# TCDS T00011AT: Embraer S.A. - Type: Type certificate data sheet - Status: Current - Holder: Embraer S.A. - Revision: 38 - Revised: January 21, 2022 - Product: Aircraft, Large Airplane - Certification basis: Part 21, Part 25 - Registered aircraft: 432, by the registry models matched to it (OpenAirDocs) - Data sheet PDF: https://openairdocs.org/files/sha256/15/ec/15ec7a1450419af7d67883828b20689185a704349a3f43232f578ef37f9fead9 - FAA DRS: https://drs.faa.gov/browse/excelExternalWindow/E44EA5DBB7CB644C862587D4004E7A3F.0001 - Page: https://openairdocs.org/tcds/T00011AT ## Models (14) As the data sheet lists them. - EMB-145 - EMB-145XR - EMB-135ER - EMB-135LR - EMB-145EP - EMB-145MP - EMB-145ER - EMB-135BJ (Legacy 600) (Legacy) - EMB-145LR - EMB-135KE - EMB-145MR - EMB-135BJ (Legacy 650) - EMB-135KL - EMB-135 (Embraer - Empresa Brasileira de Aeronautica S.A.) ## What the data sheet says From the PDF's text layer, line by line; tables lose their columns. The PDF is the record. ```text Page. No. 1 2 3 4 5 6 7 8 9 10 11 12 13 14 15 16 17 18 19 20 21 22 23 24 25 26 27 28 29 30 31 32 33 34 35 Rev. No. 38 30 30 30 30 30 30 30 30 30 30 30 30 30 30 30 30 30 30 30 30 30 30 30 30 30 30 34 34 33 33 30 30 30 33 Page. No 36 37 38 39 40 41 Rev. No 30 37 30 37 30 31 DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION T00011AT Revision 38 Embraer EMB-145 EMB-145ER EMB-145MR EMB-145LR EMB-135ER EMB-135LR EMB-135KE EMB-135KL EMB-135BJ EMB-145XR EMB-145MP EMB-145EP January 21, 2022 TYPE CERTIFICATE DATA SHEET NO. T00011AT This data sheet which is part of Type Certificate Number, T00011AT, 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 Embraer S.A. Av. Brigadeiro Faria Lima, 2170 12227-901 - São José dos Campos - SP Brazil Type Certificate Holder Record Yaborã Indústria Aeronáutica S.A. transferred the TC No. T00011AT to Embraer S.A. on January 21, 2022. Embraer S. A. Transferred TC No. T00011AT to Yaborã Indústria Aeronáutica S.A. on January 31, 2020 Empresa Brasileira de Aeronáutica S.A. (Embraer) changed company name to Embraer S.A. effective January 2011. 1. - Model EMB-145, (Transport Category), approved December 10, 1996 Engine Two – Rolls Royce Corporation (See Note 16.) Model AE 3007A Fuel Brazilian Specification CNP-08/QAV1. ASTM Specification D-1655 JET A or JET A1 MIL-T-83133A JP-8. APU Sundstrand Aerospace Model T-62T-40C11 or T-62T-40C14 Limitations as stated in Sundstrand Doc. No. ESR 0921 and No. ESR 1112 Oil Engine Synthetic Oil conforming to MIL-L-23699 or MIL-L-7808 (below -40°F) APU MIL-L-23699 or MIL-L-7808 Revision 38 Page 2 of 40 T00011AT Engine Model AE3007A Limits Operating Conditions Static Thrust (lb.) Rotor Speed (%) Temperature Interturbine (°C) -1000ft SL N1 N2 ITT Takeoff 7,593 7,457 100(2) 102.5(N23) 921(1) (1690° F) Maximum Continuous 6,851 6,725 100 102.5 868 (1600° F) Ground 53.6 (min), 102.5 (max) Starting 800 (1472° F) (1) Time limited to 5 minutes. (2) 100 % N1 =8,700 rpm (3) 102.5 % N2 = 16,270 rpm Oil Temperature Maximum: 126°C (260°F) Normal oil temperature range: 21°C to 126°C (70 at 260°F) Minimum temperature for starting: above -40°C (-40°F) for lubrication oil specified by MIL-L-23699 above -54°C (-65°F) for lubrication oil specified by MIL-L-7808 Minimum to increase N2 above 83%: 40ºC (104°F) Oil Pressure Maximum: 95 psig - This limit may be exceeded during starts if oil temperature is below 21°C. For takeoff and go-around the maximum limit is 115 psi, limited to 5 minutes. For aircraft which have complied with SBAE30071-79-025 or equivalent, the maximum limit for takeoff and go around is 155 PSI, limited to 2 minutes. Minimum: 48 psig (N2 equal or above 88%) 34 psig (N2 below 88%) APU Limits (both models) Maximum RPM: 108% Maximum EGT: Steady State (Time limited to 5 minutes) 1323°F (717º C) Running (Normal) 1256°F (680° C) Airspeed Limits (EAS) Maximum Operating Limit Speed VMO: - 0 to 8,000 ft: 250 KEAS - 10,000 to 26,300 ft: 320 KEAS - 26,300 to 37,000 ft: 0.78 Mach - (Linear variation from 8,000 to 10,000 ft.) Maneuvering speed (VA): 200 KEAS Maximum flap extended speed (VFE): − Flaps 9° (Takeoff/Approach): 250 KEAS − Flaps 22°: 200 KEAS − Flaps 45° (Landing) : 145 KEAS Maximum landing gear extended speed (VLE): 250 KEAS Maximum landing gear operating speed (VLO): -VLO for retraction 200 KEAS -VLO for extension 250 KEAS Revision 38 Page 3 of 40 T00011AT C.G Limits (landing gear extended) 592.4 to 623.3 inches (15.6% to 43% MAC) with 42,549 lbs. (19,300 kg). 592.4 to 623.3 inches (15.6% to 43% MAC) with 42,328 lbs. (19,200 kg). 588.3 to 623.3 inches (12% to 43% MAC) with 34,171 lbs. (15,500 kg). 588.3 to 623.3 inches (12% to 43% MAC) with 28,660 lbs. (13,000 kg). 619.9 inches (40% MAC) with 26,455 lbs. (12,000 kg). Straight linear variation between the points given. Moment due to landing gear retraction - 10,155 in-lbs. (-117 kgf-m) (the aircraft C.G. is moved forward with the retraction). Maximum Weights Ramp 42,549 lbs. (19,300 kgf) Takeoff 42,328 lbs. (19,200 kgf) Landing 41,226 lbs. (18,700 kgf) Zero fuel 37,698 lb (17,100 kgf) Maximum Baggage 2,646 lb (1,200 kg) Fuel Capacity 1373.8 gallons (two tanks, 686.9 gallons each at +603.6 inches). Unusable fuel of 14.3 gallons (7.15 gallons for each tank). Serial Numbers Eligible 145004 and subsequent. A Brazilian Certificate of Airworthiness for Export endorsed as noted under “Import Requirements” must be submitted for each individual aircraft for which application for U.S. certification is made. 2. - Model EMB-145ER, (Transport Category), Approved December 10, 1996 Engine Two – Rolls Royce Corporation (See Note 16.) Model AE 3007A, AE3007A1/1, AE3007A1/2, AE3007A1, or Model AE3007A1P (See Note 12 for engine intermix operation.) Fuel Brazilian Specification CNP-08/QAV1. ASTM Specification D-1655 JET A or JET A1 MIL-T-83133A JP-8. APU Sundstrand Aerospace Model T-62T-40C11 or T-62T-40C14 Limitations as stated in Sundstrand Doc. No. ESR 0921 and No. ESR 1112 Oil Engine: MIL-L-7808 or MIL-L-23699 APU: MIL-L-23699 or MIL-L-7808 Engine Models AE3007A and AE3007A1/1 Limits Operating Conditions Static Thrust (lb.) Rotor Speed (%) Temperature Interturbine (°C) -1000ft N1 N2 ITT Takeoff 7,580 100(2) 102.5(3) 921(1) (1690° F) Maximum Continuous 6,820 100 102.5 868 (1600° F) Ground 53.6 (min), 102.5 (max) Starting 800 (1472° F) (1) Time limited to 5 minutes. (2) 100 % N1 =8,700 rpm (3) 102.5 % N2 = 16,270 rpm Revision 38 Page 4 of 40 T00011AT Engine Models AE3007A1/2 and AE3007A1 Limits Operating Conditions Static Thrust (lb.) Rotor Speed (%) Temperature Interturbine (°C) -1000ft N1 N2 ITT Takeoff 7,580 100(2) 102.5(3) 948(1) (1738° F) Maximum Continuous 6,820 100 102.5 901 (1653° F) Ground 53.6 (min), 102.5 (max) Starting 800 (1472° F) (1) Time limited to 5 minutes. (2) 100% N1 = 8,700 rpm (3) 102.5 % N2 =16,270 rpm Engine Model AE3007A1P Limits Operating Conditions Static Thrust (lb.) Rotor Speed (%) Temperature Interturbine (°C) -1000ft SL N1 N2 ITT Takeoff 8,338 8,195 100(2) 102.5(3) 948(1) (1738° F) Maximum Continuous 6,852 6,759 100 102.5(3) 901 (1653° F) Ground 53.6 (min), 102.5 (max) Starting 800 (1472° F) (1) Time limited to 5 minutes. (2) 100 % N1 =8,700 rpm (3) 102.5 % N2 = 16,270 rpm Oil Temperature Maximum: 126°C (260°F) Normal oil temperature range: 21°C to 126°C (70 at 260°F) Minimum temperature for starting: above -40°C (-40°F) for lubrication oil specified by MIL-L-23699 above -54°C (-65°F) for lubrication oil specified by MIL-L-7808 Minimum to increase N2 above 83%: 40ºC (104°F) Oil Pressure Maximum: 95 psig (This limit may be exceeded during starts if oil temperature is below 21°C (70oF)) (for Airplanes with engine FADEC software previous to version B7.6 installed). 110 psig (This limit may be exceeded during starts if oil temperature is below 21oC (70oF)) (for Airplanes with engine FADEC software version B7.6 or later approved version installed). For takeoff and go-around the maximum limit is 115 psi, limited to 5 minutes. For aircraft which have complied with SBAE 30071-79-025 or equivalent, the maximum limit for takeoff and go around is 155 PSI, limited to 2 minutes. Minimum: 48 psig (N2 equal or above 88%) 34 psig (N2 below 88%) APU Limits (both models) Maximum RPM: 108% Maximum EGT: Steady State (Time limited to 5 minutes) 1323°F (717º C) Running (Normal) 1256°F (680° C) Airspeed Limits (EAS) Maximum Operating Limit Speed VMO: - 0 to 8,000 ft: 250 KEAS - 10,000 to 26,300 ft: 320 KEAS - 26,300 to 37,000 ft: 0.78 Mach - (Linear variation from 8,000 to 10,000 ft.) Revision 38 Page 5 of 40 T00011AT Maneuvering speed (VA): 200 KEAS Maximum flap extended speed (VFE): − Flaps 9° (Takeoff/Approach): 250 KEAS − Flaps 18° ( Takeoff) 200 KEAS (See Note 15) − Flaps 22°: 200 KEAS − Flaps 45° (Landing) : 145 KEAS Maximum landing gear extended speed (VLE): 250 KEAS Maximum landing gear operating speed (VLO): -VLO for retraction 200 KEAS -VLO for extension 250 KEAS C. G. Limits (landing gear extended) 594.0 to 623.3 inches (17% to 43% MAC) with 45,635 lbs. (20,700 kg). 594.0 to 623.3 inches (17% to 43% MAC) with 45,414 lbs. (20,600 kg). 588.3 to 623.3 inches (12% to 43% MAC) with 34,171 lbs. (15,500 kg). 588.3 to 623.3 inches (12% to 43% MAC) with 28,660 lbs. (13,000 kg). 619.9 inches (40% MAC) with 26,455 lbs. (12,000 kg). Straight linear variation between the points given. Moment due to landing gear retraction - 10,155 in-lbs. (-117 kgf-m) (the aircraft C.G. is moved forward with the retraction). Maximum Weights Ramp 45,635 lbs. (20,700 kgf) Takeoff 45,414 lbs. (20,600 kgf) Landing 41,226 lbs. (18,700 kgf) Zero fuel 37,698 lbs. (17,100 kgf) Maximum Baggage 2,646 lbs. (1,200 kg) Fuel Capacity 1373.8 gallons (two tanks, 686.9 gallons each at +603.6 inches). Unusable fuel of 14.3 gallons (7.15 gallons for each tank). Serial Numbers Eligible 145004 and subsequent. A Brazilian Certificate of Airworthiness for Export endorsed as noted under “Import Requirements” must be submitted for each individual aircraft which application for U.S. certification is made. 3. - Model EMB-145MR, (Transport Category), Approved May 7, 1998 Engine Two – Rolls Royce Corporation (See Note 16.) Model AE 3007A1/1, AE 3007A1/2, AE3007A1 or AE3007A1P Fuel Brazilian Specification CNP-08/QAV1. ASTM Specification D-1655 JET A or JET A1 MIL-T-83133A JP-8. APU Sundstrand Aerospace Model T-62T-40C11 or T-62T-40C14 Limitations as stated in Sundstrand Doc. No. ESR 0921 and No. ESR 1112 Oil Engine: MIL-L-7808 or MIL-L-23699 APU: MIL-L-23699 or MIL-L-7808 Revision 38 Page 6 of 40 T00011AT Engine Model AE3007A1/1 Limits Operating Conditions Static Thrust (lb.) Rotor Speed (%) Temperature Interturbine (°C) -1000ft N1 N2 ITT Takeoff 7,580 100(2) 102.5(3) 921(1) (1690° F) Maximum Continuous 6,820 100 102.5 868 (1605° F) Ground 53.6 (min), 102.5 (max) Starting 800 (1472° F) (1) Time limited to 5 minutes. (2) 100 % N1 =8,700 rpm (3) 102.5 % N2 = 16,270 rpm Engine Models AE3007A1/2 and AE3007A1 Limits Operating Conditions Static Thrust (lb.) Rotor Speed (%) Temperature Interturbine (°C) -1000ft N1 N2 ITT Takeoff 7,580 100(2) 102.5(3) 948(1) (1738° F) Maximum Continuous 6,820 100 102.5 901 (1653° F) Ground 53.6 (min), 102.5 (max) Starting 800 (1472° F) (1) Time limited to 5 minutes. (2) 100 % N1 =8,700 rpm (3) 102.5 % N2 = 16,270 rpm Engine Model AE3007A1P Limits Operating Conditions Static Thrust (lb.) Rotor Speed (%) Temperature Interturbine (°C) -1000ft N1 N2 ITT Takeoff 8,338 100(2) 102.5(3) 948(1) (1738° F) Maximum Continuous 6,852 100 102.5(3) 901 (1653° F) Ground 53.6 (min), 102.5 (max) Starting 800 (1472° F) (1) Time limited to 5 minutes. (2) 100 % N1 =8,700 rpm (3) 102.5 % N2 = 16,270 rpm Oil Temperature Maximum: 126°C (260°F) Normal oil temperature range: 21°C to 126°C (70 at 260°F) Minimum temperature for starting: above -40°C (-40°F) for lubrication oil specified by MIL-L-23699 above -54°C (-65°F) for lubrication oil specified by MIL-L-7808 Minimum to increase N2 above 83%: 40ºC (104°F) Oil Pressure Maximum: 95 psig (This limit may be exceeded during starts if oil temperature is below 21°C (70oF)) (for Airplanes with engine FADEC software previous to version B7.6 installed). 110 psig (This limit may be exceeded during starts if oil temperature is below 21oC (70oF)) (for Airplanes with engine FADEC software version B7.6 or later approved version installed). For takeoff and go-around the maximum limit is 115 psi, limited to 5 minutes. For aircraft which have complied with SBAE 30071-79-025 or equivalent, the maximum limit for takeoff and go around is 155 PSI, limited to 2 minutes. Minimum: 48 psig (N2 equal or above 88%) 34 psig (N2 below 88%) Revision 38 Page 7 of 40 T00011AT APU Limits (both models) Maximum RPM: 108% Maximum EGT: Steady State (Time limited to 5 minutes) 1323°F (717º C) Running (Normal) 1256°F (680° C) Airspeed Limits (EAS) Maximum Operating Limit Speed VMO: - 0 to 8,000 ft: 250 KEAS - 10,000 to 26,300 ft: 320 KEAS - 26,300 to 37,000 ft: 0.78 Mach - (Linear variation from 8,000 to 10,000 ft.) Maneuvering speed (VA): 202 KEAS Maximum flap extended speed (VFE): − Flaps 9° (Takeoff/Approach): 250 KEAS − Flaps 18° ( Takeoff) 200 KEAS (See Note 15) − Flaps 22°: 200 KEAS − Flaps 45° (Landing) : 145 KEAS Maximum landing gear extended speed (VLE): 250 KEAS Maximum landing gear operating speed (VLO): -VLO for retraction 200 KEAS -VLO for extension 250 KEAS C. G. Limits (landing gear extended) 595.6 to 619.4 inches (18.4% to 39.5% MAC) with 48,721 lbs. (22,100 kg). 595.6 to 619.4 inches (18.4% to 39.5% MAC) with 48,501 lbs. (22,000 kg). 592.5 to 619.4 inches (15.7% to 39.5% MAC) with 42,549 lbs. (19,300 kg). 590.1 to 623.3 inches (13.6% to 43.0% MAC) with 37,698 lbs. (17,100 kg). 588.3 to 623.3 inches (12.0% to 43.0% MAC) with 34,171 lbs. (15,500 kg). 588.3 to 623.3 inches (12.0% to 43.0% MAC) with 29,541 lbs. (13,400 kg). 