# TCDS A53EU: ATR – GIE Avions de Transport Régional - Type: Type certificate data sheet - Status: Current - Holder: ATR – GIE Avions de Transport Régional - Revision: 38 - Revised: August 27, 2026 - Product: Aircraft, Large Airplane - Certification basis: Part 25, Part 21 - Registered aircraft: 60, by the registry models matched to it (OpenAirDocs) - Data sheet PDF: https://openairdocs.org/files/sha256/7f/01/7f014077b22e4f9e962f54fa81b9b35a89de227b41dac5bf7f927e628105a724 - FAA DRS: https://drs.faa.gov/browse/excelExternalWindow/DRSDOCID115085799420260828153438.0001 - Page: https://openairdocs.org/tcds/A53EU ## Models (11) As the data sheet lists them. - ATR72-202 - ATR72-101 - ATR72-212A - ATR72-212 - ATR42-300 - ATR42-320 - ATR72-211 - ATR72-102 - ATR42-200 - ATR42-500 - ATR72-201 ## What the data sheet says From the PDF's text layer, line by line; tables lose their columns. The PDF is the record. ```text Page 1 2 3 4 5 6 7 8 9 10 11 12 13 14 15 16 17 Rev. 37 30 6 29 27 29 27 12 35 27 33 21 32 37 38 37 36 Page 18 19 20 21 22 23 24 25 26 27 28 29 30 31 32 33 34 Rev. 22 27 29 26 27 27 35 30 30 33 24 32 28 38 37 31 36 DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION TYPE CERTIFICATE DATA SHEET No. A53EU This data sheet which is a part of Type Certificate No. A53EU 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. ATR – GIE Avions de Transport Régional 1, Allée Pierre Nadot 31712 Blagnac Cedex France I. ATR42-200 (Transport Category Airplane) approved October 25, 1985. Engines. Two Pratt and Whitney Aircraft of Canada, Ltd., PW120 turboprops. Fuel. (a) The following fuels are eligible for engines MIL-T-5624 Grade JP5 AST-MD-1655 Grades JET A, JET A1 (PWC Service Bulletin No. 20 004 details approval conditions) (b) The following type of additives may be used in approved fuels: - oxidation inhibitors, - corrosion inhibitors, - thermal stability additives, - metal deactivators, - anti icing additives, - anti stating additives, - biocide additives. List of approved additives, approved concentrations and conditions of use are identified in PWC Service Bulletin no 20.004. A53EU Revision 38 ATR ATR42-200 ATR42-300 ATR42-320 ATR42-500 ATR72-101 ATR72-201 ATR72-102 ATR72-202 ATR72-211 ATR72-212 ATR72-212A August 27, 2026 A53EU, Rev 38 2 of 34 I. ATR42-200 (cont'd) Oil. The following oils are eligible for engines: - Synthetic type conforming to PWC specification PWA 521, Type II. PWC Service Bulletin 20 001 lists approved brand oils. Engine Limits. (PW-120) Operating limits with no unscheduled maintenance action required. Beyond these limits refer to maintenance manual. POWER SETTING TIME LIMIT TO ITT NH NP OIL PRESS OIL TEMP (%) (ºC) (%) (%) (PSI) (ºC) RESERVE TAKE OFF 5 minutes 105 816 100 101 55 to 65 0 to 125 (1) TAKE OFF 5 minutes 92 785 (4) 101 55 to 65 0 to 125 (1) MAXIMUM CONTINUOUS NONE 90 785 100 101 55 to 65 0 to 125 (1) GROUND IDLE 62 40 min -40 to 125 (1) min HOTEL MODE 785 40 min (2) 0 to 125 (1) STARTING 5 seconds 950 -40 min (3) TRANSIENT 10 mn 105 20 S 125 850 102 110 40 to 100 20 S 145.6 (5) 850 102 110 40 to 100 (1) Temperature up to 115ºC (120ºC in Hotel mode) is authorized without time limitation. 20 mn are authorized between 115ºC (120ºC in Hotel mode) and 125ºC. (2) For NH below 75%. NH above 75% requires 55 to 65 psi. (3) It may be assumed that before the first start of the day the oil temperature is the minimum temperature observed during the night. (4) Refer to AFM 2.04 p1A for NH limitation at take off. (5) If gearboxes incorporate SB 20316 or 20380. NOTE: Oil temperature must be maintained above 45ºC to ensure intake strut de-icing. Oil temperature must be maintained above 71ºC to ensure fuel anti-icing protection in absence of the low fuel temperature indication. Propellers. 2 Hamilton Sundstrand, four-bladed, 14 SF 5 (FAA TCDS P7NE). Blade: SFA 13( ) (see FAA TCDS P7NE) Propeller Limits. Diameter: 13 Ft. (+ 1/4 in., -3/16 in. manufacturing tolerance permissible) Pitch Setting at 42. in. of the axis: Feather: 86 degrees Flight Fine: 20 degrees Ground Fine: 7 degrees Full Reverse: -10 degrees Propeller (Np) – Take off 1200 R.P.M. Max. Continuous 1200 R.P.M. 3 of 34 A53EU, Rev 38 I. ATR42-200 (cont'd) Airspeed Limits (IAS). Maximum operating speed Vmo : 250 KIAS Maximum operating mach Mmo : 0.55 VA manoeuvering speed : 160 KIAS VFE Flaps 15o : 160 KIAS (170 KIAS with MOD. 1790) Flaps 30o : 145 KIAS (150 KIAS with MOD. 1790) Flaps 45o : 130 KIAS (Emergency only) VLO Gear extension : 160 KIAS Gear retraction : 160 KIAS VLE Landing gear extended : 160 KIAS (170 KIAS with MOD. 1790) VMC (Minimum control speed with the critical engine inoperative) - In flight - VMCA : 88.5 KIAS - Take Off - VMCG: 83 KIAS Tire speed limit (ground speed limit) 165 KIAS Center of Gravity (C.G.) Range. (Gear Extended) Forward Limit AFT Limit (% MAC) (% MAC) Take off and landing 15 36 Flight 12 38 Gear retraction has negligible effect on C.G. range. Maximum Weights. kg lb Taxi weight 15,770 34,770 Take Off weight 15,750 34,725 Landing weight 15,500 34,170 Zero Fuel weight 14,500 31,965 For aircraft incorporating ATR Modification 0863, weight limitations are modified as follows: kg lb Taxi weight 15,770 34,770 Take Off weight 15,750 34,725 Landing weight 15,500 34,170 Zero Fuel weight 15,200 33,510 Minimum Crew. 2 (pilot and co-pilot). Maximum Passengers. 46: 48 passenger capacity is approved with incorporation of modification 0481. 34: in COMBI configuration, with modification 0244 and with modification 0755 associated with the application of modifications 1073 and 1044. Maximum Baggage. Forward compartment - Maximum load 960 kg (2116 lb) 508 kg (1119 lb) with Mod 0481 Rear compartment - Maximum load 384 kg (846 lb) 768 kg (1693 lb) with Mod 0639 Fuel Capacity. Density 6,55 lb/US Gallon Usable Unusable lb US Gal 46.7 lb 2 x 4,960 2 x 757 A53EU, Rev 38 4 of 34 I. ATR42-200 (cont'd) Fuel Unbalance. Maximum fuel unbalance: 550 kg (1,212 lb) Oil Capacity. Engine oil capacity Usable 1,0 US Gallon/engine Total 4,7 US Gallon/engine Maximum Operating Altitude. 25,000 ft. II. ATR42-300 (Transport Category Airplane) approved October 25, 1985. Engines. Two Pratt and Whitney Aircraft of Canada, Ltd, PW120 turboprops. Fuel. (a) The following fuels are eligible for engines MIL-T-5624 Grade JP5 AST-MD-1655 Grades JET A, JET A1 (PWC Service Bulletin no 20 004 details approval conditions) (b) The following types of additives may be used in approved fuels: - oxidation inhibitors, - corrosion inhibitors, - thermal stability additives, - metal deactivators, - anti icing additives, - anti stating additives, - biocide additives. List of approved additives, approved concentrations and conditions of use are identified in PWC Service Bulletin no 20.004. Oil. The following oils are eligible for engines: - Synthetic type conforming to PWC specification PWA 521, Type II. PWC Service Bulletin 20 001 lists approved brand oils. Engine Limits. (PW-120) Operating limits with no unscheduled maintenance action required. Beyond these limits refer to maintenance manual. POWER SETTING TIME LIMIT TO ITT NH NP OIL PRESS OIL TEMP (%) (ºC) (%) (%) (PSI) (ºC) RESERVE TAKE OFF 5 minutes 105 816 100 101 55 to 65 0 to 125 (1) TAKE OFF 5 minutes 92 785 (4) 101 55 to 65 0 to 125 (1) MAXIMUM CONTINUOUS NONE 90 785 100 101 55 to 65 0 to 125 (1) GROUND IDLE 62 40 min -40 to 125 (1) min HOTEL MODE 785 40 min (2) 0 to 125 (1) STARTING 5 seconds 950 -40 min (3) TRANSIENT 10 mn 105 20 S 125 850 102 110 40 to 100 20 S 145.6 (5) 850 102 110 40 to 100 5 of 34 A53EU, Rev 38 II. ATR42-300 (cont'd) (1) Temperature up to 115ºC (120ºC in Hotel mode) is authorized without time limitation. 20 mn are authorized between 115ºC (120ºC in Hotel mode) and 125ºC. (2) For NH below 75%. NH above 75% requires 55 to 65 psi. (3) It may be assumed that before the first start of the day the oil temperature is the minimum temperature observed during the night. (4) Refer to AFM 2.04 p1A for NH limitation at take off. (5) If gearboxes incorporate SB 20316 or 20380. NOTE: Oil temperature must be maintained above 45ºC to ensure intake strut de-icing. Oil temperature must be maintained above 71ºC to ensure fuel anti-icing protection in absence of the low fuel temperature indication. Propellers. 2 Hamilton Sundstrand, four-bladed, 14 SF 5 (FAA TCDS P7NE). Blade: SFA 13( ) (see FAA TCDS P7NE) Propeller Limits. Diameter: 13 FT. (+ 1/4 in., -3/16 in. manufacturing tolerance permissible.) Pitch Setting at 42 in. of the axis: Feather : 86 degrees Flight Fine: 20 degrees Ground Fine: 7 degrees Full Reverse: -10 degrees Propeller (Np) – Take off 1200 R.P.M. Max. Continuous 1200 R.P.M. Airspeed Limits (IAS). Maximum operating speed VMO : 250 KIAS Maximum operating mach VMO : 0.55 VA manoeuvering speed : 160 KIAS VFE Flaps 15o : 160 KIAS (170 KIAS with MOD.1790) Flaps 30o : 145 KIAS (150 KIAS with MOD.1790) Flaps 45o : 130 KIAS (Emergency only) VLO Gear extension : 160 KIAS Gear retraction : 160 KIAS VLE Landing gear extended : 160 KIAS (170 KIAS with MOD.1790) VMC (Minimum control speed with the critical engine inoperative) - In flight - VMCA : 88.5 KIAS - Take off - VMCG : 83 KIAS Tire speed limit (ground speed limit) : 165 KIAS Center of Gravity (C.G.) Range. (Gear Extended) Forward Limit AFT Limit (% MAC) (% MAC) Take off and landing 15 36 Flight 12 38 For aircraft incorporating ATR Modification 0951 (Service Bulletin No. ATR42-08-0001), C.G. range is modified as follows: Forward Limit AFT Limit (% MAC) (% MAC) Take off: 16,150 kg. G.W. 15 36 16,700 kg. G.W 17 32 Landing: 16,000 kg. G.W. 15 36 16,400 kg. G.W. 17 32 Flight: 12 38 (Straight line variation between points). Gear retraction has negligible effect on C.G. range. A53EU, Rev 38 6 of 34 II. ATR42-300 (cont'd) Maximum Weights. kg lb Taxi weight 16,170 35,645 Take Off weight 16,150 35,605 Landing weight 16,000 35,270 Zero Fuel weight 14,800 32,625 For aircraft incorporating ATR Modification 0863, weight limitations are modified as follows: Taxi weight 16,170 35,645 Take Off weight 16,150 35,605 Landing weight 16,000 35,270 Zero Fuel weight 15,200 33,510 For aircraft incorporating ATR Modification 0951 (ATR Service Bulletin No. ATR42-08-0001), weight limitations are modified as follows: Taxi weight 16,720 36,870 Take Off weight 16,700 36,825 Landing weight 16,400 36,160 Zero Fuel weight 15,200 33,510 Minimum Crew. 2 (pilot and co-pilot). Maximum Passengers. 46: 48 passenger capacity is approved with incorporation of modification 0481. 34: in COMBI configuration, with modification 0244 and with modification 0755 associated with the application of modifications 1073 and 1044. Maximum Baggage. Forward compartment - Maximum load 2,045 lb Rear compartment - Maximum load 952 lb. Fuel Capacity. Density 6.55 lb/US Gallon Usable Unusable lb US Gal 46.7 lb 2 x 4,960 2 x 757 Fuel Unbalance. Maximum fuel unbalance: 550 kg (1,212 lb) Oil Capacity. Engine oil capacity Usable 1.0 US Gallon/engine Total 4.7 US Gallon/engine Maximum Operating Altitude. 25,000 ft. III. ATR42-320 (Transport Category Airplane) approved August 25, 1988. Engines. Two Pratt and Whitney Aircraft of Canada, Ltd, PW121 turboprops. Fuel. (a) The following fuels are eligible for engines MIL-T-5624 Grade JP5 AST-MD-1655 Grades JET A, JET A1 (PWC Service Bulletin no 20 004 details approved conditions). 7 of 34 A53EU, Rev 38 III. ATR42-320 (cont'd) Fuel. (cont'd) (b) The following types of additives may be used in approved fuels: - oxidation inhibitors, - corrosion inhibitors, - thermal stability additives, - metal deactivators, - anti icing additives, - anti stating additives, - biocide additives. List of approved additives, approved concentrations and conditions of use are identified in PWC Service Bulletin no 20.004. Oil. The following oils are eligible for engines: - Synthetic type conforming to PWC specification PWA 521, Type II. PWC Service Bulletin 20 001 lists approved brand oils. Engine Limits. (PW-121) Operating limits with no unscheduled maintenance action required. Beyond these limits refer to maintenance manual. POWER SETTING TIME LIMIT TO ITT NH NP OIL PRESS OIL TEMP (%) (ºC) (%) (%) (PSI) (ºC) RESERVE TAKE OFF 5 minutes 107,2 816 100 101 55 to 65 0 to 125 (1) TAKE OFF 5 minutes 92,9 (5) (4) 101 55 to 65 0 to 125 (1) MAXIMUM CONTINUOUS NONE 92,9 800 100 101 55 to 65 0 to 125 (1) GROUND IDLE 62 40 min -40 to 125 (1) min HOTEL MODE 785 40 min (2) -40 to 125 (1) STARTING 5 seconds 950 -40 min (3) TRANSIENT 10 mn 107,2 20 S 119.7 850 102 110 40 to 100 20 S 138,7 (6) 850 102 110 40 to 100 (1) Temperature up to 115ºC (120ºC in Hotel mode) is authorized without time limitation. 