# TCDS T00021SE: The Boeing Company - Type: Type certificate data sheet - Status: Current - Holder: The Boeing Company - Revision: 40 - Revised: September 22, 2025 - Product: Aircraft, Large Airplane - Certification basis: Part 25 - Registered aircraft: 214, by the registry models matched to it (OpenAirDocs) - Data sheet PDF: https://openairdocs.org/files/sha256/df/19/df19c54b5c6f5d8797df5a48e89c97708156ead1e861f3af8aee8d5932bf038a - FAA DRS: https://drs.faa.gov/browse/excelExternalWindow/DRSDOCID164738608120250922181118.0001 - Page: https://openairdocs.org/tcds/T00021SE ## Models (3) As the data sheet lists them. - 787-10 - 787-8 - 787-9 ## What the data sheet says From the PDF's text layer, line by line; tables lose their columns. The PDF is the record. ```text T00021SE 1 of 27 Page No. 1 2 3 4 5 6 7 8 9 10 11 12 13 14 15 16 17 18 19 Rev. No. 40 37 40 38 37 37 36 36 37 40 40 36 37 36 36 37 40 37 37 Page No. 20 21 22 23 24 25 26 27 Rev. No. 36 36 20 37 33 32 39 37 T00021SE Revision 40 BOEING 787-8 787-9 787-10 September 22, 2025 TYPE CERTIFICATE DATA SHEET T00021SE This data sheet, which is part of Type Certificate No. T00021SE, 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: The Boeing Company 737 Logan Ave N Renton, WA 98057-0000 I - 787-8, Transport Category, Approved August 26, 2011 Engines: 2 Rolls-Royce plc Turbofan Engines; Models: Trent 1000-A, Trent 1000-A2, Trent 1000-AE3, Trent 1000-C, Trent 1000-C2, Trent 1000-CE3, Trent 1000-D, Trent 1000-D2, Trent 1000-D3, Trent 1000-E, Trent 1000-G, Trent 1000-G2, Trent 1000-G3, Trent 1000-H, Trent 1000-H2, Trent 1000-H3, Trent 1000-L2 (Engine Type Certificate No. E00076EN) 2 General Electric Turbofan Engines; Models: GEnx-1B64, GEnx-1B64/P1, GEnx-1B64/P2, GEnx-1B67, GEnx-1B67/P1, GEnx-1B67/P2, GEnx-1B70, GEnx-1B70/P1, GEnx-1B70/P2, GEnx-1B70C/P1, GEnx-1B70C/P2, GEnx-1B70/75/P1or GEnx-1B70/75/P2 (Engine Type Certificate No. E00078NE) Authorization for engine intermix is contained in the appropriate FAA approved Airplane Flight Manual Fuel: Rolls-Royce plc Turbofan Engines: Fuels conforming to: ASTM D-1655 grades Jet-A and Jet A-1 MIL-DTL-5624 grade JP-5 MIL-DTL-83133 grade JP-8 GOST 10227-86 grade TS-1 are acceptable. Fuels produced to other specifications and having properties meeting the requirements of the above specifications are acceptable. The fuel and any fuel additives must conform to the relevant Engine Operating Instructions. General Electric Turbofan Engines (also, see Note 9): Fuels conforming to: ASTM D-1655 grades Jet-A and Jet A-1 MIL-DTL-5624 grade JP-5 MIL-DTL-83133 grade JP-8 GOST 10227-86 grade TS-1 are acceptable. Fuels produced to other specifications and having properties meeting the requirements of the above specifications are acceptable. The fuel and any fuel additives must conform to the relevant Engine Operating Instructions. Operation of the General Electric GEnx-1B series engine with fuel containing Kathon™ FP 1.5 biocide is prohibited. T00021SE 2 of 27 I - 787-8 (cont’d) Engine Limits: Static thrust lb, standard day, sea level Takeoff (see Note 10 for operating limits) Maximum continuous RR Trent 1000-A (See Note 7 for ICAO env comp) (see Note 11 for Applicability) 69,194 64,722 RR Trent 1000-C (See Note 7 for ICAO env comp) (see Note 12 for Applicability) 74,511 69,523 RR Trent 1000-D (See Note 7 for ICAO env comp) (see Note 12 for Applicability) 74,511 69,523 RR Trent 1000-E (See Note 7 for ICAO env comp) (see Note 12 for Applicability) 59,631 58,866 RR Trent 1000-G (See Note 7 for ICAO env comp) (see Note 12 for Applicability) 72,066 64,722 RR Trent 1000-H (See Note 7 for ICAO env comp) (see Note 12 for Applicability) 63,897 58,866 RR Trent 1000 - A2 (See Note 20 for ICAO env comp) 69,194 64,722 RR Trent 1000 - C2 (See Note 20 for ICAO env comp) 74,511 69,523 RR Trent 1000 – D2 (See Note 20 for ICAO env comp) 74,511 69,523 RR Trent 1000 - G2 (See Note 20 for ICAO env comp) 72,066 64,722 RR Trent 1000 - H2 (See Note 20 for ICAO env comp) 63,897 58,866 RR Trent 1000 – L2 (See Note 20 for ICAO env comp) 74,511 69,523 RR Trent 1000-AE3 (See Note 24 for ICAO env comp) 69,194 64,722 RR Trent 1000-CE3 (See Note 24 for ICAO env comp) 74,511 69,523 RR Trent 1000-D3 (See Note 24 for ICAO env comp) 74,511 69,523 RR Trent 1000-G3 (See Note 24 for ICAO env comp) 72,066 64,722 RR Trent 1000-H3 (See Note 24 for ICAO env comp) 63,897 58,866 GEnx-1B64 (See Note 21 for SDR Reporting) (See Note 7 for ICAO env comp) (See Note 13 for applicable BOM) 67,000 61,500 GEnx-1B64/P1 (See Note 21 for SDR Reporting) (See Note 7 for ICAO env comp) (See Note 16 for applicable BOM) 67,000 61,500 GEnx-1B64/P2 (See Note 21 for SDR Reporting) (See Note 24 for ICAO env comp) (See Note 18 for applicable BOM) 67,000 61,500 GEnx-1B67 (See Note 21 for SDR Reporting) (See Note 7 for ICAO env comp) (See Note 14 for applicable BOM) 69,400 61,500 GEnx-1B67/P1 (See Note 21 for SDR Reporting) (See Note 7 for ICAO env comp) (See Note 16 for applicable BOM) 69,400 61,500 GEnx-1B67/P2 (See Note 21 for SDR Reporting) (See Note 24 for ICAO env comp) (See Note 18 for applicable BOM) 69,400 61,500 GEnx-1B70 (See Note 21 for SDR Reporting) (See Note 7 for ICAO env comp) (See Note 15 for applicable BOM) 72,300 66,500 GEnx-1B70/P1 (See Note 21 for SDR Reporting) (See Note 7 for ICAO env comp) (See Note 16 for applicable BOM) 72,300 66,500 T00021SE 3 of 27 I - 787-8 (cont’d) Engine Limits (cont’d): Takeoff (see Note 10 for operating limits) Maximum continuous GEnx-1B70/P2 (See Note 21 for SDR Reporting) (See Note 24 for ICAO env comp) (See Note 18 for applicable BOM) 72,300 66,500 GEnx-1B70C/P1(See Note 21 for SDR Reporting) (See Note 7 for ICAO env comp) (See Note 16 for applicable BOM) 72,300 66,500 GEnx-1B70C/P2 (See Note 21 for SDR Reporting) (See Note 24 for ICAO env comp) (See Note 18 for applicable BOM) 72,300 66,500 GEnx-1B70/75/P1(See Note 21 for SDR Reporting) (See Note 7 for ICAO env comp) (See Note 16, 17 for applicable BOM) 72,300 66,500 GEnx-1B70/75/P2 (See Note 21 for SDR Reporting) (See Note 24 for ICAO env comp) (See Note 18,19 for applicable BOM) 72,300 66,500 For engine operating limits see the applicable Engine Type Certificate Data Sheet or the FAA approved Airplane Flight Manual. (See Note 2 for AFM reference) Airspeed Limits: VMO/MMO = 350KEAS / 360KIAS / 0.90M. For other airspeed limits, see the appropriate FAA-approved Airplane Flight Manual. CG Range: See the appropriate FAA-approved Airplane Flight Manual. Empty Weight C.G.: None Maximum Weights: See the appropriate FAA-approved Airplane Flight Manual. Model Eligible Serial Numbers 787-8 34422-34425, 34485-34488, 34490, 34491-34494, 34496-34498, 34501-34503, 34505-34512, 34514-34516, 34518, 34520, 34521, 34525, 34528, 34743-34752, 34785, 34786, 34788, 34789, 34791, 34795, 34796, 34821-34840, 34842, 34844, 34846, 34847, 34849, 34850, 34853-34857, 34859, 34860, 34923-34932, 34938-34945, 35257-35264, 35303-35316, 35319, 35320, 35435- 35440, 35506-35511, 35879, 35938-35944, 36040-36046, 36109-36112, 36227-36233, 36235- 36238, 36273-36299, 36400, 36412-36419, 36424, 36426-36429, 36526, 36843, 36844, 37117, 37118, 37120-37127, 37164-37167, 37227-37230, 37306, 37502-37511, 37894, 37920, 37921, 37982-37985, 38055, 38056, 38135, 38136, 38319-38348, 38363, 38364, 38464, 38466, 38471- 38473, 38475-38477, 38480, 38484, 38609-38615, 38619, 38754, 38757-38759, 39406, 39407, 40053, 40059, 40108, 40109, 40124-40127, 40618-40637, 40695, 40748-40750, 40899, 41538- 41543, 41987, 42224, 42225, 42243-42249, 42378, 42379, 43817, 43818, 44572, 60265, 60267, 60279, 60626, 60629-60631, 63396-63399, 64249, 64435-64438, 65315, 65990-66006, 66133, 67792 PERTINENT DATA Minimum Crew: Two (2): pilot and copilot Maximum Passengers: The maximum number of passengers approved for emergency evacuation is: 381with four pairs of exits in an (A, A, A, A) exit arrangement, 355 with four pairs of exits in a (C, A, A, A) exit arrangement, 330 with four pairs of exits in an (A, A, C, A) exit arrangement, and 300 with four pairs of exits in a (C, A, C, A) exit arrangement. Maximum passenger capacity may be further limited by Environmental Control System ventilation per occupant requirement defined in 25.831(a). Max. Baggage/Cargo: See appropriate FAA-approved Weight and Balance Manual. (See Note 1 for W&B ref) Fuel and Oil Capacities: See appropriate FAA-approved Weight and Balance Manual. (See Note 1 for W&B ref) Maximum Operating Altitude: 43,100 feet T00021SE 4 of 27 I - 787-8 (cont’d) Certification Basis: 14 CFR Part 25, Airworthiness Standards, through Amendment 25-119 and Amendments 25-120, 25-124, 25-125 and 25-128 with exceptions as noted below. Section No. Title At Amdt. 25- 25.1309 For Cargo Fire Protection Systems and Uncommanded High Thrust 119 Amendment 25-118 was not published and therefore has no applicability. 14 CFR Part 26, Continued Airworthiness and Safety Improvements, through Amendment 26-5, for §§ 26.11, 26.21, 26.37, 26.43, and 26.45 14 CFR Part 34, Fuel Venting and Exhaust Emission Requirements for Turbine Engine Powered, through Amendment 34-7A. In addition, the engine meets ICAO environmental standards defined in Annex 16, amendment 10, dated July 20, 2020. (See Note 24 for additional considerations) 14 CFR Part 36, Noise Standards: Aircraft Type Certification and Airworthiness Certification, through Amendment 36-28. Demonstrated compatibility with the ICAO Annex 16, Volume I, Amendment 9 is documented in the AFM. (See Note 25 for additional considerations) The Following Optional Design Regulations have been complied with: Ditching: 14 CFR §§ 25.801, 25.1411(d), (e), (f), (g) and 25.1415 Ice Protection: 14 CFR § 25.1419 ETOPS: The 787-8 has been evaluated in accordance with the type design requirements of 14 CFR § 25.3(b)(2) and 25.1535 and found suitable for greater than 180- minute ETOPS operations when operated and maintained in accordance with Boeing Document No. D021Z002-01, “Model 787 ETOPS Configuration, Maintenance, and Procedures.” This finding does not constitute approval to conduct ETOPS Exemptions from 14 CFR Part 25: 1. Grant of Exemption, § 25.562(b)(2), Relief from floor warpage testing requirements for flightdeck seats on the Boeing Model 787 series airplanes; Exemption No. 9486, September 11, 2007. 2. Grant of Exemption, § 25.809(a), Relief from the requirement that flightcrew emergency exits have a means to view outside conditions under all lighting situations for the Boeing Model 787 series airplanes; Exemption No. 10114, August 11, 2010. 3. Grant of Exemption, § 25.809(a), Relief for a limited number of the Boeing Model 787 series airplanes from the requirement that passenger emergency exits have a means to view outside conditions under all lighting situations; Exemption No. 10235A, May 01, 2013 (Limited to aircraft below Line Number 127 for the 787-8 series only). 4. Partial Grant of Exemption, § 25.841(a)(2)(i)(ii), Relief for the Boeing Model 787 series airplanes from the requirement that, during a decompression caused by failures of the engines, airplane cabin pressure altitude not exceed 25,000 feet for more than 2 minutes or exceed 40,000 feet for any duration; Exemption No. 8857, March 30, 2007. 5. Time Limited Grant of Exemption, § 25.1309(c), Temporary relief from the requirement to provide indication of anticipated fuel system contamination to the flightcrew of Boeing Model 787-8 airplanes powered by Rolls- Royce Trent 1000 engines; Exemption No. 10199, January 28, 2011, and Exemption No. 10199A, August 18, 2011, Exemption No. 10199B, June 30, 2014 (Expires April 30, 2017). 6. Grant of Exemption, § 25.1447(c)(1), Relief from the requirement for passenger oxygen masks to be automatically presented before the cabin pressure altitude exceeds 15,000 feet for the Boeing Model 787 series airplanes; Exemption No. 9801, December 12, 2008. 