TCDS T00063IB

Page No. 1 2 3 4 5 6 7 8 9 10 11 12 13 14 15 16 Rev. No. 28 25 24 17 12 25 27 23 26 22 22 23 26 28 17 28 DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION T00063IB Revision 28 Airbus A350-941 A350-1041 September 2, 2026 FAA TYPE CERTIFICATE DATA SHEET NO. T00063IB This data sheet is part of Type Certificate No. T00063IB and prescribes conditions and limitations under which the product for which the Type Certificate was issued meets the airworthiness requirements of the US Federal Aviation Regulations. Type Certificate Holder Airbus S.A.S. 2 Rond-point Emile Dewoitine 31700 Blagnac France I. A350-900 Series Transport Category Airplanes Model A350-941 (Transport Category), Approved November 12, 2014 A350-941 Type Design defined in Airbus document A350-941 FAA Type Design Definition, ref. 00 V 000 A F941 / C90 issue 2 dated April 8, 2015. Engines A350-941: Two (2) Rolls Royce Trent XWB-84, Trent XWB-84EP (Mod 120074), or Trent XWB-75 (Mod 113768) turbofan engines; Engine Type Certificate E00086EN. XWB-84 engine can be intermixed with XWB-84EP on the same aircraft. Fuel NOMENCLATURE SPECIFICATION KEROSENE JET A, JET A1, JP5, JP8, N° 3 Jet Fuel, RT and TS-1 Additives: See Rolls Royce Operating Instructions. The above-mentioned fuels are also suitable for the Auxiliary Power Unit. Engine Limits Engine Limitations (See FAA Data Sheet E00086EN) A350-941 RR Trent XWB-84 Basic Rating RR Trent XWB-75 (Mod 113768) RR Trent XWB-84 EP (Mod 120074) Net Take-off (5 minutes) 374.5 kN (84,200 lbf) 330 kN (74,200 lbf) 374.5 kN (84,200lbf) Net Maximum Continuous 317.6 kN (71,400 lbf) 296.3 kN (66,600 lbf) 317.6kN (71,400lbf_ Approved Oil Refer to the Engine Operating Instructions for information on approved oil specifications for the Trent XWB Table references: The take-off thrust, with the associated limits, shall not be used continuously more than 5 minutes. The duration may be extended to 10 minutes in case of engine failure in multi -engine aircraft. If the duration exceeds 5 minutes, this shall be recorded in the engine log book. Other engine limitations: See the relevant Engine Type Certificate Data Sheet (E00086EN). Airspeed Limits Refer to the FAA approved Airbus A350 Model A350-941 U.S. Airplane Flight Manual: STL 35000. Revision 28 Page 2 of 16 T00063IB Center of Gravity Limits Refer to the FAA approved Airbus A350 Model A350-941 U.S. Airplane Flight Manual: STL 35000. Datum The airplane reference zero datum point is located 210.24 in. (5.34 m) forward of the nose section, 5 in. (.127 m) above the floor reference. Leveling Means Quick leveling procedures are provided in the Aircraft Maintenance Manual (AMM), task A350-A-08-21 (see also WBM chapter “CTL-GRD”). Maximum Weights With Trent XWB-84 Engines: Baseline Weight Variant (000): Maximum Take off Weight (MTOW): 268,000 kgs (590,839 lbs.) Maximum Landing Weight (MLW): 205,000 kgs (451,948 lbs.) Maximum Zero Fuel Weight (MZFW): 192,000 kgs (423,288 lbs.) Heaviest Certified Weights with Trent XWB-84 Engines or Trent XWB-84EP MTOW: 283,000 kgs (623,908 lbs.) MLW: 207,000 kgs (456, 357 lbs.) MZFW: 195,700 kgs (431,445 lbs.) (MSN 5 only, MZFW: 197,200 kgs (434, 752 lbs.)) Heaviest Certified Weights with Trent XWB-75 Engines (Mod 113768) MTOW: 255,000 kgs (562,179 lbs.) MLW: 207,000 kgs (456,357 lbs.) MZFW: 195, 700 kgs (431,445 lbs.) Note: See applicable Aircraft Flight Manual (AFM), as listed in the “Operating and Service Instructions,” for configuration specific mass limitations and aircraft eligibility (weight variants). Minimum Crew Two (2): Pilot and Co-pilot Maximum Passenger Seating Capacity The maximum number of passengers approved for