# TCDS A60CE: Embraer S.A. - Type: Type certificate data sheet - Status: Current - Holder: Embraer S.A. - Revision: 14 - Revised: September 17, 2025 - Product: Aircraft, Small Airplane - Certification basis: Part 23 - Registered aircraft: 675, by the registry models matched to it (OpenAirDocs) - Data sheet PDF: https://openairdocs.org/files/sha256/e8/f1/e8f1f2d0f42bf359a7834016b06b9fe06eebcdafab5fa54f673ebb50efb01ee1 - FAA DRS: https://drs.faa.gov/browse/excelExternalWindow/DRSDOCID171918181720250918163319.0001 - Page: https://openairdocs.org/tcds/A60CE ## Models (1) As the data sheet lists them. - EMB-505 ## 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 Rev. No. 14 11 11 14 13 14 14 14 14 DEPARTMENT OF TRANSPORATION FEDERAL AVIATION ADMINISTRATION A60CE Revision 14 Embraer S.A. EMB-505 September 17, 2025 TYPE CERTIFICATE DATA SHEET NO. A60CE This data sheet which is part of Type Certificate No. A60CE 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 412227-901 -- São José dos Campos -- SP Brazil Type Certificate Holder Record Empresa Brasileira de Aeronáutica S.A. (EMBRAER) changed company name to Embraer S.A. effective November 19, 2010. I. Model EMB-505, (Commuter Category), (See certification basis) Approved December 14, 2009 Engines: Two Pratt & Whitney Canada PW535E turbofans Engine TC #E00053EN Certified December 11, 2009 OR Two Pratt & Whitney Canada PW535E1 turbofans Engine TC #E00053EN – Certified September 5, 2019 Fuel: ASTM Specification D1655-JET A and JET A-1, Military Specification MIL-DTL-83133-JP8, Brazilian Specification CNP08-QAV-1 Russian Specification GOST 10227-86 TS-1 (Use the latest version of the Standard Specifications) Engine Limits: Static thrust standard day, sea level Engine Model PW535E PW535E1 Takeoff 3,360 lb. (1,494.6 daN) 3,478 lb. (1,547.1 daN) ATR (5 minutes) 3,360 lb. (1,494.6 daN) 3,478 lb. (1,547.1 daN) ATR (10 minutes) 3,360 lb. (1,494.6 daN) (see NOTE 8) 3,478 lb. (1,547.1 daN) Maximum permissible engine rotor operating speeds (Takeoff and Maximum Continuous) N1 (fan) 100% (100% = 15,850 rpm) N2 (Gas Gen.) 101% (101% = 34,310 rpm) N1 Transient (operation 20 sec.) 102% (102% = 16,167 rpm) N2 Transient (operation 20 sec.) 103% (103% = 34,989 rpm) A60CE Page 2 of 9 Engine Limits, Continued: Maximum permissible interturbine gas temperatures Takeoff 700 Degrees C ATR 725 Degrees C Max. continuous 680 Degrees C Transient (starting 5 sec.) 740 Degrees C 765 Degrees C (see NOTE 8) Transient (operation 20 sec.) 740 Degrees C 765 Degrees C (see NOTE 8) Airspeed Limitations: VMO (maximum operating) Sea level to 26,000 ft. 320 KIAS Sea level to 27,600 ft. 320 KIAS (see NOTE 11) MMO above 26,000 ft. 0.78 Mach MMO above 27,600 ft. 0.80 Mach (see NOTE 11) VFE (maximum flap extended) 8 degrees (takeoff) 180 KIAS 26 degrees (takeoff/landing) 170 KIAS 35 degrees (takeoff/landing) 160 KIAS (see NOTE 9) VMC (minimum control speed) For takeoff 97 KIAS For takeoff 99 KIAS (see NOTE 11) Note – The value presented above refers to the maximum VMC for the aircraft envelope (the value can change according to the temperature, altitude, weight, and flaps) VLO (landing gear operating) Gear Retract and Extent 250 KIAS VLE (landing gear extended) 250 KIAS Maximum tire ground speed 182 Knots Center of Gravity Limits: Forward Limits: Takeoff and Landing (landing gear extended) From 293.57 in. of the datum (36% MAC) at 11,354 lb. to 284.69 in. of the datum (25% MAC) at 12,346 lb. and to 279.84 in. of the datum (19% MAC) at 15,102 lb. and to 279.84 in. of the datum (19% MAC) at 17,968 lb up to 280.17 in. of the datum (19.4% MAC) at 18,387 lb. In-Flight extension From 284.69 in. of the datum (25% MAC) at 12,346 lb. to 278.23 in. of the datum (17% MAC) at 15,102 lb. and to 278.23 in. of the datum (17% MAC) at 18,387 lb. Aft Limits: Takeoff and Landing (landing gear extended) From 298.41 in. of the datum (42% MAC) at 11,354 lb. to 295.82 in. of the datum (38.8% MAC) at 14,220 lb. up to 289.77 in. of the datum (31.3% MAC) at 18,387 lb. A60CE Page 3 of 9 Center of Gravity Limits, Continued: In-Flight extension From 295.82 in. of the datum (38.8% MAC) at 14,220 lb. to 292.19 in. of the datum (34.3% MAC) at 18,387 lb. Moment due to landing gear retraction: (-4,531.67 in.