20 mn are authorized between 115ºC (120ºC in Hotel mode) and 125ºC. (2) For NH below 75%. NH above 75% requires 55 to 65 psi. (3) It may be assumed that before the first start of the day the oil temperature is the minimum temperature observed during the night. (4) Refer to AFM 2.04 p1A for NH limitation at take off. (5) If gearboxes incorporate SB 20316 or 20380. NOTE: Oil temperature must be maintained above 45ºC to ensure intake strut de-icing. Oil temperature must be maintained above 71ºC to ensure fuel anti-icing protection in absence of the low fuel temperature indication. Propellers. 2 Hamilton Sundstrand, four-bladed, 14 SF 5 (FAA TCDS P7NE). Blade: SFA 13( ) (see FAA TCDS P7NE) Propeller Limits. Diameter: 13 FT. (+ 1/4 in., -3/16 in. manufacturing tolerance permissible) Pitch Setting at 42. in. of the axis: Feather: 86 degrees Flight Fine: 20 degrees Ground Fine: 7 degrees Full Reverse: -10 degrees Propeller (Np) – Take off 1200 R.P.M. Max Continuous 1200 R.P.M. A53EU, Rev 38 8 of 34 III. ATR42-320 (cont'd) Airspeed Limits (IAS). Maximum operating speed VMO : 250 KIAS Maximum operating mach VMO : 0.55 VA manoeuvering speed : 160 KIAS VFE Flaps 15o : 160 KIAS (170 KIAS with MOD.1790) Flaps 30o : 145 KIAS (150 KIAS with MOD.1790) Flaps 45o : 130 KIAS (Emergency only) VLO Gear extension : 160 KIAS Gear retraction : 160 KIAS VLE Landing gear extended : 160 KIAS (170 KIAS with MOD.1790) VMC (Minimum control speed with the critical engine inoperative) - In flight - VMCA : 90.5 KIAS - Take off - VMCG: 84.5 KIAS Tire speed limit (ground speed limit): 165 KIAS Center of Gravity (C.G.) Range. (Gear Extended) Forward Limit AFT Limit (% MAC) (% MAC) Take off and landing 15 36 Flight 12 38 For aircraft incorporating ATR Modification 0951 (Service Bulletin No. ATR42-08-0001), C.G. range is modified as follows: Forward Limit AFT Limit (% MAC) (% MAC) Take off: 16,150 kg. G.W. 15 36 16,700 kg. G.W 17 32 Landing: 16,000 kg. G.W. 15 36 16,400 kg. G.W. 17 32 Flight: 12 38 (Straight line variation between points). Gear retraction has negligible effect on C.G. range. Maximum Weights. kg lb Taxi weight 16,170 35,645 Take Off weight 16,150 35,605 Landing weight 16,000 35,270 Zero Fuel weight 14,800 32,625 For aircraft incorporating ATR Modification 0863, weight limitations are modified as follows: kg lb Taxi weight 16,170 35,645 Take Off weight 16,150 35,605 Landing weight 16,000 35,270 Zero Fuel weight 15,200 33,510 For aircraft incorporating ATR Modification 0951 (ATR Service Bulletin No. ATR42-08-0001), weight limitations are modified as follows: kg lb Taxi weight 16,720 36,870 Take Off weight 16,700 36,825 Landing weight 16,400 36,160 Zero Fuel weight 15,200 33,510 9 of 34 A53EU, Rev 38 III. ATR42-320 (cont'd) Minimum Crew. 2 (pilot and co-pilot). Maximum Passengers. 46: 48 passenger capacity is approved with incorporation of modification 0481. 34: in COMBI configuration, with modification 0244 and with modification 0755 associated with the application of modifications 1073 and 1044. Maximum Baggage. Forward compartment - Maximum load 2,045 lb. Rear compartment - Maximum load 952 lb. Fuel Capacity. Density 6.55 lb/US Gallon Usable Unusable lb US Gal 46.7 lb 2 x 4,960 2 x 757 Fuel Unbalance. Maximum fuel unbalance: 550 kg (1,212 lb) Oil Capacity. Engine oil capacity Usable 1.0 US Gallon/engine Total 4.7 US Gallon/engine Maximum operating altitude. 25,000 ft. IV. ATR42-500 (Transport Category Airplane) approved May 13, 1996. Engines. Two Pratt and Whitney Aircraft of Canada, Ltd, PW127E turboprops or PW127F by SB ATR42-72-0008 or PW127M by SB ATR42-72-0010 or in production line from aircraft serial number 675 (inclusive) or PW127XT-M with MOD 10016. Engine models PW127M and PW127XT-M are interchangeable and mixable with MOD 10302, with conditions (refer to relevant approved Airplane Flight Manual). Fuel. (a) The following fuels are eligible for engines MIL-T-5624 Grade JP5 AST-MD-1655 Grades JET A, JET A1 (PWC Service Bulletin No. 20 004 details approved conditions). (b) The following types of additives may be used in approved fuels: - oxidation inhibitors, - corrosion inhibitors, - thermal stability additives, - metal deactivators, - anti icing additives, - anti stating additives, - biocide additives. List of approved additives, approved concentrations and conditions of use are identified in PWC Service Bulletin No. 20.004. Oil. The following oils are eligible for engines: - Synthetic type conforming to PWC specification PWA 521, Type II. PWC Service Bulletin 20 001 lists approved brand oils. A53EU, Rev 38 10 of 34 IV. ATR42-500 (cont'd) Engine Limits. (PW-127E) Operating limits with no unscheduled maintenance action required. Beyond these limits refer to maintenance manual. Engine rating Time limit Torque % ITT (C) NH % NL % NP % Oil Pressure (Psi) Oil temperature (1) (C) Reserve Take off 10 mn* 100** 800 103.2 104.2 101 55 to 65 0 to 125 Take off 5 mn 90** 740 to 765 101.9 101.4 101 55 to 65 0 to 125 Maximum Continuous - 100** 800 103.2 104.2 101 55 to 65 0 to 125 Ground idle 66 mini 40 mini *** -40 to 125 Hotel mode 715 55 to 65 0 to 125 Starting 5 sec. 950 -54 mini Transient 20 sec. 5 sec. 20 mn 137.5 840 104.3 106.5 106 **** 120 40 to 100 140 * Time beyond 5 mn is linked to actual single engine operations only. ** Value linked 100% NP. *** Associated with NH ratings lower than 75 %. **** Permissible for completion of flight provided torque does not exceed 85% during climb and 84 % during cruise (1) Oil temperature must be maintained above 45C to ensure protection for the engine air inlet against ice accumulation. Propellers. 2 Hamilton Sundstrand, six-bladed, 568 F -1 (FAA TCDS P8BO). Blade: R 815 505( ) (see FAA TCDS P8BO) Propeller Limits. Diameter: 13 FT. (+ 1/4 in., -3/16 in. manufacturing tolerance permissible) Pitch Setting at 58 in. of the axis: Feather : 78.5 degrees Flight Fine: 14 degrees Ground Fine: 0 degrees Full Reverse: -14 degrees Propeller (Np) - Take off 1200 R.P.M. Max Continuous 1200 R.P.M. Airspeed Limits (IAS). Maximum operating speed VMO : 250 KIAS Maximum operating mach VMO : 0.55 VA manoeuvering speed : 160 KIAS VFE Flaps 15 : 170 KIAS/180 KIAS (*) Flaps 25 : 160 KIAS Flaps 35 : 150 KIAS VLO Gear extension : 170 KIAS Gear retraction : 160 KIAS VLE Landing gear extended : 180 KIAS VMC (Minimum control speed with the critical engine inoperative) - In flight - VMCA : 98.5 KIAS (SL, ISA) - Take off - VMCG : 95 KIAS (SL, ISA) Tire speed limit (ground speed limit) : 165 KIAS (*) with embodiment of modification 4462 11 of 34 A53EU, Rev 38 IV. ATR42-500 (cont'd) Center of Gravity (C.G.) Range. (Gear Extended) Forward Limit (% MAC) AFT Limit (% MAC) Take off 16,150 kg. G.W. 18,600 kg. G.W. 15 21 34 34 Landing: 16,150 kg. G.W. 18,300 kg. G.W. 15 20.3 34 34 Flight: 16,150 kg. G.W. 18,600 Kg. G.W. 12 18 36 36 (Straight line variation between points). Gear retraction has negligible effect on C.G. range. Maximum Weights. kg lb Taxi weight 18,770 41,380 Take Off weight 18,600 41,005 Landing weight 18,300 40,344 Zero Fuel weight 16,700 36,817 Minimum Crew. 2 (pilot and co-pilot). Maximum Passengers. 60 as limited by emergency exits configuration. Maximum Baggage. Forward compartment - Maximum load 928 kg (2,046 lb) Rear compartment - Maximum load 768 kg (1,693 lb) Fuel Capacity. Density 6.55 lb/US Gallon Usable Unusable lb US Gal 46.7 lb 2 x 4,960 2 x 757 Fuel Unbalance. Maximum fuel unbalance: 550 kg (1,212 lb) Oil Capacity. Engine oil capacity Usable 1.0 US Gallon/engine Total 4.7 US Gallon/engine Maximum Operating Altitude. 25,000 ft. (a) ATR42-500 Model “600 version” Definition (Approved April 4, 2013) The ATR42-500 “600 version” designation does not correspond to a model designation. This is only a commercial designation for an ATR42-500 on which Major modifications 5948, 6521, 6230, and 6233 have been embodied during production. Modification 5948 design change consist of the installation of a New Avionics Suite (NAS) and contains the following modifications: • Integrated Avionics Display – 5 IADs including FMS and RMS functions • Core Avionics Cabinet – CAC (including AFCS, DCA, FWS & CMA functions) (x2) • AFCS servo motors + Power Trim Box • AHRS (x2) • ADC (x2) • GPS (x1), a 2nd GPS is optional • Radio Altimeter (x1) • T²CAS (ACAS + TAWS) (x1) • Transponders (x2) • Control panels • MCDU (x2) A53EU, Rev 38 12 of 34 • Integrated Electronic Stand-by Instrument (x1) • Radio Com (VHF, HF wiring provision) (x2) • Radio Nav (VOR, ILS, MKR, ADF, DME) (x2) (2nd ADF and 2nd DME are optional) • Clocks (x2) • Ambient Pressure Sensor (x1) Modification 6521 adds NAS software version L2B2 Modification 6230 adapts the NAS on the ATR42-500 Modification 6233 installs a new fuel gauging system in kilograms DATA PERTINENT TO ATR42-200, -300, -320, -500 MODELS Datum. Station 0 (93 inches forward of fuselage nose). MAC. 90 inches (leading edge of MAC: STA 450) Leveling Means. Inclinometer on the cabin seat track rails. Maximum Control Surface Deflections. ATR 42-200/-300/-320 ATR 42-500 UP DOWN UP DOWN Aileron 14  0.5 14  0.5 14  0.5 14° ± 0.25° *** 14  0.5 14° ± 0.25° *** Aileron trim 13.75  0.7 10.15  0.5 4.5  0.4 6.7° ± 0.4° *** 4.5  0.4 6.7° ± 0.4° *** Elevator + 1 25 + 0 + 1 15 - 0.6 + 1 23 + 0 + 1 13 - 0.6 Elevator trim 5.2  0.3 8.4  0.4 4  0.3 9  0.4 Rudder : + 1.5 structural stops (damper removed)  31.5 - 0 stop included in damper  30  1 Rudder trim: + 3.4 +0 on either side of the tab  18 (-200/-300/-320): 16.7 (-500) - 2.9 -3.4° +1° Spoilers : mini: spoiler deflection as from 2.5  0.5 aileron / 2.5° aileron *** -0° maxi: 57  2 for 14 aileron Flaps : ATR 42-200/-300/-320 ATR 42-500 0; 15; 30; 45** deflections 0; 15; 25; 35* manoeuvre time from 0 to 45 : 13s from 0 to 35 : 10s 45 to 0 : 23s from 35 to 0 : 18s * Flaps 35 configuration corresponds to an effective flap deflection of 33. ** Flaps 45 configuration is authorized for emergency only. *** ATR42-500 model with modification 4372 (aileron spring tab) Serial Numbers Eligible. A French "Certificat de Navigabilité pour Exportation" endorsed as noted under "Import Requirement" must be submitted for each individual aircraft for which application for US certification is made. Certification Basis. (ATR42-200/-300/-320 models) 13 of 34 A53EU, Rev 38 FAR 25, effective February 1, 1965, including amendments 25-1 through 25-54, which the FAA considers equivalent to 1, 2 and 3 below: 1 - JAR 25 change 8 and amendment 81-2 including French national variants in effect on February 2, 1982, and 2 - French ATR-42 Special Conditions, and 3 - 14 CFR Section 21.29 and the following sections of Part 25 of the FAR as amended by amendments 25-1 through 25-54: FAR 25.2 FAR 25.777(e),(g) FAR 25.1309(a),(b) FAR 25.107(d)(e) FAR 25.781 FAR 25.1331(a)(3) FAR 25.125 FAR 25.785(g) FAR 25.1353(c)(6) FAR 25.201(d) FAR 25.787(a) FAR 25.1401(b),(f) FAR 25.331(c) FAR 25.803(c)(7) FAR 25.1411(a)(2) FAR 25.351(a)(1) FAR 25.809(j) FAR 25.1415 FAR 25.361 FAR 25.903(a) FAR 25.1438 FAR 25.491 FAR 25.901 FAR 25.1501 FAR 25.511(b)(c) FAR 25.905(a) FAR 25.1513 FAR 25.571(b)(6),(e)(2) FAR 25.994 FAR 25.1521(b)(c) FAR 25.613 FAR 25.1013 FAR 25.1547(c) FAR 25.615 FAR 25.1015 FAR 25.1549 FAR 25.621 FAR 25.1019 FAR 25.1583 FAR 25.631 FAR 25.1093(b)(1),(b)(2) FAR 25.1585(a) FAR 25.671(c)(1) FAR 25.1141(f)(2) FAR 25.1587(a) FAR 25.693 FAR 25.1303(b)(4) FAR 25.773(b)(2) FAR 25.1305(c)(6)(7) Item (1), (2), and (3) above have been examined and found to be equivalent to Part 25 of the FAR through Amendment 25-54. 