608.6 inches (30% MAC) with 27,337 lbs. (12,400 kg). Straight linear variation between the points given. Moment due to landing gear retraction - 10,763 in-lbs. (-124 kgf-m) (the aircraft C.G. is moved forward with the retraction). Maximum Weights Ramp 48,721 lbs. (22,100 kgf) Takeoff 48,501 lbs. (22,000 kgf) Landing 42,549 lbs. (19,300 kgf) Zero fuel 39,462 lbs. (17,900 kgf) Maximum Baggage 2,646 lbs. (1,200 kg) Fuel Capacity 1373.8 gallons (two tanks, 686.9 gallons each at +603.6 inches). Unusable fuel of 14.3 gallons (7.15 gallons for each tank). Serial Numbers Eligible 145048 and subsequent. A Brazilian Certificate of Airworthiness for Export endorsed as noted under “Import Requirements” must be submitted for each individual aircraft for which application for U.S. certification is made. Revision 38 Page 8 of 40 T00011AT 4. - Model EMB-145LR, (Transport Category), Approved May 7, 1998 Engine Two – Rolls Royce Corporation (See Note 16.) Model AE 3007A1/1, AE 3007A1/2, AE3007A1 or AE3007A1P Fuel Brazilian Specification CNP-08/QAV1. ASTM Specification D-1655 JET A or JET A1 MIL-T-83133A JP-8. APU Sundstrand Aerospace Model T-62T-40C11 or T-62T-40C14 Limitations as stated in Sundstrand Doc. No. ESR 0921 and No. ESR 1112 Oil Engine: MIL-L-7808 or MIL-L-23699 APU: MIL-L-23699 or MIL-L-7808 Engine Model AE3007A1/1 Limits Operating Conditions Static Thrust (lb.) Rotor Speed (%) Temperature Interturbine (°C) -1000ft N1 N2 ITT Takeoff 7,580 100(2) 102.5(3) 921(1) (1690° F) Maximum Continuous 6,820 100 102.5 868 (1605° F) Ground 53.6 (min), 102.5 (max) Starting 800 (1472° F) (1) Time limited to 5 minutes. (2) 100 % N1 =8,700 rpm (3) 102.5 % N2 = 16,270 rpm Engine Models AE3007A1/2 and AE3007A1 Limits Operating Conditions Static Thrust (lb.) Rotor Speed (%) Temperature Interturbine (°C) -1000ft N1 N2 ITT Takeoff 7,580 100(2) 102.5(3) 948(1) (1738° F) Maximum Continuous 6,820 100 102.5 901 (1653° F) Ground 53.6 (min), 102.5 (max) Starting 800 (1472° F) (1) Time limited to 5 minutes. (2) 100 % N1 =8,700 rpm (3) 102.5 % N2 = 16,270 rpm Engine Model AE3007A1P Limits Operating Conditions Static Thrust (lb.) Rotor Speed (%) Temperature Interturbine (°C) -1000ft N1 N2 ITT Takeoff 8,338 100(2) 102.5(3) 948(1) (1738° F) Maximum Continuous 6,852 100 102.5(3) 901 (1653° F) Ground 53.6 (min), 102.5 (max) Starting 800 (1472° F) (1) Time limited to 5 minutes. (2) 100 % N1 =8,700 rpm (3) 102.5 % N2 = 16,270 rpm Revision 38 Page 9 of 40 T00011AT Oil Temperature Maximum: 126°C (260°F) Normal oil temperature range: 21°C at 126°C (70 at 260°F) Minimum temperature for starting: above -40°C (-40°F) for lubrication oil specified by MIL-L-23699 above -54°C (-65°F) for lubrication oil specified by MIL-L-7808 Minimum to increase N2 above 83%: 40ºC (104°F) Oil Pressure Maximum: 95 psig (This limit may be exceeded during starts if oil temperature is below 21°C (70oF)) (for Airplanes with engine FADEC software previous to version B7.6 installed). 110 psig (This limit may be exceeded during starts if oil temperature is below 21oC (70oF)) (for Airplanes with engine FADEC software version B7.6 or later approved version installed). For takeoff and go-around the maximum limit is 115 psi, limited to 5 minutes. For aircraft which have complied with SBAE 30071-79-025 or equivalent, the maximum limit for takeoff and go around is 155 PSI, limited to 2 minutes. Minimum: 48 psig (N2 equal or above 88%) 34 psig (N2 below 88%) APU Limits (both models) Maximum RPM: 108% Maximum EGT: Steady State (Time limited to 5 minutes) 1323°F (717º C) Running (Normal) 1256°F (680° C) Airspeed Limits (EAS) Maximum Operating Limit Speed VMO: - 0 to 8,000 ft: 250 KEAS - 10,000 to 26,300 ft: 320 KEAS - 26,300 to 37,000 ft: 0.78 Mach - (Linear variation from 8,000 to 10,000 ft.) Maneuvering speed (VA): 202 KEAS Maximum flap extended speed (VFE): − Flaps 9° (Takeoff/Approach): 250 KEAS − Flaps 18° ( Takeoff) 200 KEAS (See Note 15) − Flaps 22°: 200 KEAS − Flaps 45° (Landing) : 145 KEAS Maximum landing gear extended speed (VLE): 250 KEAS Maximum landing gear operating speed (VLO): -VLO for retraction 200 KEAS -VLO for extension 250 KEAS C. G. Limits (landing gear extended) 595.6 to 619.4 inches (18.4% to 39.5% MAC) with 48,721 lbs. (22,100 kg). 595.6 to 619.4 inches (18.4% to 39.5% MAC) with 48,501 lbs. (22,000 kg). 592.5 to 619.4 inches (15.7% to 39.5% MAC) with 42,549 lbs. (19,300 kg). 590.1 to 623.3 inches (13.6% to 43.0% MAC) with 37,698 lbs. (17,100 kg). 588.3 to 623.3 inches (12.0% to 43.0% MAC) with 34,171 lbs. (15,500 kg). 588.3 to 623.3 inches (12.0% to 43.0% MAC) with 29,541 lbs. (13,400 kg). 608.6 inches (30% MAC) with 27,337 lbs. (12,400 kg). Revision 38 Page 10 of 40 T00011AT For aircraft modified 595.6 to 619.4 inches (19.0% to 38.5% MAC) with 50,044 lbs. (22,700 kg). according to SB 145-00-0032 595.6 to 619.4 inches (19.0% to 38.5% MAC) with 49,824 lbs. (22,600 kg). 592.5 to 619.4 inches (15.7% to 39.5% MAC) with 42,549 lbs. (19,300 kg). 590.2 to 623.3 inches (13.6% to 43.0% MAC) with 37,698 lbs. (17,100 kg). 588.3 to 623.3 inches (12.0% to 43.0% MAC) with 34,171 lbs. (15,500 kg). 588.3 to 623.3 inches (12.0% to 43.0% MAC) with 29,541 lbs. (13,400 kg). 608.6 inches (30% MAC) with 27,337 lbs. (12,400 kg). Straight linear variation between the points given. Moment due to landing gear retraction - 10,763 in-lbs. (-124 kgf-m) (the aircraft C.G. is moved forward with the retraction). Maximum Weights Ramp 48,721 lbs. (22,100 kgf) Takeoff 48,501 lbs. (22,000 kgf) Landing 42,549 lbs. (19,300 kgf) Zero fuel 39,462 lbs. (17,900 kgf) For aircraft modified Ramp 50,044 lbs. (22,700 kgf) according to SB 145-00-0032 Takeoff 49,824 lbs. (22,600 kgf) Landing 43,651 lbs. (19,800 kgf) Zero fuel 40,565 lbs. (17,900 kgf) Maximum Baggage 2,646 lbs. (1,200 kg) Fuel Capacity 1701.4 gallons (two tanks, 850.7 gallons each at +596.6 inches). Unusable fuel of 11.6 gallons (5.8 gallons for each tank). Serial Numbers Eligible 145002, 145003, 145048 and subsequent. A Brazilian Certificate of Airworthiness for Export endorsed as noted under “Import Requirements” must be submitted for each individual aircraft for which application for U.S. certification is made. 5. - Model EMB-135ER, (Transport Category), Approved July 15, 1999 Engine Two – Rolls Royce Corporation (See Note 16.) Models: AE 3007A1/3 or AE 3007A3 Fuel Brazilian Specification CNP-08/QAV1. ASTM Specification D-1655 JET A or JET A1 MIL-T-83133A JP-8. APU Sundstrand Aerospace Model T-62T-40C11 or T-62T-40C14 Limitations as stated in Sundstrand Doc. No. ESR 0921 and No. ESR 1112 Oil Engine: MIL-L-7808 or MIL-L-23699 APU: MIL-L-23699 or MIL-L-7808 Engine Model AE3007A1/3 Limits Operating Conditions Static Thrust (lb.) Rotor Speed (%) Temperature Interturbine (°C) -1000ft SL N1 N2 ITT Takeoff 7,580 7,462 100(2) 102.5(3) 948(1) (1738° F) Maximum Continuous 6,820 6,760 100 102.5 901 (1653° F) Ground 53.6 (min), 102.5 (max) Starting 800 (1472° F) (1) Time limited to 5 minutes. (2) 100 % N1 =8,700 rpm (3) 102.5 % N2 = 16,270 rpm Revision 38 Page 11 of 40 T00011AT Oil Temperature Maximum: 126°C (260°F) Normal oil temperature range: 21°C to 126°C (70 to 260°F) Minimum temperature for starting: above -40°C (-40°F) for lubrication oil specified by MIL-L-3699 above -54°C (-65°F) for lubrication oil specified by MIL-L-7808 Minimum to increase N2 above 83%: 40ºC (104°F) Oil Pressure Maximum: 95 psig (This limit may be exceeded during starts if oil temperature is below 21°C (70ºF)) (for Airplanes with engine FADEC software previous to version B7.6 installed). 110 psig (This limit may be exceed during starts if oil temperature is below 21oC (70oF)) (for Airplanes with engine FADEC software version B7.6 or later approved version installed). For takeoff and go-around the maximum limit is 115 psi, limited to 5 minutes. For aircraft which have complied with SBAE 30071-79-025 or equivalent, the maximum limit for takeoff and go around is 155 PSI, limited to 2 minutes. Minimum: 48 psig (N2 equal or above 88%) 34 psig (N2 below 88%) APU Limits (both models) Maximum RPM: 108% Maximum EGT: Steady State (Time limited to 5 minutes) 1323°F (717º C) Running (Normal) 1256°F (680° C) Airspeed Limits (EAS) Maximum Operating Limit Speed VMO: - 0 to 8,000 ft: 250 KEAS - 10,000 to 26,300 ft: 320 KEAS - 26,300 to 37,000 ft: 0.78 Mach - (Linear variation from 8,000 to 10,000 ft.) Maneuvering speed (VA): 202 KEAS Maximum flap extended speed (VFE): − Flaps 9° (Takeoff/Approach): 250 KEAS − Flaps 18° ( Takeoff) 200 KEAS (See Note 15) − Flaps 22°: 200 KEAS − Flaps 45° (Landing) : 145 KEAS Maximum landing gear extended speed (VLE): 250 KEAS Maximum landing gear operating speed (VLO): -VLO for retraction 200 KEAS -VLO for extension 250 KEAS C. G. Limits (landing gear extended) 518.4 to 538.7 inches (20.0% to 38.0% MAC) with 42,107 lbs. (19,100 kg). 518.4 to 538.7 inches (20.0% to 38.0% MAC) with _41,887 lbs. (19,000 kg). 517.7 to 538.7 inches (19.4% to 38.0% MAC) with 40,789 lbs. (18,500 kg). 514.7 to 538.7 inches (16.7% to 38.0% MAC) with 34,391 lbs. (15,600 kg). 512.7 to 538.7 inches (15.0% to 38.0% MAC) with 31,996 lbs. (14,500 kg). 512.7 to 538.7 inches (15.0% to 38.0% MAC) with 27,557 lbs. (12,500 kg). 521.2 to 538.7 inches (22.5% to 38.0% MAC) with 26,455 lbs. (12,000 kg). 529.7 inches (30% MAC) with 25,353 lbs. (11,500 kg). Straight linear variation between the points given. Revision 38 Page 12 of 40 T00011AT Moment due to landing gear retraction -10,155 in-lbs. (-117 kgf-m) (the aircraft C.G. is moved forward with the retraction). Maximum Weights Ramp 42,108 lbs. (19,100 kgf) Takeoff 41,887 lbs. (19,000 kgf) Landing 40,785 lbs. (18,500 kgf) Zero fuel 34,392 lbs. (15,600 kgf) Maximum Baggage 2,205 lbs. (1,000 kg) Fuel Capacity 1373.8 gallons (two tanks, 686.9 gallons each at +524.4 inches). Unusable fuel of 13.3 gallons (6.6 gallons for each tank). Serial Numbers Eligible 145145 and subsequent. A Brazilian Certificate of Airworthiness for Export endorsed as noted under “Import Requirements” must be submitted for each individual aircraft for which application for U.S. certification is made. 6. - Model EMB-135LR, (Transport Category), Approved July 15, 1999 Engine Two – Rolls Royce Corporation (See Note 16.) Models: AE 3007A1/3 or AE 3007A3 Fuel Brazilian Specification CNP-08/QAV1. ASTM Specification D-1655 JET A or JET A1 MIL-T-83133A JP-8. APU Sundstrand Aerospace Model T-62T-40C11 or T-62T-40C14 Limitations as stated in Sundstrand Doc. No. ESR 0921 and No. ESR 1112 Oil Engine: MIL-L-7808 or MIL-L-23699 APU: MIL-L-23699 or MIL-L-7808 Engine Model AE3007A1/3 Limits Operating Conditions Static Thrust (lb.) Rotor Speed (%) Temperature Interturbine (°C) -1000ft N1 N2 ITT Takeoff 7,580 100(2) 102.5(3) 948(1) (1738° F) Maximum Continuous 6,820 100 102.5 901 (1653° F) Ground 53.6 (min), 102.5 (max) Starting 800 (1472° F) (1) Time limited to 5 minutes. (2) 100 % N1 =8,700 rpm (3) 102.5 % N2 = 16,270 rpm Oil Temperature Maximum: 126°C (260°F) Normal oil temperature range: 21°C to 126°C (70 to 260°F) Minimum temperature for starting: above -40°C (-40°F) for lubrication oil specified by MIL-L-23699 above -54°C (-65°F) for lubrication oil specified by MIL-L-7808 Minimum to increase N2 above 83%: 40ºC (104°F) Revision 38 Page 13 of 40 T00011AT Oil Pressure Maximum: 95 psig (This limit may be exceeded during starts if oil temperature is below 21°C (70ºF)) (for Airplanes with engine FADEC software previous to version B7.6 installed). 110 psig (This limit may be exceed during starts if oil temperature is below 21oC (70oF)) (for Airplanes with engine FADEC software version B7.6 or later approved version installed). For takeoff and go-around the maximum limit is 115 psi, limited to 5 minutes. For aircraft which have complied with SBAE 30071-79-025 or equivalent, the maximum limit for takeoff and go around is 155 PSI, limited to 2 minutes. Minimum: 48 psig (N2 equal or above 88%) 34 psig (N2 below 88%) APU Limits (both models) Maximum RPM: 108% Maximum EGT: Steady State (Time limited to 5 minutes) 1323°F (717º C) Running (Normal) 1256°F (680° C) Airspeed Limits (EAS) Maximum Operating Limit Speed VMO: - 0 to 8,000 ft: 250 KEAS - 10,000 to 26,300 ft: 320 KEAS - 26,300 to 37,000 ft: 0.78 Mach - (Linear variation from 8,000 to 10,000 ft.) Maneuvering speed (VA): 202 KEAS Maximum flap extended speed (VFE): − Flaps 9° (Takeoff/Approach): 250 KEAS − Flaps 18° ( Takeoff) 200 KEAS (See Note 15) − Flaps 22°: 200 KEAS − Flaps 45° (Landing) : 145 KEAS Maximum landing gear extended speed (VLE): 250 KEAS Maximum landing gear operating speed (VLO): -VLO for retraction 200 KEAS -VLO for extension 250 KEAS C. G. Limits (landing gear extended) 519.7 to 538.7 inches (21.1% to 38.0% MAC) with 44,312 lbs. (20,100 kg). 519.6 to 538.7 inches (21.1% to 38.0% MAC) with 44,092 lbs. (20,000 kg). 517.7 to 538.7 inches (19.4% to 38.0% MAC) with 40,789 lbs. (18,500 kg). 514.7 to 538.7 inches (16.7% to 38.0% MAC) with 35,273 lbs. (16,000 kg). 512.7 to 538.7 inches (15.0% to 38.0% MAC) with 31,966 lbs. (14,500 kg). 512.7 to 538.7 inches (15.0% to 38.0% MAC) with 27,557 lbs. (12,500 kg). 521.2 to 538.7 inches (22.5% to 38.0% MAC) with 26,455 lbs. (12,000 kg). 529.7 inches (30% MAC) with 25,352 lbs. (11,500 kg). Straight linear variation between the points given. Moment due to landing gear retraction - 10,155 in-lbs. (-117 kgf-m) (the aircraft C.G. is moved forward with the retraction) Maximum Weights Ramp 44,312 lbs. (20,100 kgf) Takeoff 44,092 lbs. (20,000 kgf) Landing 40,785 lbs. (18,500 kgf) Zero fuel 35,274 lbs. (16,000 kgf) Revision 38 Page 14 of 40 T00011AT Maximum Baggage 2,205 lbs. (1,000 kg) Fuel Capacity 1701.4 gallons (two tanks, 850.7 gallons each at +517.6 inches). Unusable fuel of 10.8 gallons (5.4 gallons for each tank). Serial Numbers Eligible 145145 and subsequent. A Brazilian Certificate of Airworthiness for Export endorsed as noted under “Import Requirements” must be submitted for each individual aircraft for which application for U.S. certification is made. 7. - Model EMB-135KE, (ERJ-140ER), (Transport Category), Approved July 26, 2001. Engine Two – Rolls Royce Corporation (See Note 16.) Model: AE 3007A1/3 Fuel Brazilian Specification CNP-08/QAV1. ASTM Specification D-1655 JET A or JET A1 MIL-T-83133A JP-8. APU Sundstrand Aerospace Model T-62-T-40C11 or T-62T-40C14 Limitations as stated in Sundstrand Doc. No. ESR 0921 and No. ESR 1112 Oil Engine: MIL-L-7808 or MIL-L-23699 APU: MIL-L-7808 or MIL-L-23699 Engine Model AE3007A1/3 Limits Operating Conditions Static Thrust (lb.) Rotor Speed (%) Temperature Interturbine (°C) -1000ft N1 N2 ITT Takeoff 7,580 100(2) 102.5(3) 948(1) (1738° F) Maximum Continuous 6,820 100 102.5 901 (1653° F) Ground 53.6 (min), 102.5 (max) Starting 800 (1472° F) (1) Time limited to 5 minutes. (2) 100 % N1 =8,700 rpm (3) 102.5 % N2 = 16,270 rpm Oil Temperature Maximum: 126°C (260°F) Normal oil temperature range: 21°C to 126°C (70 to 260°F) Minimum temperature for starting: above -40°C (-40°F) for lubrication oil specified by MIL-L-23699 above -54°C (-65°F) for lubrication oil specified by MIL-L-7808 Minimum to increase N2 above 83%: 40ºC (104°F) Oil Pressure Maximum: 95 psig (This limit may be exceeded during starts if oil temperature is below 21°C (70ºF)) (for Airplanes with engine FADEC software previous to version B7.6 installed). 