DEPARTMENT OF TRANSPORTATION

FEDERAL AVIATION ADMINISTRATION



TC No.          A-696



Revision:           18



Models:             TAYLORCRAFT



                    BC                  BCS12-D

                    BCS                 BC12-D1

                    BC-65               BCS12-D1

                    BCS-65              BC12D-85

                    BC12-65(Army L-2H)  BCS12D-85

                    BCS12-65            BC12D-4-85

                    BC12-D              BCS12D-4-85



See (Specifications Pertinent to All Models and Notes)



Date:               March 22, 1993



               AIRCRAFT SPECIFICATION NO. A-696



Type Certificate Holder:           Taylorcraft Aircraft Company

                                   P.O. Box 480

                                   820 East Bald Eagle Street

                                   Lock Haven, PA 17745



I - Model BC, 2 PCLM, 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 rpm (50 hp.)



Propeller Limits:             Diameter: Maximum 83 in.



Airspeed Limits:

(True Ind.)



     Landplane:



          Level flight or climb    105 mph. (91 knots)

          Glide or dive            131 mph. (114 knots)



     Seaplane:



          Level flight or climb    95 mph.(83 knots)

          Glide or dive            129 mph.(112 knots)



Center of Gravity (C.G.) Range:    Landplane (+14.5) to (+19.7)

                                   Seaplane  (+15.1) to (+19.4)



Empty Weight C.G. Range:           Landplane (+15.3) to (+18.5)

                                   Seaplane  (+15.9) to (+18.3)

                         When empty weight C.G. falls within

                         pertinent range, computation of critical

                         fore and aft C.G. positions is

                         unnecessary. Ranges are not valid for

                         non-standard arrangements.



Maximum Weight:     Landplane 1100 lb.

                    (S/N 1407 and up are eligible at 1150 lb.)

                    Seaplane 1228 lb.



Number of Seats:    2 (+23)



Maximum Baggage:    30 lb. (+40)





Fuel Capacity:      12 gal.(-9).   See item 115 for

                                   auxiliary tank.



Oil Capacity:       4 qt. (-21)



Control Surface

Movements:          Elevators      Up 25°     Down 27°

                    Rudders        Right 26°  Left 26°

                    Ailerons       (Not available)



Serial No.

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 PCLM, 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 rpm. (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:

(True Ind.)



     Landplane:



          Level flight or climb    105 mph (91 knots)

          Glide or dive            131 mph (114 knots)

     Seaplane:



          Level flight or climb    95 mph (83 knots)

          Glide or dive            129 mph (112 knots)



Center of Gravity (C.G.) Range:    Landplane (+14.5) to (+19.7)

                                   Seaplane  (+15.1) to (+20.1)



Empty Weight C.G. Range:           Landplane (+15.3) to (+18.5)

                                   Seaplane  (+15.9) to (+19.0)



                    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.



Maximum Weight:     Landplane 1100 lb.

                    (S/N 1407 and up are eligible at 1150 lb.)



                    Seaplane  1228 lb.

                    (S/N 1432 and up are eligible at 1278 lb.)



Number of Seats:    2 (+23)



Maximum Baggage:    30 lb. (+40)



Fuel Capacity:      12 gal. (-9).

                    (See item 115 for auxiliary tank).



Oil Capacity:       4 qt. (-21)



Control Surface

Movements:          Elevators      Up    27°  Down 25°

                    Rudder         Right 26°  Left 26°

                    Ailerons       (Not available)



Serial No.

Eligible:           1001 and up



Required

Equipment:          Landplane Items     1, 2, 3, 4 or *8;

                                        104, 202, 203,

                                        210(a), 401



                    Seaplane Items      1, 3, 4 or *8;

                                        104, 205, 401



III - Model BC12-65 (Army L-2H), 2 PCL-SM, Approved April 7, 1941;

      Model BCS12-65, 2 PCL-SM, Approved April 7, 1941

      (Same as Model BC-65 except for minor structural changes

      and added elevator trim tab).



Engine:                  Continental A-65-7

                         (see item 114(c) for optional engines)



Fuel:                    73 min. grade aviation gasoline



Engine Limits:           For all operations, 2300 r.p.m. (65 hp.)