-lb.) The aircraft CG is moved forward with the retraction. For aircraft equipped with PW535E1 engines: Forward Limits: Takeoff and Landing (landing gear extended) From 293.6 in. of the datum (36% MAC) at 11,354 lb. to 284.7 in. of the datum (25% MAC) at 12,346 lb. and to 279.8 in. of the datum (19% MAC) at 15,102 lb. and to 279.8 in. of the datum (19% MAC) at 17,648 lb. up to 280.3 in. of the datum (19.6% MAC) at 18,551 lb. In-Flight extension From 284.7 in. of the datum (25% MAC) at 12,346 lb. to 278.2 in. of the datum (17% MAC) at 15,102 lb. and to 278.2 in. of the datum (17% MAC) at 17,648 lb. and to 278 .7 in. of the datum (17.6% MAC) at 18,551 lb. Aft Limits: Takeoff and Landing (landing gear extended) From 298.4 in. of the datum (42% MAC) at 11,354 lb. to 295.7 in. of the datum (38.7% MAC) at 14,263 lb. up to 289.5 in. of the datum (31.0% MAC) at 18,551 lb. In-Flight extension From 295.7 in. of the datum (38.7% MAC) at 14,263 lb. to 291.9 in. of the datum (34.3% MAC) at 18,551 lb. Moment due to landing gear retraction: (-4,531.67 in.-lb.) The aircraft CG is moved forward with the retraction. Notes: In-Flight Extension is a region on the Weight × CG Envelope not allowed for landing or takeoff. Consider straight linear variation between the given points. Consider all points located after aircraft reference Datum. Datum: Reference Datum is located 90 inches forward and 6.06 inches leftward of the nose jack pad position. Leveling Means: Located in the main door region on the omega beam between frames 11 and 12 (see AMM for further information) A60CE Page 4 of 9 Maximum Weight: Takeoff 17,968 lb. 18,387 lb. (see NOTE 10) 18,551 lb. (see NOTE 11) Landing 16,865 lb. 17,042 lb. (see NOTE 10) 17,272 lb. (see NOTE 11) Zero Fuel 13,999 lb. 14,220 lb. (see NOTE 10) 14,263 lb. (see NOTE 11) 14,440 lb. (see NOTE 10 and NOTE 18) 14,484 lb. (see NOTE 11 and NOTE 18) Ramp 18,078 lb. 18,497 lb. (see NOTE 10) 18,617 lb. (see NOTE 11) Minimum Crew for all Flights (See NOTE 5 for cockpit equipment/arrangement restrictions): One pilot (in the left pilot seat) plus additional equipment as specified in the Limitations Section of the FAA Approved Airplane Flight Manual (AFM) OR One pilot and one copilot No. of Seats: Maximum of eleven occupants. Refer to the AFM, section 6 “Weight & Balance” for seat configurations and moment arms. Maximum Baggage: Forward baggage compartment 110 lb. (39.37 in. aft of datum) Aft baggage compartment 463 lb. (396.85 in. aft of datum) LH forward cabinet 44 lb. (135.83 in. aft of datum) RH refreshment center 71 lb. (146.06 in. aft of datum) Lavatory cabinet 33 lb. (318.11 in. aft of datum) Some airplanes have stowage compartments in the LH forward cabinet, Lavatory cabinet, RH refreshment center and Aft baggage compartment with higher load capacities. Refer to their respective placards to find this information. Fuel Capacity (usable): Total usable fuel 5,353.2 lb. (2,428.2 kg.) @ 6.701 lb./US gal. (0.803 kg./liter) Two wing tanks with ~ 2,676.6 lb. (1,214 kg.) usable each; 275.59 in. aft of datum; For aircraft equipped with PW535E1 engines: Total usable fuel 5,402.2 lb. (2,450.4 kg.) @ 6.701 