110 psig (This limit may be exceed during starts if oil temperature is below 21oC (70oF)) (for Airplanes with engine FADEC software version B7.6 or later approved version installed). For takeoff and go-around the maximum limit is 115 psi, limited to 5 minutes. For aircraft which have complied with SBAE 30071-79-025 or equivalent, the maximum limit for takeoff and go around is 155 PSI, limited to 2 minutes. Minimum: 48 psig (N2 equal or above 88%) 34 psig (N2 below 88%) Revision 38 Page 15 of 40 T00011AT APU Limits (both models) Maximum RPM: 108% Maximum EGT: Steady State (Time limited to 5 minutes) 1323°F (717º C) Running (Normal) 1256°F (680° C) Airspeed Limits (EAS) Maximum Operating Limit Speed VMO: - 0 to 8,000 ft: 250 KEAS - 10,000 to 26,300 ft: 320 KEAS - 26,300 to 37,000 ft: 0.78 Mach - (Linear variation from 8,000 to 10,000 ft.) Maneuvering speed (VA): 202 KEAS Maximum flap extended speed (VFE): − Flaps 9° (Takeoff/Approach): 250 KEAS − Flaps 18° ( Takeoff) 200 KEAS − Flaps 22°: 200 KEAS − Flaps 45° (Landing) : 145 KEAS Maximum landing gear extended speed (VLE): 250 KEAS Maximum landing gear operating speed (VLO): -VLO for retraction 200 KEAS -VLO for extension 250 KEAS C. G. Limits (landing gear extended) 529.2 to 582.2 inches (18.2% to 38.5% MAC) with 44,532 lbs. (20,200 kg). 529.2 to 582.2 inches (18.2% to 38.5% MAC) with 44,312 lbs. (20,100 kg). 558.5 to 582.2 inches (17.5% to 38.5% MAC) with 42,548 lbs. (19,300 kg). 556.5 to 585.0 inches (15.7% to 41.0% MAC) with 37,699 lbs. (17,100 kg). 554.5 to 585.0 inches (14.0% to 41.0% MAC) with 33,068 lbs. (15,000 kg). 554.5 to 585.0 inches (14.0% to 41.0% MAC) with 28,659 lbs. (13,000 kg). 572.5 inches (30% MAC) with 26,445 lbs. (12,000 kg). Straight linear variation between the points given. Moment due to landing gear retraction - 10,155 in-lbs. (-117 kgf-m) (the aircraft C.G. is moved forward with the retraction). Maximum Weights Ramp 44,532 lbs. (20,200 kgf) Takeoff 44,312 lbs. (20,100 kgf) Landing 41,225 lbs. (18,700 kgf) Zero fuel 37,698 lbs. (17,100 kgf) Maximum Baggage 2,646 lbs. (1,200 kg) Fuel Capacity 1373.8 gallons (two tanks, 686.9 gallons each at +567.5 inches). Unusable fuel of 14.4 gallons (7.2 gallons for each tank). Serial Numbers Eligible 145425 and subsequent. A Brazilian Certificate of Airworthiness for Export endorsed as noted under “Import Requirements” must be submitted for each individual aircraft for which application for U.S. certification is made. Revision 38 Page 16 of 40 T00011AT 8. - Model EMB-135KL, (ERJ-140LR), (Transport Category), Approved July 26, 2001. Engine Two – Rolls Royce Corporation (See Note 16.) Model: AE 3007A1/3 Fuel Brazilian Specification CNP-08/QAV1. ASTM Specification D-1655 JET A or JET A1 MIL-T-83133A JP-8. APU Sundstrand Aerospace Model T-62-T-40C11 or T-62T-40C14 Limitations as stated in Sundstrand Doc. No. ESR 0921 and No. ESR 1112 Oil Engine: MIL-L-7808 or MIL-L-23699 APU: MIL-L-7808 or MIL-L-23699 Engine Model AE3007A1/3 Limits Operating Conditions Static Thrust (lb.) Rotor Speed (%) Temperature Interturbine (°C) -1000ft N1 N2 ITT Takeoff 7,580 100(2) 102.5(3) 948(1) (1738° F) Maximum Continuous 6,820 100 102.5 901 (1653° F) Ground 53.6 (min), 102.5 (max) Starting 800 (1472° F) (1) Time limited to 5 minutes. (2) 100 % N1 =8,700 rpm (3) 102.5 % N2 = 16,270 rpm Oil Temperature Maximum: 126°C (260°F) Normal oil temperature range: 21°C to 126°C (70 to 260°F) Minimum temperature for starting: above -40°C (-40°F) for lubrication oil specified by MIL-L-23699 above -54°C (-65°F) for lubrication oil specified by MIL-L-7808 Minimum to increase N2 above 83%: 40ºC (104°F) Oil Pressure Maximum: 95 psig (This limit may be exceeded during starts if oil temperature is below 21°C (70ºF)) (for Airplanes with engine FADEC software previous to version B7.6 installed). 110 psig (This limit may be exceed during starts if oil temperature is below 21oC (70oF)) (for Airplanes with engine FADEC software version B7.6 or later approved version installed). For takeoff and go-around the maximum limit is 115 psi, limited to 5 minutes. For aircraft which have complied with SBAE 30071-79-025 or equivalent, the maximum limit for takeoff and go around is 155 PSI, limited to 2 minutes. Minimum: 48 psig (N2 equal or above 88%) 34 psig (N2 below 88%) APU Limits (both models) Maximum RPM: 108% Maximum EGT: Steady State (Time limited to 5 minutes) 1323°F (717º C) Running (Normal) 1256°F (680° C) Airspeed Limits (EAS) Maximum Operating Limit Speed VMO: - 0 to 8,000 ft: 250 KEAS - 10,000 to 26,300 ft: 320 KEAS - 26,300 to 37,000 ft: 0.78 Mach - (Linear variation from 8,000 to 10,000 ft.) Revision 38 Page 17 of 40 T00011AT Maneuvering speed (VA): 202 KEAS Maximum flap extended speed (VFE): − Flaps 9° (Takeoff/Approach): 250 KEAS − Flaps 18° ( Takeoff) 200 KEAS − Flaps 22°: 200 KEAS − Flaps 45° (Landing) : 145 KEAS Maximum landing gear extended speed (VLE): 250 KEAS Maximum landing gear operating speed (VLO): -VLO for retraction 200 KEAS -VLO for extension 250 KEAS C. G. Limits (landing gear extended) 560.1 to 582.2 inches (19.0% to 38.5% MAC) with 46,737 lbs. (21,200 kg). 560.1 to 581.8 inches (19.0% to 38.5% MAC) with 46,516 lbs. (21,100 kg). 558.5 to 582.2 inches (17.5% to 38.5% MAC) with 42,548 lbs. (19,300 kg). 556.5 to 585.0 inches (15.7% to 41.0% MAC) with 37,699 lbs. (17,100 kg). 554.5 to 585.0 inches (14.0% to 41.0% MAC) with 33,068 lbs. (15,000 kg). 554.5 to 585.0 inches (14.0% to 41.0% MAC) with 28,659 lbs. (13,000 kg). 572.5 inches (30% MAC) with 26,445 lbs. (12,000 kg). Straight linear variation between the points given. Moment due to landing gear retraction - 10,155 in-lbs. (-117 kgf-m) (the aircraft C.G. is moved forward with the retraction). Maximum Weights Ramp 46,737 lbs. (21,200 kgf) Takeoff 46,516 lbs. (21,100 kgf) Landing 41,225 lbs. (18,700 kgf) Zero fuel 37,698 lbs. (17,100 kgf) Maximum Baggage 2,646 lbs. (1,200 kg) Fuel Capacity 1707.5 gallons (two tanks, 853.75 gallons each at +560.5 inches). Unusable fuel of 11.7 gallons (5.85 gallons for each tank). Serial Numbers Eligible 145425 and subsequent. A Brazilian Certificate of Airworthiness for Export endorsed as noted under “Import Requirements” must be submitted for each individual aircraft for which application for U.S. certification is made. 9. - Model EMB-135BJ – This model has two unique configurations, Legacy 600 and Legacy 650 9(a) Legacy 600, (Transport Category), Approved August 23, 2002. Engine Two – Rolls Royce Corporation (See Note 16.) Model: AE 3007A1P For S/N 145625 and on Two – Rolls Royce Corporation (See Note 16.) Model: AE 3007A1E Fuel Brazilian Specification CNP-08/QAV1. ASTM Specification D-1655 JET A or JET A1 MIL-T-83133A JP-8. APU Sundstrand Aerospace Model T-62-T-40C14 Limitations as stated in Sundstrand Doc. No. ESR 1112 Oil Engine: MIL-L-7808 or MIL-L-23699 Revision 38 Page 18 of 40 T00011AT APU: MIL-L-7808 or MIL-L-23699 Engine Model AE3007A1P Limits Operating Conditions Static Thrust (lb.) Rotor Speed (%) Temperature Interturbine (°C) -1000ft SL N1 N2 ITT Takeoff 8,338 8,195 100(2) 102.5(3) 948(1) (1738° F) Maximum Continuous 6,852 6,759 100 102.5 901 (1653° F) Ground 57 (min), 102.5 (max) Starting 800 (1472° F) (1) Time limited to 5 minutes. (2) 100 % N1 =8,700 rpm (3) 102.5 % N2 = 16,270 rpm Engine Model AE3007A1E Limits Operating Conditions Static Thrust (lb.) Rotor Speed (%) Temperature Interturbine (°C) -1000ft SL N1 N2 ITT Takeoff 8,895 8,765 100(2) 103.8(3) 970(1)(6) (1778° F) Maximum Continuous 7,354 7,222 100 102.5 935 (1715° F) Ground 57 (min), 103.8 (max) Starting 56(5) (max) 800(4) (1472° F) (1) Time limited to 5 minutes. (2) 100 % N1 =8,700 rpm (3) 103.8 % N2 = 16,470 rpm (4) ITT limit may be exceeded for up to 5 seconds to maximum temperature of 850 °C (5) Verify N2 speed is less than 56% prior to initiating any start attempt (6) ITT limit may be exceeded for up to 90 seconds to maximum temperature of 970°C Oil Temperature Maximum: 126°C (260°F) Normal oil temperature range: 21°C to 126°C (70 to 260°F) Minimum temperature for starting: above -40°C (-40°F) for lubrication oil specified by MIL-L-23699 above -54°C (-65°F) for lubrication oil specified by MIL-L-7808 Minimum to increase N2 above 83%: 40ºC (104°F) Oil Pressure Maximum: 95 psig (This limit may be exceeded during starts if oil temperature is below 21°C (70ºF)) (for Airplanes with engine FADEC software previous to version B7.6 installed). 110 psig (This limit may be exceed during starts if oil temperature is below 21oC (70oF)) (for Airplanes with engine FADEC software version B7.6 or later approved version installed). For aircraft which have complied with SBAE 3007A-79-025 or equivalent, the maximum limit for takeoff and go around is 155 PSI, limited to 2 minutes. Minimum: 50 psig (N2 equal or above 88%) 34 psig (N2 below 88%) APU Limits Maximum RPM: 104% Maximum EGT: Steady State (Time limited to 5 minutes) 1323°F (717º C) Running (Normal) 1256°F (680° C) Airspeed Limits (EAS) Maximum Operating Limit Speed VMO: - 0 to 8,000 ft: 250 KEAS - 10,000 to 27,625 ft: 320 KEAS - 27,625 to 41,000 ft: 0.80 Mach - (Linear variation from 8,000 to 10,000 ft). Revision 38 Page 19 of 40 T00011AT Maneuvering speed (VA): 200 KEAS Maximum flap extended speed (VFE): − Flaps 9° (Takeoff/Approach): 250 KEAS − Flaps 22° (Approach/Landing) 200 KEAS − Flaps 22º (Approach/Landing) in icing conditions and yaw damper off: 180 KEAS − Flaps 45° (Landing): 145 KEAS Maximum landing gear extended speed (VLE): 250 KEAS Maximum landing gear operating speed (VLO): -VLO for retraction 200 KEAS -VLO for extension 250 KEAS C. G. Limits (Landing Gear Extended) 526.1 to 535.3 inches (26.9% to 35% MAC) with 49,097 lbs. (22,270 kg). 526.1 to 535.3 inches (26.9% to 35% MAC) with 48,943 lbs. (22,200 kg). 517.6 to 535.3 inches (19.3% to 35% MAC) with 40,786 lbs. (18,500 kg). 512.7 to 535.3 inches (15.0% to 35% MAC) with 31,967 lbs. (14,500 kg). 512.7 to 535.3 inches (15.0% to 35% MAC) with 30,864 lbs. (14,000 kg). 521.2 to 535.3 inches (25.3% to 35% MAC) with 29,350 lbs. (13,313 kg). 529.6 inches (30% MAC) with 28,660 lbs. (13,000 kg). For S/N 145625 and on 515.4 to 535.3 inches (27.5% to 35% MAC) with 49,758 lbs. (22,570 kg). 515.4 to 535.3 inches (27.5% to 35% MAC) with 49,604 lbs. (22,500 kg). 517.6 to 535.3 inches (19.3% to 35% MAC) with 40,786 lbs. (18,500 kg). 512.7 to 535.3 inches (15.0% to 35% MAC) with 31,967 lbs. (14,500 kg). 512.7 to 535.3 inches (15.0% to 35% MAC) with 30,864 lbs. (14,000 kg). 521.2 to 535.3 inches (25.3% to 35% MAC) with 29,350 lbs. (13,313 kg). 529.6 inches (30% MAC) with 28,660 lbs. (13,000 kg). Straight linear variation between the points given. Moment due to landing gear retraction - 10,155 in-lbs. (-117 kgf-m) (the aircraft C.G. is moved forward with the retraction). Maximum Weights Ramp 49,097 lbs. (22,270 kgf) Takeoff 48,943 lbs. (22,200 kgf) Landing 40,786 lbs. (18,500 kgf) Zero fuel 35,274 lbs. (16,000 kgf) For S/N 145625 and on Ramp 49,758 lbs. (22,570 kgf) Takeoff 49,604 lbs. (22,500 kgf) Landing 40,786 lbs. (18,500 kgf) Zero fuel 35,274 lbs. (16,000 kgf) Maximum Baggage 1,001 lbs. (454 kg) Fuel Capacity 2682 gallons (two forward fuselage tanks of 278.97 gallons each at +332.28 inches, two wing tanks of 844.9 gallons each at +517.6 inches and two aft tanks of 217.15 gallons each at +798.94 inches). Unusable fuel of 28 gallons (forward tanks 7.13 gallons, wing tanks 11.62 gallons and aft tanks 9.25 gallons). For S/N 145625 and on 2711,64 gallons (two forward fuselage tanks of 294 gallons each at +332.28 inches, two wing tanks of 844.9 gallons each at +517.6 inches and two aft tanks of 217 gallons each at +798.94 inches). Unusable fuel of 28 gallons (forward tanks 7.13 gallons, wing tanks 11.62 gallons and aft tanks 9.25 gallons). Revision 38 Page 20 of 40 T00011AT Serial Numbers Eligible 145412, 145462 and subsequent. A Brazilian Certificate of Airworthiness for Export endorsed as noted under “Import Requirements” must be submitted for each individual aircraft for which application for U.S. certification is made. 9(b) Legacy 650 (Transport Category), Approved February 18, 2011: Engine Two – Rolls Royce Corporation (See Note 16.) Model: AE 3007A2 Fuel Brazilian Specification CNP-08/QAV1. ASTM Specification D-1655 JET A or JET A1 MIL-T-83133A JP-8. APU Sundstrand Aerospace Model T-62-T-40C14 Limitations as stated in Sundstrand Doc. No. ESR 1112 Oil Engine: MIL-L-7808 or MIL-L-23699 APU: MIL-L-7808 or MIL-L-23699 Engine Model AE3007A2 Limits Operating Conditions Static Thrust (lb.) Rotor Speed (%) Temperature Interturbine (°C) -1000ft SL N1 N2 ITT Takeoff 9,320 9,278 97,7(2) 105.0(4) 970°C(steady state condition )(1) (1778° F) Maximum Continuous 7,990 7,970 97,7 105.0 937 (1718° F) Ground Starting 800 (1472° F)(3) (1) Time limited to 5 minutes (including the transient allowance). (2) 100 % N1 =8,700 rpm (3) During starts in-flight, the ITT limit of 800°C may be exceeded for up to 5 seconds to a maximum temperature of 850°C. (4) 102.5 % N2 = 16,270 rpm Oil pressure - upper limit Oil temperature above 21°C: 110 psig (steady state) (5) (6) 155 psig (transient) 2 minutes - lower limit N2 above 88% and oil temperature above 21°C: 48 psig (7) N2 between idle and 88% and oil temperature above 21°C: 34 psig Oil temperature - upper limit (continuous operation): 126 °C - lower limit (continuous operation): 21 °C - start limit: -40 °C (8) Fuel temperature - upper limit: 57 °C - lower limit: -53 °C LP spool vibration - continuous operation: 1.8 ips (9) - transient: 2.5 ips HP spool vibration - continuous operation: 1.1 ips (9) - transient: 2.5 ips Revision 38 Page 21 of 40 T00011AT (5) May be exceeded during starts if oil temperature is below 21°C. The engine must remain at IDLE until the oil pressure is less than 110 psig. Reference: CSP 30017 (6) Operation in oil pressure amber range is permitted between 111 and 115 psi in all operational modes time limited to 5 minutes, or between 116 and 155 psi in all operational modes time limited to 2 minutes. Total time above 110 psi may not exceed 5 minutes. Reference: CSP 30017 (7) While this is an abnormal condition, operation between 48 and 34 psi is permitted during takeoff and go-around phases. Reference: CSP 30017 (8) Ensure oil temperature is above -40°F (-40°C) before attempting a start when using MIL -PRF-23699F type oil, and above -65°F (-53°C) when using MIL-PRF-7808L type oil. (9) Vibration in the amber range below 2.5 IPS is time limited to 5 minutes during the takeoff or go-around phases or 10 seconds during the remainder flight phases. Reference: ECM AE 2428-G and CSP 30017 APU Limits Maximum RPM: 104% Maximum EGT: Steady State (Time limited to 5 minutes) 1323°F (717º C) Running (Normal) 1256°F (680° C) Airspeed Limits (EAS) Maximum Operating Limit Speed VMO: - 0 to 8,000 ft: 300 KEAS - 10,000 to 27,625 ft: 320 KEAS - 27,625 to 41,000 ft: 0.80 Mach - (Linear variation from 8,000 to 10,000 ft). Maneuvering speed (VA): 200 KEAS Maximum flap extended speed (VFE): − Flaps 9° (Takeoff/Approach): 250 KEAS − Flaps 22° (Approach/Landing) 200 KEAS − Flaps 22º (Approach/Landing) in icing conditions and yaw damper off: 180 KEAS − Flaps 45° (Landing): 160 KEAS Maximum landing gear extended speed (VLE): 250 KEAS Maximum landing gear operating speed (VLO): -VLO for retraction 200 KEAS -VLO for extension 250 KEAS Center of Gravity Limitations: 3.