OWNERS MANUAL
Contents
1. _ THIS MANUAL IS A DIRECT COPY THE ORIGINAL WE ASSUME NO RESPONSIBILITY FOR THE CONTENTS UNIVAIR AIRCRAFT CORPORATION INSTRUCTION MANUAL MODEL B amp B12 FOREWARD This instruction book has been compiled with the view of giving the private owner or operator of Taylorcraft airplanes sufficient knowledge of the construction operation and care of the airplane so that the service and satisfaction built into it may be obtained Carelessness in one form or another is the true source of practically all airplane mishaps Neglect of or improper inspection on the ground is the hardest form of carelessness to over come While we all condemn reckless flying improper care on the ground cannot be too strongly pointed out as the most dangerous form of recklessness Be sure therefore when taking delivery of your Taylorcraft airplane that you know how to care for it and if you cannot give it thorough and regular care put it in the hands of a competent mechanic and give him free use of this Service Manual In case of doubt concerning any service or operating problems not covered in this manual or obtainable through our sales representatives consult our Service Department which is maintained to assist you in obtaining economical and efficient service from your Taylor craft SERVICE The Taylorcraft distributors and dealers are rapidly building up their Service Departments Parts are available and they have efficient licensed mech2. 2 of 2 50 10 6 43 also be checked This radius should be 5 64 A convenient method of checking would be to deter mine that the shank of a 5 32 drill will bottom in the groove If the groove is undersize the pulley should be replaced Record of such replace ments should be made in the Aircraft Log Book Parts required to comply with this bulletin can be determined only after inspection of the air craft Any replacement pulley which may be re quired can be obtained from the manufacturer at cost plus postage upon notification of its diameter and position in the airplane the ship Serial no date of manufacture and NC numbers None If you have sold your airplane please forward this bulletin to the new owner Harold White Service Manager 14 OS 6 7 oF sky ATawassy 31x y 79 INIONVT YO LY 15 5 Arswvws 8036 NN em 4 22 400 STABILIZER 8 2 8 A aaa 445 CES TAIL SURFACES 16 812 LEFT WING PANNEL RUDDER HORN 18 AES 6888 AY a N i mn Wa B 805 9024 SPER 7 THRUST LINE EEE oar Anf ptor NOE eto AnS A LEFT BRIGHT WING ARE RIGGED IN IWS MANNER TO
3. 6 U linen rib cord in compliance with Taylorcraft Service Bulletin No 30 Was SPECIAL NOTE 14 of A 1379 SPECIAL NOTE 2 January 2 1941 Applies only to models BC 65 and BCS 65 Replace coil in aircraft equipped with Bendix Scintilla SF4L 8 SF4L 9 SF4R 8 or SF4R 9 magnetos in accordance with Airworthiness Maintenance Bulletin No 33 Was SPECIAL NOTE 14 of A 1379 SPECIAL NOTE 3 February 5 1941 Federal SC 1 and SC 2 skis used on aircraft certified as skiplanes must incorporate reinforced channel in accordance with Federal Aircraft Works Service Letter No 2 Federal Aircraft will supply material and instructions upon request Was SPECIAL NOTE 15 of A 1379 SPECIAL NOTE 4 February 5 1941 Applies to all models except BC12 65 and BCS12 65 Inspect weld attaching central column universal to aileron control sprocket shaft If weld is crack ed rework or replace with a new factory part Was SPECIAL NOTE 16 of A 1379 SPECIAL NOTE 5 February 5 1941 Applies to all models listed except BC12 65 and BCS12 65 Inspect fuselage members adjacent to aluminum door jamb cover for wear produced by vibratory action of jamb on structure Trim jamb to provide a minimum of 1 16 clearance at all points Weld patch plates to fuselage members if wear appears excessive Was SPECIAL NOTE 17 of A 1379 SPECIAL NOTE 6 February 5 1941 Applies to all models listed except BC12 65 and BCS12 65 Make an entry in the log book outlining the e
4. 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 An ordinary level used along the rear tube of the stabilizer and rear tube of the fin will accomplish this The wires should be rigged snug but not too taut A low bass tone is satisfactory SUPERSEDES A 1379 DEPARTMENT OF COMMERCE AM 92 FOR MODELS LISTED CIVIL AERONAUTICS ADMINISTRATION TAYLORCRAFT WASHINGTON BC BCS BC 65 gt TC 696 BCS 65 BC12 65 BCS12 65 September 1 1942 AIRWORTHINESS MAINTENANCE INSPECTION NOTES IT IS THE OWNER S RESPONSIBILITY TO MAINTAIN HIS AIRPLANE SO THAT IS ALWAYS IN AIRWORTHY CONDITION COMPLIANCE WITH THE NOTES CONTAINED HEREIN IS CONSIDERED NECESSARY FOR PROPER MAINTENANCE This paper should be placed in your airplane of the above model with the airworthiness certificate or in the log book The superseded issue If any may then be discarded In the case of Air Carriers the NOTES may be kept at the operator s main base revision accordance with these NOTES must be made at the next periodic inspection and in the case of the INSPECTION 5 at each subsequent periodic inspection or at the interval stated in the note SPECIAL NOTES need be complied with once only The aircraft and engine mechanic making the periodic inspection must make an entry in the airplane or engine log book attesting to his insp