lb./US gal. (0.803 kg./liter) Two wing tanks with 2,701.1 lb. (1,225.2 kg.) usable each; 275.98 in. aft of datum (see NOTE 1 for unusable fuel) Oil Capacity (total): Tank mounted on each uninstalled engine: 8.6 U.S. quarts (8.14 liter) total each engine; 386.85 in. aft of datum; (see NOTE 1) Volume to fill "dry" engine to "Max" level installed engine: PW535E Pre SB 30488 PW535E Post SB 30488 and PW535E1 Left engine 10.47 US quarts 9.81 US quarts Right engine 9.53 US quarts 9.33 US quarts A60CE Page 5 of 9 Maximum Operating Altitude: 45,000 ft. Control Surface Movements: Elevator Up 25 +1/-1 degrees Down 15 +1/-1 degrees Elevator Trim Tab Up 2.7 +1/-1 degrees Down 9.3 +1/-1 degrees Rudder Right 34 +1/-1 degrees Left 34 +1/-1 degrees Rudder Trim Tab Right 17 +2/-1 degrees Left 17 +2/-1 degrees Aileron Up 25 +0.5/-0.5 degrees Down 15 +0.5/-0.5 degrees Aileron Trim Tab Up 18 +2/-1 degrees Down 18 +2/-1 degrees Outboard Wing Flap TO 8 +1/-1 degrees TO/Land 26 +1/-1 degrees Land 35 +1.5/-1.5 degrees Inboard Wing Flap TO 7.8 +1/-1 degrees TO/Land 25 +1/-1 degrees Land 33.4 +1.5/-1.5 degrees (see NOTE 9) Horizontal Stabilizer Up 2 +0.5/-0.5 degrees Down 13 +0.5/-0.5 degrees Ventral Rudder Right 30 +1/-1 degrees Left 30 +1/-1 degrees See Airplane Maintenance Manual (AMM) for rigging instructions. Manufacturer's Serial Numbers: 50500004 and up Import Requirements: A U.S. airworthiness certificate may be issued on the basis of a Brazilian Certificate of Airworthiness for Export signed by a representative of the Agência Nacional De Aviação Civil (ANAC) containing the following statement: " The aircraft covered by this certificate has been examined and found to comply with U.S. Type Certificate No. A60CE and to be in a condition for safe operation." Refer to the applicable bilateral agreement to verify eligibility for import into the United States of both new and used aircraft based on the scope of the agreement, to identify any required statements by the exporting authority on the export certificate of airworthiness (or equivalent document), and for procedures for coordinating exceptions to conformity statements on these documents. Refer to FAA Order 8130.2, Airworthiness Certification of Aircraft, for requirements for issuance of an airworthiness certificate for imported aircraft. A60CE Page 6 of 9 Certification Basis - Model EMB-505: (1) Part 23 of Title 14 of the Code of Federal Regulations effective February 1, 1965, as amended by Amendments 23-1 through 23-57 (a) Design changes that comply with additional regulations at Amendment 23-64 or later and have airworthiness standards prescribed in accordance with § 23.2000, are specified in NOTES 15, 16, and 17. The detailed design standards (DDS) used as a means of compliance in accordance with § 23.2010 for these design changes are documented in the Embraer DDS Summary Report No. 505CCO004 – EMB-505 DDS REPORT. (2) Part 36 of Title 14 of the Code of Federal Regulations effective December 1, 1969, as amended by Amendments 36-1 through 36-28 (Amendments 36-1 through 36-31 for aircraft equipped with PW535E1 engines), Stage 4. (3) Part 34 of Title 14 of the Code of Federal Regulations effective September 10, 1990, as amended by Amendments 34-1 through 34-3. (4) Special Conditions as follows: (a) 23-235-SC, Full Authority Digital Engine Control (FADEC) System (b) 23-243-SC, High Altitude Operations (c) 23-244-SC, Ice Protection - Auto Inhibited Anti-ice System (d) 23-242-SC, Flight Performance, Flight Characteristics, and Operating Limitations (e) 23-241-SC, High Fuel Temperature (f) 23-254-SC, Single-Place Side-Facing Lavatory Seat Dynamic Test Requirements, issued August 31, 2011 (See NOTE 12) (g) 