- C.G. VARIATIONS LIMITS, IN VARIOUS LOADING CONDITIONS ACCORDING TO SPECIFICATIONS: 3.1 - For Take-off and Landing conditions: - From 28,2 % to 38,0 % MAC for weight equal to: 53572 (lbf) - From 23,5 % to 38,0 % MAC for weight equal to: 44092 (lbf) - From 21,0 % to 38,0 % MAC for weights equal or less than: 39070 (lbf) - 21,0 % MAC for weight equal to: 30865 (lbf) - 30,0 % MAC for weight equal to: 28660 (lbf) - 38,0 % MAC for weight equal to: 29762 (lbf) 3.2 - For Flight conditions: - From 28,2 % to 38,0 % MAC for weight equal to: 53572 (lbf) - From 22,1 % to 38,0 % MAC for weight equal to: 44092 (lbf) - From 19,0 % to 38,0 % MAC for weights equal or less than: 39070 (lbf) - 19,0 % MAC for weight equal to: 30864 (lbf) - 30,0 % MAC for weight equal to: 28660 (lbf) - 38,0 % MAC for weight equal to: 29762 (lbf) Revision 38 Page 22 of 40 T00011AT Maximum Weights Ramp 53726 lbs. (24,370 kgf) Takeoff 53572 lbs. (24,300 kgf) Landing 44092 lbs. (20,000 kgf) Zero fuel 36155 lbs. (16,400 kgf) Maximum Baggage 1,001 lbs. (454 kg) Fuel Capacity 3071,1 gallons (two forward fuselage tanks of 293 .9 gallons each at +332.28 inches, two wing tanks of 888,8 gallons each at +517.6 inches , two aft tanks of 218,78 gallons each at +798.94 inches) and one ventral tank of 268 gallons. Unusable fuel of 44 gallons (forward tanks 6 gallons, wing tanks 25,62 gallons , aft tanks 5,8 gallons) and 6,65gallons of ventral tank. Serial Numbers Eligible 1451115 and subsequent. A Brazilian Certificate of Airworthiness for Export endorsed as noted under “Import Requirements” must be submitted for each individual aircraft for which application for U.S. certification is made. 10. - Model EMB-145XR (Transport Category), Approved October 22, 2002 Engine Two – Rolls Royce Corporation (See Note 16.) Model: AE 3007A1E Fuel Brazilian Specification CNP-08/QAV1. ASTM Specification D-1655 JET A or JET A1 MIL-T-83133A JP-8. APU Sundstrand Aerospace Model T-62-T-40C11 or T-62T-40C14 Limitations as stated in Sundstrand Doc. No. ESR 0921 and No. ESR 1112 Oil Engine: MIL-L-7808 or MIL-L-23699 APU: MIL-L-7808 or MIL-L-23699 Engine Model AE3007A1E Limits Operating Conditions Static Thrust (lb.) Rotor Speed (%) Temperature Interturbine (°C) -1000ft SL N1 N2 ITT Takeoff 8,895 8,765 100(2) 103.8(3) 970(1)(6) (1778° F) Maximum Continuous 7,354 7,222 100 102.5 935 (1715° F) Ground 57 (min), 103.8 (max) Starting 56(5) (max) 800(4) (1472° F) (1) Time limited to 5 minutes. (2) 100 % N1 =8,700 rpm (3) 103.8 % N2 = 16,470 rpm (4) ITT limit may be exceeded for up to 5 seconds to maximum temperature of 850 °C (5) Verify N2 speed is less than 56% prior to initiating any start attempt (6) ITT limit may be exceeded for up to 90 seconds to maximum temperature from 971°C to 992°C. Oil Temperature Maximum: 126°C (260°F) Normal oil temperature range: 21°C to 126°C (70 to 260°F) Minimum temperature for starting: above -40°C (-40°F) for lubrication oil specified by MIL-L-23699 above -54°C (-65°F) for lubrication oil specified by MIL-L-7808 Minimum to increase N2 above 83%: 40ºC (104°F) Oil Pressure Maximum: 95 psig (This limit may be exceeded during starts if oil temperature is below 21°C (70ºF)) (for Airplanes with engine FADEC software previous to version B7.6 installed). 110 psig (This limit may be exceed during starts if oil temperature is below 21oC (70oF)) Revision 38 Page 23 of 40 T00011AT (for Airplanes with engine FADEC software version B7.6 or later approved version installed). For takeoff and go-around the maximum limit is 155 psi, limited to 2 minutes. Minimum: 50 psig (N2 equal or above 88%) 34 psig (N2 below 88%) APU Limits Maximum RPM: 108% Maximum EGT: Steady State (Time limited to 5 minutes) 1323°F (717º C) Running (Normal) 1256°F (680° C) Airspeed Limits (EAS) Maximum Operating Limit Speed VMO (Airplanes Pre-Mod. SB 145-31-0038): - 0 to 8,000 ft: 250 KEAS - 10,000 to 26,300 ft: 320 KEAS - 26,300 to 37,000 ft: 0.78 Mach - (Linear variation from 8,000 to 10,000 ft.) Maximum Operating Limit Speed V MO (Airplanes Post -Mod. SB 145-31-0038 or with an equivalent modification factory incorporated): - 0 to 8,000 ft: 300 KEAS - 10,000 to 27,625 ft: 320 KEAS - 27,625 to 37,000 ft: 0.80 Mach - (Linear variation from 8,000 to 10,000 ft.) Maneuvering speed (VA): 200 KEAS Maximum flap extended speed (VFE): − Flaps 9° (Takeoff/Approach): 250 KEAS − Flaps 18° (Takeoff/Approach): 200 KEAS − Flaps 22° (Takeoff /Approach/Landing) 200 KEAS − Flaps 45° (Landing): 160 KEAS Maximum landing gear extended speed (VLE): 250 KEAS Maximum landing gear operating speed (VLO): -VLO for retraction 200 KEAS -VLO for extension 250 KEAS C. G. Limits (Landing Gear Extended) 597.8 to 617.7 inches (20.4% to 38.0% MAC) with 53,351 lbs. (24,200 kg). 597.8 to 617.7 inches (20.4% to 38.0% MAC) with 53,131 lbs. (24,100 kg). 588.4 to 623.3 inches (12.0% to 43.0% MAC) with 34,172 lbs. (15,500 kg). 588.4 to 623.3 inches (12.0% to 43.0% MAC) with 34,424 lbs. (13,800 kg). 609.2 inches (30.5% MAC) with 28,219 lbs. (12,800 kg). Straight linear variation between the points given. Moment due to landing gear retraction - 10,155 in-lbs. (-117 kgf-m) (the aircraft C.G. is moved forward with the retraction). Maximum Weights Ramp 53,351 lbs. (24,200 kgf) Takeoff 53,131 lbs. (24,100 kgf) Landing 44,092 lbs. (20,000 kgf) Zero fuel 40,785 lbs. (18,500 kgf) Maximum Baggage 2,646 lbs. (1200 kg) Revision 38 Page 24 of 40 T00011AT Fuel Capacity 1965.1 gallons (one ventral tank of 273.5 gallons and two wing tanks of 844.9 gallons each at +560.5 inches). Unusable fuel of 14.7 gallons (ventral tank 3.1 gallons and wing tanks 11.62gallons). Serial Numbers Eligible 145590 and subsequent. A Brazilian Certificate of Airworthiness for Export endorsed as noted under “Import Requirements” must be submitted for each individual aircraft for which application for U.S. certification is made. 11. - Model EMB-145MP, (Transport Category), Approved July 3, 2003 Engine Two – Rolls Royce Corporation (See Note 16.) Model AE 3007A, AE3007A1/1, AE3007A1/2, AE3007A1, or Model AE3007A1P Fuel Brazilian Specification CNP-08/QAV1. ASTM Specification D-1655 JET A or JET A1 MIL-T-83133A JP-8. APU Sundstrand Aerospace Model T-62T-40C11 or T-62T-40C14 Limitations as stated in Sundstrand Doc. No. ESR 0921 and No. ESR 1112 Oil Engine: MIL-L-7808 or MIL-L-23699 APU: MIL-L-23699 or MIL-L-7808 Engine Models AE3007A and AE3007A1/1 Limits Operating Conditions Static Thrust (lb.) Rotor Speed (%) Temperature Interturbine (°C) -1000ft N1 N2 ITT Takeoff 7,580 100(2) 102.5(3) 921(1) (1690° F) Maximum Continuous 6,820 100 102.5 868 (1600° F) Ground 53.6 (min), 102.5 (max) Starting 800 (1472° F) (1) Time limited to 5 minutes. (2) 100 % N1 =8,700 rpm (3) 102.5 % N2 = 16,270 rpm Engine Models AE3007A1/2 and AE3007A1 Limits Operating Conditions Static Thrust (lb.) Rotor Speed (%) Temperature Interturbine (°C) -1000ft N1 N2 ITT Takeoff 7,580 100(2) 102.5(3) 948(1) (1738° F) Maximum Continuous 6,820 100 102.5 901 (1653° F) Ground 53.6 (min), 102.5 (max) Starting 800 (1472° F) (1) Time limited to 5 minutes. (2) 100% N1 = 8,700 rpm (3) 102.5 % N2 =16,270 rpm Engine Model AE3007A1P Limits Operating Conditions Static Thrust (lb.) Rotor Speed (%) Temperature Interturbine (°C) -1000ft N1 N2 ITT Takeoff 8,338 100(2) 102.5(3) 948(1) (1738° F) Maximum Continuous 6,852 100 102.5(3) 901 (1653° F) Ground 53.6 (min), 102.5 (max) Starting 800 (1472° F) (1) Time limited to 5 minutes. (2) 100 % N1 =8,700 rpm (3) 102.5 % N2 = 16,270 rpm Revision 38 Page 25 of 40 T00011AT Oil Temperature Maximum: 126°C (260°F) Normal oil temperature range: 21°C to 126°C (70 at 260°F) Minimum temperature for starting: above -40°C (-40°F) for lubrication oil specified by MIL-L-23699 above -54°C (-65°F) for lubrication oil specified by MIL-L-7808 Minimum to increase N2 above 83%: 40ºC (104°F) Oil Pressure Maximum: 95 psig - This limit may be exceeded during starts if oil temperature is below 21°C (70oF)) (for Airplanes with engine FADEC software previous to version B7.6 installed). 110 psig (This limit may be exceeded during starts if oil temperature is below 21oC (70oF)) (for Airplanes with engine FADEC software version B7.6 or later approved version installed). For takeoff and go-around the maximum limit is 115 psi, limited to 5 minutes. For aircraft which have complied with SBAE 30071-79-025 or equivalent, the maximum limit for takeoff and go around is 155 PSI, limited to 2 minutes. Minimum: 48 psig (N2 equal or above 88%) 34 psig (N2 below 88%) APU Limits (both models) Maximum RPM: 108% Maximum EGT: Steady State (Time limited to 5 minutes) 1323°F (717º C) Running (Normal) 1256°F (680° C) Airspeed Limits (EAS) Maximum Operating Limit Speed VMO: - 0 to 8,000 ft: 250 KEAS - 10,000 to 26,300 ft: 320 KEAS - 26,300 to 37,000 ft: 0.78 Mach - (Linear variation from 8,000 to 10,000 ft.) Maneuvering speed (VA): 200 KEAS Maximum flap extended speed (VFE): − Flaps 9° (Takeoff/Approach): 250 KEAS − Flaps 18° ( Takeoff) 200 KEAS (See Note 15) − Flaps 22°: 200 KEAS − Flaps 45° (Landing) : 145 KEAS Maximum landing gear extended speed (VLE): 250 KEAS Maximum landing gear operating speed (VLO): -VLO for retraction 200 KEAS -VLO for extension 250 KEAS C. G. Limits (landing gear extended) 594.4 to 619.4 inches (17.4% to 39.5% MAC) with 46,495 lbs. (21,090 kg). 594.4 to 619.4 inches (17.4% to 39.5% MAC) with 46,275 lbs. (20,090 kg). 592.5 to 619.4 inches (15.7% to 39.5% MAC) with 42,549 lbs. (19,300 kg). 590.3 to 623.3 inches (13.6% to 43.0% MAC) with 37,699 lbs. (17,100 kg). 588.3 to 623.3 inches (12.0% to 43.0% MAC) with 34,171 lbs. (15,500 kg). 588.3 to 623.3 inches (12.0% to 43.0% MAC) with 29,542 lbs. (13,400 kg). 608.6 inches (30% MAC) with 27,337 lbs. (12,400 kg). Straight linear variation between the points given. Moment due to landing gear retraction - 10,155 in-lbs. (-117 kgf-m) (the aircraft C.G. is moved forward with the retraction). Maximum Weights Ramp 46,495 lbs. (21,090 kgf) Revision 38 Page 26 of 40 T00011AT Takeoff 46,275 lbs. (20,990 kgf) Landing 42,549 lbs. (19,300 kgf) Zero fuel 39,462 lbs. (17,900 kgf) Maximum Baggage 2,646 lbs. (1,200 kg) Fuel Capacity 1373.8 gallons (two tanks, 686.9 gallons each at +603.6 inches). Unusable fuel of 14.3 gallons (7.15 gallons for each tank). Serial Numbers Eligible 145178 and subsequent. A Brazilian Certificate of Airworthiness for Export endorsed as noted under “Import Requirements” must be submitted for each individual aircraft which application for U.S. certification is made. 12. - Model EMB-145EP, (Transport Category), Approved October 14, 2003 Engine Two – Rolls Royce Corporation (See Note 16.) Model AE 3007A, AE3007A1/1, AE3007A1, or Model AE3007A1P (See Note 12 for engine intermix operation.) Fuel Brazilian Specification CNP-08/QAV1. ASTM Specification D-1655 JET A or JET A1 MIL-T-83133A JP-8. APU Sundstrand Aerospace Model T-62T-40C11 or T-62T-40C14 Limitations as stated in Sundstrand Doc. No. ESR 0921 and No. ESR 1112 Oil Engine: MIL-L-7808 or MIL-L-23699 APU: MIL-L-23699 or MIL-L-7808 Engine Models AE3007A and AE3007A1/1 Limits Operating Conditions Static Thrust (lb.) Rotor Speed (%) Temperature Interturbine (°C) -1000ft N1 N2 ITT Takeoff 7,580 100(2) 102.5(3) 921(1) (1690° F) Maximum Continuous 6,820 100 102.5 868 (1600° F) Ground 53.6 (min), 102.5 (max) Starting 800 (1472° F) (1) Time limited to 5 minutes. (2) 100 % N1 =8,700 rpm (3) 102.5 % N2 = 16,270 rpm Engine Model AE3007A1 Limits Operating Conditions Static Thrust (lb.) Rotor Speed (%) Temperature Interturbine (°C) -1000ft N1 N2 ITT Takeoff 7,580 100(2) 102.5(3) 948(1) (1738° F) Maximum Continuous 6,820 100 102.5 901 (1653° F) Ground 53.6 (min), 102.5 (max) Starting 800 (1472° F) (1) Time limited to 5 minutes. (2) 100% N1 = 8,700 rpm (3) 102.5 % N2 =16,270 rpm Engine Model AE3007A1P Limits Operating Conditions Static Thrust (lb.) Rotor Speed (%) Temperature Interturbine (°C) -1000ft N1 N2 ITT Takeoff 8,338 100(2) 102.5(3) 948(1) (1738° F) Maximum Continuous 6,852 100 102.5(3) 901 (1653° F) Ground 53.6 (min), 102.5 (max) Revision 38 Page 27 of 40 T00011AT Starting 800 (1472° F) (1) Time limited to 5 minutes. (2) 100 % N1 =8,700 rpm (3) 102.5 % N2 = 16,270 rpm Oil Temperature Maximum: 126°C (260°F) Normal oil temperature range: 21°C to 126°C (70 at 260°F) Minimum temperature for starting: above -40°C (-40°F) for lubrication oil specified by MIL-L-23699 above -54°C (-65°F) for lubrication oil specified by MIL-L-7808 Minimum to increase N2 above 83%: 40ºC (104°F) Oil Pressure Maximum: 95 psig (This limit may be exceeded during starts if oil temperature is below 21°C (70oF)) (for Airplanes with engine FADEC software previous to version B7.6 installed). 