TCDS A57NM

DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION FAA TYPE CERTIFICATE DATA SHEET NO. A57NM This data sheet which is part of Type Certificate No. A57NM prescribes conditions and limitations under which the product for which the Type Certificate was issued meets the airworthiness requirements of the US Federal Aviation Regulations. Type Certificate Holder Embraer S.A. Av. Brig. Faria Lima, 2170 12227-901 São Jose dos Campos, SP Brazil Type Certificate Holder Record Yaborã Indústria Aeronáutica S.A. transferred TC No A57NM to Embraer S.A. on January 1, 2022. Embraer S.A. transferred TC No A57NM 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 November 2010. I. Model ERJ 190-100 STD (Transport Category Airplane) approved on September 2, 2005 Engines Two General Electric Aircraft Engines (GE) models: CF34-10E7, CF34-10E6, CF34-10E6A1, CF34-10E5, CF34-10E5A1. (Engine Type Certificate E00070EN) (See Note 8). Auxiliary Power Unit One – Hamilton Sundstrand APS 2300 Auxiliary Power Unit. Fuel Specifications: Brazilian Specification ANP nº 1/2003 - QAV1 ASTM D-1655 JET A or JET A1 MIL-T-83133 JP-8 Russian GOST 10227-86 (RT, TS-1 Premium and TS-1 Regular) Ukranian GSTU 320.001.499.43.011 (TS-1) Ukranian GSTU 320.001.499.43.007 (RT) Oil Types of approved oils for use in engines or APU are: Synthetic Oil conforming to MIL-PRF-23699 or MIL-PRF-7808 Engine Limits Refer to AFM No. AFM-1912. APU Limits Maximum RPM 108% Maximum EGT 717ºC (continuous) 1032ºC (start) Other limitations as stated in Hamilton Sundstrand Document No. ESR 1235. Page No. 1 2 3 4 5 6 7 8 9 10 11 12 13 14 15 16 17 18 19 20 Rev. No. 23 15 9 24 11 15 12 15 12 15 24 24 24 26 24 24 26 23 26 24 A57NM Revision 26 Embraer ERJ 190-100 STD ERJ 190-100 LR ERJ 190-100 IGW ERJ 190-100 ECJ ERJ 190-200 STD ERJ 190-200 LR ERJ 190-200 IGW ERJ 190-300 ERJ 190-400 October 1, 2025 A57NM 2 of 20 Airspeed Limits (I.A.S.) VMO 300 KIAS from sea level to 8,000 ft. increasing linearly to 320 KIAS at 10,000 ft. VMO 320 KIAS from 10,000 ft to 28,887 ft. MMO 0.82 Mach from 28,887 ft to 41,000 ft. VA (Maneuvering) 250 KIAS from sea level increasing linearly to 286 KIAS at 25,590 ft., and increasing linearly to 295 KIAS at 32,684 ft. VA (Maneuvering) 0.82 Mach from 32,684 ft to 41,000 ft. VFE (Flaps Extended) Detent 1 230 KIAS (IAS up to 25,590 ft) Detent 2 215 KIAS Detent 3 200 KIAS Detent 4 180 KIAS Detent 5 180 KIAS Detent FULL 165 KIAS Maximum Landing Gear Operating Speed (VLO): Retraction 235 KIAS Extension265 KIAS Maximum Landing Gear Extended Speed (VLE): 265 KIAS Tire Speed 225 MPH Datum A perpendicular plane to the fuselage centerline, located at 14,857 mm ahead of the wing jack points, as illustrated below. Mean Aerodynamic Chord The MAC length is 3,682 mm. Leveling Means Plumb line between the points P1 and P2 located inside of the landing gear compartment on the left side, as illustrated below. 3 of 20 A57NM Center of Gravity Limits Refer to AFM No. AFM-1912. Maximum Weights Max Ramp Weight: Max Takeoff Weight: Max Landing Weight: Max Zero Fuel Weight: 105,711 lb. (47,950 kg) 105,359 lb. (47,790 kg) 94,798 lb. (43,000 kg) 89,948 lb. (40,800 kg) Maximum Baggage Forward Cargo Compartment Aft Cargo Compartment 4,078 lb. (1,850 kg) 3,638 lb. (1,650 kg) Fuel Capacity 4,267 gallons (16,152.6 liters) in two tanks of 2,133 gallons (8,076.3 liters) each. Unusable fuel of 29.96 gallons (113.4 liters) (56.7 liters at 0.811 kg/liter in each tank). Minimum Crew 2 - Pilot and Copilot. Maximum Passenger Seating Capacity 110 maximum through S/N 190-00348. 