# TCDS A60EU: Daher Aircraft SAS - Type: Type certificate data sheet - Status: Current - Holder: Daher Aircraft SAS - Revision: 40 - Revised: April 24, 2026 - Product: Aircraft, Small Airplane - Certification basis: Part 21, Part 23 - Registered aircraft: 1,000, by the registry models matched to it (OpenAirDocs) - Data sheet PDF: https://openairdocs.org/files/sha256/9e/35/9e3588247658bd833343d0b5427f4a372644bb031fd07ed0e95c5988c2006a84 - FAA DRS: https://drs.faa.gov/browse/excelExternalWindow/DRSDOCID103072862720260427180201.0001 - Page: https://openairdocs.org/tcds/A60EU ## Models (1) As the data sheet lists them. - TBM 700 ## 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 No. 1 2 3 4 5 6 7 8 9 10 11 12 13 14 15 16 17 18 19 20 Rev. No. 40 37 37 23 25 31 38 39 32 37 39 37 32 39 39 39 39 39 40 39 DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION TYPE CERTIFICATE DATA SHEET NO. A60EU This data sheet which is part of Type Certificate No. A60EU prescribes 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 AIRCRAFT, SAS Immeuble BELAIA 7 Avenue de l’Union F-94310 ORLY Type Certificate Holder Record Name of the TC Holder is changed from DAHER AEROSPACE to DAHER AIRCRAFT, SAS on August 19, 2025 (see note 28) I. Model TBM 700, 6 PCLM (Normal Category) approved August 28, 1990. [See note 14, certification Basis section, and Equipment section for information on different versions and trade names of the TBM 700.] Engine Airplanes not equipped with modification No MOD. 70-0188-00 (see note 7): Pratt and Whitney of Canada, Ltd., PT6A-64 Turbo prop Airplanes equipped with modification No MOD. 70-0188-00 (see note 7): Pratt and Whitney of Canada, Ltd., PT6A-66D Turbo prop Airplanes equipped with modification No MOD. 70-0621-76: Pratt and Whitney of Canada, Ltd., PT6E-66XT Turbo prop Fuel Jet A, Jet A1, Jet B, JP4, JP5, JP8, anti-ice additive according to the specification MIL-I- 27686 E or specification MIL-I-85470 A in the following proportions: minimum content 0.06% by volume maximum content 0.15% by volume Engine Limits Airplanes not equipped with modification No MOD. 70-0188-00 (see note 7): Take-off and maximum continuous power 700 SHP Gas generator rotation speed 39 000 RPM (104.1 %) Propeller rotation speed 2 000 RPM Interturbine maximum temperature 800ºC Oil: minimum pressure 60 psi maximum pressure 135 psi maximum temperature 104ºC Airplanes equipped with modification No MOD. 70-0188-00 (see note 7) and not equipped with modification No MOD70-0357-7 (see note 23): Take-off power (flap extended) 700 SHP Maximum continuous power (flap up) 850 SHP Gas generator rotation speed 39 000 RPM (104.1 %) Propeller rotation speed 2 000 RPM Interturbine maximum temperature for take off 850ºC Interturbine maximum temperature for climb/cruise 840ºC Oil: minimum pressure 60 psi maximum pressure 135 psi maximum temperature 104ºC A60EU Revision 40 DAHER AIRCRAFT TBM 700 April 24, 2026 Page 2 of 20 Airplanes equipped with modification No MOD. 70-0188-00 (see note 7) and equipped with modification No MOD70-0357-71 (see note 23): Take-off power (flap extended) 850 SHP Maximum continuous power (flap up) 850 SHP Gas generator rotation speed 39 000 RPM (104.1 %) Propeller rotation speed 2 000 RPM Interturbine maximum temperature for take off 850ºC Interturbine maximum temperature for climb/cruise 840ºC Oil: minimum pressure 60 psi maximum pressure 135 psi maximum temperature 104ºC Airplanes equipped with modification No MOD. 70-0621-76 and modification No MOD70-0665-61: Take-off power (flap extended) 895 SHP Maximum continuous power (flap up) 895 SHP Gas generator rotation speed 39 000 RPM (104 %) Propeller rotation speed 1 925 RPM Interturbine maximum temperature for take off 850ºC Interturbine maximum temperature for climb/cruise 825ºC Oil: minimum pressure 60 psi maximum pressure 135 psi maximum temperature 104ºC Propeller and Propeller Limits Aircraft not equipped with optional SOCATA modification No MOD70-0345-61 HARTZELL Constant speed HC-E4N-3 / E9083 S (K) Diameter: not over 91 in., not under 90 in. Pitch setting at 30 in., sta.: Low 21º Feather 86º Reverse - 11º Aircraft equipped with optional SOCATA modification No MOD70-0345-61 HARTZELL Constant speed HC-E5N-3C / NC8834 K Diameter: not over 91 in., not under 90 in. Pitch setting at 30 in., sta.: Low 19.5º Feather 85º Reverse - 9º Aircraft equipped with optional SOCATA modification No MOD70-0665-61 HARTZELL Constant speed 5D31-NK366B1/86DB01B Diameter: not over 91 in., not under 90 in. Pitch setting at 30 in., sta.: Low 19.5º Feather 86.1º Reverse - 9.3º Airspeed Limits Aircraft not equipped with MOD70-0357-71 (see note 23): VMO (Maximum operating speed) 271 KCAS VA (Maneuvering speed) 160 KCAS VFE (Maximum flaps extended speed) Landing configuration 120 KCAS Takeoff configuration 180 KCAS VLO (Maximum landing gear operation speed) retraction 130 KCAS extension 180 KCAS VLE (Maximum landing gear extended speed) 180 KCAS Aircraft equipped with MOD70-0357-71(see note 23): VMO (Maximum operating speed) 270 KCAS VA (Maneuvering speed) 160 KCAS Page 3 of 20 VFE (Maximum flaps extended speed) Landing configuration 120 KCAS Takeoff configuration 180 KCAS VLO (Maximum landing gear operation speed) Retraction 151 KCAS extension 180 KCAS VLE (Maximum landing gear extended speed) 180 KCAS C.G. Range Airplanes not equipped with modification No. MOD 70-139-00 (see note 6): (+ 181.3) to (+ 194.9) at 4409 lbs. or less (+ 183.6) to (+ 194.9) at 6250 lbs. or less (+ 184.8) to (+ 194.3) at 6579 lbs. or less Straight line between points given. Airplanes equipped with modification No. MOD 70-139-00 (see note 6): (+ 181.3) to (+ 194.9) at 4409 lbs. or less (+ 183.6) to (+ 194.9) at 6250 lbs. (+ 185.3) to (+ 194.3) at 6579 lbs. (+ 187) forward limit at 7024 lbs. (+ 187) to (+ 193.65) at 7394 lbs. Straight line between points given. Airplanes equipped with modification No. MOD 70-680-10: (+ 181.3) to (+ 194.9) at 4409 lbs. or less (+ 183.6) to (+ 194.9) at 6250 lbs. (+ 185.3) to (+ 194.3) at 6579 lbs. (+194.0) aft limit at 6986 lbs. (+ 187) forward limit at 7024 lbs. (+ 187) to (+ 193.7) at 7394 lbs. (+ 193.4) to (+ 193.6) at 7615lbs. Straight line between points given. Empty Weight C.G. Range None Datum 118.11 in. ahead of firewall front face. Leveling Means Cabin floor mounting rail. Maximum Weight Airplanes not equipped with modification No. MOD 70-139-00 (see note 6): 6579 lbs.: takeoff 6250 lbs.: landing 6614 lbs.: ramp Airplanes equipped with modification No. MOD 70-139-00 (see note 6): 7394 lbs.: takeoff 7024 lbs.: landing 7430 lbs.: ramp Airplanes equipped with modification No. MOD 70-0680-10: 7615 lbs.: takeoff 7110 lbs.: landing 7650 lbs.: ramp Number of Seats & Maximum Baggage Airplanes not equipped with modification No. MOD70-0315-25 (see note 17) Standard version Seats limits 1 thru 6 seats Baggage Page 4 of 20 - In the front compartment: 110 lbs. at 128.0 See * 1 - Behind the cabin: 220 lbs. at 297.6 See * 2 - Behind the cabin: 220 lbs. at 303 100 lbs. at 303 See * 3 See * 4 - In the rear compartment: 77 lbs. at 340.9 See * 5 * 1: Valid S/N 1 to 243, except S/N 205 and 240 and from S/N 434. * 2: Valid S/N 1 to 23, 25, 28, 33 and 35, except airplanes equipped as a retrofit with modification No. MOD 70-019-25. * 3: Valid S/N 24, 26, 27, 29 to 32, 34, 36 to 9999, except airplanes equipped with modification No. MOD 70-139-00 (see note 6), plus airplanes equipped as a retrofit with modification No. MOD 70-019-25. * 4: Valid airplanes equipped with modification No. OPT 70-01-029 or modification No. MOD 70-139-00 (see note 6) * 5: Valid for airplanes equipped with modifications No. MOD 70-139-00 (see note 6) or MOD 70-140-00 Not valid for aiplanes equipped with modification No. MOD70-0207-00. 7- place accommodation A. Option No. OPT 70-25-002 A Seats limits 1 to 7 seats - L.H. and R.H. front seats at +180.5 - L.H. and R.H. intermediate seats at +216.8 - R.H. rear seat at +249.0 - two-place rear divan at +283.6 Baggage limits - In the front compartment: 110 lbs. at 128.0 - Behind the cabin: 77 lbs. at 309.0 B. Option No. OPT 70-25-002 B or Option No. OPT 70-25-002 C Seat Limits 1 to 7 seats - L.H. and R.H. front seats at +180.5 - L.H. intermediate seats at +223.1 - R.H. intermediate seats at +209.5 - R.H. rear seat at +239.5 - two place rear divan at +272.3 Baggage limits - In the front compartment: 110 lbs. at 128.0 - Behind the cabin: 77 lbs. at 303.0 Airplanes equipped with modification No. MOD70-0315-25 (see note 17) 6-seat accommodation Seats limits 1 thru 6 seats - 2 seats at +180.5 - 2 seats at +224.8 - 2 seats at +259.3 Baggage limits - In the front compartment: 110 lbs. at 128.0 - Behind the cabin: 220 lbs. at 297.6 4- seat accommodation Page 5 of 20 Seats limits 1 thru 4 seats - 2 seats at +180.5 - 2 seats at +224.8 Baggage limits - In the front compartment: 110 lbs. at 128.0 - Behind the cabin: 220 lbs. at 303.0 176 lbs. at 259.3 Fuel Capacity Airplanes not equipped with modification No. MOD 70-0211-57: 290.6 gal. (two 145.3 gal. at + 189.8 : 281.6 gal. usable) See Note 1 for weight and unusable fuel Airplanes equipped with modification No. MOD 70-0211-57: 301 gal. (two 150.5 gal. at + 189.8 : 292 gal. usable) See Note 1 for weight and unusable fuel Oil Capacity 12.7 qt (at + 82.3 - 6 qt unusable) See Note 1 for weight Maximum Operating Altitude Airplanes not equipped with modifications No. OPT 70-01-026 MOD 70-139-00 nor MOD 70-140-00: 30,000 ft. Airplanes equipped with modifications No. OPT 70-01-026 MOD 70-139-00 or MOD 70-140-00: 31,000 ft. Control Surface Movements Elevator (Angles references: stabilator chord) Nose-up attitude: 30º ± 1.5º Nose-down attitude: 10º ± 1º Stabilator tab (elevator at 0º) Nose-up attitude: 15º ± 1º Nose-down attitude: 20º ± 1º Roll - Ailerons (Reference: wing chord) up 15º ± 1º down 20º ± 1º - Spoiler (Reference: wing upper surface) up 58º +2°/-3° down 20.5º +1°/-5° - Tab up 14º ± 1º down 14º ± 1º Yaw control Rudder (Reference: fin chord) left turn 26º ± 1º right turn 35º ± 1.5º Rudder tab (Reference: rudder chord) left turn 13.5° ± 1° right turn 9.5° ± 1° Certification Basis Effective date of certification basis: January 15, 1987 Date of U.S. application: January 22, 1988 Type Certificate issued on August 28, 1990 Type Certification under 14 CFR Section 21.29 including the following requirements: Airplanes not equipped with modification No. MOD 70-139-00 (see note 6): - 14 CFR Part 23 effective February 1, 1965, including Amendments 23-1 through 23-34 and Sections 23.783, 23.811 and 23.807 of Amendments 36 Page 6 of 20 - 14 CFR Part 36 effective December 1, 1969, including Amendments 36-1 through Amendment 36-17. - Special Federal Aviation Regulation Number 27, effective February 1, 1974 including Amendments 27-1 through 27-6. Airplanes equipped with modification No. MOD 70-139-00 (see note 6): - 14 CFR Part 23 effective February 1, 1965, including Amendments 23-1 through 23-34, Sections 23.783, 23.811 and 23.807 of Amendments 36 and Sections 23.49, 23.561, 23.562 and 23.785 of Amendment 44. - 14 CFR Part 34 effective September 10,1990, including Amendments 34-1 through Amendment 34-3. - 14 CFR Part 36 effective December 1, 1969, including Amendments 36-1 through Amendment 36-22. Airplanes (s/n 434 -999, except 687) equipped with modification No. MOD 70 -0211-57 (“Fuel tanks extension”), modification No. MOD 70 -0176-00 (“Garmin G1000”), and optional modification No. MOD 70-0226-00 (“SVS” option to G1000) (see notes 8, 9, 10, 11, 12): - 14 CFR Part 23 effective February 1, 1965, including Amendments 23-1 through 23-34, Section 23.1301 of Amendment 23-20, Sections 23.783, 23.811 and 23.807 of Amendments 36, Sections 23.1322 and 23.1331 of Amendment 43, Sections 23.49, 23.561, 23.562 and 23.785 of Amendment 44, Sections 23.1309, 23.1311 23.1321, 23.1323, 23.1353, 23.1365 and 23.1431 of Amendment 49 and Section 23.1308 of Amendment 57. - 14 CFR Part 34 effective September 10, 1990, including Amendments 34-1 through Amendment 34-3. - 14 CFR Part 36 effective December 1, 1969, including Amendments 36-1 through Amendment 36-22. Airplanes (s/n 687, 1000 -1105) equipped with modification MOD 70 -0176-00 (“Garmin G1000”), modification No. MOD 70 -0234-24 (“New electrical generation and primary distribution”), MOD70-0322-00 (“Aerodynamic efficiency improvement”), MOD70- 0323-71 (“Propulsion efficiency improvement”), MOD70-0324-00 (“Human Machine Interface improvement”), MOD70-0357-71 (“Take-off and landing operations at 850SHP”), optional modification No MOD70-0345-61 (“New five-blade propeller”), optional modification No. MOD70-407-00 (“Aural alerts evolution and V15 Software for G1000 Integrated Flight Deck on TBM850/900“) and optional modification No. MOD70- 0407-00 Ed 2 Version C (“ESP and USP option to G1000”) (see notes 18, 19, 20, 21, 22 and 23): or Airplanes (s/n 1170-9999) equipped with modification MOD 70-0176-00 (“Garmin G1000”) and optional modification MOD70-0539-00 (“Garmin G1000 Nxi”), modification No. MOD 70-0234-24 (“New electrical generation and primary distribution”), MOD70-0322-00 (“Aerodynamic efficiency improvement”), MOD70- 0323-71 (“Propulsion efficiency improvement”), MOD70 -0324-00 (“Human Machine Interface improvement”), MOD70-0357-71 (“Take-off and landing operations at 850SHP”), optional modification No MOD70-0345-61 (“New five-blade propeller”), optional modification No. MOD70-407-00 (“Aural alerts evolution and V15 Software for G1000 Integrated Flight Deck on TBM850/900“) and optional modification No. MOD70- 0407-00 Ed 2 Version C (“ESP and USP option to G1000”) (see notes 18, 19, 20, 21, 22, 23, 24 and 25): - 14 CFR Part 23 effective February 1, 1965, including Amendments 23-1 through 23-34, Section 23.1301 of Amendment 23-20, Sections 23.783, 23.811 and 23.807 of Amendments 36, Sections 23.1322 and 23.1331 of Amendment 43, Sections 23.49, 23.561, 23.562 and 23.785 of Amendment 44, Sections 23.1309, 23.1311 23.1321, 23.1323, 23.1353, 23.1365 and 23.1431 of Amendment 49, Section 23.207 of Amendment 50, Section 23.1308 of Amendment 57 and Section 23.1306 of Amendment 61. (Note: Airplanes equipped with optional modification No. MOD70 - 0423-34 “Lift transducer and AOA” also include Section 23.207 of Amendment 50. Airplanes equipped with opti onal modification No. MOD70 -0388- 25 “AMSAFE Airbag Seatbelt on Pilot and Co-Pilot Seats” also include FAA Special Conditions No. 23-276-SC.) - 14 CFR Part 34 effective September 10,1990, including Amendments 34-1 through Amendment 34-3. - 14 CFR Part 36 effective December 1, 1969, including Amendments 36-1 Page 7 of 20 through Amendment 36-28. Airplanes (s/n 1111-1215) equipped with optional modification No. MOD70-0476-00 (“Garmin G3000” including ESP and USP option to G3000), modification No. MOD 70- 0234-24 (“New electrical generation and primary distribution”), MOD70-0322-00 (“Aerodynamic efficiency improvement”), MOD70-0323-71 (“Propulsion efficiency improvement”), MOD70-0324-00 (“Human Machine Interface improvement”), MOD70- 0357-71 (“Take-off and landing operations at 850SHP”) and optional modification No MOD70-0345-61 (“New five-blade propeller”) (see notes 18, 19, 20, 21, 22 and 23): or Airplanes (s/n 1216-9999) equipped with optional modification No. MOD70-0476-00 (“Garmin G3000” including ESP and USP option to G3000) and optional modification No. MOD70-0549-00 (“Garmin G3000 2018”), modification No. MOD 70-0234-24 (“New electrical generation and primary distribution”), MOD70-0322-00 (“Aerodynamic efficiency improvement”), MOD70-0323-71 (“Propulsion efficiency improvement”), MOD70-0324-00 (“Human Machine Interface improvement”), MOD70-0357-71 (“Take- off and landing operations at 850SHP”) and optional modification No MOD70-0345-61 (“New five-blade propeller”) (see notes 18, 19, 20, 21, 22, 23, 24 and 26): or Airplanes (s/n 1272, 1275-9999) equipped with optional modification No. MOD70 -0476- 00 (“Garmin G3000” including ESP and USP option to G3000), optional modification No. MOD70-0549-00 (“Garmin G3000 2018”) and optional modification No. MOD70 -0649- 00 (“G3000 system Software V21.25”), modification No. MOD 70-0234-24 (“New electrical generation and primary distribution”), MOD70-0322-00 (“Aerodynamic efficiency improvement”), MOD70-0323-71 (“Propulsion efficiency improvement”), MOD70-0324-00 (“Human Machine Interface improvement”), MOD70 -0357-71 (“Take- off and landing operations at 850SHP”), optional modification No MOD70-0345-61 (“New five-blade propeller”), modification No. MOD70-0550-00 (“Auto-throttle”), modification No. MOD70-0619-11 (“Modification of cabin interior markings”) and optional modification No. MOD70 -0632-34 (“Magnetometer MD032 integration”) (see notes 18, 19, 20, 21, 22, 23, 24, 31 and 32): or Airplanes (s/n 1333 -9999) equipped with optional modification No. MOD70 -0476-00 (“Garmin G3000” including ESP and USP option to G3000), optional modification No. MOD70-0549-00 (“Garmin G3000 2018”) and optional modification No. MOD70-0649- 00 Version E (G3000 system new Software SR 5.1.8) and optional modification No. MOD70-0650-34 (“Emergency Autoland/HomeSafe system”), modification No. MOD 70- 0234-24 (“New electrical generation and primary distribution”), MOD70-0322-00 (“Aerodynamic efficiency improvement”), MOD70-0323-71 (“Propulsion efficiency improvement”), MOD70-0324-00 (“Human Machine Interface improvement”), MOD70 - 0357-71 (“Take-off and landing operations at 850SHP”), optional modification No MOD70-0345-61 (“New five-blade propeller”), modification No. MOD70-0550-00 (“Auto-throttle”), modification No. MOD70 -0619-11 (“Modification of cabin interior markings”) and optional modification No. MOD70 -0632-34 (“Magnetometer MD032 integration”) (see notes 18, 19, 20, 21, 22, 23, 24, 31, 32 and 33): - 14 CFR Part 23 effective February 1, 1965, including Amendments 23-1 through 23-34, Section 23.1301 of Amendment 23-20, Sections 23.783, 23.811 and 23.807 of Amendments 36, Sections 23.1322 and 23.1331 of Amendment 43, Sections 23.49, 23.561, 23.562 and 23.785 of Amendment 44, Sections 23.1309, 23.1311 23.1321, 23.1323, 23.1353, 23.1365 and 23.1431 of Amendment 49, Section 23.207 of Amendment 50, Section 23.1308 of Amendment 57 and Section 23.1306 of Amendment 61. (Note: Airplanes equipped with optional modification No. MOD70 - 0423-34 “Lift transducer and AOA” also include Section 23.207 of Amendment 50. Section 1308 of Amendment57 and Section 23.1306 of Amendment 61. - 14 CFR Part 34 effective September 10,1990, including Amendments 34-1 through Amendment 34-3. - 14 CFR Part 36 effective December 1, 1969, including Amendments 36-1 through Amendment 36-28. Airplanes (s/n 1408-9999) equipped with modifications No. MOD70-0646-21 (“ENVIRO components based ECS”), modification No. MOD70 -0753-00 (“Software Upgrade”), modification No. MOD70-0680-10 (“Weight and balance modification”): - 14 CFR Part 23 effective February 1, 1965, including Amendments 23-1 through 23-34, Section 23.1301 of Amendment 23-20, Sections 23.783, 23.811 and 23.807 of Amendments 36, Sections 23.1322 and 23.1331 of Amendment 43, Sections Page 8 of 20 23.49, 23.561, 23.562 and 23.785 of Amendment 44, Sections 23.1309, 23.1311 23.1321, 23.1323, 23.1353, 23.1365 and 23.1431 of Amendment 49, Section 23.207 of Amendment 50, Section 23.1308 of Amendment 57 and Section 23.1306 of Amendment 61. (Note: Airplanes equipped with optional modification No. MOD70 - 0423-34 “Lift transducer and AOA” also include Section 23.207 of Amendment 50. Section 1308 of Amendment 57 and Section 23.1306 of Amendment 61. - 14 CFR Part 34 effective September 10,1990, including Amendments 34-1 through Amendment 34-3. - 14 CFR Part 36 effective December 1, 1969, including Amendments 36-1 through Amendment 36-28. Airplanes (s/n 140 8-9999) equipped with modifications