emergency evacuation is: - 385 for the passenger doors configuration C-A-A-A and A-A-C-A, - 275 for the passenger doors configuration C-C-C-A, - 330 for the passenger doors configuration C-A-C-A, - 440 for the passenger doors configuration A-A-A-A. - 480 for the passenger doors configuration A+-A+-A+-A+ (see ELOS memorandum AT11003IB-T-CS-1015) Further limitations on passenger distribution ar e contained in Passenger Seat Frame Specification document, ref. 00V252K0005/C91 at latest approved issue, or 00V252K0005/C01 at the latest approved issue, and must be maintained in order to comply with §§ 25.803(c) and 25.807(e). Maximum Compartment Weights Cargo Compartment Maximum Load (basic) Mods 110456 and 11512 kg lb kg lb Forward 22,000 48,501 0 0 Aft 19,000 41,888 19,000 41,888 Rear (bulk) 3,468 7,646 3,468 7,646 For the positions and the loading conditions authorized in each position (references of containers, pallets and associated we ights), see Weight and Balance Manual Chapter 1.10 ref. 00 V 080 A0001 / C9S. Revision 28 Page 3 of 16 T00063IB Fuel Capacity Tanks Usable Fuel Usable Fuel with Mod 110211 Liters kg US Gallons lb Liters kg US Gallons lb Wing 29,924 23,490 7,905 51,786 29,726 23,335 7,853 51,445 Center 80,947 63,543 21,384 140,088 107,036 84,023 28,276 185,239 Total 140,795 110,523 37,194 243,660 166,488 130,693 43,981 288,129 Maximum Operating Altitude 43,100 feet Control Surface Movements Control Surface Maximum Travel Aileron +20°/-30° #1,2 Spoilers +12° / -35° #3 to 7 Spoilers +13° / -50° Aileron Droop 10º Flaps 37.5º Slats 27º Stabilizers +0.8º / -13.7º Elevator +20º / -30º Rudder +35º / -35º Import Requirements Refer to the applicable bilateral agreement to verify eligibility for import into the United States of both new and used aircraft based on the scope of the agreement, to identify any required statements by the exporting authority on the export certificate of airworthiness (or equivalent document), and for procedures for coordinating exceptions to conformity statements on these documents. Refer to FAA Order 8130.2, Airworthiness Certification of Aircraft, for requirements for issuance of an airworthiness certificate for imported aircraft. In order for the FAA to determine that a Model A350-900 aircraft is in a condition for safe operation under the provisions of 14 CFR 21.183, prior to issuance of the U.S. airworthiness certificate the FAA certificating inspector or other authorized person must ensure the aircraft complies with the FAA Required Airworthiness Action List (RAAL) for the A350-900. The RAAL contains a list of type design modifications and inspections that have been determined by the European Union Aviation Safety Agency (EASA), which is the state of design authority for the Airbus A350-900, to be required to correct unsafe conditions discovered on the original type design of the A350-900. EASA has issued Airworthiness Directives that require the accomplishment of these modifications and inspections to correct the identified unsafe conditions and has advised the FAA of this mandatory continuing airworthiness information (MCAI). Based on this MCAI the FAA has determined that the airworthiness actions identified in the EASA ADs listed in Model A350-900 RAAL are required in the interest of safety and are necessary for this airplane to be in a condition for safe operation. Prior to issuance of a Standard Certificate of Airworthiness (C of A) on any Airbus A350-900 model aircraft, all airworthiness actions shown in the Model A350-900 RAAL must be accomplished in accordance with the compliance times listed in the MCAI, except as noted in the RAAL. The MCAI listed in the RAAL