23-257-SC, Inflatable Side-Facing Seat Three-Point Restraint Safety Harness with an Integrated Airbag Device in the Side-Facing Divan Aft Position, issued March 16, 2012 (See NOTE 13) (5) Equivalent levels of safety as follows: (a) ACE-09-01: 14 CFR § 23.1555(d)(1); Control Markings - Usable Fuel Capacity (b) ACE-10-01: 14 CFR §§ 23.1305, 23.1309, 23.1321 and 23.1549; Digital Only Display of N2, Oil Temperature, Oil Pressure, and Fuel Flow (c) ACE-09-12: 14 CFR § 23.608 and 23.807; Ditching Emergency Exits (d) ACE-09-17: 14 CFR § 23.1553; Digital Fuel Quantity Indication (e) ACE-09-18: 14 CFR § 23.815; Cabin Aisle Width (f) ACE-10-02: 14 CFR § 23.855(c); Cargo and Baggage Compartment Fire Protection (g) ACE-10-05: 14 CFR § 23.5(b)(4); ATR Function Deactivation (h) ACE-10-04: 14 CFR § 23.841(b); Cabin Pressurization for High Altitude Takeoff and Landing Operations (i) ACE-10-03: 14 CFR §§ 23.1389(b), 23.1391, 23.1393, 23.1395; Position Light Intensity Requirements (j) ACE-09-11: 14 CFR § 23.853(d)(2); No Smoking Placard (k) AT01032CE-A-P-2: 14 CFR § 23.1549(b); Powerplant Instruments – Normal Operating Range Color (l) ACE-13-05: 14 CFR § 23.672(c)(1); Spoiler Control System (See NOTE 9) (m) AT00921CE-A-C-1: 14 CFR § 23.815(b); Aisle Height at Video Monitor (See NOTE 14) (n) AT11224IB-A-P-2: 14 CFR §§ 23.779(b)(1), 23.1143(c); Motion and Effect of Cockpit Control and Engine (See NOTE 17) A60CE Page 7 of 9 Certification Basis, Continued: (6) Exemptions as follows: (a) No. 9550A granted to use a relaxed “Dutch Roll” damping criteria above 18,000 ft. in lieu of damping criteria of 14 CFR § 23.181(b), issued June 14, 2009, Regulatory Docket No. FAA-2007-28080 (b) No. 9302B granted to address the requirement 23.3(d), issued March 17, 2010, Regulatory Docket No. FAA-2006-26659 (see NOTE 7) (c) No. 10321 granted to address the requirement 23.562(a), issued July 20, 2011. Regulatory Docket No. FAA-2011-0336 (See NOTE 13) (7) Compliance with ice protection has been demonstrated in accordance with 14 CFR § 23.1416 and 23.1419 and special conditions 23-244-SC. (8) Not approved for ditching. Compliance with the provisions for ditching equipment in accordance with 14 CFR § 23.1415(a)(b) has not been demonstrated. Type Certificate A60CE issued December 14, 2009. Application for type certificate dated October 9, 2006 (extended to February 28, 2007). RVSM Approval: S/N 50500004 and on: All airplanes are equipped with dual Goodrich Smart Probe RVSM capable Air Data Computers, and Garmin G1000 or G3000 pilot’s and copilot’s Primary Flight Displays as standard equipment. Each operator must obtain RVSM operating approval directly from the FAA. Production Basis: Production Certificate No. 346CE The manufacturer Embraer Executive Aircraft Inc. located in Melbourne, Florida, is licensed by Embraer S.A. to manufacture the Model Aircraft listed in this Type Certificate Data Sheet. S/N 50500118 and subsequent may be produced either by Embraer Executive Aircraft Inc. in Melbourne, Florida or Embraer S.A. in Brazil. The manufacturer can be confirmed by the aircraft data plate. Aircraft produced by Embraer Executive Aircraft Inc. in Melbourne, Florida with a S/N 50500118 or 50500122 were produced under the Type Certificate. 