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MANUAL - Taylorcraft

1. paar e Muselave Game A ia Puselase drawing ucro pra u 2 Control system drawing PCT dues RE 23 Wing frame eee T pad sque 4 Wing frame drawings STEPS ee 5 Specifications and performance data d Ground handling and general maintenance T TTE 8 Leveling and rigging procedure ehe a eee da 8 assembly rigging issu a de Ier 9 Tail assembly v E 10 Windows and Windshields PTS COSE 11 Brake adjustments IAE AAA T Electrical equipment E D PERPE PU ie TA Instrument panel drawing E sues Fuselage fuel tank drawing Landinp gear installation anne deed T Engine P pA 18 Starting and stopping procedure S ARA RS 20 Engine installation drawings ER VESPERE EFAS TEER Rae Eee 21 Airframe and engine lubrication yu a cea dae 23 Inspection instructions ET MER gard due PTT 24 APPENDIX Aircraft Specifications A 696 R
2. 2 ia Imai 4 1 242 49 242 f amp 2 gop3 As SHT OFF NU ECT MN TAVCERCRAFT AVIATION eae AL ALL i e Cen L En Mr Oder il 2 owes EIL DUE acres erst RITE ER 42050 924 1942 aye AIR EAS Mo 5 2 7 Ir LEE Ar CAREN ez 9086 PRIMER kw 66 see 7 224069 M 2 4 ST E eine uy m mee rA leva a E Re A ee D IA in VIEW i A FL dir 24 Ly 7 x A nn 05 E EYE ENG IN E E 2 4 IA reet From f Ru 8 8 sue D AED 92 manner RESET za Gest gel INS 3 C804 15 14 MOLLY TT Wists so 1 718 om ome Fedele P om un nd EVO TITEL me ng Wi Mt re owen We m vase Ld we 9 99 NOS 8 e e 2 Cv greens Ys awe tege prr EI rs d U k 20 IM 64 TM 4 DY RT Mw eie w 39 gt reu emnt gue aa A y lik aso woso elo 2 NOV WAY 2 592007 44
3. 20 COCKPIT AND BAGGAGE AREA Seats Check general condition Check condition of safety belts Airworthiness Directives on seat if frayed replace Check baggage area canvas if deteriorated or ripped replace WINDSHIELD Check weatherstripping for security in channels and for leaks Check plastic windshield and side windows for cracks crazing distortion and discolor ation POWERPLANT INSTRUMENTS Check powerplant instruments for mounting security Check connections and plugs Check placards and limitation markings Tachometer Red line 2300 RPM Oil pressure Redline 10 PSI amp 35 PSI Oil temperature Hed ine 220 degrees F Green arc 120 to 220 degrees F Yellow arc 40 to 120 degrees F FLIGHT INSTRUMENTS Check flight instruments for mounting security Check connections and plugs Check placards and limitation markings Air speed Red line 140 MPH Landplane 129 MPH Seaplane DOOR LATCH AND HINGES Check door hinge and rivets for looseness Check door latch plunger for complete extension to prevent doors opening while taxiing Check door for proper fit or damage resulting in air leaks ENGINE CONTROLS Check mixture control for panel placard and operation smoothness Check carburetor heat for panel placard and smoothness of operation Check throttie for smooth operation and operation of friction lock Check primer for operation and leaks behind the panel Check cabin heat fo
4. Mea es 4 MA 4114 Ar Y AVIATION ALLA 0496 WING FRAME The wing frame consists of laminated Spruce spars re inforced at the butt and strut attachments with three ply Spruce pads All ribs are one piese we formed aluminum _ re inforced at the spar openings E Spar butt attachment and strut attachment fitting holes are re inforced with micarta bushings pressed and glued to the spar blank Kem wood primer is applied to the spar as a protective coating and should be re applied to any exposed wood after or repairs Methods of finish and das are covered in FAA manual 18 which way be obtained from the Superintendant of Public Documents Washington 25 D C Spar butt fittings are X4130 steel clevis type Damaged or worn spar butt fittings should never be welded or bushed but should be replaced complete and may be ordered by giving He number shown on the accompanying dde The wings are attached to the fusel age with AN4 13 bolt and AN365 4 nut rear spar and AN5 15 bolt and AN365 5 Nut front spar These bolts pass through the spar fittings and fuselage spar attachment fittings The spar butt attachment fittings are designed to fit snugly to the fuselage fittings and should not be bushed or shimmed The front spar strut attachment fittings include tie down rings The rear strut is attached with a bolt through the spat and the strut upper end fitting Position light wiring
5. Check for Operations Limitations Form Above items are required in cockpit when aircraft is currently licensed 31 DEPARTMENT OF TRANSPORTATION A 696 FEDERAL AVIATION ADMINISTRATION Revision 15 TAYLORCRAFT BCS12 D BC12 Dl BCS12 D1 BC12D 85 BC12 65 Army L 2H 512 85 BCS12 65 BC12D 4 85 BC12 D BCS12D 4 85 November 1 1967 AIRCRAFT SPECIFICATION NO A 696 Type Certificate Holder Feris Flying Service Hinsdale Airport Route 1 Hinsdale Illinois 60521 I Model BC 2 PCIM Approved August 24 1938 Model BCS 2 PCSM Approved April 5 1939 Engine Continental A 50 1 see item 114 a for optional engines Fuel 73 min grade aviation gasoline Engine limits For all operations 1900 r p m 50 hp Propeller limits Diameter Maximum 83 in Airspeed limits Landplane Level flight or climb 105 m p h 91 knots True Ind Glide or dive 131 m p h 114 knots True Ind Seaplane Level flight or climb 95 m p h 83 knots True Ind Glide or dive 129 m p h 112 knots True Ind C G range Landplane 14 5 to 19 7 Seaplane 15 1 to 419 4 Empty wt range Landplane 415 3 to 418 5 Seaplane 15 9 to 418 3 When empty weight C G falls within pertinent range computation of critical fore and aft positions is unnecessary Ranges are not valid for non standard arrangements Maximum weight Landplane 1100 1b S N s 1407 and up are eligible at 1150 1b Seaplane 1228 1b No
6. LEICHEN E c d LA gL TU install R 0866 17 ENGINE INSTALLATION GENERAL Continental A65 8A T C 205 Horizontally opposed four cylinder air cooled with 3 7 8 bore and 3 5 8 stroke Total piston displacement is 171 cubic inches and comp ression ratio 6 3 to 1 Rated horsepower at sea level 65 hp at 2300 RPM Recommended cruising 2150 RPM NOTE Recommended cruising RPM should be static or the maximum RPM shown on the tachometer when the engine is run up prior to flight with carburetor heat off OIL REQUIRED Warm weather SAE 40 Cold weather SAE 30 Oil pressure 10 35 lbs Oil Temperature Minimum 120 degrees F Maximum 220 degrees F Carburetor E Stromberg NA 5341 Fuel required 13 Octane minimum The next highest Octane may be used if the recommended fuel is not available ie 80 or 90 Octane permissible Fuel consumption 4 25 US gallons per hour 3 52 Imperial gallons per hour Ignition Bendix Scintilla or Eiseman magnetos Champion C26 Spark Plugs Firing order m 0 8 4 30 degrees Before Top Dead Center with both magnetos Left magneto fires lower spark plugs right magneto fires upper plugs 18 MOUNT Attachment of engine to fuselage is provided by the engine mount assembly fabricated of 1010 1025 and X4130 steel tubing engineered to lessen vibration transmission to the
7. 1957 CONTINENTAL A65 8F FLANGER 8 CRANKSHAFT Mr 9 0 2 BCD ES e DETAIL A 456 2575 572490 OF OGY USE MY OF PS AS DETALED 3160 10 5 NUT AN362 2 2 PIN 4E ACH REG Ol PRESSURE LINE 6 706 FIREWALL REF oll BREATHE A Tus 6 HOSE 8C 909 CLAMP 2 REQ easter 3 73 9653 2 crane Il epose 0 BA 206 e fuk Press Live E 4 1 A TT 1 TI so NUT E I e 4 1 EAT a leo 7 t cookie met IN Fo arg etsnes nis CITE Ol 444 29 2023 t Eve 9940 11 TA 2366 21 FUEL INSTAL 0865 1 0 ws TALL 49886 Tue Capel pin Peers 24 M el AS TT TT VEIR 5 E 2 Ex E Mood Tt PANNE AN OO 10 br andi pt YT 21370 57 76 mea VEU Pt 10 980 m BE CONTINENTAU ACS Y ces O 706 WAS OFS EO 9199 D290 este SRS LUBRICATION CHART ENGINE 30 winter 40 summer is recommended the oil be changed every 25 hours of engine running time for maximum engine life Detergent oil Shell W may be used if used con sistantly from overhaul For the first 25 hours however use non additive mineral oil to allow the rin
8. 4Y Dee pe amay wd het Ay OA oor ves 19 9 MA Y Y 9 20 VO DIGO tvo 596 20 rs 040 we bumsen 29 9014914 NN un y we patty 26 tet ds gere t 2005 tw re Y 208 28 IO LIE ow 2799 7740 777 4 16 ANPARTS CALLED ON DWG Y wid EU SREQ STANLARD BOLT 1 1 ANS 27 BOLT O90I 1L pma Lo O 8 P El en 95 0 1 gt TICHT e a TT Pe G2 seamganeg pa sj fti ire 43020 Rare E A wear Ber n soe ral a ganas 74 KITTEL proa la a 7 AZER A AED T AMARO 2 RPM a ae Draw 8 09866 __ CE t Tan veiut CZ E UO CY 6 00 6 TIE EE XII SUN 3 INSTALLATION A tole ACNE TAVLORCHAFTA CORP Ti e Trl FA ALIGHTING GEAR AUX _ le 2110 22 y II Ll lese o SPRING 5946 0 2 2 269 GT SPR