7. Time Limited Grant of Exemption, §§ 25.1305(c)(6) and 25.1309(c), Temporary relief from the requirements to provide indication of impending bypass of the engine oil fuel cooled oil coolers and to provide indication of impending bypass on the main fuel filters of multiple engines, for the Boeing Model 787-8 airplanes powered by General Electric GEnx-1B, or subsequent variants of the engine; Exemption No. 10268 (corrected copy), May 24, 2011, and Exemption No. 10268A, August 15, 2011, Exemption No. 10268B, June 30, 2014 (Expires April 30, 2017). T00021SE 5 of 27 I - 787-8 (cont’d) Exemptions (cont’d) 8. Grant of Exemption, Section 25.853(d) which requires that certain interior components of airplanes with passenger capacities of 20 or more meet the flammability test requirements of parts IV and V (heat release and smoke emission) of appendix F of 14 CFR part 25; 10868A, November 5, 2013 9. Grant of Exemption, Section 25.813(e) at Amendment 25-116 – No door may be installed between any passenger seats that is occupiable for takeoff and landing and any passenger emergency exit, such that the door crosses any egress path (including aisles, cross aisles and passageways); Exemption 10879, October 18, 2013. Partial Grant of Exemption 10879A, amended in entirety on March 7, 2018, Partial Grant of Exemption 10879B, amended in entirety on December 3, 2018. Grant of Exemption 10879C, amended in entirety on February 1, 2023 10. Time Limited Grant of Exemption §25.1305(c)(5) at Amendment 25-120, providing flight-deck annunciation of operation of the engine VBV ice-protection system; Exemption 11081, issued October 10, 2014, requires production airplanes to be fully compliant after June 30, 2015 and the in-service fleet to be fully compliant after March 31, 2016. Time Limited Grant of Exemption § 25.939(a), at Amendment 25-40, for airplanes that have incorporated engine ice protection system modifications and associated AFM limitations; Exemption 11081A, issued January 20, 2015, requires production airplanes to be fully compliant by June 30, 2015 and prohibits in-service fleet retrofit after June 30, 2015. Exemption 11081B, issued June 10, 2015, extends the dates of 11081A requiring production airplanes to be fully compliant to § 25.939(a), at Amendment 25-40, to December 31, 2015and prohibits in-service fleet retrofit after December 31, 2015. 11. Time Limited Grant of Exemption, § 25.901(c), 25.1301(a)(4), 25.1309(a), and 25.1309(b).Temporary relief from the requirements as they relate to single failures of the thrust control module that could result in uncommanded high thrust conditions and to the extent necessary to allow type certification of new propulsion control system designs for Model 787-8 and 787-9 airplanes equipped with General Electric GEnx-1B engines; Exemption No. 17112 dated September 23, 2016. The conditions of TLE 17112 require production airplanes to be fully compliant after December 31, 2018, and the in-service fleet to be fully compliant by December 31, 2020. 12. Grant of Exemption, § 25.901(c) to allow type certification of new propulsion control system designs for the Model 787 airplanes without an exact showing of compliance with the "no single failure" requirement of § 25.901(c) relating to UHT in combination with high crosswinds in certain takeoff and approach-and-landing scenarios. This exemption applies only to those UHT failure conditions that, when combined with high crosswinds, do not comply with § 25.901(c).; Exemption 17319, issued May 2, 2017 13. Time Limited Grant of Exemption, § 25.903(a)(1) to allow type certification of the Model 787 airplanes equipped with Rolls-Royce Trent 1000-AE3, Trent 1000-CE3, Trent 1000-D3, Trent 1000-G3 and Trent 1000- H3 engines from the engine requirement that mandates engines comply with the smoke emissions requirements of 14 CFR Part 34. This exemption is based on Time-Limited Grant of Exemption 17550A which was issued to Rolls-Royce plc and is required to meet the conditions and limitations of, that time- limited exemption for their engines. Exemption No. 17613, issued October 25, 2017. The conditions of TLE 17613 requires that all in-service airplanes be fully compliant by December 31, 2022. On February 12, 2018 Rolls-Royce plc met condition 6.b of Exemption 17550A showing full compliance to 14 CFR Part 34 which meets the requirement of § 25.903(a)(1). 14. Grant of Exemption, §§ 25.863(a), 25.863(b)(3), 25.901(c), 25.981(a)(3), 25.981(b), 25.981(d), 25.1309(b), and Special Conditions 25-414-SC will either improve or maintain the current level of safety on existing in- service Boeing Model 787 airplanes by incorporation of design changes required to address the unsafe condition in AD 2018-11-13 for the upper wing stringer-to-skin joints and address the installation of cap seals in lighting Zone 3 and the separate installation of edge sealant; Exemption 20370, issued June 11, 2023. Equivalent Levels of Safety (ELOS) are identified as: TC6918SE-T-A-9 §§ 25.341, 25.343, 25.345, 25.371, 25.373, and 25.391 ELOS Finding for Gust and Continuous Turbulence Design Loads TC6918SE-T-A-10 § 25.335(b) ELOS Finding for Design Airspeeds TC6918SE-T-A-11 §§ 25.391, 25.393, and 25.415 ELOS Finding for the Ground Gust Requirements TC6918SE-T-A-12 § 25.331(c) ELOS for Symmetric Maneuvering Conditions TC6918SE-T-A-13 § 25.629 ELOS for Aeroelastic Stability T00021SE 6 of 27 I - 787-8 (cont’d) ELOS (cont’d) PS08-0670-C-1 § 25.853(a) ELOS Finding for Adhesives Used in Interior Panel Joint Potting Applications PS13-1000-C-5 § 25.853(a)(d) ELOS Finding for Flammability Testing Hierarchy PS19-0580-C-44 Exemption 10879B ELOS Finding for Moveable Privacy Dividers between Adjacent Mini-suites TC6918SE-T-CS-1 § 25.810(a)(1)(ii) ELOS Finding for Escape Slide Inflation Times TC6918SE-T-CS-2 § 25.811(f) ELOS Finding for Emergency Exit Markings and Door Sill Reflectance PS07-0585-CS-10 §§ 25.811(d), 25.811(g), 25.812(b)(1)(i), and 25.812(b)(1)(ii) ELOS Finding for Graphical Exit Signs TC6918SE-T-CS-12 § 25.791(a) ELOS Finding for Lighted “No Smoking” Signs in Lieu of Placards TC6918SE-T-CS-14 §§ 25.853 and 25.856(b) ELOS Finding for Associated to Post-Crash Fire Survivability PS07-0585-CS-18 § 25.811(e)(4)(i), (ii), and (iii) ELOS Finding for the Passenger Door Operational Arrow Location and Color PS06-0413-CS-25 § 25.783(e)(2) ELOS Finding for Passenger and Large Cargo Door Indication PS09-0987-CS-28 § 25.562 and 25.785 ELOS Finding for Dynamic Test Requirements for Single Occupant Side- Facing Seats PS12-1032-CS-31 RevA §§ 25.562 and 25.785 ELOS Finding for Dynamic Test Requirements for Single Occupant Oblique Seats with Inflatable Restraints PS12-1033-C-32 §§ 25.562 and 25.785 ELOS Finding for Dynamic Test Requirements for Single Occupant Side- Facing Seats PS13-0679-CS-33 §§ 25.561 and 25.621 ELOS Finding for Critical Casting Factor Requirements for Model 787 Series Aircraft PS13-0906-CS-37 §§ 25.562 and 25.785 ELOS Finding for Dynamic Test Requirements for Side-Facing Seats with Shoulder Restraints PS18-0046-EE-10 §§ 25.1535 and K25.2.2 ELOS Finding for 787 Rolls-Royce Trent 1000-TEN Early ETOPS Airplane Demonstration Tests TC6918SE-T-ES-5 § 25.831(g) ELOS Finding for Acceptable High Temperature Physiological Environment During Failure Condition TC6918SE-T-ES-16 § 25.1443(c) ELOS Finding for the Passenger Oxygen System TC6918SE-T-ES-18 § 25.1441(c) ELOS Finding for Pulse Oxygen System for Passenger TC6918SE-T-ES-19 § 25.841(b)(6) ELOS Finding for Cabin Altitude Warning System for Operations into High Altitude Airports TC6918SE-T-ES-20 § 25.1443(d) ELOS Finding for Portable Pulse Oxygen System TS15-0029-F-1 § 25.251 ELOS Finding for Vibration/Buffeting Compliance Criteria, Taxi Aid Camera TC6918SE-T-F-4 § 25.1517 ELOS Finding for Rough Air Speed (VRA) TC6918SE-T-F-6 § 25.107 (e)(1)(iv) ELOS Finding for Minimum Unstick (VMU) Speed Margin T00021SE 7 of 27 I - 787-8 (cont’d) ELOS (cont’d) TC6918SE-T-F-14 § 25.677(b) ELOS Finding for Trim Displays TC6918SE-T-F-17 § 25.255 ELOS Finding for Out-of-Trim Characteristics PS06-0496-F-18 § 25.1555 ELOS Engine and APU Fire Handle Design PS06-0413-F-20 § 25.1325(e) ELOS Finding for the Standby Air Data System PS14-0452-F-23A § 25.251 ELOS Finding for Vibration/Buffeting Compliance Criteria, Panasonic Ku-Band Radome Antenna TC6918SE-T-G-8 §§ 25.1529, Appendix H25.4 ELOS Finding for formatting of Boeing ICA Manuals – Airworthiness PS05-0177-P-2 § 25.981(b)(2) ELOS Finding for the Fuel Tank Flammability Rule (FTFR) TC6918SE-T-P-2 §§ 25.933(a)(1)(i) and 25.933(a)(1)(ii) ELOS Finding for Flight Critical Thrust Reverser TC6918SE-T-P-3 § 25.1182(a) ELOS Finding for Fire Safety Requirements for the Aft Strut Fairing Compartment TC6918SE-T-P-13 §§ E25.1, F25.1 and G25.1 ELOS Finding for the Auxiliary Power Unit (APU) Installation PS14-0470-P-15 K25.2.2(d)(1) ELOS Finding for the 787-8/-9 Rolls-Royce Trent 1000-TEN ETOPS Ground Test TC6918SE-T-P-17 § 25.934 ELOS Finding for the Engine and Thrust Reverser System Testing TC6918SE-T-P-19 §§ 25.1023(b) and 25.1121(c) ELOS Finding for Auxiliary Power System TC6918SE-T-P-20 §§ 25.997 and 25.1305(c)(6) ELOS Finding for Warning Means for Engine Fuel Filter Contamination TC6918SE-T-P-27 § 25.1145(a) ELOS Finding for Engine Igniter Flight-deck Switch Configuration PS06-0414-P-34 §§ 25.1181(a)(6), 25.1181(b), 25.1182, and 25.1183(a) ELOS Finding for Fire Safety Requirements for GEnx-1B PS13-0546-P-36 §§ 25.1549(a) and 25.1549(b) ELOS Finding for the Display of Powerplant Instruments TC6918SE-T-SA-7 §§ 25.1301, 25.1309 and 25.1310 ELOS Finding for use of ARAC Recommended Revision TC6918SE-T-SA-10 § 25.1459(a)(2) ELOS Finding for Flight Recorders TC6918SE-T-SA-11 § 25.1303(c)(1) ELOS Finding for Overspeed Aural Warning TC6918SE-T-SA-29 § 25.1333(a) ELOS Finding for Instrument Systems TC6918SE-T-SE-14 § 25.1351(b)(5) ELOS Finding for the Flight Control Electronics DC Power System PS06-0496-T-SE-15 § 25.1317(b) ELOS Finding for High Intensity Radiated Fields (HIRF) TC6918SE-T-SF-1 § 25.671(c)(2) ELOS Finding for Flight Control System Failure Criteria TC6918SE-T-SF-5 § 25.777(e) ELOS Finding for the Wing Flap Control Lever PS06-0496-SF-7 § 25.675 ELOS Finding for Seal Krueger Flap Stops T00021SE 8 of 27 I - 787-8 (cont’d) Special Conditions with respect to the following subjects apply to the Model 787-8: Special Condition. Subject 25-348-SC Composite Wing and Fuel Tank Structure—Fire Protection Requirements 25-354A-SC Interaction of Systems and Structures, Electronic Flight Control System- Control Surface Awareness, High Intensity Radiated Fields (HIRF) Protection, Limit Engine Torque Loads for Sudden Engine Stoppage, and Design Roll Maneuver Requirement 25-355-SC Reinforced Flightdeck Bulkhead 25-356-SC Systems and Data Networks Security-Isolation or Protection from Unauthorized Passenger Domain Systems Access 25-357-SC Systems and Data Networks Security-Protection of Airplane Systems and Data Networks from Unauthorized External Access 25-359-SC Lithium Ion Battery Installation 25-360-SC Composite Fuselage In-Flight Fire/Flammability Resistance 25-362-SC Crashworthiness Emergency Landing Conditions 25-363-SC Tire Debris Penetration of Fuel Tank Structure 25-365-SC Operation Without Normal Electrical Power 25-370-SC Seats with Non-Traditional, Large, Non-Metallic Panels 25-414-SC Lightning Protection of Fuel Tank Structure to Prevent Fuel Tank Vapor Ignition 25-418-SC Overhead Flight Crew Rest Compartment Occupiable during Taxi, Takeoff, and Landing 25-419-SC Overhead Crew Rest Compartment 25-431-SC Seats with Inflatable Lapbelts 25-458-SC Single-place Side-facing Seats with Inflatable Lapbelts 25-605-SC Structure- Mounted Airbags 25-626A-SC Dynamic Test Requirements for Single-Occupant Oblique (Side-Facing) Seats With or Without Airbag Devices or 3-Point Restraint Systems 25-682-SC Non-Rechargeable Lithium Battery Installations 25-745-SC Seats with Inertia Locking Devices 25-770-SC Dynamic Test Requirements for Single-Occupant Oblique Seats With Pretensioner Restraint Systems 25-786-SC Seats With Pretensioner Restraint Systems T00021SE 9 of 27 II. 787-9, Transport Category, Approved June 13, 2014 Engines: 2 Rolls-Royce plc Turbofan Engines; Models: Trent 1000-A2, Trent 1000-AE3, Trent 1000-D2, Trent 