5. frequently at the top of thelanding gear between the fittings on the fuselage and landing gear On planes equipped with a swivel type tail wheel oil the swivel bearing and grease the ball bearings in the hub of the tail wheel Note IT IS IMPORTANT that the bumpers on the fuselage truss under the shock cords be inspected every 20 hours and replaced when needed PARACHUTES Provisions for parachutes have been made By removing the four bolts the nuts are rivet ed in place on the front edge of the seat and making one half turn of the leading edge frame and replacing the bolts the seat is lowered ample to accommodate parachutes 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 rareoccasions it may be necessary to remove the gas tank To accomplish this remove 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 removed Hemove 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 ADJUSTMENT OF BRAKE SHOES ON MODEL 6C2HB 6 AND 6 5 WHEELS 1 Unhook lock springs from adjustment nuts located outside of brake dust shield 2 Screw in adjustment
6. those airplanes of the Model A and B Series which still incorporate control pulleys made of micarta easily recognized by their black color and glossy finish Inspection to be made and any change required by Description of Change below to be accomplished by the owner As precautionary measure the manufacturer re quests that at the next periodic inspection on all Model A and Model B aircraft it be determined whether any of the pulleys over which flight con trol cables pass are made of micarta These pul leys can easily be distinguished by their glossy black color as compared with the usual brown color for similar pulleys in later models Record of the inspection made in accordance with this bul letin and the results thereof should be record ed in the Aircraft Log Bock If there is no black pulley in the system this should be noted in the Aircraft Log Book and no further action need be taken to comply with this bulletin If black pulleys appear in the system their position should be noted in the Aircraft Log Book and on this and subsequent periodic inspection they should be carefully inspected to determine that they are sound and free from splits or cracks par ticularily in the groove through which the cable runs If such cracks appear the pulleys should be replaced immediately The groove radius should Page No Bulletin No Date Parts Reguired Per Airplane Special Tools Attention
7. BE IN LEVEL POSITION ARE PARALLEL SURFACE OF STABILIZERS THRUST LINE 20 aa ha as DN ere 21 AILERON LUBRICATION d UOLVA3713 1131 219 29219 DPV ad 22 3 8 I a li fo 21d Less 218 255 28 RE ee 173 FUSELAGE ASSEMBLY 7 A 1525 age Ii 7 i uu a n T TOM JEW 3 l1 J 141 IA ix MODEL B LL SIDE sto 1527 FUSELAGE ASSEMBLY 8 2 Als STATION NUMBERS ARE FoR REFERENCE s te 490 e REY q AAL Afi u p np M ODEL B2 al Brom me Mew 24 SM EAT 850 064775 gt IR 229 0 E AN 18 243 scd 9 58 FIN ASSY 43 43 en 26 AW Sg 2707 ASSY NJ 2 1895 0 99 28 lt 27
8. EM The fuel system on the B12 consists of a twelve gallon terneplate gas tank located in the front of the fuselage and a six gallon tank in the right wing The valve for the wing tank is located above the corresponding door The wing tank should be emptied when the main tank is half empty Fuel is gravity fed to the carburetor small copper screen is placed in the outlet of the tank Flexible hose connections are used between the tank filtrap and engine A small copper line is attached to the filtrap inlet to deliver gas through the primer to the cylinders for starting The fuel system on the Model B consists of a twelve gallon tank in the front of the fuse lage as standard and a six gallon auxiliary tank can be installed behind the seat as extra equipment ENGINES The engines are wet sump motors having an oil capacity in their crankcase for one gallon of oil each ASSEMBLY OF LANDING VEES The landing vees are made right and left and the bearings should be oiled or greased just before assembly With the fuselage supported at the front end the vees are then put in place and assembled with the bolts provided Tighten the bolts to a snug fit but not tight enough to resist the motion of the landing gear Looseness permits excessive wear of the fittings Install one shock cord then the safety cable followed by the second shock cord ring for each vee To install wheels place the tapered roller bearings in their proper positions insta