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, 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 t he design data only). NOTES: 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: Unusable fuel 50.26 lb. at 6.701 lb./US gal. at 256.22 in. aft of datum Full engine oil 35.27 lb. at 386.85 in. aft of datum; includes the oil from the engine installation (filters and lines) Hydraulic Fluid 19.40 lb. at 313.50 in. aft of datum A60CE Page 8 of 9 NOTES, continued: NOTE 2. Airplanes must be operated according to the FAA Approved AFM, part number AFM- 2665, dated December 11, 2009 or later approved revision. Required placards and markings are listed in Chapter Eleven (11) of the Aircraft Illustrated Parts Catalog (AIPC) and AMM. NOTE 3. See AMM, Chapter Four (4), "Airworthiness Limitations" for Systems Airworthiness Limitations, Structure Airworthiness Limitations (ALI) and Life-Limited Items (LLI). The life limit for rotating parts on the PW535E/PW535E1 engine is in the Airworthiness Limitations Manual, Pratt & Whitney Canada P/N 3072702, latest revision. NOTE 4. All replacement seats (crew and passenger), although they may comply with TSO C127, must also be demonstrated to comply with installation requirements into the aircraft listed in 14 CFR §§ 23.2, 23.561, 23.562, and 23.785. The foam cushion buildup of all seats (crew and passenger) may not be altered. Any deviations in the foam construction or stiffness must be demonstrated by test or analysis to comply with the 14 CFR 23.562 paragraph. NOTE 5. Approval for operation with a minimum crew of one pilot is based upon the cockpit equipment installation and arrangement evaluated during FAA certification testing. No significant changes may be made to the installed cockpit equipment or arrangement (EFI S, autopilot, avionics, etc.), except as permitted by the approved MMEL, without prior approval from the responsible Aircraft Certification Office. NOTE 6. The EMB-505 is often referred to in Embraer marketing literature as the “PHENOM 300” and “Phenom 300E”. These names are strictly marketing designations and are not part of the official model designation. NOTE 7. The EMB-505 is not eligible for operations under 14 CFR part 121. NOTE 8. For airplanes equipped with FADEC software version 4.3. Post SB 505-73-0001 incorporation or with an equivalent factory-incorporated mod. NOTE 9. For airplanes equipped with the Flap Full Utilization mod. Post SB 505-27-0011 incorporation or with an equivalent factory-incorporated mod. NOTE 10. For airplanes equipped with Increased Maximum Operating Weights. Post SB 505-00- 0008 incorporation or with an equivalent factory-incorporated mod. NOTE 11. For airplanes equipped with PW535E1 engines. NOTE 12. For airplanes equipped with the Belted Toilet System Installation mod. Post SB 505-25- 0004 or SB 505-25-0011 incorporation or with an equivalent factory-incorporated mod. NOTE 13. For airplanes equipped with the 2-Place Side Facing Seat Installation mod. Post SB 505- 25-0038 incorporation or with an equivalent factory-incorporated mod. NOTE 14. For airplanes equipped with an Aisle Video Monitor. NOTE 15. For airplanes equipped with the Garmin Flight Stream 510 (FS510) mod. Post SB 505-46- 0001 or with an equivalent factory-incorporated mod. The following additional regulations at Amendment 23-64 apply: §§ 23.2010, 23.2500(b), 23.2505, and 23.2510. A60CE Page 9 of 9 NOTES, continued: NOTE 16. For airplanes equipped with the Autothrottle mod. Post SB 505-22-0007 or with an equivalent factory-incorporated mod. The following additional regulations at Amendment 23-64 apply: §§ 23.2010, 23.2500(b), 23.2510, 23.2600(b), and 23.2605(b) and (c). NOTE 17. For airplanes equipped with the Current Speed Control function. The following additional regulations at Amendment 23-64 apply: §§ 23.2010, 23.2500(b), 23.2510, 23.2600(b), and 23.2605(b) and (c). In addition, Equivalent Level of Safety No. AT11224IB-A-P-2 applies. NOTE 18. For airplanes equipped with Increased Maximum Zero Fuel Weight. Post SB 505-00-0030 or with an equivalent factory-incorporated mod. END ``` ## ADs (17, in force first) - [AD 