1000-D3, Trent 1000-J2, Trent 1000-J3, Trent 1000-K2, Trent 1000-K3 (Engine Type Certificate No. E00076EN) 2 General Electric Turbofan Engines; Models: GEnx-1B64/P2, GEnx-1B67/P2, GEnx-1B70, GEnx-1B70/P1, GEnx-1B70/P2, GEnx-1B70/75/P2, GEnx-1B74/75/P1, GEnx-1B74/75/P2, GEnx-1B76A/P2 (Engine Type Certificate No. E00078NE) Authorization for engine intermix is contained in the appropriate FAA approved Airplane Flight Manual Fuel: Rolls-Royce plc Turbofan Fuels conforming to: ASTM D-1655 grades Jet-A and Jet A-1 MIL-DTL-5624 grade JP-5 MIL-DTL-83133 grade JP-8 GOST 10227-86 grade TS-1 are acceptable. Fuels produced to other specifications and having properties meeting the requirements of the above specifications are acceptable. The fuel and any fuel additives must conform to the relevant Engine Operating Instructions. General Electric Turbofan Engines (also, see Note 9): Fuels conforming to: ASTM D-1655 grades Jet-A and Jet A-1 MIL-DTL-5624 grade JP-5 MIL-DTL-83133 grade JP-8 GOST 10227-86 grade TS-1 are acceptable. Fuels produced to other specifications and having properties meeting the requirements of the above specifications are acceptable. The fuel and any fuel additives must conform to the relevant Engine Operating Instructions. Operation of the General Electric GEnx-1B series engine with fuel containing Kathon™ FP 1.5 biocide is prohibited. Engine Limits: Static thrust lb, standard day, sea level Takeoff (see Note 10 for operating limits) Maximum continuous RR Trent 1000-A2 (See Note 20 for ICAO env comp) 69,194 64,722 RR Trent 1000-D2 (See Note 20 for ICAO env comp) 74,511 69,523 RR Trent 1000-K2 (See Note 20 for ICAO env comp) 78,129 71,818 RR Trent 1000-J2 (See Note 20 for ICAO env comp) 78,129 71,818 RR Trent 1000-AE3 (See Note 24 for ICAO env comp) 69,194 64,722 RR Trent 1000-D3 (See Note 24 for ICAO env comp) 74,511 69,523 RR Trent 1000-J3 (See Note 24 for ICAO env comp) 78,129 71,818 RR Trent 1000-K3 (See Note 24 for ICAO env comp) 78,129 71,818 GEnx-1B64/P2 (See Note 21 for SDR Reporting) (See Note 24 for ICAO env comp) (See Note 18 for applicable BOM) 67,000 61,500 GEnx-1B67/P2 (See Note 21 for SDR Reporting) (See Note 24 for ICAO env comp) (See Note 18 for applicable BOM) 69,400 61,500 T00021SE 10 of 27 II - 787-9 (cont’d) Engine Limits (cont’d): GEnx-1B70 (See Note 21 for SDR Reporting) (See Note 7 for ICAO env comp) (See Note 15 for applicable BOM) 72,300 66,500 GEnx-1B70/P1 (See Note 21 for SDR Reporting) (See Note 7 for ICAO env comp) (See Note 16 for applicable BOM) 72,300 66,500 GEnx-1B70/P2 (See Note 21 for SDR Reporting) (See Note 24 for ICAO env comp) (See Note 18 for applicable BOM) 72,300 66,500 GEnx-1B70/75/P2 (See Note 21 for SDR Reporting) (See Note 24 for ICAO env comp) (See Note 18, 19 for applicable BOM) 72,300 66,500 GEnx-1B74/75/P1 (See Note 21 for SDR Reporting) (See Note 20 for ICAO env comp) (See Note 16 for applicable BOM) 76,700 68,600 GEnx-1B74/75/P2 (See Note 21 for SDR Reporting) (See Note 24 for ICAO env comp) (See Note 18 for applicable BOM) 76,700 68, 600 GEnx-1B76A/P2 (See Note 21 for SDR Reporting) (See Note 24 for ICAO env comp) (See Note 18 for applicable BOM) 78,500 68,600 For engine operating limits see the applicable Engine Type Certificate Data Sheet or the FAA approved Airplane Flight Manual. (See Note 2 for AFM ref) Airspeed Limits: VMO/MMO = 350KEAS / 360KIAS / 0.90M. For other airspeed limits, see the appropriate FAA-approved Airplane Flight Manual. CG Range: See the appropriate FAA-approved Airplane Flight Manual. Empty Weight C.G.: None Maximum Weights: See the appropriate FAA-approved Airplane Flight Manual. Model Serial Number 787-9 34305-34319, 34334, 34335, 34499, 34500, 34504, 34513, 34517, 34519, 34522-34524, 34526, 34527, 34529-34534, 34810-34819, 34841, 34843, 34845, 34848, 34851, 34852, 34858, 35151- 35154, 35168, 35265-35270, 35317, 35318, 35321, 35322, 35422-35431, 35880, 36113, 36239- 36241, 36401-36409, 37071, 37109, 37112-37116, 37119, 37128-37131, 37146, 37168-37184, 37307, 37308, 37388-37390, 37449, 37811-37815, 37931, 37963-37981, 38047, 38083, 38084- 38087, 38134, 38137, 38138, 38180, 38182, 38269, 38274, 38276, 38356-38362, 38459, 38461, 38467-38470, 38474, 38478, 38479, 38481-38483, 38616-38618, 38620-38632, 38755, 38756, 38760-38803, 38891-38895, 39038-39040, 39287-39298, 39646-39667, 39669, 39671, 39672, 39675-39678, 39679, 39680, 39982-39987, 39996, 39997, 40045-40049, 40601, 40602, 40638- 40659, 40751, 40752, 40918, 40939, 40941, 40942, 40956, 41544-41551, 41988, 41989, 42116- 42119, 42368, 42369, 42372, 42373, 42380, 42486-42488, 42490, 42491, 42493, 42495, 42497, 42498, 42506, 42509, 43217, 43218, 43859-43862, 43864-43874, 43983, 44426, 44427, 44578, 44579, 60141-60144, 60146, 60147, 60283-60285, 60311-60315, 60322, 60326-60328, 60627, 60628, 61519-61529, 62082, 62143-62146, 62148, 62169-62176, 62178, 62517, 62518, 62522, 62523, 62710-62742, 63040-63043, 63310-63323, 63345, 63346, 63390-63395, 63522, 63523, 63526, 63548, 63634, 63706-63717, 63720, 63978-63987, 63988, 64053, 64209-64226, 64228- 64232, 64239, 64293, 64294, 64312-64316, 64625, 64626, 64968, 64969, 64974-64982, 64983, 65086-65094, 65098, 65099, 65102, 65103, 65106, 65107, 65246-65249, 65313, 65314, 65429- 65433, 65558, 65559, 65801-65824, 66007, 66010, 66011, 66013, 66073-66078, 66134-66146, 66161-66163, 66407, 66409, 66428, 66429-66431 66514, 66515, 66522-66524, 66526-66531, 66816, 66877, 66991-66993, 68622 T00021SE 11 of 27 II - 787-9 (cont’d) PERTINENT DATA Minimum Crew: Two (2): pilot and copilot Maximum Passengers: The maximum number of passengers approved for emergency evacuation is: 420 with four pairs of exits in an (A, A, A, A) exit arrangement, 355 with four pairs of exits in a (C, A, A, A) exit arrangement, 355 with four pairs of exits in an (A, A, C, A) exit arrangement, and 300 with four pairs of exits in a (C, A, C, A) exit arrangement. Maximum passenger capacity may be further limited by Environmental Control System ventilation per occupant requirement defined in 25.831(a). Max. Baggage/Cargo: See appropriate FAA-approved Weight and Balance Manual. (See Note 1 for W&B ref) Fuel and Oil Capacities: See appropriate FAA-approved Weight and Balance Manual. (See Note 1 for W&B ref) Max Operating Altitude: 43,100 feet Certification Basis: 14 CFR Part 25, Airworthiness Standards, through Amendment 25-128, with exceptions as noted below. Section No. Title At Amdt. 25- 25.107 Takeoff Speeds 135 25.795(a)(4) For Installed Physical Secondary Barrier (IPSB) 150 25.795(b)(1) Security considerations N/A 25.795(c)(2) Security considerations N/A 25.795(c)(3)(i) Security considerations N/A 25.125(b)(2)(ii)(B) Landing 108 25.1309 For Cargo Fire Protection Systems and Uncommanded High Thrust 128 25.1317 remains at FAA Special Condition 25-354A-SC for the Integrated Standby Flight Display (ISFD) 14 CFR Part 26, Based on 14 CFR §21.101(g) for changes made to TCs applicable provisions of 14 CFR part 26 are included in the certification basis. For any future 14 CFR part 26 amendments, the holder of this TC must demonstrate compliance with the applicable sections. Compliance has been found for the following regulations through Amendment 26-5, for §§ 26.21, 26.37, 26.43, and 26.45 14 CFR Part 34, Fuel Venting and Exhaust Emission Requirements for Turbine Engine Powered, through Amendment 34-7A. In addition, the engine meets ICAO environmental standards defined in Annex 16, amendment 10, dated July 20, 2020. (See Note 24 for additional considerations) 14 CFR Part 36, Noise Standards: Aircraft Type Certification and Airworthiness Certification, through Amendment 36-28. Demonstrated compatibility with the ICAO Annex 16, Volume I, Amendment 9 is documented in the AFM. (See Note 25 for additional considerations) The Following Optional Design Regulations have been complied with: Ditching: 14 CFR §§ 25.801, 25.1411(d), (e), (f), (g) and 25.1415 Ice Protection: 14 CFR § 25.1419 ETOPS: The 787-9 has been evaluated in accordance with the type design requirements of 14 CFR § 25.3(b)(2) and 25.1535 and found suitable for greater than 180- minute ETOPS operations when operated and maintained in accordance with Boeing Document No. D021Z002-01, “Model 787 ETOPS Configuration, Maintenance, and Procedures.” This finding does not constitute approval to conduct ETOPS. Installed Addition of optional Installed Physical Secondary Barrier (IPSB) aft of the flight Physical Barrier deck door to comply with 14 CFR § 25.795(a)(4). (IPSB): T00021SE 12 of 27 II - 787-9 (cont’d) Exemptions from 14 CFR Part 25: 1. Grant of Exemption, § 25.562(b)(2), Relief from floor warpage testing requirements for flightdeck seats on the Boeing Model 787 series airplanes; Exemption No. 9486, September 11, 2007. 2. Grant of Exemption, § 25.809(a), Relief from the requirement that flightcrew emergency exits have a means to view outside conditions under all lighting situations for the Boeing Model 787 series airplanes; Exemption No. 10114, August 11, 2010. 3. Partial Grant of Exemption, § 25.841(a)(2)(i)(ii), Relief from the requirement that the airplane must be designed so that occupants will not be exposed to a cabin pressure altitude that exceeds the following after decompression from any failure condition not shown to be extremely improbable: (i) Twenty-five thousand (25,000) feet for more than 2 minutes; or (ii) Forty thousand (40,000) feet for any duration for the Boeing Company’s Model 787-9 airplanes. Exemption No. 10962, March 3, 2014 4. Grant of Exemption, § 25.1447(c)(1), Relief from the requirement for passenger oxygen masks to be automatically presented before the cabin pressure altitude exceeds 15,000 feet for the Boeing Model 787 series airplanes; Exemption No. 9801, December 12, 2008. 5. Time Limited Grant of Exemption §25.1301(a)(1), Relief from the requirements that the airplane must function properly when installed be designed appropriate to its intended function for Ram Air Turbine (RAT) Generator Control Unit (GCU) on the Boeing model 787-9 airplane and Time Limited Grant of Exemption §25.1301(a)(4), §25.1309(a) and §25.1309(b)(2), Relief from the requirements that Systems and equipment must function properly when installed; Systems and equipment must perform intended function and Hazardous effects must be improbable for the Altitude-Select knob on the Boeing model 787-9 Autoflight Mode Control Panel; Exemption No. 11002, June 12, 2014 (Expires August 31, 2015 for the RAT GCU, November 30, 2015 for the MCP Altitude-select knob). 6. Grant of Exemption, § 25.853(d) and condition 1 of Special Condition No. 25-370-SC relief from the flammability requirements for large surface areas on seats in the Boeing Model 787-9 series airplanes; Exemption 10868, September 12, 2013 and Exemption No. 10868A, November 5, 2013. 7. Grant of Exemption, Section 25.813(e) at Amendment 25-116 – No door may be installed between any passenger seats that is occupiable for takeoff and landing and any passenger emergency exit, such that the door crosses any egress path (including aisles, cross aisles and passageways); Exemption 10879, October 18, 2013. Partial Grant of Exemption 10879A, amended in entirety on March 7, 2018, Partial Grant of Exemption 10879B, amended in entirety on December 3, 2018. Grant of Exemption 10879C, amended in entirety on February 1, 2023. 8. Time Limited Grant of Exemption §25.1305(c)(5) at Amendment 25-120, providing flight-deck annunciation of operation of the engine VBV ice-protection system; Exemption 11081, issued October 10, 2014, requires production airplanes to be fully compliant after June 30, 2015 and the in-service fleet to be fully compliant after March 31, 2016. Time Limited Grant of Exemption § 25.939(a), at Amendment 25- 40, for airplanes that have incorporated engine ice protection system modifications and associated AFM limitations; Exemption 11081A, issued January 20, 2015, requires production airplanes to be fully compliant by June 30, 2015 and prohibits in-service fleet retrofit after June 30, 2015. Exemption 11081B, issued June 10, 2015, extends the dates of 11081A requiring production airplanes to be fully compliant to § 25.939(a), at Amendment 25-40, to December 31, 2015and prohibits in-service fleet retrofit after December 31, 2015. 