9. anics When in need of service contact the nearest T aylorcraft representative The factory maintains a Service Department to assist the representative and you to obtain the most service from your airplane HOW TO ORDER PARTS When ordering parts always give the following information to the Taylorcraft represent ative 1 The model Serial No NC No and engine Serial No of your plane The model and serial number can be found on the metal plate attached to the floor board on the right side of the cabin 2 The part number and name of the piece wanted whenever possible See Diagram If you cannot find the part number give as complete a description as possible of the part required and location stating right or left A sketch is frequently of assistance in filling orders 3 Quantity needed THIS IS IMPORTANT 4 If representatives do not carry the part needed state to whom the shipment is to be made address to where parts are to be sent transportation Parcel Post Air Mail Air Express Railway Express or Freight 5 Parts will be shipped C O D unless credit is established or a certified check or J A money order accompanies the order 6 Parts ordered to be shipped by Air Express must be accompanied by a money order or a certified check NOTE In order to avoid delays all communications should be addressed to the atten tion of the Service Department RETURN OF PARTS Parts returned fo
10. ection in compliance with these NOTES In the case of Air Carriers compliance may be noted in the maintenance base records The NOTES listed below are based on service experience and are forwarded in an endeaver to assist in maintaining the airworthiness of your airplane If you have sold your airplane of the above noted model please forward this list to the new owner INSPECTION NOTE 1 August 7 1940 Applies only to airplanes equipped with Freedman Burnham propeller INSPECTION REQUIRED EACH 10 HOURS OF OPERATION Inspect Freedman Burnham propeller models P 201 72 and P 201 70 for cracks and loose rivets after each 10 hours of operation in accordance with Airworthiness Maintenance Bulletin No 31 Was SPECIAL NOTE 12 of A 1379 INSPECTION NOTE 2 September 4 1941 Ascertain that the adjusting nut located at the bottom of the glass bowl of the fuel strainer is positively safetied in position and also that the cork gasket between the glass bowl and screen is in serviceable condition Was SPECIAL NOTE 22 of A 1379 d 5 23530 The following NOTES need be complied with once only 10 AIRWORTHINESS MAINTENANCE INSPECTION NOTES Page 2 of 3 pages AM 92 SPECIAL NOTE 1 July 2 1940 revised December 29 1941 Applies to all models listed except 12 65 and 512 65 On serial Nos between 1001 and 1970 inclusive restitch the wing ribs using a
11. ed to an H column to control the elevators and ailerons The control wheel shafts slide through composition bearings and are connected to the control column by a universal joint These wheels may be removed by removing the bolt connecting the shaft to the universal joint Always remove the rear hub of the univer sal joint when removing duals The right set of rudder pedals may be removed by removing one bolt from each pedal Flexible steel cables are used throughout the control system to transmit motion All pull eys are mounted on graphite bronze bushings The trim tab control on the Model B is below the left seat and is to compensate for slight nose or tail heaviness To correct for nose heaviness the handle is raised and to correct for tail heaviness the handle is lowered The trim tab control on the Model B12 is located on the ceiling and is turned clockwise to correct for nose heaviness See diagram for lubrication and adjustment of trim tab 3 ENGINE CONTROLS The engine controls consist of an ignition switch throttle a carburetor heater gas shut off and primer There is an altitude adjustment on the Continental carburetor equipped engines and available on the Lycoming and Franklin at extra cost Operation instructions for the controls are shown on the instrument panel or control knobs The throttle is located at the lower center of the instrument pane and is of the push pull type The throttle is pushed forward to open FUEL SYST