Propeller Limits:        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.



Airspeed Limits:

(True Ind.)



     Landplane:



          Level flight or climb    105 mph.

          Glide or dive            140 mph.



     Seaplane:



          Level flight or climb    95 mph.

          Glide or dive            129 m.p.h.



Center of Gravity (C.G.) Range:    Landplane (+14.2) to (+20.0)



                                   Seaplane  (+14.2) to (+20.0)

                                   with Edo floats (item 205)



                                             (+14.6) to (+20.0)

                                   with Heath floats (item 211)



Empty Weight C.G. Range:           Landplane (+14.8) to (+17.9)



                                   Seaplane: (+14.8) to (+18.3)

                                   with Edo floats (item 205)



                                             (+15.2) to (+18.3)

                                   with Heath floats (item 211)



Maximum Weight:     Landplane      1200 lb.

                    Seaplane       1278 lb.



Number Of Seats:    2 (+23)



Maximum Baggage:    Landplane      50 lb. (+40)

                    Seaplane       30 lb. (+40)



Fuel Capacity:                     18 gal (12 gal in fuselage

                                   (-9) and 6 gal. in wing (+24))

                                   See NOTE 3.



Oil Capacity:                      4 qt. (-21)



Control Surface

Movements:          Elevators      Up 27°     Down 25°

                    Elevator tab   Up 25°     Down 30°

                    Ailerons       Up 25°     Down 25°

                    Rudder         Right 26°  Left 26°



Serial No.

Eligible:           2401, 2501, 2503, 2504, 2529 and up

                    and all USAF numbers.

                    Use manufacturer's numbers if available.

Required

Equipment:          Landplane 1, 2, 4, 5 or *8;

                              104, 108, 202, 203, 210(a), 401



                    Seaplane  1 or 4;

                              104, 108; 205, 401



IV - Model BC12-D, 2 PCLM, Approved November 23, 1945;

     Model BCS-12D, 2 PCSM, Approved 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 not-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:                  Continental A-65-8

                         (see item 114(d) for optional engines)



Fuel:                    73 min. grade aviation gasoline



Engine Limits:           For all operations, 2300 r.p.m. (65 hp.)



Propeller Limits:        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.



Airspeed Limits:

(True Ind.)



     Landplane:



          Level flight or climb    105 mph.

          Glide or dive            140 mph.



     Seaplane:



          Level flight or climb    95 mph.

          Glide or dive            129 mph.



Center Or Gravity (C.G.) Range:    Landplane (+14.2) to (+20.0)



                                   Seaplane  (+14.2) to (+20.0)

                                   with Edo floats (item 205)



                                             (+14.6) to (+20.0)

                                   with Heath floats (item 211)



Empty Weight C.G. Range:      Landplane      (+14.8) to (+17.9)



                              Seaplane       (+14.8) to (+18.3)

                                   with Edo floats (item 205)



                                             (+15.2) to (+18.3)

                                   with Heath floats (item 211)



                    When empty weight C.G. falls within pertinent

                    range, computation or critical fore and aft

                    C.G. positions is unnecessary. Ranges are not

                    valid for non-standard arrangements.

Maximum Weight:     Landplane      1200 lb.

                    Seaplane       1278 lb.



Number Of Seats:    2 (+23)



Maximum Baggage:    Landplane      50 lb. (+40)

                    Seaplane       30 lb. (+40)



Fuel Capacity:      18 gal.

                    (12 gal. fuselage tank at (-9) and 6 gal.

                    wing tank at (+24).) See NOTE 3.



Oil Capacity:       4 qt. (-21)



Control Surface

Movements:          Elevators      Up 27°     Down 25°

                    Elevator tab   Up 25°     Down 30°

                    Ailerons       Up 23°     Down 23°

                    Rudder         Right 26°  Left 26°



Serial No.