9. Time Limited Grant of Exemption, § 25.901(c), 25.1301(a)(4), 25.1309(a), and 25.1309(b).Temporary relief from the requirements as they relate to single failures of the thrust control module that could result in uncommanded high thrust conditions and to the extent necessary to allow type certification of new propulsion control system designs for Model 787-8 and 787-9 airplanes equipped with General Electric GEnx-1B engines; Exemption No. 17112 dated September 23, 2016. The conditions of TLE 17112 require production airplanes to be fully compliant after December 31, 2018, and the in-service fleet to be fully compliant by December 31, 2020. T00021SE 13 of 27 II - 787-9 (cont’d) Exemptions (cont’d): 10. Grant of Exemption, § 25.901(c) to allow type certification of new propulsion control system designs for the Model 787 airplanes without an exact showing of compliance with the "no single failure" requirement of § 25.901(c) relating to UHT in combination with high crosswinds in certain takeoff and approach-and-landing scenarios. This exemption applies only to those UHT failure conditions that, when combined with high crosswinds, do not comply with § 25.901(c).; Exemption 17319, issued May 2, 2017 11. Time Limited Grant of Exemption, § 25.903(a)(1) to allow type certification of the Model 787 airplanes equipped with Rolls-Royce Trent 1000-AE3, Trent 1000-D3, Trent 1000-J3 and Trent 1000-K3 engines from the engine requirement that mandates engines comply with the smoke emissions requirements of 14 CFR Part 34. This exemption is based on Time-Limited Grant of Exemption 17550A which was issued to Rolls-Royce plc and is required to meet the conditions and limitations of, that time-limited exemption for their engines. Exemption No. 17613, issued October 25, 2017. The conditions of TLE 17613 requires that all in-service airplanes be fully compliant by December 31, 2022. On February 12, 2018 Rolls-Royce plc met condition 6.b of Exemption 17550A showing full compliance to 14 CFR Part 34 which meets the requirement of § 25.903(a)(1). 12. Grant of Exemption, §§ 25.863(a), 25.863(b)(3), 25.901(c), 25.981(a)(3), 25.981(b), 25.981(d), 25.1309(b), and Special Conditions 25-414-SC will either improve or maintain the current level of safety on existing in- service Boeing Model 787 airplanes by incorporation of design changes required to address the unsafe condition in AD 2018-11-13 for the upper wing stringer-to-skin joints and address the installation of cap seals in lighting Zone 3 and the separate installation of edge sealant; Exemption 20370, issued June 11, 2023. Equivalent Levels of Safety (ELOS) are identified as: TC6918SE-T-A-9 §§ 25.341, 25.343, 25.345, 25.371, 25.373, and 25.391 ELOS Finding for Gust and Continuous Turbulence Design Loads TC6918SE-T-A-10 § 25.335(b) ELOS Finding for Design Airspeeds TC6918SE-T-A-11 §§ 25.391, 25.393, 25.415 ELOS Finding for Ground Gust Requirements TC6918SE-T-A-12 § 25.331(c) ELOS Finding for Symmetric Maneuvering Conditions TC6918SE-T-A-13 §§ 25.629, 25.671(c)(2) ELOS Finding for Aeroelastic Stability PS13-1000-C-5 § 25.853(a)(d) ELOS Finding for Flammability Testing Hierarchy PS12-1033-C-32 §§ 25.562 and 25.785 ELOS Finding for Dynamic Test Requirements for Single Occupant Side- Facing Seats PS19-0580-C-44 Exemption 10879B ELOS Finding for Moveable Privacy Dividers between Adjacent Mini-suites TC6918SE-T-CS-1 § 25.810(a)(1)(ii) ELOS Finding for Escape Slide Inflation Times TC6918SE-T-CS-2 § 25.811(f) ELOS Finding for Emergency Exit Markings and Door Sill Reflectance PS07-0585-CS-10 §§ 25.811(d) and (g), 25.812(b)(1)(i) and (b)(1)(ii) ELOS Finding for Graphical Exit Signs TC6918SE-T-CS-12 § 25.791 ELOS Finding for Lighted “No smoking” Signs in Lieu of Placards TC6918SE-T-CS-14 § 25.856(b) ELOS Finding for Fuselage Post-Crash Fire Survivability PS07-0585-CS-18 § 25.811(e)(4)(i), (ii) and (iii) ELOS Finding for Passenger Door Operational Arrow Location and Color PS06-0413-CS-25 § 25.783(e)(2) ELOS Finding for Passenger and Large Cargo Door Indication PS13-0679-CS-33 §§ 25.561 and 25.621 ELOS Finding for Critical Casting Factor Requirements for Model 787 Series Aircraft T00021SE 14 of 27 II - 787-9 (cont’d) ELOS (cont’d) PS13-0906-CS-37 § 25.562 and 25.785 ELOS Finding for Dynamic Test Requirements for Single Occupant Side- Facing Seats PS18-0046-EE-10 §§ 25.1535 and K25.2.2 ELOS Finding for 787 Rolls-Royce Trent 1000-TEN Early ETOPS Airplane Demonstration Tests TC6918SE-T-ES-5 § 25.831(g) ELOS Finding for Acceptable High Temperature Physiological Environment During Failure Conditions TC6918SE-T-ES-16 § 25.1443(c) ELOS Finding for Passenger Oxygen System TC6918SE-T-ES-18 § 25.1441(c) ELOS Finding for Pulse Oxygen System for Passengers TC6918SE-T-ES-19 § 25.841(b)(6) ELOS Finding for Cabin Altitude Warning Systems for Operation into High Altitude Airports TC6918SE-T-ES-20 § 25.1443(d) ELOS Finding for Portable Pulse Oxygen System TS15-0029-F-1 § 25.251 ELOS Finding for Vibration/Buffeting Compliance Criteria, Taxi Aid Camera TC6918SE-T-F-4 § 25.1517 ELOS Finding for Finding for Rough Air Speed (VRA) TC6918SE-T-F-14 § 25.677(b) ELOS Finding for Trim Displays TC6918SE-T-F-17 § 25.255 ELOS Finding for Out of Trim Characteristics PS06-0496-F-18 § 25.1555(d)(1) ELOS Finding for Engine and APU Fire Handle Design PS06-0496-T-F-21 § 25.1325(e) ELOS Finding for Standby Air Data System PS06-0496-F-22 § 25.123(a) and (b) ELOS Finding for Speeds for En Route Flight Paths PS14-0452-F-23A § 25.251 ELOS Finding for Vibration/Buffeting Compliance Criteria, Panasonic Ku-Band Radome Antenna TC6918SE-T-G-8 §§ 25.1529, 25.1729, Appendix H25.4(a) and (b) ELOS Finding for Formatting of Boeing Instructions for Continued Airworthiness Manuals - Airworthiness Limitations PS05-0177-P-2 §§ 25.981(b)(2) ELOS Finding for Fuel Tank Flammability Reduction Rule TC6918SE-T-P-2 § 25.933(a)(1)(i) and (a)(1)(ii) ELOS Finding for Flight Critical Thrust Reverser TC6918SE-T-P-3 § 25.1182(a) ELOS Finding for Fire Safety Requirements for the Aft Strut Fairing Compartment TC6918SE-T-P-13 Part 25 subpart E, F & G ELOS Finding for Auxiliary Power Unit (APU) Installation PS14-0470-P-15 K25.2.2(d)(1) ELOS Finding for the 787-8/-9 Rolls-Royce Trent 1000-TEN ETOPS Ground Test TC6918SE-T-P-17 § 25.934 ELOS Finding for Engine and Thrust Reverser System Testing TC6918SE-T-P-19 §§ 25.1023(b), 25.1121(c) ELOS Finding for Auxiliary Power System TC6918SE-T-P-20 §§ 25.997 and 25.1305(c)(6) ELOS Finding for Warning Means for Engine Fuel Filter Contamination TC6918SE-T-P-27 § 25.1145(a) ELOS Finding for Engine Igniter Flightdeck Switch Configuration T00021SE 15 of 27 II - 787-9 (cont’d) ELOS (cont’d) PS06-0414-P-34 §§ 25.1181(a)(6), 25.1181(b), 25.1182, and 25.1183(a) ELOS Finding for Fire Safety Requirements for GEnx-1B PS13-0546-P-36 §§ 25.1549(a) and 25.1549(b) ELOS Finding for the Display of Powerplant Instruments TC6918SE-T-SA-10 § 25.1459(a)(2) ELOS Finding for Flight Recorders TC6918SE-T-SA-11 § 25.1303(c)(1) ELOS Finding for Overspeed Aural Warning TC6918SE-T-SA-29 § 25.1333(a) ELOS Finding for Instrument Systems PS06-0496-T-SA-31 §§ 25.1301, 25.1309, and 25.1310 ELOS Finding for Use of ARAC Recommended Revision PS12-0038-SE-11 § 25.1713(c) ELOS Finding for the Engine Wiring Interconnection System (EWIS) PS14-1031-SE-28 § 25.1713(c) ELOS Finding for Engine Electrical Wiring Interconnection System (EWIS) - Fire Protection TC6918SE-T-SE-14 § 25.1351(b)(5) ELOS Finding for Flight Control Electronics DC Power System PS06-0496-T-SE-15 § 25.1317(b) ELOS Finding for High Intensity Radiated Fields (HIRF) TC6918SE-T-SF-1 § 25.671(c)(2) ELOS Finding for Flight Control System Failure Criteria TC6918SE-T-SF-5 § 25.777(e) ELOS Finding for Wing Flap Control Lever PS06-0496-SF-7 § 25.675 ELOS Finding for Seal Krueger Flap Stops Special Conditions with respect to the following subjects apply to the Model 787-9: Special Condition Subject 25-348-SC Composite Wing and Fuel Tank Structure—Fire Protection Requirements 25-354A-SC Interaction of Systems and Structures, Electronic Flight Control System-Control Surface Awareness, High Intensity Radiated Fields (HIRF) Protection, Limit Engine Torque Loads for Sudden Engine Stoppage, and Design Roll Maneuver Requirement 25-356-SC Systems and Data Networks Security-Isolation or Protection From Unauthorized Passenger Domain Systems Access 25-357-SC Systems and Data Networks Security-Protection of Airplane Systems and Data Networks from Unauthorized External Access 25-359-SC Lithium Ion Battery Installation 25-360-SC Composite Fuselage In-Flight Fire/Flammability Resistance 25-362-SC Crashworthiness Emergency Landing Conditions 25-363-SC Tire Debris Penetration of Fuel Tank Structure 25-365-SC Operation Without Normal Electrical Power 25-370-SC Seats with Non-Traditional, Large, Non-Metallic Panels 25-414-SC Lightning Protection of Fuel Tank Structure to Prevent Fuel Tank Vapor Ignition 25-418-SC Overhead Flight Crew Rest Compartment Occupiable during Taxi, Takeoff, and Landing 25-419-SC Overhead Crew Rest Compartment 25-431-SC Seats With Inflatable Lapbelts 25-458-SC Single-place Side-facing Seats with Inflatable Lapbelts 25-552-SC Dynamic Test Requirements for Multiple Occupant Side-Facing Seats with Inflatable Restraints 25-605-SC Structure- Mounted Airbags 25-626A-SC Dynamic Test Requirements for Single-Occupant Oblique (Side- Facing) Seats With or Without Airbag Devices or 3-Point Restraint Systems 25-682-SC Non-Rechargeable Lithium Battery Installations 25-745-SC Seats with Inertia Locking Devices 25-770-SC Dynamic Test Requirements for Single-Occupant Oblique Seats with Pretensioner Restraint Systems 25-786-SC Seats With Pretensioner Restraint Systems T00021SE 16 of 27 III. 787-10, Transport Category, Approved January 19, 2018 Engines: 2 Rolls-Royce plc Turbofan Engines; Models: Trent 1000-J3, Trent 1000-K3 (Engine Type Certificate No. E00076EN) 2 General Electric Turbofan Engines; Models: GEnx- 1B67/P2, GEnx-1B74/75/P2, GEnx-1B76/P2, GEnx-1B76A/P2, (Engine Type Certificate No. E00078NE) Fuel: Rolls-Royce plc Turbofan Fuels conforming to: ASTM D-1655 grades Jet-A and Jet A-1 MIL-DTL-5624 grade JP-5 MIL-DTL-83133 grade JP-8 GOST 10227-86 grade TS-1 are acceptable. Fuels produced to other specifications and having properties meeting the requirements of the above specifications are acceptable. The fuel and any fuel additives must conform to the relevant Engine Operating Instructions. General Electric Turbofan Fuels conforming to: ASTM D-1655 grades Jet-A and Jet A-1 MIL-DTL-5624 grade JP-5 MIL-DTL-83133 grade JP-8 GOST 10227-86 grade TS-1 are acceptable. Fuels produced to other specifications and having properties meeting the requirements of the above specifications are acceptable. The fuel and any fuel additives must conform to the relevant Engine Operating Instructions. Operation of the General Electric GEnx-1B series engine with fuel containing Kathon™ FP 1.5 biocide is prohibited. Engine Limits: Static thrust lb, standard day, sea level Takeoff (see Note 10 for operating limits) Maximum continuous RR Trent 1000-J3 (See Note 24 for ICAO env comp) 78,129 71,818 RR Trent 1000-K3 (See Note 24 for ICAO env comp) 78,129 71,818 GEnx-1B67/P2 (See Note 21 for SDR Reporting) (See Note 24 for ICAO env comp) (See Note 18 for applicable BOM) 69,400 61,500 GEnx-1B74/75/P2 (See Note 21 for SDR Reporting) (See Note 24 for ICAO env comp) (See Note 18 for applicable BOM) 76,700 68, 600 GEnx-1B76/P2 (See Note 21 for SDR Reporting) (See Note 24 for ICAO env comp) (See Note 18 for applicable BOM) 78,500 68,600 GEnx-1B76A/P2 (See Note 21 for SDR Reporting) (See Note 24 for ICAO env comp) (See Note 18 for applicable BOM) 78,500 68,600 For engine operating limits see the applicable Engine Type Certificate Data Sheet or the FAA approved Airplane Flight Manual. (See Note 2 for AFM ref) Airspeed