TCDS TC00062IB

Page No. 1 2 3 4 5 6 7 8 9 Rev. No. 14 10 10 7 14 12 7 10 17 DEPARTMENT OF TRANSPORATION FEDERAL AVIATION ADMINISTRATION TYPE CERTIFICATE DATA SHEET NO. TC00062IB This data sheet which is part of Type Certificate No. TC00062IB prescribes conditions and limitations under which the product for which the type certificate was issued meets the airworthiness requirements of Title 14 of the Code of Federal Regulations. Type Certificate Holder Embraer S.A. Av. Brigadeiro Faria Lima, 2.170 12227-901 -- São José dos Campos -- SP Brazil I. Model EMB-550, (Transport Category), (See certification basis) Approved October 21, 2014 II. Model EMB-545, (Transport Category), (See certification basis) Approved August 26, 2015 Engines: Two Honeywell AS907-3-1E Engine Type certificate E00010LA Fuel: Fuels conforming to: ASTM D1655 grade JET A and JET A1 MIL-DTL-83133 Turbine Fuels, Aviation, Kerosene Types, NATO F-34 (JP-8), NATO F-35 and JP-8+100 Brazilian Specification for Aviation Turbine Fuels CNP08 or superseding specification QAV-1 No. 3 Jet Fuel (Peoples Republic of China Specification GB6537-94 or superseding specification) Defense Standard DEF STAN 91-91 AVTUR EMB-550 approved additives are: Corrosion inhibitor per MIL-I-25017 or similar Anti-fungi additives: 1. Biobor JF 2. Kathan FP 1.5 (Rhom & Hass) Icing inhibitors (FSII) conforming to MIL-I-27686 (NATO S-748), ASTM- D4171, MIL-I-85470A, GOST 8313-88 (Russia) or similar. Note these are different than the approved additives in the Honeywell engine installation manual 24-IM-8030. TC00062IB Revision 17 Embraer EMB-545 EMB-550 August 25, 2026 TC00062IB Page 2 of 9 Rev 17 . Engine Limits: EMB-550 Static thrust lb, ambient temperature, sea level Max Continuous Takeoff 7,335 at ISA +22.5ºC 7,638 at ISA + 18ºC EMB-545 Static thrust lb, ambient temperature, sea level Max Continuous Takeoff 6,855 at ISA +22.5ºC 7,138 at ISA + 18ºC For engine operating limits see the FAA approved Airplane Flight Manual. Airspeed Limits: VMO/MMO = 320 KIAS / 0.83M For other airspeed limits, including the performance changes for the EMB-550 MOD, see the FAA approved Airplane Flight Manual. Center of Gravity Range: See the FAA Approved Airplane Flight Manual Empty Weight CG Range: None Datum: EMB-550: The Airplane Datum is a plane, perpendicular to the fuselage centerline, located 429.92 inches ahead of the wing jack points. EMB-545: The Airplane Datum is a plane, perpendicular to the fuselage centerline, located 404.4 inches ahead of the wing jack points Leveling Means: EMB-550: Located in the main door region on the omega beam between frames 11 and 12 (see the Airplane Maintenance Manual Part II Chapter 8 for further information) EMB-545: Located in the main door region on the omega beam between frames 10 and 11 (see the Airplane Maintenance Manual Part II Chapter 8 for further information) Maximum Weights: EMB-550 EMB-545 Without SB 550-042-0004 With SB 550-042-0004 MOD (See Note 4) Without SB 550-042-0004 With SB 550-042-0004 MOD (See Note 4) Max Ramp Weight 38,096 lb (17,280 kg) 38,536 lb (17,480 kg) 42,990 lb (19,500 kg) 35,406 lb (16,060 kg) 35,891 lb (16,280 kg) 37,699 lb (17,100 kg) Max Takeoff Weight 37,920 lb (17,200 kg) 38,360 lb (17,400 kg) 42,857 lb (19,440 kg) 35,274 lb (16,000 kg) 35,758 lb (16,220 kg) 37,567 lb (17,040 kg) Max Landing Weight 34,128 lb (15,480 kg) 34,524 lb (15,660 kg) 37,478 lb (17,000 kg) 32,518 lb (14,750 kg) 32,518 lb (14,750 kg) 34,172 lb (15,500 kg) Max Zero Fuel Weight 26,500 lb (12,020 kg) 26,500 lb (12,020 kg) 28,660 lb (13,000 kg) 25,904 lb (11,750 kg) 25,904 lb (11,750 kg) 25,959 lb (11,775 kg) 26,510* lb (12,025 kg) * If SB 550-00-0016 is installed or with an equivalent modification factory incorporated TC00062IB Page 3 of 9 Rev 17 . Minimum Crew: Two pilots Number of Passengers: EMB-550: Limited to 12 for step-down distance with the Type III exit. EMB-545: Limited to 9 for step-down distance with the Type III exit. Maximum Compartment