110 psig (This limit may be exceeded during starts if oil temperature is below 21oC (70oF)) (for Airplanes with engine FADEC software version B7.6 or later approved version installed). For takeoff and go-around the maximum limit is 115 psi, limited to 5 minutes. For aircraft, which have complied with SBAE 30071-79-025 or equivalent, the maximum limit for takeoff and go around is 155 PSI, limited to 2 minutes. Minimum: 48 psig (N2 equal or above 88%) 34 psig (N2 below 88%) APU Limits (both models) Maximum RPM: 108% Maximum EGT: Steady State (Time limited to 5 minutes) 1323°F (717º C) Running (Normal) 1256°F (680° C) Airspeed Limits (EAS) Maximum Operating Limit Speed VMO: - 0 to 8,000 ft: 250 KEAS - 10,000 to 26,300 ft: 320 KEAS - 26,300 to 37,000 ft: 0.78 Mach - (Linear variation from 8,000 to 10,000 ft.) Maneuvering speed (VA): 200 KEAS Maximum flap extended speed (VFE): − Flaps 9° (Takeoff/Approach): 250 KEAS − Flaps 18° ( Takeoff) 200 KEAS (See Note 15) − Flaps 22°: 200 KEAS − Flaps 45° (Landing) : 145 KEAS Maximum landing gear extended speed (VLE): 250 KEAS Maximum landing gear operating speed (VLO): -VLO for retraction 200 KEAS -VLO for extension 250 KEAS C. G. Limits (landing gear extended) 594.4 to 619.4 inches (17.4% to 39.5% MAC) with 46,495 lbs. (21,090 kg). 594.4 to 619.4 inches (17.4% to 39.5% MAC) with 46,275 lbs. (20,990 kg). 594.0 to 619.4 inches (17% to 39.5% MAC) above 45,415 lbs. (20,600 kg). 594.0 to 623.3 inches (17% to 43% MAC) with 45,415 lbs. (20,600 kg). 588.3 to 623.3 inches (12% to 43% MAC) with 34,172 lbs. (15,500 kg). 588.3 to 623.3 inches (12% to 43% MAC) with 28,660 lbs. (13,000 kg). 619.9 inches (40% MAC) with 26,455 lbs. (12,000 kg). Revision 38 Page 28 of 40 T00011AT Straight linear variation between the points given. Moment due to landing gear retraction - 10,155 in-lbs. (-117 kgf-m) (the aircraft C.G. is moved forward with the retraction). Maximum Weights Ramp 46,495 lbs. (21,090 kgf) Takeoff 46,275 lbs. (20,990 kgf) Landing 41,226 lbs. (18,700 kgf) Zero fuel 37,699 lbs. (17,100 kgf) Maximum Baggage 2,646 lbs. (1,200 kg) Fuel Capacity 1373.8 gallons (two tanks, 686.9 gallons each at +603.6 inches). Unusable fuel of 14.3 gallons (7.15 gallons for each tank). Serial Numbers Eligible 145004 and subsequent. A Brazilian Certificate of Airworthiness for Export endorsed as noted under “Import Requirements” must be submitted for each individual aircraft which application for U.S. certification is made. Data Pertinent to all EMB-145 ( ) Models Certification Basis Federal Aviation Regulation (FAR) Part 21, including Amendments through 21-69, effective August 16, 1991; Part 25 including Amendments through 25-84, effective July 10, 1995, with the following additions: Special Condition No. 25-ANM-118: “High Intensity Radiated Fields (HIRF) Protection” (FARs 21.16, 25.1309, 25.1333 and 25.1431) Special Condition No. 25-ANM-131: “Thrust reverser systems” used as optional equipment. (FAR 21.16; for aircraft without thrust reversers, the effect of wet runway surfaces on accelerate-stop distances must be accounted for in accordance with criteria contained in NPRM 93-8 and its associated guidance; takeoff limitations for operation on wet runway surfaces must be predicated on the wet runway accelerate-stop criteria contained in NPRM 93-8). FAR 25 amendment 92 (final rule of the NPRM 93-8) was the means of compliance to the Special Condition. Special Condition No. 25-468 -SC “Flammability Requirements of Aircraft seat s Special condition” (FAR 25.853) Special Condition No. 25-673- SC, Non-Rechargeable Lithium Batteries, effective to design changes applied for after May 16, 2017. See the applicability section of this special condition for more information on which design changes must meet it. Equivalent Level of Safety Findings: - Use of 1g stall criteria (various FARs); - Cockpit underfloor access hatch and rear fuselage electronic compartment access hatch (FAR 25.783(f)); - Flight critical thrust reverser (FAR 25.933(a)(1)(ii)); ELOS Memo TC0714AT-T-P-1. - Turbine engine tailpipe fire detection (FAR 25.1203(a)); - Digital only display of turbine engine high/intermediate pressure rotor speed (N2) (FAR 25.1305(c)); ELOS Memo TC0714AT-T-P-10. -APU instrumentation and monitoring requirements (FAR 25.1305 and 25.1501(b)); and - Cabin Altitude Warning System – High Altitude takeoff and landing Operations – (FAR 25.841(b)(6)) for EMB-145XR and EMB-145LR. ELOS Memo AT0134IB-T-S-1. Optional Requirements: Optional compliance to the icing requirements of FAR 25.1419 was demonstrated. Compliance to the ditching requirements of FAR 25.801 has not been demonstrated. The EMB-145 ( ) models are approved with the thrust reversers removed. Noise Standard : FAR 36 - including amendment 36-1 through 36-21, effective January 21, 1996. Fuel venting and Revision 38 Page 29 of 40 T00011AT Exhaust Emission : FAR 34 - including amendment 34-1 through 34-2 effective January 21, 1996. Datum Is a perpendicular plane to fuselage center line located 535.5 inches forward of the center section spar of the wing (wing stub). This spar is located 114.1 inches forward of the rear jacking points. Mean Aerodynamic Chord 112.8 inches. The MAC leading edge is 574.8 inches aft of the datum. Leveling Means Plumb between the upper part hole and a mark in the lower part of the forward window frame which is located aft of the emergency exit (reference 610.7 inches). Minimum Crew Two (pilot and copilot) for all types of flight. Number of Occupants Maximum 55, including 1 pilot, 1 copilot, 2 attendants (1 required per 14 CFR §121.391), 1 observer (check pilot) and 50 passengers. Oil Capacity 3.0 gallons in each nacelle at 879.2 inches Data Pertinent to EMB-135ER and EMB-135LR Models Certification Basis Federal Aviation Regulation (FAR) Part 21, including Amendments through 21-74, effective March 12, 1997; Part 25 including Amendments through 25-84; 25-85; FAR 25.1517 from 25-86; 25-88; 25-90; FAR 25.331, 25.335(b)(2), 25.345, 25.351, 25.363, 25.371, 25.415, 25.491, 25.499 and 25.561 from 25-91; 25-93; FAR 25.807 from 25-94; and 25-97. Special Condition No. 25-ANM-118: “High Intensity Radiated Fields (HIRF) Protection” (FARs 21.16, 25.1309, 25.1333 and 25.1431) Special Condition No. 25-ANM-131: “Thrust reverser systems” used as optional equipment. (FAR 21.16; for aircraft without thrust reversers, the effect of wet runway surfaces on accelerate-stop distances must be accounted for in accordance with criteria contained in NPRM 93-8 and its associated guidance; takeoff limitations for operation on wet runway surfaces must be predicated on the wet runway accelerate-stop criteria contained in NPRM 93-8) Special Condition No. 25-438 -SC “Flammability Requirements of Aircraft seats Special condition” (FAR 25.853) Special Condition No. 25-673- SC, Non-Rechargeable Lithium Batteries, effective to design changes applied for after May 16, 2017. See the applicability section of this special condition for more information on which design changes must meet it. Exemption No. 6910 (Docket No. 29596): Allows use of 1-g stall speed instead of the minimum speed in the stall as the basis for compliance to FAR 36.201(a), Appendix C, section C36.9(e)(1). Exemption No. 6919 (Docket No. 29593): Partial grant of exemption to FAR 25.783(f), which expires on December 31, 2001. This exemption is applicable only to airplane serial numbers 145145, 145156, 145162, 145164, 145166, 145173 and 145174 which are not modified by SB 145-52-0030. Equivalent Level of Safety Findings: - Use of 1g stall criteria (various FARs); - Flight critical thrust reverser (FAR 25.933(a)(1)(ii)); ELOS Memo TC0714AT-T-P-1 - Turbine engine tailpipe fire detection (FAR 25.1203(a)); - Digital only display of turbine engine high/intermediate pressure rotor speed (N2) (FAR 25.1305(c)); ELOS Memo TC0714AT-T-P-10 and - APU instrumentation and monitoring requirements (FAR 25.1305 and 25.1501(b)). Optional Requirements: Optional compliance to the icing requirements of FAR 25.1419 was demonstrated. Compliance to the ditching requirements of FAR 25.801 has not been demonstrated. The EMB-135ER and EMB-135LR models are approved with thrust reversers removed. Revision 38 Page 30 of 40 T00011AT Part 26 – Continued Airworthiness and Safety Improvements for Transport Category Airplanes: Based on § 21.29(a) for new import TCs, or § 21.101(g) for changes to TCs, applicable provisions of Part 26 are included in the certification basis. For any future Part 26 amendments, the holder of this TC must demonstrate compliance with the applicable sections. Noise standard : FAR 36 - including amendment 36-1 through 36-21, effective January 21, 1996. Fuel venting and exhaust emission : FAR 34 - including amendment 34-1 through 34-3 effective February 3, 1999. Datum Is a perpendicular plane to fuselage center line located 456.5 inches forward of the center section spar of the wing (wing stub). This spar is located 114.1 inches forward of the rear jacking points. Mean Aerodynamic Chord 112.8 inches. The MAC leading edge is 495.8 inches aft of the datum. Leveling Means Plumb between the upper part hole and a mark in the lower part of the forward window frame which is located aft of the emergency exit (reference 531.5 inches). Minimum Crew Two (pilot and copilot) for all types of flight. Number of Occupants EMB-135ER/LR Maximum 42, including 1 pilot, 1 copilot, 2 attendants (1 required per 14 CFR §121.391), 1 observer (check pilot) and 37 passengers. Oil Capacity 3.0 gallons in each nacelle at +739.6 inches Data Pertinent to EMB-135KE and EMB-135KL Models Certification Basis Models EMB-135KE and EMB-135KL comply with all FAR 25 requirements noted above for EMB-135ER/LR models. In addition, the EMB-135KE and EMB-135KL comply with Amendment 25-98, and the following other regulations: Special Condition No. 25-673- SC, Non-Rechargeable Lithium Batteries, effective to design changes applied for after May 16, 2017. See the applicability section of this special condition for more information on which design changes must meet it. Exemption No. 7554 (Docket No. FAA -2001-0-9103-1): Allows use of 1 -g stall speed instead of the minimum speed in the stall as the basis for compliance to FAR 36.201(a), Appendix C, section C36.9(e)(1). Optional Requirements: Optional compliance to the icing requirements of FAR 25.1419 was demonstrated. Compliance to the ditching requirements of FAR 25.801 has not been demonstrated. The EMB-135KE and EMB-135KL models are approved to operate with the thrust reversers removed. Part 26 – Continued Airworthiness and Safety Improvements for Transport Category Airplanes: Based on § 21.29(a) for new import TCs, or § 21.101(g) for changes to TCs, applicable provisions of Part 26 are included in the certification basis. For any future Part 26 amendments, the holder of this TC must demonstrate compliance with the applicable sections. Noise Standard: FAR 36 - including amendment 36-1 through 36-22 effective December 13, 1999. Fuel Venting and Exhaust Emission: FAR 34 - including amendment 34-1 through 34-3 effective February 3, 1999. Datum Is a perpendicular plane to fuselage center line located 499.4 inches forward of the center section spar of the wing (wing stub). This spar is located 114.1 inches forward of the rear jacking points. Mean Aerodynamic Chord 112.8 inches. The MAC leading edge is 538.7 inches aft of the datum. Revision 38 Page 31 of 40 T00011AT Leveling Means Plumb between the upper part hole and a mark in the lower part of the forward window frame which is located aft of the emergency exit (reference 574.4 inches). Minimum Crew Two (pilot and copilot) for all types of flight. Number of Occupants EMB-135KE/KL Maximum 49, including 1 pilot, 1 copilot, 2 attendants (1 required per 14 CFR §121.391), 1 observer (check pilot) and 44 passengers. Oil Capacity 4.1 gallons in each nacelle at +739.6 inches Data Pertinent to EMB-135BJ Model Data pertinent to Legacy 600: Certification Basis Model EMB-135BJ complies with all FAR 25 requirements noted above for EMB-135ER/LR models. In addition, the EMB-135BJ complies with FAR 25.571(e)(1) of Amendment 25-96, Amendment 25-98 and the following other regulations: Special Condition No. 25-207-SC (Docket No.NM255): “Interaction of Systems and Structures” (FAR 25.1309) Special Condition No. 25-673- SC, Non-Rechargeable Lithium Batteries, effective to design changes applied for after May 16, 2017. See the applicability section of this spec ial condition for more information on which design changes must meet it. Exemption No. 7554 (Docket No. FAA -2001-0-9103-1): Allows use of 1-g stall speed instead of the minimum speed in the stall as the basis for compliance to FAR 36.201(a), Appendix C, section C36.9(e)(1). Exemption No. 7811 (Docket No. FAA-2001-9337): Side-facing divans (FAR 25.785(b)). (See Note 19.) Exemption No. 7878 (Docket No. FAA-2001-9337): Side-facing divans (FAR 25.785(b)). This exemption is applicable only to those Embraer EMB-135BJ model airplanes manufactured prior to January 1, 2004. (See Note 19.) Exemption No. 7878A (Docket No. FAA -2001-9337): Side-facing divans (FAR 25.785(b)). This exemption granted an amendment to exemption No 7878 to remove the limitation t hat restricts its applicability to airplanes manufactured before to January 1, 2004. Exemption No. 10050 from 14 CFR §§ 26.11, 26.33 26.35 26.43 26.45 26.49. Exemption No. 7909 (Docket No. FAA -2002-13283): Pressure Fueling System (FAR 25.979(b)(2)). (See Note 20.) Exemption No. 7933 (Docket No. FAA -2002-13021): Uncontrollable High Engine Thrust or Power (FAR 25.901(c)). (See Note 21) Equivalent Level of Safety (ELOS) Equivalent safety findings issued in accordance with 14 CFR part 21, §21.21(b)(1): 1. Minor Crash Landing (FARs 25.721(b) and 25.963(d) ELOS Memo No. T5124AT-T- A-2. 2. Checked Maneuver Loads FAR 25.331(c)(2), ELOS Memo No. AT5124AT-T-A-5. 3. Baggage Compartment Access Door FARs 25.787, 25.855, 25.857 (c) and 25.1447, ELOS Memo No. AT5124AT-T-A-6. 4. Airplane Operation with Air Conditioning Packs Off During Takeoff FAR 25.831(a), ELOS Memo No. AT5124AT-T-S-3. 5. Flight Critical Thrust Reverser EMB-135, EMB-145, EMB-135BJ model airplanes, FARs 25.933(a)(1)(i), (a)(1)(ii), (a)(2), 25.1309(b)(1) ELOS Memo No. TC0714AT-T-P-1. 