Limits: VMO/MMO = 350KEAS / 360KIAS / 0.90M. For other airspeed limits, see the appropriate FAA-approved Airplane Flight Manual. CG Range: See the appropriate FAA-approved Airplane Flight Manual. Empty Weight C.G.: None Maximum Weights: See the appropriate FAA-approved Airplane Flight Manual. T00021SE 17 of 27 III - 787-10 (cont’d) Model Serial Number 787-10 40050-40052, 40054-40058, 40926, 40929-40931, 40934-40938, 40940, 42485, 42489, 42492, 42496, 42499-42501, 42503, 42504, 42507, 42508, 60138-60140, 60145, 60253-60264, 60266, 60268-60272, 60274, 60280-60282, 60286-60290, 60294, 60295-60297, 60300-60304, 60306, 60307, 60632-60636, 60637-60643, 60755-60759, 60761, 60763, 60765, 60768, 60770, 62684- 62686, 63510-63512, 63514-63516, 63520, 64805, 66878, 66879, 66881, 66984-66990, 66995- 67000, 67155- 67157 PERTINENT DATA Minimum Crew: Two (2): pilot and copilot Maximum Passengers: The maximum number of passengers approved for emergency evacuation is: 440 with four pairs of exits in an (A, A, A, A) exit arrangement, 355 with four pairs of exits in a (C, A, A, A) exit arrangement, 355 with four pairs of exits in an (A, A, C, A) exit arrangement, and 300 with four pairs of exits in a (C, A, C, A) exit arrangement. Maximum passenger capacity may be further limited by Environmental Control System ventilation per occupant requirement defined in 25.831(a). Max. Baggage/Cargo: See appropriate FAA-approved Weight and Balance Manual. (See Note 1 for W&B ref) Fuel and Oil Capacities: See appropriate FAA-approved Weight and Balance Manual. (See Note 1 for W&B ref) Max Operating Altitude: 41,100 feet Certification Basis: 14 CFR Part 25, Airworthiness Standards, through Amendment 25-137, 25-141, 25-140 for §25.1093(b)(1) for ice crystal icing conditions only (remains at amendment 72 for icing conditions in part 25 appendix C and falling and blowing snow), and 25-139 for structures to 25.307, 25.621, 25.721, 25.787, and 25.963 with exceptions as noted below. Section No. Title Amdt 25- 25.795(b)(1), (c)(2) and (c)(3)(i) Security Considerations N/A 25.125(b)(2)(ii)(B) Landing 108 25.1302 Installed systems and equipment for use by the flightcrew N/A 25.1316 ECS components: Pack Control Unit (PCU) Common Motor/Starter Controller (CMSC) Auto Transformer Rectifier Unit (ATRU) E5 and E6 Power Panels Power Electronics Cooling Systems (PECS) Pumps PECS Diverter Valve Overheat Detection System Valve Control Unit (Cabin Pressure Control System) 80 14 CFR Part 26, Based on 14 CFR §21.101(g) for changes made to TCs applicable provisions of 14 CFR part 26 are included in the certification basis. For any future 14 CFR part 26 amendments, the holder of this TC must demonstrate compliance with the applicable sections. Compliance has been found for the following regulations through Amendment 26-6, for §§ 26.37, 26.43, and 26.45 14 CFR Part 34, Fuel Venting and Exhaust Emission Requirements for Turbine Engine Powered, through Amendment 34-7A. In addition, the engine meets ICAO environmental standards defined in Annex 16, amendment 10, dated July 20, 2020 . (See Note 24 for additional considerations) 14 CFR Part 36, Noise Standards: Aircraft Type Certification and Airworthiness Certification, through Amendment 36-29. Demonstrated compatibility with the ICAO Annex 16, Volume I, Amendment 10 is documented in the AFM. (See Note 25 for additional considerations) T00021SE 18 of 27 III - 787-10 (cont’d) The Following Optional Design Regulations have been complied with: Ditching: 14 CFR §§ 25.801, 25.1411(d), (e), (f), (g) and 25.1415 Ice Protection: 14 CFR § 25.1419 ETOPS: The 787-10 has been evaluated in accordance with the type design requirements of 14 CFR § 25.3(b)(2) and 25.1535 and found suitable for greater than 180- minute ETOPS operations when operated and maintained in accordance with Boeing Document No. D021Z002-01, “Model 787 ETOPS Configuration, Maintenance, and Procedures.” This finding does not constitute approval to conduct ETOPS. Exemptions from 14 CFR Part 25: 1. Partial Grant of Exemption, § 25.841(a)(2)(i)(ii), Relief from the requirement that the airplane must be designed so that occupants will not be exposed to a cabin pressure altitude that exceeds the following after decompression from any failure condition not shown to be extremely improbable: (i) Twenty-five thousand (25,000) feet for more than 2 minutes but not more than 3 minutes; or (ii) Forty thousand (40,000) feet for 1 minute but not to exceed 41,100 feet for any duration for the Boeing Company’s Model 787-10 airplanes. Exemption No. 14821, February 12, 2016. 2. Grant of Exemption, § 25.853(d) and condition 1 of Special Condition No. 25-370-SC relief from the flammability requirements for large surface areas on seats in the Boeing Model 787-9 series airplanes; Exemption 10868, September 12, 2013 and Exemption No. 10868A, November 5, 2013. 3. Grant of Exemption, § 25.562(b)(2), Relief from floor warpage testing requirements for flightdeck seats on the Boeing Model 787 series airplanes; Exemption No. 9486, September 11, 2007. 4. Grant of Exemption, § 25.809(a), Relief from the requirement that flightcrew emergency exits have a means to view outside conditions under all lighting situations for the Boeing Model 787 series airplanes; Exemption No. 10114, August 11, 2010. 5. Grant of Exemption, § 25.1447(c)(1), Relief from the requirement for passenger oxygen masks to be automatically presented before the cabin pressure altitude exceeds 15,000 feet for the Boeing Model 787 series airplanes; Exemption No. 9801, December 12, 2008. 6. Grant of Exemption, § 25.901(c) to allow type certification of new propulsion control system designs for the Model 787 airplanes without an exact showing of compliance with the "no single failure" requirement of § 25.901(c) relating to UHT in combination with high crosswinds in certain takeoff and approach-and-landing scenarios. This exemption applies only to those UHT failure conditions that, when combined with high crosswinds, do not comply with § 25.901(c).; Exemption 17319, issued May 2, 2017 7. Time Limited Grant of Exemption, § 25.903(a)(1) to allow type certification of the Model 787 airplanes equipped with Rolls-Royce Trent 1000-J3 engines from the engine requirement that mandates engines comply with the smoke emissions requirements of 14 CFR Part 34. This exemption is based on Time-Limited Grant of Exemption 17550A which was issued to Rolls-Royce plc and is required to meet the conditions and limitations of, that time-limited exemption for their engines. Exemption No. 17613, issued October 25, 2017. The conditions of TLE 17613 requires that all in-service airplanes be fully compliant by December 31, 2022. On February 12, 2018 Rolls-Royce plc met condition 6.b of exemption 17550A showing full compliance to 14 CFR Part 34 which meets the requirement of § 25.903(a)(1). 8. Time Limited Grant of Exemption, § 25.939(a), Temporary relief for Boeing Model 787-10 airplanes with GEnx-1B/P2 engines from the requirement that turbine engines must be free of adverse operating conditions during normal and emergency operation within the airplane operational envelope while operating in ice crystal icing conditions: Exemption No. 17966 dated August 31, 2018. The conditions of TLE 17966 require production airplanes to be fully compliant after December 20, 2019 and airplanes produced under this exemption to be retrofitted by December 20, 2019. 9. Partial Grant of Exemption, Section 25.813(e) at Amendment 25-128 – No door may be installed between any passenger seats that is occupiable for takeoff and landing and any passenger emergency exit, such that the door crosses any egress path (including aisles, cross aisles and passageways); Exemption 10879B, amended in entirety on December 3, 2018. Grant of Exemption 10879C, amended in entirety on February 1, 2023. 10. Grant of Exemption, §§ 25.863(a), 25.863(b)(3), 25.901(c), 25.981(a)(3), 25.981(b), 25.981(d), 25.1309(b), and Special Conditions 25-414-SC will either improve or maintain the current level of safety on existing in- service Boeing Model 787 airplanes by incorporation of design changes required to address the unsafe condition in AD 2018-11-13 for the upper wing stringer-to-skin joints and address the installation of cap seals in lighting Zone 3 and the separate installation of edge sealant; Exemption 20370, issued June 11, 2023. T00021SE 19 of 27 III - 787-10 (cont’d) Equivalent Levels of Safety (ELOS) are identified as: TC6918SE-T-A-9 §§ 25.341, 25.343, 25.345, 25.371, 25.373, and 25.391 ELOS Finding for Gust and Continuous Turbulence Design Loads TC6918SE-T-A-10 § 25.335(b) ELOS Finding for Design Airspeeds TC6918SE-T-A-13 §§ 25.629, 25.671(c)(2) ELOS Finding for Aeroelastic Stability PS13-0546-A-21 §§ 25.571(b) ELOS Finding for Damage Tolerance and Fatigue Evaluation of Structure PS08-0670-C-1 § 25.853(a) ELOS Finding for Adhesives Used in Interior Panel Bent Joint Potting Applications PS13-1000-C-5 §§ 25.853(a)(d) ELOS Finding for Flammability Testing Hierarchy PS19-0580-C-44 Exemptions 10879B ELOS Finding for Moveable Privacy Dividers between Adjacent Mini-suites TC6918SE-T-CS-1 § 25.810(a)(1)(ii) ELOS Finding for Escape Slide Inflation Times TC6918SE-T-CS-2 § 25.811(f) ELOS Finding for Emergency Exit Markings and Door Sill Reflectance PS07-0585-CS-10 §§ 25.811(d) and (g), 25.812(b)(1)(i) and (b)(1)(ii) ELOS Finding for Graphical Exit Signs TC6918SE-T-CS-12 § 25.791 ELOS Finding for Lighted “No smoking” Signs in Lieu of Placards TC6918SE-T-CS-14 § 25.856(b) ELOS Finding for Fuselage Post-Crash Fire Survivability PS07-0585-CS-18 § 25.811(e)(4)(i), (ii) and (iii) ELOS Finding for Passenger Door Operational Arrow Location and Color PS06-0413-CS-25 § 25.783(e)(2) ELOS Finding for Passenger and Large Cargo Door Indication PS13-0679-CS-33 §§ 25.561 and 25.621 ELOS Finding for Critical Casting Factor Requirements for Model 787 Series Aircraft PS18-0046-EE-10 §§ 25.1535 and K25.2.2 ELOS Finding for 787 Rolls-Royce Trent 1000-TEN Early ETOPS Airplane Demonstration Tests TC6918SE-T-ES-5 § 25.831(g) ELOS Finding for Acceptable High Temperature Physiological Environment During Failure Conditions TC6918SE-T-ES-16 § 25.1443(c) ELOS Finding for Passenger Oxygen System TC6918SE-T-ES-18 § 25.1441(c) ELOS Finding for Pulse Oxygen System for Passengers TC6918SE-T-ES-19 § 25.841(b)(6) ELOS Finding for Cabin Altitude Warning Systems for Operation into High Altitude Airports TC6918SE-T-ES-20 § 25.1443(d) ELOS Finding for Portable Pulse Oxygen System TC6918SE-T-F-14 § 25.677(b) ELOS Finding for Trim Displays TC6918SE-T-F-17 § 25.255 ELOS Finding for Out of Trim Characteristics PS06-0496-F-18 § 25.1555(d)(1) ELOS Finding for Engine and APU Fire Handle Design PS06-0496-F-22 § 25.123(a) and (b) ELOS Finding for Speeds for En Route Flight Paths T00021SE 20 of 27 III - 787-10 (cont’d) ELOS (cont’d) PS14-0452-F-23A § 25.251 ELOS Finding for Vibration/Buffeting Compliance Criteria, Panasonic Ku-Band Radome Antenna TC6918SE-T-G-8 §§ 25.1529, 25.1729, Appendix H25.4(a) and (b) ELOS Finding for Formatting of Boeing Instructions for Continued Airworthiness Manuals - Airworthiness Limitations PS05-0177-P-2 §§ 25.981(b)(2) ELOS Finding for Fuel Tank Flammability Reduction Rule TC6918SE-T-P-2 § 25.933(a)(1)(i) and (a)(1)(ii) ELOS Finding for Flight Critical Thrust Reverser TC6918SE-T-P-3 § 25.1182(a) ELOS Finding for Fire Safety Requirements for the Aft Strut Fairing Compartment TC6918SE-T-P-13 Part 25 subpart E, F & G ELOS Finding for Auxiliary Power Unit (APU) Installation PS14-0470-P-15 K25.2.2(d)(1) ELOS Finding for the 787-8/-9 Rolls-Royce Trent 1000-TEN ETOPS Ground Test TC6918SE-T-P-17 § 25.934 ELOS Finding for Engine and Thrust Reverser System Testing TC6918SE-T-P-19 §§ 25.1023(b), 25.1121(c) ELOS Finding for Auxiliary Power System TC6918SE-T-P-20 §§ 25.997 and 25.1305(c)(6) ELOS Finding for Warning Means for Engine Fuel Filter Contamination TC6918SE-T-P-27 § 25.1145(a) ELOS Finding for Engine Igniter Flightdeck Switch Configuration PS06-0414-P-34 §§ 25.1181(a)(6), 25.1181(b), 25.1182, and 