112 maximum S/N 190-00349 and on. Oil Capacity Oil capacity per Engine: Total: 13.8 liters (14.6 US quarts) Useable: 9.4 liters (9.9 US quarts) Maximum Altitudes 41,000 ft. (operating) 10,000 ft. (takeoff and landing)* 14,000 ft. (takeoff and landing)** * Standard Altitude ** If post-mod SB 190-35-0005 Control Surface Movements Ailerons 25° TE up, 15° TE down Elevator 25° TE up, 18° TE down Stabilizer 11° TE up, 4° TE down Rudder 31.5° right, 31.5° left Ground Spoiler 60° Outboard Spoiler 40° A57NM 4 of 20 Flap and Slat Detent Inboard Flap Outboard Flap Slat 1/Slat 2,3&4 Main/Aft Main/Aft 0 0°/0° 0° 0°/0° 1 7.07°/15.36° 7.04° 12°/15° 2 10.11°/16.62° 10.06° 12°/15° 3 20.20°/19.18° 19.99° 12°/15° 4 20.20°/19.18° 19.99° 20°/25° 5 20.20°/19.18° 19.99° 20°/25° Full 37.07°/22.01° 36.49° 20°/25° Deflections are in the planes normal to the hinge lines, except for the flaps, which are in stream wise planes normal to the wing reference plane. Deflections of a surface supported by another moveable surface are relative to the parent surface. Stabilizer deflections are relative to the airplane horizontal reference. Elevator and rudder maximum deflections are scheduled by the flight control system as a function of airspeed; the data presented herein correspond to zero airspeed. See AMM for control surface deflection tolerances. Serial Numbers 19000002, 19000004, 19000006 and subsequent. II. Model ERJ 190-100 LR (Transport Category Airplane) approved on September 2, 2005 Same as model ERJ 190-100 STD, except for the following items: Maximum Weights Max Ramp Weight: 111,245 lb. (50,460 kg) Max Takeoff Weight: 110,892 lb. (50,300 kg)* 110,230 lb. (50,000 kg)** Max Landing Weight: 94,798 lb. (43,000 kg) Max Zero Fuel Weight: 89,948 lb. (40,800 kg) * Standard Weight or if post-mod SB 190-00-0003 is applied ** If post-mod SB 190-00-0002 is applied Center of Gravity Limits Refer to AFM No. AFM-1912. III. Model ERJ 190-100 IGW (Transport Category Airplane) - This model has two unique configurations, Passenger and Freighter III(a) Passenger configuration, approved on September 2, 2005 Same as model ERJ 190-100 LR, except for the following items: Maximum Weights Max Ramp Weight: 114,552 lb. (51,960 kg) Max Takeoff Weight: 114,199 lb. (51,800 kg)* Max Takeoff Weight: 101,412 lb. (46,000 kg)** Max Takeoff Weight: 110,231 lb. (50,000 kg)*** Max Landing Weight: 97,003 lb. (44,000 kg) Max Zero Fuel Weight: 90,169 lb. (40,900 kg) * Standard Weight or if post-mod SB 190-00-0009 or 190-00-0021 ** If post-mod SB 190-00-0008 *** If post-mod SB 190-00-0020 Center of Gravity Limits Refer to AFM No. AFM-1912. III(b) Freighter configuration (post-MOD SB 190-25-0270), approved on August 26, 2024 Same as model ERJ 190-100 IGW passenger configuration, except for the following items: Maximum Weights Max Ramp Weight: 114,552 lb. (51,960 kg) Max Takeoff Weight: 114,199 lb. (51,800 kg) Max Landing Weight: 97,003 lb. (44,000 kg) Max Zero Fuel Weight: 90,169 lb. (40,900 kg) Maximum Baggage Forward Cargo Compartment Aft Cargo Compartment 3,483 lb. (1,580 kg) 3,638 lb. (1,650 kg) Maximum Passenger Seating Capacity: 01 Supernumerary Center of Gravity Limits: Refer to AFM No. AFM-1912. 