are airworthiness limitations in addition to those listed in note 3 of this TCDS and must be included in the operator’s airplane maintenance or inspection program. All inspections or modifications, required by the EASA MCAI, that have surpassed the initial compliance time, must be accomplished prior to issuance of the C of A. The A350-900 RAAL is finalized through its publication in TCDS Revision 2 and requirements will not be added by later TCDS revisions. Therefore, the RAAL in TCDS T00063IB Revision 2 or any later TCDS revision are equivalent and acceptable for compliance. All future mandatory modifications and inspections that the FAA determines must be accomplished on U.S. registered aircraft will be addressed by issuance of an Airworthiness Directive (AD). Any deviation from the requirements of the MCAIs listed in the RAAL must be approved by the Manager, Certification Program Management Branch, AIR-510, FAA Integrated Certificate Management Division; 2200 South 216th Street; Des Moines, Washington 98198, telephone 1-516-228-7300. A Notice of Policy Statement announcing the FAA’s policy with respect to foreign MCAI, when no aircraft of the affected design are currently registered in the U.S. was published in the Federal Register on May 1, 1998, docket 98-11648. Additional guidance is contained in FAA advisory Circular 21-23, Airworthiness Certification of Civil Aircraft, Engines, Propellers, and Related Products Imported into the United States. Revision 28 Page 4 of 16 T00063IB FAA Required Airworthiness Action List (RAAL) for the Airbus Model A350-900 aircraft are listed in the table below. RAAL # (MCAI) EASA AD # & Date Airbus Service Information EASA AD Title Applicable Airplane Models Compliance Time 1 2015-0241R2 13-Jan-17 ID 13-Jan-17 ED AOT A27P007- 15-00 original issue, dated 15 December 2015 ATA 27 – Flight Controls – Aileron Electro-Hydrostatic Actuator – Inspection / Replacement A350-941 airplanes, all serial numbers, except those on which Airbus modification (mod) 109426 or mod 109427 has been embodied in production Before 14 days after 28 December 2015 [the ED of the original issue of this AD and thereafter every flight day, not exceeding 2 FCs 2 2016-0074 15-Apr-16 ID 22-Apr-16 ED SB A350-78-P001 original issue dated 25 January 2016 ATA 78 – Exhaust – Thrust Reverser Actuation System – Replacement A350-941 airplanes, all serial numbers Before 750FC since first flight or 50FC after the AD ED, whichever occurs later. 3 2017-0027 15-Feb-17 ID 01-Mar-17 ED A350 ALS Part 2 Revision 03 dated 28 June 2016. ATA 05 – Time Limits / Maintenance Checks – Damage Tolerant Airworthiness Limitation Items – ALS Part 2 – Amendment A350-941 airplanes, all serial numbers See MCAI This MCAI has been superseded and is now addressed via FAA AD. 4 2017-0029 15-Feb-17 ID 01-Mar-17 ED Airbus A350 ALS Part 3 Revision 03 dated 24 June 2016. ATA 05 – Time Limits / Maintenance Checks – Certification Maintenance Requirements - ALS Part 3 – Amendment A350-941 airplanes, all serial numbers See MCAI This MCAI has been superseded and is now addressed via FAA AD. 5 2017-0030 15-Feb-17 ID 01-Mar-17 ED Airbus A350 ALS Part 4 Revision 02 dated 24 June 2016. ATA 05 – Time Limits / Maintenance Checks – System Equipment Maintenance Requirements – ALS Part 4 – Amendment A350-941 airplanes, all serial numbers See MCAI This MCAI has been superseded and is now addressed via FAA AD. 6 2017-0093 24-May-17 ID 31-May-17 ED Airbus SB A350- 53-P017 original issue, dated 25 January 2017. ATA 53 – Fuselage – Potable Water Tank Brackets – Modification Airbus A350-941 airplanes, manufacturer serial numbers (MSN) 0021 to 0025 inclusive, 0027 