4 - Special conditions in accordance with § 21.16: a. FAA Special Conditions for ATCPS dated July 11, 1985 (FAR 25.904, Amendment 25-62 for the ATR42-320) b. FAA Special conditions issued for “Seats with Non-Traditional, Large, Non-Metallic Panels”, published in the Federal Register July 29, 2016, Docket No. FAA-20 16-8246, Special Conditions No. 25-624–SC. 5 - SFAR 27, Amendments 1 thru 5 6 - 14 CFR part 36 through amendment 36-31. Airplanes with ATR42 and ATR72 Airplane Flight Manual, Revision 30 and above are certificated to 14 CFR part 36 through amendment 36-31, Stage 5. 7 - FAA Exemption No. NM 104 regarding 25.571 (e) (2), granted April 19, 1984 (Propeller debris) 8 - In addition voluntary compliance with FAR 25.832, Amendment 25-56 has been demonstrated. 9 - A finding of regulatory adequacy pursuant to the "Noise Control Act of 1972" 10 - FAA findings of Equivalent safety for the following rules: FAR 25.773(b)(2), FAR 25.807(c) and (d) FAR 25.865 11 - Compliance with the following optional requirements has been established: Ice protection provisions JAR 25.1419. Structural Provisions for ditching: JAR 25.801 (a)(b)(c)(d)(e) 12 - Compliance with the following optional requirements has been established: Ditching Provisions JAR 25.1411 (a)(b)(d)(e)(f)(g)(1) and JAR 25.1415 (a)(b)(c)(d)(e) When requested by the operational rules, the life rafts must be installed in accordance with the locations defined in document 421.054/92, issue 5. 13 - For precision approach and landing, the applicable technical requirements are complemented by JAR AWO - Subpart 2 Type Certificate No. A53EU, issued October 25, 1985, amended August 25, 1988. Date of application for Type Certificate: February 26, 1982. A53EU, Rev 38 14 of 34 14 - Compliance with the requirement of FAR 25.856 at amendment 25-111 for thermal/acoustic insulation has been demonstrated to meet operational requirements. 15 - Compliance with the requirements of the following paragraphs of FAR 25.562 at amendment 25-64 for Geven Classic and Prestige passenger seats are demonstrated though ATR modification 6594 for ATR42-200/-300/-320 models: FAR 25.562(a) FAR 25.562(b) FAR 25.562(c)(2) FAR 25.562(c)(4) FAR 25.562(c)(5) FAR 25.562(c)(6) FAR 25.562(c)(7) FAR 25.562(c)(8) Based on 14 CFR § 21.29(a) for new import TCs, (or § 21.101(g) for changes to TCs), applicable provisions of 14 CFR part 26 are included in the certification basis. For any future 14 CFR part 26 amendments, the holder of this TC must demonstrate compliance with the applicable sections. Certification Basis. (ATR42-500 Model) No later regulations or special conditions are recognized at time as being necessary to provide an adequate TC basis for this amendment of TC project. The VSIG project will involve an equivalent safety finding to a number of sections and/or paragraphs in Part 1 and Part 25 of the FAR’s. Issue Paper F-2, applicable to the VSIG project, addresses this equivalent safety finding issue. The equivalent safety finding approach has been used on previously accomplished 1-G stall speed (VSIG) projects. Therefore, the certification basis established at the time of the original type certification of the ATR42 and ATR72 series airplanes shown on TCDS A53EU, with an additional equivalent safety finding for the VSIG project, will provide an acceptable TC basis for this Amendment of TC project. It has also been recognized that compliance has been demonstrated to JAR Ch.13 amended by NPA 25BDG 244 “Accelerate-STOP distances and related performance matters”: §25.101(i), §25.105(c), §25.109, §25.113, §25.115(a), §25.735 (f)(g)(h)(i)(j), §25X1591 (a)(b(c)(d). Modification 4626 is required for ditching approval. The Direction Générale de l'Aviation Civile (DGAC) of France originally type certificated this aircraft under its type certificate Number 176. The FAA validated this product under U.S. Type Certificate Number A53EU. Effective September 28, 2003, the European Aviation Safety Agency (EASA) began oversight of this product on behalf of the Direction Générale de l'Aviation Civile (DGAC) of France. Based on 14 CFR § 21.29(a) for new import TCs, (or § 21.101(g) for changes to TCs), applicable provisions of 14 CFR part 26 are included in the certification basis. For any future 14 CFR part 26 amendments, the holder of this TC must demonstrate compliance with the applicable sections. Compliance with the requirements of FAR 25.856 at amendment 25-111 for thermal/acoustic insulation has been demonstrated to meet operational requirements. Compliance with the requirements of FAR 25.562 at amendment 25-64 for rear 16G Sicma cabin attendant seat through modification 6524 and forward 16G Sicma cabin attendant seat though ATR modification 6525 has been demonstrated to meet operational requirements for ATR42-500 model. Compliance with the requirements of the following paragraphs of FAR 25.562 at amendment 25-64 for Geven Classic and Prestige passenger seats are demonstrated through modification ATR 6594 for ATR42-500 model: FAR 25.562(a) FAR 25.562(b) FAR 25.562(c)(2) FAR 25.562(c)(4) FAR 25.562(c)(5) FAR 25.562(c)(6) FAR 25.562(c)(7) FAR 25.562(c)(8) Compliance with the requirements of the following paragraphs of the following FARs are demonstrated through modification ATR 7932 (Installation of Flame Arrestor) for ATR42-500 model: 15 of 34 A53EU, Rev 38 • FAR 25.899 at amendment 25-123 • FAR 25.975(a)(7) at amendment 25-143 • FAR 25.981(a)(1), (a)(2) & (a)(3) at amendment. 25-102 14 CFR part 36 through amendment 36-31. Airplanes with ATR42 and ATR72 Airplane Flight Manual, Revision 30 and above are certificated to 14 CFR part 36 through amendment 36-31, Stage 5. Note: The noise certification values between FAA and EASA are different for the full power take-off certification point due to the different noise measurement methodology required by FAA ("Alternate Sideline" instead of "Sideline"). Please refer to the AFM for the specific noise values. Equivalent Safety Findings as applicable in accordance with Part 21 of the FAR will apply to this airplane. Equivalent Safety Findings: (1) Section 25.811(g), 25.812(b)(1) (i), 25.812(b)(1)(ii), Emergency Exit Marking Requirements (documented in FAA ELOS Memo ATI0740IB-T-CS-l). (2) Section 25.1457(d)(5), Cockpit Voice Recorders Requirements ( documented in FAA ELOS Memo SP0778IB-T-SE- 101). Certification Basis. (ATR42-500 Model “600 version”) The final FAA type certification basis, for the ATR-GIE ATR 42-500 incorporating modification 5948 (commercially called the ATR 42-500 “600 version”) is as follows: Airworthiness & Environmental Standards for components and areas not affected by the change Unchanged from the basic ATR 42-500 certification basis. Airworthiness and Environmental Standards for components and areas affected by the change 14 CFR part 25, effective February 1, 1965, including Amendments 25-1 through 25-123. The following sections are applicable: SUBPART B – Flight 25.255(a)(2) SUBPART C – STRUCTURE 25.581 SUBPART D – DESIGN AND CONSTRUCTION 25.671(b),(c), 25.672(a), 25.677(b), 25.679(a)(2), 25.685, 25.699(a),(b), 25.703, 25.729(e),(f)(3), 25.735(d), 25.771(a),(c),(e), 25.773(a), 25.777(f), 25.783(e), 25.841(b)(5),(b)(6),(b)(8), 25.843(b)(3), 25.853(a),(d),(e), 25.854(a), 25.855(h), 25.857(b)(3), 25.869(a), 25.899 SUBPART E - POWERPLANT 25.1141(f), 25.1165(g), 25.1203(a),(b)(2),(b)(3) SUBPART F - EQUIPMENT 25.1301, 25.1303, 25.1305, 25.1307(c),(d),(e), 25.1309, 25.1316, 25.1317, 25.1321, 25.1322, 25.1323, 25.1325(a),(d),(e),(f), 25.1326(a), 25.1327, 25.1329, 25.1331, 25.1333, 25.1337, 25.1351(a),(b)(6),(c),(d), 25.1353(a),(b),(c)(6),(d),(e), 25.1355, 25.1357, 25.1360, 25.1381, 25.1419(c), 25.1431, 25.1435(b)(1), 25.1459 SUBPART G – OPERATING LIMITATIONS AND OPERATIONS 25.1501, 25.1523, 25.1525, 25.1527, 25.1529, 25.1541, 25.1543, 25.1545, 25.1547, 25.1549, 25.1555, 25.1563, 25.1581, 25.1583, 25.1585, 25.1587 SUBPART H – ELECTRICAL WIRING INTERCONNECTION SYSTEMS 25.1701, 25.1703, 25.1705, 25.1707, 25.1709, 25.1711, 25.1713, 25.1715, 25.1717, 25.1719, 25.1721, 25.1729 FAA Special Condition 25-473-SC “Aircraft Electronic System Security Protection from Unauthorized External Access” FAA Special Condition 25-896-SC “Airplanes; Electronic System Security Protection from Unauthorized Internal Access” A53EU, Rev 38 16 of 34 For ATR42-500 “600 version” airplanes incorporating modification MOD 7055 “High Altitude Airport Operations up to 11,000 ft”, an Equivalent Level of Safety Finding in accordance with the provisions of 14 CFR 21.21(b)(1) for Section 25.841(d)(1): Pressurized Cabins (documented in ELOS memo AT20368IB-T-SE-101) has been made. Service Information. Each of the documents listed below that contain a statement 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) of France, are accepted by the FAA and are considered FAA approved. Additionally, approvals issued by ATR under the authority of EASA approved Design Organization EASA.21J.044 - or for approvals made before September 28, 2003 - under the authority of DGAC Design Organization Approval No. F.JA.12 are considered FAA approved. These approvals pertain to the type design only. • ATR Service Bulletins, except as noted below, • Structural repair manuals, • Vendor manuals referenced in ATR service bulletins • Aircraft flight manuals, • Repair Instructions. Note: Design changes that are contained in ATR Service Bulletins and that are classified as Level 1 Major or Non-Basic in accordance with either the US/France or US/EASA Bilateral Aviation Safety Agreement Implementation Procedures for Airworthiness must be approved by the FAA. Equipment. The basic required equipment as prescribed in the applicable Federal Aviation Regulations must be installed in the aircraft. ATR equipment list, document GATR/C No 422.204/85 (ATR42-200/-300/-320 models) or A/RT/C No. 425.0469/95 (ATR42-500 model) identifies all required equipment and all optional equipment approved by the Direction Générale de l'Aviation Civil (DGAC) of France. In addition, the following is required: (1) DGAC/EASA approved FAA Airplane Flight Manual - Import Information. 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) of France 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 conform with Type Design approved under U.S. Type Certificate No. A53EU and to be in a condition for safe operation. Compliance with Airworthiness Directives (ADs) has been checked only for ADs issued by EASA, ADs adopted by EASA and ADs published by FAA.’ 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. NOTES NOTE 1 - Weight and Balance (a) Current weight and balance report including list of equipment, entitled "Aircraft Inspection Report", included in certificated empty weight, and loading instructions, must be in each aircraft at the time of original certification and at all times thereafter except in the case of operators having an approved weight control systems. ATR Report, "Weight and Balance Manual", contains loading information for each airplane and interior arrangement configuration as delivered. This report contains, or refers to, information relative to location and capacity of all cargo and baggage compartments, buffets, storage spaces and coat rooms, location and capacity of lounges, lavatories, and the required placards in the passenger compartment. 