25.1183(a) ELOS Finding for Fire Safety Requirements for GEnx-1B PS13-0546-P-36 §§ 25.1549(a) and 25.1549(b) ELOS Finding for the Display of Powerplant Instruments TC6918SE-T-SA-10 § 25.1459(a)(2) ELOS Finding for Flight Recorders TC6918SE-T-SA-11 § 25.1303(c)(1) ELOS Finding for Overspeed Aural Warning TC6918SE-T-SA-29 § 25.1333(a) ELOS Finding for Instrument Systems PS06-0496-T-SA-31 §§ 25.1301, 25.1309, and 25.1310 ELOS Finding for Use of ARAC Recommended Revision PS12-0038-SE-11 § 25.1713(c) ELOS Finding for the Engine Wiring Interconnection System (EWIS) PS14-1031-SE-28 § 25.1713(c) ELOS Finding for Engine Electrical Wiring Interconnection System (EWIS) - Fire protection TC6918SE-T-SE-14 § 25.1351(b)(5) ELOS Finding for Flight Control Electronics DC Power System PS06-0496-T-SE-15 § 25.1317(b) ELOS Finding for High Intensity Radiated Fields (HIRF) TC6918SE-T-SF-1 § 25.671(c)(2) ELOS Finding for Flight Control System Failure Criteria TC6918SE-T-SF-5 § 25.777(e) ELOS Finding for Wing Flap Control Lever PS06-0496-SF-7 § 25.675 ELOS Finding for Seal Krueger Flap Stops T00021SE 21 of 27 III - 787-10 (cont’d) Special Conditions with respect to the following subjects apply to the Model 787-10: Special Condition Subject 25-348-SC Composite Wing and Fuel Tank Structure—Fire Protection Requirements 25-354A-SC Interaction of Systems and Structures, Electronic Flight Control System-Control Surface Awareness, and Design Roll Maneuver Requirement 25-356-SC Systems and Data Networks Security-Isolation or Protection From Unauthorized Passenger Domain Systems Access 25-357-SC Systems and Data Networks Security-Protection of Airplane Systems and Data Networks from Unauthorized External Access 25-359-SC Lithium Ion Battery Installation 25-360-SC Composite Fuselage In-Flight Fire/Flammability Resistance 25-362-SC Crashworthiness Emergency Landing Conditions 25-363-SC Tire Debris Penetration of Fuel Tank Structure 25-365-SC Operation Without Normal Electrical Power 25-370-SC Seats with Non-Traditional, Large, Non-Metallic Panels 25-414-SC Lightning Protection of Fuel Tank Structure to Prevent Fuel Tank Vapor Ignition 25-418-SC Overhead Flight Crew Rest Compartment Occupiable during Taxi, Takeoff, and Landing 25-419-SC Overhead Crew Rest Compartment 25-431-SC Seats With Inflatable Lapbelts 25-552-SC Dynamic Test Requirements for Multiple Occupant Side-Facing Seats with Inflatable Restraints 25-605-SC Structure- Mounted Airbags 25-626A-SC Dynamic Test Requirements for Single-Occupant Oblique (Side- Facing) Seats With or Without Airbag Devices or 3-Point Restraint Systems 25-644-SC Flaps Up Vertical Modal Suppression (F0VMS) 25-682-SC Non-Rechargeable Lithium Battery Installations 25-745-SC Seats with Inertia Locking Devices 25-770-SC Dynamic Test Requirements for Single-Occupant Oblique Seats with Pretensioner Restraint Systems 25-786-SC Seats With Pretensioner Restraint Systems THE FOLLOWING INFORMATION AND NOTES APPLY TO ALL MODELS UNLESS OTHERWISE NOTED ADDITIONAL DESIGN REQUIREMENTS AND CONDITIONS: The following design details or information must be maintained to ensure that an unsafe design condition is not present: In-flight Engine Restart The Boeing Model 787 engines incorporate numerous technological advances intended to increase efficiency and reliability. However, some of these features have the potential to decrease engine in-flight starting performance relative to the engines envisioned when the applicable sections of 14 CFR Part 25 were promulgated. The following criteria for engine in-flight starting performance must be met to ensure that the level of safety intended by §§ 25.903(e) and 25.1351(d) is maintained on airplanes powered by current technology engines. 1. Appropriate procedures for restarting the engines in the following cases must be provided in the airplane flight manual (AFM): a. a fuel cut during climb after the takeoff phase (defined as the flight phase from start of the takeoff roll to 1500 feet above the runway altitude), b. loss of all alternating current (AC) power in combination with an all engine flameout, and c. all engine flame-out at or below 20,000 feet. T00021SE 22 of 27 THE FOLLOWING INFORMATION AND NOTES APPLY TO ALL MODELS UNLESS OTHERWISE NOTED (cont’d): Uncontrollable High Engine Thrust or Power Numerous single and anticipated combinations of failures within traditional engine control systems result in losing the normal means to control the magnitude and/or direction of engine thrust (power). For some of these anticipated failure conditions, the flight crew cannot be relied upon to recognize and mitigate the failures before they become hazardous or catastrophic. The following design features are required to ensure an unsafe condition does not exist with regards to the loss of the normal means to control engine thrust (power): 1. Dual channel full authority digital electronic (engine) control (FADEC) which monitors engine conditions to trim fuel flow 2. Thrust control malfunction accommodation to address conditions where fuel metering is not responding to pilot input on the ground, and 3. Redundant mechanical control interface between the flight crew and the FADEC. Engine Rotor-Lock Evaluation Service experience has shown that some engines are susceptible to a condition known as rotor-lock following an in-flight shut-down from power settings ranging from high power to idle. The engine design must be free from engine rotor lock. Fuel Feed System Icing Threats Under certain conditions, over a period of low fuel temperatures, ice may accumulate in the airplane fuel feed system and then be fed or released downstream to the engine, and result in failure to achieve a commanded thrust level, and this is considered an unsafe condition. As such, each aircraft/engine and aircraft/auxiliary power system (APS) fuel feed system must either be designed to prevent an accumulation of ice anywhere within the fuel tank and feed system from being released into the engine and APS fuel system, or be designed so no loss of engine thrust occurs due to release of any ice accumulation anywhere within the airplane/engine operating envelope. Return Landing Capability Examination of takeoff performance capabilities of current and proposed large transport aircraft indicates that requirements other than climb performance should be addressed when considering safe return operations and the need for a fuel jettison system. The 787 fuel jettison system must be installed, and the jettison rate should be such that there is adequate return to landing capability, when considering the following items, in a 30- minute flight with 15 minutes of active fuel jettisoning in conjunction with operational procedures: 1. Exceedance of certificated maximum brake energies; 2. Exceedance of tire speed limits; 3. Controllability (e.g., hydraulic or flight control system failures); 4. Margins to flap placard, or load relief operation speeds in turbulent air; 5. Climb capability, engine inoperative procedure; 6. Landing distances (actual distances, including contaminated runway). 25.125 – Landing (787-9/-10) The enhanced stall protection (ESP) is a required by design to ensure the intended level of safety. Any subsequent type design change, modification, or repair that disable or modify ESP are not acceptable. Security Considerations (787-9/-10) The Boeing Model 787-9/-10 was granted an exception per 14 CFR 21.101(b) for §§25.795(b)(1), (c)(2) and (c)(3)(i) based on design feature similar to but not equivalent to their intent. These security features must be in consideration in any subsequent type design change, modification, or repair to ensure the level of safety designed into the 787-9/-10 is maintained. Modifications that reduce flight critical system separation or adversely impact flight deck smoke protection, system separation and protections for searching above the overhead stowage compartments are not acceptable. T00021SE 23 of 27 THE FOLLOWING INFORMATION AND NOTES APPLY TO ALL MODELS UNLESS OTHERWISE NOTED (cont’d): Operational Exemptions for Domestic or Foreign Operators into or out of airports in the United States: Boeing Model 787 airplanes equipped with Rolls-Royce Trent 1000-X(X)3 series engines were granted Time Limited Exemption (TLE) 17550A for relief from § 34.21(e)(2). § 91.203(d) requires compliance with the fuel venting and exhaust emission requirement of 14 CFR Part 34 for operators coming into or flying out of airport in the United States. The following TLE’s were granted for operators whose engines were produced under Rolls-Royce TLE No. 17550A: Exemption No. 17644 (NPD) Exemption No. 17645 (NSB) Exemption No. 17646 (ANZ) Exemption No. 17675A (ANA, ARE, BAB, BEJ, ELA, ETH, GUL, LOT, LAN, NEO, RBA, SIA, VAA). These TLE are to be considered granted to these airlines and their subsidiaries. The conditions of these TLE’s require that all in-service airplanes be fully compliant by December 31, 2022. On February 12, 2018 Rolls-Royce plc met condition 6.b of exemption 17550 showing full compliance to 14 CFR Part 34. This showing of compliance is applicable to engines produced under this exemption and meets the § 91.203(d) requirement for all domestic or foreign operators into or out of airports in the United States. Certification Maintenance Requirements (CMRs): See FAA-approved Certification Maintenance Requirements, document number D011Z009-03-03. Production Basis: Production Certificate No. 700. (See Note 4 and Note 8 for PC applicability). Leveling Means: A plumb bob attachment and leveling provision scale are provided in the left main gear wheel well. Datum: Sta 0.0, located 55.8 in forward of airplane nose (B.S. 55.8). Mean Aerodynamic Chord (MAC): 246.9 inches Control Surface Movements: To insure proper operation of the airplane, the movement of the various control surfaces must be carefully controlled by proper rigging of the flight control systems. The airplane must, therefore, be rigged according to the following FAA-approved data in the following Boeing documents: B787-A-27-11-00-18A-270B-A - Aileron – Rigging B787-A-27-11-00-19A-270B-A - Flaperon – Rigging B787-A-27-31-00-27A-270B-A - Elevator – Rigging B787-A-27-21-00-31A-270B-A - Rudder – Rigging B787-A-27-51-00-28A-270B-A - Trailing Edge Flap System – Rigging B787-A-27-61-00-17A-270B-A - Spoiler – Rigging T00021SE 24 of 27 THE FOLLOWING INFORMATION AND NOTES APPLY TO ALL MODELS UNLESS OTHERWISE NOTED (cont’d): 787-8 Maximum control surface travel: Control Surface Maximum TED/TEL (Deg.) Maximum TEU/TER (Deg.) Ailerons 16.94° -32.20° Elevators 26.93° -32.54° Flaperon 39.26° -31.61° Spoilers 6, 7, 8, 9 -13.21° 60.95° Spoilers 1, 2, 3, 12, 13, 14 -13.24° 60.77° Spoilers 4, 5, 10, 11 -13.16° 63.00° Rudder 32.10° -31.83° Horizontal Stabilizer 4.25° -12.75° Inboard Flaps 41.20° -2.80° Outboard Flaps 41.20° -2.00° Inboard Slats 23.47° -0.34° Outboard Slats 30.16° -0.40° 787-9 Maximum Control Surface Travel: Control Surface Maximum TED/TEL (Deg.) Maximum TEU/TER (Deg.) Ailerons 16.94° -32.20° Elevators 26.93° -32.54° Flaperon 39.26° -31.61° Spoilers 6, 7, 8, 9 -13.23° 61.15° Spoilers 1, 2, 3, 12, 13, 14 -13.24° 60.77° Spoilers 4, 5, 10, 11 -13.40° 62.91° Rudder 32.40° -32.00° Horizontal Stabilizer 4.25° -12.75° Inboard Flaps 43.00° -2.80° Outboard Flaps 43.00° -2.00° Inboard Slats 26.52° -0.34° Outboard Slats 31.56° -0.40° T00021SE 25 of 27 THE FOLLOWING INFORMATION AND NOTES APPLY TO ALL MODELS UNLESS OTHERWISE NOTED (cont’d): 787-10 Maximum Control Surface Travel: Control Surface Maximum TED/TEL (Deg.) Maximum TEU/TER (Deg.) Ailerons 16.94° -32.20° Elevators 26.93° -32.54° Flaperon 39.26° -31.61° Spoilers 6, 7, 8, 9 -13.23° 61.15° Spoilers 1, 2, 3, 12, 13, 14 -13.24° 60.77° Spoilers 4, 5, 10, 11 -13.40° 62.91° Rudder 32.40° -32.00° Horizontal Stabilizer 4.25° -12.75° Inboard Flaps 43.00° -2.80° Outboard Flaps 43.00° -2.00° Inboard Slats 26.52° -0.34° Outboard Slats 31.56° -0.40° Trailing Edge Down = TED Trailing Edge Up = TEU Trailing Edge Left = TEL Trailing Edge Right = TER Degrees = Deg. Required Equipment The basic