# TCDS A51EU: Daher Aerospace

- Type: Type certificate data sheet
- Status: Current
- Holder: Daher Aerospace
- Revision: 18
- Revised: August 30, 2021
- Product: Aircraft, Small Airplane
- Certification basis: Part 23
- Registered aircraft: 315, by the registry models matched to it (OpenAirDocs)
- Data sheet PDF: https://openairdocs.org/files/sha256/0c/f6/0cf6087e04b4e9b3049fb528b209489c0c33310033b432cf88b09c4f6e4b1d26
- FAA DRS: https://drs.faa.gov/browse/excelExternalWindow/24C79B848BBFF2A8862587AB005708C1.0001
- Page: https://openairdocs.org/tcds/A51EU

## Models (5)

As the data sheet lists them.

- TB 200
- TB9
- TB 21
- TB 20
- TB 10

## What the data sheet says

From the PDF's text layer, line by line; tables lose their columns. The PDF is the record.

```text
Page 1 2 3 4 5 6 7 8 9 10 11 12 13 14 15 16 17 18 19 
Rev. 18 7 12 16 14 12 14 12 8 18 13 15 7 12 8 7 12 12 12 
 
 DEPARTMENT OF TRANSPORTATION 
 FEDERAL AVIATION ADMINISTRATION 
 
A51EU 
Revision 18 
DAHER 
(SOCATA) 
 TB  9 
 TB 10 
 TB 20 
 TB 21 
 TB 200 
August 30, 2021 
  
TYPE CERTIFICATE DATA SHEET A51EU 
 
This data sheet which is part of Type Certificate No. A51EU prescribe s conditions and limitations under which the product for 
which the Type Certificate was issued meets the airworthiness requirements of the Federal Aviation Regulations. 
 
Type Certificate Holder.  DAHER AEROSPACE 
    23 route de TOURS 
    41400 SAINT JULIEN DE CHEDON 
    FRANCE  
 
Type Certificate Holder Record SOCATA name dropped by owner DAHER in 2015 
65921 - TARBES Cedex 9 
    France 
 
S O C A T A - Groupe AEROSPATIALE transferred to SOCATA 
    on February 16, 2011 
 
I.  Model TB 20, 4 PCLM (Normal Category), approved January 27, 1984. 
 
Engine.    LYCOMING IO-540-C4D5D 
 
Fuel.    100 minimum octane aviation gasoline 
 
Engine Limits.   For all operations, 2575 r.p.m. (250 H.P.)  
 
Propeller & Propeller Limits.  HARTZELL Constant Speed 
    HC-C2YK-1BF/F8477-4 
    Diameter: not over 80 in., not under 78 in. 
    Pitch setting at 30 in., sta.:    Low 15o 
                                                             High 31o 
 
    Spinner SOCATA TB 10.58.018.100, TB 10.58.018.104 or TB 10.58.026.001  
 
    OR 
 
    HARTZELL Constant Speed 
    HC-C3YR-1RF/F7693F or HC-C3YR-1RF/F7693FB 
    Diameter: not over 78 in., not under 76 in. 
    Pitch setting at 30 in., sta.:    Low 13o 
                                                             High 31o 
 
    Spinner HARTZELL A-2295-3(P) 
    
    WOODWARD hydraulic governor: 
     -E210681 for aircraft from S/N 1 to 730 
     -M210681 for aircraft from S/N 1 to 878 (except S/N 823 to 849 and 888).

A51EU 2 of 20     A51EU 
     -C210761 or F210 761 for aircraft from S/N 1

A51EU 3 of 20     A51EU 
Airspeed Limits (I.A.S.)  Normal Category. 
    a) Aircraft up to S/N 587 where modification No 50 has not been applied. 
        Maximum take-off and landing weight: 2943 lbs. 
 
    Never exceed   189 knots - 217 m.p.h. 
    Maximum structural cruising  151 knots - 174 m.p.h. 
    Maneuvering   127 knots - 146 m.p.h. 
    Flaps extended   100 knots - 115 m.p.h. 
    Gear extended   140 knots - 162 m.p.h.  
    Gear operating   130 knots - 149 m.p.h. 
 
    b) Aircraft from S/N 588 up to S/N 878 except S/N 823 to 849 and those where 
               modification No 50 has been applied.    
    Maximum take-off weight: 3086 lbs;  
    Maximum landing weight: 2943 lbs. 
 
    Never exceed    187 knots - 216 m.p.h. 
    Maximum structural cruising   150 knots - 173 m.p.h. 
    Maneuvering    129 knots - 149 m.p.h. 
    Flaps extended    103 knots - 119 m.p.h. 
    Gear extended    139 knots - 160 m.p.h. 
    Gear operating    129 knots - 149 m.p.h. 
 
    c) Aircraft from S/N 879 and S/N 823 to 849. 
    Maximum take-off and landing weight: 3086 lbs 
 
    Never exceed    187 knots - 216 m.p.h. 
    Maximum structural cruising   150 knots - 173 m.p.h. 
    Maneuvering    129 knots - 149 m.p.h. 
    Flaps extended take-off position  129 knots - 149 m.p.h. 
    Flaps extended landing position   103 knots - 119 m.p.h. 
    Gear extended    139 knots - 160 m.p.h. 
    Gear operating    129 knots - 149 m.p.h. 
 
C.G. Range.   Normal Category. 
    a) Aircraft up to S/N 587 and where modification No 50 has not been applied. 
    Take-off and landing maximum weight: 2943 lbs 
 
    (+ 36.9) to (+ 47.4) at 2000 lbs or less 
    (+ 37.9) to (+ 47.4) at 2645 lbs 
    (+ 42.6) to (+ 47.4) at 2943 lbs 
    Straight line between points given. 
 
    b) Aircraft where modification No 50 has been applied for S/N 1 to 587. 
    (+ 36.9) to (+ 47.4) at 2000 lbs or less 
    (+ 37.9) to (+ 47.4) at 2645 lbs 
    (+ 42.6) to (+ 47.4) at 2943 lbs 
    (+ 42.6) to (+ 47.4) at 3086 lbs 
    Straight line between points given. 
 
    c) Aircraft from S/N 588 included 
    (+ 35.9) to (+ 47.4) at 2205 lbs or less 
    (+ 37.4) to (+ 47.4) at 2756 lbs 
    (+ 42.2) to (+ 47.4) at 3086 lbs 
    Straight line between points given. 
 
Empty Weight C.G. Range.  None. 
 
Maximum Weight.   Normal Category 
 a) Aircraft where modification No 50 has not been applied. 
  - Maximum take-off and landing weight: 2943 lbs

A51EU 4 of 20     A51EU 
 
b) Aircraft from S/N 588 and those where modification No 50 has been applied, up to  
 S/N 878, except for S/N 823 to 849. 
  - Maximum take-off: 3086 lbs 
  - Maximum landing: 2943 lbs 
 
 c) Aircraft from S/N 879 and S/N 823 to 849. 
  - Maximum take-off weight:    3086 lbs 
  - Maximum landing weight:     3086 lbs 
 
Number of seats.   4 (2 at + 45.5, 2 at + 80.1) - See Note 5 for additional rear seat. 
 
Maximum Baggage.   110 lb at (+ 102) or 143 lb at (+ 102) if modification No. 40 is applied.  
 
Fuel Capacity.   88.8 gal. (two 44.4 gal. at + 42.7: 86.2 gal. usable) 
    See Note 1 for weight and unusable fuel 
 
Oil Capacity.   13.3 qt at (-23.6) (3.9 qt unusable) 
    See Note 1 for weight 
 
Control Surface Movements.  Stabilator (Angles references: upper fuselage spar) 
    Leading edge down: 16o ± 1o 
    Leading edge up: 3o ± 1o 
 
    Stabilator tab (Angles reference: stabilator chord) 
    with stabilator leading edge full down. 
 
    a)  Aircraft where modification No 50 has not been applied. 
