel tanks 3 and 4 when using booster pumps (for aircraft having 4 tank fuel system). For airplanes in which the leveling lugs have been removed during conversion to a civil status, the use of a plunb bob dropped fron the top to the bottom door sill at fuselage station 270.5 (+102) is considered satisfactory. ``` ## ADs None name its models. ## Registered aircraft by registry model (OpenAirDocs) - [Douglas B-23](https://openairdocs.org/model/douglas-b-23): 2 aircraft (registry code 3020702) - [Douglas UC-67](https://openairdocs.org/model/douglas-uc-67): 0 aircraft (registry code 3020704) ## STCs approved under this data sheet (4) - [STC SA01406NY](https://openairdocs.org/stc/SA01406NY): Installation of Airwolf remote mounted engine oil filter kit AFC-K017 on single and multi-engine fixed light aircraft and rotary wing. Airwolf Filter Corporation - [STC SA2-228](https://openairdocs.org/stc/SA2-228): The generator system rewired to accommodate a 200-amp load and equipment.. Signature Flight Support Corporation - [STC SA2-229](https://openairdocs.org/stc/SA2-229): The anti-icer system is altered.. Signature Flight Support Corporation - [STC SA2-739](https://openairdocs.org/stc/SA2-739): Installation of picture window.. Sierra Industries, Inc --- 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.