Weights: EMB-550 Wardrobe 88 lb (153.15 inches aft of datum) Internal Stowage Compartment 330 lb (452.76 inches aft of datum) External Cargo Compartment 881 lb (543.30 inches aft of datum) EMB-545 Wardrobe 88 lb (153.15 inches aft of datum) Internal Stowage Compartment 330 lb (409.45 inches aft of datum) External Cargo Compartment 881 lb (500 inches aft of datum) Fuel Capacity: Total Fuel Capacity Total Usable Fuel Total Unusable Fuel EMB-550 except for EMB-550 MOD (see Note 4) 13,146 lbs 6,573 lbs each in two wing tanks at +367.72 in. 13,058 lbs 6,529 lbs each 88.6 lbs SEE NOTE 1 EMB-550 MOD (see Note 4) 16,265 lbs 6,573 lbs each in two wing tanks at +356.50 in. 1,432 lbs in a forward tank at +279.53 in. and 1,687 lbs in a ventral tank at +462.60 in. 16,145 lbs 6,529 lbs each wing tank 1,432 lbs aft tank 1,655 lbs ventral tank 120.3 lbs SEE NOTE 1 EMB-545 post-SB 550-28-0002 (or equivalent factoryincorporated modification) except for EMB-545 MOD (see Note 4) 12,940 lbs 6,470 lbs each in two wing tanks at +339.5 in. 11,925 lbs 5,962.5 lbs each 88.6 lbs SEE NOTE 1 EMB-545 pre-SB 550-28-0002 except for EMB-545 MOD (see Note 4) 10,939.7 lbs 5,469.8 lbs each in two wing tanks at +342.1 in. 10,851.1 lbs 5,425.6 lbs each 88.6 lbs SEE NOTE 1 EMB-545 MOD (see Note 4) 13,146 lbs 6,573 lbs each in two wing tanks at +367.72 in. 13,058 lbs 6,529 lbs each 88.6 lbs SEE NOTE 1 Oil Capacity (total): Tank mounted on each engine: 7.6 U.S. quarts (7.19 liters) total on each engine Maximum Operating Altitude: 45,000 ft (13,716 m). See the Approved Airplane Flight Manual - AFM 3921 TC00062IB Page 4 of 9 Rev 17 . Control Surface Movements: Elevator Up 25° ±1° Down 15° ±1° Rudder Right 30° ±1° Left 30° ±1° Aileron Up 25° ±0.8° Down 15° ±0.8° Outboard Wing Flap TO 6.56° ±1° TO/Land 19.72° ±1° Land 36.58° ±1.5° Inboard Wing Flap TO 6.77° ±1° TO/Land 20.11° ±1° Land 35.72° ±1.5° Spoiler 1 and 3 In Air 30° Inbd ±1.3° / Outbd ±1.9° On Ground 40.5° Inbd ±1.3° / Outbd ±1.9° Spoiler 2 In Air 30° ± 1.4° On Ground 43° ± 1.4 Horizontal Stabilizer Up 12° ±0.5° Down 3° ±0.5° Manufacturer’s Serial Numbers: EMB-550 (except EMB-550 MOD, See Note 4): 55000001 up to 55009999, except for 55000009, 55000020, and 55000070 EMB-550 MOD: 55000070, 55020002, 55020103 and subsequent EMB-545: 55000009, 55000020, 55010003 up to 55019999 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, EMB-545, EMB-550: 1) 14 CFR part 25, effective February 1, 1965, including Amendments 25-1 through 25-129 in their entirety. 2) Special Conditions: The following special conditions have been applied: SC No. Subject 25-475-SC Hydrophobic Coatings in Lieu of Windshield Wipers 25-476-SC Flight Envelope Protection: Performance Credit for Automatic Takeoff Thrust Control System (ATTCS) During Go-Around 25-478-SC Electronic Flight Control System: Control Surface Awareness and Mode Annunciation 25-479-SC Limit Pilot Forces for Sidestick Control 25-480-SC Design Roll Maneuver for Electronic Flight Controls 25-481-SC Interaction of Systems and Structures TC00062IB Page 5 of 9 Rev 17 . 25-482-SC Flight Envelope Protection: High Speed Limiting SC No. Subject 25-483-SC Electronic Flight Control System: lateral-Directional and Longitudinal Stability and Low Energy Awareness 25-485-SC Electrical/Electronic Equipment Bay Fire Detection and Smoke Penetration 25-486-SC Flight Envelope Protection: Pitch and Roll Limiting Functions 25-490-SC Landing Pitch over Condition 25-491-SC Dive Speed Definition With Speed Protection System 25-492-SC Flight Envelope Protection: General Limiting Requirements 25-494-SC Sudden Engine Stoppage 25-495-SC Side-Facing Seats; Installation of Airbag Systems in Shoulder Belts 25-496-SC Airplane Electronic System Security Protection From Unauthorized External Access 25-497-SC Isolation or Airplane Electronic System Security Protection from Unauthorized Internal Access 25-498-SC Sidestick Controllers 25-520-SC Flight Envelope Protection: Normal Load Factor (g) Limiting 25-520A-SC Flight Envelope Protection: Normal Load Factor (g) Limiting (EMB-550 only) 25-554-SC Installation of Rechargeable Lithium Batteries 25-557-SC Operation Without Normal Electrical Power 25-558-SC Stowage Compartment Fire Protection 25-564-SC Flight Envelope Protection: High Incidence Protection System 25-595-SC Seats With Inflatable Lap Belts (EMB-545 only) 25-603-SC Occupant Protection For Side-Facing Seats Forward of Aft-Facing Seats 25-629-SC Synthetic Vision System and Enhanced Flight Vision System on Head-Up Display 25-679-SC Non-Rechargeable Lithium Batteries (Effective to design changes applied for after May 26, 2017. See the applicability section of this special condition for more information on which design changes must meet it.) 3) Equivalent Safety Findings Equivalent Level of Safety (ELOS) findings have been made for the following regulations: TAD ELOS Memo No. Regulation Title TC0717IB-T-A-2 §§ 25.629, 25.671, 25.1309 Aeroelastic Stability Requirements TC0717IB-T-A-6 §§ 25.721, 25.963(d), 25.994 Crash Protection of Fuel Tanks and Systems TC0717IB-T-A-11 § 25.331(c)(2) Checked Maneuver Loads TC0717IB-T-A-13 §§ 25.341, 25.343, 25.345, 25.371, 35.373, 25.391, 25.1517 Gust and Turbulence Design Loads; Rough Air Speed TC0717IB-T-C-1 § 25.807 Step-down distance outside the airplane for the Type III exit located on the right side of the airplane TC0717IB-T-C-5 §§ 25.811, 25.812 Emergency Exit Marking; Emergency Lighting TC0717IB-T-C-9 §25.811(e)(4) Emergency Exit Marking AT10411IB-T-C-19 § 25.562, 25-495-SC Belted Toilet Side-Facing Seat ATD Placement on Embraer Model EMB- 545 and Model EMB-550 airplanes TC0717IB-T-F-25 § 25.255 Out of Trim Characteristics TC00062IB Page 6 of 9 Rev 17 . TC0717IB-T-P-3 § 25.1305, 25.1549(a)(b)(c) Powerplant Instruments; Powerplant and Auxiliary Power Unit TC0717IB-T-P-7 part 25 subparts E, F, and G Powerplant, Equipment, Operating Limitations and Information TC0717IB-T-P-9 § 25.1203(a) Fire Detector System TAD ELOS Memo No. Regulation Title TC0717IB-T-P-10 §§ 25.933(a)(1)(ii) Flight Critical Thrust Reverser TC0717IB-T-P-19 appendix I25.5(b)(4) Lack of On/Off Switch for ATTCS TC0717IB-T-P-24 § 25.934 Turbojet Engine Thrust Reverser System Tests TC0717IB-T-P-26 § 25.1141(f)(2) Powerplant Controls and Accessories TC0717IB-T-S-2 §§ 25.1301, 25.1309 Equipment, Systems, and Installations TC0717IB-T-S-3 § 25.671(c)(2) Flight Control System Failure Criteria TC0717IB-T-SE-2 § 25.1303(a) Flight and Navigation Instruments TC0717IB-T-SE-4 § 25.1317(b) High-Intensity Radiated Fields (HIRF) Protection TC0717IB-T-SE-5 § 25.1383(b) Landing Lights Single Switch TC0717IB-T-SE-13 §§ 25.1389(b), 25.1391, 25.1393, 25.1395, 25.1401(f) Position and Anti-Collision Lighting Systems Luminous Intensity Deviations TC0717IB-T-SM-5 § 25.841(a)(b)(6) Pressurized Cabins TC0717IB-T-SM-6 § 25.831(g) Cabin Ventilation – Humidity Requirement TC0717IB-T-SM-13 §§ 25.841(b)(1), 25.843(b)(1) Pressurized Cabins and Tests for Pressurized Cabins 4) Exemptions from 14 CFR Part 25 Exemption No. 10338, August 24, 2011. Grant of Exemption for “private, not-for-hire” operations to § 25.813(e), for configurations with interior doors installed between passengers and emergency exits. Exemption No. 10338A, August 7, 2015. This exemption granted an amendment to exemption No 10338 to add the Model EMB-545 airplane. Exemption No. 10338B, June 11, 2018. This exemption granted an amendment to exemption No 10338 to install electrically actuated interior doors installed between passengers and emergency exits. Exemption No. 10431, January 11, 2012. Grant of Exemption to § 25.981(a)(3), Relief from the requirements for fuel-tank-ignition prevention as it relates to structural lightning protection. Exemption No. 10557, June 11, 201. Partial Grant of Exemption for “private, not for hire, not for common carriage” operations to § 25.791(a), Relief to allow the installation of a single no-smoking placard located near