9. E s SPEED ZIETIERLEE TE gt li CEA mmu ob 2 MAU TU hh 2 CHF 55 PU A AN IZ CAC gt A A4 3 2 72 E Payo 1 Compr ss _ 3 Led i Y lL TUCASA i Y A TE DISCO i t popni a RR y 3 A Ea i v TRA METER gt an ROA ae YA pe Sec SUUM LLLI EEE y B TEMO a 2 STE dev eee c 612 9277 bee fy J 0 766 Er yY i 5 B 7050 PLACARD AE 7 Bay i rri ner 1115 SPACER 206 A 24 3944 Birgit 0993 0000 As time 9 0 0836 1 INST Y i FWP ATURE __ 527612 MSCI veg _ RJ bi 2 7104 THA 7 LE SWITCH MAG A B 3 2 1 56 BRKT REF 0978 09 9 1 Cv n 8 2 9 _ 826 017 N 577 E an 8 NUT A S ob EA 812 317 narn AM 8 2 9012 lt lt WASHES pees 2 gt 874 9 7 52 2 Bi CABIN 4 ACTON X CONTROL INST JI AD 82 9127 Jus Mia SPACE E Re DL uns IRS tnc oo s ver B SO EP 2 ra IPSE 2 Ac MUT t 722 c y 6 2 arm DONE 8 2 4102 72 E EN zZ E paste D
10. Seaplane 1278 1b 2 23 Landplane 50 1b 40 Seaplane 30 1b 40 12 gal 9 4 qt 21 34 Control surface movements Serial Nos eligible Required equipment A 696 Elevators Up 27 Down 25 Elevator tab Up 25 Down 30 Ailerons Up 23 Down 23 Rudder Right 26 Left 26 6402 and up Landplane 4 or 8 104 108 202 203 210 a 401 1 25 3 Seaplane 1 3 4 or 8 104 108 205 401 VI Model BC12D 85 2 PCL SM Approved September 30 1948 Model BCS12D 85 2 PCL SM Approved September 30 1948 same as Model BC12 D except for increased power and gross weight fuel system changes auxiliary wing fuel tank revised wing fittings and minor structural changes Engines Fuel Engine limits Propeller limits with item 6 range Empty Wt range Maximum weight No of seats Maximum baggage Fuel capacity Oil capacity Control surface movements Serial Nos eligible Required equipment Continental C85 8F 80 min grade aviation gasoline For all operations 2575 r p m 85 hp Static r p m at maximum permissible throttle setting no additional tolerance permitted Landplane not over 2350 not under 2100 Seaplane not over 2310 not under 2010 exception 2100 with item 205 a not under Diameter Landplane not over 72 in not under 68 Seaplane not over 72 in not under 70 in Landplane 14 2 to 420 0 Seaplane 415 8 to 1
11. all operations 2300 r p m 65 hp 2 A 65 7 or A 65 7J Engine limits same as b 1 c Models BC12 65 BCS12 65 1 A 65 7J 65 8 A 65 8F A 65 8j Engine limits same as 1 d Models BC12 D BCS12 D BC12 D1 BCS12 D1 1 A 65 8F A 65 8J Engine limits same as b 1 Auxiliary 6 gal fuselage fuel tank installation fuel arm 35 BC BCS BC 65 BCS 65 Enclosed type engine cowl dwg BL L628 BC BCS BC 65 BCS 65 Revised engine mount dwg BC65 A128 for engines incorporating integral rubber bushings 38 11 1b 34 13 1b 34 2 1b 40 4 1b 20 16 lb 24 2 33 6 1b 10 1 3 1b 13 1b No weight change 10 1b No weight change No weight change No weight change 8 1b 30 9 Ib 18 Negligible wt A 696 Landing Gear and Floats 201 Two main wheel brake assemblies 6 00 6 Type III a Cleveland Aircraft Products Model 6 00 DHB T4 1b 2 Wheel assembly No C 38500HMA Brake assembly No C 7000 14 202 Two main wheels 6 00 6 Type III Firestone 604 9 1b 2 15 203 Tail skid 16 204 Parking brake 1 1b 9 17 205 Edo float installation Model 60 1320 floats 165 1b 20 Auxiliary fin required on all models except BCS12D 85 4 lb 176 and BCS12D 4 85 unless the seaplane aft C G limit for maximum weight is reduced to 18 9 When propeller item 1 or 6 is installed on Models BCS12D 85 or BCS12D 4 85 the minimum static
12. answers Switch off only after checking switch visually and by feel Prop man commands Brakes Operator answers Brakes only after firmly pressing brakes Prop man then tries to move aircraft so as to check that brakes are actually holding plane firm i CAUTION DO NOT DISREGARD ANY ITEM IN ABOVE CHECK LIST PEOPLE ARE STILL GETTING KILLED BY PROPELLERS Prop man then pulls the prop through several compressions If the engine is in good condition and the weather warm no priming is necessary He then commands Contact to which the operator replies Contact turning the switch quick twist and the engine should start smoothly The throttle should be open 1 10th during the starting procedure If the engine does not start immediately it may have too much fuel in the induction system The switch is turned off the throttle opened all the way and the prop pulled thr ough several times in the normal direction of rotation It is a common misconception that _ to rotate the prop backwards clears the engine There is no basis for this thinking To stop the engine reduce the throttle until the engine is turning about 800 RPM Turn the ignition switch off and as it stops open the throttle to the stop This will reduce pre ignition which causes the engine to NEED running 20 ale irs POR BAY A A WOR 8 Mang Vra frog
13. auxiliary fin 4 1 176 BCS12 D and BCS12 D1 only 24 212 Wheel fenders Consolidair Model 16 Consolidair instln dwg 0029 Electrical Equipment 310 Battery and box a b 12 v c 12 v BC12D 4 85 and BCS12D 4 85 319 Position lights a Grimes B 6 v b Grimes D 6 v BC12 D BC12D 85 and BCS12 D only c Grimes D 12 v BC12 D BC12D 85 BCS12D 85 BC12D 4 85 and BCS12D 4 85 322 Generator Delco Remy 1101876 BC12D 4 85 and BCS12D 4 85 only 323 Voltage regulator Delco Remy 1118323 BC12D 4 85 BCS12D 4 85 Interior Equipment 25 401 Wheel type control 26 402 Cabin heater Taylorcraft BC L606 or BC L630 27 403 Stick type control Miscellaneous not listed above 28 601 Auxiliary door A 696 12 1b 2 5 lb 2 122 1b 25 10 1b 2 9 1b 10 16 1b 70 2 1b 77 10 1b 24 1 1b 18 2 1b 22 Negligible wt 5 1b 25 NOTE 1 Weight and balance report including list of equipment included in certificated empty weight and loading instructions when necessary must be provided for each aircraft at the time of original certification NOTE 2 Left hand wing tank eligible as 6 gal auxiliary on all models except BCS 65 and BC12D 85 END 40 NOTES THIS MANUAL IS A DIRECT COPY OF THE ORIGINAL E WE ASSUME NO RESPONSIBILITY FOR THE CONTENTS UNIVAIR AIRCRAFT CORPORATION
14. is ponti in each wing and is attached to the drag wire inter sections running from the fuselage to the wing tip Rigidity between front and pu spars is accomplished by the use of ten drag wires and five compression struts The drag wires are heat treated steel 125 000 PSI Rockwell test and in no instance should they be replaced with soft wire Care should be used when re building or repairing the wing to avoid the use of tools such as pliers which might scratch or crack these wires small scratch in this material may develop into a crack and structural failure The compression struts are X4130 round steel tubing not heat treated These com pression assemblies are bolted to the rear and front spars The leading edges are re inforced with 016 24ST H aluminum Replacement of these parts be ordered by numbers shown on the drawing DAA VIBE 9 990 ii 8 ii i if an sma poo ud irt rn at res zu 49V 14060 2 2 py ie i sh 5 qui ibi i ik sith f LE fi m dE Hu ph i a i bin p bl h i li gt i p uod TE gt gt gt M MAN Fein e SR 1 5 1 N stess amp ts AS ETN an i HET heh nti ent ip B us 21 45 Beppe amp 7 Ses tute 11 RR e Ps Be xA EA
15. oian MATO A qe oA MAL MAY Uma y 2004 De PT STERN 390c9 To Laia ANTES SC Tas OTHER OE DINER 6 Safe rye To SPC 30e TS INSTALLATION 7 2 Cro AN QIDO NGINE inis T COWLING ASSEM TOP USE Osso 2 INSTEAD 0990 1 68 9039 SUP SEAM COWLING HEATER MUFF REF Bc 6209 M2 9902 CABLE REF 2 wo ti ACTU COWLING E S 545 6 6 sores n 565 32 n9co WASHER View A FRO NE EE E LEONE us NN SINN MEN A DEDO OSTEN SE NN AT 4 A ELE EE ARGOS we EEE T TC d o I I ASIS 5 LLL 4 NE en RE SERENO ENERO SA NE RSS 2 20 EN AY BE o 43 TA A 20 4N _ GAFETY SEE NOTE _ qoo adc E m _ _ B 69 SPRING SA EEE See DEI D 614 BOLT Noii a AHN3320 3fhn U I COR Ca T Fs OSE CONTROLRER Bares Opa e BORSA 1 mE ARDRE TOR RE
16. r p m limit is increased to not under 2100 r p m As an alternate method of installing these floats Taylor craft clamp on fuselage fittings P N s 2554 2555 and 2556 may be used b Mod21 92 1400 floats 181 1b 19 Auxiliary fin required on all models except BCS12D 85 4 lb 176 and BCS12D 4 85 18 206 Tail wheel assemblies 193 6 x 2 00 steerable with brake Baxter 5 1b b 6 x 2 00 steerable Aircraft Associates 3 1b c 6 x 2 00 full swiveling Firestone Industrial 3 1b d 6 x 2 00 steerable Lake State Products 5 40 31 4 1b e 6 x 2 00 steerable Heath 4 1b f Maule SFS 12 SS 12 SAFS 12 SFS 1 2 P8 4 1b g Steerable Lang D 501 formerly Decker 6 1b h Scott Model 3 248 steerable full swiveling 6 1b 19 207 Two main wheel brake assembl es 6 00 6 Type III FREUT Firestone Model 6C3HB 4 1b 2 20 208 Wheel streamlines dwg A 9015 or A 9016 6 1b 2 21 209 Skis eligible on any airplane of these models provided the Use act wt change propeller installation meets the m nimum 9 in ground clearance The maximum weight for the skiplane will be the same as for the corresponding landplane or that shown in parenthesis after each Ski model whichever is less Marston 1200 max 1200 1b b Air Transport 1220 480 1220 1b c Air Transport 1224 580 1 max 1220 1b d Federal SC 1 1400 1b e Piper S 1000 max 1200 1b f Jennings TY 2 ma