17 of 34 A53EU, Rev 38 (b) The airplane must be loaded so that the C.G. is within specified limits at all times, considering fuel loading and usage, gear retraction and movement of crew and passengers from their assigned positions. (c) The weights of system fuel and oil, as defined below, and hydraulic fluid, all of which must be included in the airplane empty weight, are listed for each airplane in the Weight and Balance Manual specified in paragraph (a) above. (d) System fuel is the weight of all fuel required to fill all lines and tanks up to zero-fuel point on the fuel gages in the most critical flight attitude, including the unusable tank fuel as defined by FAR Part 25.959. (The usable fuel in the crossfeed manifold lines, manifolds, and engine that is not part of the system, fuel must be included in the total usable fuel to obtain correct weight and C.G. for take off). (e) The unusable fuel is that amount of fuel in the tanks which is unavailable to the engines under critical flight conditions as defined in FAR Part 25.959. This "unusable" fuel is included in System Fuel as indicated in (d) above and need not be accounted for separately. (f) System oil is the weight of oil remaining in the engine, lines and tanks after subtracting the oil in the tanks which is above the standpipe (zero gauge) levels. The engine oil capacities shown elsewhere in this data sheet include only the useable oil for which the tanks must be placarded. NOTE 2 The aircraft must be operated in accordance with the DGAC-Approved FAA Airplane Flight Manual. ("DGAC approved" is considered equivalent to "FAA Approved"). NOTE 3 The required Airworthiness limitations including structural inspections and retirements times for safe life parts are covered by the "Time Limits" document ATR 42-200/-300/-320/-500 models, approved by EASA. NOTE 4 Cabin Equipment Seats and galleys must be designed in accordance with ATR Specifications 419.282/82 and 419.464/82 for ATR 42-200/-300/-320 models, with ATR Specifications 419.0008/95 issue 4 and 421.614/94 for ATR 42-500 model. NOTE 5 The list of modifications permitting use of the ATR42 for Category II approach is contained in Service Letter ATR42-22-5001 for ATR42-200/-300/-320 models. The modification permitting use of the ATR 42-500 model for Category II approach is 1112. NOTE 6 The basic definition for US import certification is contained in Document GATR/C 422.627/85 (ATR42- 200/-300/-320 models) or A/RT/C 425.0985/95 (ATR42-500 model), initial issue or later approved revision. NOTE 7 ATR Modification 0885 (ATR 42 Service Bulletin ATR42-30-0005) is a required part of the United States approved Type Design A53EU and must be incorporated on all U.S. registered aircraft. NOTE 8 Operation on narrow runways is approved for ATR42-500 with incorporation of modification 4718 A53EU, Rev 38 18 of 34 V. ATR72-101/-201 (Transport Category Airplane) approved November 15, 1989 ATR72-102/-202 (Transport Category Airplane) approved January 18, 1991. Engines. Two Pratt and Whitney Aircraft of Canada, Ltd., 124B PW turboprops. Fuel. (a) The following fuels are eligible for engines MIL-T-5624 Grade JP5 AST-MD-1655 Grades JET A, JET A1 Conforming to PWC Specification PN A204. (PWC Service Bulletin No. 20.004 details approval conditions). (b) The following types of additives may be used in approved fuels: - oxidation inhibitors, - corrosion inhibitors, - thermal stability additives, - metal deactivators, - anti icing additives, - anti stating additives, - biocide additives. List of approved additives, approved concentrations and conditions of use are identified in PWC Service Bulletin No. 20.004 Oil. The following oils are eligible for engines: - Synthetic type conforming to PWC specification PWA 521, Type II. PWC Service Bulletin 20.001 lists approved brand oils. Engine Limit. Operating limits with no unscheduled maintenance action required. Beyond these limits refer to maintenance manual. ENGINE DURATION TORQUE ITT NH NL NP OIL PRESS OIL TEMP RATINGS % ( C) % % % (PSI) ( C) Take off 5 mn 800 102.7 104 55 to 65 0 to 125 (3) with 106,3 101 reserve Take off 5 mn 90 (1) 101 101.7 101 55 to 65 0 to 125 (3) Maximum -------- 89.6 800 102 102.9 101 55 to 65 0 to 125 (3) Continuous 102,5* 102.7* 104* 101 55 to 65 Ground 66 40 min -40 to 125 Idle min (3) Hotel 715 55 to 65 -40 to 125 mode (3) Starting 5 s 950 -54 min Other 102,3 800 (2) Transient 20 s 124.5 840 103.7 104.3 115 40 to 100 10 mn 106.3 * Limitation for engine fitted with mod. 2735 (1) ITT limits depend on outside air temperature. (2) When NP is below 86% NOTE: Using a reduced NP, TQ may exceed 100% but not 102.3% (3) Temperature up to 115ºC (120ºC in hotel mode) is authorized without time limitation. 20 mn are authorized between 115ºC (120ºC in hotel mode) and 125ºC. NOTE: Oil temperature must be maintained above 45ºC to ensure intake strut de-icing. Oil temperature must be maintained above 71ºC to ensure fuel anti-icing protection in absence of the low fuel temperature indication. 19 of 34 A53EU, Rev 38 V. ATR72-101/-201, ATR72-102/-202 (Continued) 765 770 775 780 0 20 40 54 60 ITT TG ( C)o ( C)oOAT Propellers. 2 Hamilton Sundstrand, four-bladed, 14 SF 11 (FAA TCDS P7NE) Blade: SFA 13( ) (see FAA TCDS P7NE) Propeller Limits. Diameter: 13 Ft. (+ 1/4 in., -3/6 in. manufacturing tolerance permissible) Pitch Setting at 42. in. of the axis: Feather: 86 degrees Flight Fine: 20 degrees Ground Fine: 7 degrees Full Reserve:-10 degrees Propeller (NP) – Take off 1200 R.P.M. Max Continuous 1200 R.P.M. Airspeed Limits (IAS). VMO Maximum operating speed MMO Maximum operating speed VA Design manoeuvering speed VFE 15º flaps 30º flaps VLO L/G extension VLO L/G extension VLE Landing gear extension speed Tyre limit speeds (ground speed) 250 kt 0.55 175 kt 185 kt 150 kt 170 kt 160 kt 185 kt 165 kt Center of Gravity (CG) Range. (Gear extended) ** Models 101/102 Forward Limit AFT Limit % MAC % MAC _________________________________________________________________________________ Take off and Landing up to 18000 kg (39690 lbs) 13.7 37 19990 kg (44078 lbs) 17.1 37 _________________________________________________________________________________ Flight up to 18000 kg (39690 lbs) 10 39 19990 kg (44078 lbs) 13.7 39 A53EU, Rev 38 20 of 34 V. ATR72-101/-201, ATR72-102/-202 (Continued) Models 201/202 Forward Limit AFT Limit % MAC % MAC _________________________________________________________________________________ Take off and Landing up to 18000 kg (39690 lbs) 14 37 21500 kg (47408 lbs) 19 37 _________________________________________________________________________________ Flight up to 18000 kg (39690 lbs) 10 39 21500 kg (47408 lbs) 16 39 _________________________________________________________________________________ * (Straight line variation between points). ** Gear Extension has negligible effect on CG Range. Maximum Weights ATR 72-101/-102 Basic ATR 72-201/-202 Basic ATR 72-201/202 Mod. 3651 At taxiing 20020 kg (44136 lbs) 21530 kg (47465 lbs) 22030 (48667 lbs) At take off 19990 kg (44070 lbs) 21500 kg (47400 lbs) 22000 (48501 lbs) At Landing 19900 kg (43871 lbs) 21350 kg (47068 lbs) 21350 (47068 lbs) With no fuel Mod. 3849 19350 kg (42659 lbs) N/A 19700 kg (43430 lbs) 20000 kg (44071 lbs) 19700 (43430 lbs) 20000 kg (44071 lbs) Minimum Crew. 2 (pilot and co-pilot) Maximum Passengers. 74 passengers Maximum Baggage. -101/-201: - Forward compartment - Maximum load 624 kg. (1376 lb) -102/-202: - Forward compartment - Maximum load 928 kg. (2046 lb) - Rear compartment - Maximum load 768 kg. (1693 lb) - Mod. 2059: - RH Rear compartment - Maximum load 512 kg. (1129 lb) Fuel Capacity. Density 6.55 lb/US Gallon UNUSABLE USABLE FUEL FUEL Normal refueling Refueling with high (kg) level cut-off 30 5000 kg 5050 kg 6360 l. Fuel Unbalance. Maximum fuel unbalance: 730 kg (1609 lb) Oil Capacity. Engine oil capacity Usable 1.0 US Gallon/engine Total 4.7 US Gallon/engine Maximum Operating Altitude. 25,000 ft. 21 of 34 A53EU, Rev 38 VI. ATR72-211/-212 (Transport Category Airplane) approved December 15, 1992. Engines. Two Pratt and Whitney Aircraft of Canada, Ltd., PW127 or PW127F turboprops. through SB ATR72-72-1004 Fuel. (a) The following fuels are eligible for engines MIL-T-5624 Grade JP5 AST-MD-1655 Grades JET A, JET A1 Conforming to PWC Specification PN A204. (PWC Service Bulletin No. 20.004 details approval conditions). (b) The following types of additives may be used in approved fuels: - oxidation inhibitors, - corrosion inhibitors, - thermal stability additives, - metal deactivators, - anti icing additives, - anti stating additives, - biocide additives. List of approved additives, approved concentrations and conditions of use are identified in PWC Service Bulletin No. 20.004 R3. Oil. The following oils are eligible for engines: - Synthetic type conforming to PWC specification PWA 521, Type II. PWC Service Bulletin 20.001 R3 lists approved brand oils. Engine Limit. Operating limits with no unscheduled maintenance action required. Beyond these limits refer to maintenance manual. ENGINE DURATION TORQUE ITT NH NL NP OIL PRESS OIL TEMP RATINGS % ( C) % % % (PSI) ( C) Take off 5 mn 800 103.2 104.2 55 to 65 0 to 140 (3) with 106,3 101 reserve Take off 5 mn 90 (1) 101.9 101.4 101 55 to 65 0 to 140 (3) Maximum ------- 90.9 800 103.2 104.2 101 55 to 65 0 to 140 (3) Continuous Ground 66 40 min -40 to 140 Idle min (3) Hotel 715 55 to 65 -40 to 140 mode (3) Starting 5 s 950 -54 min. Other 800 106 (2) Transient 20 s 5 s 109.6 840 104.3 106.5 120 10 mn 106.3 (1) ITT limits depend on outside air temperature (2) TQ not to exceed 75% (3) Temperature up to 125º is authorized without time limitation. 20 mn are authorized between 125ºC and 140º C. NOTE: Oil temperature must be maintained above 45ºC to ensure intake strut de-icing. Oil temperature must be maintained above 71ºC to ensure fuel anti-icing protection in absence of the low fuel temperature indication. A53EU, Rev 38 22 of 34 VI. ATR72-211/-212 (Continued) LIMITATION IN APPROACH During final approach, if SAT is greater than ISA, do not maintain NH under 78%. (1) The ITT Limits depend on the exterior temperature. -50 -40 -30 -20 -10 0 10 15 30 OAT ( C)o 720 740 760 765 780 ITT T6 ( C)o Propellers. a) Basic Installation 2 Hamilton Sundstrand, four-bladed, 247F-1 (FAA TCDS P1BO) or 2 Hamilton Sundstrand, four-bladed, 247F-1E (FAA TCDS P1BO) Blade: R810640( ) or R817370( ) (see FAA TCDS P1BO) Propeller Limits. Diameter: 13 FT. (+ 1/4 in., -3/6 in. manufacturing tolerance permissible) Pitch Setting at 60. in. of the axis: Feather: 78.5 degrees Flight Fine: 12.6 degrees Ground Fine: -3 degrees Full Reserve: -15.2 degrees Propeller (Np) – Take off 1200 R.P.M. Max Continuous 1200 R.P.M. Propellers. b) Second Source (embodiment of modification 3560). 2 Hamilton Sundstrand, four-bladed, 14 SFL-11 (FAA TCDS P7NE) Blade: SFA 13( ) (see FAA TCDS P7NE) 23 of 34 A53EU, Rev 38 VI. ATR72-211/-212 (Continued) Propeller Limits. Diameter: 13 Ft. (+ 1/4 in., -3/6 in. manufacturing tolerance permissible). Pitch Setting at 42. in . of the axis: Feather: 86 degrees Flight Fine: 20 degrees Ground Fine: 7 degrees Full Reserve: -10 degrees Propeller (NP) - Take off 1200 R.P.M. Max Continuous 1200 R.P.M. Airspeed Limits (IAS). VMO Maximum operating speed MMO Maximum operating speed VA Design manoeuvering speed VFE 15º flaps 30º flaps VLO L/G extension VLO L/G retraction VLE Landing gear extended speed Tire limit speeds (ground speed) 250 kt 0.55 175 kt 185 kt 150 kt 170 kt 160 kt 185 kt 165 kt Center of Gravity (CG) Range. (Gear extended) ** Models 211/212 Forward Limit AFT Limit % MAC % MAC _________________________________________________________________________________ Take off and Landing up to 18000 kg (39690 lbs) 14 37 21500 kg (47408 lbs) 19 37 _________________________________________________________________________________ Flight up to 18000 kg (39690 lbs) 10 39 21500 kg (47408 lbs) 16 39 _________________________________________________________________________________ * (Straight line variation between points). ** Gear Extension has negligible effect on CG Range. Maximum Weights. ATR 72-211/-212 Basic ATR 72-211/-212 Mod. 3651 At taxiing 21530 kg (47465 lbs) 22030 kg (48567 lbs) At take off 21500 kg (47400 lbs) 22000 kg (48501 lbs) At Landing 21350 kg (47068 lbs) 21350 kg (47068 lbs) With no fuel Mod. 3849 19700 kg (43430 lbs) 20000 kg (44091 lbs) 19700 kg (43430 lbs) 20000 kg (44091 lbs) Minimum Crew. 2 (pilot and co-pilot). Maximum Passengers. 74 passengers. Maximum Baggage. -211 : - Forward compartment - Maximum load 624 kg. (1376 lb) -212 : - Forward compartment - Maximum load 928 kg. (2046 lb) - Rear compartment - Maximum load 768 kg. (1693 lb) -Mod.2059:- LH Rear compartment - Maximum load 512 kg. (1129 lb) A53EU, Rev 38 24 of 34 VI. ATR72-211/-212 (Continued) Fuel Capacity. Density 6.55 lb/US Gallon UNUSABLE USABLE FUEL FUEL Normal refueling Refueling with high (kg) level cut-off 30 5000 kg 5050 kg 6360 l. Fuel Unbalance. Maximum fuel unbalance: 730 kg (1609 lb) Oil Capacity. Engine oil capacity Usable 1.0 US Gallon/engine Total 4.7 US Gallon/engine Maximum operating altitude. 