No. MOD70-0621-76 (“Engine power increase, Engine control and e-Throttle”), modification No. MOD70-0665-61 (“Five blades Raptor Propeller”): - 14 CFR Part 23 at Amendment 23-64 sections 23.2005, 23.2010, 23.2105, 23.2115(a)(1)(2)(3)(b), 23.2120(a)(1)(2)(c), 23.2125, 23.2135, 23.2140, 23.2145, 23.2155, 23.2160, 23.2200, 23.2205, 23.2210, 23.2215, 23.2225, 23.2230, 23.2235, 23.2240(a)(b)(c)(1)(2), 23.2245, 23.2300, 23.2335, 23.2400(a)(b)(c)(1)(2)(3)(4)(e), 23.2405, 23.2410, 23.2415, 23.2420, 23.2425, 23.2500(a)(1)(2), 23.2505, 23.2510, 23.2515, 23.2520, 23.2525, 23.2600, 23.2605, 23.2610, 23.2615, 23.2620, Appendix A - 14 CFR Part 23, including Amendments 23-1 through Amendment 23-62. - -Sections 23.201, 23.203, 23.207, 23.221 - 14 CFR Part 34 effective September 10,1990, including Amendments 34-1 through Amendment 34-6. - 14 CFR Part 36 effective December 1, 1969, including Amendments 36-1 through Amendment 36-31, Appendix G. Equivalent Safety Items: Equivalent levels of safety finding made per the provisions of 14 CFR Part 21.21(b)(1) for: ELOS ACE-02-01: 14 CFR §23.807(a)(1), Emergency Exits; Refer to FAA letter dated October 7, 2001, applicable to cargo configured airplanes only (See Note 4.) ELOS ACE-14-01: 14 CFR §23.777(d) Cockpit Controls Location and 14 CFR §23.781(b), Shape – Single Power Lever for TBM 700 dated December 12, 2013, applicable to aircraft equipped with MOD70-0324-00 (see note 21) ELOS AT01004CE-A-P-2: 14 CFR §23.1305(e),(j, and (m), amendment 23-24, Part Time and Full Time Digital Only Powerplant Indications, applicable for aircraft equipped with MOD70-0550-00 (see note 31) ELOS AT01078CE-A-S-2: 14 CFR part 23 §23.671, 23.697, 23.729, 23.777, 23.779, 23.991, 23.1141, 23.1189, 23.1301, 23.1303, 23.1305, 23.1309, 23.1311, 23.1321, 23.1322, 23.1337, 23.1555, Airplanes equipped with DAHER modification No. MOD70-0650-34 (“Emergency Autoland/HomeSafe System”) s/n 1272, 1275-9999 ELOS AT11910IB-A-23.1303:14 CFR 21.21(b)(1), 23.1301, 23.1303, 23.1309, 23.1311, 23.1321, 23.1459 Indications removal from Primary Flight Displays during ground phase on Model Daher TBM700N airplane Airplanes equipped with DAHER modification No. MOD70-0876-00 Special Conditions: Special Condition per the provisions of 14 CFR Part 21.21(b)(1) for: Special Condition No. 23-276-SC Airbag seatbelt on Pilot and Co-Pilot Seats (See Note 24) Special Condition No. 23-296-SC Autothrust System effective August 30, 2019 (See Note 31) Approved for flight into known icing. Page 9 of 20 Direction Générale de l’Aviation Civile (DGAC) originally type certified this aircraft under its type certificate number TC 181, and EASA Type Certificate Number EASA.A.010. The FAA validated this product under U.S. Type Certificate Number A60EU. Effective September 28, 2003, the European Aviation Safety Agency (EASA) began oversight of this product on behalf of France. Serial Nos. Eligible Serial Numbers 0001-9999 Import Requirements A Certificate of Airworthiness for Export endorsed as noted in this section must be submitted for each individual aircraft for which application for U.S. certification is made. a) To be considered eligible for operation in the United States, each aircraft manufactured under this type certificate must be accompanied by a certificate of airworthiness for export or certifying statement endorsed by the exporting foreign civil airworthiness authority which states (in the English language): This aircraft conforms to its U.S. type design (type certificate number A60EU) and is in a condition for safe operation. b) The U.S. airworthiness certification basis for aircraft type certificated under FAR Section 21.29 and exported by the country of manufacture is FAR Sections 21.183 (c) or 21.185(c). c) The U.S. airworthiness certification basis for aircraft type certificated under FAR Section 21.29 exported from countries other than the country of manufacture (e.g., third party country) is FAR Section 21.183(d) or 21.183(b). 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. airworthiness regulations 14 CFR 23 approved under U.S. Type Certificate No. A60EU 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 cer tificate for imported aircraft. 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: Main equipment list: NAV Nr 34/90 edition 2 or later revision In addition, the following items of equipment are required: French DGAC or EASA approved Pilot's Operating Handbook For aircraft with the Modification No. MOD 70 -091-52 “Wide Entrance Door” or Option No. OPT 70-52-002 “Pilot Door”, the Pilot’s Operating Handbook must be at revision 7 or later revision. For aircraft with option No OPT 70 -25-027 Cargo Transportation Capability installed, Pilot’s Operating Handbook Supplement 30 revision 2 or later revision must be utilized. For aircraft with Modification No MOD 70 -140-00 “TBM 700 C1 version”, the “C1 version” of the Pilot's Operating Handbook is required. For aircraft with Modification No MOD 70 -139-00 (see note 6), the “C1 version” of the Pilot's Operating Handbook is required and Pilot's Operating Handbook Supplement 41 “TBM 700 C2”must be utilized. For aircraft with Modification No. MOD 70-0188-00 “TBM 700 N version”, the “TBM850” Rev 1 (P/N T00.DMNFM00EEN) or later approved Pilot's Operating Handbook revision is required (see note 7). For aircraft with Modification No. MOD 70-0176-00, Pilot's Operating Handbook TBM850 Page 10 of 20 Edition 1, Rev 0 (P/N Z00.DMNFM00EE1R0EN) or later approved Pilot’s Operating Handbook revision is required (see notes 8, 9, 10). For aircraft with Optional Modification No MOD 70 -0226-00 (Synthetic Vision System (SVS)), TBM 700 POH Supplement No. 50 Edition 0 Revision 0 with EASA approval date November 17, 2008 or later FAA/EASA approved revision is required or other Supplement No. 50 Editions according to airplane effectivity (see Note 12). For aircraft with optional SOCATA modification No. MOD 70 -0275-00 (Multi -Mission Aircraft), TBM 700 POH Supplement No. 53 Revision 1 with EASA approval date November 19, 2010 or later FAA/EASA approved revision is required (see Note 15). For aircraft with optional SOCATA modification No. MOD 70 -0276-00 (“Garmin G1000 Retrofit”), the appropriate SOCATA TBM 700 POH (P/N No. Z00.DMAFM00EE1R0EN) ED1 dated November 30, 2010 or later FAA/EASA approved revision is required (see Note 16). For aircraft with SOCATA modification No. MOD 70-0315-25 (“4 seats accommodation”), the appropriate SOCATA TBM 850 POH Edition 1, Revision 7 (P/N Z00.DMNFM00EE1R7EN) or later approved revision and SOCATA TBM850 POH Edition 1, Temporary revision 11 dated March 2012 with EASA approval date July 4, 2012 or later FAA/EASA approved revision are required (see Note 17). For aircraft with SOCATA modifications No. MOD 70-0176-00, MOD 70-0211-57, MOD 70-0234-24, MOD 70-0322-00, MOD 70-0323-71, MOD 70-0324-00 and MOD 70- 0357-71, the appropriate SOCATA TBM 900 POH Edition 0 (P/N Z00.DMHFM00EE0R0EN) dated October 31, 2013 or later FAA/EASA approved revisions is required (see notes 18 through 23). For aircraft with SOCATA modifications No. MOD 70-0176-00, MOD 70-0211-57, MOD 70-0234-24, MOD 70-0322-00, MOD 70-0323-71, MOD 70-0324-00, MOD 70- 0357-71 and MOD 70-0439-79, the appropriate SOCATA TBM 900 POH Edition 1 (P/N Z00.DMHFM00EE1R0EN) dated December 5, 2014 or later FAA/EASA approved revisions is required (see notes 18 through 23). For aircraft with SOCATA modifications No. MOD 70-0476-00, MOD 70-0211-57, MOD 70-0234-24, MOD 70-0322-00, MOD 70-0323-71, MOD 70-0324-00, MOD 70- 0357-71, MOD 70-0439-79 and MOD 70-0462-34, the appropriate SOCATA TBM 930 POH Edition 0 (P/N Z00.DMJFM00EE0R0EN) dated December 31, 2015 or later FAA/EASA approved revisions is required (see notes 18 through 23). For aircraft s/n 687, 1000 -1169 with optional SOCATA modification No. MOD70 -0407- 00 Ed 2 Version C (“ESP and USP option to G1000”), TBM 900 POH Supplement No. 62 Edition 0, Revision 0 dated April 15, 2016 or later FAA/EASA approved revision is required (see notes 18 through 23). For aircraft s/n 1170-1269 with SOCATA modification MOD 70-0539-00 (G1000 Nxi), MOD 70-0211-57, MOD 70-0234-24, MOD 70-0322-00, MOD 70-0323-71, MOD 70- 0324-00, MOD 70-0357-71, MOD 70-0439-79, MOD 70-0407-00 and MOD70-0462-34, the appropriate TBM 910 POH: - Edition 0 (P/N Z00.DMDFM00EE0R0EN) dated January 15, 2017 or later FAA/EASA approved revisions is required for s/n 1170-1269 (see notes 18 through 25 and 27) or - Edition 1 (P/N Z00.DMDFM00EE1R0EN) dated January 15, 2019 or later FAA/EASA approved revisions is required for s/n 1270-9999 (see notes 18 through 25, 27, 29 and 30). For aircraft with SOCATA modification MOD 70-0549-00 (G3000 2018), the appropriate TBM 930 POH: - Edition 1 (P/N Z00.DMJFM00EE1R0EN) dated January 15, 2018 or later FAA/EASA approved revisions is required for s/n 1216-1269 (see notes 18 through 24, 26 and 27). For aircraft with DAHER modification MOD 70 -0649-00 (G3000 Software V21.25), the appropriate TBM 940 POH: - Edition 0 (P/N DMKFM00EE0R0EN) dated March 5, 2019 or later FAA/EASA approved revisions is required for s/n 1272, 1275-9999 (see notes 18 through 24, 26, 27 and 29 through 32). Page 11 of 20 For aircraft with DAHER modification MOD70-0650-34 (Emergency Autoland/HomeSafe System) and MOD 70-0649-00 Version E (G3000 New Software SR 5.1.8), the appropriate TBM 940 POH: - Edition 0 (P/N DMKFM00EE0EN) dated March 5, 2019 at revision 3 dated May 31, 2020 or later FAA/EASA approved revisions is required for s/n 1333 -9999 (see notes 18 through 24, 26, 27 and 29 through 33). For aircraft with DAHER modification MOD70-0621-76 (Engine power increase, Engine control and e-Throttle), MOD70-0665-61 (Five blades Raptor Propeller), MOD70-0646-21 (“ENVIRO components based ECS ”), MOD70-0753-00 (“Software Upgrade”) and MOD70-0680-10 (“Weight and balance modification”), the appropriate TBM 960 POH:Edition 0 (P/N DMMFM00EE0EN) dated