 
    Tab trailing edge minimum up     2.5o ± 0.5o 
    Tab trailing edge maximum up    17.5o ± 1.5o 
 
    b)  Aircraft from S/N 588 and those where modification No 50 has been applied. 
 
    Tab trailing edge minimum up      0o ± 0.5o 
    Tab trailing edge maximum up    15o ± 1.5o 
 
    Ailerons (Reference: wing chord) 
                    up 15o ± 1.5o 
                down 15o ± 1.5o 
 
    Rudder (Reference: fin chord) 
           Right and left               25o ± 2o 
 
    Rudder tab (Reference: rudder chord) 
            Left turn                    10o ± 2o 
           Right turn                   25o ± 2o 
 
    Flaps (Reference: wing chord)          + 0.5o 
          Full flaps                    40o 
                                                                                    -   1o 
 
II.  Model TB 10, 4 PCLM (Normal and Utility Category) approved November 27, 1985 
     Similar to the TB 20 but with fixed gear. 
 
Engine.    LYCOMING O-360-A1AD 
 
Fuel.                    100 minimum octane aviation gasoline 
 
 
Engine Limits.   For all operations, 2700 r.p.m. (180 HP)

A51EU 5 of 20     A51EU 
 
Propeller & Propeller Limits.  HARTZELL constant speed 
    HC-C2YK-1BF/F-7666 A-2 
    Diameter: not over 74 in., not under 72 in. 
    Pitch setting at 30 in., sta.:   Low 13o30 
                    High 31o 
 
    Spinner SOCATA TB 10.58.018.100, TB 10.58.018.104 or TB 10.58.026.001  
    HARTZELL Hydraulic governor F4-26 or F4-4A or F4-4AZ or F4-18 
       
Airspeed Limits (IAS).  Normal and Utility Category. 
    Never exceed  165 knots - 190 m.p.h. 
    Maneuvering  122 knots - 142 m.p.h. 
    Flaps extended   95 knots - 109 m.p.h. 
 
C.G. Range.   Normal Category. 
    (+ 37.3) to (+ 47.4) at 2138 lbs or less 
    (+ 39.8) to (+ 47.4) at 2359 lbs 
    (+ 45.0) to (+ 47.4) at 2535 lbs (Aircraft up to S/N 947) 
    (+ 42.6) to (+ 47.4) at 2535 lbs (Aircraft from S/N 948 included) 
    Straight line variation between points given. 
 
    Utility Category. 
    (+ 37.3) to (+ 47.4) at 2138 lb or less 
    (+ 38.3) to (+ 47.4) at 2249 lb 
    (+ 40.7) to (+ 47.4) at 2359 lb 
    Straight line variation between points given. 
 
Empty weight C.G. Range.  None 
 
Maximum Weight.   Normal Category. 
 a) Aircraft up to S/N 822, except S/N 804, 807, 808, and 816 to 819.  
  - Maximum take-off weight: 2535 lbs 
  - Maximum landing weight : 2407 lbs 
 
 b) Aircraft from S/N 823, and S/N 804, 807, 808 and 816 to 819.  
  - Maximum take-off weight: 2535 lbs 
  - Maximum landing weight : 2535 lbs 
 
    Utility Category. 
    Maximum take-off and landing weight: 2359 lbs 
 
Number of seats.   4 (2 at + 45.9, 2 at + 82.4) See Note 5 for rear seat occupancy. 
 
Maximum Baggage.  22 lbs at (+ 116.7) and 66 lbs at (+ 99) for aircraft up to S/N 399 and  
    143 lbs at (+ 102.3) from aircraft S/N 400 
 
Fuel Capacity.   55.4 gal. (two 27.7 gal. at + 42.3 ; 53.8 gal. usable) 
    See Note 1 for weight and unusable fuel. 
 
Oil Capacity.   8.45 qt at (-23.8)(-2.64 qt unusable) 
    See Note 1 for weight. 
 
Control Surface Movements.  Stabilator (Angles reference: upper fuselage spar) 
 
    Leading edge down   17o ± 1o 
    Leading edge up     2o ± 1o 
 
    Stabilator tab (Angles reference: stabilizer chord) with stabilator leading edge full down 
 
    Tab trailing edge minimum up  2.5o ± 0.5o

A51EU 6 of 20     A51EU 
    Tab trailing edge maximum up  17o ± 1.5o 
 
Control Surface Movements,  Ailerons (Reference: wing chord)      up  15o ± 1.5 
Continued            down  15o ± 1.5o 
 
    Rudder (Reference: fin chord) 
    Right and left            25o ± 2o 
 
    Flaps (Reference: wing chord)         + 0.5o 
          Full flaps                           25.5o 
                                                                                   - 1o 
 
III. Model TB 21, 4 PCLM (Normal Category) approved March 5, 1986 
     Similar to the TB 20 but with a turbocharged engine. 
 
Engine.    LYCOMING TIO-540-AB1AD 
 
Fuel.    100 minimum octane aviation gasoline 
Engine Limits.   For all operations, 2575 r.p.m. (250 HP) 
 
Propeller and Propeller Limits. HARTZELL Constant Speed 
    HC-C2YK-1BF/F 8477-4 
 
    Diameter: not over 80 in., not under 78 in. 
    Pitch setting at 30 in., sta.:     Low 15o 
                      High 31o 
 
    Spinner SOCATA TB 10.58.018.100 or TB 10.58.018.104  
 
    OR 
 
    HARTZELL Constant Speed 
    HC-C3YR-1RF/F7693F or HC-C3YR-1RF/F7693FB 
    Diameter: not over 78 in., not under 76 in. 
    Pitch setting at 30 in., sta.:    Low 13o 
                                                             High 31o 
 
    Spinner HARTZELL A-2295-3(P) 
 
    WOODWARD hydraulic governor: 
      -E210681 or M210681 or C210761 for aircraft from S/N 1 to 730  
      -C210761 or F210761 for aircraft from S/N 1 
 
Airspeed Limits (I.A.S.)  Normal Category. 
    a)  Aircraft up to S/N 878: 
    Never exceed    187 knots - 216 m.p.h. 
    Maximum structural cruising   150 knots - 173 m.p.h. 
    Maneuvering    129 knots - 149 m.p.h. 
    Flaps extended    103 knots - 119 m.p.h. 
    Gear extended    139 knots - 160 m.p.h. 
    Gear operating    129 knots - 149 m.p.h. 
 
Airspeed Limits (I.A.S.)  b)  Aircraft from S/N 879: 
Continued   Never exceed    187 knots - 216 m.p.h. 
    Maximum structural cruising   150 knots - 173 m.p.h. 
    Maneuvering    129 knots - 149 m.p.h. 
    Flaps extended take-off position  129 knots - 149 m.p.h. 
    Flaps extended landing position  103 knots - 119 m.p.h. 
    Gear extended    139 knots - 160 m.p.h. 
    Gear operating    129 knots - 149 m.p.h.

A51EU 7 of 20     A51EU 
C.G. Range.   Normal Category. 
 
    (+ 35.9) to (+ 47.4) at 2205 lbs or less 
    (+ 37.4) to (+ 47.4) at 2756 lbs 
    (+ 42.2) to (+ 47.4) at 3086 lbs 
    Straight line between points given. 
 
Empty weight C.G. Range.  None 
       
Maximum Weight.   Normal Category 
 
    a)  Aircraft up to S/N 878: 
    - Maximum take-off weight: 3086 lbs 
    - Maximum landing weight : 2943 lbs 
 
    b)  Aircraft from S/N 879: 
    - Maximum take-off weight: 3086 lbs 
    - Maximum landing weight : 3086 lbs 
 
Number of Seats.   4(2 at + 45.5, 2 at + 80.1) - See Note 5 for additional rear seat. 
 
Maximum Baggage.  143 lbs at (+ 102) 
 
Fuel Capacity.   88.8 gal. (two 44.4 gal. at + 42.7; 86.2 gal. usable) 
    See Note 1 for weight and unusable fuel 
 
Oil Capacity.   13.3 qt at (-23.6) (3.9 qt unusable) 
    See Note 1 for weight 
 
Control Surface Movements.  Stabilator (Angles references: upper fuselage spar) 
    Leading edge down :     16o ± 1o 
    Leading edge up :       3o ± 1o 
 
    Stabilator tab (Angles reference: stabilator chord) with stabilator leading edge full down. 