25,000 ft. VII. ATR72-212A (Transport Category Airplane) approved June 19, 1997. Engines. Two Pratt and Whitney Aircraft of Canada, Ltd, PW127F turboprops or PW127M by SB ATR72-72-1006 or from production line from aircraft serial number 779 (inclusive) or PW127XT-M with MOD 10016 or PW127N with MOD 7079. Engine models PW127M and PW127XT-M are interchangeable and mixable with MOD 10302, with conditions (refer to relevant approved Airplane Flight Manual). Fuel. (a) The following fuels are eligible for engines MIL-T-5624 Grade JP5 AST-MD-1655 Grades JET A, JET A1 (PWC Service Bulletin No. 20 004 details approved conditions). (b) The following types of additives may be used in approved fuels: - oxidation inhibitors, - corrosion inhibitors, - thermal stability additives, - metal deactivators, - anti icing additives, - anti stating additives, - biocide additives. List of approved additives, approved concentrations and conditions of use are identified in PWC Service Bulletin No. 20.004. The following oils are eligible for engines: - Synthetic type conforming to PWC specification PWA 521, Type II. PWC Service Bulletin 20 001 lists approved brand oils. 25 of 34 A53EU, Rev 38 VII. ATR72--212A (Continued) Engine Limits. (PW-127F) Operating limits with no unscheduled maintenance action required. Beyond these limits refer to maintenance manual. Engine Rating Time limit Torque % ITT (°C) NH % NL % NP % Oil Pressure (Psi) Oil Temperature (1) (°C) Reserve Take off 10 mn* 100** 800 103.2 104.2 101 55 to 65 0 to 125 Take off 5 mn 90** 740 to 765 101.9 101.4 101 55 to 65 0 to 125 Maximum Continuous - 90.9** 800 103.2 104.2 101 55 to 65 0 to 125 Ground idle 66 mini 40 mini *** -40 to 125 Hotel mode 715 55 to 65 0 to 125 Starting 5 sec. 950 -54 mini Transient 20 sec. 5 sec. 20 mn 120 840 106.4 106.8 106 **** 120 40 to 100 140 * Time beyond 5 mn is linked to actual single engine operations only. ** Value linked 100% NP. *** Associated with NH ratings lower than 75%. **** Permissible for completion of flight provided torque does not exceed 75.2 % during climb and 73.13 % during cruise. (1) Oil temperature must be maintained above 45°C to ensure protection for the engine air inlet against ice accumulation. Propellers. 2 Hamilton Sundstrand, six-bladed, 568 F-1 (FAA TCDS P8BO). Blade: R 815 505( ) (see FAA TCDS P8BO) Propeller Limits. Diameter: 13 FT. (+ ¼ in., -3/16 in. manufacturing tolerance permissible) Pitch Setting at 58 in. of the axis: Feather: 78.5 degrees Flight Fine: 14 degrees Ground Fine: 0 degrees Full Reverse: -14 degrees Propeller (Np) – Take off 1200 R.P.M. Max Continuous 1200 R.P.M. Airspeed Limits. VMO Maximum operating speed MMO Maximum operating speed VA Design manoeuvering speed VFE 15° flaps 30° flaps VLO L/G extension VLO L/G retraction VLE Landing gear extended speed Tire limit speeds (ground speed) 250 kt 0.55 175 kt 185 kt 150 kt 170 kt 160 kt 185 kt 165 kt A53EU, Rev 38 26 of 34 VII. ATR72-212A (Continued) Center of Gravity (CG) Range. (Gear extended) (2) Forward Limit % MAC AFT Limit % MAC Take off and Landing up to 18000 kg (39690 lbs) 22000 kg (48501 lbs) (3) 22500 kg (49603 lbs) (4) 22800 kg (50265 lbs) (5) 23000 kg (50706 lbs) 14 19.5 20.2 20.6 20.9 37 37 37 37 37 Flight up to 18000 kg (39690 lbs) 22000 kg (48501 lbs) (3) 22500 kg (49603 lbs) (4) 22800 kg (50265 lbs) (5) 23000 kg (50706 lbs) 10 16.6 17.4 17.9 18.25 39 39 39 39 39 (1) (Straight line variation between points). (2) Gear Extension has negligible effect on CG Range. (3) With embodiment of modification 4671 (4) With embodiment of modification 5555 (5) With embodiment of modification 6219 Maximum Weights . ATR 72-212A Basic ATR 72-212A Mod. 4671 ATR 72-212A Mod. 4671 + 5213 At taxiing 22180 kg(48898 lbs) 22670 kg (49978 lbs) 22670 kg (49978 lbs) At take off 22000 kg (48501 lbs) 22500 kg (49603 lbs) 22500 kg (49603) At landing 21850 kg (48170 lbs) 22350 kg (49273) 22350 kg (49273 lbs) With no fuel 20000 kg (44092 lbs) 20300 kg (44753 lbs) 20500 (45194 lbs) ATR 72-212A Mod. 5555 ATR 72-212A Mod. 6219 ATR 72-212A Mod. 6404 operations on dry unpaved runways At taxiing 22970 kg (50640 lbs) 23170 kg (51080 lbs) 21670 kg (47674 lbs) At take off 22800 kg (50265 lbs) 23000 (50706 lbs) 21500 kg (47300 lbs) At landing 22350 kg (49273 lbs) 22350 kg (49273 lbs) 21350 kg (46970 lbs) With no fuel 20800 kg (45856 lbs) 21000 kg (46296 lbs) 19700 kg (43340 lbs) Minimum Crew. 2 (pilot and co-pilot). Maximum Passengers. 74 passengers (not applicable to ATR 72-212A “600F version” (full cargo)) Maximum Baggage. - Forward compartment - Maximum load 928 kg. (2046 lb) - Rear compartment - Maximum load 768 kg. (1693 lb) Note: both Maximum baggage configurations are not applicable to ATR 72-212A “600F version” (full cargo). Fuel Capacity. Density 6.55 lb/US Gallon UNUSABLE USABLE FUEL FUEL Normal refueling Refueling with high level cut-off (kg) 30 5000 kg 5050 kg 6360 l. 27 of 34 A53EU, Rev 38 VII. ATR72-212A (Continued) Fuel Unbalance. Maximum fuel unbalance: 730 kg (1609 lb) Oil Capacity. Engine oil capacity Usable 1.0 US Gallon/engine Total 4.7 US Gallon/engine Maximum Operating Altitude. 25,000 ft. (a) ATR72-212A Model “600 version” Definition (Approved April 4, 2013) The ATR72-212A “600 version” designation does not correspond to a model designation. This is only a commercial designation for an ATR72-212A on which Major modifications 5948, 6521, and 5977 have been embodied during production. Modification 5948 design change consists of the installation of a New Avionics Suite (NAS) and contains the following modifications: • Integrated Avionics Display – 5 IADs including FMS and RMS functions • Core Avionics Cabinet – CAC (including AFCS, DCA, FWS & CMA functions) (x2) • AFCS servo motors + Power Trim Box • AHRS (x2) • ADC (x2) • GPS (x1) • Radio Altimeter (x1) • T²CAS (ACAS + TAWS) (x1) • Transponders (x2) • Control panels • MCDU (x2) • Integrated Electronic Stand-by Instrument (x1) • Radio Com (VHF, HF wiring provision) (x2) • Radio Nav (VOR, ILS, MKR, ADF, DME) (x2) (1 ADF and 1 DME are optional) • Clocks (x2) • Ambient Pressure Sensor (x1) Modification 6521 adds NAS software version L2B2 Modification 5977 installs a new fuel gauging system in kilograms (b) ATR72-212A “600F version” (full cargo) Definition (Approved March 3, 2021) ATR72-212A “600F version” designation does not correspond to a model designation. This is only a commercial designation for an ATR72-212A, with New Avionics Suite (NAS), on which Major modification 7900 has been embodied during production. Another allowable commercial designation is ATR72-600F. Modification 7900 design change consists of the full cargo conversion with the following main modifications: • A Large Cargo Door (LCD) in replacement of the standard forward LH cargo door, based on FAA ST01761 NY technical solutions, • An upper hinged rear cargo door of the same opening size as the passenger door, • A structural tube for class-E cargo operations, based on the same STC technical solutions, • A windowless fuselage, without type III doors nor the aft RH service door, • Removal of thermo-acoustics blankets, except for section 11 (Flight deck area), • Removal of passenger oxygen and air conditioning distribution and other passengers systems and features. • A fire protection system and cargo interiors compatible with class-E cargo operations, • A cockpit door "western" type not secured (made from ATR 42-500 standard version one), • Reinforcement of floor panels at 488Kg/m2 [100lbs/ft2], • A basic MTOW = 22800 kg (50265 lbs) and MZFW = 20800 kg (45856 lbs), with an option to reach MTOW = 23000 kg (50706 lbs) and MZFW = 21000 kg (46296 lbs). • An enhanced corrosion protection, • A lower surround skin protection plates for each cargo door. A53EU, Rev 38 28 of 34 DATA PERTINENT TO ATR72-101/-201, -102/-202, -211/-212 AND -212A MODELS. Datum. Station 0 (93 inches forward of fuselage nose). MAC. 93,5 inches (leading edge of MAC: STA 535,6). Leveling Means. Clinometer on the main landing gear fairing. Maximum Control Surface Deflection. UP DWN Aileron 14º ± 0.5º + 14° ± 0.25°* 14º ± 0.5º + 14° ± 0.25°* Aileron Trim 4º ± 0.35º 6.7° ± 0.4°* 4º ± 0.35º 6.7° ± 0.4°* Pitch 23° +1° +0° 13° +1° -0.6° Pitch Trim + 5º ± 0.25° - 1.5º ± 0.1° * ATR 72-212A model Rudder : Structural stops (damper removed) ± 28.5o + 1.5o - 0o Stops included in damper ± 27o ± 1o Rudder Trim : On either side of the tab ± 16.7o + 0o - 3.4o Spoilers : Min. spoiler actuation for -2.5o ± 0.25o aileron : Max.: 57om± 2o for -14o aileron Flaps : Deflection 0o; 15o; 28o (-101/-201 and -102/-202 models) : Deflection 0o; 15o; 33o (-211/-212/-212A models) Operating time from 0o to 28o Operating time from 0o to 33o Extension 0o to 15o : 4s Extension 0o to 15o : 4s 15o to 28o : 4s 15o to 33o : 5s Retraction 28o to 15o: 7s Retraction 33o to 15o: 8s 15o to 0o: 6s 15o to 0o: 6s Serial Number Eligible. A French "Certificat de Navigabilité pour Exportation" endorsed as noted under "Import Requirements" must be submitted for each individual aircraft for which application for US certification is made. Certification Basis. (ATR 72-101/-102, -201/-202, -211/-212 models) 1. - JAR 25 Change 8 and Amendment 81-2 including French national variants in effect on February 2, 1982. 2. - French ATR-42 Special Conditions. 3. - French ATR-72 Special Condition B6 and B7. 29 of 34 A53EU, Rev 38 4. - The following Sections of Part 25 of the FAR, as amended by Amendments 25-1 through 25-54: 25.2 25.777(e),(g) 25.1309(a),(b) 25.107(d)(e) 25.781 25.1331(a)(3) 25.125 25.785(g) 25.1353(c)(6) 25.201(d) 25.787(a) 25.1401(b),(f) 25.331(c) 25.803(c)(7) 25.1411(a)(2) 25.351(a)(1) 25.809(j) 25.1415 25.361 25.903(a) 25.1438 25.491 25.901 25.1501 25.511(b)(c) 25.905(a) 25.1513 25.571(b)(6),(e)(2) 25.994 25.1521(b)(c) 25.613 25.1013 25.1547(c) 25.615 25.1015 25.1549 25.621 25.1019 25.1583 25.631 25.1093(b)(1),(b)(2) 25.1585(a) 25.671(c)(1) 25.1141(f)(2) 25.1587(a) 25.693 25.1303(b)(4) 25.773(b)(2) 25.1305(c)(6)(7) 5. - The applicant has volunteered to comply with the following Sections: 25.832 as amended by Amendment 25-56. 25.812 as amended by Amendment 25-58. 25.853 as amended by Amendment 25-59. The combined requirements shown in 1, 2, 3, and 4 above have been determined to provide a certification basis equivalent to FAR Part 25, effective February 1, 1965, as amended by Amendments 25-1 through 25-54. 6. - Section 25.904, as amended by Amendment 25-1 through 25-62, in place of FAA Special Conditions dated July 11, 1985, for the ATPCS. 7. - SFAR 27, including all amendments, effective on or before the ATR-72 TC date. This is expected to be SFAR 27-6. 8. - 14 CFR part 36 through amendment 36-28. Airplanes (ATR72-101/-201, -102/-202 models) with ATR42 and ATR72 Airplane Flight Manual, Revision 30 and above are certificated to 14 CFR part 36 through amendment 36-28, Stage 4. 14 CFR part 36 through amendment 36-31. Airplanes (ATR72-211/-212 models) with ATR42 and ATR72 Airplane Flight Manual, Revision 30 and above are certificated to 14 CFR part 36 through amendment 36-31, Stage 5. 9. - FAA Exemption 4385 (NM104) regarding Section 25.571(e)(2), granted April 19, 1984, (propeller debris). 10. - A finding of regulatory adequacy pursuant to the "Noise Control Act of 1972." 11. - FAA findings of equivalent safety for Section 25.773(b)(2). 12. - Compliance with the following optional requirements has been established: Ice protection provisions JAR 25.1419. 13. - Compliance with the following optional requirements has been established: Ditching provisions JAR 25.1411(a)(b)(c)(d)(e)(f)(g)(1) and JAR 25.1415(b)(c)(d)(e). JAR 25.801(a)(b)(c)(d)(e). When requested by the operational rules, the life rafts must be installed in accordance with The locations defined in document 421.0178/96 issue 2. 