2026-10-18](https://openairdocs.org/ad/2026-10-18): Flight Control System · Embraer EMB-505. Effective Jul 6, 2026 - [AD 2026-03-05](https://openairdocs.org/ad/2026-03-05): Autopilot Main Servo · Embraer EMB-505. Effective Mar 31, 2026 - [AD 2024-22-06](https://openairdocs.org/ad/2024-22-06): Cabin Equipment/Furnishings · Embraer EMB-505. Effective Jan 2, 2025 - [AD 2024-17-09](https://openairdocs.org/ad/2024-17-09): Cabin Equipment/Furnishings · Embraer EMB-505. Effective Nov 12, 2024 - [AD 2023-21-04](https://openairdocs.org/ad/2023-21-04): Indicating/recording system · Embraer EMB-505. Effective Dec 11, 2023 - [AD 2023-10-02](https://openairdocs.org/ad/2023-10-02): Indicating/Recording System, Navigation · Boeing 18, 23, 35 and 1,060 more. Effective May 26, 2023 - [AD 2022-05-12](https://openairdocs.org/ad/2022-05-12): Elevator Structure, Rudder Structure, Ailerons · Embraer EMB-505. Effective Apr 13, 2022 - [AD 2021-24-21](https://openairdocs.org/ad/2021-24-21): Operations · Embraer EMB-500 and EMB-505. Effective Jan 25, 2022 - [AD 2018-07-10](https://openairdocs.org/ad/2018-07-10): Flight Controls · Embraer EMB-500 and EMB-505. Effective May 15, 2018 - [AD 2016-22-02](https://openairdocs.org/ad/2016-22-02): Equipment/Furnishing · Embraer EMB-500 and EMB-505. Effective Dec 1, 2016 - [AD 2014-19-01](https://openairdocs.org/ad/2014-19-01): Landing Gear · Embraer EMB-505. Effective Oct 22, 2014 - [AD 2012-13-04](https://openairdocs.org/ad/2012-13-04): Flight Controls · Embraer - Empresa Brasileira de Aeronautica EMB-505. Effective Aug 6, 2012 - [AD 2023-22-11](https://openairdocs.org/ad/2023-22-11) (historical): Autopilot Main Servo · Embraer EMB-505. Effective Dec 26, 2023 - [AD 2023-21-06](https://openairdocs.org/ad/2023-21-06) (historical): Cabin Equipment/Furnishings · Embraer EMB-505. Effective Dec 11, 2023 - [AD 2020-12-08](https://openairdocs.org/ad/2020-12-08) (historical): Elevator Structure; Rudder Structure; Ailerons · Embraer EMB-505. Effective Jul 1, 2020 - [AD 2013-22-20](https://openairdocs.org/ad/2013-22-20) (historical): Landing Gear · Embraer EMB-505. Effective Nov 8, 2013 - [AD 2011-20-01](https://openairdocs.org/ad/2011-20-01) (historical): Flight Controls · Embraer - Empresa Brasileira de Aeronautica EMB-505. Effective Oct 31, 2011 ## Registered aircraft by registry model (OpenAirDocs) - [Embraer Executive EMB-505](https://openairdocs.org/model/embraer-executive-emb-505): 529 aircraft (registry code 3260390) - [Embraer S A EMB-505](https://openairdocs.org/model/embraer-s-a-emb-505): 113 aircraft (registry code 326040C) - [Embraer-Empresa Brasileira De EMB-505](https://openairdocs.org/model/embraer-empresa-brasileira-de-emb-505): 33 aircraft (registry code 3260407) ## STCs approved under this data sheet (47) - [STC SA12141IB](https://openairdocs.org/stc/SA12141IB): GOGO HDX antenna systems integration. FTI ENGINEERING NETWORK GmbH - [STC SA02279AT](https://openairdocs.org/stc/SA02279AT): Installation of a Boom Beam bulb, starter, and ballast. Whelen Aerospace Technologies - [STC SA04761NY](https://openairdocs.org/stc/SA04761NY): True Blue TS56 Emergency Battery Power Supply Replacement. Mid-Continent Instrument Co. Inc. - [STC SA12286AT](https://openairdocs.org/stc/SA12286AT): Installation of a LEO Connectivity System. Embraer Engineering & Technology Center, USA, Inc. - [STC SA12143CH](https://openairdocs.org/stc/SA12143CH): Installation of SpaceX Starlink Aviation System. Nextant Aerospace - [STC SA11158SC](https://openairdocs.org/stc/SA11158SC): Demonstration of aircraft tolerance to potential electromagnetic interference from certain Transmitting Potable Electronic Devices (T-PEDS). Liberty Partners Inc. - [STC