Eligible:           6402 and up



Required

Equipment:          Landplane      1, 2, 3, 4 or *8;

                                   104, 108, 202, 203,

                                   210(a), 401



                    Seaplane       1, 3, 4 or *8;

                                   104, 108, 205, 401



V - Model BC12-D1, 2 PCL-SM, Approved September 10, 1946;

    Model BCS12-D1, 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-D1 eligible as BC12-D when items 601 and 204 and

    6 gal. right-hand wing tank are installed)



Engine:                  Continental A-65-8

                         (see item 114(d) for optional engines)



Fuel:                    73 min. grade aviation gasoline



Engine Limits:           For all operations, 2300 r.p.m. (65 hp.)



Propeller Limits:        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.



Airspeed Limits:

(True Ind.)



     Landplane:



          Level flight or climb    105 mph.

          Glide or dive            140 mph.

     Seaplane:



          Level flight or climb    95 mph.

          Glide or dive            129 mph.



Center of Gravity (C.G.) Range:    Landplane (+14.2) to (+20.0)



                                   Seaplane  (+14.2) to (+20.0)

                                   with Edo floats (item 205)



                                             (+14.6) to (+20.0)

                                   with Heath, floats (item 311)



Empty Weight C G. Range:      Landplane      (+14.8) to (+17.9)



                              Seaplane       (+14.8) to (+18.3)

                                   with Edo floats (item 205)



                                             (+15.2) 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.



Maximum Weight:     Landplane      1200 lb.

                    Seaplane       1278 lb.



Number of Seats:    2 (+23)



Maximum Baggage:    Landplane      50 lb.(+40)

                    Seaplane       30 lb.(+40)



Fuel Capacity:      12 gal. (-9)



Oil Capacity:       4 qt. (-21)



Control Surface

Movements:          Elevators      Up 27°     Down 25°

                    Elevator tab   Up 25°     Down 30°

                    Ailerons       Up 23°     Down 23°

                    Rudder         Right 26°  Left 26°



Serial No.

Eligible:           6402 and up.



Required

Equipment:          Landplane 1, 2, 3, 4 or *8;

                              104, 108, 202, 203,

                              210(a), 401



                    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:                 Continental C85-8F



Fuel:                    80 min grade aviation gasoline



Engine Limits:           For all operations, 2575 rpm. (85 hp.)



Propeller Limits:        Static r.p.m. at maximum permissible

(with item 6)            throttle setting (no additional

                         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.



Airspeed Limits:

(True Ind.)



     Landplane:



          Level flight or climb    105 mph (91 knots)

          Glide or dive            142 mph (124 knots)



     Seaplane:



          Level flight or climb    95 mph (83 knots)

          Glide or dive            128 mph (111 knots)





Center of Gravity (C.G.) Range:    Landplane (+14.2) to (+20.0)



                                   Seaplane  (+15.8) to (+17.6)

                                             at 1351 lb.

                                             (+13.4) to (+17.6)

                                             at 1200 lb. or less



                    Straight line variation between points given

                    Figure 1

Empty Weight C.G. Range:      Landplane      (+14.8) to (+17.9)

                              Seaplane       (+13.7) to (+15.1)



                         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.



Maximum Weight:     Landplane      1280 lb.

                    Seaplane       1351 lb.



Number of Seats:    2 (+23)



Maximum Baggage:    Landplane      50 lb.(+40)

                    Seaplane       30 lb.(+40)



Fuel Capacity:      18 gal (12 gal. tank in fuselage at (-9) and

                    6 gal. tank in wing at(+24).) See NOTE 3.



Oil Capacity:       4-1/2 qt. (-21)



Control Surface

Movements:          Elevators      Up 27°     Down 25°

                    Elevator tab   Up 25°     Down 30°

                    Ailerons       Up 23°     Down 23°

                    Rudder         Right 26°  Left 26°



Serial No.

Eligible:           12001 and up



Required

Equipment:          Landplane: 1, 4, 6, 7 or *9; 104, 108, 202,

                               206, 210(a), 401



                    Seaplane:  1, 4, 6, 7 or *9; 104, 108,

                               205, 401

VII - Model BC12D-4-85, 2 PCL-SM, Approved July 13, 1949; Model

      BCS12D-4-85, 2 PCL-SM Approved July 13, 1949.