14. - For precision approach and landing, the applicable technical requirements are complemented by the following FAA Advisory Circulars (AC): AC 25-1329-1A for the autopilot. AC 20-57A for autoland. AC 120-29 for Category II. AC 120-28C with applicable Appendices for Category III. 15. – FAA Special conditions issued for “Seats with Non-Traditional, Large, Non-Metallic Panels”, published in the Federal Register July 29, 2016, Docket No. FAA-20 16-8246, Special Conditions No. 25-624–SC. 16 - Compliance with the requirements of the following paragraphs of FAR 25.562 at amendment 25-64 for Geven Classic and Prestige passenger seats are demonstrated through ATR modification 6594 for ATR 72-102/-202/-212/-212A models: FAR 25.562(a) A53EU, Rev 38 30 of 34 FAR 25.562(b) FAR 25.562(c)(2) FAR 25.562(c)(4) FAR 25.562(c)(5) FAR 25.562(c)(6) FAR 25.562(c)(7) FAR 25.562(c)(8) Based on 14 CFR § 21.29(a) for new import TCs, (or § 21.101(g) for changes to TCs), applicable provisions of 14 CFR part 26 are included in the certification basis. For any future 14 CFR part 26 amendments, the holder of this TC must demonstrate compliance with the applicable sections. Compliance with the requirements of FAR 25.856 at amendment 25-111 for thermal/acoustic insulation has been demonstrated to meet operational requirements. Certification Basis (ATR 72-212A model). The TC basis for the baseline airplane is Part 25 of the Federal Aviation Regulations dated February 1, 1965 as amended by Amendments 25-1 through and including Amendment 25-54 plus specified Special Conditions, Exemptions, and Equivalent Level of Safety Findings. The design changes introduced by ATR 72-212A model are not considered extensive enough to require evaluation in accordance with the derivative procedures discussed in FAA Order 8110.4A. Therefore, no later regulations or special conditions are recognized at this time as being necessary to provide an adequate TC basis for this amendment of TC project, except as noted below. While installation of a new-look interior may not require re-substantiation of interior components or compliance to later airworthiness standards under the guidance FAA Order 8110.4A, it has been shown that installation of seats meeting Amendment 25-64 significantly enhances safety. In accordance with agreements reached between FAA, DGAC, and Aerospatiale during certification of the Model ATR-42-500, Aerospatiale has agreed to comply with FAR 25 Amendment 25-64. A discussion of this issue as it relates to this airplane is contained in Issue Paper C-1. Occasionally, Part 121 is amended to require compliance with newly adopted standards of Part 25 on a retroactive basis. In order to facilitate US operator compliance with Part 121 and to provide a consistent certification basis with the latest operating rules, any Part 121 requirement for which the Aerospatiale ATR72-212A complies and which has a corresponding Part 25 requirement, should be included in the certification basis. Additional Part 121 requirements, with a corresponding Part 25 requirement, published after closure of this issue paper will not be required to be included in the certification basis. The FAA has raised the issue of Structural Design Stall Speeds, and a discussion of this issue as it applies to this airplane is contained in Issue Paper A-1. The FAA has raised the issue of Supercooled Large Droplets (SLD) Icing Effects on ATR-42/72 New Ailerons, and a discussion of this issue as it applies to this airplane is contained in Issue Paper F-1. Compliance with the requirements of FAR 25.562 at amendment 25-64 for rear 16G Sicma cabin attendant seat through modification 6524 and forward 16G Sicma cabin attendant seat though ATR modification 6525 has been demonstrated to meet operational requirements for ATR72-212A model. Compliance with the requirements of the following paragraphs of the following FARs are demonstrated through modification ATR 7928 (Installation of Flame Arrestor) for ATR72-212A model: • FAR 25.899 at amendment 25-123 • FAR 25.975(a)(7) at amendment 25-143 • FAR 25.981(a)(1), (a)(2) & (a)(3) at amendment. 25-102 In accordance with § 21.16 of the FAR the special conditions listed on TCDS A53EU are part of the Aerospatiale ATR72-211/- 212 certification basis and will also be part of the Aerospatiale ATR72-212A (Reference Type Certificate Data Sheet No. A53EU). Part 34 of the FAR as amended at the time of certification will apply to this airplane. 31 of 34 A53EU, Rev 38 14 CFR part 36 through amendment 36-31. Airplanes with ATR42 and ATR72 Airplane Flight Manual, Revision 30 and above are certificated to 14 CFR part 36 through amendment 36-31, Stage 5. Note: The noise certification values between FAA and EASA are different for the full power take-off certification point due to the different noise measurement methodology required by FAA ("Alternate Sideline" instead of "Sideline"). Please refer to the AFM for the specific noise values. Exemptions granted in accordance with Part 11 of the FAR will apply to this airplane. Equivalent Safety Findings as applicable in accordance with Part 21 of the FAR will apply to this airplane. Equivalent Safety Findings: (1) Section 25.811(g), 25.812(b)(1) (i), 25.812(b)(1)(ii), Emergency Exit Marking Requirements (documented in FAA ELOS Memo ATI0740IB-T-CS-l). (2) Section 25.1457(d)(5), Cockpit Voice Recorders Requirements ( documented in FAA ELOS Memo SP0778IB-T-SE- 101). Certification Basis. (ATR72-212A Model “600 version”) The final FAA type certification basis, for the ATR 72-212A incorporating modification 5948 (commercially called the ATR72- 212A “600 version”) is as follows: Airworthiness & Environmental Standards for components and areas not affected by the change Unchanged from the basic ATR 72-212A certification basis. Airworthiness and Environmental Standards for components and areas affected by the change 14 CFR part 25, effective February 1, 1965, including Amendments 25-1 through 25-123. The following sections are applicable: SUBPART B – Flight 25.255(a)(2) SUBPART C – STRUCTURE 25.581 SUBPART D – DESIGN AND CONSTRUCTION 25.671(b),(c), 25.672(a), 25.677(b), 25.679(a)(2), 25.685, 25.699(a),(b), 25.703, 25.729(e),(f)(3), 25.735(d), 25.771(a),(c),(e), 25.773(a), 25.777(f), 25.783(e), 25.841(b)(5),(b)(6),(b)(8), 25.843(b)(3), 25.853(a),(d),(e), 25.854(a), 25.855(h), 25.857(b)(3), 25.869(a), 25.899 SUBPART E - POWERPLANT 25.1141(f), 25.1165(g), 25.1203(a),(b)(2),(b)(3) SUBPART F - EQUIPMENT 25.1301, 25.1303, 25.1305, 25.1307(c),(d),(e), 25.1309, 25.1316, 25.1317, 25.1321, 25.1322, 25.1323, 25.1325(a),(d),(e),(f), 25.1326(a), 25.1327, 25.1329, 25.1331, 25.1333, 25.1337, 25.1351(a),(b)(6),(c),(d), 25.1353(a),(b),(c)(6),(d),(e), 25.1355, 25.1357, 25.1360, 25.1381, 25.1419(c), 25.1431, 25.1435(b)(1), 25.1459 SUBPART G – OPERATING LIMITATIONS AND OPERATIONS 25.1501, 25.1523, 25.1525, 25.1527, 25.1529, 25.1541, 25.1543, 25.1545, 25.1547, 25.1549, 25.1555, 25.1563, 25.1581, 25.1583, 25.1585, 25.1587 SUBPART H – ELECTRICAL WIRING INTERCONNECTION SYSTEMS 25.1701, 25.1703, 25.1705, 25.1707, 25.1709, 25.1711, 25.1713, 25.1715, 25.1717, 25.1719, 25.1721, 25.1729 FAA Special Condition 25-473-SC “Aircraft Electronic System Security Protection from Unauthorized External Access” FAA Special Condition 25-896-SC “Airplanes; Electronic System Security Protection from Unauthorized Internal Access” A53EU, Rev 38 32 of 34 The Direction Générale de l'Aviation Civile (DGAC) of France originally type certificated this aircraft under its type certificate Number 176. The FAA validated this product under U.S. Type Certificate Number A53EU. Effective September 28, 2003, the European Aviation Safety Agency (EASA) began oversight of this product on behalf of the Direction Générale de l'Aviation Civile (DGAC) of France. Based on 14 CFR § 21.29(a) for new import TCs, (or § 21.101(g) for changes to TCs), applicable provisions of 14 CFR part 26 are included in the certification basis. For any future 14 CFR part 26 amendments, the holder of this TC must demonstrate compliance with the applicable sections. Compliance with the requirements of FAR 25.856 at amendment 25-111 for thermal/acoustic insulation has been demonstrated to meet operational requirements. Certification Basis. (ATR72-212A Full Cargo Model “600 version” (ATR72-600F)) The final FAA type certification basis, for the ATR 72-212A “600 version” incorporating modification 7900 –full cargo conversion – (commercially called the ATR72-600F) is as follows: Airworthiness & Environmental Standards for components and areas not affected by the change: Unchanged from the basic ATR 72-212A certification basis. Airworthiness and Environmental Standards for components and areas affected by the change: 14 CFR part 25, effective February 1, 1965, including Amendments 25-1 through 25-144. The following sections are applicable: Equivalent Safety Finding: ESF IP C-1 - Freighter Embedded Crew Door installed on ATR72-212A (version 600F). (ELOS Memo AT10903IB-T-C-1) SUBPART B – Flight 25.25 SUBPART C – STRUCTURE 25.301, 25.303, 25.305 (a), (b), 25.307 (a) (for Equipment and furnishings), 25.365, 25.519, 25.561 Note: 25.305, 25.307 at Amendment 25-54 for Loads structure SUBPART D – DESIGN AND CONSTRUCTION 25.601, 25.603, 25.605, 25.607, 25.609, 25.613, 25.619, 25.621, 25.623, 25.625, 25.631, 25.777 (a), (c), 25.783 all except (b),(c), (g), (h), 25.803 (a), 25.807 (j), 25.851 ((a) except a(1)), 25.855 (a), (b)(1), (d,), (f), (h)(2), 25.857(e), 25.858, 25.869 (a)(1), 25.899 Note: 25.783 (c) at original Amendment 25-54 For rear door 25.855(e1),(e2) at Amendment 25-116 for Electrical & Electronic common installation SUBPART F - EQUIPMENT 25.1301(a)(1), (a)(2), (a)(3), (a)(4), 25.1302, 25.1309 (a), (b), (c) (for cargo lights, equipment and furnishing), 25.1317, 25.1351 (a)(1), (d)(1), (d)(3), 25.1353(a) (for EMH, Air Conditioning, Fire Protection, Cargo Light and Doors), 25.1357 (a), (b), (c), (d), (f), 25.1360, 25.1431 (a), (c), (d) Note: 25.1309 (a), (b), (d), (g) at original Amendment 25-54 for Air conditioning, doors, oxygen, wing light and landing gear 25.1353(a) at original amendment 25-54 for wing light) SUBPART G – OPERATING LIMITATIONS AND OPERATIONS 25.1519, 25.1529, 25.1541, 25.1557 (a), 25.1581, 25.1583, 25.1585 For ATR72-212A “600 version” and “600F version” airplanes incorporating modification MOD 7055 “High Altitude Airport Operations up to 11,000 ft” an Equivalent Level of Safety Finding in accordance with the provisions of 14 CFR 21.21(b)(1) for Section 25.841(d)(1): Pressurized Cabins (documented in ELOS memo AT20368IB-T-SE-101) has been made. 33 of 34 A53EU, Rev 38 Service Information. Each of the documents listed below that contain a statement 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) of France, are accepted by the FAA and are considered FAA approved. Additionally, approvals issued by ATR under the authority of EASA approved Design Organization EASA.21J.044 - or for approvals made before September 28, 2003 - under the authority of DGAC Design Organization Approval No. F.JA.12 are considered FAA approved. These approvals pertain to the type design only. • ATR Service Bulletins, except as noted below, • Structural repair manuals, • Vendor manuals referenced in ATR service bulletins • Aircraft flight manuals, • Repair Instructions. Note: Design changes that are contained in ATR Service Bulletins and that are classified as Level 1 Major or Non-Basic in accordance with either the US/France or US/EASA Bilateral Aviation Safety Agreement Implementation Procedures for Airworthiness must be approved by the FAA. Equipment. The basic required equipment as prescribed in the applicable Federal Aviation Regulations must be installed in the aircraft. ATR equipment list, document GATR/C No. 425.892/89 identifies all required equipment and all optional equipment approved by the Direction Générale de l'Aviation Civile (DGAC) of France. In addition, the following is required: (1) DGAC/EASA Approved FAA Airplane Flight Manual - 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) of France 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 conform with Type Design approved under U.S. Type Certificate No. A53EU and to be in a condition for safe operation. Compliance with Airworthiness Directives (ADs) has been checked only for ADs issued by EASA, ADs adopted by EASA and ADs published by FAA.’ 