 
    Tab trailing edge minimum up    0o ± 0.5o 
    Tab trailing edge maximum up                15o ± 1.5o 
 
    Ailerons (Reference: wing chord)           up 15o ± 1.5o 
             down 15o ± 1.5o 
 
    Rudder (Reference: fin chord) 
           Right and left                                            25o ± 2o 
 
    Rudder tab (Reference: rudder chord) 
           Left turn                                   10o ± 2o 
           Right turn                                  25o ± 2o 
 
    Flaps (Reference: wing chord)                                + 0.5o 
          Full flaps                                   40o 
                                                                   - 1o 
 
IV.  Model TB9, 4 PCLM (Utility Category) approved July 11, 1988 
     Similar to the TB10 but with a 160 HP engine. 
 
Engine.    LYCOMING O-320-D2A 
 
Fuel.    100 minimum octane aviation gasoline 
 
Engine Limits.   For all operations, 2700 r.p.m. (160 HP)

A51EU 8 of 20     A51EU 
Propeller & Propeller Limits.  Aircraft up to S/N 878 except S/N 765: 
      SENSENICH fixed pitch 
      74 DM6 S8 061 
      Diameter: not over 74 in., not under 72 in. 
      Spinner SOCATA TB 9.58.013.100 or TB 9.58.013.104  
 
      HARTZELL constant speed 
      HC-C2YL-1BF/F-7663 A-4 
      Diameter: not over 72 in., not under 70 in. 
      Pitch setting at 27 in., sta.:                Low 11o 
                                  High 26o06' 
      Spinner SOCATA TB 10.58.018.104 or TB 10.58.026.001  
      HARTZELL hydraulic governor F4-26 or F4-4A or F4-4AZ or F4-18 
 
    Aircraft from S/N 879 and S/N 765: 
      SENSENICH fixed pitch 
      74 DM6 SB 054 
      Diameter: not over 74 in., not under 72 in. 
                                      Spinner SOCATA TB9.58.013.100 or TB 9.58.013.104  
 
    Aircraft from S/N 1851 and from S/N 948 retrofitted with modification no. 139: 
      SENSENICH fixed pitch 
      74 DM6 S8 058 
      Diameter: not over 74 in., not under 72 in. 
                                      Spinner SOCATA TB9.58.013.100 or TB 9.58.013.104  
 
Wheel Fairings.   Wheel fairing equipments are mandatory with propeller: 
      - SENSENICH 74 DM6 S8 061 and 
      - HARTZELL HC-C2YL-1BF/F 7663 A-4 
      - SENSENICH 74 DM6 S8 058 
 
Airspeed Limits (I.A.S.)  Never exceed   165 knots - 190 m.p.h. 
    Maneuvering   122 knots - 142 m.p.h. 
    Flaps extended    95 knots - 109 m.p.h. 
 
C.G. Range.   Utility Category. 
    (+ 38.3) to (+ 47.4) at 2138 lbs or less 
    (+ 41.3) to (+ 47.4) at 2337 lbs 
    Straight line variation between points given. 
 
Empty Weight C.G. Range.  None 
 
Maximum Weight.   Maximum take-off weight : 2337 lbs 
    Maximum landing weight  : 2337 lbs 
 
Number of seats.   4 (2 at + 45.9, 2 at + 82.4) See Note 5 for rear seat occupancy 
 
Maximum Baggage.  88 lbs at (+ 102.3) for aircraft up to S/N 399 and 413 
    143 lbs at (+ 102.3) from aircraft S/N 400 
 
Fuel Capacity.   41.7 gal. (two 20.85 gal. at + 42.3; 40.2 gal. usable) 
    or 
    55.4 gal. (two 27.7 gal. at + 42.3; 53.8 gal. usable) 
 
    See Note 1 for weight and unusable fuel. 
 
Oil Capacity.   8.45 qt at (-23.8) (2.64 qt unusable) 
    See Note 1 for weight. 
 
Control Surface Movements.  Stabilator (Angles reference: upper fuselage spar) 
    Leading edge down    17o ± 1o

A51EU 9 of 20     A51EU 
    Leading edge up      2o ± 1o 
 
    Stabilator tab (angles reference: stabilizer chord) with stabilator leading edge full down. 
    Tab trailing edge minimum up  2.5o ± 0.5o 
    Tab trailing edge maximum up  17o ± 1.5o 
 
    Ailerons (Reference: wing chord) 
                  up 15o ± 1.5o 
             down  15o ± 1.5o 
    Rudder (Reference: fin chord) 
               Right and left            25o ± 2o 
 
    Flaps (Reference: wing chord) 
        - Aircraft up to S/N 878 except S/N 765 
                + 0.5o 
        Full flaps                             32o 
                 - 1o 
 
       - Aircraft from S/N 879 and S/N 765 
                 +0.5o 
         Full flaps                             25.5o 
                 -1o 
 
V.  Model TB 200, 4 PCLM (Normal Category) approved September 14, 1992.  Similar to the TB 20 but with fixed gear. 
 
Engine.    LYCOMING IO 360 A1B6 
 
Fuel.    100 minimum octane aviation gasoline 
 
Engine Limits.   For all operations, 2700 r.p.m. (200 Hp) 
 
Propeller and Propeller Limits. HARTZELL constant speed 
    HC-C2YK-1BF/F-7666 A-2 
    Diameter: not over 74 in., not under 72 in. 
    Pitch setting at 30 in., sta.:        Low  13o30 
              High 31o 
 
    Spinner SOCATA TB 10.58.018.100, TB 10.58.018.104 or TB 1058.026.001  
    WOODWARD governor A210776 
 
Airspeed Limits (IAS).  Never exceed   165 knots - 190 m.p.h. 
    Maneuvering   122 knots - 142 m.p.h. 
    Flaps extended    95 knots - 109 m.p.h. 
 
C.G. Range.   42.6 in to (+47.4) at 2535 lbs 
    39.8 in to (+47.4) at 2359 lbs 
    37.3 in to (+47.4) at 2138 lbs or less 
 
Empty Weight C.G. Range.  None 
 
Maximum Weight.   Maximum take-off and landing weight: 2535 lbs 
 
Number of Seats.   4 (2 at +45.9, 2 at 82.4) See Note 5 for rear seat occupancy 
 
Maximum Baggage.  143 lbs at (+102.3) 
 
Fuel Capacity.   55.4 gal. (two 27.7 gal. at 42.3 ; 53.8 gal. usable) 
    See Note 1 for weight and unusable fuel. 
 
Oil Capacity.   8.45 qt at (-23.8) (2.64 qt unusable) 
    See Note 1 for weight

A51EU 10 of 20     A51EU 
 
Control Surface Movements  Stabilator (Angles reference: upper fuselage spar) 
    Leading edge down   17o ± 1o 
    Leading edge up     2o ± 1o 
 
    Stabilator tab (angles reference: stabilizer chord) with stabilator leading edge full down. 
    Tab trailing edge minimum up 2.5o ± 0.5o 
    Tab trailing edge maximum up 17o  ± 1.5o 
 
    Ailerons (reference: wing chord)     Up 15o ± 1.5 
        Down 15o ± 1.5o 
    Rudder (Reference: fin chord)   
    Right and left   25o ± 2o  
 
    Flaps (Reference: wing chord)         + 0.5o 
    Full flaps    25.5o 
                 - 1o 
 
DATA PERTINENT TO ALL MODELS 
 
Certification Basis.   Type Certification under 14 CFR Section 21-29 including the following requirements: 
    TB 20 
    - 14 CFR Part 23 effective February 1, 1965, including amendments 23-1 through 23-16. 
    - 14 CFR Part 36 effective Dec 1, 1969, including amendments 36-1 through 36-11. 