March 02, 2022 or later FAA/EASA approved revisions is required for s/n 140 8-9999 (see notes 1 7 through 21, 29, 30, 31, 33 and 34). For aircraft with DAHER modifications MOD70-0876-00 (“G3000 PRIME Integrated Flight Deck”), MOD70-0770-28 (“Operations without Anti Ice Additive”), MOD70-0796-28 (“Electrical Fuel Pump and Fuel Unit Filter Removal”), the appropriate TBM 980 POH: Edition 0 (P/N DMLFM00EE0) dated December 15, 2025 or later FAA/EASA approved revisions is required for s/n 1627-9999 (see notes 17 through 21, 24, 29, 30, 31, 33 and 34). Service Information Each of the documents 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 1 Current 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. The certificated empty weight and corresponding center of gravity location must include unusable fuel of 60 lb at (+189.8) and full oil of 23.8 lb at (+82.3) Note 2 The placards specified in the DGAC/EASA approved Pilot's Operating Handbook must be displayed. Note 3 For TBM 700A, B, C1 and C2 versions and TBM 700N version not equipped with SOCATA modifications No. MOD70-0176-00 and MOD70-0211-57 (see notes 10 and 14): Airworthiness Limitations are contained in Chapter 4 of the FAA and DGAC/EASA approved TBM 700 aircraft maintenance manual Rev 31, (P/N Z00.DMAMMPXEE0R31), or later approved revision. These Limitations may not be changed without FAA approval and EASA approval. For TBM 700N version equipped with SOCATA modifications No. MOD70 -0176-00 and Page 12 of 20 MOD70-0211-57 (see notes 10 and 14): And For TBM 700N version equipped with SOCATA modifications No. MOD70 -0176-00, - 0211-57, -0234-24, -0322-00, -0323-71, -0324-00 and -0357-71 and optional modification No. MOD70-0345-61 (see notes 18 through 23): And For TBM 700N version equipped with SOCATA modifications No. MOD70 -0176-00, - 0211-57, -0234-24, -0322-00, -0323-71, -0324-00 and -0357-71, optional modification No. MOD70-0345-61, optional modification No. MOD70 -0462-34, optional modification No. MOD70-0407-00 and optional modification No. MOD70 -0539-00 (see notes 18 through 25, 27, 29 and 30): Airworthiness Limitations are contained in Chapter 4 of the FAA and DGAC/EASA approved TBM aircraft maintenance manual Edition 0 Rev 11, (P/N Z00.DMNMMPXEE0R11), or later approved revision. These Limitations may not be changed without FAA approval and EASA approval. Remark: From Revision 11 the TBM850 aircraft maintenance manual becomes the TBM aircraft maintenance manual. For TBM 700N version equipped with SOCATA modifications No. MOD70 -0476-00, - 0211-57, -0234-24, -0322-00, -0323-71, -0324-00 and -0357-71, optional modifications No. MOD70-0345-61 and MOD70 -0462-34, optional modification No. MOD70 -0549-00, optional modification No. MOD70 -0649-00, optional modification No. MOD70 -0550-00 and optional modification No. MOD70-0650-34 (see notes 18 through 24, 26, 27, 29 through 33): Airworthiness Limitations are contained in Chapter 4 of the FAA and DGAC/EASA approved TBM aircraft maintenance manual Edition 0 Rev 0, (P/N Z00.DMJMMPXEE0R0), or later approved revision. These Limitations may not be changed without FAA approval and EASA approval. For aircraft with DAHER modification MOD70-0621-76 (Engine power increase, Engine control and e -Throttle), MOD70-0665-61 Five blades Raptor Propeller , MOD70-0646-21 (“ENVIRO components based ECS ”), MOD70-0753-00 (“Software Upgrade”) and MOD70-0680-10 (“Weight and balance modification, the appropriate”): Airworthiness Limitations are contained in Chapter 4 of the FAA and DGAC/EASA approved TBM aircraft maintenance manual Edition 0 Rev 0, (P/N DMMMMPXEE0R0), or later approved revision. These Limitations may not be changed without FAA approval and EASA approval. Note 4 TBM 700 Cargo Version: Airplanes to be converted to the cargo version must be modified with SOCATA option No. OPT 70-52-002 “Pilot Door”, MOD 70-091-52 “Wide Entrance Door” and must also be modified for cargo operations by having SOCATA option No. OPT70 -25-027 “Cargo Transportation Capability” installed. Cargo aircraft must be operated with appropriate Pilot’s Operating Handbooks and Supplements as described in the Equipment section of this data sheet. Cargo aircraft seating capacity: Airplanes equipped with SOCATA option No. OPT70-25-027 version A (R.H. emergency exit not accessible): - limited to one occupant (pilot) as defined in equivalent level (ELOS) of safety ACE-02-01. (See Certification Basis.) Airplanes equipped with SOCATA option No. OPT70-25-027 version B (R.H. emergency exit accessible): - limited to two occupants (front seats) Note 5 TBM 700 airplane serial numbers 245 and 246 may be modified to the Modification No MOD 70-140-00 “TBM 700 C1Version” configuration when accomplished in accordance with DGAC approved technical instructions and other applicable requirements of this data sheet. Note 6 SOCATA modification No MOD 70-139-00 allows an extended MTOW. Page 13 of 20 It is an optional modification applicable to s/n 205, 240, 244-9999. The retrofit is possible only for airplanes within the above range of serial numbers already equipped with SOCATA modification No MOD 70-140-00 “TBM 700 C1 Version”. Note 7 SOCATA modification No MOD 70-0188-00 “TBM 700 N version” allows a maximum continuous power of 850 shp for climb and cruise (i.e. with flaps up), and a maximum power of 700 shp when flaps are extended. This modification basically consists in the installation of PT6A -66D in lieu of PT6A -64 engine. It is applicable to TBM 700 s/n 346-9999. “TBM850” is the first trade name of the “TBM 700 N version” (see Note 14). Note 8 SOCATA modification No MOD 70-0211-57 “Fuel tanks extension” extends the wing fuel tanks by one bay (between wing ribs 18 and 19) further outboard on each wing. The modification relocated the fuel tank filler cap, fuel vent, temperature probe, and pitot probe. There is no change to the external wing geometry, MTOW, center of gravity, or aircraft flight envelope. Note 9 SOCATA modification No MOD 70-0176-00 “Garmin G1000” factory installs Garmin G- 1000 Integrated Avionics System as standard equipment on model TBM 700 (“TBM850”, “TBM900” and “TBM910”). Note 10 SOCATA modification No MOD 70-0211-57 is only applicable to model TBM 700 (“TBM850”, “TBM900”, “TBM910” and “TBM930”) s/n 434 -9999 equipped with MOD 70-188-00. SOCATA modification No MOD 70-0176-00 is only applicable to model TBM 700 (“TBM850”, “TBM900” and “TBM910”) s/n 434-9999 equipped with MOD 70-188-00, MOD 70-211-57 and MOD 70-0158-28 (Fuel Gauging Amplifier). SOCATA modification No MOD 70 -0211-57 and MOD 70 -0176-00 are installed in conjunction at the factory and are only applicable to model TBM 700 (“TBM850”, “TBM900” and “TBM910”) s/n 434-9999. Previously manufactured aircraft are not eligible to be retrofitted with MOD 70-0211-57 or MOD 70-0176-00. Note 11 Airplanes (s/n 434-9999), which are equipped with SOCATA modification No. MOD 70- 0176-00 (“Garmin G1000”) or SOCATA modification No. MOD 70 -0476-00 (“Garmin G3000”), meet the initial airworthiness requirements for operation in Reduced Vertical Separation when required equipment (refer to Pilot Operating Handbook List of Critical RVSM equipment) is maintained in accordance with the airplane Maintenance Manual. Each operator must obtain final RVSM operating approval directly from the FAA. Note 12 Airplanes (s/n 434-9999) which have SOCATA modification No. MOD 70-0176-00 (“Garmin G1000”) or SOCATA modification No. MOD 70 -0476-00 (“Garmin G3000”), are eligible for Optional SOCATA modification No. MOD 70 -0226-00 (Synthetic Vision System (SVS)). These airplanes can be modified through incorporation of SOCATA optional service bulletin SB70-164-34 in the field or by SOCATA at the factory under their major level 1 type design approval. Airplanes with this SVS modification must have SOCATA TBM 700 POH titled: - “TBM 850 supplement 50 Revision 0” with EASA approval date November 17, 2008 (G1000 system) or later FAA/EASA approved revisions or - “TBM 900 supplement 50 Edition 1 Revision 0” with EASA approval date February 6, 2014 (G1000 system also) or later FAA/EASA approved revisions or - “TBM supplement 50 Edition 2 Revision 1” with EASA approval date March 27, 2017 (G3000 and G1000 Nxi systems) or later FAA/EASA approved revisions. Note 13 Optional SOCATA modification No. MOD 70-0246-25 (Chemical Toilet and its associated curtain installation). Airplanes (s/n 434-9999) are eligible for version A of MOD 70 -0246-25. These airplanes can be modified through incorporation of SOCATA optional service bulletin SB70-175-25 in the field or by SOCATA at the factory under their major level 1 type design approval. Airplanes with this modification must have SOCATA TBM 700 POH temporary revision titled “TBM 850 Pilot’s Operating Handbook Temporary Revision No. 2 (TR02)” with EASA approval date July 17, 2009 or later FAA/EASA approved revisions. Airplanes (s/n 126-433 (not including 269)), are eligible for version B of MOD 70-0246- Page 14 of 20 25. These airplanes can be modified through incorporation of SOCATA optional service bulletin SB70-184-25 in the field or by SOCATA at the factory under their major level 1 type design approval. Airplanes with this modification must have the appropriate SOCATA TBM 700 POH temporary revision (“TBM 850 Pilot’s Operating Handbook Temporary Revision No. 4 (TR04)”, (“TBM 700 B Pilot’s Operating Handbook Temporary Revision No. 4 (TR04)”, (“TBM 700C Pilot’s Operating Handbook Temporary Revision No. 4 (TR04)”) with EASA approval date October 5, 2010 or later FAA/EASA approved revisions Note 14 TBM 700 versions: TBM 700A = s/n 1-125 TBM 700B = s/n 126-243, except s/n 205 and 240 TBM 700C: - TBM 700C1 = s/n 244-345, except s/n 269, plus s/n 205 and 240 (MOD70-140-00) - TBM 700C2 = s/n 244-345, except s/n 269, plus s/n 205 and 240 (TBM 700C1 equipped with SOCATA modification No. MOD70-139-00) (see note 6) TBM 