5 of 20 A57NM IV. Model ERJ 190-100 ECJ (Transport Category Airplane) approved on November 7, 2007 Same as model ERJ 190-100 IGW, except for the following items: Engines Two General Electric Aircraft Engines (GE) models: CF34-10E7-B (Engine Type Certificate E00070EN) (See Note 8) or CF34-10E6 (See Note 14). Airspeed Limits (I.A.S.) VA (Maneuvering) 265 KIAS from sea level increasing linearly to 269 KIAS at 15,000 ft., increasing linearly to 286 KIAS at 25,590 ft. and increasing linearly to 295 KIAS at 32,684 ft. Maximum Passenger Seating Capacity 19 maximum. Limited by requirement §25.807(g) Emergency Exits. Maximum Baggage Forward Cargo Compartment 705 lb. (320 kg) Aft Cargo Compartment 2,293 lb. (1,040 kg) Serial number 19000109 and subsequent. Maximum Weights Max Ramp Weight: 120,591 lb. (54,700 kg), 114,552 lb. (51,960 kg) (See Note 14) Max Takeoff Weight: 120,150 lb. (54,500 kg), 114,199 lb. (51,800 kg) (See Note 14) 100,000 lb. (45,360 kg)* 95,000 lb. (43,092 kg)** 90,000 lb. (40,824 kg)*** Max Landing Weight: 100,970 lb. (45,800 kg), 97,003 lb. (44,000 kg) (See Note 14) Max Zero Fuel Weight: 80,467 lb. (36,500 kg), 90,169 lb. (40,900 kg) (See Note 14) 76,212 lb. (34,570 kg)**** 77,712 lb. (35,250 kg)***** * If post-mod SB 190LIN-00-0018 ** If post-mod SB 190LIN-00-0017 *** If post-mod SB 190LIN-00-0016 **** If post-mod SB 190LIN-00-0012 ***** If post-mod SB 190LIN-00-0007R01 Fuel Capacity Maximum usable fuel: 7,194 gallons (27,232.0 liters) in two wing tanks totaling 4,268 gallons (16,155 liters) and in auxiliary fuel tanks totaling 2,926 gallons (11,077.0 liters). Maximum usable fuel: 4,267 gallons (16,152.6 liters) in two tanks of 2,133 gallons (8,076.3 liters) each (See Note 14) Unusable fuel: 43.5 gallons (165.2 liters) (72.1 liters at 0.803 kg/liter in each wing tank and 21 liters in auxiliary tanks). Unusable fuel: 29.96 gallons (113.4 liters) (56.7 liters at 0.811 kg/liter in each wing tank) (See Note 14). Center of Gravity Limits Refer to AFM No. AFM-1912. Maximum Altitudes 41,000 ft. (operating) 10,000 ft. (takeoff and landing)* 14,000 ft. (takeoff and landing)** * Standard Altitude ** If post-mod SB 190LIN-35-0004 V. Model ERJ 190-200 STD (Transport Category Airplane) approved on June 20, 2007 Same as model ERJ 190-100 LR, except for the following items: Engines Two General Electric Aircraft Engines (GE) models: CF34-10E6, CF34-10E6A1, CF34-10E5, CF34-10E5A1, CF34-10E7. (Engine Type Certificate E00070EN) (See Note 8). Airspeed Limits (I.A.S.) VA (Maneuvering) 253 KIAS from sea level increasing linearly to 288 KIAS at 25,590 ft., and increasing linearly to 295 KIAS at 32,680 ft. VA (Maneuvering) 0.82 Mach from 32,680 ft. to 41,000 ft. A57NM 6 of 20 Datum A perpendicular plane to the fuselage centerline, located at 15,670 mm ahead of the wing jack points, as illustrated below. Mean Aerodynamic Chord The MAC length is 3,682 mm. Leveling Means Plumb line between the points P1 and P2 located inside of the landing gear compartment on the left side, as illustrated below. Maximum Weights Max Ramp Weight: Max Takeoff Weight: Max Landing Weight: Max Zero Fuel Weight: 107,914 lb. (48,950 kg) 107,562 lb. (48,790 kg) 99,206 lb. (45,000 kg) 93,695 lb. (42,500 kg) Center of Gravity Limits Refer to AFM No. AFM-1912. Maximum Baggage Forward Cargo Compartment Aft Cargo Compartment 4,189 lb. (1,900 kg) 3,968 lb. (1,800 kg) Maximum Passenger Seating Capacity 124 maximum (Note 13). Serial Numbers 19000005, 19000029 and subsequent. 