6. Digital Only Display of Turbine Engine High/Intermediate Pressure Rotor Speed (N2) previously approved for EMB-135 model airplane. (§§ 25.901, 25.1305, 25.1309, 25.1321, & 25.1549) ELOS Memo No. TC0714AT-T-P-10. Optional Revision 38 Page 32 of 40 T00011AT Requirements: Optional compliance to the icing requirements of FAR 25.1419 at Amendment 25-72 was demonstrated. Compliance to the ditching requirements of FAR 25.801 has not been demonstrated. Part 26 – Continued Airworthiness and Safety Improvements for Transport Category Airplanes: Based on § 21.29(a) for new import TCs, or § 21.101(g) for changes to TCs, applicable provisions of Part 26 are included in the certification basis. For any future Part 26 amendments, the holder of this TC must demonstrate compliance with the applicable sections. The EMB-135BJ model is not approved with the thrust reversers removed. Noise Standard : FAR 36 - including amendment 36-1 through 36-24 effective August 7, 2002. Fuel Venting and Exhaust Emission : FAR 34 - including amendment 34-1 through 34-3 effective February 3, 1999. Datum Is a perpendicular plane to fuselage center line located 456.5 inches forward of the center section spar of the wing (wing stub). This spar is located 114.1 inches forward of the rear jacking points. Mean Aerodynamic Chord 112.8 inches. The MAC leading edge is 495.8 inches aft of the datum. Leveling Means Plumb between the upper part hole and a mark in the lower part of the forward window frame which is located aft of the emergency exit (reference 531.5 inches). Minimum Crew Two (pilot and copilot) for all types of flight. Number of Occupants EMB-135BJ Maximum 23, including 1 pilot, 1 copilot, 1 attendant (optional), 1 observer (check pilot) and 19 passengers. Oil Capacity 3,0 gallons in each nacelle at +739.6 inches Data pertinent to Legacy 650: Certification Basis: Based on September 19, 2008, date of application to the FAA, under the provisions of 14 CFR 21.101, the applicable type certification standards are as follows: - The original certification basis for the Legacy 600 is applicable for the Airworthiness and Environmental standards for components, areas, appliance and systems not affected by the type design change presented in the DCA 0145-000-00020-2008/FAA Rev F. - New compliance determination is required for the following US Title 14 CFR part 25 airworthiness standards effective February 1, 1965, including amendments 25-1 through 25-124 for components, areas, appliance and systems affected by the type design change presented in the DCA 0145-000-00020-2008/FAA Rev F: 25.1 25.2 25.5 25.21 25.23 25.25 25.27 25.29 25.31 25.101 25.103 25.105 25.107 25.109 25.111 (a)(b)(c)(d) 25.113 25.115 25.117 25.119 25.121 25.123 (a)(b) 25.125(a)(b) (c)(f)(g) 25.143 25.145 25.147 (a)(c)(d)(f) Revision 38 Page 33 of 40 T00011AT 25.149 (a)(b)(c)(d) 25.161 (a)(b)(c)(d) 25.171 25.173 25.175 25.177 25.181 25.201 25.203 25.207 25.231(a) 25.233 25.235 25.237(a) 25.251 25.253 25.255 25.301 25.303 25.305 25.307 25.321 25.331 25.333 25.335 (a)(b)(c) 25.337 (a)(b)(c) 25.341 25.343 (a)(b)(3) 25.345 (a)(b)(2)(d) 25.349 25.351 25.361 (b) 25.363 25.365 25.367 25.371 25.373 (a) 25.391 25.393 25.395 25.397 25.399 (a)(1)(b) 25.409 (c) 25.415 25.427 (a)(b)(c) 25.445 (a) 25.457 25.459 25.471 25.477 25.479 (a)(c)(d) 25.481 (a)(c) 25.483 25.485 25.487 25.489 25.491 25.493 (b)(d)(e) 25.495 25.499 (a)(b)(c)(e) 25.503 25.507 (a)(b) 25.509 (a)(1)(2)(3)(ii) 25.511 25.519 25.561 25.581 25.601 25.603 25.605 25.607 25.609 25.611 25.613 25.619 25.621 25.623 25.625 25.629 25.631 25.651 25.657 25.671 (a)(b)(c) 25.672 (b)(c) 25.675 25.677 25.683 25.685 25.689 25.693 25.697 25.699 25.701 25.703 25.721 25.729 (a)(1)(b)(c) 25.731 (a)(b)(c)(d) 25.733 (b)(c) 25.735 (a)(d)(e)(1) 25.775 25.777 (a)(b)(d) 25.785 (b)(c)(f)(1)(3) 25.787 (a)(b) 25.789 (a) 25.807 (i)(2) 25.831 (a) 25.855 (j) 25.863 25.865 25.869 (a)(3) 25.899 25.901 (a)(b)(2)(3) (c) 25.903 (a)(b)(c)(d) (e) 25.904 25.933 (a) 25.934 25.939 25.943 25.951 (a)(b)(2)(c) (d) 25.952 25.953 25.954 25.955 25.957 25.959 25.961 25.963 25.965 (a)(b) 25.967 Revision 38 Page 34 of 40 T00011AT 25.969 25.971 25.973 25.975 (a) 25.977 (a)(2)(c)(d) (e) 25.979 25.981 25.991 25.993 25.994 25.995 25.997 25.999 25.1001 (a) 25.1011 (a) 25.1013 (b)(c)(d)(e) 25.1015 25.1017 25.1019 25.1021 25.1023 25.1041 25.1043 (a)(1)(2)(b) 25.1045 (a)(b)(c) 25.1091 (a)(1) (d)(1)(2) 25.1093 (b) 25.1103 (c) (d) 25.1141 (f)(2) 25.1143 (c) 25.1181 (b) 25.1182 25.1183 25.1185 25.1187 25.1189 (a)(1)(b)(c) 25.1191 25.1193 (a)(b)(d) 25.1195 25.1199 (d) 25.1203 25.1207 25.1301 25.1303 25.1305 (a)(1)(2) (d)(1) 25.1309 25.1310 25.1316 25.1317 25.1321 (a)(c)(1) 25.1322 25.1329 (g) 25.1337 (b)(1) 25.1351 (a)(1)(d) 25.1353 (a)(c) 25.1357 (a)(c)(d)(e) 25.1360 (a)(b) 25.1419 25.1431 25.1438 (b)(c) 25.1455 25.1461 (b)(c) 25.1501 (a)(b) 25.1503 25.1505 25.1507 25.1511 25.1513 25.1515 25.1516 25.1517 25.1519 25.1521 (a)(c)(d) 25.1523 (as per App. D) 25.1527 25.1529 (as per App. H) 25.1531 25.1533 25.1541 25.1549 25.1551 25.1553 25.1555 (c) 25.1581 25.1583 (a)(1)(2)(3) 25.1585 25.1587 25.1701 25.1703 25.1705 (a)(b)(2)(4) 25.1707 (a)(b)(e)(f) 25.1709 25.1711 (e) 25.1713 25.1715 25.1717 25.1719 25.1721 (b) 25.1723 25.1725 25.1727 25.1729* * Embraer was required to demonstrate compliance with 25.1729 for the changed part of the type design, however elected to demonstrate compliance with 25.1729 for the entire airplane. Under the provisions of Title 14 CFR part 21.101(b)(3) exceptions were approved for following part 25 airworthiness standards, for which compliance was demonstrated in accordance with original certification basis applicable to Legacy 600 : a. 25.473 b. 25.571 c. 25.723 d. 25.725 Revision 38 Page 35 of 40 T00011AT e. 25.727 f. 25.1435 Special conditions: Special Conditions applicable to Legacy 600 will remain applicable for Legacy 650 unless otherwise incorporated by adopting later 14 CFR amendments. In addition, as a result of type design changes presented in DCA 0145- 000-00020-2008/FAA Rev F,, following Special Conditions have been proposed in accordance with 14 CFR § 21.16. 1. SC Limit Engine Torque Loads for Sudden Engine Stoppage Special Condition No. 25-673-SC, Non-Rechargeable Lithium Batteries, effective to design changes applied for after May 16, 2017. See the applicability section of this special condition for more information on which design changes must meet it. Equivalent Level of Safety (ELOS) Equivalent safety findings issued in accordance with 14 CFR part 21, §21.21(b)(1): 1. Minor Crash Landing – (§§ 25.721 (b), 25.963(d) ) ELOS Memo No AT0647IB-T-A-2 2. Lack of Pressurization Prevention Means for Maintenance Access Hatches previously approved for EMB-145 model airplane. (§25.783(f)) ELOS Memo No 3. Flight Critical Thrust Reverser p EMB-135, EMB-145, and EMB-135BJ model airplanes. (§§ 25.933(a)(1)(i), (a)(1)(ii), (a)(2), 25.1309(b)(1) ELOS Memo No. TC0714AT-T-P-1 4. Digital Only Display of Turbine Engine High/Intermediate Pressure Rotor Speed (N2) previously approved for EMB-135 model airplane. (§§ 25.901, 25.1305, 25.1309, 25.1321, & 25.1549) ELOS Memo No. TC0714AT-T-P-10. Exemptions Exemptions applicable to Legacy 600 will remain applicable for Legacy 650 unless otherwise amended. In addition, as a result of type design changes presented in the DCA 0145-000-00020-2008/FAA Rev D, following new exemptions have been proposed in accordance with 14 CFR 11.25: 1. Exemption from 14 CFR §§ 26.11, 26.33 26.35 26.43 26.45 26.49. Exemption No 10050 2. Exemption from § 25.981(a)(3) amendment 25-102 for fuel-tank structural lightning protection Exemption No 10138 3. Amended Exemption from § 25.901(c) - Uncontrollable high thrust failure conditions Exemption No 7933A 4. Exemption from § 25.981(a)(3) amendment 25-102 for Fuel System Wiring Installation. Exemption No 10180 5. Exemption from § 25.981(a)(3) amendment 25-102 for Fuel System Wiring Installation. Exemption No 10180A –granted time limitations extension in the current exemption by one year. 6. Exemption from §§ 25.901(c), 25.954 – Auxiliary Fuel Tank Vents. Exemption No 10213 Optional Design Regulations: Ice Protection § 25.1419 Noise Standards: 14 CFR part 36, as amended by Amendments 36-1 through 36-28, effective February 03, 2006 Revision 38 Page 36 of 40 T00011AT Fuel Venting and Exhaust Emissions Standards: 14 CFR part 34, as amended by Amendments 34-1 through 34-03, effective 03 February 1999. 14 CFR Part 26: The exemption for 14 CFR Part 26.11 granted for the EMB-135BJ (Legacy 600) is implied to be applicable to this type design change. EMBRAER was required to demonstrate compliance with § 25.1729 for the changed part of the type design, however elected to demonstrate compliance with § 25.1729 for the entire airplane. The exemption granted for 14 CFR Parts 26.33, 26.35, 26.43, 26.45 and 26.49 applicable to EMB-135BJ (Legacy 600) is implied to be applicable to this type design change Additional Design Requirements and Conditions: As a result of type design changes presented in the DCA 0145-000-00020-2008/FAA Rev F, the following subjects has been reviewed and evaluated in accordance with § 21.21(b)(2) : 1. Auxiliary Fuel Tank Penetration 2. Auxiliary Fuel Tank Protection During Survivable Crash Datum Perpendicular plane to fuselage centerline located 11595 mm forward of the center section spar of the wing (wing stub). This spar is located 2899 mm forward the aft jacking points. Mean Aerodynamic Chord 2865 mm; the MAC leading edge is 12594 mm Leveling Means Plumb between the upper part hole and a mark in the lower part of the forward window frame which is located after the emergency exit, 13500 mm of the datum Minimum Crew 2 (pilot and copilot) Number of Occupants 19 pax maximum Oil Capacity 6 liters in each reservoir Data Pertinent to EMB-145XR Models Certification Basis Model EMB-145XR complies with all FAR 25 requirements noted above for EMB-135ER/LR models. In addition, the EMB-145XR complies with FAR 25.571(e)(1) of Amendment 25-96, Amendment 25-98 and the following other regulations: Special Condition No 25-207-SC (Docket No. NM225) § 25.1309 Interaction of Systems and Structures. Special Condition No. 25-673- SC, Non-Rechargeable Lithium Batteries, effective to design changes applied for after May 16, 2017. See the applicability section of this special condition for more information on which design changes must meet it. Exemption No. 7909 (Docket No. FAA -2002-13283): Pressure Fueling System (FAR 25.979(b)(2)). (See Note 20) Exemption No. 7908 (Docket No. FAA -2002-12717) Uncontrollable High Engine Thrust or Power (FAR 25.901(c)). (See Note 21) Equivalent Level of Safety Findings: - Minor Crash Landing (FARs 25.721(b) and 25.963(d) ELOS Memo No. AT0057IB-T-A-8 ); Revision 38 Page 37 of 40 T00011AT - Checked Maneuver Loads (FAR 25.331(c)(2), ELOS Memo No. AT5124AT-T-A-5 ); - Airplane Operation with Air Conditioning Packs Off During Takeoff (FAR 25.831(a), ELOS Memo No. AT5124AT-T-S-3 ) Optional Requirements: Optional compliance to the icing requirements of FAR 25.1419 at Amendment 25-72 was demonstrated. Compliance to the ditching requirements of FAR 25.801 has not been demonstrated. The EMB-145XR model is approved with the thrust reversers removed. Part 26 – Continued Airworthiness and Safety Improvements for Transport Category Airplanes: Based on § 21.29(a) for new import TCs, or § 21.101(g) for changes to TCs, applicable provisions of Part 26 are included in the certification basis. For any future Part 26 amendments, the holder of this TC must demonstrate compliance with the applicable sections. Noise Standard : FAR 36 - including amendment 36-1 through 36-24 effective August 07, 2002. Fuel Venting and Exhaust Emission : FAR 34 - including amendment 34-1 through 34-3 effective February 3, 1999. Datum Is a perpendicular plane to fuselage center line located 535.5 inches forward of the center section spar of the wing (wing stub). This spar is located 114.1 inches forward of the rear jacking points. Mean Aerodynamic Chord 112.8 inches. The MAC leading edge is 574.8 inches aft of the datum. Leveling Means Plumb between the upper part hole and a mark in the lower part of the forward window frame which is located aft of the emergency exit (reference 610.2 inches). Minimum Crew Two (pilot and copilot) for all types of flight. Number of Occupants Maximum 55, including 1 pilot, 1 copilot, 2 attendants (1 required per 14 CFR §121.391), 1 observer (check pilot) and 50 passengers. Oil Capacity 3,0 gallons in each nacelle at +879.2 inches Data Pertinent to All Models (EMB-145( ) and EMB-135( )) Import Requirements 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. Service Information Service bulletins, structural repair manuals, vendor manuals, aircraft flight manuals, and overhaul and maintenance manuals, which contain a statement that the document is CTA approved, are accepted by the FAA and are considered FAA approved. These approvals pertain to the type design only. Changes to type design that are approved by CTA designated engineering representatives via either CTA Form FDH -200-10 or FDH -200-06( ) are also considered FAA approved. Equipment The basic required equipment as prescribed in the applicable airworthiness regulations (see Certification Basis) must be installed in the aircraft. The approved equipment is listed in the Embraer Technical Report 145-MS-370. For the EMB- 135BJ, the equipment is listed in Embraer Report 135-MS-705. Maximum Operating Altitude All Models EMB-145( ) and EMB-135( ), except EMB-135BJ: 37,000 ft (11,278 m ). Model EMB-135BJ S/N 145863 and on (or modified according to SB 145LEG-00-0007): 41,000 ft (12,497 m). Model EMB-135BJ previous to S/N 145863: 39,000 ft (11,887 m). Revision 38 Page 38 of 40 T00011AT Takeoff and Landing All Models EMB-145( ) and EMB-135( ), except EMB-135BJ: 8,000 ft (2,438 m). EMB-135BJ: 13,800 ft. (4,206m) EMB-145XR modified according to SB 145-31 -0042 or equivalent factory modification: 10,000 ft (3,048 m). EMB-145LR modified according to SB 145-21-0042 and SB 145-32-0093 or equivalent factory modification: 10,000 ft (3,048 m). Control Surfaces Rudder I:(1) 15.0° ± 1.0° left Movements 15.0° ± 1.0° right Rudder II:(1)(3) 11.0° ± 1.0° right 11.0° ± 1.0° left Elevator:(1) 27.0° ± 1.0° up 16.5° ± 1.0° down for pre-mod EO 145-056355 or SB 145-27-0043 14.0° ± 1.0° down for pos-mod EO 145-056355 or SB 145-27-0043 Ailerons:(1) 25.0° ± 1.0° up 15.0° ± 1.0° down Flap (outboard):(2) 7.5° ± 1.0° 45.0° ± 1.5° maximum deflection Flap (inboard):(2) 