to 0029 inclusive, 0032 to 0036 inclusive, 0038 to 0040 inclusive, 0042 to 0053 inclusive, 0055 to 0058 inclusive, 0061, 0064, 0066 and 0067. Within 7 months after the AD ED Note 1: “ID” is EASA AD issue date, “ED” is effective date Note 2: Compliance with the FAA Required Airworthiness Action List for Airbus Model A350-900 Aircraft as included under the Import Requirements section of TCDS Revision 2, dated June 23, 2017, or later TCDS revision, is necessary for an A350-900 aircraft to be found in a condition for safe operation. The FAA has accepted:  Model A350-941 aircraft in the Airbus as-delivered configuration for MSN 115 and on as compliant with the applicable modifications of the A350 RAAL.  RAAL Items 3, 4, and 5 may be complied with in accordance with later EASA-approved revisions of the respective ALS part. Certification Basis For the model A350-941 airplane, the certification basis is 14 CFR part 25, effective February 1, 1965, including Amendments 25- 1 through 25-129. Revision 28 Page 5 of 16 T00063IB Special Conditions: Item Special Condition No. Subject 1 25-537-SC Crashworthiness – Emergency Landing Conditions [Docket No. FAA-2013-0892; Special Conditions No. 25-537-SC] 2 25-535-SC High-Speed Protection System [Docket No. FAA-2013-1001; Special Conditions No. 25-535-SC] 3 25-532-SC Interaction of Systems and Structures [Docket No. FAA-2013-0894; Special Conditions No. 25-532-SC] 4 25-516-SC Design Roll Maneuver Requirement [Docket No. FAA-2013-0895; Special Conditions No. 25-516-SC] 5 25-529-SC Limit Pilot Forces Because of Side Stick Controller [Docket No. FAA-2013-0896; Special Conditions No. 25-529-SC] 6 25-523-SC Transient Engine Failure Loads [Docket No. FAA-2013-0897; Special Conditions No. 25-523-SC] 7 25-524-SC Ground Pivoting Loads [Docket No. FAA–2013–0890; Special Conditions. 25–524–SC] 8 25-526-SC Composite Fuselage In-Flight Fire/Flammability Resistance [Docket No. FAA–2013–0898; Special Condition. No. 25–526–SC] 9 25-459-SC Flammability Requirements of Aircraft Seats [Docket No. FAA–2012–0325; Special Condition No. 25–459–SC] 10 25-460A-SC Crew Rest Compartments [Docket No. FAA–2012–0343; Special Condition No. 25–460A–SC] 11 25-517-SC Flight Envelope Protection: High Incidence Protection and Alpha Floor Systems [Docket No. FAA-2012-1207; Special Conditions No. 25-517-SC] 12 25-522-SC Electronic Flight Control System: Control Surface Awareness and Mode Annunciation [Docket No. FAA-2013-0899; Special Conditions No. 25-522-SC] 13 25-540-SC Flight Envelope Protection: General Limiting Requirements [Docket No. FAA-2013-0900; Special Conditions No. 25-540-SC] 14 25-536-SC Flight Envelope Protection: High Speed Limiting [Docket No. FAA-2013-0901; Special Conditions No. 25-536-SC ] 15 25-521-SC Flight Envelope Protection: Pitch and Roll Limiting [Docket No. FAA-2013-0902; Special Conditions No. 25-521-SC] 16 25-529-SC Side Stick Controllers [Docket No. FAA–2013–0896;Special Conditions No. 25–529–SC] 17 25-542-SC Electronic Flight Control System: Lateral-Directional and Longitudinal Stability and Low Energy Awareness [Docket No. FAA-2013-0904; Special Conditions No. 25-542-SC] 18 25-531-SC Flight Envelope Protection: Normal Load Factor (g) Limiting [Docket No. FAA-2013-0905; Special Conditions No. 25-531-SC] 19 25-530-SC Lightning Protection of Fuel-Tank Structure To Prevent Fuel-Tank Vapor Ignition [Docket No. FAA-2013-1002; Special Conditions No. 25-530-SC] 20 25-541-SC Tire Failure – Debris Penetration or Rupture of Fuel Tank Structure [Docket No. FAA-2013-0907; Special Conditions No. 25-541-SC] 21 25-538-SC Post-Crash Fire Survivability: Airplane Level of Safety Provided by Composite