      (Same 80 Model BC12D-65 except for engine, baggage

      compartment, side windows and sky-lights)



Engine:                  Continental C85-12F



Fuel:                    80 min. grade aviation gasoline



Engine Limits:           For all operations, 2575 r.p.m. (85 hp.)



Propeller Limits:        Static r.p.m. at maximum permissible

(with item 6)            throttle setting (no additional

                         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.



Airspeed Limits:

(True Ind.)



     Landplane:



          Level flight or climb    105 mph.(91 knots)

          Glide or dive            142 mph. (124 knots)



     Seaplane:



          Level flight or climb    95 mph. (83 knots)

          Glide or dive            128 mph. (111 knots)



Center of Gravity (C.G.) Range:    Landplane (+14.2) to (+20.0)



                                   Seaplane  (+15.8) to (+17.6)

                                             at 1351 lb.

                                             (+13.4) to (+17.6)

                                             at 1200 lb. or less



               Straight line variation between points given.

               (See Figure under Section VI)



Empty Weight C.G. Range:           Landplane (+14 9) to (+16 3)

                                   Seaplane  (+13 8) to (+14 3)



                         When empty weight C.G. falls within the

                         pertinent range, computation of critical

                         fore and aft C.G. positions is

                         unnecessary. Ranges not valid for

                         non-standard arrangements.

Maximum Weight:          Landplane      1280 lb.

                         Seaplane       1351 lb.



Number of Seats:         2 (+23)



Maximum Baggage:         Landplane      50 lb. (+70)

                         Seaplane       30 lb. (+70)



Fuel Capacity:           18 gal. (12 gal. tank in fuselage at

                         (-9) and 6 gal. tank in wing at (+24).

                         See Note 3.



Oil Capacity:            4-1/2 qt. (-30)



Control Surface

Movements:          Elevators      Up 27°      Down 25°

                    Elevator tab   Up 25°      Down 30°

                    Ailerons       Up 23°      Down 23°

                    Rudder         Right 26°   Left 26°



Serial No. Eligible:     4-13010 and up



Required Equipment:      Landplane 1, 4, 6, 7 or *9;

                                   104, 108, 202, 206,

                                   210(a), 401



                         Seaplane  1, 4, 6, 7 or *9;

                                   104, 108, 205, 401



Specifications Pertinent to All Models.



Datum:                   Leading edge of wing



Leveling Means:          Upper surface Or horizontal stabilizer



Certification Basis:     Part 04 of the Civil Air Regulations

                         effective as amended to May 1, 1938.

                         Type Certificate No. 696 issued.



Production Basis:        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.



Export Eligibility.      Eligible for export to 811 countries

                         subject to the provisions Of Advisory

                         Circular 21-2, except as follows:



                              Canada - Landplane and seaplane

                              eligible with the exception of

                              Model BC12-D1. Model BC12-D1

                              eligible provided auxiliary door

                              (item 601) is installed.



                         Skiplane not eligible: however,

                         structure complies with Canadian

                         requirements as follows:

                              (1) At 1100 lb. 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-lb. maximum

                              weight - landing gear per dwg.

                              B-A515, ski height 9 in., tread 72

                              in. (centerline of ski 5.19 in. out

                              from center of bolt attaching

                              diagonal streamline member to axle)



Equipment:     A plus (+) or minus (-) sign preceding the weight

               of an item indicates net weight change when that

               item is installed. Approval for the installation

               of all items of equipment listed herein has been

               obtained by the aircraft manufacturer except those

               items preceded by an asterisk (*). This symbol

               denotes that approval has been obtained by someone

               other than the aircraft manufacturer. An 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.