the passenger-entry door. Exemption No. 10557A, August 7, 2015. This exemption granted an amendment to exemption No 10557 to add the Model EMB-545 airplane. Exemption No. 10757, April 25, 2013. Grant of Exemption to § 25.809(a), Relief to allow viewing the first point of contact with the ground after the exit has been opened and the evacuee is on the upper surface of the wing. TC00062IB Page 7 of 9 Rev 17 . Exemption No. 10757A, August 7, 2015. This exemption granted an amendment to exemption No 10757 to add the Model EMB-545 airplane. Exemption 10974B, December 15, 2016. Grant of Exemption to §§ 25.562(a) and 25.785(b) and Special Condition 25-495-SC number 2(e), Relief from the lower-leg flail requirements for the forward-most seat position on all side-facing seats to all Embraer model EMB-545 and EMB-550 delivered through December 31, 2017. 5) Modifications Affecting the Certification Basis Modification Certification Basis for Affected Areas EMB-550 MOD: DCA 0550-000-00026-2016 and DCA 0550-031-00067-2016 EMB-550 MOD adopts EMB-550’s Certification Basis, plus, for the components and areas affected by the change, the following additional requirements: Amendments 25-1 through 25-142 in its entirety except: 25.21(g) at Amd 25-135 25.143(c) and (h) at Amd 25-129 25.253(c) at Amd 25-135 25.571 at Amd 25-96 25.903 at Amd 25-100 25.1322 at Amd 25-38 25.1323 at Amd 25-109 25.1325 at Amd 25-108 25.1521 at Amd 25-72 25.1533 at Amd 25-92 H25.4 at Amd 25-123 and Special condition 25-520A-SC, Flight Envelope Protection: Normal Load Factor (g) Limiting 6) Optional Requirements complied with: The following Optional Design Regulations have been complied with: Ice Protection: §§ 25.1403, 25.1419 Safety Equipment: §§ 25.1411(a),(b),(c), 25.1415(e) 7) Environmental Standards 14 CFR part 36, effective December 1, 1969 including Amendments 36-1 through 36-28. 14 CFR part 34, effective September 10, 1990, including Amendments 34-1 through 34-5A. 8) RVSM Capability The aircraft is RVSM capable from S/N 55000001 and on. Each operator must obtain RVSM operating approval directly from the FAA. Additional Design Requirements and Conditions: The following design details or information must be maintained to ensure that an unsafe design condition is not present: Inflight Engine Restart: Compliance shown by test. Any modifications to the associated AFM procedures require evaluation to ensure an unsafe condition is not introduced. Changes in the engine design affecting engine restart require aircraft-level evaluation. Engine Damage from Wing Ice Caused by Cold Soaked Fuel: Compliance shown with an AFM procedure for a tactile check for wing ice. Any modification to the AFM procedure requires evaluation to ensure an unsafe condition is not introduced. TC00062IB Page 8 of 9 Rev 17 . Certification: Type Certificate TC00062IB granted October 21, 2014. Date of Application: May 14, 2009 amended to October 14, 2010 Equipment: The basic required equipment as prescribed in the applicable airworthiness regulations (see Certification Basis) must be installed in the airplane for certification. Service Information: Service bulletins, repair instructions (letters, drawings, specifications, forms used for transmitting repair descriptions, etc.), structural repair manuals, vendor manuals, AFMs, and overhaul and maintenance manuals, which contain a statement that the document is approved by ANAC are accepted by the FAA and are considered FAA approved. (These approvals pertain to the design data only.) NOTE 1. A current weight and balance report, including a list of equipment included in the certificated empty weight, and loading instructions when necessary must be provided for each aircraft at the time of original certification. The certificated empty weight and corresponding center of gravity location must include: EMB-550, except EMB-550 MOD (See Note 4) Unusable fuel 88.6 lb at 356.50 inches aft of datum Full engine oil 48.5 lb at 559.37 inches aft