12. lar drag link transmits the motion to the ailerons TAIL SURFACES The tail surfaces are built up with steel tubing frame work and formed steel ribs The two stabilizers and the fin are bolted to the fuselage and wire braced The two elevators are bolted at the horn so that they act as a single unit The fuselage fin and stabilizers are equipped with replaceable bronze bushings which should be oiled frequently LANDING GEAR The landing gear is built of tubing forming two separate units and are individually hinged to the fuselage Each has replaceable bronze bearings which should be oiled frequently See diagram No part of the landing gear is heat treated The shock absorbers for each side consist of two 9 16 shock cords There is a rubber bumper installed on the shock truss in the fuselage which separates the landing gear and the fuselage structure at the point where the shock cord is attached stop cable is also provided at this point to prevent the Shock cord being stretched beyond its elastic limit Roller bearings are installed in the wheels The brakes are cable controlled and of the internal expanding type with the lining on the drums Standard planes without brakes are equipped with a spring leaf tail skid When brakes are installed a special spring with a full swivel tail wheel is used in place of the spring and skid A steerable tail wheel is also available CONTROLS The control system has dual wheels attach
13. les There is one pulley on the left side of the floor carrying the other rudder cable These pulleys should be oiled and checked frequently There are also cable guides in the rear of the fuselage that may be seen through the rear zipper opening that should be checked every 20 hours for frayed cables There are also cable guides under the seat which may be inspected by lifting the edge of the seat can vess Inspection covers at the rear of the fuselage provide access to the elevator control cable ends and these points should be oiled frequently CONTROLS IN WINGS The aileron control horn which is located in the wing at the center aileron hinge bracket may be reached by removing the cover plate on the top of the wing Oil placed in the hole of the control horn will lubricate the bearing The ball joints and drag link at this point should be checked for looseness Looseness due to wear may be removed by tightening the ball stud seat in the end of the drag link The bronze bearings in the aileron hinge brackets should be oiled frequently When wear occurs here new bushings and hinge pins be installed SURFACES The hinge joints on all tail surfaces should be oiled frequently When looseness occurs new bushings and hinge pins will correct this condition LANDING GEAR The roller bearings in the landing wheels should be lubricated with graphite grease being careful not to get grease on the brake drum or band Oil the hinge bearings
14. ll special lock washer and tighten nut sufficient to hold the wheel snugly in place Be care ful not to cause any binding ASSEMBLY OF WINGS The wings are attached to the fuselage through the hinge fittings with the bolts provided Hold or block the wing in its approximate position while the wing struts are installed with the bolts provided The proper amount of incidence is built into the fuselage fittings and the dihedral is fixed by the length of the front struts The rear struts are adjusted at the factory and must be assembled as tagged After the plane is out in service it may change balance slightly by developing wing heaviness To correct this remove the bolt at the upper end of the rear wing strut of the opposite of that which is heavy and unscrew the plug 1 2 turn or more until the balance is corrected After an airplane has recieved a major overhaul it may be advisable to check the complete rigging of the airplane To accomplish this level the plane laterally by attaching a cord from wing tip to wing tip over the front spar Place a line level on the center of the string and level the plane by blocking up the low wheel by a jack or other means Level the plane longitudinally by placing a level on the stabilizer close to and parallel to the fuselage Use a 30 level to check the incidence at the tip of the wing readings to be taken on the first full rib from the tip By placing the edge of the level at the forward part of the rear spa