7 of 20 A57NM VI. Model ERJ 190-200 LR (Transport Category Airplane) approved on June 20, 2007 Same as model ERJ 190-200 STD, except for the following items: Maximum Weights Max Ramp Weight: 112,324 lb. (50,950 kg) Max Takeoff Weight: 111,971 lb. (50,790 kg)* Max Landing Weight: 99,206 lb. (45,000 kg) Max Zero Fuel Weight: 93,695 lb. (42,500 kg) Center of Gravity Limits Refer to AFM No. AFM-1912. VII. Model ERJ 190-200 IGW (Transport Category Airplane) approved on June 20, 2007 Same as model ERJ 190-200 LR, except for the following items: Maximum Weights Max Ramp Weight: 115,631 lb. (52,450 kg) Max Takeoff Weight: 115,278 lb. (52,290 kg) Max Landing Weight: 100,970 lb. (45,800 kg) Max Zero Fuel Weight: 93,915 lb. (42,600 kg) VIII. Model ERJ 190-300 (Transport Category Airplane) approved on February 28, 2018 Engines Two Pratt & Whitney Engine PW1900G series, models: PW1919G and PW1922G (Engine Type Certificate E00090EN). Auxiliary Power Unit Pratt & Whitney model APS2600[E]. Fuel Specifications: Brazilian Specification RANP37-2009 and RANP38-2011 from ANP, QAV-1 Jet Fuel ASTM Specification D1655, Grades JET A and JET A-1 neat (no additives); Specification DEF STAN 91-91 JET A-1; Specification MIL-DTL-83133 JP-8 (NATO codes F-34 / F-35) and JP-8+100 (NATO code F-37); Specification MIL-DTL-5624 JP-5; Russian Specification GOST 10227-86 grades TS-1 and RT; Ukrainian Specification GSTU 320.00149943.011 grade TS-1 and .007 grade RT; Chinese Specification GB 6537-2006, No.3. Oil Types of approved oils for use in engines or APU are: Synthetic Oil conforming to MIL-PRF-23699 or MIL-PRF-7808 Engine Limits Refer to AFM No. AFM-5692. APU Limits Maximum RPM 108% Other limitations as stated in Hamilton Sundstrand Document No. ESR 1235. Airspeed Limits (I.A.S.) VMO (Maximum operating limit speed): 300 KIAS from sea level to 8,000 ft. increasing linearly to 320 KIAS at 10,000 ft. 320 KIAS from 10,000 ft. to 28,887 ft. 0.82 Mach from 28,887 ft. to 41,000 ft. VA (Maneuvering) 265 KIAS from sea level to 15,000 ft. increasing linearly to 320 KIAS at 28,887 ft. 0.82 Mach from 28,887 ft to 41,000 ft. VFE (Flaps Extended) Detent 1 230 KIAS (IAS up to 25,590 ft) Detent 2 215 KIAS Detent 3 200 KIAS Detent 4 180 KIAS Detent 5 180 KIAS Detent FULL 165 KIAS Maximum Landing Gear Operating Speed (VLO): Retraction 220 KIAS Extension 250 KIAS Maximum Landing Gear Extended Speed (VLE): 265 KIAS Tire Speed 225 MPH A57NM 8 of 20 Datum A perpendicular plane to the fuselage centerline, located at 13,571 mm ahead of the wing jack points, as illustrated below. Mean Aerodynamic Chord The MAC length is 3,665 mm. Leveling Means Plumb line between the points P1 and P2 located inside of the landing gear compartment on the left side, as illustrated below. LEVELING OF FUSELAGE COORDINATE POINTS POINT P1 P2 X 15,881.02 15,881.02 Y -211.00 -211.00 Z -851.49 -1,736.42 Center of Gravity Limits Refer to AFM No. AFM-5692. Maximum Weights Max Ramp Weight: Max Takeoff Weight: Max Landing Weight: 124,781 lb. (56,600 kg) 124,340 lb. (56,400 kg) 108,136 lb. (49,050 kg) Max Zero Fuel Weight: 102,876 lb. (46,700 kg) Maximum Baggage Forward Cargo Compartment Aft Cargo Compartment 3,505 lb. (1,590 kg) 4,210 lb. (1,910 kg) Fuel Capacity 4,504 gallons (17,060 liters) 720 gallons (2,730 liters) in each LH or RH wing tank and 3064 gallons (11,600 liters) in center tank. Unusable fuel of 19.65 gallons (74.4 liters) (37.2 liters at 0.803 kg/liter in each wing tank). 