Special Note:  So that all items of equipment might be in their

               proper categories, the following items were

               renumbered as indicated:



1/  Item 1 was formerly item 103(a)    

2/  Item 2 was formerly item 103(b)

3/  Item 3 was formerly item 103(c)

4/  Item 4 was formerly item 103(d)

5/  Item 5 was formerly item 103(e)

6/  Item 6 was formerly item 103(f)

7/  Item 7 was formerly item 103(g)

8/  Item *8 was formerly item 103*(h)

9/  Item *9 was formerly item 108*(i)

10/ Item 114 was formerly item 308

11/ Item 115 was formerly item 312

12/ Item 116 was formerly item 313

13/ Item 117 was formerly item 315

14/ Item 202 was formerly item 101

15/ Item 203 was formerly item 102

16/ Item 204 was formerly item 107

17/ Item 205 was formerly item 151

18/ Item 206 was formerly item 302

19/ Item 207 was formerly item 304

20/ Item 208 was formerly item 305

21/ Item* 209 was formerly item *316

22/ Item 210 was formerly item 317

23/ Item* 211 was formerly item *320

24/ Item* 212 was formerly item *321

25/ Item 401 was formerly item 105

26/ Item 402 was formerly item 306

27/ Item 403 was formerly item 314

28/ Item 601 was formerly item 106

Propellers and Propeller Accessories.



1/1. Approved wood                 All Except     BC12D-4-85

(fixed or adjustable pitch).       BC12D-4-85 &        &

(See Static limits under           BCS12D-4-85    BCS12D-4-85

individual models                  10 lb. (-46)   10 lb. (-50)

and item 205(a) for

minimum static r.p.m.

limits for Models

BCS12D-85 and BCS12D-4-85)



2/2. Beech R003 controllable,      BC-65, BC12-65

hub R-002-101 or R-003-100,        BC12-D & BC12-D1

blades R-002-205-72.               +20 lb. (-47)

Diameter 72 in. Pitch at 27 in.

sta.: low 11-3/4°

high 17-3/4° (Pitch limits

under individual models are

not applicable to these

propellers). Includes

Beech mechanical

propeller control.



3/3. McCauley 1A90 with            BC-65, BCS-65,

the following limits:              BC12-D, BCS12-D

Static r.p m. at maximum           BC12-D1 & BCS12-D1

permissible throttle               +21 lb. (-46)

setting:

Landplane:     not over 2210, not under 1960

Seaplane:      not over 2210, not under 2070

No additional tolerance permitted.

Diameter: not over 74 in.,

not under 72.5 in.



4/4. Hartzell ground          All Except     BC12D-4-85

adjustable, hub HA-12U,       BC12D-4-85 &        &

blades 7414 to 6814 or        BCS12D-4-85    BCS12D-4-85

7214M to 6814M. Eligible at   18 lb. (-46)   18 lb. (-50)

diameter and static r.p.m.

limits shown above for

fixed pitched wood models.



5/5. McCauley 1A90 with       BC12-65

the following limits:         21 lb. (-46)

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.



6/6. Lewis L11CK-45 or        BC12D-85       BC12D-4-85

any other fixed pitch wood         &              &

propeller eligible for        BCS12D-85      BCS12D-4-85

the engine power and          10 lb. (-46)   10 lb. (-50)

speed and meeting static

r.p.m. and diameter

limits noted for the

various models eligible.

7/7. McCauley 1A90 with       BC12D-85       BC12D-4-85

the following limits:              &              &

Static r.p.m. at              BCS12D-85      BCS12D-4-85

maximum permissible           +21 lb. (-46)  +21 lb. (-50)

throttle setting:

not over 2350, not

under 2170. No additional

tolerance permitted

Diameter: not over 71 in.,

not under 69.5 in.



8/*8. Sensenich M74CK,             BC-65,

fixed pitch metal.                 BC12-D         BCS-65

Static r.p.m. at maximum           BC12-D1        BCS12-D

permissible throttle               BC12-65        BCS12-D1

setting:                           21 lb. (-46)   21 lb. (-50)



     Landplane: not over 2210, not under 1960

     Seaplane: not over 2210, not under 2070

No additional tolerance permitted

Diameter: not over 74.,

not under 72.5 in.



9/*9. Sensenich M74CK-2            BC12D-85       BC12D-4-85

fixed pitch metal.                 BCS12D-85      BCS12D-4-85

Static r.p.m. at maximum           21 lb. (-46)   21 lb. (-50)

permissible throttle

setting: not over 2350,

not under 2170.

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 certificated with single ignition engines

or were originally certificated prior to August 1, 1941.



