TCDS A51EU

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