    Effective date of certification basis: November 2, 1975 
    Date of U.S. application: April 5, 1982 
    Type Certificate issued on January 27, 1984 
 
    TB 10 
    - 14 CFR Part 23 effective February 1, 1965, including amendments 23-1 through 23-16. 
    - 14 CFR Part 36 effective Dec 1, 1969, including amendments 36-1 through 36-11. 
    Effective date of certification basis: November 2, 1975  
    Date of U.S. application: May 3, 1979 
    Type Certificate issued on November 27, 1985. 
 
    TB 21 
    - 14 CFR Part 23 effective February 1, 1965, including amendments 23-1 through 23-16. 
    - 14 CFR Part 36 effective Dec 1, 1969, including amendments 36-1 through 36-11. 
    Effective date of certification basis: November 2, 1975 
    Date of U.S. application: September 30, 1985 
    Type Certificate issued on March 5, 1986. 
 
    TB 9 
    - 14 CFR Part 23 effective February 1, 1965, including amendments 23-1 through 23-16. 
    - 14 CFR Part 36 effective Feb 17, 1987, including amendments 36-1 through 36-13. 
    Effective date of certification basis: November 2, 1975 
    Date of U.S. application: August 10, 1987 
    Type Certificate issued on July 11, 1988. 
 
Certification Basis;   TB 200 
(Cont.)    - 14 CFR Part 23 effective February 1, 1965, including amendments 23-1 through 23-16. 
    - 14 CFR Part 36 effective Dec 1, 1969, including amendments 36-1 through 36-11. 
    Effective date of certification basis: November 2, 1975 
    Date of U.S. application:  April 15, 1992. 
    Type Certificate issued on September 14, 1992. 
 
    The Direction Générale de l’Aviation Civile (DGAC) originally type certificated this  
    aircraft under its type certificate Number 165. The FAA validated this product under U.S.  
    Type Certificate Number A51EU. Effective September 28, 2003, the European Aviation 
Safety Agency (EASA) began oversight of this product on behalf of France.

A51EU 11 of 20     A51EU 
Import Requirements.  The FAA can issue a U.S. airworthiness certificate based on an NAA Export Certificate  
    of Airworthiness (Export C of A) signed by a representative  of the Direction Générale de 
l’Aviation Civile (DGAC) on behalf of the European Community.  The Export C of A 
should contain the following statement: ‘The aircraft covered by this certificate has been 
examined, tested, and found to comply with U.S. airwor thiness regulations 14 CFR Part 
23 approved under U.S. Type Certificate No. A51EU and to be in a condition for safe 
operation.’ 
 
Refer to the applicable bilateral agreement to verify eligibility for import into the United 
States of both new and used aircraft based on the scope of the agreement, to identify any 
required statements by the exporting authority on the export certificate of airworthiness 
(or equivalent document), and for procedures for coordinating exceptions to conformity 
statements on these documents. Refer to FAA Order 8130.2, Airworthiness Certification 
of Aircraft, for requirements for issuance of an airworthiness certificate for imported 
aircraft. 
 
     
Serial Nos. Eligible.  A certificate of Airworthiness for Export endorsed as noted under "Import Requirements" 
must be submitted for each individual aircraft for which application for U.S. Certification 
is made. 
 
Equipment.   The basic required equipment as prescribed in the applicable airworthiness regulations 
(see certification basis) must be installed in the aircraft for certification.  Approved 
equipment is listed as follows: 
 
 TB20: 
 1) Aircraft up to S/N 947 except S/N 823 to 849 and 888 (14 volt electrical system) 
  SOCATA Equipment List TB 20 BE/EQ No 91/81, Issue No 6 dated November 85  
  or later version. 
2) Aircraft from to S/N 948 and S/N 823 to 849 plus S/N 888 (28 volt electrical  
  system)  
  SOCATA Equipment List TB 20 NAV No 92/89, Issue No 1 dated MAY 89 or later  
  version. 
 
 TB10: 
 1) Aircraft up to S/N 947 (14 volt electrical system) SOCATA Equipment List TB 20  
  BE/EQ No 74/79, Issue No 5 dated November 85 or later version. 
 2) Aircraft from S/N 948 (28 volt electrical system) SOCATA Equipment List TB 10  
  NAV No 232/89, Issue No 1 dated November 89 or later version. 
 
 TB21: 
 1) Aircraft from S/N 879 to 947 (14 volt electrical system) SOCATA Equipment List  
  TB 21 BE/EQ No 142/85, Issue No 3 dated November 85 or later version. 
 2) Aircraft from S/N 948 (28 volt electrical system) SOCATA Equipment List TB 21  
  NAV No 124/89, Issue No 1 dated August 89 or later version. 
 
    TB9: 
 1) Aircraft up to 947 (14 volt electrical system) SOCATA Equipment List TB 9 NAV  
  No 102/87, Issue No 1 dated May 87 or later version. 
Equipment (Cont.) 2) Aircraft from S/N 948 (28 volt electrical system) SOCATA Equipment List TB 10  
  NAV No 232/89, Issue No 1 dated November 89 or later version. 
 
    TB200: 
    SOCATA Equipment List to TB 200 NAV No. 410/91 or later version. 
    In addition, the following items of equipment are required 
    Model TB 20 
 (a) French DGAC approved Airplane Flight Manual or Pilot's Operating Handbook 
  (1) Aircraft up to S/N 587 A.F.M. DGAC approved on December 14, 1983;  
   edition  
   1 of December 1983 to edition 4A of December 1985 or  
   (1.1) aircraft up to S/N 587 without kit 9118, P.O.H. DGAC approved on

A51EU 12 of 20     A51EU 
    February 18, 1991; edition 3 of December 31, 1989 or;  
   (1.2) aircraft up to S/N 587 with kit 9118, P.O.H. DGAC approved on  
    February 18, 1991; edition 4 of January 31, 1990. 
  (2) Aircraft from S/N 588 up to 730 A.F.M. DGAC approved on January 23,  
   1986; edition 5 of December 1985 or P.O.H. DGAC approved on February 18,  
   1991; edition 4 of January 31, 1990. 
  (3) Aircraft from S/N 731 up to S/N 878 (except S/N 823 to 849) P.O.H.  
   DGAC approved on April 21, 1987; edition 0 of December 31, 1986 or later  
   approved revisions. 
  (4) Aircraft from S/N 879 up to S/N 947 (except S/N 888) P.O.H. DGAC 
   approved on January 31, 1989; edition 1 of January 31, 1988 or later  
   approved revisions. 
  (5) Aircraft S/N 823 to S/N 849, plus S/N 888, and from S/N 948 on:  
   (5.1) P.O.H. DGAC approved on August 23, 1989; edition 2 of June 30, 1988  
   or later approved revisions. 
      (5.2) "I.A.F" version - P.O.H. DGAC approved on November 17, 1994;  
      edition 2 of September 30, 1994. 
     (6) Aircraft equipped with SOCATA option OPT10-61-001 must have Pilot's  
      Operating Handbook Supplement 45, "Three Bladed Propeller." 
 
 (b) Stall warning system, SOCATA Reference TB 10-61-017-000. 
    
 Model TB 10 
 (a) French DGAC approved Airplane Flight Manual or Pilot's Operating Handbook 
(1) Aircraft up to S/N 730 A.F.M. DGAC approved on November 1985; edition 1  
   of January 1985 or A.F.M. DGAC approved on March 1986; edition 2 of  
   March 1986 and 3 of May 1986 or P.O.H. DGAC approved on November 4,  
   1988; edition 0 of January 31, 1988 or later approved revisions.  
  (2) Aircraft from S/N 731 up to S/N 822 except S/N 804, 807, 808 and S/N 816 up  
   to 819, A.F.M. DGAC approved on March 1986; edition 4 of December 1986  
   or P.O.H.  DGAC approved on November 4, 1988; edition 1 of February 29,  
   1988 or later approved revisions. 
  (3) Aircraft from S/N 823 to S/N 947 and S/N 804, 807, 808 and S/N 816 up to  
   819, P.O.H. DGAC approved on November 4, 1988; edition 2 of March 31,  
   1988 or later approved revisions. 