17. shoe Reassemble brake shoes and springs Screw in adjustment wedge screw adjacent plate which has lock nut loosened one turn and try wheel and drum over brake Continue tightening wedge screws one turn at a time and testing wheel brake drum over brake until a noticable drag is developed by each shoe If the range of the adjustment wedge is insufficient lock its 10 24 nut firmly and continue with the adjustment on the opposite end of the shoe by the same methods WARNING Never force the adjustment wedge screw when the 10 24 lock nut has not been previously loosened 5 With the brake drum over the brake assembly apply brake release brakes with the 10 24 nuts loosened usually results in clearance enough to remove the drag If either of the shoes still drags it will be necessary to back out the wedge adjustment screw on that shoe one half turn and again apply the brake firmly with the wheel drum in place and check for drag 6 After satisfactory adjustment is obtained remove the shoes and tighten the 10 24 nuts firmly to lock adjustment and plates 7 Finally tighten wedge adjustment screw slightly and reassemble brake WORN LININGS If the brake linings are worn down to the rivet heads les should be relined before ad justment is attempted See the bulletin on relining brakes 12 dM ADJUSTMENT OF BRAKE SHOES ON MODEL 6C2HB 6C4HB and 6C5HB WHEELS Unhook lock springs from adjustment nuts lo
18. the aircraft is longitudinally level To level aircraft laterally place bubble level on one of the top fuselage cross members or the seat cross tube For weight and balance computation it is not necessary to level aircraft laterally However for rigging wings this step is very necessary RIGGING INFORMATION As the airplane is built entirely in jigs it requires no re rigging to disassemble and reassemble the wings There are only two points where any wing adjustment may be made The front wing struts being jig built have no adjustment To check the rigging of the wings and tail stretch a cord across the wings at the front spar and level the ship with a line level placed over the center of the cabin Stretch a second cord across the wings at the rear spar and level with a line level The rear strut adjustment is used to accomplish this The bolt at the point of attachment of the wing strut with the wing fitting must first be removed long screwdriver may be used to move the adjustment nut as required In flight testing if the airplane flies either wing heavy the rear strut adjustment may be used to correct this by washing the opposite wing out or the heavy wing in If the airplane flies nose heavy both wings may be washed in or if tail heavy both wings may be washed out for correction The tail is rigged level and perpendicular while the ship is level n ordinary level used along the rear tube of the stabilizer and rear tub
19. tolerance permitted Landplane not over 2350 not under 2100 Seaplane not over 2310 not under 2010 exception not under 2100 with item 205 a Diameter Landplane not over 72 in not under 68 in Seaplane not over 72 in not under 70 in Landplane Level flight or climb 105 m p h 91 knots True Ind Glide or dive 142 m p h 124 knots True Ind Seaplane Level flight or climb 95 m p h 83 knots True Ind Glide or dive 128 m p h 111 knots True Ind Landplane 14 2 to 420 0 Seaplane 15 8 to 417 6 at 1351 1b 13 4 to 417 6 at 1200 1b or less Straight line variation between points given See Figure under Section VI Landplane 414 9 to 16 3 Seaplane 13 8 to 14 3 When empty weight falls within the pertinent range computation of critical fore and aft positions is unnecessary Ranges not valid for non standard arrangements Landplane 1280 1b Seaplane 1351 1b 2 23 Landplane 50 1b 70 Seaplane 30 1b 470 18 gal 12 gal tank in fuselage at 9 and 6 gal tank in wing at 24 4 1 2 qt 30 Elevators Up 27 Down 25 Elevator tab Up 25 Down 30 Ailerons Up 23 Dom 23 Rudder Right 26 Left 26 4 13010 and up Landplane 1 7 or 9 104 108 202 206 210 a 401 Seaplane 1 4 or 9 104 108 205 401 Specifications Pertinent to All Models Datum Leveling means Certification basis Production basis Export eligibility Leadin
20. when worn Check rudder travel 26 degrees left 26 degrees right ELEVATORS Check fabric condition and finish on the elevators Check for open drain grommets along the elevator trailing edge Sight one elevator against the other for alignment Check hinge pins and bushings for wear and replace any worn pins or bushings Check elevator cable horns for safety worn bolts and clearance in travel Check elevator travel 27 degrees up 25 degrees down EXTERNAL BRACING Check empennage rigging wires for corrosion and cracks or nicks that might result in failure Check fittings for alignment with the wire and check bolts for safety Rigging wires should be taut with little hand deflection Check each wire to be sure there are no loose fork lock nuts RUDDER AND ELEVATOR CONTROLS Check rudder and elevator horns for worn bolts and safety with no threads in bearing Check horns for alignment with the cable and freedom of travel Check top and bottom cable turnbuckles for safety and a maximum of three threads showing outside the barrel Sight the cables the Sele for and chafing FLOATS OR SKI INSTALLATION Sight check rigging All brace wires tight and Water ballast if carried No leaks in floats Structure checked FAA REQUIREMENTS Check all airworthiness directives for applicability and compliance Check for presence of airworthiness form Check for presence of Certificate of Registration
21. 05 401 V Model BC12 D1 2 PCL SM Approved September 10 1946 Model 512 1 2 PCL SM Approved September 10 1946 Same as Model BC12 D except for elimination of left hand door item 601 parking brake item 204 and 6 gal R H wing tank Model BC12 Dl eligible as BC12 D when items 601 and 204 and 6 gal right hand wing tank are installed Engine Fuel Engine limits Propeller limits Airspeed limits C C range Empty wt range Maximum weight No of seats Maximum baggage Fuel capacity Oil capacity Continental A 65 8 see item ll4 d for optional engines 73 min grade aviation gasoline For all operations 2300 r p m 65 hp Static r p m at full throttle not over 2250 not under 2070 No additional tolerance permitted Diameter not over 72 in not under 70 in Landplane Level flight or climb 105 m p h True Ind Glide or dive 140 m p h True Ind Seaplane Level flight or climb 95 m p h True Ind Glide or dive 129 m p h True Ind Landplane 14 2 to 420 0 Seaplane 414 2 to 420 0 with Edo floats item 205 14 6 to 20 0 with Heath floats item 311 Landplane 14 8 to 417 9 Seaplane 414 8 to 418 3 with Edo floats item 205 415 2 to 18 3 with Heath floats item 311 When empty weight C G falls within the pertinent range computation of critical fore and aft C G positions is unnecessary Ranges are not valid for non standard arrangements Landplane 1200 1b
22. 7 6 at 1351 1b 13 4 to 17 6 at 1200 1b or less Straight line variation between points given 1400 LA 1100 100 12 13 14 15 16 17 18 INCHES Landplane 414 8 to 417 9 Seaplane 13 7 to 15 1 When empty weight falls within the pertinent range computation of critical fore and aft positions is unnecessary Ranges are not valid for non standard arrangements Landplane 1280 Lb Seaplane 1351 1b 2 23 Landplane 50 1b 40 Seaplane 30 1b 40 18 gal 12 tank in TS at 9 and 6 gal tank in wing at 24 Elevators Up 27 Down 25 Elevator tab Up 25 Down 30 Ailerons Up 23 Down 23 Rudder Right 26 Left 26 12001 and u Landplane 4 6 7 or 9 104 108 202 206 210 a 401 Seaplane 1 4 6 7 or 9 104 108 205 401 35 VII Model BC12D 4 85 2 PCL SM Approved July 13 1949 A 696 Model BCS12D 4 85 2 PCL SM Approved July 13 1949 Same as Model BC12D 85 except for engine baggage compartment side windows zd nee Fuel Engine limits Propeller limits with item 6 Airspeed limits C G range Empty wt range Maximum weight No of seats Maximum baggage Fuel capacity 011 capacity Control surface movements Serial Nos eligible Required equipment Continental C85 12F 80 min grade aviation gasoline For all operations 2575 r p m 85 hp Static r p m at maximum permissible throttle setting no additional