9.18° ± 0.8° 45.1° ± 1.5° maximum deflection Stabilizer:(1) 0° ± 0.5° neutral 4.0° + 0.5°/−0.0° up 10.0°+0.5°/−0.0° down Spring tab:(1)(3) 9.0° to 10.5° trailing edge up 12.0° to 13.5° trailing edge down for pre -mod EO 145-099134 or SB 145-27-0110 5.5° to 6.5° trailing edge down for pos-mod EO 145-099134 or SB 145- 27-0110 Servo tab:(1)(3) 8.5° ± 0.5° up for pre-mod EO 145-056355 or SB 145-27-0043 7.2° ± 0.5° up for pos-mod EO 145-056355 or SB 145-27-0043 13.0° ± 0.5° down Spoiler (inboard):(1) 52.0° ± 2.0° Spoiler (outboard):(1) 30.0° ± 2.0° (1) Deflections measured normal plane to hinge lines; (2) Deflections measured parallel to the fuselage center line and normal to wing reference plane, (3) Deflections measured are relative to the main control surface. NOTE 1 Current weight and balance report (WB-135/1562 for the EMB-135BJ and WB-145/1161 for all other EMB- 145() and EMB-135() models) including list of equipment included in certificated empty weight and loading instructions, and CTA approved U.S. Airplane Flight Manual must be provided for each aircraft at the time of original certification. The AFM may consist of either 1 or 2 volumes. The certificated basic empty weight and corresponding center of gravity location must include the total engine oil, hydraulic fluid and unusable fuel. For all the EMB-145 ( ) models and for EMB-135ER/LR models, the PN for the U.S. Airplane Flight Manual is AFM- 145/1153. For the EMB-135KE/KL models, the PN is AFM-140/1330. For the EMB-135BJ model, the PN is AFM-135/1540. NOTE 2 All placards required in either the FAA-Approved Airplane Flight Manual, the applicable operating rules or the certification basis must be installed in the airplane. NOTE 3 Except for the EMB-135BJ, all the life limitations are provided in the item A 2.2 of “Appendix 2”, “Airworthiness Limitation Requirements” of the document MRB-145/1150. Life Limitations for the EMB- 135BJ are provided in section A2.2 of “Appendix 2” of the “ Manufacturers Recommended Inspection Program,” document MPG-1483. NOTE 4 For all models except the EMB-135BJ, the Certification Maintenance Requirements are listed in section A1.2 of “Appendix 1”, of the document MRB no. 145/1150. For all models except the EMB-135BJ, the Systems and Structural Airworthiness Limitation are listed in A2.2 of “Appendix 2” of document MRB no. 145/1150. The EMB-135BJ Certification Maintenance Requirements are listed in section A1.2 of “Appendix 1” of the Revision 38 Page 39 of 40 T00011AT “Manufacturers Recommended Inspection Program,” document MPG-1483. The EMB-135-BJ Systems and Structural Airworthiness Limitations are listed in section A2.2 of Appendix 2 of the “ Manufacturers Recommended Inspection Program” document MPG-1483. Embraer Report No. 145-MS-015 for EMB-145 and EMB-135 series, and Report 135-MS-715 for the EMB- 135BJ, approved by CTA, contain the Certification Maintenance Requirements (CMR’s), retirement times for safe-life parts and the required thresholds for certain structural items. CMR’s for the engine are listed in the engine Type Certificate Data Sheet. The more restrictive requirement from these two documents shall be in force. NOTE 5 Deleted. (Previous information is included in Note 4.) NOTE 6 Deleted. (Previous information is included under “Optional Requirements” for each aircraft model.) NOTE 7 Deleted. NOTE 8 The systems containing User Modifiable Software are: - IC-600 User modifiable Check List and - FMS User Modifiable Jeppesen Data Plan Flight Plans. Modifications by the airplane operator must be submitted for FAA Approval. NOTE 9 Standby altimeter must be marked in inches/Hg. NOTE 10 Preflight Checks - The ice protection system tests referenced in the Normal Procedures section of AFM - 145/1153, AFM-140/1330 and AFM -135/1540 must be performed on the ground, daily, when flight into known or forecast icing is anticipated. This test interval may not be extended without approval of the aircraft certification office. NOTE 11 Engine and FADEC combinations installed on the EMB-145 and EMB-135 series airplanes are found in the FAA or ANAC approved technical documentation, which may include but is not limited to Embraer service bulletins. The FAA, or ANAC may approve different combinations. No intermixing of FADECS is permitted. NOTE 12 Intermix of engine models AE 3007A and AE 3007A1/1 is permissible in the Model EMB-145ER and EMB- 145EP per Embraer Service Bulletin 145-71-0006, issued December 18, 1998, or later CTA approved revision. Intermix operation requires installation of part number 23068689(*) (software version VI.6A) in all four FADEC positions or of part number 23071903(*) (software version VI.7) in all four FADEC positions. NOTE 13 (a) The airplanes EMB-145ER serial numbers 145044 and 145046 may be converted to the model EMB- 145MR if Embraer Service Bulletin No. 145-00-0002 is incorporated. (b) The airplanes EMB-145MR serial numbers 145044 and 145046 may be converted to the model EMB- 145LR if Embraer Service Bulletin No. 145-28-007 is incorporated. NOTE 14 The Models EMB-145xx and EMB-135xx are often referred to in Embraer marketing literature as the “ERJ- 145xx”, “RJ145xx”, “ERJ-135xx” or “RJ135xx”, with the appropriate model (LR, MR, ER, etc.) substituted for the “xx” . The Model EMB- 135KE is often referred to in Embraer marketing literature as the “EMB- 140ER”, “ERJ-140ER,” or “RJ-140ER”. The Model EMB-135KL is often referred to in Embraer marketing literature as the “EMB-140LR”, “ERJ-140LR,” or “RJ-140LR”. The model EMB-135BJ is often referred to in Embraer marketing literature as “Legacy”. These names are strictl y marketing designations, and are not part of the official model designations. NOTE 15 The Airplanes EMB -145MR, EMB-145ER, EMB-145EP, EMB-145MP and EMB-145LR models may be factory incorporated with Flaps 18° (Takeoff) approval with AE3007A1P Engines installed. They may also be converted to Flaps 18° (Takeoff) approval when AE3007A1P engines are installed by accomplishing Embraer Service Bulletins 145-27-0042, 145-71-0010 and 145-73-0007. The Airplanes EMB-135ER and EMB-135LR models may be factory incorporated with Flaps 18°(Takeoff) approval, or may be converted to Flaps 18° (Takeoff) approval by accomplishing Embraer Service Bulletin 145-27-0042. NOTE 16 The Engine Data Plates identifying the Engines models installed on the Aircraft models, which are the subject of this Type Certificate Data Sheet, may have either the name “Allison Engine Company” or “Rolls Royce Revision 38 Page 40 of 40 T00011AT Corporation” on them. This is a name change only, and does not affect the configuration or certification status of the engines identified in Type Certificate Data Sheet TE6CH. NOTE 17 Airworthiness Directives (ADs) with effective dates prior to July 26, 2001, with applicability to Embraer Model “EMB -135 series” were incorporated into the production of the models EMB-135KE and EMB- 135KL. Airworthiness Directives (ADs) with effective dates prior to August 23, 2002, with applicability to Embraer Model “EMB -135 series” were incorporated into the production of the model EMB-135BJ. Airworthiness Directives (ADs) with effective dates prior to October 22, 2002, with applicability to Embraer Model “EMB-145 series” were incorporated into the production of the model EMB-145XR. The document “Statement of Airworthiness Directives Status”, issued by Embraer Quality Assurance for each new aircraft, provides a complete listing of all AD modifications that were incorporated at the Embraer factory prior to first delivery. NOTE 18 The seat installation limitations are defined and approved in the Embraer technical report 135-SA -770 for each EMB-135BJ airplane. The interior configuration is defined and approved in the Embraer technical report 135-IR-708 for each EMB-135BJ airplane. For the S/N 145686 and on, the reports 135-SA -1270 and 135- IR-1208 define the seat installation limitations and the interior configuration respectively. NOTE 19 Exemption No. 7811 for side -facing divans is applicable to private use airplanes and does not have a time limitation. Exemption No. 7878 for side-facing divans is applicable to airplanes, which may be operated for hire or offered for common carriage and does have a time limitation. An EMB-135BJ airplane to which these exemptions are applicable may use either Exemption No. 7811 or Exemption No. 7878, but not both. NOTE 20 Exemption No. 7909 for pressure refueling, applic able to Embraer Models EMB-135BJ and EMB-145XR expires on June 30, 2004. No person may operate these airplanes after June 30, 2004, unless the pressure refueling panel has been modified in accordance with the terms of Exemption No. 7909. NOTE 21 As stated in Exemptions No. 7908 (EMB-145XR) and 7933 (for EMB-135BJ): The FAA has concluded that the occurrence of any uncontrollable high thrust failure condition, or any of the associated causal failures listed in Embraer letters GEC -3791/2002 and GEC-4202/2002 “may endanger the safe operation of an airplane” and hence are reportable under §121.703(c), 125.409(c), and 135.415(c). NOTE 22 EMB-135LR with S/N 145599, and any subsequent, may be configured with 18 passenger seats, other equipment and placards in accordance with Embraer reports 135-IR-008 and 135-MS -322. EMB-135LR having serial number prior may be converted to the 18 passengers seat configuration with accomplishment of an Embraer Service Bulletin approved by the CTA. NOTE 23 EMB -135BJ’s with S/N 145625 and on are configured with two Rolls Royce Corporation Engine models AE3007A1E. NOTE 24 All AE 300 7A1P engines on EMB-135BJ model aircraft which are operated following the Engine Conditioning Monitoring program as described in Chapter 5 of the AE3007A Series Engine Maintenance Manual must use the “N2 Trend Minimum Margin” listed for engine serial numbers 312181 and higher, even if engines with serial numbers 312180 or lower are installed on the aircraft. NOTE 25 The EMB-145 family has been demonstrated for Reduced Vertical Separation Minimum (RVSM) capability in compliance with FAA Memorandum 91-RVSM. Maintenance requirements necessary for the EMB -145 to continue to meet RVSM standards are provided in the EMB -145 Maintenance Review Board, MRB- 145/1150, Appendix 11 and EMB-135BJ Maintenance Planning Guide, MPG-1483, Appendix 11. Operators must obtain approval from their Flight Standards District Office or Certificate Management Office, as appropriate, to conduct flight in RVSM, Minimum Navigation Performance Specifications (MNPS), and Required Navigational Performance 10 (RNP-10) airspace. NOTE 26 From the airplanes Serial Number 145801 and on, the identification serial number changed with the inclusion of two more digits (for example, the Serial Number 145802 turned into 14500802). By the time of the implementation of this modification, an aircraft with serial number 14500801 was created but a different aircraft with serial number 145801 already existed. ----END--- ``` ## ADs (144, first 50, in force first) - [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 2025-08-07](https://openairdocs.org/ad/2025-08-07): Flight Controls · Embraer EMB-145, EMB-145ER, EMB-145MR and 4 more. Effective Jun 26, 2025 - [AD 2024-26-07](https://openairdocs.org/ad/2024-26-07): Fuselage · Embraer EMB-135ER, EMB-135KE, EMB-135KL and 8 more. Effective Mar 11, 2025 - [AD 2023-24-02](https://openairdocs.org/ad/2023-24-02): Wings · Embraer EMB-135BJ (Legacy 600), EMB-135BJ (Legacy 650) and EMB-135BJ. Effective Jan 22, 2024 - [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 2021-07-14](https://openairdocs.org/ad/2021-07-14): Main landing gear · Yaborã Indústria Aeronáutica EMB-135BJ (Legacy 600), EMB-135BJ (Legacy 650), EMB-135ER and 10 more. Effective Apr 20, 2021 - [AD 2021-04-09](https://openairdocs.org/ad/2021-04-09): Engine fuel and control · Yaborã Indústria Aeronáutica EMB-135BJ (Legacy 600), EMB-135BJ (Legacy 650), EMB-135ER and 10 more. Effective Mar 30, 2021 - [AD 2019-03-30](https://openairdocs.org/ad/2019-03-30): Engine Exhaust · Embraer EMB-135ER, EMB-135KE, EMB-135KL and 8 more. Effective Mar 26, 2019 - [AD 2017-15-16](https://openairdocs.org/ad/2017-15-16): Flight controls · Embraer EMB-135ER, EMB-135KE, EMB-135KL and 8 more. Effective Sep 5, 2017 - [AD 2017-12-09](https://openairdocs.org/ad/2017-12-09): Fuel · Embraer EMB-135BJ (Legacy 600), EMB-135BJ (Legacy 650), EMB-135ER and 10 more. Effective Jul 20, 2017 - [AD 2017-09-09](https://openairdocs.org/ad/2017-09-09): Passenger Compartment Equipment · Boeing 717-200, MD-90-30, CL-600-2C10 (Regional Jet Series 700) and 17 more. Effective Jun 28, 2017 - [AD 2017-04-12](https://openairdocs.org/ad/2017-04-12): Ice and rain protection · Embraer EMB-135BJ (Legacy 600), EMB-135BJ (Legacy 650), EMB-135ER and 10 more. Effective Mar 29, 2017 - [AD 2015-17-23](https://openairdocs.org/ad/2015-17-23): Fuel; Fuselage; Nacelles/Pylon · Embraer EMB-135BJ (Legacy 600) and EMB-135BJ (Legacy 650). Effective Oct 7, 2015 - [AD 2015-02-13](https://openairdocs.org/ad/2015-02-13): Nacelles/pylons; Fuselage · Embraer EMB-135ER, EMB-135KE, EMB-135KL and 8 more. Effective Mar 6, 2015 - [AD 2012-26-15 R1](https://openairdocs.org/ad/2012-26-15-R1): Navigation · Agusta AW139, A318-111, A318-112 and 70 more. Effective Dec 3, 2014 - [AD 2014-16-28](https://openairdocs.org/ad/2014-16-28): Fuselage · Embraer EMB-135BJ (Legacy 600) and EMB-135BJ (Legacy 650). Effective Oct 1, 2014 - [AD 2013-22-18](https://openairdocs.org/ad/2013-22-18): Fuselage · Embraer EMB-135ER, EMB-135KE, EMB-135KL and 8 more. Effective Nov 20, 2013 - [AD 2012-19-06](https://openairdocs.org/ad/2012-19-06): Stabilizers · Embraer EMB-135BJ (Legacy 600), EMB-135BJ (Legacy 650), EMB-135ER and 9 more. Effective Oct 29, 2012 - [AD 2011-21-15](https://openairdocs.org/ad/2011-21-15): Fuselage · Embraer EMB-135ER, EMB-135KE, EMB-135KL and 7 more. Effective Nov 23, 2011 - [AD 2011-01-01](https://openairdocs.org/ad/2011-01-01): Fuel · Embraer EMB-135BJ (Legacy 600). Effective Feb 9, 2011 - [AD 2011-01-09](https://openairdocs.org/ad/2011-01-09): Oxygen · Airbus A300 B2-1A, A300 B2-1C, A300 B2-203 and 290 more. Effective Feb 9, 2011 - [AD 2010-16-01](https://openairdocs.org/ad/2010-16-01): Fuel · Embraer EMB-135ER, EMB-135KE, EMB-135KL and 8 more. Effective Sep 9, 2010 - [AD 2010-16-02](https://openairdocs.org/ad/2010-16-02): Airborne