  (4) Aircraft from S/N 948 P.O.H. DGAC approved on December 13, 1989; edition  
   3 of September 30, 1989. 
 (b) Stall warning system, SOCATA Reference TB 10-61-017-000 
 (c) Aileron-Rudder controls interconnection option No. 597 
 
 Model TB 21 
 (a) French DGAC approved Airplane Flight Manual or Pilot's Operating Handbook 
  (1) Aircraft up to S/N 730, A.F.M. DGAC approved on November 1985; editions  
   1 of April 1985, to edition 3 of June 1986 or P.O.H.  DGAC approved on  
   February 18, 1991; edition 3 of December 31, 1989. 
  (2) Aircraft from S/N 731 up to S/N 878, P.O.H. DGAC approved on April 21,  
   1987; edition 0 of December 31, 1986 or later approved revisions.  
  (3) Aircraft from S/N 879 up to S/N 947, P.O.H. DGAC approved on June 2,  
   1989; edition 1 of January 31, 1988 
(4) Aircraft from S/N 948, P.O.H. DGAC approved on November 21, 1989;  
   edition 2 of May 31, 1989 or later approved revisions. 
      (5) Aircraft equipped with SOCATA option OPT10-61-001 must have Pilot's     
   Operating Handbook Supplement 45, "Three Bladed Propeller." 
 
 (b) Stall warning system, SOCATA Reference TB 10-61-017-000 
 
 Model TB 9 
 (a) French DGAC approved Airplane Flight Manual or Pilot's Operating Handbook 
(1) Aircraft from S/N 731 up to S/N 878, A.F.M. DGAC approved on May 16,

A51EU 13 of 20     A51EU 
   1988; edition 1bis of August 1987 or (except S/N 765) P.O.H. DGAC  
   approved on April 6, 1989; edition 1 of February 29, 1988 or later approved  
   revisions. 
  (2) Aircraft from S/N 879 to 947 and S/N 765, P.O.H. DGAC approved on  
   December 13, 1988; edition 2 of September 30, 1988 
  (3) Aircraft from S/N 948, P.O.H. DGAC approved on February 02, 1990 edition  
   3 of September 30, 1989 
(4) Aircraft up to S/N 730, P.O.H. DGAC approved on September 5 1989; edition  
   0 of January 31, 1988, or later approved revisions. 
  (5)   Aircraft from S/N 1851 and from S/N 948 retrofitted with modification no.  
   139, P.O.H. DGAC approved on February 2001; edition 4 of December 31,  
   1997, revision 1 of October 31, 2000 or later approved revisions. 
 
 (b) Stall warning system, SOCATA Reference TB 10-61-017-000 
 (c) Aileron-Rudder controls interconnection option No. 597  
 
    Model TB 200 
    (a) French DGAC approved Airplane Flight Manual or Pilot's Operating Handbook. 
    (b) Stall warning system, SOCATA Reference TB 10-61-017-000. 
 
Datum.    Front face of firewall 
 
Leveling Means.   Upper fuselage spar horizontal (Maintenance Manual Subchapter 15 of Chapter II) 
 
Service Information.    Each of the documen ts listed below must state that it is approved by the European 
Aviation Safety Agency (EASA) or – for approvals made before September 28, 2003 – 
by the Direction Générale de l’Aviation Civile (DGAC).  
     • Service bulletins,  
     • Structural repair manuals,  
     • Vendor manuals,  
     • Aircraft flight manuals, and  
     • Overhaul and maintenance manuals.  
 
    The FAA accepts such documents and considers them FAA -approved unless one of the 
following conditions exists: 
 
   • The documents change the limitations, performance, or procedures of the 
FAA approved manuals; or 
 
   •The documents make an acoustical or emissions changes to this product’s U.S. 
type certificate as defined in 14 CFR § 21.93.  
 
    The FAA uses the post type validation procedures to approve these documents.  The FAA 
may delegate on case-by-case to EASA to approve on behalf of the FAA for the U.S. type 
certificate.  If this is the case it will be noted on the document.   
 
 
NOTE 
Note 1    Current weight and balance report including l ist 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 1 (Cont.)    Model TB 20 
    The certificated empty weight and corresponding center of gravity location must include  
    unusable fuel of 15.9 lb at (+ 42.7) and full oil of 24.8 lb at ( -23.6). 
 
    Model TB 10 
    The certificated empty weight and corresponding center of gravity location must include 
unusable fuel of 9.5 lb at (+ 42.3) and full oil of 15.8 lbs at (-23.8). 
 
    Model TB 21

A51EU 14 of 20     A51EU 
    The certificated empty weight and corresponding center of gravity location must include 
unusable fuel of 15.9 lb at (+ 42.7) and full oil of 24.8 lbs at ( -23.6). 
 
    Model TB 9 
    The certificated empty weight and corresponding center of gravity location must include 
unusable fuel of 9.5 lb at (+ 42.3) and full oil of 15.8 lbs at ( - 23.8). 
 
                  Model TB 200 
    The certificated empty weight and corresponding center of gravity locat ion must include 
unusable fuel of 9.5 lb at (+42.3) and full oil of 15.8 lb at  
    (-23.8) 
 
Note 2.    Model TB 20 
    a) The following placard must be displayed in front and in clear view of the pilot. 
   
  1) Aircraft up to S/N 587 and where modification No 50 has not been applied. 
 
    "This aircraft must be operated as a normal category airplane in compliance with the 
operating limitations stated in the form of placards, markings and manual." 
 
    Inverted flight   Prohibited 
    Acrobatic maneuvers  Prohibited 
    Intentional spins   Prohibited 
    Icing Conditions   Prohibited 
     
    Maximum weight     2943 lbs 
    Maneuver speed VA      127 kt  
 
    Never exceed speed VNE     189 kt 
    Flaps extended speed VLE      100 kt 
    Landing gear extended maximum speed VLE   140 kt 
     Landing gear operating maximum speed  VLO      130 kt 
 
    Design positive load factor (Maximum) 
    Flaps retracted                + 3.8 
    Flaps extended                       + 2 
 
2) Aircraft from S/N 588 up to 878, except S/N 823 to 849, and those where  
    modification No 50 has been applied. 
 
    "This airplane must be operated as a normal category airplane in compliance with the 
operating limitations stated in the form of placards, markings and flight manual." 
 
    Inverted flight     Prohibited 
    Acrobatic maneuvers    Prohibited 
    Intentional spins     Prohibited 
    Icing Conditions     Prohibited 
 
    Maximum take-off weight    3086 lbs 
    Maximum computation weight and landing  2943 lbs 
 
Note 2 (Cont.)   Maneuver speed VA     129 kt 
    Never exceed speed VNE     187 kt 
    Flaps extended speed VFE     103 kt 
    Landing gear extended maximum speed VLE   139 kt 
    Landing gear operating maximum speed  VLO   129 kt 
 
    Design positive load factor (Maximum) 
    Flaps retracted                + 3.8 
    Flaps extended                 + 2

A51EU 15 of 20     A51EU 
    3)  Aircraft from S/N 879 
    "This airplane must be operated as a normal category airplane in compliance with the  
    operating limitations stated in the form of placards, markings and flight manual." 
 
    Inverted Flight     Prohibited 
    Acrobatic Maneuvers    Prohibited 
    Intentional Spins     Prohibited 
    Icing Conditions     Prohibited 
 
    Maximum take-off and landing weight   3086 lbs 
    Maneuver speed VA     129 kt 
    Never exceed speed VNE     187 kt 
    Flaps extended maximum speed VFE 
    - Flaps "take-off"      129 kt 
    - Flaps "landing"      103 kt 
    Landing gear extended maximum speed VFE   139 kt 
    Landing gear operating maximum speed VFE   129 kt 
    Design positive load factor (maximum) 
    - Flaps retracted                + 3.8  
    - Flaps extended      + 2 
       
    b) The following placard must be displayed on the baggage door: 
    - Maximum weight:  110 lb or if modification No. 40 is applied 
 
               65 Kg - 143 lbs maximum 
            For loading instructions see 
                         "Weight and Balance Data" in Flight Manual 
 
    c) The following placard must be displayed on the fuel selector: 
    Left tank 43.1 U.S. gal. usable 
    OFF 
    Right tank 43.1 U.S. gal. usable 
 
    d) The following placard must be displayed on each tank: 
 
    100/130 octane or AVGAS 100 LL 
    43.1 U.S. gal. 
 
 e) The following placard must be displayed on each rear window: 
    In emergency, kick out here. 