23. N SOUT f s o ARE pw tita 2 B20 BUSHING 2849 ID 25 CABLE ASSEM ELEMITOR I A B A2I CABLE ASSEM ELEVATOR e A ht WHEEL 498 oL 2844 B 154 cuoc 4mQ 5 BOLT Ar320 3MUT ANSSO 2 271 Ac A 88 06 40 MACH SCREV 5 650 AN 340 6 ORIQ AALS sPROCKET Mi Au310 AN 380 5 5 Fi Ar 909 PULLEY 4 AN 3 8 BOLT AREA anisze INYTEREQ AN380 5 fir 4RIQ A 999 BUSHING seta Kung wur Av 860 WASH An390 a tr 49880 2 2 47148 PUSHING AD SBT BALA 910 3 AN390 2 209 an Tesa CABLES ATTACH i EMPUNMAGE INSTAL 94994 _ cour Asin Rieur _ 146 I _ 9 A RUBBER CHANNEL 5 RUBBER CHANNEL AREA 0 1 IA B A 2 7 leaple assim RUOSIR_ LEFT e 7 0044 8320 3 A DOO 8 200 DEREN 1 ARNO 9 hrs 43 4 40 ANS 4 wur aar a Qaem Anti 1 NA fern 8 Asigeo 6 s rn 4 49 7 244 6 6 6 43 4 n AREA i 9012 42 1 CAM 9 24 4 4 487 1 8 206 1 CAR 9 55 4 9 04 sube 4 90 429 ir wies Owes Geers M E de DAB cabit MM
24. NG GEAR Hoist aircraft by engine mount at firewall and check gear bushings vee bushings are replaceable if worn Check for skin wrinkles indicative of inside damage WING FITTINGS With wing root fairings removed inspect wing fittings with a flashlight and magnifying glass for minute cracks in the ears Check bolts to be sure there are no threads in bearing and bolts are properly safetied Check wing fitting holes for elongation by having some one pull up and down on wing tips LANDING GEAR FITTINGS Remove both landing gear fairings and inspect all fittings with flashlight and magnifying glass for signs of cracks or hole elongation FUSELAGE STRUCTURE Through inspection openings and through the baggage compartment cover check the cond ition of all tubing for rust damage and protective coating Check all wood stringers for damage and security DEBRIS ACCUMULATION Check the bottom of the fuselage and fabric under floor boards for bolts nuts and other objects that might jam controls or pulleys Check the rear of fuselage for open drain grommets If considerable dirt or oilexists on the fuselage bottom use a non caustic soap and wash out the dirt to prevent fabric rot CONTROL CABLES AND PULLEYS Check for broken control cable strands by sliding a cloth over the cable in vicinity of fairleads Check upper and lower elevator turnbuckles for safety and maximum of three threads show ing outside of barrel Ch
25. OF COMPASS WAM EOLA TYPE WITH 2073 ORACKE 7 MAY bes b USE SIS B 990 STREAMLINE COMPASS A Ini Luc Ger 2 gt 2 INSTALLATION INT 4 DLE Coen E MISI EA A A INN gt DAICH __ f ON al isse po for enr ri 8 x REET SEES De a _ es ER un SYS au 9 4 l lus 3rF R AL mss Q E 9 si sinn DO 4 F AcACI 7 METAL MH EA m a ATION SR EET nn 52540 1 WASHER POWs m 7 ER 51223110 TROW AIS HED SD 05 20 42 A TIMETER A ALT 8 FO SEG IMU 0400 202 TACHOMETER At fervare cdo RD MACH Screw f Be 29979 panei Bec m E RED iint sco RPM NEGUN To AN 513 652 Rio 2 RER 7 EA RcQ ASSEM pp 035924 BLOM E KL SHEED NUT DONE tnANI I REQ ERE AA Semi 2 s 1 NUT 3 E 74 rni ComBwELT S25 4G 21 NASHER li gt lt TO 315 2 C 7 2 64 SE DIOO 4 E Dre pecy NUT Cane Aman N i VO Een Pt e gt Dre E
26. S ve Ro Stute iN y im pim 35 gt 1 HE N 9 S la seht i HU HSS EE 8 N e ge h a gt E dressy f 4 3 jg i 4 rp i li GC lio 5 LN il 4 EN M ls 3 ss 30 LEVEL THRUST LINE LEFT RIGHT WING ARE RIGGED IN THIS MANNER PLANE TO BE IN LEVEL POSITION SURFACE OF STABILIZERS ARE PARALLEL TO THRUST LINE ANGLE OF RIB FOR CORRECT WASH OF WINGS SPECIFICATIONS and PERFORMANCE DATA Gross weight Landplane 1200 Lbs Seaplane 1278 Lbs Consult latest FAA 337 for empty weight and useful load as well as current weight and balance PERFORMANCE Never Exceed Speed Landplane 140 MPH Seaplane 129 MPH Cruising Speed 95 MPH Best Approach Speed 60 MPH Stall speed power off gross weight Approx 35 MPH Rate of climb full power gross weight 500 FPM Fuel capacity 18 Gal 12 gal fuselage tank at minus 9 and 6 gal wing tank at plus 24 aft of datum Fuel consumption 4 2 gal per hour Range 4 Hrs 30 Min 427 miles no wind condition Center of gravity range Landplane plus 14 8 to plus 17 9 Seaplane plus 14 8 to plus 18 3 Datum location Leading edge of wing Leveling means Upper surface of horizontal stabilizer GROUND HANDLING and GENERAL MAINTENANCE l Head the airplane into the prevailing wind and
27. T Dco 629I SHER 222121 HT n ANSG5 G 32NUT Wsis 6 6SCRE w ADDED 6209 CALLO las ro 4 0166 N oTt 414 E gt gt VIEW 9 lt A AD DED 7 EYI ven EE o D 1B Pas BUNA ras Gmb 7 A AT LETTE i poseer OBES G palena ne da clar mermar s peed EE NST me D WASHE on 64 Bel v FURNISHED WITH ENGINE BEA REO Pi gsi ARTE 4 ALL Aet preti LATEST y unm Vo SIGO 1 ES 2387 Noes pas CON T PARTS CAA MATA e A AVA Ne 34 BO UP NUTS ON AN 6 BOLTS To ATORQUE OF FROM 6 6 To IFN LBS REF NTAL ANIGO 3 3 Rs 5010 LE KY REED A PROPELLER SHAFT SEO MEW TS PROPERLY RUST PROoFED SS BE W ITH PAR AN EQUIVALENT THIANEOWIT EQUA B9093 feme pera 2C AB UNT PARTS of LEAOF REE GASOLINE TINE NT AL SECTION THRU RUBBER MOUNTING Arasten wir H AIRCRAFT MOEL 3 en FULL SIZE BATA ASSEM TACHOMETER TAPE 6 WRAPS An 2 Sc AIACFUSELA CE REF DUSALTERNATE ENGINE 0400
28. as lights or radio for more than a fifteen minute period If the ship is equipped with a generator charging rate should be held down either by a brake or adjustment and if the battery is charged outside charging should never exceed 2 1 2 amperes If the charging rate is excessive or if one cell is broken down the battery will boil causing acid to leave the battery and perhaps come in contact with parts of the ship which may result in a failure If the battery is charged out of the airplane there is not the danger of damage to the airplane but the battery is likely to be injured if the charging rate is excessive 14 5 i i Wise 1396 cmos Asse conten A010 5 1032 V SER T REF 2 SPO LAD wi TH paa KET 1 D 4 pa P A he wwe ye bull t 4 6 tra 5 4 d 4 B wen ARE SUPPLIED with MOUNT WE NUTS WLGRAL WIT TINNERPAN NUTS SHOULD BE ust ODA DELUXE INSTALLATION SCREW MY t DINE NUT ON OA WHEN Luft SweTcH WiTURe 2 Gr Akt Oniricp AW Le p 144 OW _ ASM WITH RUT 924 A 5 D 39790 USED 2071
29. cated ere of brake disi shields Screw in adjustment nuts until a heavy drag is produced on each shoe Back out each nut one half turn Apply brake firmly release and check for drag If still too much drag on either shoe the corresponding adjustment nut must be backed out one sixth turn at a time brakes applied released and checked for drag until sufficient clearance is obtained After a satisfactory adjustment is obtained the lock springs are engaged i in the holes in the adjustment nut BRAKE LINING INSTALLATION IN 6 SERIES BRAKE CAN BE INSTALLED WITHOUT ANY SPECIAL TOOLS Lightly grind ends of lining until lining is right length for a snug fit in drums Push lining in drum with gap in lining centered between the rivets which are 1 1 2 between centers Start by hand then place a board over lining and tap down until it is flush with edge of drum Using drum as a jig drill rivet holes through hune from auta des with an ordinary 9 64 drill Hemove lining from drum with a claw hammer or other flat ended bar using care to raise it evenly all around the circumference Countersink lining with countersink drill to correct size for rivet head 5 16 to 3 32 depth Replace lining in drum with holes aligned Place rivets drum and rivet by setting head of rivet on end of 5 16 rod held in vise and hitting tubular end of rivet with hammer Care should be taken not to hit the aluminum drum and not to hammer the