700N: - (Trade name: TBM850) not factory equipped with G1000 system = s/n 346-433, except s/n 269 - (Trade name: TBM850) equipped with G1000 system = s/n 434-999, except 687 - (Trade name: TBM900) equipped with G1000 system, winglets, composite cowlings, power single lever = s/n 687, 1000-1169, of which only airplanes equipped with MOD70- 0176-00 - (Trade name: TBM930) equipped with G3000 system, winglets, composite cowlings, power single lever = s/n 1111 -1271, of which only airplanes equipped with MOD70 - 0476-00 and optional MOD70-0549-00 - (Trade name: TBM910) equipped with G1000 system, G1000 Nxi system, winglets, composite cowlings, power single lever = s/n 1170-9999, of which only airplanes equipped with MOD70-0539-00 - (Trade name: TBM940) equipped with G3000 system, winglets, composite cowlings, power single lever = s/n 1172, 1275 -9999, of which only airplanes equipped with MOD70-0549-00, MOD70-0649-00, MOD70-0550-00 and MOD70-0650-34. - (Trade name: TBM960) equipped with modification MOD70-0621-76 (“Engine power increase, Engine control and e -Throttle”), MOD70 -0665-61 (“Five blades Raptor Propeller”), MOD70 -0646-21 (“ENVIRO components based ECS”), MOD70 -0753-00 (“Software Upgrade”) and MOD70 -0680-10 (“Weight and balance modification, the appropriate”): = s/n 1408-9999 - (Trade name: TBM980) equipped with modification MOD70-0876-00 (“G3000 PRIME Integrated Flight Deck”), MOD70 -0770-28 (“Operations without Anti Ice Additive”), MOD70-0796-28 (“Electrical Fuel Pump and Fuel Unit Filter Removal”): = s/n 1627- 9999 Note 15 Optional SOCATA modification No. MOD 70-0275-00 (Multi-Mission Aircraft). Airplanes (s/n 14 -9999)) are eligible for Optional SOCATA modification No. MOD 70 - 0275-00 (Multi -Mission Aircraft). These airplanes can be modified by SOCATA at the factory under their major level 1 type design approval. Airplanes with this modification must have the appropriate SOCATA TBM 700 POH Supplement No. 53, Revision 1 with EASA approval date Novembre 19, 2010 or later FAA/EASA approved revisions and SOCATA TBM 700 Aircraft Maintenance Manual Supplement (P/N Z00.DMAMMS01PEE0R0) dated March 2011 or later FAA/EASA approved revisions. Note 16 Optional SOCATA modification No. MOD 70-0276-00 (“Garmin G1000 Retrofit”). Airplanes TBM 700A (s/n 14 – 125) equipped with MOD 70-01-0158-28B (Fuel Gauging Amplifier) and TBM 700B (s/n 126 – 243, except s/n 205 and 240) equipped with MOD70- 0158-28B (Fuel Gauging Amplifier) are eligible for Optional Socata modification No. MOD 70-0276-00. These airplanes can be modified by SOCATA at the factory under their major level 1 type design approval. Airplanes with this modification must have the appropriate SOCATA TBM 700 POH (P/N No. Z00.DMAFM00EE1R0EN) ED1 dated November 30, 2010 or later FAA/EASA approved revisions and SOCATA TBM 700 Aircraft Maintenance Manual Supplement (P/N Z00.DMAMMS02PEE0R0) dated October 2010 or later FAA/EASA approved revisions. Note 17 Airplanes equipped with SOCATA modification No. MOD 70-0316-25 (capability for 4 seats configuration) are eligible for SOCATA modification No. MOD 70-0315-25 (4 seats accommodation). SOCATA modification No. MOD 70 -0316-25 (capability for 4 seats configuration) is Page 15 of 20 installed in factory from s/n 609. SOCATA modification No. MOD 70 -0315-25 (4 seats accommodation) can be installed on airplanes equipped with SOCATA modification No. MOD 70 -0316-25 (capability for 4 seats configuration) through incorporation of SOCATA optional service bulletin SB70 - 200-25 in the field. SOCATA modification No. MOD 70 -0315-25 (4 seats accommodation) is installed in factory on s/n 615 and from s/n 627-9999. Airplanes equipped with SOCATA modification No. MOD 70-0315-25 (4 seats accommodation) must have the appropriate: - SOCATA TBM 850 POH Edition 1, Revision 7 or later approved update and SOCATA TBM850 POH Edition 1, Temporary revision 11 dated March 2012 with EASA approval date July 4, 2012 or later FAA/EASA approved revisions, or - SOCATA TBM 900 POH Edition 0, Revision 1 (s/n 1000-1049, plus s/n 687) dated February 1, 2014 with EASA approval date February 24, 2014 or later FAA/EASA approved revisions, or - SOCATA TBM 900 POH Edition 1, Revision 0 (s/n 1050 -1169, only airplanes equipped with MOD70-0176-00) dated December 05, 2014 with EASA approval date December 22, 2014 or later FAA/EASA approved revisions, or - SOCATA TBM 930 POH Edition 0, Revision 0 (s/n 1111 -1215, only airplanes equipped with MOD70-0476-00) dated December 31, 2015 with EASA approval date February 18, 2016 or later FAA/EASA approved revisions or - SOCATA TBM 930 POH Edition 1, Revision 0 (s/n 1216 -1269, only airplanes equipped with MOD70 -0549-00 Versions A thru C) dated January 15, 2018 with EASA approval date March 5, 2018 or later FAA/EASA approved revisions or - SOCATA TBM 910 POH Edition 0, Revision 0 (s/n 1170 -1269, only airplanes equipped with MOD70 -0539-00 Versions A thru G) dated January 15, 2017 with EASA approval date March 24, 2017 or later FAA/EASA approved revisions or - DAHER TBM 910 POH Edition 1, Revision 0 (s/n 1270 -9999, only airplanes equipped with MOD70 -0539-00 Version H) dated January 15, 2019 with EASA approval date January 14, 2019 or later FAA/EASA approved revisions, - DAHER TBM 940 POH Edition 0, Revision 1 (s/n 1272, 1275 -9999, only airplanes equipped with MOD70-0549-00, MOD70-0649-00 and MOD70-0550-00) dated March 5, 2019 with EASA approval date September 23, 2019 or later FAA/EASA approved revisions. - DAHER TBM960 POH Edition 0, Revision 0 (s/n 1408 -9999, only airplanes equipped with MOD70-621-71) dated March 02, 2022 with EASA approval date March 02, 2022 or later FAA/EASA approved revisions. - DAHER TBM 980 POH Edition 0, Revision 0 (s/n 1629 -9999, only airplanes equipped with MOD70-0876-00) dated Dec 15, 2025 with EASA approval date Dec 15, 2025 or later FAA/EASA approved revisions Note 18 SOCATA modification No MOD 70-0234-24 “New electrical generation and primary distribution” installs new electrical distribution as standard equipment on model TBM 700 (“TBM900”, “TBM910”, “TBM930” and “TBM940”) s/n687, 1000-9999. Airplanes equipped with SOCATA modification No. MOD 70-0234-24 must have the appropriate: - SOCATA TBM 900 POH Edition 0, Revision 1 or later FAA/EASA approved revisions or - SOCATA TBM 900 POH Edition 1, Revision 0 (s/n 1050 -1169, only airplanes equipped with MOD70-0176-00) or later FAA/EASA approved revisions, or - SOCATA TBM 930 POH Edition 0, Revision 0 (s/n 1111 -1215, only airplanes equipped with MOD70-0476-00) or later FAA/EASA approved revisions or - SOCATA TBM 930 POH Edition 1, Revision 0 (s/n 1216 -1269, only airplanes equipped with MOD70 -0549-00 Versions A thru C) or later FAA/EASA approved revisions or - SOCATA TBM 910 POH Edition 0, Revision 0 (s/n 1170 -1269, only airplanes equipped with MOD70 -0539-00 Versions A thru G) or later FAA/EASA approved revisions or - DAHER TBM 910 POH Edition 1, Revision 0 (s/n 1270-9999, only airplanes equipped with MOD70-0539-00 Version H) or later FAA/EASA approved revisions or - DAHER TBM 940 POH Edition 0, Revision 1 (s/n 1272, 1275 -9999, only airplanes equipped with MOD70 -0549-00, MOD70 -0649-00 and MOD70 -0550-00) or later FAA/EASA approved revisions - DAHER TBM 960 POH Edition 0, Revision 0 (s/n 1408 -9999, only airplanes equipped with MOD70-621-71) dated March 02, 2022 with EASA approval date March 02, 2022 or later FAA/EASA approved revisions. Page 16 of 20 - - DAHER TBM 980 POH Edition 0, Revision 0 (s/n 1627 -9999, only airplanes equipped with MOD70-0876-00) dated Dec 15, 2025 with EASA approval date Dec 15, 2025 or later FAA/EASA approved revisions. Note 19 SOCATA modification No MOD70-0322-00 “Aerodynamic efficiency improvement” installs winglets, new position, landing and anti-collision LED lights and modified tail cone on model TBM 700 (“TBM900”, “TBM910”, “TBM930” and “TBM940”) s/n687, 1000- 9999. Airplanes equipped with SOCATA modification No. MOD 70 -0322-00 must have the appropriate: - SOCATA TBM 900 POH Edition 0, Revision 1 or later FAA/EASA approved revisions or - SOCATA TBM 900 POH Edition 1, Revision 0 (s/n 1050 -1169, only airplanes equipped with MOD70-0176-00) or later FAA/EASA approved revisions, or - SOCATA TBM 930 POH Edition 0, Revision 0 (s/n 1111 -1215, only airplanes equipped with MOD70-0476-00) or later FAA/EASA approved revisions or - SOCATA TBM 930 POH Edition 1, Revision 0 (s/n 1216 -1269, only airplanes equipped with MOD70 -0549-00 Versions A thru C) or later FAA/EASA approved revisions or - SOCATA TBM 910 POH Edition 0, Revision 0 (s/n 1170 -1269, only airplanes equipped with MOD70 -0539-00 Versions A thru G) or later FAA/EASA approved revisions or - DAHER TBM 910 POH Edition 1, Revision 0 (s/n 1270-9999, only airplanes equipped with MOD70-0539-00 Version H) or later FAA/EASA approved revisions or - DAHER TBM 940 POH Edition 0, Revision 1 (s/n 1272, 1275 -9999, only airplanes equipped with MOD70 -0549-00, MOD70 -0649-00 and MOD70 -0550-00) or later FAA/EASA approved revisions - DAHER TBM 960 POH Edition 0, Revision 0 (s/n 1408 -9999, only airplanes equipped with MOD70-621-71) dated March 02, 2022 with EASA approval date March 02, 2022 or later FAA/EASA approved revisions. - DAHER TBM 980 POH Edition 0, Revision 0 (s/n 1627 -9999, only airplanes equipped with MOD70-0876-00) dated Dec 15, 2025 with EASA approval date Dec 15, 2025 or later FAA/EASA approved revisions. Note 20 SOCATA modification No MOD70-0323-71“Propulsion efficiency improvement” installs new composite cowlings and a new engine inlet on model TBM 700 (“TBM900”, “TBM910”, “TBM930” and “TBM940”) s/n687, 1000 -9999. Airplanes equipped with SOCATA modification No. MOD 70-0323-71 must have the appropriate: - SOCATA TBM 900 POH Edition 0, Revision 1 or later FAA/EASA approved revisions or - SOCATA TBM 900 POH Edition 1, Revision 0 (s/n 1050 -1169, only airplanes