Fuel Tank Structure [Docket No. FAA-2013-0908; Special Conditions No. 25-538-SC ] 22 25-533-SC Electronic System-Security Protection From Unauthorized External Access [Docket No. FAA-2013-0909; Special Conditions No. 25-533-SC] 23 25-534-SC Isolation or Protection of the Aircraft Electronic System Security From Unauthorized Internal Access [Docket No. FAA-2013-0910; Special Conditions No. 25-534-SC] 24 25-562-SC Permanently Installed Rechargeable Lithium-Ion Batteries and Battery Systems [Docket No. FAA-2013-0801; Special Conditions No. 25-562-SC] 25 25-561-SC Operation without Normal Electrical power [Docket No. FAA-2014-0303; Special Conditions No. 25-561-SC] 26 25-539-SC Lateral Trim Function through Differential Flap Setting [Docket No. FAA-2013-0911; Special Conditions No. 25-539-SC] Revision 28 Page 6 of 16 T00063IB Special Conditions: 27 25-683-SC Non Rechargeable Lithium Battery Installations [Docket No. FAA-2017-0370; Special Conditions No. 25-683-SC, effective to design changes applied for after May 31, 2017. See the applicability section of this special condition for more information on which design changes must meet it.] 28 25-860-SC Incorporation of Inertia Locking Device in Dynamic Seats [Docket No. FAA-2024-0449; Special Condition No. 25-860-SC] NOTE: The FAA Special Conditions referenced above may be accessed at internet location: http://www.drs.faa.gov Equivalent Level of Safety Findings: Item Section Subject ELOS Memo reference (1) §§ 25.107(e)(1)(iv) Reduced Margins Between Takeoff Rotation Speed and Liftoff Speed for Geometry Limited Airplanes TC0544IB-T-F-13 (2) §§ 25.251 Vibration/Buffeting AT12025IB-T-F-23 (3) §§ 25.331 Checked Pitch Maneuver Loads TC0544IB-T-A-7 (4) §§ 25.341 Continuous Turbulence Loads and Rough Airspeed TC0544IB-T-A-10 (5) §§ 25.365(a) Pressurized Compartment Loads TC0544IB-T-A-8 (6) §§ 25.471, 25.473, 25.477, 25.479, 25.481, 25.485, 25.491, 25.493, 25.499, 25.503, 25.507, 25.511, 25.519, 25.723 Ground Load Conditions TC0544IB-T-A-11 (7) §§ 25.495 Ground Turning Conditions TC0544IB-T-A-12 (8) §§ 25.671(c)(1) Slat Geared Rotary Actuator Failure TC0544IB-T-SF-6 (9) §§ 25.671(c)(2) Flight Control System Failure Criteria TC0544IB-T-SF-5 (10) §§ 25.779(b)(1) Reduced (flexible) takeoff Thrust Operations and Throttle Motion TC0544IB-T-P-7 (11) §§ 25.783(a) APU Maintenance Doors TC0544IB-T-CS-14 (12) §§ 25.783(e)(2) Passenger/Crew Doors Closed Latched Locked Indication TC0544IB-T-CS-10 (13) §§ 25.795(a)(1) Reduced intrusion loads in certain areas of the flight deck boundaries TC0544IB-T-CS-13 (14) §§ 25.807(g) Type A-plus emergency exits AT11003IB-T-CS-1015 (15) §§ 25.811(g), 25.812(b)(1) Use of Symbolic Exit Signs TC0544IB-T-CS-1 SEE NOTE 2 (16) §§ 25.811(e)(4) Green Arrow and "OPEN" Placard for Emergency Exit Marking” TC0544IB-T-CS-12 (17) §§ 25.831(g) Cabin Temperature-Humidity Limits TC0544IB-T-ES-15 (18) §§ 25.841(a), 25.841(b)(6) Cabin Pressurization – High Altitude Takeoff and Landing Operations TC0544IB-T-ES-14 (19) §§ 25.841(b)(1), 25.843(b)(1) Overpressure Relief valves and Outflow valves TC0544IB-T-ES-11 (20) §§ 25.856(b), appendix F part VII Composite Fuselage Post-Crash Fire Survivability TC0544IB-T-CS-5 (21) §§ 25.933(a)(1) Prevention of Inadvertent In-flight Thrust Reverser Deployment TC0544IB-T-P-10 (22) §§ 25.934 Thrust Reverser Testing TC0544IB-T-P-33 (23) §§ 25.963(d) Fuel Tank Emergency Loads TC0544IB-T-A-13 (24) §§ 25.979 (b)(1) Pressure fueling System shut-off operation check TC0544IB-T-P-24 (25) §§ 25.981(b) Aircraft Descent Rate for Fuel Tank Flammability Reduction Assessment TC0544IB-T-P-30 (26) §§ 25.1191(b)(1) Firewall Caps and Seals Fire