30. e For all operations 2300 r p m 65 hp 33 Propeller limits Airspeed limits range Empty wt C G range Maximum weight No of seats Maximum baggage Fuel capacity Oil capacity Control surface movements Serial Nos eligible Required equipment A 696 Static r p m at full throttle not over 2250 not under 2070 additional tolerance permitted Diameter not over 72 in not under 70 in Landplane Level flight or climb 105 m p h True Ind Glide or dive 140 m p h True Ind Seaplane Level flight or climb 95 m p h True Ind Glide or dive 129 m p h True Ind Landplane 14 2 to 420 0 Seaplane 14 2 to 420 0 with Edo floats item 205 14 6 to 420 0 with Heath floats item 211 Landplane 14 8 to 417 9 Seaplane 14 8 to 418 3 with Edo floats item 205 15 2 to 18 3 with Heath floats item 211 When empty weight falls within pertinent range computation of critical fore and aft positions is unnecessary Ranges are not valid for non standard arrangements Landplane 1200 1b Seaplane 1278 1b 2 23 Landplane 50 1b 40 Seaplane 30 1b 40 18 gal 12 gal fuselage tank at 9 and 6 gal wing tank at 24 4 qt 21 Elevators Up 27 Down 25 Elevator tab Up 25 Down 30 Ailerons Up 23 Dow 23 Rudder Right 26 Left 26 6402 and up Landplane 1 2 3 4 or 8 104 108 202 203 210 a 401 Seaplane 1 3 4 or 8 104 108 2
31. e connections for deterioration and clamp security Check intake system for leaks and cracks Clean air filter in kerosene and saturate with 10 oil and allow to drain before installation FUEL LINES AND STRAINER Check fuel lines for leaks and hose deterioration Check hose supports for security and chafing Drain and clean fuel strainer and resafety Check for stains around fuel system indicating leaks Check all connections for tightness EXHAUST STACK Check stack flanges for security cracks and leaks Remove all heater shrouds and inspect for corrosion cracks and leaks that might transfer gas to the cockpit particularly through the cabin heater system Check tailpipe and stacks for security at all clamps and joints Check cabin heater box and control valve for operation Check cabin and carburetor heat flexible tubing for and general conditions ENGINE CONTROLS AND FIREWALL Check firewall for open holes and gas leaks from engine Son ardent holes use zink chromate putty or some other recommended commercial brand Check all controls for grommets and sealing putty PROPELLER Remove spinner and check for cracks or dents in spinner and back plates Check propeller for separated laminations cracks loose metal tipping and protective finish Blade track within 1 16 Wood propeller hub bolts are to torque from 140 to 150 inch lbs Metal propeller hub bolts are to torque 350 to 375 inch lbs
32. e of the fin will accomplish this The wires should be rigged snug but not too taut low bass tone is satisfactory TAIL ASSEMBLY RIGGING Level the stabilizers at the rear spar with the airplane in level position Adjustment is accomplished by tightening and loosening of the tail brace wires Take up as many turns as the opposite wires are let out to keep the same tension on the wires Take up all slack and put a slight amount of tension on the wires On the test flight note the tail surfaces If the wires are too loose the surfaces will vibrate an undue amount CONTROL SURFACE TRAVELS IU MR 23 degrees 23 degrees down Elevators 27 degrees up 25 degrees down Elevator tab _25 degrees 30 degrees down Rudder__________________ 26 degrees R __ 26 degrees L RA AA A TAD T kike EZI 4 e ale Uv 1594 hov 02554 skoor V uiSTeusotv gt x 26127 FOFICLIN 13 4 4 47 4 T 4028 TEYE TT s9 38 a 6 ty diee 1 1 1 1 77771 1 71912 44 1 1 v ple ii 4 UD Y TES AS aneka 1 1 e a rae 3 A ejeerenv EE Je IT KAU CT TT fF 4 1 Ff 1 gotern
33. e scratches a coating of wax is applied again with a soft clean cloth A waxed surface is easier to keep clean and to a certain extent resist further scratching Apply a thin film of wax a bring to a high gloss by rub bing with a large pad of soft clean cloth CAUTION Rapid changes in temperature should be avoided i e moving from warm hanger to ex treme cold which will cause rapid contraction and breakage Allow fifteen minutes after Plexiglass has cooled before starting engine Vibration increases the possibility of break age during cooling TE WINDSHIELD The windshield may be changed by simply removing the bolts and clamps around its edges and replacing it with a new windshield GAS TANK On rare occasions it may be necessary to remove the gas tank To accomplish this re move the control wheels and the front instrument panel which will give access to the tie rods which support the tank Next remove the caps from the control column bearings and drop the column to the floor Several engine controls and attachments must also be re moved Remove the forward tie rod nuts next to the firewall and pull the rods The tank is then free to be removed down and out through the cabin TO ADJUST BRAKES MODEL 6C2B 6C3B 6C4B WHEELS 1 Remove wheel unhook brake springs and remove shoes 2 Loosen 10 24 nut on one end of each shoe enough so that end plate can slide and yet maintain some friction between adjustable end plate and
34. e various models eligible 37 not over 74 in not under 72 5 in All Except BC12D 4 85 amp BCS12D 4 85 10 Ib 46 BC 65 BC12 65 BC12 D amp BC12 Dl 20 1b 47 46 All Except BC12 65 21 lb BC12D 85 amp BCS12D 85 BC12D 4 85 amp BCS12D 4 85_ 18 1b 46 46 10 1b 46 BC12D 4 85 amp BCS12D 4 85 10 Ib 50 BC 65 BCS 65 BC12 D BCS12 D BC12 D1 amp 512 1 21 Ib BC12D 4 85 amp BCS12D 4 85_ 18 1b 50 BC12D 4 85 amp BCS12D 4 85 10 1b 50 Propellers and Propeller Accessories con 7 McCauley 1490 with the following limits BC12D 85 BC12D 4 85 _7 7 _8 8 _9 9 696 Static r p m at maximum permissible throttle amp amp setting not over 2350 not under 2170 BCS12D 85 BCS12D 4 85 No additional tolerance permitted 21 1b 46 21 1b 50 Diameter not over 71 in not under 69 5 in e Sensenich M74CK fixed pitch metal BC 65 Static r p m at maximum permissible throttle BC12 D BCS 65 setting 12 1 BCS12 D Landplane not over 2210 not under 1960 12 65 BCS12 D1 Seaplane not over 2210 not under 2070 21 1b 46 21 1b 50 No additional tolerance permitted om ds Diameter not over 74 in not under 72 5 in Sensenich M74CK 2 fixed pitch metal BC12D 85 BC12D 4 85 Static r p m at maximum permissible throttle BCS12D 85 BC 12D 4 85 setting not over 2350 not unde
35. eck stabilizer control for slippage Increase tension by tightening nut on idler pulley F AIRINGS Check all fairings for cracks and missing screws 28 WINGS AND AILERONS Wing fabric Check left and right wing fabric for holes cracks or checks in the finish and open drain grommets at each rib bay trailing edge Fabric usually deteriorates on the upper surface of the wing or along the trailing edge Install inspection grommets at drag wire fittings to inspect drag wires for tension and wing ribs and compression members for damage STRUTS LIFT Check right and left wing strut fittings for elongation by having some one lift up and down on the wing Check bolts for fitting attachment to the spar Check struts for dents or PRESS also sight down strut trailing edge to ascertain that Struts are straight Check strut end forks and fork lock nut WING BOLTS Check strut attachment bolts to be sure there are no threads in bearing that nuts are not bottoming on unthreaded part of bolt and bolts are properly safetied AILERONS Check both ailerons for wrinkles which are possible signs of structural damage Check each rib bay for an open drain grommet Check condition of fabric and finish refinishing any dope cracks checks or ringworm AILERON HINCES Check aileron hinge legs for security at rear spar and false spar Check hinge pins for wear and safety Worn or loose pins must be replaced AILERON CONTROLS Rem
36. ed April 7 1941 696 Landplane 14 5 19 7 Seaplane 15 1 to 420 1 Landplane 15 3 to 418 5 Seaplane 15 9 to 419 0 When empty weight C G falls within the pertinent range computation of critical fore anc aft positions is unnecessary Ranges are not valid for non standard arrangements Landplane 1100 1b S N s 1407 and up are eligible at 1150 1b Seaplane 1228 1b S N s 1432 and up are eligible at 1278 1b 2 23 30 1b 40 12 gal 9 See item 115 for auxiliary tank 4 qt 21 Elevators Up 27 Down 25 Rudder BC Right 26 Left 26 Ailerons Not available 1001 and up Landplane Items 1 2 3 4 or 8 104 202 203 210 a 401 Seaplane Items 1 3 4 or 8 104 205 401 L 2H 2 PCL SM Approved April 7 1941 Same as Model BC 65 except for minor structural changes and added elevator trim tab Engine Fuel Engine limits Propeller limits Airspeed limits range Empty wt range Maximum weight of seats Maximum baggage Fuel capacity Oil capacity Control surface movements Serial Nos eligible Required equipment Continental A 65 7 see item 114 for optional engines 73 min grade aviation gasoline For all operations 2300 r p m 65 hp Static r p m at full throttle not over 2250 not under 2070 No additional tolerance permitted Diameter not over 72 in not under 70 in Landplane Level flig