equipped with MOD70-0176-00) or later FAA/EASA approved revisions, or - SOCATA TBM 930 POH Edition 0, Revision 0 (s/n 1111 -1215, only airplanes equipped with MOD70-0476-00) or later FAA/EASA approved revisions or - SOCATA TBM 930 POH Edition 1, Revision 0 (s/n 1216 -1269, only airplanes equipped with MOD70 -0549-00 Versions A thru C) or later FAA/EASA approved revisions or - SOCATA TBM 910 POH Edition 0, Revision 0 (s/n 1170 -1269, only airplanes equipped with MOD70 -0539-00 Versions A thru G) or later FAA/EASA approved revisions or - DAHER TBM 910 POH Edition 1, Revision 0 (s/n 1270-9999, only airplanes equipped with MOD70-0539-00 Version H) or later FAA/EASA approved revisions or - DAHER TBM 940 POH Edition 0, Revision 1 (s/n 1272, 1275 -9999, only airplanes equipped with MOD70 -0549-00, MOD70 -0649-00 and MOD70 -0550-00) or later FAA/EASA approved revisions - DAHER TBM 960 POH Edition 0, Revision 0 (s/n 1408 -9999, only airplanes equipped with MOD70-621-71) dated March 02, 2022 with EASA approval date March 02, 2022 or later FAA/EASA approved revisions. - DAHER TBM 980 POH Edition 0, Revision 0 (s/n 1627 -9999, only airplanes equipped with MOD70-0876-00) dated Dec 15, 2025 with EASA approval date Dec 15, 2025 or later FAA/EASA approved revisions. Page 17 of 20 Note 21 SOCATA modification No MOD70-0324-00 “Human machine interface improvement” modifies pylon and installs a single powerplant control lever on model TBM 700 (“TBM900”, “TBM910”, “TBM930” and “TBM940”) s/n687, 1000-9999. Airplanes equipped with SOCATA modification No. MOD 70-0324-00 must have the appropriate: - SOCATA TBM 900 POH Edition 0, Revision 1 or later FAA/EASA approved revisions or - SOCATA TBM 900 POH Edition 1, Revision 0 (s/n 1050 -1169, only airplanes equipped with MOD70-0176-00) or later FAA/EASA approved revisions, or - SOCATA TBM 930 POH Edition 0, Revision 0 (s/n 1111 -1215, only airplanes equipped with MOD70-0476-00) or later FAA/EASA approved revisions or - SOCATA TBM 930 POH Edition 1, Revision 0 (s/n 1216 -1269, only airplanes equipped with MOD70 -0549-00 Versions A thru C) or later FAA/EASA approved revisions or - SOCATA TBM 910 POH Edition 0, Revision 0 (s/n 1170 -1269, only airplanes equipped with MOD70 -0539-00 Versions A thru G) or later FAA/EASA approved revisions or - DAHER TBM 910 POH Edition 1, Revision 0 (s/n 1270-9999, only airplanes equipped with MOD70-0539-00 Version H) or later FAA/EASA approved revisions or - DAHER TBM 940 POH Edition 0, Revision 1 (s/n 1272, 1275 -9999, only airplanes equipped with MOD70 -0549-00, MOD70 -0649-00 and MOD70 -0550-00) or later FAA/EASA approved revisions - DAHER TBM 960 POH Edition 0, Revision 0 (s/n 1408 -9999, only airplanes equipped with MOD70-621-71) dated March 02, 2022 with EASA approval date March 02, 2022 or later FAA/EASA approved revisions. - DAHER TBM 980 POH Edition 0, Revision 0 (s/n 1627 -9999, only airplanes equipped with MOD70-0876-00) dated Dec 15, 2025 with EASA approval date Dec 15, 2025 or later FAA/EASA approved revisions Note 22 Optional SOCATA modification No MOD70-0345-71 “New five blade propeller” on model TBM 700 (“TBM900”, “TBM910”, “TBM930” and “TBM940”), s/n687, 1000- 9999. Airplanes equipped with SOCATA modification No. MOD 70-0345-61 must have the appropriate: - POH Supplement No. 58 Revision 1 to SOCATA TBM 900 POH Edition 0, Revision 1 or later FAA/EASA approved revisions or - SOCATA TBM 900 POH Edition 1, Revision 0 (s/n 1050 -1169, only airplanes equipped with MOD70-0176-00) or later FAA/EASA approved revisions, or - SOCATA TBM 930 POH Edition 0, Revision 0 (s/n 1111 -1215, only airplanes equipped with MOD70-0476-00) or later FAA/EASA approved revisions or - SOCATA TBM 930 POH Edition 1, Revision 0 (s/n 1216 -1269, only airplanes equipped with MOD70 -0549-00 Versions A thru C) or later FAA/EASA approved revisions or - SOCATA TBM 910 POH Edition 0, Revision 0 (s/n 1170 -1269, only airplanes equipped with MOD70 -0539-00 Versions A thru G) or later FAA/EASA approved revisions or - DAHER TBM 910 POH Edition 1, Revision 0 (s/n 1270-9999, only airplanes equipped with MOD70-0539-00 Version H) or later FAA/EASA approved revisions or - DAHER TBM 940 POH Edition 0, Revision 1 (s/n 1272, 1275 -9999, only airplanes equipped with MOD70 -0549-00, MOD70 -0649-00 and MOD70 -0550-00) or later FAA/EASA approved revisions Note 23 SOCATA modification No MOD70-0357-71 “Takeoff and landing operations at 850SHP” on model TBM 700 (“TBM900”, “TBM910”, “TBM930” and “TBM940”), s/n687, 1000- 9999. Airplanes equipped with SOCATA modification No. MOD 70-0357-71 must have the appropriate: - SOCATA TBM 900 POH Edition 0, Revision 1 or later FAA/EASA approved revisions or - SOCATA TBM 900 POH Edition 1, Revision 0 (s/n 1050 -1169, only airplanes equipped with MOD70-0176-00) or later FAA/EASA approved revisions or - SOCATA TBM 930 POH Edition 0, Revision 0 (s/n 1111 -1215, only airplanes equipped with MOD70-0476-00) or later FAA/EASA approved revisions or - SOCATA TBM 930 POH Edition 1, Revision 0 (s/n 1216 -1269, only airplanes Page 18 of 20 equipped with MOD70 -0549-00 Versions A thru C) or later FAA/EASA approved revisions or - SOCATA TBM 910 POH Edition 0, Revision 0 (s/n 1170 -1269, only airplanes equipped with MOD70 -0539-00 Versions A thru G) or later FAA/EASA approved revisions or - DAHER TBM 910 POH Edition 1, Revision 0 (s/n 1270-9999, only airplanes equipped with MOD70-0539-00 Version H) or later FAA/EASA approved revisions or - DAHER TBM 940 POH Edition 0, Revision 1 (s/n 1272, 1275 -9999, only airplanes equipped with MOD70 -0549-00, MOD70 -0649-00 and MOD70 -0550-00) or later FAA/EASA approved revisions Note 24 Airplanes equipped with Optional SOCATA modification No. MOD70-0388-25 “AMSAFE Airbag Seatbelt on Pilot and Co-Pilot Seats” must have the appropriate: - SOCATA TBM 930 POH Edition 0, Revision 1 (s/n 1111 -1215, only airplanes equipped with MOD70-0476-00) or later FAA/EASA approved revisions or - SOCATA TBM 930 POH Edition 1, Revision 0 (s/n 1216 -1269, only airplanes equipped with MOD70 -0549-00 Versions A thru C) or later FAA/EASA approved revisions or - SOCATA TBM 910 POH Edition 0, Revision 0 (s/n 1170 -1269, only airplanes equipped with MOD70 -0539-00 Versions A thru G) or later FAA/EASA approved revisions or - DAHER TBM 910 POH Edition 1, Revision 0 (s/n 1270-9999, only airplanes equipped with MOD70-0539-00 Version H) or later FAA/EASA approved revisions or - DAHER TBM 940 POH Edition 0, Revision 1 (s/n 1272, 1275 -9999, only airplanes equipped with MOD70 -0549-00, MOD70 -0649-00 and MOD70 -0550-00) or later FAA/EASA approved revisions - DAHER TBM 960 POH Edition 0, Revision 0 (s/n 1408 -9999, only airplanes equipped with MOD70-621-71) dated March 02, 2022 with EASA approval date March 02, 2022 or later FAA/EASA approved revisions. - DAHER TBM 980 POH Edition 0, Revision 0 (s/n 1627 -9999, only airplanes equipped with MOD70-0876-00) dated Dec 15, 2025 with EASA approval date Dec 15, 2025 or later FAA/EASA approved revisions Note 25 SOCATA modification No MOD70-0539-00 is only applicable to model TBM 700N equipped with SOCATA modification No MOD70 -0176-00. SOCATA modification No MOD70-0539-00 modifies original basic SOCATA modification No MOD70 -0176-00 hardware and uses a new software. Airplanes equipped with SOCATA modification No. MOD70 -0539-00 (“Garmin G1000 Nxi”) must have the appropriate: - SOCATA TBM 910 POH Edition 0, Revision 0 (s/n 1170 -1269, only airplanes equipped with MOD70 -0539-00 Versions A thru G) or later FAA/EASA approved revisions or - DAHER TBM 910 POH Edition 1, Revision 0 (s/n 1270-9999, only airplanes equipped with MOD70-0539-00 Version H) or later FAA/EASA approved revisions Note 26 SOCATA modification No MOD70-0549-00 is only applicable to model TBM 700N equipped with SOCATA modification No MOD70 -0476-00. SOCATA modification No MOD70-0549-00 modifies original basic SOCATA modification No MOD70 -0476-00 hardware and uses a new software. Airplanes equipped with SOCATA modification No. MOD70 -0549-00 (“Garmin G3000 2018”) must have the appropriate: - SOCATA TBM 930 POH Edition 1, Revision 0 (s/n 1216 -1269, only airplanes equipped with MOD70 -0549-00 Versions A thru C) or later FAA/EASA approved revisions Note 27 Optional SOCATA modification No. MOD70-0505-25 “Cabinet installation: Lavatory compartment” Airplanes (s/n 615, 627 -9999) are eligible for version C of MOD 70 -0505-25. These airplanes must have embodied the SOCATA modification No. MOD70 -0315-25 (4 seats accommodation). Airplanes with this optional modification must have the appropriate SOCATA TBM 700 POH titled: - “TBM 850 supplement 63 Edition 3 Revision 0” with EASA approval date June 13, Page 19 of 20 2017 (s/n 434- 999) or later FAA/EASA approved revisions or - “TBM 900 supplement 63 Edition 2 Revision 0” with EASA approval date June 13, 2017 (s/n 687, 1000 -1169, only airplanes equipped with MOD70 -0176-00) or later FAA/EASA approved revisions or - “TBM supplement 63 Edition 1 Revision 1” with EASA approval date March 27, 2017 (airplanes equipped with MOD70-0476-00 or MOD70-0539-00) or later FAA/EASA approved revisions. Note 28 On April 27, 2018, the TC Holder name changed from SOCATA to DAHER AEROSPACE. In conjunction, the Manufacturer name changed from SOCATA to COMPAGNIE DAHER. On August 19, 2025, the TC Holder name changed from Daher Aerospace to Daher Aircraft, SAS. On April 24, 2026, the Manufacturer name changed from COMPAGNIE DAHER to DAHER AIRCRAFT, SAS. Note 29 Airplanes equipped with Optional DAHER modification No. MOD70-0619-11 “Modification of cabin interior marking” must have the appropriate: - DAHER TBM 910 POH Edition 1, Revision 0 (s/n 1270-9999, only airplanes equipped with MOD70-0539-00 Version H) or later FAA/EASA approved revisions or - DAHER TBM 940 POH Edition 0, Revision 0 (s/n 1272, 1275 -9999, only airplanes equipped with MOD70 -0549-00, MOD70 -0649-00 and MOD70 -0550-00) or later FAA/EASA approved revisions - DAHER TBM 960 POH Edition 0, Revision 0 (s/n 1408 -9999, only airplanes equipped with MOD70-621-71) dated March 02, 2022 with EASA approval date March 02, 2022 or later FAA/EASA approved revisions. - DAHER TBM 980 POH Edition 0, Revision 0 (s/n 1627 -9999, only airplanes equipped with MOD70-0876-00) dated Dec 15, 2025 with EASA approval date Dec 15, 2025 or later FAA/EASA approved revisions Note 30 Airplanes equipped with Optional DAHER modification No. MOD70-0632-34 “Whiskey compass removal and Magnetometer MD032 integration” must have the appropriate: - DAHER TBM 910 POH Edition 1, Revision 0 (s/n 1270-9999, only airplanes equipped with MOD70-0539-00 Version H) or later FAA/EASA approved revisions or - DAHER TBM 940 POH Edition 0, Revision 0 (s/n 1272, 1275 -9999, only airplanes equipped with MOD70 -0549-00, MOD70 -0649-00 and MOD70 -0550-00) or later FAA/EASA approved revisions - or - DAHER TBM 960 POH Edition 0, Revision 0 (s/n 1408 -9999, only airplanes equipped with MOD70-621-71) dated March 02, 2022 with EASA approval date March 02, 2022 or later FAA/EASA approved revisions. - DAHER TBM 980 POH Edition 0, Revision 0 (s/n 1627 -9999, only airplanes equipped with MOD70-0876-00) dated Dec 15, 2025 with EASA approval date Dec 15, 2025 or later FAA/EASA approved revisions Note 31 Airplanes equipped with DAHER modification No. MOD70-0550-00 (“Auto-throttle”) must have the appropriate: - DAHER TBM 940 POH Edition 0, Revision 0 (s/n 1272, 1275 -9999, only airplanes equipped with MOD70 -0549-00, MOD70 -0649-00 and MOD70 -0550-00) or later FAA/EASA approved revisions - DAHER TBM 960 POH Edition 0, Revision 0 (s/n 140 8-9999, only airplanes equipped with MOD70-621-71) dated March 02, 202 2 with EASA approval date March 02, 2022 or later FAA/EASA approved revisions. - DAHER TBM 980 POH Edition 0, Revision 0 (s/n 1627 -9999, only airplanes equipped with MOD70-0876-00) dated Dec 15, 2025 with EASA approval date Dec 15, 2025 or later FAA/EASA approved revisions Note 32 DAHER modification No MOD70-0649-00 is only applicable to model TBM 700 N equipped with SOCATA modification No MOD70 -0476-00. SOCATA modification No MOD70-0649-00 supplements modification No MOD70-0549-00 by implementing a new software. Airplanes equipped with DAHER modification No. MOD70 -0649-00 (“G3000 Software V21.25”) must have the appropriate: Page 20 of 20 - DAHER TBM 940 POH Edition 0, Revision 0 (s/n 1272, 1275 -9999, only airplanes equipped with MOD70-0549-00 Version D, MOD70-0550-00 and MOD70-0650-34) or later FAA/EASA approved revisions Airplanes equipped with DAHER modification No. MOD70 -0649-00 Version E (Garmin G3000 New Software SR 5.1.8) must have the appropriate: - DAHER TBM 940 POH Edition 0, Revision 3 (s/n 1272, 1275 -9999, only airplanes equipped with MOD70-0549-00 Version D, MOD70-0550-00 and MOD70-0650-34) or later FAA/EASA approved revisions Note 33 Airplanes equipped with DAHER modification No. MOD70-0650-34 (“Emergency Autoland/HomeSafe System”) must have the appropriate: - DAHER TBM 940 POH Edition 0, Revision 3 (s/n 1272, 1275 -9999, only airplanes equipped with MOD70-0549-00 Version D, MOD70-0649-00 Version E and MOD70-0550-00) or later FAA/EASA approved revisions - DAHER TBM 960 POH Edition 0, Revision 0 (s/n 1408 -9999, only airplanes equipped with MOD70-621-71) dated March 02, 2022 with EASA approval date March 02, 2022 or later FAA/EASA approved revisions. - DAHER TBM 980 POH Edition 0, Revision 0 (s/n 1627 -9999, only airplanes equipped with MOD70-0876-00) dated Dec 15, 2025 with EASA approval date Dec 15, 2025 or later FAA/EASA approved revisions. Note 34 Airplanes equipped with DAHER modification MOD70-0621-76 (“Engine power increase, Engine control and e -Throttle”), MOD70-0665-61 (“Five blades Raptor Propeller”), MOD70-0646-21 (“ENVIRO components based ECS ”), MOD70-0753-00 (“Software Upgrade”) and MOD70-0680-10 (“Weight and balance modification, the appropriate”) must have the appropriate: - DAHER TBM 960 POH Edition 0, Revision 0 (s/n 140 8-9999, only airplanes equipped with MOD70-621-71) dated March 02, 20 22 with EASA approval date March 02, 2022 or later FAA/EASA approved revisions. - DAHER TBM 980 POH Edition 0, Revision 0 (s/n 1627 -9999, only airplanes equipped with MOD70-0876-00) dated Dec 15, 2025 with EASA approval date Dec 15, 2025 or later FAA/EASA approved revisions. - END - ``` ## ADs (65, first 50, in force first) - [AD 2025-26-02](https://openairdocs.org/ad/2025-26-02): Vertical Stabilizer Structure · Daher Aerospace TBM 700. Effective Feb 12, 2026 - [AD 2025-02-08](https://openairdocs.org/ad/2025-02-08): Fire Protection System · DAHER AEROSPACE TBM 700. Effective Mar 19, 2025 - [AD 2025-01-04](https://openairdocs.org/ad/2025-01-04): TE Flap Control System; TE Flap Actuator · DAHER AEROSPACE TBM 700. Effective Mar 11, 2025 - [AD 2023-11-12](https://openairdocs.org/ad/2023-11-12): Emergency Exits · DAHER AEROSPACE TBM 700. Effective Jul 21, 2023 - [AD 2021-25-10](https://openairdocs.org/ad/2021-25-10): Engine Oil System (Airframe) · Daher Aerospace TBM 700. Effective Jan 24, 2022 - [AD 2021-24-13](https://openairdocs.org/ad/2021-24-13): Cabin Pressure Control System · Daher Aerospace TBM700. Effective Jan 12, 2022 - [AD 2017-15-15](https://openairdocs.org/ad/2017-15-15): Flight Controls · SOCATA TBM 700. Effective Sep 6, 2017 - [AD 2015-17-10](https://openairdocs.org/ad/2015-17-10): Landing gear · SOCATA TBM 700. Effective Sep 29, 2015 - [AD 2014-09-03](https://openairdocs.org/ad/2014-09-03): Stabilizers · SOCATA TBM 700. Effective Jun 5, 2014 - [AD 2014-06-06](https://openairdocs.org/ad/2014-06-06): Landing Gear · SOCATA TBM 700. Effective May 2, 2014 - [AD 2012-10-14](https://openairdocs.org/ad/2012-10-14): Landing gear · SOCATA TBM 700. Effective Jul 23, 2012 - [AD 2011-27-09](https://openairdocs.org/ad/2011-27-09): Flight Controls · SOCATA TBM 700. Effective Feb 15, 2012 - [AD 2011-23-03](https://openairdocs.org/ad/2011-23-03): Navigation · SOCATA TBM 700. Effective Dec 6, 2011 - [AD 2011-17-06](https://openairdocs.org/ad/2011-17-06): Flight Controls · SOCATA TBM 700. Effective Sep 19, 2011 - [AD 2011-02-02](https://openairdocs.org/ad/2011-02-02): Air Conditioning. · SOCATA TBM 700. Effective Mar 1, 2011 - [AD 2010-23-28](https://openairdocs.org/ad/2010-23-28): Oxygen · SOCATA TBM 700. Effective Dec 29, 2010 - [AD 2010-11-15](https://openairdocs.org/ad/2010-11-15): Fire Protection · SOCATA TBM 700. Effective Jul 6, 2010 - [AD 2010-07-07](https://openairdocs.org/ad/2010-07-07): Towing and Taxiing · SOCATA TBM 700. Effective May 7, 2010 - [AD 2009-24-15](https://openairdocs.org/ad/2009-24-15): Electric power · SOCATA TBM 700. Effective Jan 4, 2010 - [AD 2007-03-17 R1](https://openairdocs.org/ad/2007-03-17-R1): Fuselage · SOCATA TBM 700. Effective Sep 9, 2009 - [AD 2009-08-09](https://openairdocs.org/ad/2009-08-09): Wiring harness · SOCATA TBM 700. Effective May 20, 2009 - [AD 2008-19-10](https://openairdocs.org/ad/2008-19-10): Movement of the emergency landing gear by-pass selector. · SOCATA TBM 700. Effective Oct 23, 2008 - [AD 2008-17-09](https://openairdocs.org/ad/2008-17-09): Alternator · SOCATA TBM 700. Effective Sep 23, 2008 - [AD 2008-03-15](https://openairdocs.org/ad/2008-03-15): Pilot door · SOCATA TBM 700. Effective Mar 11, 2008 - [AD 2007-23-07](https://openairdocs.org/ad/2007-23-07): Main landing gear wheel · SOCATA TBM 700. Effective Nov 28, 2007 - [AD 2007-21-10](https://openairdocs.org/ad/2007-21-10): Upper access door · SOCATA TBM 700. Effective Nov 21, 2007 - [AD 2007-09-07](https://openairdocs.org/ad/2007-09-07): Nose landing gear (NLG) · SOCATA TBM 700. Effective Jun 4, 2007 - [AD 2007-06-14](https://openairdocs.org/ad/2007-06-14): Propeller control cables · SOCATA TBM 700. Effective Apr 20, 2007 - [AD 2007-06-04](https://openairdocs.org/ad/2007-06-04): Flap carriage rollpins · SOCATA TBM 700. Effective Apr 19, 2007 - [AD 2007-05-18](https://openairdocs.org/ad/2007-05-18): Pulley brackets · SOCATA TBM 700. Effective Apr 12, 2007 - [AD 2007-03-16](https://openairdocs.org/ad/2007-03-16): Excessive lateral play caused by a nonconforming washer · SOCATA TBM 700. Effective Mar 15, 2007 - [AD 2007-02-08](https://openairdocs.org/ad/2007-02-08): Master cylinder yoke failure · SOCATA TBM 700. Effective Feb 26, 2007 - [AD 2006-22-11](https://openairdocs.org/ad/2006-22-11): Initial elevator trim actuator greasing · SOCATA TBM 700. Effective Dec 1, 2006 - [AD 2005-20-24](https://openairdocs.org/ad/2005-20-24): VHF1 antenna mounting area · SOCATA TBM 700. Effective Nov 9, 2005 - [AD 2005-01-19](https://openairdocs.org/ad/2005-01-19): Mode S transponders · GARMIN International GTX 330D, GTX 330, GTX 33D and 830 more. Effective Feb 23, 2005 - [AD 2003-26-06](https://openairdocs.org/ad/2003-26-06): Safety Belts and Restraint Systems · Anjou Aeronautique Safety Belts and Restraint Systems, AS332C, AS332L and 14 more. Effective Feb 17, 2004 - [AD 2002-09-11](https://openairdocs.org/ad/2002-09-11): Attaching Bolt/Screw Threads of Inboard, Central, and Outboard Carriages · SOCATA TBM 700. Effective Jun 20, 2002 - [AD 2002-03-03](https://openairdocs.org/ad/2002-03-03): Strainer Draining System in the Cabin Fuselage · SOCATA TBM 700. Effective Mar 29, 2002 - [AD 2001-23-17](https://openairdocs.org/ad/2001-23-17): GNS 430 units · Cessna 172, 182, 206 and 209 more. Effective Dec 28, 2001 - [AD 2001-23-06](https://openairdocs.org/ad/2001-23-06): Fuel Tank Air Vent Valves · SOCATA TBM 700. Effective Dec 27, 2001 - [AD 2001-06-05](https://openairdocs.org/ad/2001-06-05): Oil Breather Vent · SOCATA TBM 700. Effective May 11, 2001 - [AD 2001-04-07](https://openairdocs.org/ad/2001-04-07): Control Cable · SOCATA TBM 700. Effective Apr 13, 2001 - [AD 2000-26-19](https://openairdocs.org/ad/2000-26-19): Fuel Tank Air Vent Valve Hose · SOCATA TBM 700. Effective Feb 2, 2001 - [AD 