15. nuts untill a heavy drag is produced on each shoe Back out each nut one half turn 3 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 untill sufficient clearance is obtained 4 After a satisfactory adjustment is obtained the lock springs are engaged in the holes in the adjustment nut BRAKE LINING INSTALLATION IN 6C SERIES BRAKE _ Can be installed without any special tools 1 Lightly grind ends of lining untill lining is right length for a snug fit in drums 2 Push lining in drum with gap in lining centered between the rivets which 1 between centers Start by hand then place a board over lining and tap down untill it is flush with edge of drum 3 Using drum as jig drill rivet holes through lining from outside with an ordinary 9 64 drill 4 Remove lining from drum with a claw hammer or other flat Ended bar using care to raise it evenly all around the circumference 5 Countersink lining with countersink drill to correct size for rivet head 5 16 to 3 32 depth 6 Replace lining in drum with holes digred 7 Place rivets in drum and rivet by setting head of rivet on end of a5 16 rod held in a vise and hitting tubular end of rivet with hammer Care should taken to hit the aluminum drum and not to hammer the rivet m
16. ore than necessary as there is danger of distorting the drum with excessive pounding If a special long shank countersink is used it is not necessary to remove the lining from the drum in order to countersink it 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 ELECTRICAL EQUIPMENT All models of Taylorcraft after serial No 2529 are 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 wires on the fin are taped to the top edge just ahead of the trailing edge 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 Ihe system is fused in the positive 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 air craft batteries should not be charged over 2 1 2 amperes in excess of any outside draw such 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 b
17. r along the rib mentioned with the level in horizontal position there will be a gap between the front edge of the level and the wing of 1 5 16 The plug at the top of the rear strut is used for adjustment The tail surfaces are bolted to the fuselage and rigged level and plumb with the wings with an ordinary level used along the rear tube of the stabilizer and the rear tube of the fin The wires to be rigged snug but not too taut low bass is satisfactory The control cables are provided with turnbuckles for proper adjustment of the rudder and elevators When rigging the ailerons with the wheel centered adjust the cables through the zipper in the back of the cabin so that the trailing edge of the aileron is in line with the trailing edge of the wing All cables should be adjusted until they are snug NOT TIGHT If the cables are too tight there will be too much drag in the aileron control STARTING Before the start of any flight a complete check should be made of the quantity of gasoline and oil contained in the tank or motor Also it is recommended that the filter bowl be cleaned frequently because water and dirt will collect there When starting always have a competent person at the controls Be sure the gas is turned on and with the switch IN THE OFF POSITION give the primer one or two shots then pull the prop through four or five times Put the switch in the ON position opening the throttle a little and pull the prop through q
18. r replacement repair or credit should be accompanied by a letter stating the reason for return with the plane serial number and number of hours the parts have been in service All possible information that will assist us to determine the cause of the trouble is essential Transportation must be prepaid PRICES Prices are subject to change without notice GENERAL DESCRIPTION The Taylorcraft Model B or B12 is a high wing strut braced two place cabin monoplane and is available as a land plane or seaplane The Model or B12 is obtainable with the following 65 horsepower engine installations Lycoming 0 145 B Franklin 4AC 176 B2 Continental A 65 8 SPECIFICATIONS General Models Wing Span died pde dde Sc dp e vr 36 ft Height Tall Down cau aeta 9 18 in Ming Chords OF in Length Overall 2 4 35 ne ae 21 ft 9 in Medal A AR dica as 1 Wheeler nu enc neces N dn E Shinn Dc EL 6 00 x 6 2 ply Tail Wheel ua es ico an daa 6 x 200 FUSELAGE The fuselage is composed entirely of steel tubing welded into a unit structure All members are of S A E No 1025 or No 4130 steel All members are jig cut and in case of replace ment they can be furnished ready for welding into the fuselage All fuselage tubes are given a protective coating of primer Saltwater seaplane fuselages require extra fittings and