104. Carburetor air heater (dwg. BC-L601)



108. Enclosed engine cowl

     (all except BC, BCS, BC-65, BCS-65)



109. McDowell starter installation

     (BC-12D, BC12D-85)                              11 lb. (-34)

     (BC-A6014 nose cowl must be installed)





110. McDowell starter installation using

     horizontal operating handle (BC12-D, BCS12-D)   13 lb. (-34)



111. Exhaust muffler, Ryan Aero. Co. dwg. 52112       2 lb. (-40)

     (with items  114(b) (1) and (2) only)

112. Oil filter, Fram PB-5, Kit No. 510.

      Weight includes 1 qt. oil                       4 lb. (-20)

     (a) 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)



113. Starter (Delco-Remy 1109656) (BC12D-4-85 only)  16 lb. (-24)



10/114. Engines (Continental, see Engine Specs.

        No. 190 and 205)                                    (-33)

     (a) Models BC, BCS

          (1) A-50-2                                  +6 lb.

          (2) A-50-3 or A-50-8                       +10 lb.

          (3) A-50-4                                  +3 lb.

          (4) A-50-5                                 +13 lb.

          (5) A-50-7                             No weight change

     (b) Models BC-65, BCS-65

          (1) A-65-3, A-65-3J, A-65-8 or A-65- &     +10 lb.

          Engine limits: for all operations,

          2300 r.p.m. (65 hp.)

          (2) A-65-7 or A-65-7J                  No weight change

          Engine limits same as (b)(1)

     (c) Models BC12-65

          (1) A-65-7J, A-65-8, A-65-8F, A-65-8J  No weight change

          Engine limits same as (b)(1)

     (d) Models BC12-D, BCS12-D, BC12-D1,

         BCS12-D1

          (1) A-65-8F, A-65-8J                   No weight change

          Engine limits same as (b)(1)

11/115. Auxiliary 6 gal. fuselage fuel tank

          installation (fuel arm +35)                 8 lb. (+30)

          (BC, BCS, BC-65, BCS-65)



12/116. Enclosed type engine cowl (dwg. BL-L628)

          (BC, BCS, BC-65, BCS-65)                    9 lb. (-18)



13/117. Revised engine mount (dwg. BC65-A128)

          (for engines incorporating              Negligible wt.

          integral rubber bushings)



Landing Gear and Floats.



201. Two main wheel-brake assemblies, 600-6, Type III

     (a) Cleveland Aircraft Products Co.

     Model 6.00 DHB                                  +4 lb. (+2)

     Wheel assembly No. C-38500HMA

     Brake assembly No. C-7000



14/202. Two main wheels, 6.00-6,

        Type III, Firestone 604                       9 lb. (+2)



15/ 203. Tail skid



16/ 204. Parking brake                                1 lb. (-9)

17/ 205. Edo float installation

     (a) Model 60-1320 floats                       165 lb. (+20)

     Auxiliary fin (required on                      4 lb. (+176)

     all models except BCS12D-85

     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 r.p.m. limit is

     increased to not under 2100 r.p.m.)

     As an alternate method of installing

     these floats, Taylorcraft clamp-on

     fuselage fittings, P/N 2554, 2555 and 2556

     may be used.



     (b) Model 92-1400 floats                       181 lb. (+19)

     Auxiliary fin (required on

     all models except BCS12D-85                     4 lb. (+176)

     and BCS12D-4-85)



18/206. Tail wheel assemblies                              (+193)



     (a) 6 x 2.00 steerable with brake (Baxter)      +5 lb.



     (b) 6 x 2.00 steerable (Aircraft Associates)    +3 lb.



     (c) 6 x 2.00 full swiveling

     (Firestone Industrial)                          +3 lb.



     (d) 6 x 2.00 steerable

     (Lake State Products 5-40-31)                   +4 lb.



     (e) 6 x 2.00 steerable (Heath)                  +4 lb.



     (f) Maule SFS-12, SS-12, SAFS-1-2-P8            +4 lb.



     (g) Steerable (Lang D-501, formerly Decker)      6 lb.



     (h) Scott Model 3-24B, Steerable,

     full swiveling                                   6 lb.