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. NOTE 1 - Weight and Balance (a) Current weight and balance report including list of equipment, entitled "Aircraft Inspection "Report", included in certificated empty weight, and loading instructions, must be in each aircraft at the time of original certification and at all times thereafter except in the case of operators having an approved weight control system. ATR Report, "Weight and Balance Manual", contains loading information for each airplane and interior arrangement configuration as delivered. This report contains, or refers to, information relative to location and capacity of all cargo and baggage compartments, buffets, storage spaces and coat rooms, location and capacity of lounges, lavatories, and the required placards in the passenger compartment. (b) The airplane must be loaded so that the C.G. is within specified limits at all times, considering fuel loading and usage, gear retraction and movement of crew and passengers from their assigned positions. (c) The weights of system fuel and oil, as defined below, and hydraulic fluid, all of which must be included in the airplane empty weight, are listed for each airplane in the Weight and Balance Manual specified in paragraph (a) above. (d) System fuel is the weight of all fuel required to fill all lines and tanks up to zero-fuel point on the fuel pages in the most critical flight attitude, including the unusable tank fuel as defined by FAR Part 25.959. (The usable fuel in the crossfeed manifold lines, manifolds, and engine that is not part of the system, fuel must be included in total usable fuel to obtain correct weight and C.G. for take off). A53EU, Rev 38 34 of 34 (e) The unusable fuel is that amount of fuel in the tanks which is unavailable to the engines under critical flight conditions as defined in FAR Part 25.959. This "unusable" fuel is included in System Fuel as indicated in (d) above and need not be accounted for separately. (f) System oil is the weight of oil remaining in the engine, lines and tanks after subtracting the oil in the tanks which is above the standpipe (zero gauge) levels. The engine oil capacities shown elsewhere in this data sheet include only the useable oil for which the tanks must be placarded. NOTE 2. The aircraft must be operated in accordance with the DGAC/EASA-Approved FAA Airplane Flight Manual. ("DGAC/EASA approved" is considered equivalent to "FAA Approved"). NOTE 3. The required Airworthiness limitations including structural inspections and retirements times for safe life parts are covered by the "Time Limits" document for ATR 72 models, approved by EASA. NOTE 4. Cabin Equipment Galleys and seats must be designed in accordance with ATR Specifications 419.464/82 and 419.282/82 (ATR72-101/-102, -201/-202, -211/-212 models) or 421.614/94 and 419.0008/95, issue 4 (ATR 72-212A model). NOTE 5. The modification permitting use of the ATR-72 for Category II approach is: 1112. NOTE 6. The basic definition for US import certification is contained in Documents: * GATR/C 422.174/89 for ATR72-101/-201 models * GATR/C 425.731/90 for ATR72-102/-202 models * GATR/C 425.839/92 for ATR72-211 model * GATR/C 425.840/92 for ATR72-212 model * A/RT/C 540.0410/97 for ATR72-212A model Initial issue or later approved revision. NOTE 7. Modification whose retrofit is mandatory. 1) Modification included in the type definition 2334 - Engine debris deflectors to be retrofitted before 10,000 flight hours on the following A/C: 108 - 126 - 140 - 145 - 147 - 150 - 154 - 157 - 162 - 164 - 167 - 171 - 174 - 177 - 180 - 183 - 186 - 189 - 192 - 195 - 198 - 201 - 204 -207 - 210 - 212 - 215 2) Modification 1931 or 8019 related to the center wing box must be embodied on A/C: 108 - 126 - 140 - 145 - 147 - 150 before 10000 flight hours. NOTE 8. For Interior arrangement limitations, see Aerospatiale Document GATR/C 425.776/89, Substantiation Report. NOTE 9. Operation on narrow runway is approved for ATR72-201/-202/-211/-212 and -212A with incorporation of modification 4406. .....END..... ``` ## ADs (248, first 50, in force first) - [AD 2026-16-07](https://openairdocs.org/ad/2026-16-07): Stabilizers · ATR – GIE Avions de Transport Régional ATR42-500 and ATR72-212A. Effective Sep 18, 2026 - [AD 2026-18-01](https://openairdocs.org/ad/2026-18-01): Time Limits/Maintenance Checks, Air Conditioning and Pressurization · ATR – GIE Avions de Transport Régional ATR42-500. Effective Sep 18, 2026 - [AD 2026-10-08](https://openairdocs.org/ad/2026-10-08): Time Limits/Maintenance Checks · ATR – GIE Avions de Transport Régional ATR42-500. Effective Jul 1, 2026 - [AD 2026-10-09](https://openairdocs.org/ad/2026-10-09): Time Limits/Maintenance Checks · ATR – GIE Avions de Transport Régional ATR72-101, ATR72-102, ATR72-201 and 4 more. Effective Jul 1, 2026 - [AD 2026-13-02](https://openairdocs.org/ad/2026-13-02): Navigation · Airbus Canada Limited Partnership 18, 49-46, 80-A and 555 more. Effective Jul 1, 2026 - [AD 2026-09-13](https://openairdocs.org/ad/2026-09-13): Flight controls · ATR – GIE Avions de Transport Régional ATR42-200, ATR42-300 and ATR42-320. Effective Jun 18, 2026 - [AD 2026-08-08](https://openairdocs.org/ad/2026-08-08): Time Limits/Maintenance Checks · ATR – GIE Avions de Transport Régional ATR72-101, ATR72-102, ATR72-201 and 4 more. Effective Jun 3, 2026 - [AD 2025-25-10](https://openairdocs.org/ad/2025-25-10): Time Limits/Maintenance Checks · ATR – GIE Avions de Transport Régional ATR42-500. Effective Feb 9, 2026 - [AD 2025-26-01](https://openairdocs.org/ad/2025-26-01): Time Limits/Maintenance Checks · ATR – GIE Avions de Transport Régional ATR42-200, ATR42-300 and ATR42-320. Effective Feb 9, 2026 - [AD 2025-23-04](https://openairdocs.org/ad/2025-23-04): Fire Protection · ATR – GIE Avions de Transport Régional ATR42-300, ATR42-320, ATR42-500 and 6 more. Effective Jan 13, 2026 - [AD 2025-24-09](https://openairdocs.org/ad/2025-24-09): Ice and rain protection · ATR – GIE Avions de Transport Régional ATR42-200, ATR42-300, ATR42-320 and 8 more. Effective Jan 13, 2026 - [AD 2025-20-01](https://openairdocs.org/ad/2025-20-01): Flight Controls · ATR – GIE Avions de Transport Régional ATR42-500, ATR72-101, ATR72-102 and 5 more. Effective Nov 6, 2025 - [AD 2025-17-09](https://openairdocs.org/ad/2025-17-09): Time Limits/Maintenance Checks · ATR – GIE Avions de Transport Régional ATR72-101, ATR72-102, ATR72-201 and 4 more. Effective Sep 29, 2025 - [AD 2025-17-15](https://openairdocs.org/ad/2025-17-15): Hydraulic Power · ATR – GIE Avions de Transport Régional ATR42-500 and ATR72-212A. Effective Sep 11, 2025 - [AD 2025-10-08](https://openairdocs.org/ad/2025-10-08): Stabilizers · ATR – GIE Avions de Transport Régional ATR42-500 and ATR72-212A. Effective Jul 2, 2025 - [AD 2025-12-02](https://openairdocs.org/ad/2025-12-02): Equipment/furnishings · Ipeco Holdings 3A063-0100-( )-( ), 3A063-0080-( )-( ), 3A063-0038-( )-( ) and 18 more. Effective Jun 30, 2025 - [AD 2025-10-06](https://openairdocs.org/ad/2025-10-06): Time Limits/Maintenance Checks · ATR – GIE Avions de Transport Régional ATR42-200, ATR42-300 and ATR42-320. Effective Jun 26, 2025 - [AD 2025-06-11](https://openairdocs.org/ad/2025-06-11): Stabilizers · ATR – GIE Avions de Transport Régional ATR42-500 and ATR72-212A. Effective May 2, 2025 - [AD 2025-05-11](https://openairdocs.org/ad/2025-05-11): Fire protection · ATR – GIE Avions de Transport Régional ATR42-200, ATR42-300, ATR42-320 and 8 more. Effective Apr 22, 2025 - [AD 2025-04-04](https://openairdocs.org/ad/2025-04-04): Landing gear · ATR – GIE Avions de Transport Régional ATR72-101, ATR72-102, ATR72-201 and 4 more. Effective Apr 4, 2025 - [AD 2025-04-06](https://openairdocs.org/ad/2025-04-06): Flight controls · ATR – GIE Avions de Transport Régional ATR42-200, ATR42-300, ATR42-320 and 8 more. Effective Apr 4, 2025 - [AD 2025-02-10](https://openairdocs.org/ad/2025-02-10): Doors · ATR – GIE Avions de Transport Régional ATR42-200, ATR42-300, ATR42-320 and 8 more. Effective Mar 19, 2025 - [AD 2024-23-10](https://openairdocs.org/ad/2024-23-10): Placards and Marking · Decompression Panel (Aeroconseil STC ST04602NY). Effective Jan 13, 2025 - [AD 2024-24-06](https://openairdocs.org/ad/2024-24-06): Time Limits/Maintenance Checks · ATR – GIE Avions de Transport Régional ATR72-101, ATR72-102, ATR72-201 and 4 more. Effective Jan 13, 2025 - [AD 2024-19-15](https://openairdocs.org/ad/2024-19-15): Oxygen · Safran Aerosystems Oxygen Cylinder, Valve Assembly, Oxygen Valve and 103 more. Effective Nov 26, 2024 - [AD 2024-19-02](https://openairdocs.org/ad/2024-19-02): Time Limits/Maintenance Checks · ATR – GIE Avions de Transport Régional ATR42-500. Effective Nov 15, 2024 - [AD 2024-15-14](https://openairdocs.org/ad/2024-15-14): Instruments · ATR – GIE Avions de Transport Régional ATR42-200, ATR42-300 and ATR42-320. Effective Oct 23, 2024 - [AD 2024-08-02](https://openairdocs.org/ad/2024-08-02): Electrical power · ATR – GIE Avions de Transport Régional ATR42-200, ATR42-300, ATR42-320 and 8 more. Effective Jun 6, 2024 - [AD 2024-09-03](https://openairdocs.org/ad/2024-09-03): Flight Controls · ATR – GIE Avions de Transport Régional ATR72-101, ATR72-102, ATR72-201 and 4 more. Effective Jun 6, 2024 - [AD 2024-05-05](https://openairdocs.org/ad/2024-05-05): Fire Protection · ATR – GIE Avions de Transport Régional ATR42-200, ATR42-300, ATR42-320 and 8 more. Effective Mar 29, 2024 - [AD 2023-19-07](https://openairdocs.org/ad/2023-19-07): Electrical Power · ATR - GIE Avions de Transport Régional ATR42-500, ATR72-101, ATR72-102 and 5 more. Effective Nov 9, 2023 - [AD 2023-17-01](https://openairdocs.org/ad/2023-17-01): Landing gear · ATR - GIE Avions de Transport Régional ATR42-200, ATR42-300, ATR42-320 and 8 more. Effective Oct 19, 2023 - [AD 2023-14-10](https://openairdocs.org/ad/2023-14-10): Flight Compartment Equipment · Ipeco Holdings Pilot and Co-Pilot seats, ATR42-200, ATR42-300 and 9 more. Effective Sep 7, 2023 - [AD 2023-10-02](https://openairdocs.org/ad/2023-10-02): Indicating/Recording System, Navigation · Boeing 18, 23, 35 and 1,060 more. Effective May 26, 2023 - [AD 2023-06-01](https://openairdocs.org/ad/2023-06-01): Instruments · ATR - GIE Avions de Transport Régional ATR42-500 and ATR72-212A. Effective May 18, 2023 - [AD 2022-15-08](https://openairdocs.org/ad/2022-15-08): Information systems · Airbus A318-111, A318-112, A319-111 and 49 more. Effective Aug 12, 2022 - [AD 2021-24-07](https://openairdocs.org/ad/2021-24-07): Fire protection · ATR - GIE Avions de Transport Régional ATR42-200, ATR42-300, ATR42-320 and 8 more. Effective Nov 22, 2021 - [AD 2021-22-07](https://openairdocs.org/ad/2021-22-07): Fire Bottle, Portable · Airbus A319-111, A319-112, A319-113 and 127 more. Effective Nov 18, 2021 - [AD 2021-19-13](https://openairdocs.org/ad/2021-19-13): Navigation · ATR - GIE Avions de Transport Régional ATR42-500 and ATR72-212A. Effective Nov 9, 2021 - [AD 2021-12-17](https://openairdocs.org/ad/2021-12-17): Fuselage · ATR - GIE Avions de Transport Régional ATR42-300, ATR42-320, ATR42-500 and 7 more. Effective Aug 4, 2021 - [AD 2021-09-18](https://openairdocs.org/ad/2021-09-18): Electrical Routing · ATR - GIE Avions de Transport Régional ATR72-212A. Effective Jul 1, 2021 - [AD 2021-07-04](https://openairdocs.org/ad/2021-07-04): Ice and Rain Protection. · ATR - GIE Avions de Transport Régional ATR42-200, ATR42-300, ATR42-320 and 8 more. Effective May 10, 2021 - [AD 2020-26-17](https://openairdocs.org/ad/2020-26-17): Instruments · ATR - GIE Avions de Transport Régional ATR42-500, ATR72-101, ATR72-102 and 5 more. Effective Jan 4, 2021 - [AD 2020-21-14](https://openairdocs.org/ad/2020-21-14): Landing gear · ATR - GIE Avions de Transport Régional ATR72-101, ATR72-102, ATR72-201 and 4 more. Effective Nov 20, 2020 - [AD 2020-07-19](https://openairdocs.org/ad/2020-07-19): Electrical routing · ATR - GIE Avions de Transport Régional ATR72-101, ATR72-102, ATR72-201 and 4 more. Effective May 26, 2020 - [AD 2020-07-11](https://openairdocs.org/ad/2020-07-11): Hydraulic power and Electronic common installation · ATR - GIE Avions de Transport Régional ATR42-200, ATR42-300, ATR42-320 and 8 more. Effective May 18, 2020 - [AD 2020-07-12](https://openairdocs.org/ad/2020-07-12): Flight controls · ATR - GIE Avions de Transport Régional ATR42-500. Effective May 18, 2020 - [AD 2019-20-11](https://openairdocs.org/ad/2019-20-11): Landing gear · ATR - GIE Avions de Transport Régional ATR72-101, ATR72-102, ATR72-201 and 4 more. Effective Nov 15, 2019 - [AD 2019-07-03](https://openairdocs.org/ad/2019-07-03): Cabin Equipment/Furnishings · ATR - GIE Avions de Transport Régional