37. es 1 1 XO SAY 72412 2127 QOC A TI 1 a 1 1 E weile di pened 2 tw 77 Jua M 7 p Md lt lt Lo AS E Lir tem i oe Gs 2047 Wut 7 Waroasc MEM TAS ele s FE f F1 Fj TT GEN Ah S93 45 42 NY V 50 BPE 1431 927117154 get Mes OOM BVL wyi He v ng 3206 0 sae ru res Ge e BOR GLAD GM 9 outs tah 9 9 ee uen nd Maj 9294099 U sser O coP iVO 400144204 WINOT BF IST AI ssva mog 941 33 5 e 2 Ww ASES Qui rg 9 b W 2 a Met Sbu RO E DWE w t 7 oJU WV 7 LANG Y 5 V Fr 1097 4 Ae AQ 771 d is 2 M 12 OS S ES Tange 8 omes imma WINDOWS and WINDSHIELDS Plexiglass is used throughout assuring a minimum of discoloration due to exposure Door windows are aluminum reinforced sliding in felt insulated channel which is an in tegral part of the door frame assemb
38. ev 15 m 32 thru 40 THE TAYLORCRAFT 120 The Taylorcraft BC12D is a two place side by side high wing strut braced monoplane Basic construction consists of welded tube fabric covered fuselage Wings are fabric co vered wood spar with formed aluminum alloy ribs Power is supplied by the Continental A65 8 engine developing 65 horsepower at 2300 RPM The engine is insulated against excessive vibration with rubber bushings at the mo tor mount attachment points resulting in smooth noise free operation Any of several propellers may be used Refer to latest revised copy of FAA on Sheet 696 copy appears in the appendix of this pacem Unrestricted vision is attained through the use of a one piece moulded windshield large door windows and rear side windows Cabin control cables are concealed adding to the comfort of the spacious cabin Engine and flight controls are readily accessible from both seats The baggage compartment cap acity is 50 lbs 30 lbs for the seaplane version allowing the accommodation of small suitcases and other small items The shock absorbing system consists of bungee cord assembly attached to two exten sions of the main gear at the center line of the fuselage and the main structure of the fuse lage Ease in ground handling is assured with a steerable leaf spring tail wheel and pos itive acting mechanical brakes FUSELAGE FRAME Basically the fuselage frame consist
39. fuselage Four AN bolts attach the mount to the fuselage and four AN bolts attach the engine to the mount Hubber bushings are provided by the engine manufacturer to insulate further against vibration at the engine mount attachments PAFFLES Two side and two rear baffles make up the basic cylinder barrel and cylinder head pressure cooling system Aluminum alloy sheet is used in the fabrication of these parts Air upon entering the upper front of the nose cowling is forced around the cylinder fins of the engine assembly Air from the upper cowling and baffle chamber is passed through flexible aluminum tubing to muffs at the junction of the exhaust stack Y on each side of the engine The air is heated upon contact with the exhaust stacks the left muff and stack assembly providing heated air for cabin heater the right muff and stack assembly providing heated air for the carburetor heater assembly INTER CYLINDER BAFFLES Two baffles are incorporated below and between the cylinder heads and barrels on each side of the engine Supported with a spring and rod assembly these units complete the baffle system for the engine cylinders It is very important that these inter cylinder baffles are in place at all times to prevent leakage of the pressure in the upper baffle system resulting in improper cooling CRANKCASE BAFFLES These baffles are provided to force cool air around the crankcase of the engine Out side air enters through the lower fron
40. g edge of wing Upper surface of horizontal stabilizer Part 04 of the Civil Air Regulations effective as amended to May 1 1938 Type Certificate No 696 issued None Prior to original certification an FAA representative must perform a detailed inspection for workmanship materials and conformity with the approved technical data and a check of the flight characteristics Eligible for export to all countries subject to the provisions of Advi sory Circular 21 2 except as follows Canada Landplane and seaplane eligible with the exception of Model BC12 D1 Model 12 1 eligible provided auxiliary door item 601 is installed Skiplane not eligible However structure complies with Canadian requirements as follows 1 At 1100 1b maximum weight landing gear per dwg B A50 ski height 10 in tread 72 in centerline of ski 5 19 in out from center of bolt attaching diagonal stream lined member to axle 2 At 1150 and 1200 1b maximum weight landing gear per dwg B A515 ski height 9 tread 72 centerline of ski 5 19 in out from center of bolt attaching diagonal streamline member to axle 36 Equ pment Special Note when that item is installed A 696 A plus or minus sign preceding the weight of an item indicates net weight change Approval for the installation of all items of equipment listed herein has been obtained by the aircraft manufacturer except those items preceded by an asteris
41. gs to seat and allow the oil consumption to stabilize Control column amp Rudder bearings SAE 40 mixed with graphite Aileron pulleys SAE 10 Wheel bearings AN G 5 Universal joints amp control sprockets amp chain SAEs 10 oil Control column Powdered graphite or Dow DC4 compound Aileron bellcrank and hinges SAE 10 oil wheel axle bearing AN G 15 Door latches and hinges Powdered graphite Tail surface hinges Powdered graphite 23 INSPECTION INSTRUCTIONS ENGINE OPERATION Run engine to minimum 120 degrees oil temperature het full throttle static RPM con sult specifications for propeller used Check magnetos 75 RPM drop at 1800 RPM Check carburetor heat 100 RPM drop at full throttle Check ignition switch for operation Check idle RPM 550 600 RPM with carburetor heat off Oil pressure 10 35 lbs 30 good ENGINE MOUNTS AND ATTACHMENTS Check engine mount for damage and cracks at gussets or in corners Inspect protective finish on mount sand and touch up bare areas Inspect rubber shock mounts for rubber deterioration and tension Engine mount bolts should be tightened to 60 to 80 inch lbs Check mount bolts for safety COWLING AND BAFFLES Clean and inspect engine cowling for dents and cracks at hinges and reinforcement Check for tension adjustment on cowl doors at fasteners Tension prevents vibration and cowl cracking Check baffles for cracks and leather installation t
42. ht or climb 105 m p h True Ind Glide or dive 140 m p h True Ind Seaplane Level flight or climb 95 m p h True Ind Glide or dive 129 m p h True Ind Landplane 14 2 to 420 0 Seaplane 14 2 to 420 0 with Edo floats item 205 14 6 to 420 0 with Heath floats item 211 Landplane 14 8 to 417 9 Seaplane 14 8 to 418 3 with Edo floats item 205 2 15 2 to 418 3 with Heath floats item 211 Landplane 1200 1b Seaplane 1278 lb 2 23 Landplane 50 1b 40 Seaplane 30 1b 40 18 gal 12 gal in fuselage 9 and 6 gal in wing 24 4 qt 21 Elevators Up 27 Down 25 Elevator tab Up 25 Down 30 Ailerons Up 25 Down 25 Rudder Right 26 Left 26 2401 2501 2503 2504 2529 and up and all USAF numbers Use manufacturer S numbers if available Landplane 1 2 4 5 or 8 104 108 202 203 210 401 1 1 de 104 108 205 401 IV Model BC12 D 2 PCIM Approved November 23 1945 A Model BCS 12D 2 PCSM roved February 19 1946 Same as Model BC12 65 except for alternate tail surface revised aileron travel alternate one piece windshield and other miscellaneous structural and non structural changes Model BC12 D1 eligible as Model BC12 D when items 601 and 204 and 6 gal right hand wing tank are installed Engine Fuel Engine limits Continental A 65 8 see item 114 4 for optional engines 73 min grade aviation gasolin
43. k than the aircraft manufacturer This symbol denotes that approval has been obtained by someone other n item so marked may not have been manufactured under an FAA monitored or approved quality control system and therefore conformity must be determined if the item is not identified by a Form FAA 186 PMA or other evidence of FAA production approval So that all items of equipment might be in their proper categories the following items were renumbered as indicated _1 Item _2 Item 3 Item 4 Item _5 Item 6 Item _7 Item _8 Item _9 Item l was 2 was 3 was 4 was 5 was 6 was 7 was 8 was 10 Item 114 was 11 Item 115 was 12 Item 116 was 13 Item 117 was 14 Item 202 was formerly formerly formerly formerly formerly formerly formerly formerly formerly formerly formerly formerly formerly formerly item item item item item item item item item item item item item item 103 a 103 b 103 c 103 d 103 e 103 103 8 103 h 103 1 308 312 313 315 101 sje pe Ps pc Ts Pa ee Lm col Nil oM val el ol Sd H Of ool oM ta Item 203 was Item 204 was Item 206 was Item 207 was Item 208 was Item 209 was Item 210 was Item 211 was Item 212 was Item 401 was Item 402 was Item 403 was Item 601 was Item 205 was formerly formerly formerly formerly formerly formerly formerly formerly formerly former