9 of 20 A57NM Minimum Crew 2 - Pilot and Copilot. Maximum Passenger Seating Capacity 114 Oil Capacity Oil capacity per Engine: Total: 24.4 liters (25.8 US quarts) Useable: 6.1 liters (6.4 US quarts) Maximum Altitudes 41,000 ft. (operating) 14,000 ft. (takeoff and landing) Control Surface Movements Ailerons 25° TE up, 15° TE down Elevator 25° TE up, 18° TE down Stabilizer 11.6° TE up, 4.4° TE down Rudder 30.0° right, 30.0° left Ground Spoiler 60° Outboard Spoiler 40° Flap and Slat 0 0.0° 0.0° 0.0° 0.0° 1 11.2° 10.6° 7.3° 8.0° 2 11.2° 10.6° 18.2° 20° 3 21.5° 22.0° 18.2° 20° 4 25.9° 26.9° 22.8° 25° 5 25.9° 26.9° 22.8° 25° Full 33.0° 35.1° 22.8° 25° Deflections shown in degrees (°) are in the planes normal to hinge lines, excepting for the flaps, which are in stream wise planes normal to wing reference plane. Deflections of a surface supported at another movable surface are relative to the parent surface. Stabilizer defections are relative to the airplane horizontal reference. For tolerances, see AMM. Serial Numbers 19020009, and subsequent IX. Model ERJ 190-400 (Transport Category Airplane) approved on April 15, 2019 Same as model ERJ 190-300, except for the following items: Engines Two Pratt & Whitney Engine PW1900G series, models: PW1921G, PW1923G and PW1923G-A (Engine Type Certificate E00090EN). Datum A perpendicular plane to the fuselage centerline, located at 16,497 mm ahead of the wing jack points, as illustrated below. Flap setting Inboard Outboard Slat position position flap flap 1 2, 3 & 4 A57NM 10 of 20 Leveling Means Plumb line between the points P1 and P2 located inside of the landing gear compartment on the left side, as illustrated below. LEVELING OF FUSELAGE COORDINATE POINTS POINT P1 P2 X 18,807.02 18,807.02 Y -211.00 -211.00 Z -851.49 -1,736.42 Maximum Weights Max Ramp Weight: Max Takeoff Weight: Max Landing Weight: Max Zero Fuel Weight: 136,025 lb. (61,700 kg) 135,584 lb. (61,500 kg) 119,049 lb. (54,000 kg) 114,309 lb. (51,850 kg) Maximum Baggage Forward Cargo Compartment Aft Cargo Compartment 5,236 lb. (2,375 kg) 5,634 lb. (2,555 kg) Maximum Passenger Seating Capacity 146 Control Surface Movements Stabilizer 12.0° TE up, 3.5° TE down Serial Numbers 19020018, and subsequent 11 of 20 A57NM DATA PERTINENT TO MODELS ERJ 190-100 AND ERJ 190-200 EXCEPT AS INDICATED 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. Certification Basis 14 CFR part 25, effective February 1, 1965, including the following amendments: - Amendments 25-1 through 25-101 in entirety; - Amendment 25-102, §§ 25.981(a) and (b), H25.4 only; - Amendments 25-103 through 25-105 in entirety; - Amendment 25-107, § 25.731(d) and (e); § 25.735(a) through (g), and (i) through (k) only; - Amendments 25-108 through 25-110 in entirety; - Amendments 25-112 through 25-114 in entirety; - Amendment 25-117 in entirety; and - Amendment 25-120 in entirety. Note: The ERJ 190-100 ECJ (Commercially Known as Lineage 1000) auxiliary fuel tanks comply with the requirement 