Auxiliary Power · Embraer EMB-135BJ (Legacy 600), EMB-135ER, EMB-135KE and 9 more. Effective Sep 9, 2010 - [AD 2010-12-07](https://openairdocs.org/ad/2010-12-07): Wings · Embraer EMB-135ER, EMB-135KE, EMB-135KL and 8 more. Effective Jul 22, 2010 - [AD 2010-11-01](https://openairdocs.org/ad/2010-11-01): Fuselage · Embraer EMB-135BJ (Legacy 600), EMB-135ER, EMB-135KE and 9 more. Effective Jul 6, 2010 - [AD 2010-10-11](https://openairdocs.org/ad/2010-10-11): Landing gear · Embraer EMB-135BJ (Legacy 600), EMB-135ER, EMB-135KE and 9 more. Effective Jun 21, 2010 - [AD 2010-07-02](https://openairdocs.org/ad/2010-07-02): Integrated navigation units (INUs) · 328 Support Services 328-100, 328-300, Jetstream Model 4101 and 26 more. Effective May 3, 2010 - [AD 2010-03-07](https://openairdocs.org/ad/2010-03-07): Landing gear · Embraer EMB-135BJ (Legacy 600), EMB-135ER, EMB-135KE and 9 more. Effective Mar 11, 2010 - [AD 2009-26-02](https://openairdocs.org/ad/2009-26-02): Ice and rain protection · Embraer EMB-135BJ (Legacy 600), EMB-135ER, EMB-135KE and 9 more. Effective Jan 19, 2010 - [AD 2009-01-05](https://openairdocs.org/ad/2009-01-05): Maximum takeoff weight (MTOW) · Embraer EMB-145, EMB-145EP, EMB-145ER and 4 more. Effective Mar 27, 2009 - [AD 2008-22-19](https://openairdocs.org/ad/2008-22-19): Flight deck · Embraer EMB-135BJ (Legacy 600), EMB-135ER, EMB-135KE and 9 more. Effective Dec 19, 2008 - [AD 2008-17-18](https://openairdocs.org/ad/2008-17-18): Aileron control cables · Embraer EMB-135BJ (Legacy 600). Effective Oct 17, 2008 - [AD 2008-17-05](https://openairdocs.org/ad/2008-17-05): Fuel tanks · Embraer EMB-135BJ (Legacy 600), EMB-135ER, EMB-135KE and 9 more. Effective Sep 23, 2008 - [AD 2008-12-07](https://openairdocs.org/ad/2008-12-07): Fuel leakage · Embraer EMB-135BJ (Legacy 600) and EMB-145XR. Effective Jul 16, 2008 - [AD 2008-10-08](https://openairdocs.org/ad/2008-10-08): Reduces the compliance time for doing the modification · Embraer EMB-135BJ (Legacy 600), EMB-135ER, EMB-135KE and 9 more. Effective May 23, 2008 - [AD 2008-05-02](https://openairdocs.org/ad/2008-05-02): Tail section or rudder pedals · Embraer EMB-135BJ (Legacy 600), EMB-135ER, EMB-135KE and 9 more. Effective Apr 8, 2008 - [AD 2008-02-01](https://openairdocs.org/ad/2008-02-01): Adhesive tapes · Embraer EMB-135BJ (Legacy 600). Effective Feb 20, 2008 - [AD 2008-03-03](https://openairdocs.org/ad/2008-03-03): Elevator control system · Embraer EMB-135BJ (Legacy 600), EMB-135ER, EMB-135KE and 9 more. Effective Feb 14, 2008 - [AD 2007-24-03](https://openairdocs.org/ad/2007-24-03): Forward fuselage right hand (RH) side skin · Embraer EMB-135ER, EMB-135KE, EMB-135KL and 8 more. Effective Jan 2, 2008 - [AD 2007-21-12](https://openairdocs.org/ad/2007-21-12): Wiring harnesses · Embraer EMB-135BJ (Legacy 600). Effective Nov 20, 2007 - [AD 2007-17-10](https://openairdocs.org/ad/2007-17-10): Drain mast · Embraer EMB-135BJ (Legacy 600). Effective Oct 2, 2007 - [AD 2007-16-16](https://openairdocs.org/ad/2007-16-16): Valance panel lighting system wiring · Embraer EMB-135BJ (Legacy 600). Effective Sep 18, 2007 - [AD 2007-13-03](https://openairdocs.org/ad/2007-13-03): Ventral fuel tank · Embraer EMB-145XR. Effective Jul 25, 2007 - [AD 2007-11-14](https://openairdocs.org/ad/2007-11-14): Fuel level control units (LCU) · Embraer EMB-135BJ (Legacy 600). Effective Jul 5, 2007 - [AD 2007-10-11](https://openairdocs.org/ad/2007-10-11): Electrical bonding clamps · Embraer EMB-135BJ (Legacy 600), EMB-135LR, EMB-145LR and 2 more. Effective Jun 21, 2007 - [AD 2007-07-14](https://openairdocs.org/ad/2007-07-14): Forward and aft auxiliary fuel tanks · Embraer EMB-135BJ (Legacy 600). Effective May 10, 2007 - [AD 2007-04-09](https://openairdocs.org/ad/2007-04-09): Left- and right-hand windshield temperature controllers · Embraer EMB-135BJ (Legacy 600), EMB-135ER, EMB-135KE and 9 more. Effective Mar 23, 2007 - [AD 2007-04-03](https://openairdocs.org/ad/2007-04-03): Pitot static heating relay K0057 · Embraer EMB-135BJ (Legacy 600), EMB-135ER, EMB-135KE and 9 more. Effective Mar 21, 2007 - [AD 2006-26-04](https://openairdocs.org/ad/2006-26-04): Passenger seat tracks · Embraer EMB-145XR. Effective Jan 31, 2007 - [AD 2006-25-07](https://openairdocs.org/ad/2006-25-07): Fuel quantity indication system (FQIS) wire harness and the direct current (DC) fuel pump wire harness · Embraer EMB-135ER, EMB-135KE, EMB-145 and 4 more. Effective Jan 16, 2007 All 144: https://openairdocs.org/tcds/T00011AT/ads.md ## Registered aircraft by registry model (OpenAirDocs) - [Embraer EMB-145LR](https://openairdocs.org/model/embraer-emb-145lr): 204 aircraft (registry code 3260212) - [Embraer EMB-145XR](https://openairdocs.org/model/embraer-emb-145xr): 98 aircraft (registry code 3260214) - [Embraer EMB-135BJ](https://openairdocs.org/model/embraer-emb-135bj): 48 aircraft (registry codes 3260306, 3260308) - [Embraer EMB-135KL](https://openairdocs.org/model/embraer-emb-135kl): 31 aircraft (registry code 3260302) - [Embraer EMB-135LR](https://openairdocs.org/model/embraer-emb-135lr): 29 aircraft (registry code 3260305) - [Embraer EMB-135ER](https://openairdocs.org/model/embraer-emb-135er): 10 aircraft (registry code 3260307) - [Embraer EMB-145](https://openairdocs.org/model/embraer-emb-145): 7 aircraft (registry code 3260210) - [Embraer EMB-145EP](https://openairdocs.org/model/embraer-emb-145ep): 4 aircraft (registry code 3260221) - [Embraer EMB-135](https://openairdocs.org/model/embraer-emb-135): 1 aircraft (registry code 3260304) - [Embraer EMB-145ER](https://openairdocs.org/model/embraer-emb-145er): 0 aircraft (registry code 3260211) - [Embraer EMB-145MP](https://openairdocs.org/model/embraer-emb-145mp): 0 aircraft (registry code 3260216) - [Embraer EMB-145MR](https://openairdocs.org/model/embraer-emb-145mr): 0 aircraft (registry code 3260213) ## STCs approved under this data sheet (123, first 50) - [STC ST00885LA](https://openairdocs.org/stc/ST00885LA): Installation of fire extinguisher cartridges as replacements for Pacific Scientific fire extinguisher cartridges in fire extinguisher bottles.. AMETEK AMERON, LLC d/b/a MASS Systems - [STC ST02176AT-D](https://openairdocs.org/stc/ST02176AT-D): Installation of a Teledyne Mini Flight Data Acquistion Unit. AIRCRAFT RECONFIG TECHNOLOGIES, LLC - [STC ST02216AT-D](https://openairdocs.org/stc/ST02216AT-D): Installation of Teledyne Mini Flight Data Acquisition Unit in a Provisioned EMB-135/145.. AIRCRAFT RECONFIG TECHNOLOGIES, LLC - [STC ST02310AT](https://openairdocs.org/stc/ST02310AT): Installation of SAF-T-GLO photoluminescent floor proximity emergency escape path marking system (FPEEPMS). STG Aerospace Inc. - [STC ST00892LA](https://openairdocs.org/stc/ST00892LA): Installation of Emergency Vision Assurance System (EVAS).. VisionSafe LLC - [STC ST03885AT](https://openairdocs.org/stc/ST03885AT): Installation of an Avionica, Inc. avCM Cellular Module. Aircraft Systems and Manufacturing Inc. - [STC ST01409LA](https://openairdocs.org/stc/ST01409LA): Installation of a reinforced cockpit door.. Safran Cabin Inc. - [STC ST01984LA-D](https://openairdocs.org/stc/ST01984LA-D): Modification and installation of passenger seats, passenger service units and filler panels, seat track covers, and seat row placards. Safran Cabin Inc. - [STC ST04219NY](https://openairdocs.org/stc/ST04219NY): Installation of SpaceX Starlink Aviation System. Aerospace Design & Compliance LLC. - [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 ST01117DE](https://openairdocs.org/stc/ST01117DE): Installation of the Gogo ATG C1.. Peregrine - [STC ST00640DE](https://openairdocs.org/stc/ST00640DE): Installation of Tropospheric Airborne Meteorolocigal Data Reporting System (TAMDAR). FLYHT Inc. - [STC ST00079IB](https://openairdocs.org/stc/ST00079IB): Integration of Halon-free Portable Fire Extinguisher HAFEX. UMLAUT ENGINEERING GMBH - [STC ST00215IB](https://openairdocs.org/stc/ST00215IB): Installation of saf-Tglo ECO Photoluminescent Aisle Path Marking Systems. STG AEROSPACE GERMANY GmbH - [STC ST01936WI](https://openairdocs.org/stc/ST01936WI): Installation of LED lights. AeroLED's Holdings LLC - [STC ST04159CH](https://openairdocs.org/stc/ST04159CH): Upgrade of Honeywell Primus II Communications Units RCZ-8XX Transponders to support Certification of Automatic Dependent Surveillance -Broadcast (ADS-B) Out. CMD Flight Solutions LLC - [STC ST04527CH](https://openairdocs.org/stc/ST04527CH): Installation of a 16 passenger configuration. C&L STC Holdings LLC - [STC ST04635CH](https://openairdocs.org/stc/ST04635CH): Installation of Gogo Business Aviation Avance L5 Broadband System. West Star Aviation LLC - [STC ST04177NY](https://openairdocs.org/stc/ST04177NY): Installation of ALI LED Cabin Lighting, Cabin and Crew AC Power Outlets, LH Fwd Closet and Misc Cabin Mods.. C & L STC Holdings LLC - [STC ST02815LA](https://openairdocs.org/stc/ST02815LA): Installation of Airworthy R/H and L/H Stowage Units. Airworthy Incorporated - [STC ST01983WI](https://openairdocs.org/stc/ST01983WI): Installation of a folding stair in the main entrance for models equipped with a side-hinged main door.. Worldwide Aviation Engineering LLC - [STC ST01861WI](https://openairdocs.org/stc/ST01861WI): Upgrade of Honeywell Electronic Display System. Duncan Aviation Inc - [STC ST04212NY](https://openairdocs.org/stc/ST04212NY): Installation of Universal UNS-1Lw Flight Management System. C&L Engineering Services, LLC. - [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 ST00098IB](https://openairdocs.org/stc/ST00098IB): Introduction of ADS-B Out. STC Twenty One Limited - [STC ST04213NY](https://openairdocs.org/stc/ST04213NY): PAX Social Distance Floorplan Reconfiguration. C&L Engineering Services LLC - [STC ST04551AT](https://openairdocs.org/stc/ST04551AT): Installation of the Universal UNS-ILW FMS/GPS. Chippewa Aerospace Inc. - [STC ST01046DE](https://openairdocs.org/stc/ST01046DE): Installation of Datalink Communications Systems supporting Air Traffic Services (ATS) using a Honeywell Mark II+ CMU System in accordance with West Star Aviation Master Data List, Doc. No. A20311L-149, Revision D, dated August 4, 2021, or later FAA-approved revision.. West Star Aviation - [STC ST04327CH](https://openairdocs.org/stc/ST04327CH): Installation of High Speed Internet System and Wireless Activation. Nextant Aerospace LLC - [STC ST04281AT](https://openairdocs.org/stc/ST04281AT): Installation for the Upgrade of the NZ-2000 FMS computer for software version NZ6.. Chippewa Aerospace Inc - [STC ST04473CH](https://openairdocs.org/stc/ST04473CH): Installation of a Honeywell RDR -7000 Weather Radar System. Honeywell International Inc - [STC ST03158CH-D](https://openairdocs.org/stc/ST03158CH-D): Installation of a Reconfiguration of a Cabin Floorplan. Standard Aero Business Aviation Services LLC - [STC ST04525AT](https://openairdocs.org/stc/ST04525AT): Installation of the Universal Avionics Flight Management System (FMS) Model No. UNS-1LW. SKH Aerospace LLC - [STC SA9087SC-D](https://openairdocs.org/stc/SA9087SC-D): RECORE® Hamilton Sundstrand heat exchanger, P/N 816630-1 / -2 in accordance with Honeywell LORI Sealed Drawing List SDL3869-1 Rev. A, dated June 7, 2005 or later FAA approved revision.. Honeywell International Inc. - [STC ST01013DE](https://openairdocs.org/stc/ST01013DE): Installation of a Universal Avionics Systems Corporation (UASC) CVR-120A Cockpit Voice Recorder (CVR) in accordance with West Star Aviation MDL Doc # A20336L-209, Revision C, dated July 30, 2021, or later FAA-approved revision.. West Star Aviation - [STC ST00818DE](https://openairdocs.org/stc/ST00818DE): Installation of Honeywell Control Display Unit (CDU) model CD-830. Premier Air Center LLC d/b/a West Star Aviation - [STC ST04177AT](https://openairdocs.org/stc/ST04177AT): Installation of a Talon Aerospace LED Replacement General Purpose Lamps. Aaxico Technical Services Inc. - [STC ST01039DE](https://openairdocs.org/stc/ST01039DE): Passenger seating arrangement for 30 or less passengers. Deluxe Public Charter LLC - [STC ST04537NY](https://openairdocs.org/stc/ST04537NY): Installation of Air Filtration. Kilroy Aviation LLC - [STC ST09858SC](https://openairdocs.org/stc/ST09858SC): Installation of cabin automatic coffee brewing system.. Safran Cabin Germany Gmbh - [STC ST04463CH](https://openairdocs.org/stc/ST04463CH): Installation of Very High Frequency (VHF) and Iridium Antenna Installations (Provisions for Data Link Communication System) in accordance with West Star Aviation Master Data List, Doc. No. A20366L-468, Revision I/R, dated March 10, 2020, or later FAA approved revision.. West Star Aviation - [STC ST04527NY](https://openairdocs.org/stc/ST04527NY): PM-CPDLC with MKII+ CMU and VDR upgrade. 328 Support Services GmbH - [STC ST01270WI-D](https://openairdocs.org/stc/ST01270WI-D): Installation of Honeywell MK V and MK VII EGPWS Runway Awareness and Advisory System (RAAS). This approval is limited to specifically idenitfied aircraft.. Duncan Aviation Inc - [STC ST04255CH](https://openairdocs.org/stc/ST04255CH): Installation of an Automatic Dependent Surveillance-Broadcast (ADS-B Out) System. ENVOY AIR - [STC ST01008DE](https://openairdocs.org/stc/ST01008DE): Upgrade of Honeywell FMZ-2000 Flight Management Systems (FMS) VIA upgrade of NZ-2010 Navigation Computers (NZ 6.1.1). West Star Aviation - [STC ST03420NY](https://openairdocs.org/stc/ST03420NY): Installation of a Cabin Interior. Delta Engineering Corporation - [STC ST02327LA](https://openairdocs.org/stc/ST02327LA): Installation of replacement proximity sensor harness assembly part numbers used on the nose and main landing gears. Safran Electrical Components USA Inc. - [STC ST04423NY](https://openairdocs.org/stc/ST04423NY): Installation of ADS-B Out. FTI Engineering Nework GmbH - [STC ST00015IB](https://openairdocs.org/stc/ST00015IB): Installation of a Honeywell HF Communication System, model KHF 1050, with provisions for a dual installation. Embraer Engineering & Technology Center - USA Inc. - [STC ST00014IB](https://openairdocs.org/stc/ST00014IB): Installation of a second Honeywell HF Communication System, model KHF 1050. Embraer Engineering & Technology Center - USA Inc. All 123: https://openairdocs.org/tcds/T00011AT/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.