 
    Model TB 10 
    a) The following placard must be displayed in front of and in clear view of the pilot. 
 
     1) Aircraft up to S/N 822, except S/N 804, 807, 808, and 816 to 819.  
 
    "The airplane must be operated as a normal and utility categori es airplane in compliance 
with the operating limitations stated in the form of placards, markings and manuals." 
 
    Inverted flight     Prohibited 
    Acrobatic maneuvers in normal category   Prohibited  
Note 2 (Cont.)   Intentional spins     Prohibited 
    Icing Conditions     Prohibited 
    Normal Category 
    Maximum take-off weight    2535 lb 
    Maximum landing weight    2407 lb 
    Maneuver speed VA      122 kt 
    Never exceed speed VNE      165 kt 
    Flap extended speed  VFE        95 kt 
     Design limit load factor 
    Flaps retracted             + 3.8

A51EU 16 of 20     A51EU 
    Flaps extended                       + 2 
 
    Utility Category 
    Maximum take-off weight    2359 lb 
    Maximum landing weight    2359 lb 
    Maneuver speed VA      122 kt 
    Never exceed speed VNE      165 kt 
    Flap extended speed VFE          95 kt 
    Design limit load factor 
    Flaps retracted            + 4.4 
    Flaps extended                       + 2  
 
                               Entry Speed 
    Chandelles         135 kt 
    Lazy eight         130 kt 
    Steep turns                     108 kt 
    Stalls 
 
    2)  Aircraft from S/N 823 and S/N 804, 807, 808 and 816 to 819.  
    "This airplane must be operated as a normal and utility categories airplane in compliance 
with the operating limitations stated in the form of placards, markings and manuals." 
 
    Inverted flight     Prohibited 
    Acrobatic maneuvers in normal category  Prohibited  
    Intentional spins     Prohibited 
    Icing conditions     Prohibited 
 
    Normal Category 
    Maximum take-off and landing weight   2535 lbs 
    Maneuver Speed VA    122 KIAS   
                          Never exceed speed VNE     165 KIAS 
    Flap extended speed VFE       95 KIAS 
 
    Design limit load factor 
    Flaps retracted                              + 3.8 
    Flaps extended                                + 2 
 
    Utility Category 
    Maximum take-off weight and landing weight  2359 lbs 
    Maneuver speed VA     122 KIAS 
    Never exceed speed VNE       165 KIAS 
    Flap extended speed VFE       95 KIAS 
    Design limit load factor 
    Flaps retracted                           + 4.4 
    Flaps extended                         + 2 
 
                                        Entry Speed 
    Chandelles             135 KIAS 
    Lazy eight                      130 KIAS         
    Steep turn                                                 108 KIAS 
    Stall 
 
Note 2 (Cont.)   b)  The following placard from the flight manual, (placard 2.12 (3)) must be displayed on 
    the baggage door: 
                 
      Valid up to S / N 399 
                                                                                       
         
                      MAX. MAX.          
       30 Kg 10 Kg       
                                                          66 lbs       22 lbs

A51EU 17 of 20     A51EU 
 
                                                                                      Valid from  S / N 400 
 
 
 
 
 
 
    c)  The following placard must be displayed on the fuel selector 
 
    Left tank 26.9 U.S. gal. usable 
    OFF 
    Right tank 26.9 U.S. gal. usable 
 
    d)  The following placard must be displayed on each fuel tank 
 
    100/130 octane AVGAS 100 LL 
    26.9 U.S. gal. 
 
    e)  The following placard must be displayed on each rear window. 
    In emergency, kick out here. 
 
    Model TB 21 
    a)  The following placard must be displayed in front and in clear view of the pilot. 
 
    1)  Aircraft up to S/N 878. 
 
    "This aircraft must be operated as a normal category airplane in compliance with the 
operating limitations stated in the form of placards, markings and flight manual." 
 
    Inverted flight     Prohibited 
    Acrobatic maneuvers    Prohibited 
    Intentional spins     Prohibited 
    Icing conditions     Prohibited 
 
    Maximum take-off weight    3086 lbs 
    Maximum computation weight and landing  2943 lbs 
 
    Maneuver speed VA     129 kt 
    Never exceed speed VNE     187 kt 
    Flaps extended speed VFE     103 kt 
    Landing gear extended maximum speed VLE   139 kt 
    Landing gear operating maximum speed   VLO    129 kt 
 
    Design positive load factor (Maximum) 
    Flaps retracted              + 3.8 
    Flaps extended                 + 2 
 
    2)  Aircraft from S/N 879 
 
Note 2 (Cont.)   "This airplane must be operated as a normal category airplane in compliance wit h the 
operating limitations stated in the form of placards, markings and flight manual." 
 
    Inverted flight     Prohibited 
    Acrobatic maneuvers    Prohibited 
    Intentional spins     Prohibited 
    Icing conditions     Prohibited 
 
    Maximum take-off and landing weight   3086 lbs 
 
    Maneuver speed VA     129 kt 
65 kg - 143 lbs MAXIMUM 
FOR LOADING INSTRUCTIONS 
SEE "WEIGHT AND BALANCE" 
DATA IN FLIGHT MANUAL

A51EU 18 of 20     A51EU 
    Never exceed speed VNE     187 kt 
    Flaps extended speed VFE 
      - Flaps "TAKE-OFF"   129 kt 
      - Flaps "LANDING"   103 kt 
    Landing gear extended maximum speed VLE   139 kt 
    Landing gear operating maximum speed VLO   129 kt 
    Design positive load factor (Maximum) 
    Flaps retracted             + 3.8 
    Flaps extended              + 2 
 
    b)  The following placard must be displayed on the baggage door: 
 
            65 Kg - 143 lb maximum 
 
                               For loading instructions see 
         "Weight and Balance Data" in Flight Manual 
 
    c)  The following placard must be displayed on the fuel selector: 
 
     Left tank 43.1 U.S. gal. usable 
     OFF 
     Right tank 43.1 U.S. gal. usable 
 
    d)  The following placard must be displayed on each tank: 
 
     100/130 octane AVGAS 100 LL 
     43.1 U.S. gal. 
 
    e)  The following placard must be displayed on each rear window: 
     In emergency, kick out here. 
 
    Model TB 9 
    a)  The following placard must be displayed in front of and in clear view of the pilot. 
 
    "This aircraft must be flown in utility category in accordance with the placards, markings 
and Flight Manual." 
 
    Inverted Flight    Prohibited 
    Acrobatic Maneuvers   Prohibited (except as noted below) 
    Intentional Spins    Prohibited 
    Icing Conditions    Prohibited 
 
    Maximum Weight    2337 lbs 
    Maneuvering speed VA   122 KIAS 
    Never Exceed VNE   165 KIAS 
    Flap Extended Speed VFE     95 KIAS 
    Design Limit Load Factor :  
    Flaps retracted       - 1.8  to  + 4.4 
                    Flaps extended                   0    to  + 2 
 
Note 2 (Cont.)   The following acrobatic maneuvers are permitted in utility category. 