of datum APU oil 4.4 lb at 673.50 inches aft of datum Hydraulic Fluid 109.6 lb at 496.34 inches aft of datum EMB-550 MOD (See Note 4) Unusable fuel 88.6 lb at 356.50 inches aft of datum (wing tanks) 5.5 lb at 279.53 inches aft of datum (forward tank) 26.2 lb at 462.60 inches aft of datum (ventral tank) Full engine oil 48.5 lb at 559.37 inches aft of datum APU oil 4.4 lb at 673.50 inches aft of datum Hydraulic Fluid 109.6 lb at 496.34 inches aft of datum EMB-545 Unusable fuel 88.6 lb at 330.7 inches aft of datum Full engine oil 48.5 lb at 519.7 inches aft of datum APU oil 4.4 lb at 631.2 inches aft of datum Hydraulic Fluid 105.2 lb at 467.2 inches aft of datum EMB-545 MOD (See Note 4) Unusable fuel 88.6 lb at 330.7 inches aft of datum Full engine oil 48.5 lb at 519.7 inches aft of datum APU oil 4.4 lb at 631.2 inches aft of datum Hydraulic Fluid 105.2 lb at 467.2 inches aft of datum NOTE 2. Airplanes must be operated according to the FAA approved Airplane Flight Manual (AFM), Embraer document number: • AFM-3921-200 for the EMB-550 except the EMB-550 MOD, • AFM-3921-800 for the EMB-550 MOD, • AFM-3921-500 for the EMB-545 except the EMB-545 MOD, or • AFM-3921-850 for the EMB-545 MOD. Required placards and markings are listed in Chapter 11 of the Aircraft Illustrated Parts Catalog (AIPC) and Airplane Maintenance Manual (AMM). TC00062IB Page 9 of 9 Rev 17 . NOTE 3. The Airworthiness Limitations Section is found in Chapter 4 of the Aircraft Maintenance Manual (AMM-5613). The life limit for rotating parts on the AS907-3-1E engine is in the engine Light Maintenance Manual, Airworthiness Limitations Section. NOTE 4. The EMB-550 with the weight increase, fuel tank additions, and new winglets described in DCA 0550-000-00026-2016, “EMB-550 Performance Enhancements,” and the avionics updates described in DCA 0550-031-00067-2016, “Pro Line Fusion Avionics Load 6.3,” is often referred to in Embraer marketing literature as the “Praetor 600.” This name is strictly for marketing purposes and is not part of the official model designation. This TCDS distinguishes it as EMB550 MOD. The EMB-550, except for EMB-550 MOD, is often referred to in Embraer marketing literature as the “Legacy 500.” This name is strictly for marketing purposes and is not part of the official model designation. “PRAETOR 600E” is strictly a marketing designation of “PRAETOR 600” with a factory- incorporated “New Interior Configuration” modification (ref.: DCA 0550-025-00123- 2023/FAA), and is not part of the official model designation. The EMB-545 modified by SB 550-00-0011 to include the weight increase, fuel increase, and new winglets described in DCA 0550-000-00100-2018, “EMB-545 Weight Increase and Modified Winglet,” and modified by the avionics updates described in DCA 0550-031-00076- 2019, “Pro Line Fusion Avionics Load 6.3,” is often referred to in Embraer marketing literature as the “Praetor 500.” This name is strictly for marketing purposes and is not part of the official model designation. This TCDS distinguishes it as EMB-545 MOD. The EMB-545, except for EMB-545 MOD, is often referred to in Embraer marketing literature as the “Legacy 450.” This name is strictly for marketing purposes and is not part of the official model designation. “PRAETOR 500E” is strictly a marketing designation of “PRAETOR 500” with a factory- incorporated “EMB-545 New Interior Configuration” modification (ref.: DCA 0550-025-00123- 2023/FAA and DCA 0550-025-00122-2023/ANAC), and is not part of the official model designation. NOTE 5. The EMB-550 FAA type design definition is contained in Embraer document number 550TDSD002, "Type Design Standard Document.” The EMB-545 FAA type design definition is contained in Embraer document number 550TDSD005, "Type Design Standard Document.” NOTE 6: Serial numbers 55000073, 55000074, 55000076, 55000080, 55010014, 55010029 and 55010039 were produced by Embraer Executive Aircraft Inc. in Melbourne, Florida, under the Type Certificate. END