44. ly Plexiglass is secured in the rear windows with Aluminastic compound and reinforced with aluminum alloy channel This method of installation insures a watertight seal The one piece moulded windshield provides unobstructed visibility never before offered in the light plane field CARE OF PLEXIGLASS To clean PLEXIGLASS flush the surface with plenty of water using the bare hand to feel and dislodge caked dirt or mud A grit free soft cloth or chamois may be used but to guarantee against the introduction of dirt and possible scratching the bare hand is prefer able Kerosene or hexene not aviation or ethyl gasoline may be used to remove grease or oil po NOT USE acetone carbon tetrachloride fire extinguisher or deicing fluids or lacquer thinners since these strong solvents attack and may soften the PLEXIGL ASS NEVER USE DIRTY OILY RAGS TO CLEAN PLEXIGL ASS DO NOT USE kitchen scouring compounds which contain abrasives and will scratch PLEXIGLASS If after washing no scratches are apparent on the Plexiglass surface apply wax as directed below However if the surface shows a number of minor scratches it is possible to remove or reduce most of them by applying a suitable polish by hand Use a small pad of soft grit free cloth Several applications may be necessary but the majority of scratches can be reduced and visibility markedly improved within a relatively short time To protect the surface and to fill in minor hairlin
45. ly formerly formerly formerly formerly item 102 item 107 item 151 item 302 item 304 item 305 item 316 item 317 item 320 item 321 item 105 item 306 item 314 item 106 Propellers and Propeller Accessories 17 1 Approved wood fixed or adjustable pitch See static limits under individual models and item 205 a for minimum static r p m limits for Models BCS12D 85 and BCS12D 4 85 Diameter Y Beech R003 controllable hub R 002 101 or R 003 100 blades R 002 205 72 Diameter 72 in Pitch at 27 in sta low 11 3 4 high 17 3 4 Pitch limits under indi vidual models are not applicable to these propellers Includes Beech mechanical propeller control McCauley 1A90 with the following limits Static r p m at maximum permissible throttle setting Landplane not over 2210 not under 1960 Seaplane not over 2210 not under 2076 No additional tolerance permitted Hartzell ground adjustable hub HA 12U blades 7414 to 6814 or 7214M to 6814M Eligible at diameter and static r p m limits shown above for fixed pitch wood models McCauley 1A90 with the following limits Static r p m at maximum permissible throttle setting not over 2250 not under 2070 No additional tolerance permitted Diameter not over 74 in not under 72 5 in Lewis L11CK 45 or any other fixed pitch wood propeller eligible for the engine power and speed and meeting static r p m and diameter limits noted for th
46. o prevent chafing MAGNETOS WIRING AND SHIELDING IF INSTALLED Check magneto for secure attachment Check breaker point housing for excessive oil Check points for gap pitting For correct gap Check plug wiring connections at magneto and insulation for deterioration and chafing Check for grommets at baffles and at firewall OIL DRAIN AND SAFETY PLUG Drain oil and check for metal particles Remove clean and check oil screen for metal particles drain plug and inlet oil temp erature housing Reinstall oil drain plug Change oil filter if installed and check flexible lines for deterioration 24 SPARK PLUG SERVICE Hemove plugs abrasive blast and clean Plugs with badly burned electrodes should be replaced Reset gap to 016 C26 plugs consult manufacturers charts for others m Heinstall using thread lubricant and new gaskets to prevent leakage and SEDE Torque to 300 to 360 inch lbs CARBURETOR AND HEATER Check carburetor for mounting security 1 Inspect carburetor bowl for cracks particularly at inlet Drain carburetor float chamber and check inlet finger screen safety Operate throttle in cockpit to be sure that throttle arm hits stops in open and closed po sitions without binding or sticking Check operation of mixture control if installed for binding or sticking and full rich position Inspect carburetor air box for security und cracks heater valve for full travel Check rubber intake hos
47. of seats 2 423 Maximum baggage 30 1b 40 Fuel capac ty 12 gal 9 See item 115 for auxiliary tank Oil capacity 4 qt 21 Control surface Elevators Up 225 Down 27 movements Rudders Right 26 Left 26 Ailerons Not available Serial Nos eligible 1001 and up Required equipment Landplane 1 or 4 104 202 203 210 a 401 Seaplane 1 or 4 104 205 401 II Model BC 65 2 PCIM Approved July 22 1939 Model BCS 65 2 PCSM Approved October 7 1939 Same as Model BC except engine installation Engine Continental A 65 1 see item 114 b for optional engines Fuel 73 min grade aviation gasoline Engine limits For all operations 2350 r p m 65 hp Propeller limits Static r p m at full throttle A 65 1 engine not over 2300 not under 2070 Optional engines not over 2250 not under 2070 No additional tolerance permitted Diameter landplane not over 83 in not under 70 in seaplane not over 79 in not under 70 in Airspeed limits Landplane Level flight or climb 105 m p h 91 knots True Ind Glide or dive 131 m p h 114 knots True Ind Seaplane Level flight or climb 95 m p h 83 knots True Ind Glide or dive 129 m p h 112 knots True Ind 32 range Empty wt C G range Maximum weight of seats Maximum baggage Fuel capacity Oil capacity Control surface movements Serial Nos eligible Required equipment III Model BC12 65 A Model BCS12 65 2 PCL SM Approv
48. ove inspection covers and check the two cables in each wing for interference and chafing Check the two pulleys in each wing for condition wear and safety Lubricate pulley bearings Check travel 23 degrees up 23 degrees down Check the four aileron horn bolts for wear threads in bearing and safety Check the six turnbuckles in the center top of fuselage for safety and not more than three threads showing outside the barrel To locate broken strands at fairleads or pulleys slide a cloth over the cable All cables with broken strands are to be replaced 29 WING ROOT FAIRINGS Check left and right wing root fairings for tension Check all metal screws for security and the fairing for cracks EMPENNAGE STABILIZER Check stabilizer fabric condition and drain grommets for restrictions If the fabric strength is suspected a Seybooth tester may be used to accurately test the strength Lift up and down on the stabilizer checking for excessive play FIN Inspect vertical fin for fabric condition and finish Check for wrinkles dents and signs of internal damage RUDDER Inspect the fabric cover on the rudder for fabric and dope condition Check bottom of rudder for an open drain grommet Check rudder for alignment and possible internal damage usually indicated by a wrinkle in the fabric Inspect rudder hinge pins for wear and safety Check hinge bushings for play These bushings are pressed in and should be replaced
49. r 2170 21 1b 46 21 1b 50 No additional tolerance permitted Diameter not over 72 in not under 70 in Engines and Engine Accessories No aircraft of these models shall be eligible for original certification with single ignition engines after August 1 1941 In addition no aircraft of these models shall be eligible for recertification with single ignition engines unless such aircraft were either previously certifi cated with single ignition engines or were originally certificated prior to August 1 1941 104 108 109 110 111 112 113 10 114 11 115 12 116 13 117 Carburetor air heater dwg BC L601 Enclosed engine cowl all except BC BCS BC 65 BCS 65 McDowell starter installation BC 12D BCS 12D BC12D 85 BC A6014 nose cowl must be installed McDowell starter installation using horizontal operating handle BC12 D BCS12 D Exhaust muffler Ryan Aero Co dwg 52112 with items 114 b 1 and 2 only Oil filter Fram PB 5 Kit No 510 Weight includes 1 qt oil Fram Instln dwg No 61544 BC BCS BC12 65 BCS12 65 b Fram Instln dwg No 61524 BC12 D BCS12 D Bc12 D1 BCS12 D1 Starter Delco Remy 1109656 BC12D 4 85 only Engines Continental see Engine Specs Nos 190 and 205 a Models BC BCS 5 1 50 2 2 50 3 50 8 3 50 4 4 50 5 5 50 7 b Models BC 65 BCS 65 1 A 65 3 A 65 3J A 65 8 or A 65 8J pas Engine limits for