25.981(c) of Amendment 25-102. Special Conditions: No. 25-296-SC, consisting of the following subjects: - Interaction of Systems and Structure; - Limit Engine Torque Loads for Sudden Engine Stoppage; - Control Surface Position Awareness; - Performance Credit for ATTCS During Go-Around; - High Intensity Radiated Fields (HIRF); and - Operations without Normal Electrical Power. No. 25-559-SC, Enhanced Flight-Vision System. No. 25-685-SC, Non-Rechargeable Lithium Batteries (Effective to design changes applied for after May 31, 2017. See the applicability section of this special condition for more information on which design changes must meet it.) For the ERJ 190-100 ECJ: No. 25-372-SC, Multiple Electrical/Electronic equipment bays; and No. 25-273-SC, Flight Accessible Class C Cargo Compartment. For the ERJ 190-100 STD, 190-100 LR, and 190-100 IGW: No. 25-408-SC, Seats with Non-Traditional, Large, Non-Metallic Panels. NOTE: The FAA Special Conditions referenced above may be accessed at the FAA’s Dynamic Regulatory System website. Equivalent Level of Safety Findings: - § 25.331(c)(2), Pitch Maneuver Conditions (documented in TAD ELOS Memo TC0099IB-T-A-10); - § 25.1301, 25.1309, Equipment, Systems, and Installations (documented in TAD ELOS Memo TC0099IB-T-S-13); - § 25.933(a)(1)(ii), Flight Critical Thrust Reverser (documented in TAD ELOS Memo TC0099IB-T-P-3 for ERJ 190-100 models and TAD ELOS Memo AT0286IB-T-P-22 for ERJ 190-200 models); - 14 CFR part 25 subparts E, F, & G requirements applicable to APU installations, APU Certification Rules (documented in TAD ELOS Memo TC0099IB-T-P-4); - 14 CFR part 25 Appendix I25.4(a), ATTCS - Reduction in initial power setting to less than 90% of takeoff thrust (documented in TAD ELOS Memo TC0099IB-T-F-28); - 14 CFR part 25 Appendix I25.5(b)(4), ATTCS - Deactivation control (documented in TAD ELOS Memo TC0099IB-T-P-10); - § 25.1305(c)(3), Digital Only Display of Turbine Engine High/Intermediate Pressure Rotor Speed (documented in TAD ELOS Memo TC0099IB-T-P-18); A57NM 12 of 20 - § 25.1389(b), 25.1391, 25.1393, 25.1395, Position Light Intensities (documented in TAD ELOS Memo TC0099IB-T-S-34); - § 25.831(g), Humidity Requirement (documented in TAD ELOS Memo TC0099IB-T-S-36); - § 25.811(d)(1) and (3), Emergency Exit Locator Sign (documented in TAD ELOS Memo TC0099IB-T-C-9) (See Note 11); - § 25.811(d)(1), (2), (3) and 25.812(b)(1), Emergency Exit Sign for the ERJ 190-100 ECJ (documented in TAD ELOS Memo TD0490IB-T-C11); - § 25.841(b)(6), Cabin Altitude Warning System – High Altitude Takeoff and Landing Operations (documented in TAD ELOS Memo TD0629IB-T-S-58); - § 25.1443(c), Determination of Minimum Oxygen Flow for the Lavatory Oxygen System (documented in TAD ELOS Memo AT10108IB-T-SM-1); - § 25.1441(c), Crew Determination of Quantity of Oxygen in Lavatory Oxygen System Distributed Bottles (documented in TAD ELOS Memo AT10108IB-T-SM-2); - § 26.43, Sec. 26.45, Sec. 26.47, Three Stage Approval Process for New Repairs to Alteration Structure (documented in TAD ELOS Memo TD0756IB-T-A-1); and - § 26.43, Sec. 26.45, Sec. 26.47, DT data for Existing Unpublished Repairs to Alteration Structure (documented in TAD ELOS Memo TD0756IB-T-A-1). - § 25.1389(b), 25.1395 LED Position Light Intensities (documented in TAD ELOS Memo AT10315IB-T-S-61 - § 25.1389(b)(1) and (b)(2), 25.1391, 25.1393 Minimum Intensity of Position Lights System with Protective Tape (documented in ELOS Memorandum AT11188IB-T-25.1389-1) NOTE: The FAA Equivalent Level of Safety Memos referenced above may be accessed at the FAA’s Dynamic Regulatory System website. Exemptions: - Exemption No. 8613, 14 CFR part 25, Section 25.901(c), Uncontrollable High Thrust; and - Exemption No. 8612, 14 CFR part 25, Section 25.841(a)(2)(i) and (ii), Pressurized Cabin. For the ERJ 190-100 ECJ: - Exemption No. 9459, 14 CFR part 25, Section 25.785(b), General occupant protection for occupants of multiple-place side-facing seats that are occupied during takeoff and landing; - Exemption No. 9457, 14 CFR part 25, Section 25.785(j), Firm handhold along each aisle; and - Exemption No. 9458A, 14 CFR part 25, Section 25.813(e), Prohibits installation of interior doors in between passenger compartments. NOTE: The FAA Exemptions referenced above may be accessed at the FAA’s Dynamic Regulatory System website. Optional Requirements complied with: - Section 25.801 Ditching; - Sections 25.1411, 25.1415 Safety equipment required for ditching certification (ERJ190-100 models only); - Section 25.1403 Wing icing detection lights; - Section 25.1419 Ice protection; and - Section 25.1421 Megaphones Part 26 of the Federal Aviation Regulations: Based on § 21.29(a) for new 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. 13 of 20 A57NM Environmental Standards complied with: - All Models: 14 CFR Part 36 effective December 1, 1969, including Amendments 36-1 through 36-24, Stage 3. See the appropriate FAA Approved Airplane Flight Manual for aircraft configurations certified as Stage 3 through amendment 36-28 and for applicability of Stage 4 Noise Recertification through amendment 36-31. - ERJ 190-100 ECJ: 14 CFR Part 36 effective December 1, 1969, including Amendments 36-1 through 36-28, Stage 3. - 14 CFR Part 34 effective September 10, 1990, including all amendments effective on the TC date. Equipment The basic required equipment as prescribed in the applicable airworthiness regulations (see the Certification Basis) must be installed in the aircraft. The lists of all equipment as well as optional approved equipment are contained in the Embraer documents: - Type Design Standard Document for ERJ 190-100 No. 190-100TDSD; - Type Design Standard Document for ERJ 190-200 No. 190-200TDSD_FAA; and - Type Design Standard Document for ERJ 190-100 No. 190-100TDSD_ECJ, Airplane Flight Manual ANAC approved Airplane Flight Manual AFM-1912. Service Information Service bulletins, repair instructions (letters, drawings, specifications, forms used for transmitting repair descriptions, etc.), structural repair manuals, airplane flight manuals, vendor manuals, and overhaul and maintenance manuals that are published in the English language and indicate applicability to the U.S. approved type designs included in this Type Certificate and that include a statement “ANAC Approved” are accepted by the FAA and are considered “FAA Approved” (See Note 9). These approvals pertain to the type design only. Additionally, changes to type design that are approved by ANAC designated engineering representatives via ANAC form F-200-06 are also considered FAA approved (See Note 9). DATA PERTINENT TO MODEL ERJ 190-100 IGW post-MOD SB 190-25-0270