2000-02-29](https://openairdocs.org/ad/2000-02-29): Airframe Pneumatic Deicing Boots · SOCATA TBM 700. Effective Mar 27, 2000 - [AD 98-24-04](https://openairdocs.org/ad/98-24-04): Flap Carriage · SOCATA TBM 700. Effective Dec 28, 1998 - [AD 98-25-02](https://openairdocs.org/ad/98-25-02): Top-mounted Antenna · Bell Helicopter Textron Canada 407, 172, 172A and 243 more. Effective Dec 22, 1998 - [AD 98-21-15](https://openairdocs.org/ad/98-21-15): Oxygen Generators · SOCATA TBM 700. Effective Nov 20, 1998 - [AD 98-12-02](https://openairdocs.org/ad/98-12-02): Elevator Trim Tab Fittings · SOCATA TBM 700. Effective Jul 17, 1998 - [AD 98-08-27](https://openairdocs.org/ad/98-08-27): Left-Hand Wheel Assembly · SOCATA TBM 700 with STC SA2786CE. Effective May 31, 1998 - [AD 98-04-04](https://openairdocs.org/ad/98-04-04): Starter Generator Mounting Adapter · SOCATA TBM 700. Effective Mar 24, 1998 All 65: https://openairdocs.org/tcds/A60EU/ads.md ## Registered aircraft by registry model (OpenAirDocs) - [Socata TBM 700](https://openairdocs.org/model/socata-tbm-700): 643 aircraft (registry code 8682000) - [Compagnie Daher TBM 700](https://openairdocs.org/model/compagnie-daher-tbm-700): 314 aircraft (registry code 8682010) - [Daher TBM 700](https://openairdocs.org/model/daher-tbm-700): 31 aircraft (registry code 8682014) - [EADS Socata TBM 700](https://openairdocs.org/model/eads-socata-tbm-700): 12 aircraft (registry code 8682004) - [Compagnie Daher TBM-700 C1](https://openairdocs.org/model/compagnie-daher-tbm-700-c1): 0 aircraft (registry code 8680213) - [Compagnie Daher TBM700N](https://openairdocs.org/model/compagnie-daher-tbm700n): 0 aircraft (registry code 8680212) ## STCs approved under this data sheet (84, first 50) - [STC SA01844WI](https://openairdocs.org/stc/SA01844WI): Installation of Garmin GFC 600 Automatic Flight Control System. Garmin International Inc. - [STC SA02279AT](https://openairdocs.org/stc/SA02279AT): Installation of a Boom Beam bulb, starter, and ballast. Whelen Aerospace Technologies - [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 SA02019SE-D](https://openairdocs.org/stc/SA02019SE-D): Installation of Garmin Model GTN 625/635/650; 725/750 Navigation System. Garmin International Inc. - [STC SA12408LA](https://openairdocs.org/stc/SA12408LA): Description of Type Design Change: Installation of Dedicated Gas Generator Case drain. Blackhawk Modifications, LLC - [STC SA11158SC](https://openairdocs.org/stc/SA11158SC): Demonstration of aircraft tolerance to potential electromagnetic interference from certain Transmitting Potable Electronic Devices (T-PEDS). Liberty Partners Inc. - [STC SA12179DE](https://openairdocs.org/stc/SA12179DE): Replacement of the original Pratt and Whitney PT6A-64 engine with a Pratt and Whitney PT6A-66D engine. Blackhawk Modifications LLC - [STC SA12024SE](https://openairdocs.org/stc/SA12024SE): Installation of Ram Air Cowling. American Aviation Inc. - [STC SA02738CH](https://openairdocs.org/stc/SA02738CH): Installation of L-3 Communications Avionics Systems. Acron Aviation Inc. - [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 SA09887AC](https://openairdocs.org/stc/SA09887AC): Installation of an Avionica MK-III mini Quick Access Recorder (QAR) and optional 4G or LTE Avionica Cellular Module (avCM. Aircraft Systems and Manufacturing Inc. - [STC SA01572CH](https://openairdocs.org/stc/SA01572CH): Installation of a Honeywell KMH 880 and KTA 870 Multi-hazard Awareness and Traffic Advisory system.. Amphenol Cable and Interconnect Technologies Inc. - [STC SA03316CH](https://openairdocs.org/stc/SA03316CH): Activation of an 802.11 a/b/g/n WiFi System. Elliott Aviation Technical Products Development Inc. - [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 SA01596SE](https://openairdocs.org/stc/SA01596SE): Installation of Butterfield Industries Oil Residue Collection System, kit P/N BI 3401-1.. Raisbeck Engineering Inc. - [STC SA00076IB](https://openairdocs.org/stc/SA00076IB): Installation of Photo luminescent Safety Systems. STG AEROSPACE GERMANY GmbH - [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 SA09856AC](https://openairdocs.org/stc/SA09856AC): Installation of BendixKing Aerowave 100 In-flight Data Link System for non-essential, non-required aircraft Cabin Systems & Equipments. 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 SA02265SE](https://openairdocs.org/stc/SA02265SE): Installation of a camera housing. Airborne Sensor LLC - [STC SA02075SE](https://openairdocs.org/stc/SA02075SE): Installation of a Mid-Continent MD835( ) Lithium Ion Battery. Mid-Continent Instrument Co. Inc. - [STC SA10236SC](https://openairdocs.org/stc/SA10236SC): Installation of a GDC 31 Roll Steering Converter. DAC International Inc - [STC SA04514NY](https://openairdocs.org/stc/SA04514NY): Single/Dual Transponder System ADS-B Upgrade. Scandinavian Avionics Design ApS - [STC SA00930WI-D](https://openairdocs.org/stc/SA00930WI-D): Installation of Bendix/King KMD 550/850 Multi-Function Display (MFD) system and optional Bendix/King KGP 560 General Aviation Enhanced ground proximity warning system (GA-EGPWS). Honeywell International Inc - [STC SA2328CE-D](https://openairdocs.org/stc/SA2328CE-D): Installation of the Bendix/King KLN 88 Loran C system.. Honeywell International Inc - [STC SA01522WI-D](https://openairdocs.org/stc/SA01522WI-D): SERIAL NUMBERS up to and including 433 Excluding 269: Installation of the alternate part number EFS 40 SG 465 Symbol Generator. Honeywell International Inc - [STC SA01452CH](https://openairdocs.org/stc/SA01452CH): Installation of an air ambulance conversion kit.. Med-Pac 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 SA8107SW](https://openairdocs.org/stc/SA8107SW): Installation of Electrically Powered vapor cycle Air Conditioning System utilizing freon 12 or R134A refrigerant. Air Comm Corporation - [STC SA00344BO PAGE 2](https://openairdocs.org/stc/SA00344BO%20PAGE%202): Installation of Parmetheus Plus LED PAR36 and PAR46 taxi and landing lights.. Whelen Aerospace Technologies - [STC SA02486LA](https://openairdocs.org/stc/SA02486LA): Replacement of Socata Leading Edge Assemblies and Pneumatic Deicer. SMR Technologies Inc - [STC SA00765DE](https://openairdocs.org/stc/SA00765DE): Installation of Automatic Dependent Surveillance Broadcast (ADS-B) Out functionality using the BendixKing KT74 Transponder and qualified position sensor. Peregrine - [STC SA04263NY](https://openairdocs.org/stc/SA04263NY): Installation of Gogo Business Aviation ATG System. Maxcraft Avionics Ltd. - [STC SA04165NY](https://openairdocs.org/stc/SA04165NY): Installation of Latitude Technologies Skynode S200 Satcom system must be performed. Latitude Technologies Corporation - [STC SA02153LA-D PAGE 2](https://openairdocs.org/stc/SA02153LA-D%20PAGE%202): Installation of Garmin G600 Primary Flight Display (PFD) and Multifunction Display (MFD) System. Garmin International Inc. - [STC SA02013CH](https://openairdocs.org/stc/SA02013CH): Installation of Avidyne Corporation Traffic Advisory System (TAS). Avidyne Corporation - [STC SA01933LA-D](https://openairdocs.org/stc/SA01933LA-D): Installation of Garmin Model 400W / 500W Series GPS-WAAS Navigation System. Garmin International Inc - [STC SA00343BO](https://openairdocs.org/stc/SA00343BO): Installation of a single configuration or a dual configuration Avidyne Corporation Integrated Flight Display, Model IFD540 loaded with Release 10.0 software (or later FAA approved release). Avidyne Corporation - [STC SA2786CE](https://openairdocs.org/stc/SA2786CE): Installation of fuselage shell upholstery panels, window shade assemblies, cabinets, table, and seat upholstery. Textron Aviation Inc - [STC SA00352BO PAGE 2](https://openairdocs.org/stc/SA00352BO%20PAGE%202): Installation of an Avidyne Corporation Mode A/C/S Transponder with ADS-B Out capability, Model AXP340 loaded with Version 3.13 software (or later FAA approved version),. Avidyne Corporation - [STC SA02119SE PAGE 2](https://openairdocs.org/stc/SA02119SE%20PAGE%202): Installation of Garmin GDL 88 ADS-B UAT Transceiver System. Garmin International Inc - [STC SA01969SE](https://openairdocs.org/stc/SA01969SE): Installation of a Mid-Continent MD302 Standby Attitude Module. Mid-Continent Instruments and Avionics - [STC SA01229SE PAGE 2](https://openairdocs.org/stc/SA01229SE%20PAGE%202): Installation of GNS 480 (CNX80) GPS WAAS Navigator with integrated VHF Navigation and Communication radios. Garmin International Inc - [STC SA02442AK PAGE 2](https://openairdocs.org/stc/SA02442AK%20PAGE%202): Approval of the L-3 Communications NGT 2000/2500 ADS-B system. ADS-B Technologies, LLC - [STC SA01933LA-D PAGE 2](https://openairdocs.org/stc/SA01933LA-D%20PAGE%202): Installation of Garmin Model 400W / 500W Series GPS-WAAS Navigation System. Garmin International Inc - [STC SA03931AT-D](https://openairdocs.org/stc/SA03931AT-D): Installation of a Modified Battery Heat Shield. Socata North America Inc - [STC SA02121SE](https://openairdocs.org/stc/SA02121SE): Installation of Garmin GTS 825 (TAS) or GTS 855 (TCAS I) Traffic System. Garmin International Inc - [STC SA00269BO](https://openairdocs.org/stc/SA00269BO): Installation of Avidyne Corporation TWX 670 Tactical Weather Detection System P/N 850-00026-000-( ) consisting of Avidyne Processor P/N 700-00033-000-( ), Sensor Systems Inc. Antenna P/N S72-1715-1 with doubler plate P/N S72-171530-1, and Avidyne Mounting Tray P/N 700-00034-000.. Avidyne Corporation - [STC SA02717NY PAGE 2](https://openairdocs.org/stc/SA02717NY%20PAGE%202): Installation of VoiceFlight Systems LLC VFS101 Speech Recognition Module. VoiceFlight Systems LLC All 84: https://openairdocs.org/tcds/A60EU/stcs.md --- OpenAirDocs.org is an independent research project of [Contrail Labs](https://contraillabs.com/). It is not affiliated with the FAA or the NTSB. Source documents are U.S. government works in the public domain.