SA02779SE](https://openairdocs.org/stc/SA02779SE): Installation of Gogo AVANCE L3 Inflight Connectivity System. AeroMech Incorporated - [STC SA12140IB](https://openairdocs.org/stc/SA12140IB): Mechanical provisions for the installation of a GOGO HDX antenna. FTI ENGINEERING NETWORK GmbH - [STC SA09887AC](https://openairdocs.org/stc/SA09887AC): Installation of an Avionica MK-III mini Quick Access Recorder (QAR) and optional 4G or LTE Avionica Cellular Module (avCM. Aircraft Systems and Manufacturing Inc. - [STC SA03316CH](https://openairdocs.org/stc/SA03316CH): Activation of an 802.11 a/b/g/n WiFi System. Elliott Aviation Technical Products Development Inc. - [STC SA02658SE](https://openairdocs.org/stc/SA02658SE): Installation of Garmin GI 275 Multi-Function Display System. Garmin International Inc. - [STC SA09942AC](https://openairdocs.org/stc/SA09942AC): Installation of Schatz Bearing Corporation, Radial Bearing P/N’s : KP60BHT-H-OPG and KP64BHT-H-OPG. AV8 PMA LLC - [STC SA00087IB](https://openairdocs.org/stc/SA00087IB): Medical reconfiguration of the EMB-505. UMLAUT ENGINEERING GMBH - [STC SA00076IB](https://openairdocs.org/stc/SA00076IB): Installation of Photo luminescent Safety Systems. STG AEROSPACE GERMANY GmbH - [STC SA04552AT](https://openairdocs.org/stc/SA04552AT): Installation of cargo compartment floor covering. Embraer Engineering and Technology Center, USA, Inc. - [STC SA04548AT](https://openairdocs.org/stc/SA04548AT): Installation of an Avionica, LLC Quick Access Recorder/Data Concentrator model avRDC MAX (QAR) P/N 804-1250-32 and optional Avionica, LLC Cellular Module LTE (avCM LTE) P/N 650-0100-05. Aircraft Systems and Manufacturing Inc. - [STC SA00038IB](https://openairdocs.org/stc/SA00038IB): Replacement of the Passenger Seat Cushion Covers and Foams on the Embraer S.A. EMB-505. Waypoint Aerotec Limited - [STC SA09856AC](https://openairdocs.org/stc/SA09856AC): Installation of BendixKing Aerowave 100 In-flight Data Link System for non-essential, non-required aircraft Cabin Systems & Equipments. Honeywell International Inc (Bendix King) - [STC SA01727WI](https://openairdocs.org/stc/SA01727WI): Interior Alteration for Installation of a Coffee Maker and Modification of No Smoking Signs. Netjets Aviation Inc. - [STC SA04514NY](https://openairdocs.org/stc/SA04514NY): Single/Dual Transponder System ADS-B Upgrade. Scandinavian Avionics Design ApS - [STC SA04463AT](https://openairdocs.org/stc/SA04463AT): Installation of a Gogo Business Aviation Avance L5 Air To Ground (ATG) In-Flight Entertainment and Connectivity (IFEC) System. Embraer Engineering & Technology Center - USA Inc. - [STC SA03010CE](https://openairdocs.org/stc/SA03010CE): Installation of a Lacobucci HF Electronics Nespresso Machine PIN HFE96-28T-10 and/or Monogram System -TIA Division Wavejet Microwave Oven PIN 400-1860-01. Embraer Engineering & Technology Center - USA Inc. - [STC SA04397NY](https://openairdocs.org/stc/SA04397NY): Installation of Satcom system. 328 Support Services GmbH - [STC SA03003CE](https://openairdocs.org/stc/SA03003CE): Installation of an Aviator 200 Satcom System. Embraer Engineering & Technology Center - USA Inc. - [STC SA03005CE](https://openairdocs.org/stc/SA03005CE): Installation of an Aviator 200 Satcom System. Embraer Engineering & Technology Center - USA Inc. - [STC SA03001CE](https://openairdocs.org/stc/SA03001CE): Installation of Honeywell High Frequency (HF) Communication System, model KHF1050HF, and AvTec Selective Calling (SELCAL), model CSD-714. Embraer Engineering & Technology Center - USA Inc. - [STC SA03006CE](https://openairdocs.org/stc/SA03006CE): Installation of a Medical Evacuation Configuration (Medevac). Embraer Engineering & Technology Center - USA