ATR42-200, ATR42-300, ATR42-320 and 8 more. Effective May 16, 2019 - [AD 2018-25-18](https://openairdocs.org/ad/2018-25-18): Landing gear · ATR - GIE Avions de Transport Régional ATR42-200, ATR42-300, ATR42-320 and 8 more. Effective Jan 22, 2019 All 248: https://openairdocs.org/tcds/A53EU/ads.md ## Registered aircraft by registry model (OpenAirDocs) - [Atr-Gie Avions De Trnsp Rgnl ATR 72-212A](https://openairdocs.org/model/atr-gie-avions-de-trnsp-rgnl-atr-72-212a): 14 aircraft (registry code 8680905) - [Aerospatiale/Aeritalia ATR 42-300](https://openairdocs.org/model/aerospatiale-aeritalia-atr-42-300): 12 aircraft (registry code 8680920) - [Aerospatiale ATR 72-212](https://openairdocs.org/model/aerospatiale-atr-72-212): 9 aircraft (registry code 8680945) - [Atr-Gie Avions De Trnsp Region ATR42-500](https://openairdocs.org/model/atr-gie-avions-de-trnsp-region-atr42-500): 6 aircraft (registry code 8681050) - [Aerospatiale/Aeritalia ATR 42-320](https://openairdocs.org/model/aerospatiale-aeritalia-atr-42-320): 4 aircraft (registry code 8680930) - [Aerospatiale/Alenia ATR-72-212](https://openairdocs.org/model/aerospatiale-alenia-atr-72-212): 3 aircraft (registry code 8680946) - [ATR ATR72-212A](https://openairdocs.org/model/atr-atr72-212a): 3 aircraft (registry code 8681911) - [Aerospatiale/Alenia ATR 42-320](https://openairdocs.org/model/aerospatiale-alenia-atr-42-320): 2 aircraft (registry code 8680947) - [Aerospatiale/Atr ATR 72 202](https://openairdocs.org/model/aerospatiale-atr-atr-72-202): 2 aircraft (registry code 8680940) - [Aerospatiale/Aeritalia ATR72-212](https://openairdocs.org/model/aerospatiale-aeritalia-atr72-212): 1 aircraft (registry code 868094B) - [Aerospatiale/Alenia ATR42-500](https://openairdocs.org/model/aerospatiale-alenia-atr42-500): 1 aircraft (registry code 868094E) - [Atr-Gie Avions De Transport ATR-42-320](https://openairdocs.org/model/atr-gie-avions-de-transport-atr-42-320): 1 aircraft (registry code 8680938) - [Atr-Gie Avions De Trnsp Rgnl ATR 42-300](https://openairdocs.org/model/atr-gie-avions-de-trnsp-rgnl-atr-42-300): 1 aircraft (registry code 8680939) - [Eads/Alenia ATR ATR 42-500](https://openairdocs.org/model/eads-alenia-atr-atr-42-500): 1 aircraft (registry code 868094C) - [Aerospatiale ATR 42-200](https://openairdocs.org/model/aerospatiale-atr-42-200): 0 aircraft (registry code 8680910) - [Aerospatiale ATR 72-101](https://openairdocs.org/model/aerospatiale-atr-72-101): 0 aircraft (registry code 8680901) - [Aerospatiale ATR 72-212A](https://openairdocs.org/model/aerospatiale-atr-72-212a): 0 aircraft (registry code 8680902) - [Aerospatiale ATR-72-201](https://openairdocs.org/model/aerospatiale-atr-72-201): 0 aircraft (registry code 8680943) - [Aerospatiale ATR42-500](https://openairdocs.org/model/aerospatiale-atr42-500): 0 aircraft (registry code 8680948) - [Aerospatiale/Aeritalia ATR 42-500](https://openairdocs.org/model/aerospatiale-aeritalia-atr-42-500): 0 aircraft (registry code 868094A) - [Aerospatiale/Alenia ATR 72-212A](https://openairdocs.org/model/aerospatiale-alenia-atr-72-212a): 0 aircraft (registry code 8680953) - [Aerospatiale/Alenia ATR-42/300](https://openairdocs.org/model/aerospatiale-alenia-atr-42-300): 0 aircraft (registry code 8680921) - [ATR - Gie Avions De Trnspt Reg ATR72-212](https://openairdocs.org/model/atr-gie-avions-de-trnspt-reg-atr72-212): 0 aircraft (registry code 8681910) - [Atr-Gie Avions De Transport ATR 72-202](https://openairdocs.org/model/atr-gie-avions-de-transport-atr-72-202): 0 aircraft (registry code 868094D) - [Atr-Gie Avions De Transport ATR-72-201](https://openairdocs.org/model/atr-gie-avions-de-transport-atr-72-201): 0 aircraft (registry code 8681903) ## STCs approved under this data sheet (138, first 50) - [STC ST01305WI-D](https://openairdocs.org/stc/ST01305WI-D): Modification of a Collins ALT-50A or ALT-55B Radio Altimeter system installation to a Collins ALT-1000 or ALT-4000 Radio Altimeter system installation in accordance with Collins Drawing Index as listed on AML No. ST01305WI-D, Revision -, or later FAA approved revision.. Rockwell Collins Inc - [STC ST12466CH](https://openairdocs.org/stc/ST12466CH): Installation of Seat Blocker Interior Reconfiguration. STS Engineering Solutions, LLC - [STC ST01761NY](https://openairdocs.org/stc/ST01761NY): Conversion of an ATR-420/300/320 passenger configuration into a full Class E cargo configuration, including a new lining, smoke detection system, large cargo door with an embedded crew door, and provisions for the transportation of bulk weight and standard unit load devices.. PMV Engineering - [STC ST12461IB](https://openairdocs.org/stc/ST12461IB): Installation of Cockpit Voice Recorder with optional RIPS Upgrade. Mid- Canada Mod Center - [STC ST00197IB](https://openairdocs.org/stc/ST00197IB): Installation of the Universal Quick Access Recorder (uQAR). Flight Data Technologies Inc. - [STC ST00952LA](https://openairdocs.org/stc/ST00952LA): Installation of Mass Systems fire extinguisher cartridges as replacements for Kidde fire extinguisher cartridges in fire extinguisher bottles.. AMETEK AMERON LLC d/b/a MASS Systems - [STC ST12365IB](https://openairdocs.org/stc/ST12365IB): Installation of ERT/CNG/1579 Fuselage Protection for Unpaved Runway for Belly Fuselage Skin Panels. EIRTECH AVIATION SERVICES LIMITED - [STC ST04328NY](https://openairdocs.org/stc/ST04328NY): The Manufacture and Installation of Exterior Placards, Labels and Signs is to be performed, installed. Libellule Monde Inc - [STC ST03875NY](https://openairdocs.org/stc/ST03875NY): Installation of interior placards, signs and markings. Libellule Monde Inc. - [STC SA2622NM](https://openairdocs.org/stc/SA2622NM): Installation of Precise Flight Pulselite Control Unit in landing/taxi system. (767-200 B17) (DHC-8 101). Precise Flight Inc. - [STC ST03428CH](https://openairdocs.org/stc/ST03428CH): Installation of printed advertising onto cabin interior surfaces. Atin OOH LLC - [STC ST12220IB](https://openairdocs.org/stc/ST12220IB): Installation of Starlink Aviation In-Flight Entertainment System. PMV Engineering - [STC ST00892LA](https://openairdocs.org/stc/ST00892LA): Installation of Emergency Vision Assurance System (EVAS).. VisionSafe LLC - [STC ST00030IB](https://openairdocs.org/stc/ST00030IB): Installation of Test Tech ELT. APTOZ EHF - [STC ST12198IB](https://openairdocs.org/stc/ST12198IB): Replacement of the Right Hand Side Cabin Emergency Exit Door by a Reinforced Structural Plug. PMV Engineering - [STC ST03885AT](https://openairdocs.org/stc/ST03885AT): Installation of an Avionica, Inc. avCM Cellular Module. Aircraft Systems and Manufacturing Inc. - [STC ST12152IB](https://openairdocs.org/stc/ST12152IB): Installation of Side Rails Extension from Frame 35 to Frame 36. PMV ENGINEERING - [STC ST12067AT](https://openairdocs.org/stc/ST12067AT): Installation of USCS Door Sill Protectors P/N 70042-101 and 70042-102. Telair US LLC - [STC ST12056IB](https://openairdocs.org/stc/ST12056IB): The Manufacture and Installation of External Printed Aircraft Graphics Film. Libellule Monde Inc. - [STC ST03166AT](https://openairdocs.org/stc/ST03166AT): Installation of L3 Communications Micro Quick Access Recorder (uQAR) models QAR100, 200 or 201.. Acron Aviation Inc. - [STC ST02472AT](https://openairdocs.org/stc/ST02472AT): Installation of a mini Quick Access Recorder (QAR) model MKI, MKII, or MKIII. Aircraft Systems and Manufacturing Inc. - [STC ST04486NY](https://openairdocs.org/stc/ST04486NY): Installation of the Dual SFIM F227 APIRS. Mid Canada Mod Center - [STC ST01189WI](https://openairdocs.org/stc/ST01189WI): Passenger to all cargo conversion.. IPR M7 CONVERSIONS (USA) LIMITED c/o Vistra International - [STC ST03930AT](https://openairdocs.org/stc/ST03930AT): Installation of a Lead Acid Battery as a replacement for the existing Nickel-Cadmium Battery in accordance with Concorde Master Drawing List (MDL) 5-0372, Rev. C, Dated June 20, 2011 or later FAA approved revision.. Concorde Battery Corporation - [STC ST00079IB](https://openairdocs.org/stc/ST00079IB): Integration of Halon-free Portable Fire Extinguisher HAFEX. UMLAUT ENGINEERING GMBH - [STC ST03042CH](https://openairdocs.org/stc/ST03042CH): Installation of a Global AirWorks Cockpit Door Surveillance System. Aero Technik Inc. - [STC ST02020WI](https://openairdocs.org/stc/ST02020WI): Reduce maximum zero fuel weight to restrict maximum payload to 7500 lbs. Worldwide Aircraft Services Inc. - [STC ST00215IB](https://openairdocs.org/stc/ST00215IB): Installation of saf-Tglo ECO Photoluminescent Aisle Path Marking Systems. STG AEROSPACE GERMANY GmbH - [STC ST00192IB](https://openairdocs.org/stc/ST00192IB): Installation of Automatic Dependent Surveillance – Broadcast (ADS-B) Out System and Single UNS-1Lw Flight Management System including Localizer Performance with Vertical Guidance (LPV) Monitor. 365 AEROSPACE DDS LIMITED - [STC ST02529AT](https://openairdocs.org/stc/ST02529AT): Installation of photoluminescent floor proximity emergency escape path marking system (FPEEPMS).. STG Aerospace Inc. - [STC ST04562NY](https://openairdocs.org/stc/ST04562NY): Installation of saf-Tglo® SuperSeal UltraLite-X (SSUL-X) Photoluminescent Floor Proximity Emergency Escape Path Marking Systems. STG AEROSPACE GERMANY GmbH - [STC ST03238NY](https://openairdocs.org/stc/ST03238NY): The installation of a single HF-9000 Communication Transceiver System. Roeder Praezision GMBH - [STC ST00098IB](https://openairdocs.org/stc/ST00098IB): Introduction of ADS-B Out. STC Twenty One Limited - [STC ST00095IB](https://openairdocs.org/stc/ST00095IB): Conversion of Passenger to Freighter Configuration. Aerodisa S.L. - [STC ST01925CH](https://openairdocs.org/stc/ST01925CH): Installation of a Honeywell RESCU 406AF Emergency Locator Transmitter (ELT) System.. Honeywell International Inc. - [STC ST03912AT](https://openairdocs.org/stc/ST03912AT): Installation of a T2CAS System into an ATR42/72 Series Aircraft and associated hardware. Woven Electronics LLC - [STC ST00043IB](https://openairdocs.org/stc/ST00043IB): Installation of ADSB OUT. Aeroconseil - [STC ST04532AT](https://openairdocs.org/stc/ST04532AT): Installation of a Bulk Cargo Loading System, P/N 72150-101, or a Bulk Cargo Loading System Foldout Section, P/N 72729-102. Telair US LLC - [STC SA9077SC-D](https://openairdocs.org/stc/SA9077SC-D): Recore of Normalair-Garrett heat exchanger part number 8534C000.. Honeywell International Inc. - [STC SA8860SW](https://openairdocs.org/stc/SA8860SW): Replace core assembly of AiResearch Primary/Secondary Air-to-Air Heat Exchangers, part numbers 194776-1, SR1; 194776-2, SR1; and 194776-2, SR2. Honeywell International Inc. - [STC ST02757LA](https://openairdocs.org/stc/ST02757LA): Installation of main deck cargo loading system. Ancra International LLC - [STC ST00016IB](https://openairdocs.org/stc/ST00016IB): Installation of Bulk Freighter Conversion (BFC). PMV Engineering - [STC ST04177AT](https://openairdocs.org/stc/ST04177AT): Installation of a Talon Aerospace LED Replacement General Purpose Lamps. Aaxico Technical Services Inc. - [STC ST04608NY](https://openairdocs.org/stc/ST04608NY): Installation of the Rockwell Collins TDR-94D Transponder Upgrade. Mid Canada Mod Center - [STC ST04602NY](https://openairdocs.org/stc/ST04602NY): Installation of Decompression Panel for Bulk Freighter Conversion. Aeroconseil - [STC SA01452CH](https://openairdocs.org/stc/SA01452CH): Installation of an air ambulance conversion kit.. Med-Pac Inc. - [STC ST04372NY](https://openairdocs.org/stc/ST04372NY): Installation of saf-Tglo® SSUL23 Photoluminescent Aisle Path Marking System. STG Aerospace Ltd - [STC ST02480LA](https://openairdocs.org/stc/ST02480LA): Installation of main deck cargo loading system. Ancra International LLC - [STC ST04340NY](https://openairdocs.org/stc/ST04340NY): Installation of TCAS 7.1 (ACAS II) upgrade of Prior Existing TCAS 7.0. Scandinavian Avionics Design ApS - [STC ST04443AT](https://openairdocs.org/stc/ST04443AT): Replacement of the HT1000 MCDU (Multi-Function Control Display Unit) with the HT9100 MCDU. Chippewa Aerospace Inc All 138: https://openairdocs.org/tcds/A53EU/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.