19/ 207. Two main wheel-brake assemblies,

         6.00-6, Type III Firestone Model 6C3HB       +4 lb. (+2)



20/ 208. Wheel streamlines (dwg. A-9015 or A-9016)     6 lb. (+2)



21/*209. Skis (eligible on any airplane                Use act.

         of these models provided the                  wt. change

         propeller installation meets the

         minimum 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)



          (a) Marston 1200 (max. 1200 lb.)

          (b) Air Transport 1220-480 (max. 1220 lb.)

          (c) Air Transport 1224-580-1 (max. 1220 lb.)

          (d) Federal SC-1 (max. 1400 lb.)

          (e) Piper S-1000 (max. 1200 lb.)

          (f) Jennings TY-2 (max. 1200 lb.)

          (g) Federal SA-1 (max. 1200 lb.)

          (h) Aviation Service B (max. 1650 lb.)

          (i) Richards 1-B (max. 2220 lb.)

          (j) Washington Aircraft (max. 1200 lb.)

          (k) Heath 655 (max. 1210 lb.)

          (l) Federal SC-2 (max. 1650 lb.)

          (m) Aviation Service A (max. 1100 lb.)

          (n) Federal SA-1A (max. 1300 lb.)

          (o) Jacobsen (formerly Escanaba) EAS-100

               (max. 1200 lb.)

          (p) Richards 1-A (max. 1600 lb.)

          (q) Marston MFS-1600 (max. 1600 lb.)

          (r) Heath 725 (max. 1450 lb.)

          (s) Aero. & Sales & Service AS-6.00 (max. 1320 lb.)

          (t) Jack Carr Service 16 (max. 1600 lb.)

          (u) Fairbanks MF-5 (max. 1310 lb.)

          (v) Heath 725A (max. 1450 lb.)

          (w) Federal SK4-1 (max. 1400 lb.)

          (x) Cell S2 (max. 1800 lb.)

          (y) Federal A-1500 (max. 1500 lb.),

               Federal Instln. dwg. 11R232

          (z) Federal A-1500A (max. 1500 lb.),

               Federal Instln. dwg. 11R232



          (aa) Federal A-1850 (max. 1850 lb.),

               Federal Instln. dwg. 11R232

          (ab) Federal A-2000 (max. 2000 lb.),

               Federal Instln. dwg. 11R232

          (ac) Federal A-200CA (max. 2000 lb.),

               Federal Instln. dwg. 11R232

          (ad) Federal CA-1850-6 (max. 1850 lb.),

               Federal Instln. dwg. 11R232

          (ae) Wesco A-15, Western Aircraft Equipment Co.

               dwg. 148, 202, 203.

          (af) Wesco A-20, Western Aircraft Equipment Co.

               dwg. 148, 202, 203.



22/210. Two main-wheel tires, 6.00-6,

        Type III with regular tubes

     (a) 2-ply rating                                12 lb. (+ 2)

     (b) 4-ply rating                                +5 lb. (+ 2)



23/*211. Heath 1460A float installation,

         172 lb. including auxiliary fin,          +122 lb. (+25)

         4 lb. (+176) (BCS12-D and BCS12-D1 only)



24/*212. Wheel fenders, Consolidair Model 16         10 lb. (+2)

         (Consolidair instln. dwg. 0029).



Electrical Equipment.



310. Battery and box

     (a) 6 v.                                         9 lb. (+10)

     (b) 12 v.                                       15 lb. (+10)

     (c) 12 v. (BC12D-4-85 and BCS12-D-4-85)         16 lb. (+70)



319. Position lights                                  2 lb. (+77)

     (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)               10 lb. (-24)



323. Voltage regulator (Delco-Remy 1118323)

     (BC12D-4-85, BCS12D-4-85)                        1 lb. (-18)



Interior Equipment.



25/401. Wheel type control



26/402. Cabin heater

        (Taylorcraft BC-L606 or BC-L630)              2 lb. (-22)



27/403. Stick type control                         Negligible wt.



Miscellaneous (not listed above).



26/601. Auxiliary door                              +5 lb. (+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.



NOTE 3.   Required placard adjacent to shutoff valve of right and

          left wing tanks:

          "Refill main tank in level flight only".