50. r panel placard and full travel of heater butterfly valve Check ignition switch for panel and terminal security Check for placard Off left right and both 26 RUDDER PEDALS AND LINKAGE Check rudder pedal assembly for play and travel freedom Lubricate hinges and torque tube bearings and check for safety Check rudder pedal return springs for attachment CABLES AND PULLEYS Check all cables for broken strands Remove butt fairings and check top deck aileron pulleys for wear and security Check aileron pulleys at both ends of panel Remove floorboards and check pulleys FLIGHT CONTROL OPERATION Check aileron rudder and elevator controls from cockpit for smooth operation Check wheel for neutral position with control surfaces streamlined TRIM TAB CONTROLS Check stabilizer trim control for smooth operation Check indicator against stabilizer for proper position FUEL SELECTOR VALVE Check fuel valve for smooth operation Check placard for and positions Check valve for leaks LANDING GEAR Shock cord for broken strands and elongation AXLES AND WHEELS Remove wheels wash check and relubricate bearings Check brake shoes for wear and drums for scoring Install wheel and axle nut only tight enough to remove end play TIRES AND FAIRING Check tires for 20 lbs of air pressure Replace tires that have cord showing Check gear fairings for security and chafing 27 LANDI
51. rivet more than necessary as there is danger of distorting the drum with excessive pounding NOTE As brake lining service shops have a standardized set up for automobile brake work and do not care for special jobs it is recommended that this work be taken to a small machine Shop or garage where there is a drill press or electric drill available If a special long shank countersink is used it is not necessary to remove the lining from the drum in order to countersink it Information for any service shop tools can be furnished upon request 13 ELECTRICAL EQUIPMENT All models of Tayolrcraft have the wings wired for lights and on those that are not equipped with navigation lights the wires are strung through the wing and taped to the wing bow at the extreme tip The fuselage i is not wired unless wiring is ordered at the factory and it vill be necessary to wire the fuselage and rudder if are installed The battery is placed on the floor immediately ahead of the seat slightly to the left of the center of the ship and is grounded to the fuselage framework under the seat The sy stem is fused in the pcsitive lead where it comes out of the battery box and the fuse should always be replaced by a fuse of the same capacity as the original installation If the ship is equipped with a battery care must be exercised in charging as small aircraft batteries should not be charged over 2 1 2 amperes in excess of any outside draw such
52. s of 1025 and X4130 acetylene we to form the body structure of the fuselage Tubing members are shown on the accompanying drawing in order that they may be iden tified in the event repairs are necessary in the field Tubing size and type are shown on the fuselage frame drawing The entire fuselage structure is coated with rust preventative primer at the factory Upon making any repairs in the field care should be taken to thoroughly clean the repaired areas and recoat with rust preventative primer Zink chromate or palidin has been found to be an excellent corrosion proofing and adds materially to the life of the structure AN 4 380 4 2 Pin qanm 426 wasi Grita 32 22 x QETAN PULL y 4 CABLES ATTACH Te Mee INSTA 0481 4 CABLE ASEM UNNERSAL RINT 2 un e heer m gt 110805 Anis aee aeg 619 44 116 PULLSY 4215 400 A A BUSHING 4319 8wvr An380 2 2 Pret ante A 10 pvurvame iy N Arat q Spobr MB AZO BAR 11 2 22 CONTROL ASIEN K 17CLAMP 8 216 SHm RIQ BB A2 BAR ASSUM L A 1094 BEARING Ho uro IRER 0 2 0 BOLT ING 4 8 8 Bo17 4 c 9 PUUEY A
53. set the controls by securing the wheel all the way back with the safety belt Rudder controls do not normally require locking as rudder is held in place by the tail wheel springs However for long term storage outside or where it is suspected the wind could change and blow from the tail a clamp can be used to secure the rudder Two pieces of wood felt covered with a screw and wing nut should do the job very well This assembly is fastened at the bottom of the rudder the screw going between the vertical stabilizer and rudder 2 If high winds are anticipated or airplane is to be parked unattended it is recommended that the airplane be moored To moore airplane attach ropes to tail wheel leaf springs and to mooring rings optional equipment near each wing strut end Stake ropes to the ground leaving enough slack to allow for shrinkage of ropes due to moisture or rain If your airplane is not equipped with mooring rings tie the mooring ropes to the outer end of the front lift strut If mooring stakes are not available and new ones are being driven do not drive straight into the ground directly under the tie down point but drive diagonally into the ground several feet away from the tie down point so as to fix a 90 degree angle between the rope and the stake when tied LEVELING and RIGGING PROCEDURE Level in a fore and aft direction by supporting tail on stand and placing bubble level on the horizontal stabilizer When bubble is centered in level
54. t nose cowling building up pressure at the front of the crankcase HEAT CONTROL Flow of the heated air to the carburetor heater and cabin heater is controlled from the engine control panel CARBURETOR HEATER This assembly controls the flow of heated air from the baffle system to the carburetor venturi A butterfly valve connected to the carburetor heater control cable directs the air flow to the carburetor when heat is desired or through the outlet at the bottom of the air scoop assembly when not in use 19 Proper functioning of the heater butterfly valve may be determined as follows Set throttle at cruising RPM 2150 RPM Pull heater contia on RPM should drop not less than 75 RPM not more than 200 RPM If no change is noted check butterfly valve for proper seating A65 8 Continental Service Instructions Overhaul Manuals and Parts catalogs are avail able at a nominal price complete overhaul of these engines is not considered a major repair and any A amp P mechanic is licensed to do this work provided he has the proper equipment STARTING and STOPPING ENGINE Be sure area is clear and only qualified people start engines Always seat operator in the aircraft Do not try to start engine with tail wheel tied down and assume this is safe Aircraft have been known to slip the tail ropes and cause extensive damage STARTING PROCEDURE Switch off Fuel on Brakes on Prop man commands Switch off Operator
55. x 1200 1b g Federal SA 1 max 1200 1b h Aviation Service B max 1650 1b i Richards 1 B max 2220 1b j Washington Aircraft max 1200 1b k Heath 655 max 1210 1b 1 Federal SC 2 max 1650 1b m Aviation Service max 1100 1b n Federal 1 max 1300 1b o Jacobsen formerly Escanaba EAS 100 1200 1b p Richards 1 A 1600 1b q Marston MFS 1600 max 1600 1b r Heath 725 max 1450 1b s Aero Sales amp Service 5 6 00 max 1320 1b t Jack Carr Service 16 max 1600 1b u Fairbanks MF 5 max 1310 1b v Heath 725A max 1450 1b w Federal SK4 1 max 1400 1b x Call S2 max 1800 Ib y Federal A 1500 max 1500 1b Federal Instin dwg 11R232 39 Landing Gear and Floats con 21 209 con 2 Federal A 1500A max 1500 1b Federal Instln dwg 118232 aa Federal A 1850 max 1850 1b Federal Instln dwg 11R232 ab Federal A 2000 max 2000 1b Federal Instln dwg 11R232 ac Federal A 2000A max 2000 1 Federal Instin dwg 118232 ad Federal CA 1850 6 1850 1 Federal Instln dwg 118232 e ae Wesco A 15 Western Aircraft Equipment dwg 148 202 203 af Wesco A 20 Western Aircraft Equipment dwg 148 202 203 22 210 Two main wheel tires 6 00 6 Type III with regular tubes a 2 ply rating b 4 ply rating 23 211 Heath 1460A float installation 172 1b including

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