 
         Entry Speed 
    Chandelles       130 KIAS 
    Lazy Eight       124 KIAS 
    Steep Turns       108 KIAS 
    Stalls 
 
    b)  The following placard must be displayed on the baggage door: 
             65 Kg - 143 lb maximum 
          For loading instructions see

A51EU 19 of 20     A51EU 
              "Weight and Balance Data" in Flight Manual 
 
    c)  The following placard must be displayed on the fuel selector 
     Left tank 20.1 U.S. gal. usable 
     OFF 
     Right tank 20.1 U.S. gal. usable  
     or  
     Left tank 26.9 U.S. gal. usable 
     OFF 
     Right tank 26.9 U.S. gal. usable 
 
    d)  The following placard must be displayed on each fuel tank 
     100/130 octane AVGAS 100 LL 
     26.9 U.S. gal. 
     or 
     100/130 octane AVGAS 100 LL 
     20.1 U.S. gal. 
 
    e)  The following placard must be displayed on each rear window. 
    In emergency, kick out here. 
 
    Model TB 200 
    a) The following placard must be displayed in front of and in clear view of the pilot. 
 
    "This airplane must be operated as a normal and utility categories  airplane in compliance 
with the operating limitations stated in the form of placards, markings and manuals." 
 
    Inverted flight     Prohibited 
    Acrobatic maneuvers    Prohibited 
   
    Intentional spins     Prohibited 
    Icing conditions     Prohibited 
 
    Maximum take-off and landing weight   2535 lb 
    Maneuver speed VA     122 kt 
    Never exceed speed VNE     165 kt 
    Flap extended speed VFE      95 kt 
    Design limit load factor 
    Flap retracted     + 3.8 and - 1.5 
    Flap extended                    + 2 and 0 
 
    b) The following placard must be displayed on the baggage door: 
     65 Kg - 143 lb maximum 
 
     For loading instructions see 
     "weight and balance Data" in Flight Manual 
 
    c) The following placard must be displayed on the fuel selector 
     Left tank 26.9 U.S. gal. usable 
     OFF 
Note 2 (Cont.)    Right tank 26.9 U.S. gal. usable 
 
    d) The following placard must be displayed on each fuel tank 
    100/130 octane AVGAS 100 LL 
     26.9 U.S. gal. 
 
    e) The following placard must be displayed on each rear window. 
     In emergency, kick out here. 
       
Note 3.    Service Life Limits

A51EU 20 of 20     A51EU 
    Information with respect to service life limited parts is contained in the applicable 
manufacturer's Maintenance Manual, chapter 4 DGAC approved: 
 
    TB10: Maintenance Manual TB10 revision 4 dated April 1995 DGAC approved on  
    June 11, 1996, and later approved revisions. 
 
    TB9: Maintenance Manual TB9 revision 4 dated April 1995 DGAC approved on 
    June 11, 1996, and later approved revisions. 
 
    TB20: Maintenance Manual TB20 revision 4 dated April 1995 DGAC approved on  
    June 11, 1996, and later approved revisions. 
 
    TB21: Maintenance Manual TB21 revision 4 dated April 1995 DGAC approved on  
    March 4, 1996, and later approved revisions. 
 
    TB200: Maintenance Manual TB21 revision 4 dated April 1995 DGAC approved on  
    June 11, 1996, and later approved revisions. 
       
Note 4.                 Information essential for the proper maintenance of the airplane is contained in the 
SOCATA Maintenance Manual.   
 
Note 5.    Model TB 20 
    Rear seat may be fitted out with three seats: 
    a)  The rear seat is equipped with three separate safety belts in accordance SOCATA 
option No. 502 
    b)  Weight and C.G. position are within limits. 
    c)  3 seats at + 80.1 
 
    Model TB 10 
    Rear seat may be fitted out with three seats: 
    a)  The rear seat is equipped with three separate safety belts in accordance SOCATA 
option No. 502 
    b)  The total weight on the rear seats is under 454 lbs 
    c)  Weight and C.G. position are within limits 
    d)  3 seats at + 80.1 
 
    Model TB 21 
    Rear seat may be fitted out with three seats: 
    a)  The rear seat is equipped with three safety belts in accordance SOCATA option No. 
502 
    b)  Weight and C.G. position are within limits 
    c)  3 seats at + 80.1 
 
    Model TB 9 
    Rear seat may be fitted out with three seats: 
    a)  The rear seat is equipped with three separate safety belts in accordance SOCATA    
          option No. 502 
    b)  The total weight on the rear seats is under 386 lbs  
    c)  Weight and C.G. position are within limits 
    d)  3 seats at + 80.1 
 
Note 5 (Cont.)   Model TB 200 
    Rear seat may be fitted out with three seats: 
    a) The rear seat is equipped with three separate safety belts in accordance SOCATA 
    option No. 502 
    b) The total weight on the rear seats is under 454 lb 
    c) Weight and C.G. position are within limits 
    d) 3 seats at + 80.1 
 
 
.....END.....
```

## ADs (35, in force first)

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- [AD 87-03-11](https://openairdocs.org/ad/87-03-11): Stabilator Rod Ends · SOCATA TB 10, TB 20 and TB 21. Effective Mar 11, 1987
- [AD 86-21-08](https://openairdocs.org/ad/86-21-08): Battery Tray · SOCATA TB 10 and TB 20. Effective Oct 24, 1986
- [AD 86-17-03](https://openairdocs.org/ad/86-17-03): Elevator Attachments · SOCATA TB 20. Effective Sep 22, 1986
- [AD 85-23-07](https://openairdocs.org/ad/85-23-07): Autopilot Systems · Aerostar PA-60-700P (Aerostar 700P), 172L, 172P and 37 more. Effective Jan 27, 1986
- [AD 85-25-02](https://openairdocs.org/ad/85-25-02): Autopilot Systems · King Radio Autopilot Systems, M20J, M20K and 1 more. Effective Jan 27, 1986
- [AD 98-16-03](https://openairdocs.org/ad/98-16-03) (historical): Wing Front Attachments · SOCATA TB 10 and TB9. Effective Sep 21, 1998

## Registered aircraft by registry model (OpenAirDocs)

- [Socata TB-20 TRINIDAD](https://openairdocs.org/model/socata-tb-20-trinidad): 175 aircraft (registry code 8680695)
- [Socata TB 10](https://openairdocs.org/model/socata-tb-10): 53 aircraft (registry code 8680696)
- [Socata TB21](https://openairdocs.org/model/socata-tb21): 50 aircraft (registry code 8680697)
- [Socata TB20](https://openairdocs.org/model/socata-tb20): 25 aircraft (registry code 8680602)
- [Socata TB200](https://openairdocs.org/model/socata-tb200): 11 aircraft (registry code 8680750)
- [Socata Group Aerospatiale TB9](https://openairdocs.org/model/socata-group-aerospatiale-tb9): 1 aircraft (registry code 8680752)

## STCs approved under this data sheet (177, first 50)

- [STC SA02571SE](https://openairdocs.org/stc/SA02571SE): Installation of Garmin G500/G600 TXi Integrated Avionics System (Primary Flight Display, Multi-Function Display, and Engine Indicating System Display).. Garmin International Inc.
- [STC SA12428CH](https://openairdocs.org/stc/SA12428CH): Installation of the Lycoming Engines Electronic Ignition System (EIS). Lycoming Engines, An Operating Division of AVCO Corporation
- [STC SA04837NY](https://openairdocs.org/stc/SA04837NY): Installation of AeroLED's Holdings, LLC., position lights, navigation lights, strobe lights and beacon lights. AeroLED's Holdings, LLC
- [STC SA12406WI](https://openairdocs.org/stc/SA12406WI): Installation of a Garmin AXIS Flight Display System. Garmin International Inc.
- [STC SA04652CH](https://openairdocs.org/stc/SA04652CH): To allow use of 100R grade aviation fuel meeting Swift Fuel, LLC specification. Swift Fuels LLC
- [STC SA02636SE](https://openairdocs.org/stc/SA02636SE): Installation of Garmin GPS 175 Navigation System and GNX 375 Navigation System with ADS-B In/Out Transponder.. Garmin International Inc.
- [STC SA02019SE-D](https://openairdocs.org/stc/SA02019SE-D): Installation of Garmin Model GTN 625/635/650; 725/750 Navigation System. Garmin International Inc.