Inc. - [STC ST04340NY](https://openairdocs.org/stc/ST04340NY): Installation of TCAS 7.1 (ACAS II) upgrade of Prior Existing TCAS 7.0. Scandinavian Avionics Design ApS - [STC SA00959DE](https://openairdocs.org/stc/SA00959DE): Installation of Concorde valve regulated Lead-Acid batteries in replacement of aircraft main batteries. Concorde Battery Corporation - [STC SA00901DE](https://openairdocs.org/stc/SA00901DE): Installation of up to Two Exxternally Mounted Gimbal Systems. Straight Flight Inc - [STC SA04165NY](https://openairdocs.org/stc/SA04165NY): Installation of Latitude Technologies Skynode S200 Satcom system must be performed. Latitude Technologies Corporation - [STC SA03004CE](https://openairdocs.org/stc/SA03004CE): In accordance with Part 23 regulations specified in the current certification basis of Type Certificate Number A60CE, installation of pilot's new, extended seat tracks. Embraer S.A. - [STC SA03956AT](https://openairdocs.org/stc/SA03956AT): Installation of Aircell ATG-4000 High Speed Internet System (AHSI) and Aircell Axxess II Iridium Satcom or Aircell Aviator 200 SBB Satcom, Aircell ATG 5000 High Speed Internet System (AHSI) all with Wireless Local Area Network (WLAN). Nextant Aerospace - [STC SA03973NY](https://openairdocs.org/stc/SA03973NY): Replacement of existing TCAS 7.0 by TCAS 7.1. Scandinavian Avionics Design ApS - [STC SA03764NY](https://openairdocs.org/stc/SA03764NY): Installation of the Low Gain Satcom Antenna. Roeder Praezision GMBH - [STC ST03776NY](https://openairdocs.org/stc/ST03776NY): Modification to upgrade existing Rockwell Collins TCAS (Model: TTR-920, TTR-921, and TTR-4000) at VERSION 7.0 to Rockwell Collins TCAS (Model: TTR-921, TTR-4000, and TTR-4100) at VERSION 7.1 (ACAS II). Scandinavian Avionics Design ApS - [STC SA04278AT](https://openairdocs.org/stc/SA04278AT): Installation of a cabin In-Flight Entertainment & Passenger Audio System. Embraer Engineering & Technology Center - USA Inc. - [STC SA04145CH](https://openairdocs.org/stc/SA04145CH): Installation of a cosmetic threshold in the aft baggage compartment to protect interior coverings/materials from loading and removal of baggage. Elliott Aviation Technical Products Development, Inc. - [STC SA04260AT](https://openairdocs.org/stc/SA04260AT): Installation of an 802.11 Wireless Internet System. Embraer Engineering & Technology Center - USA Inc. - [STC SA04243AT](https://openairdocs.org/stc/SA04243AT): Installation of AFT Lavatory Coat Hanger Support. Embraer Engineering & Technology Center - USA Inc. - [STC SA01969SE](https://openairdocs.org/stc/SA01969SE): Installation of a Mid-Continent MD302 Standby Attitude Module. Mid-Continent Instruments and Avionics - [STC SA03352CH](https://openairdocs.org/stc/SA03352CH): Activation of an 802.11 a/b/g and n Wi-Fi System. Elliott Aviation Technical Products Development, Inc. - [STC SA01789WI](https://openairdocs.org/stc/SA01789WI): Quasar II Cabin Lighting with eConnect and Noise Mitigation. Duncan Aviation Inc - [STC SA01760WI](https://openairdocs.org/stc/SA01760WI): Installation of an Aircell Universal Cabin System (UCS) 5000 with Wireless Local Area Network (WLAN).. Duncan Aviation Inc - [STC SA02121SE](https://openairdocs.org/stc/SA02121SE): Installation of Garmin GTS 825 (TAS) or GTS 855 (TCAS I) Traffic System. Garmin International Inc - [STC SA01703WI](https://openairdocs.org/stc/SA01703WI): Installation of Concorde RG-380E/44 and RG-390E VRSLA Batteries. Concorde Battery Corporation - [STC SA01692WI](https://openairdocs.org/stc/SA01692WI): Installation of Aircell High Speed Internet (AHSI) System with Wireless Local Area Network (WLAN) capability. 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