required equipment as prescribed in the applicable airworthiness regulations (see Certification Basis) must be installed in the aircraft for certification. Service Information: The following documents are FAA-approved; Service Bulletins and other service information, when FAA-approved, will contain a statement declaring FAA approval. Boeing Document B787-81205-Z0210-00, “787-8 Structural Repair Manual” Boeing Document B787-81205-Z0310-00 “787-9 Structural Repair Manual” Boeing Document B787-81205-Z0410-00 “787-10 Structural Repair Manual” INFORMATION AND 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. This is in accordance with 14 CFR 25.29 Note 2 Airplane operation must be in accordance with the FAA-approved Airplane Flight Manual, Boeing Document D631Z003. All placards required by either the FAA-approved Flight Manual, the applicable operating rules, or the Certification Basis must be installed in the airplane in accordance with 14 CFR 25.1541 through 25.1563. Note 3 In accordance with 14 CFR 25.571, 25.981, 25.1529 (and 25.1729 for 787-9 and 787-10), the FAA has accepted the Boeing Model 787 Instructions for Continued Airworthiness in Section 9 of the 787 Maintenance Planning Data, Boeing Document D011Z009-03 and sub-tier documents listed below. The operational limitations and maintenance tasks set forth in the following documents constitute the Airworthiness Limitations of the Boeing 787-8/-9/-10 model airplanes. For airplanes delivered after August 5, 2019, the applicable revision level of each of these documents is listed on the airplane-specific Revision Effectivity Record (RER) MPE-RER-787-LNXXXX letter of each airplane. Airplane operators are required to observe the limitations and perform the maintenance tasks per the specified revision level or a later FAA- approved revision of the documents. D011Z009-03-01, 787 Airworthiness Limitations (AWLs). Contains required structural inspections and the retirement times for structural safe-life and life-limited parts. Also contains required retirement times for systems life-limited parts and other systems limitations. T00021SE 26 of 27 THE FOLLOWING INFORMATION AND NOTES APPLY TO ALL MODELS UNLESS OTHERWISE NOTED (cont’d): INFORMATION AND NOTES: (cont’d) D011Z009-03-02, 787 Airworthiness Limitations (AWLs) – Line Number Specific. Existing structures AWLs that were impacted by airplane production non- conformances may result in airplane specific revised inspection requirements and/or inspection intervals. D011Z009-03-03, 787 Certification Maintenance Requirements (CMRs). Required periodic tasks to specific Systems installations. D011Z009-03-04, 787 Special Compliance Items (SCIs) /Airworthiness Limitations. This document lists and provides instructions for Airworthiness Limitation Instructions (ALIs) and Critical Design Configuration Control Limitations (CDCCLs) required to comply with 14 CFR Part 25.981. D925W704-04, The Boeing Commercial Airplanes Universal Airplane Network Security Operator Guidance, D925W704-04, contains required Instructions for Continued Airworthiness and security guidance that when followed meets compliance requirements of the Network Cybersecurity Special Conditions. Note 4 The following Aircraft Serial Numbers were produced under the Type Certification only: 787-8: (Added to the PC700 Production Limitation Record on August 26, 2011) 34486, 34832, 36277, 36278, 36281, 36282, 36283, 36284, 40693, 40694, & 40695 787-9: (Added to the PC700 Production Limitation Record on June 13, 2014) 34334, 34522, 35422, 36404, 36405, 41988, 41989 787-10: (Added to the PC700 Production Limitation Record on February 15, 2018) 40929, 60256, 60253, 60257 Note 5 Installations using quick release hardware to install commodities such as galleys, closets, lavatories and stowage bins in adaptable zones in the passenger cabin shall be shown compliant to 25.561(c)(2). Note 6 The models 787-8, 787-9 and 787-10 have been approved to operate in “Reduced Vertical Separation Minimum” (RVSM) airspace. Continued airworthiness and operational approval aspects of RVSM must be constructed according to FAA document 91-RVSM Change 2, dated 19 February 2004 title d “Approval of Aircraft and Operators for Flight in Airspace Above Flight Level (FL) 290 Where a 1,000 Foot Vertical Separation Minimum is Applied.” Note 7 EASA has found the model 787-8 and 787-9 to be compliant with the International Civil Aviation Organization (ICAO) Annex 16, Volume II, Amendment 6, for Emissions Note 8 Production Certificate No. 700 was amended to include the 787-8, 787-9 and 787-10 and issued. Boeing is authorized to issue airworthiness certificates under the Organization Delegation Authorization (ODA) Procedures of 14 CFR part 183, subpart D, and FAA Order 8100.15. Note 9 Boeing and GE have determined that the GEnx engines on these 787-8 aircraft intermittently emit a sometimes clearly visible fuel vapor fog after shutdown, as a result of a small quantity of fuel being released from the engine’s fuel system. These emissions do not present a safety issue or appreciable environmental impact. Boeing and GE will modify the design of the aircraft and engines by December 31, 2012 to completely eliminate this fuel venting on new aircraft. Boeing has included an airworthiness limitation in the instructions for continued airworthiness for the affected aircraft requiring incorporation of the modified design by December 31, 2014. Note 10 See the FAA approved Flight Manual for engine ratings and operating limits. The normal 5-minute takeoff time limit may be extended to 10 minutes for engine out contingency if permitted by the Limitations Section of the FAA approved Airplane Flight Manual. Note 11 Applicable to Trent 1000-A Engines with or without M/SB 72-G319 incorporated. Note 12 Applicable only to Trent 1000-C, Trent 1000-D, Trent 1000-E, Trent 1000-G and Trent 1000-H Engines with M/SB 72-G319 incorporated. T00021SE 27 of 27 ….END… THE FOLLOWING INFORMATION AND NOTES APPLY TO ALL MODELS UNLESS OTHERWISE NOTED (cont’d): INFORMATION AND NOTES: (cont’d) Note 13 Applicable to Bill of Materials for GEnx-1B64G03 or GEnx-1B64G04 Note 14 Applicable to Bill of Materials for GEnx-1B67G03 or GEnx-1B67G04 Note 15 Applicable to Bill of Materials for GEnx-1B70G03 or GEnx-1B70G04 Note 16 Applicable to Bill of Materials for GEnx-1B64/P1G01, GEnx-1B67/P1G01, GEnx-1B70/P1G01, GEnx- 1B70C/P1G01, GEnx-1B70/75/P1G01 and GEnx-1B74/75/P1G01 respectively. Note 17 Same as GEnx-1B70/P1 except for extended takeoff flat rating ambient temperature (101.8°F/38.8°C at sea level). Note 18 Applicable to Bill of Materials for GEnx-1B64/P2G01 or GEnx-1B64/P2G02, GEnx-1B67/P2G01 or GEnx-1B67/P2G02, GEnx-1B70/P2G01 or GEnx-1B70/P2G02, GEnx-1B70C/P2G02, GEnx- 1B70/75/P2G01 or GEnx-1B70/75/P2G02, GEnx-1B74/75/P2G01 or GEnx-1B74/75/P2G02, GEnx- 1B76/P2G01 or GEnx-1B76/P2G02, and GEnx-1B76A/P2G01 or GEnx-1B76A/P2G02 respectively. Note 19 Same as GEnx-1B70/P2 except for extended takeoff flat rating ambient temperature (101.8°F/38.8°C at sea level). Note 20 For the 787-8 and 787-9 the engine manufacturers have declared that the ICAO emissions standards identified in Annex 16, Volume II, Third Edition, Part III, Chapter 2, Section 2.2.2 for SN, Section 2.3 .2 for CO and HC, Section 2.3.2.e.3 for NOx (also known as CAEP/8), and Part II Chapter 2 for fuel venting have also been demonstrated. Note 21 The FAA has concluded that the occurrence of any uncommanded high-thrust failure condition, or any of the associated causal failures listed within Boeing Document D011Z009-03-01, may endanger the safe operation of an airplane. Consequently, the FAA recommends that operators report any such failures in accordance with Title 14, Code of Federal Regulations 121.703(c), 125.409(c), and 135.415(c). Note 22 For the 787-10 the engine manufacturers have declared that the ICAO emissions standards identified in Annex 16, Volume II, Third Edition, Part III, Chapter 2, Section 2.2.2 for SN, Section 2.3 .2 for CO and HC, Section 2.3.2.e.3 for NOx (also known as CAEP/8), and Part II Chapter 2 for fuel venting have also been demonstrated. Note 23 The 787-8, 787-9, and 787-10 Airplane Condition Monitoring Function (ACMF), a 787 Maintenance System (MS) functionality, was certified to enable the monitoring, recording, engine reporting, and airplane systems performance, in accordance with Title 14 Code of Federal Regulations Part 25.1301; allowing collected data to be used by airlines for purposes including but not limited to trend analysis and scheduled maintenance credits, as applicable and appropriate. Note 24 In addition to the FAA’s finding of compliance based on the certification requirements defined in this TCDS, the engine manufacturer has declared that the ICAO emissions standards identified in Annex 16, Volume II, Fourth Edition, Amendment 10, effective July 20, 2020, have also been demonstrated for the following: Part II, Chapter 2 for Fuel Venting Part III, Chapter 2, Section 2.2.2 for Smoke Number Part III, Chapter 2, Section 2.3.2 for Carbon Monoxide and Hydrocarbons Part III, Chapter 2, Section 2.3.2 for Oxides of Nitrogen (also known as CAEP/8), and Part III, Chapter 4, Section 4.2.2 for non-volatile Particulate Matter (also known as CAEP/10 & CAEP/11) Note 25 The FAA has found the 787-8 and 787-9 compatible with the ICAO Annex 16, Volume I, Amendment 9, Chapter 4 for Noise. The FAA has found the 787-10 compatible with the ICAO Annex 16, Volume I, Amendment 10, Chapter 4, for Noise. ``` ## ADs (125, first 50, in force first) - [AD 2026-20-16](https://openairdocs.org/ad/2026-20-16): Powerplant · Boeing 787-8, 787-9 and 787-10. Effective Nov 23, 2026 - [AD 2026-20-10](https://openairdocs.org/ad/2026-20-10): Flight Controls · Boeing 787-8, 787-9 and 787-10. Effective Nov 12, 2026 - [AD 2026-20-01](https://openairdocs.org/ad/2026-20-01): Fuselage · Boeing 787-8, 787-9 and 787-10. Effective Nov 2, 2026 - [AD 2026-20-02](https://openairdocs.org/ad/2026-20-02): Air · Boeing 787-8, 787-9, Trent 1000-A and 17 more. Effective Oct 14, 2026 - [AD 2026-17-02](https://openairdocs.org/ad/2026-17-02): Wings · Boeing 787-8, 787-9 and 787-10. Effective Oct 1, 2026 - [AD 2026-13-07](https://openairdocs.org/ad/2026-13-07): Equipment/furnishings · Boeing 787-8, 787-9 and 787-10. Effective Aug 6, 2026 - [AD 2026-12-07](https://openairdocs.org/ad/2026-12-07): Auto flight · Boeing 787-8, 787-9 and 787-10. Effective Jul 20, 2026 - [AD 2026-13-02](https://openairdocs.org/ad/2026-13-02): Navigation · Airbus Canada Limited Partnership 18, 49-46, 80-A and 555 more. Effective Jul 1, 2026 - [AD 2026-13-11](https://openairdocs.org/ad/2026-13-11): Navigation · Boeing 787-8, 787-9 and 787-10. Effective Jul 1, 2026 - [AD 2026-09-01](https://openairdocs.org/ad/2026-09-01): Water/waste · Boeing 787-8, 787-9 and 787-10. Effective Jun 3, 2026 - [AD 2026-05-01](https://openairdocs.org/ad/2026-05-01): Navigation · Boeing 787-8, 787-9 and 787-10. Effective Apr 16, 2026 - [AD 2026-02-10](https://openairdocs.org/ad/2026-02-10): Water/waste · Boeing 787-8, 787-9 and 787-10. Effective Mar 9, 2026 - [AD 2026-01-04](https://openairdocs.org/ad/2026-01-04): Fuselage · Boeing 787-9 and 787-10. Effective Feb 20, 2026 - [AD 2026-01-06](https://openairdocs.org/ad/2026-01-06): Fuselage · Boeing 787-9 and 787-10. Effective Feb 20, 2026 - [AD 2025-23-05](https://openairdocs.org/ad/2025-23-05): Fuselage · Boeing 787-8, 787-9 and 787-10. Effective Jan 13, 2026 - [AD 2025-23-06](https://openairdocs.org/ad/2025-23-06): Fuselage · Boeing 787-9 and 787-10. Effective Jan 13, 2026 - [AD 2025-20-03](https://openairdocs.org/ad/2025-20-03): Equipment/furnishings · Boeing 787-8, 787-9 and 787-10. Effective Nov 6, 2025 - [AD 2025-18-02](https://openairdocs.org/ad/2025-18-02): Oxygen · Boeing 787-8, 787-9 and 787-10. Effective Oct 22, 2025 - [AD 2025-11-05](https://openairdocs.org/ad/2025-11-05): Fuselage · Boeing 787-8, 787-9 and 787-10. Effective Jul 8, 2025 - [AD 2025-06-13](https://openairdocs.org/ad/2025-06-13): Fuselage · Boeing 787-9 and 787-10. Effective Jul 2, 2025 - [AD 2025-09-12](https://openairdocs.org/ad/2025-09-12): Fuselage · Boeing 787-8, 787-9 and 787-10. Effective Jun 18, 2025 - [AD 2025-06-10](https://openairdocs.org/ad/2025-06-10): Stabilizers · Boeing 787-8, 787-9 and 787-10. Effective May 2, 2025 - [AD 2025-01-09](https://openairdocs.org/ad/2025-01-09): Windows · Boeing 787-8, 787-9 and 787-10. Effective Mar 11, 2025 - [AD 2024-22-05](https://openairdocs.org/ad/2024-22-05): Landing gear · Boeing 787-8, 787-9 and 787-10. Effective Dec 31, 2024 - [AD 2024-18-02](https://openairdocs.org/ad/2024-18-02): Equipment/furnishings · Boeing 787-8, 787-9 and 787-10. Effective Nov 12, 2024 - [AD 2024-16-07](https://openairdocs.org/ad/2024-16-07): Navigation · Boeing 787-8, 787-9 and 787-10. Effective Oct 23, 2024 - [AD 2024-13-05](https://openairdocs.org/ad/2024-13-05): Nacelles/pylons · Boeing 787-8, 787-9 and 787-10. Effective Sep 24, 2024 - [AD 2024-16-14](https://openairdocs.org/ad/2024-16-14): Equipment/furnishings · Boeing 787-8, 787-9 and 787-10. Effective Aug 21, 2024 - [AD 2024-01-04](https://openairdocs.org/ad/2024-01-04): Turbine/turboprop engine · Boeing 787-9, 787-8 and 787-10. Effective Mar 7, 2024 - [AD 2023-25-10](https://openairdocs.org/ad/2023-25-10): Equipment/furnishings · Boeing 787-8, 787-9 and 787-10. Effective Feb 7, 2024 - [AD 2023-19-09](https://openairdocs.org/ad/2023-19-09): Auto flight · Boeing 787-8, 787-9 and 787-10. Effective Nov 6, 2023 - [AD 2023-10-09](https://openairdocs.org/ad/2023-10-09): Fire Protection · Boeing 787-8, 787-9 and 787-10. Effective Jun 26, 2023 - [AD 2023-12-10](https://openairdocs.org/ad/2023-12-10): Navigation · Boeing 787-8, 787-9 and 787-10. Effective Jun 21, 2023 - [AD 2023-08-02](https://openairdocs.org/ad/2023-08-02): Cargo and accessory compartments · Boeing 787-8, 787-9 and 787-10. Effective Jun 20, 2023 - [AD 2023-10-02](https://openairdocs.org/ad/2023-10-02): Indicating/Recording System, Navigation · Boeing 18, 23, 35 and 1,060 more. Effective May 26, 2023 - [AD 2023-05-04](https://openairdocs.org/ad/2023-05-04): Hydraulic power · Boeing 787-8, 787-9 and 787-10. Effective May 12, 2023 - [AD 2022-24-11](https://openairdocs.org/ad/2022-24-11): Fire protection · Boeing 787-8, 787-9 and 787-10. Effective Jan 18, 2023 - [AD 2022-14-04](https://openairdocs.org/ad/2022-14-04): Fuel · Boeing 787-8, 787-9 and 787-10. Effective Oct 6, 2022 - [AD 2022-15-01](https://openairdocs.org/ad/2022-15-01): Stabilizers · Boeing 787-8, 787-9 and 787-10. Effective Aug 25, 2022 - [AD 2022-09-08](https://openairdocs.org/ad/2022-09-08): Stabilizers · Boeing 787-8, 787-9 and 787-10. Effective Jul 7, 2022 - [AD 2022-03-21](https://openairdocs.org/ad/2022-03-21): Fuel · Boeing 787-8, 787-9 and 787-10. Effective Apr 11, 2022 - [AD 2022-02-14](https://openairdocs.org/ad/2022-02-14): Main landing gear · Boeing 787-8, 787-9 and 787-10. Effective Mar 30, 2022 - [AD 2021-24-14](https://openairdocs.org/ad/2021-24-14): Thrust Reverser · Boeing 787-8, 787-9 and 787-10. Effective Feb 15, 2022 - [AD 2021-23-20](https://openairdocs.org/ad/2021-23-20): Fuselage · Boeing 787-8 and 787-9. Effective Jan 10, 2022 - [AD 2021-23-21](https://openairdocs.org/ad/2021-23-21): Fuselage · Boeing 787-8 and 787-9. Effective Jan 10, 2022 - [AD 2021-02-06](https://openairdocs.org/ad/2021-02-06): Fire protection · Boeing 787-10, 787-8 and 787-9. Effective Mar 30, 2021 - [AD 2020-20-09](https://openairdocs.org/ad/2020-20-09): Flight Controls · Boeing 787-8 and 787-9. Effective Nov 13, 2020 - [AD 2020-17-13](https://openairdocs.org/ad/2020-17-13): Air conditioning · Boeing 787-8 and 787-9. Effective Oct 8, 2020 - [AD 2020-17-02](https://openairdocs.org/ad/2020-17-02): Fuel, Engine · Boeing 747-8 Series, 747-8F Series, 787-10 and 2 more. Effective Aug 25, 2020 - [AD 2020-05-26](https://openairdocs.org/ad/2020-05-26): Nacelles/Pylons · Boeing 787-8. Effective May 4, 2020 All 125: https://openairdocs.org/tcds/T00021SE/ads.md ## Registered aircraft by registry model (OpenAirDocs) - [Boeing 787-9](https://openairdocs.org/model/boeing-787-9): 118 aircraft (registry code 1385609) - [Boeing 787-8](https://openairdocs.org/model/boeing-787-8): 75 aircraft (registry codes 1388002, 05628NI) - [Boeing 787-10](https://openairdocs.org/model/boeing-787-10): 21 aircraft (registry codes 1386010, 1386011) ## STCs approved under this data sheet (93, first 50) - [STC ST02730SE](https://openairdocs.org/stc/ST02730SE): Installation of a VIP interior. Greenpoint Technologies, Inc. - [STC ST12361SE](https://openairdocs.org/stc/ST12361SE): Replacement of Business Class Venture Seat Furniture Obsolescence parts (brush seals, backshell primer, gloss clear coat, and hook-and-loop velcro fasteners). Jamco America Inc. - [STC ST02528LA](https://openairdocs.org/stc/ST02528LA): Installation of the Thales Avionics, Inc. Data Transfer Device (DTD) or Solid State Drive (SSD) into the existing Cabin Media Loader (CML). Thales Avionics Inc. - [STC ST09847DS](https://openairdocs.org/stc/ST09847DS): This STC enables activation of business mini-suites doors. United Airlines - [STC ST04474NY](https://openairdocs.org/stc/ST04474NY): Activation of Wireless Local Area Network (WLAN) system. Jet Aviation AG - [STC ST04254NY](https://openairdocs.org/stc/ST04254NY): Installation of Viasat Satcom Software. ALOFT AeroArchitects - [STC ST00197IB](https://openairdocs.org/stc/ST00197IB): Installation of the Universal Quick Access Recorder (uQAR). Flight Data Technologies Inc. - [STC ST09918AC](https://openairdocs.org/stc/ST09918AC): Installation of a VIP interior. Northwest Aerospace Technologies, Inc. - [STC ST04388AT](https://openairdocs.org/stc/ST04388AT): Class Divider Installation. AIRCRAFT RECONFIG TECHNOLOGIES, LLC - [STC ST02708SE](https://openairdocs.org/stc/ST02708SE): Replacement of an Electronic Module Assembly (EMA) for an inflatable restraint system. Greenpoint Technologies, Inc. - [STC ST02711SE](https://openairdocs.org/stc/ST02711SE): Installation of structural provisions for a treadmill. Greenpoint Technologies, Inc. - [STC ST02735SE](https://openairdocs.org/stc/ST02735SE): Electrical outlet installation - Boeing 787-8 and 787-9 VIP. Greenpoint Technologies, Inc. - [STC ST04328NY](https://openairdocs.org/stc/ST04328NY): The Manufacture and Installation of Exterior Placards, Labels and Signs is to be performed, installed. Libellule Monde Inc - [STC ST03875NY](https://openairdocs.org/stc/ST03875NY): Installation of interior placards, signs and markings. Libellule Monde Inc. - [STC ST12335IB](https://openairdocs.org/stc/ST12335IB): Installation of B787-9 Cabin Modification. Lufthansa Technik AG - [STC ST09845DS](https://openairdocs.org/stc/ST09845DS): Foldable Table Installation. United Airlines - [STC ST00030IB](https://openairdocs.org/stc/ST00030IB): Installation of Test Tech ELT. APTOZ EHF - [STC ST03885AT](https://openairdocs.org/stc/ST03885AT): Installation of an Avionica, Inc. avCM Cellular Module. Aircraft Systems and Manufacturing Inc. - [STC ST12096CH](https://openairdocs.org/stc/ST12096CH): Panasonic In-Flight Entertainment (IFE) and Viasat In-Flight Connectivity (IFC) System Integration. Envoy Aerospace LLC - [STC ST04566AT](https://openairdocs.org/stc/ST04566AT): Replacement of the AY01-BEA-TSPCU-LRU-01 Touch Screen Power Control Unit (TSPCU) with the AV2232 to control the premium cabin seats position. B/E Aerospace, Inc Aftermarket Services (B/E-AS) - [STC ST12053IB](https://openairdocs.org/stc/ST12053IB): Installation of LATAM 787-9 Cabin Reconfiguration. BOEING IRELAND LIMITED - [STC ST11266DS](https://openairdocs.org/stc/ST11266DS): Activation of business class mini-suite doors. American Airlines Inc., M&E Engineering Division - [STC ST12056IB](https://openairdocs.org/stc/ST12056IB): The Manufacture and Installation of External Printed Aircraft Graphics Film. Libellule Monde Inc. - [STC ST11261DS](https://openairdocs.org/stc/ST11261DS): Installation ofUmlaut HAFEX UL (a Halon-Equivalent) Handheld Fire Extinguishers in the passenger cabin, flight deck, and overhead flight and cabin crew rests Interior modification. American Airlines Inc. - [STC ST11928SE](https://openairdocs.org/stc/ST11928SE): Installation of an interior reconfiguration. Northwest Aerospace Technologies Inc. - [STC ST02472AT](https://openairdocs.org/stc/ST02472AT): Installation of a mini Quick Access Recorder (QAR) model MKI, MKII, or MKIII. Aircraft Systems and Manufacturing Inc. - [STC ST03436NY](https://openairdocs.org/stc/ST03436NY): Installation of a Panasonic Avionics Corporation Global Communications Suite (GCS) and/or In-Flight Entertainment System. Delta Engineering Corporation - [STC ST00079IB](https://openairdocs.org/stc/ST00079IB): Integration of Halon-free Portable Fire Extinguisher HAFEX. UMLAUT ENGINEERING GMBH - [STC ST04078NY](https://openairdocs.org/stc/ST04078NY): Update of Intelsat Cabin Connectivity and Connectivity Antenna. Delta Engineering Corporation - [STC ST00215IB](https://openairdocs.org/stc/ST00215IB): Installation of saf-Tglo ECO Photoluminescent Aisle Path Marking Systems. STG AEROSPACE GERMANY GmbH - [STC ST00211IB](https://openairdocs.org/stc/ST00211IB): Installation of Cabin layout configuration from 338 Passenger (56 Premium Economy (PY) / 282 Tourist Class (Y)) to 320. BOEING IRELAND LIMITED - [STC ST02709SE](https://openairdocs.org/stc/ST02709SE): Modification of existing Jamco lavatory doors to install a new door handle, latch knob and placards. Jamco America Inc. - [STC ST00186IB](https://openairdocs.org/stc/ST00186IB): Installation of Avianca Cabin Reconfiguration. Boeing Ireland Limited - [STC ST02773SE](https://openairdocs.org/stc/ST02773SE): Replacement of existing decorative laminate. Jamco America Inc. - [STC ST04574AT](https://openairdocs.org/stc/ST04574AT): Installation of the Avionics Support Group Constant Friction Mount (cfMount) and Cradle. Avionics Support Group Inc. - [STC ST00126IB](https://openairdocs.org/stc/ST00126IB): Replacement of Halon agent with alternate Halon-free Portable Fire Extinguisher agent. AMAC Aerospace Switzerland AG - [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 ST00110IB](https://openairdocs.org/stc/ST00110IB): Introduction of Premium Economy Cabin (PEC). BOEING IRELAND LIMITED - [STC ST04609CH](https://openairdocs.org/stc/ST04609CH): Medical Interior Installation. Spectrum Aeromed LLC - [STC ST00105IB](https://openairdocs.org/stc/ST00105IB): Introduction of Activation of Wireless Charging Systems for Portable Electronic Devices. AMAC AEROSPACE SWITZERLAND AG - [STC ST00074IB](https://openairdocs.org/stc/ST00074IB): Introduction of Premium Economy Cabin (PEC) for KLM. BOEING IRELAND LIMITED - [STC ST03422NY](https://openairdocs.org/stc/ST03422NY): Update of Intelsat components. Delta Engineering Corporation - [STC ST04693NY](https://openairdocs.org/stc/ST04693NY): Installation of VIP Cabin Interior "Silkroad. Lufthansa Technik AG - [STC ST01963WI](https://openairdocs.org/stc/ST01963WI): Installation of Integra Pulse Portable Oxygen Bottle. B/E Aerospace - [STC ST02755LA](https://openairdocs.org/stc/ST02755LA): Installation of Cargo Handling Access Door Assembly. Hartwell Corporation - [STC ST02545AK](https://openairdocs.org/stc/ST02545AK): Provisioning of aircraft for zero passengers and no cargo on the passenger compartment floor. Altech Aerospace LLC - [STC ST04096NY](https://openairdocs.org/stc/ST04096NY): Update of VIP Cabin Interior. Delta Engineering Corporation - [STC ST04433NY](https://openairdocs.org/stc/ST04433NY): Installation of United Airlines Cabin Reconfiguration - Business Class, Premium Economy and Economy Class Seating. Boeing Ireland Limited - [STC ST04453NY](https://openairdocs.org/stc/ST04453NY): Installation of United Airlines Cabin Reconfiguration - Business Class, Premium Economy and Economy Class Seating. Boeing Ireland Limited - [STC ST04524NY](https://openairdocs.org/stc/ST04524NY): Removal of passenger seats for Zero Occupancy in Passenger Cabin. Boeing Ireland Limited All 93: https://openairdocs.org/tcds/T00021SE/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.