- [STC SA02511SE](https://openairdocs.org/stc/SA02511SE): Installation of replacement fuel quantity indicator sending unit(s). CiES Inc.
- [STC SA01866WI](https://openairdocs.org/stc/SA01866WI): Installation of Garmin GFC 500 Autopilot with Electronic Stability and Protection. Garmin International Inc.
- [STC SA00081NY](https://openairdocs.org/stc/SA00081NY): Installation of Iceman Aviation Supplies, Inc. Carburetor Ice Detector.. Alcor LLC
- [STC SA04046CH PAGE 2](https://openairdocs.org/stc/SA04046CH%20PAGE%202): Installation of L-3 GENESIS  (TM) Electronic Standby Instrument System (ESI-500/MAG-500). Acron Aviation Inc.
- [STC SA04378CH](https://openairdocs.org/stc/SA04378CH): Installation of an engine modified per STC SE04349CH. SureFly Partners Ltd.
- [STC SA02594SE](https://openairdocs.org/stc/SA02594SE): SkyView HDX Instrumentation and Autopilot System manufactured. Dynon Avionics
- [STC SA02386AK](https://openairdocs.org/stc/SA02386AK): Replacement of existing landing and/or taxi light reflector and bulbs with Light Emitting Diode (LED) lighting systems. AeroLED's Holding LLC
- [STC SA01757WI](https://openairdocs.org/stc/SA01757WI): To allow the use of UL91 or UL94 (minimum) grade aviation fuel. Swift Fuels LLC
- [STC SA04568CH](https://openairdocs.org/stc/SA04568CH): Installation of the uAvionix tailBeaconX, a tail mounted position light with integrated Automatic Dependent Surveillance - Broadcast (ADS-B) Out and 1090MHz Mode-S transponder functionality. uAvionix Corporation
- [STC SA02658SE](https://openairdocs.org/stc/SA02658SE): Installation of Garmin GI 275 Multi-Function Display System. Garmin International Inc.
- [STC SA1069NE](https://openairdocs.org/stc/SA1069NE): Installation of a Sensenich Model74DM6S8 fixed-pitch-metal propeller.. Sensenich Propeller Company
- [STC SA02019WI](https://openairdocs.org/stc/SA02019WI): Installation of the Trig Avionics TX56, TX56A, TX57, or TX57A VHF Nav-Com Radio.. Peregrine
- [STC SA04400NY](https://openairdocs.org/stc/SA04400NY): Installation of the Integrated Back-up Battery System (IBBS). TCW Technologies LLC
- [STC SA01435LA](https://openairdocs.org/stc/SA01435LA): Installation of engines modified with Firewall Forward Technologies LLC modified camshaft. Centri-Lube Technologies LLC
- [STC SA04192NY](https://openairdocs.org/stc/SA04192NY): KFD 900 Primary Flight Display System Additional Functions. Honeywell International Inc
- [STC SA00756DE](https://openairdocs.org/stc/SA00756DE): Installation of Automatic Dependent Surveillance  Broadcast (ADS-B) Out Equipment using a Trig Avionics TT22 Transponder and an approved Global Positioning System (GPS) Position Sensor. Peregrine
- [STC SA11137SC](https://openairdocs.org/stc/SA11137SC): Installation of Plane-Power ALT-FLX alternator. Hartzell Engine Technologies, LLC
- [STC SA04586CH](https://openairdocs.org/stc/SA04586CH): Installation of Electroair Back Up Battery Panel System Control. Electroair Aquisition Corp.
- [STC SA00076IB](https://openairdocs.org/stc/SA00076IB): Installation of Photo luminescent Safety Systems. STG AEROSPACE GERMANY GmbH
- [STC SA01967WI](https://openairdocs.org/stc/SA01967WI): Use of GAMI G100UL High Octane Unleaded Avgas. General Aviation Modifications Inc.
- [STC SA02203AK](https://openairdocs.org/stc/SA02203AK): Installation of FlightLogic Synthetic Vision Electronic Flight Information System (EFIS-SV).. Genesys Aerosystems Inc.
- [STC SA02444AK](https://openairdocs.org/stc/SA02444AK): Approval of the L-3 Communications NGT 9000/9000R ADS-B system installed. ADS-B Technologies LLC
- [STC SA01818WI](https://openairdocs.org/stc/SA01818WI): Installation of Garmin G5 Electronic Flight Instrument. Garmin International Inc.
- [STC SA09902AC](https://openairdocs.org/stc/SA09902AC): Installation of BendixKing KFD 900 Flight Display System. Honeywell International Inc. (Bendix King)
- [STC SA11174SC PAGE 2](https://openairdocs.org/stc/SA11174SC%20PAGE%202): Installation of BendixKing by Honeywell KSN 770 and KSN 765 WAAS LPV approach capable nav/comm systems. Honeywell International Inc (Bendix King)
- [STC SA10822SC](https://openairdocs.org/stc/SA10822SC): Installation of EFD1000 Primary Flight Display. Aspen Avionics Inc.
- [STC SA00401BO](https://openairdocs.org/stc/SA00401BO): Installation of a SkyTrax100B UAT receiver. Avidyne Corporation
- [STC SA04181NY](https://openairdocs.org/stc/SA04181NY): Installation of the KFC 230 Aerocruze Automatic Flight Control System. Honeywell International Inc
- [STC SA04182NY](https://openairdocs.org/stc/SA04182NY): Installation of BendixKing KA 310 Autopilot Adapter. Honeywell International Inc
- [STC SA00410BO](https://openairdocs.org/stc/SA00410BO): Installation of an AV-30-C Multi-Mode Indicator. uAvionix Corporation
- [STC SA01831WI](https://openairdocs.org/stc/SA01831WI): To allow the use of UL91 (minimum) grade aviation fuel. Petersen Aviation Inc
- [STC SA10236SC](https://openairdocs.org/stc/SA10236SC): Installation of a GDC 31 Roll Steering Converter. DAC International Inc
- [STC SA00900WI-D](https://openairdocs.org/stc/SA00900WI-D): Installation of Bendix/King KMD 550 Multi-Function Display.. Honeywell International Inc
- [STC SA00826WI-D](https://openairdocs.org/stc/SA00826WI-D): Installation of Bendix/King KFC 225 automatic flight control system. Honeywell International Inc
- [STC SA00827WI-D](https://openairdocs.org/stc/SA00827WI-D): Installation of Bendix/King KMD 150 MFD Multi-Function Display.. Honeywell International Inc
- [STC SA1786CE-D](https://openairdocs.org/stc/SA1786CE-D): Installation of the King Model KNS 80 navigation system.. Honeywell International Inc
- [STC SA1787CE-D](https://openairdocs.org/stc/SA1787CE-D): Installation of the King Model KNS 81 navigation system.. Honeywell International Inc
- [STC SA1785CE-D](https://openairdocs.org/stc/SA1785CE-D): Install KAP 100 single axis, KAP 150 two axis, or KFC 150 two axis flight control system with optional KAS 297B vertical speed and altitude selector. Honeywell International Inc
- [STC SA01560WI-D](https://openairdocs.org/stc/SA01560WI-D): Installation of the Honeywell KFD 840 Primary Flight Display System.. Honeywell International Inc
- [STC SA01714WI](https://openairdocs.org/stc/SA01714WI): Installation of a Garmin transponders: (a) GTX 330/330D/33/33D with ADS-B Out functionality; (b) GTX 335/335R/345/345R with ADS-B Out and In functionality; or (c) GTX 335R/345R with ADS-B Out functionality in select airplanes installed with G950/G1000 systems.. Garmin International Inc
- [STC SA03286CH](https://openairdocs.org/stc/SA03286CH): Install an electronic engine ignition system. Electroair Acquisition Corporation
- [STC SA04032CH](https://openairdocs.org/stc/SA04032CH): Install rocker switch assemblies. Electroair Acquisition Corporation
- [STC SA08991AC](https://openairdocs.org/stc/SA08991AC): Installation of vapor cycle air conditioning system. Air Comm Corporation

All 177: https://openairdocs.org/tcds/A51EU/stcs.md

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