19. rake or adjustment and if the battery is charged outside charging should never exceed 2 1 2 amperes If the charging rate is excessive 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 8 TAYLORCRAFT MODEL amp B12 RIGGING INFORMATION As the airplane is built entirely in jigs it requires no rerigging 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 A long screwdriver may be used to move the adjusting 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
20. special corrosion protection Fresh water fuselages have no special corrosion protection Care should be taken to give re placements for seaplanes the same corrosion protection as the original material All saltwater seaplane fuselage tubes are sandblasted primed coated with enamel and oiled on the inside Information concerning the size and material on any member can be obtained from the Service Department m WINGS The wings are a built up structure having two solid spruce spars braced with steel tubular drag struts and steel tie rods The ribs are built up of riveted aluminum sections and nailed to the spars The leading edge is formed of sheet aluminum fastened to the ribs by self tapping metal screws The wings are covered with medium airplane fabric which is sewed to the ribs with 6U commercial gray waxed linen right twist rib cord reinforced by means 3 8 herringbone tape and covered with 1 1 2 pinked edge wing tape Seven or more coats of high grade airplane nitrate dope provides the cloth with tautness and finish AILERONS The ailerons are also a built up structure with a spruce spar and with stamped aluminum ribs Aluminum leading edge is fastened to the ribs by means of self tapping metal screws and nailed to the spar They are fabric covered and doped The ailerons are attached to the wing through steel hinge brackets which are bolted to the rear spar in the wing The center hinge bracket carries a horn from which a tubu
21. uickly If the engine fails to start repeat the operation If the engine loads up put the switch in the OFF position open the throttle wide and turn the prop backwards a few times to clear the engine Then start in the conventional manner CAUTION Always block the wheels when starting the engine unless an experienced pers on is in the cabin controlling the brakes POINTS LUBRICATED EACH PERIODIC INSPECTION CONTROLS IN FUSELAGE In the fuselage the main points to be lubricated are in the control system The shafts of the control wheels slide through Bakelite bearings A small amount of grease on the shafts will make a smoother working control at this point The following points on the Control Column should be oiled frequently 1 The universal joint at the top of the control column 2 There is also an oil hole on the top of the control column to lubricate the shaft of the universal joint 3 The sprocket chain links 4 The bearings at the bottom of the control column 5 pulley bearings and faces of pulleys NOTE There are two pulleys for the aileron cable at the top front of the cabin and two more at the rear of the cabin The front two can be reached through the zipper openings in the top of the cabin lining and the other two through the zipper opening in the back of the cabin On the right side of the floor just in front of the door are three pulleys carrying the eleva tor cables and one of the rudder cab
22. xtent of the changes made to insure proper engine _ idling operation in compliance with Airworthiness Maintenance Bulletin No 41 Was SPECIAL NOTE 18 of A 1379 SPECIAL NOTE 7 July 11 1941 Install the stainless steel oil filler cap spring Continental Part No 22060 for the following engines in accordance with Continental Service Bulletin No 40 3 Engine Model Engine Serial No 50 Series Up to No 1332 Inclusive 65 Series Up to No 4304 Inclusive And all fuel injection models Was SPECIAL NOTE 19 of A 1379 5 23530 11 AIRWORTHINESS MAINTENANCE INSPECTION NOTES Page 3 of 3 pages 92 SPECIAL NOTE 8 October 1 1941 Ascertain that the complete engine model designation is shown the name plate i e A 65 8 in accordance with Continental Service Bulletin No 41 12 as the series designation was omitted on some of the following engines 50 Up to Serial No 139819 incl A 65 Up to Serial No 1089618 incl Was SPECIAL NOTE 23 of A 1379 s Vollnecke Chief Aircraft Engineering Division KS MRH 5723530 12 Subject Reason for Change Airplanes Affected Accomplishment Description of Change Page 1 of 2 Bulletin No 50 Date 10 6 43 S E R V I C E B U L L E T I N TAYLORCRAFT AVIATION CORPORATION ALLIANCE OHIO INSPECTION OF CONTROL CABLE PULLEYS TAYLORCRAFT MODELS AND B To assure airworthiness of the subject airplanes All
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