Withstanding Capability AT10383IB-T-P-1038 (27) §§ 25.1193(e)(3) Cowlings and Nacelle Skins Fireproof Regions TC0544IB-T-P-31 (28) §§ 25.1195(c) Fire Extinguishing Agent Concentration TC0544IB-T-P-25 (29) §§ 25.1203(d) Turbine Overheat Detection TC0544IB-T-P-19 (30) §§ 25.1301, 25.1309 Use of ARAC Recommended Revision to §§ 25.1301 and 25.1309 TC0544IB-T-S-2 (31) §§ 25.1305(c)(6) Warning Means for Engine Fuel Filter Contamination TC0544IB-T-P-9 (32) §§ 25.1317(b) HIRF Equipment Protection Test Levels TC0544IB-T-SE-11 (33) §§ 25.1329 Pitot Heat Indication TC0544IB-T-SA-23 (34) §§ 25.1383(b) Single Landing Light Switch TC0544IB-T-SE-5 Revision 28 Page 7 of 16 T00063IB Equivalent Level of Safety Findings: (35) §§ 25.1438 Pneumatic Systems TC0544IB-T-ES-10 (36) §§ 25.1441(c) Crew Determination of Quantity of Oxygen in Passenger Gaseous Oxygen System Distributed Cylinders TC0544IB-T-ES-7 (37) §§ 25.1443 Minimum Oxygen Flow rates TC0544IB-T-ES-13 (38) §§ 25.1443 (d) Portable First Aid Oxygen Equipment AT11173IB-T-25.1443-1 (39) §§ 25.1447(c)(1) Improved Passenger Oxygen Mask Deployment System TC0544IB-T-ES-3 (40) §§ 25.1457(d)(5) Independent Power Source for Cockpit Voice Recorder TC0544IB-T-SA-5 (41) §§ 25.1529 Instructions for Continued Airworthiness TC0544IB-T-G-5 (42) §§ 25.1549(a) Oil temperature Indication TC0544IB-T-P-16 (43) §§ 25.1549 Digital Only Display of the Turbine Engine High (N3), Intermediate (N2), and Fan (N1) Rotor Speeds TC0544IB-T-F-16 (44) 14 CFR 25 Subpart E, F, and G requirements applicable to APU installation Adoption of Draft Harmonized Rules for APU Certification TC0544IB-T-P-11 (45) §§ 25.1535, K25.2.2(c) Validation of Maintenance Procedures for ETOPS Significant Systems TC0544IB-T-EE-7 (46) §§ 25.1563 Airspeed Placard AT11145IB-T-25.1563-1 NOTE 1: The FAA Equivalent Level of Safety Memos referenced above may be accessed at internet location: http://www.drs.faa.gov NOTE 2: For airplanes equipped with pictograms on exit marking signs and on exit location signs, the cabin crew in char ge of the safety briefing must highlight these pictograms to the passengers prior to each takeoff and each landing. Exemptions: (1) §§ 25.562(b)(2) per Amendment 25-64 Emergency Landing Dynamic Conditions Exemption No. 9999 (2) §§ 25.841(a)(2) and (3), per Amendment 25-87 Cabin Pressurization Exemption No. 10228 (3) §§ 25.809(a), per Amendment 25-116 Outside viewing of the flight deck emergency exit Exemption No. 10996 (4) §§ 25.813(e), per Amendment 25-129 and 121.310(f)(5) and (f)(6) Installation of doors on mini-suites (32 mini-suites installed) Exemption No. 17186 (5) §§ 25.813(e), per Amendment 25-129 and 121.310(f)(5) and (f)(6) Installation of doors on mini-suites (40 mini-suites installed) Exemption No. 22021 NOTE: The FAA Exemptions referenced above may be accessed at internet location: http://www.drs.faa.gov Modifications Changing the Certification Basis: Modification Number Revision (or later) 14 CFR Requirements Added for Affected Areas 109178 Issue 2 25.1302 at Amendment 25-137 Type A+ doors, modification numbers: 110654 110655 110656 110657 114823 115016 Issue 1 Regulations at Amendment 25-0 to Amendment 25-144: 25.561(c), 25.601, 25.603(a)(b)(c), 25.605(a)(b), 25.789(a), 25.795(d), 25.801(a), 25.801(d), 25.803 (a), 25.803(c), 25.807(a)(7), 25.807(g), 25.807(i), 25.807(f), 25.809, 25.810 (a)(1), 25.811(d)(2), 25.811(g), 25.812(h)(k), 25.813, 25.853(a), 25.869(a)(3), 25.901(c), 25.1301 (a)(1),(a)(2),(a)(3), 25.1309 (a)(b), 25.1411(c)(d), 25.1415(a)(b)(c), 25.1438, 25.1501, 25.1561(a)(d)(e), 25.1701 (a), 25.1703 (a)(b)(c), 25.1705 (a), 25.1707 (a)(d)(l), 25.1709 (a)(b), 25.1711(a)(c)(d)(e), 25.1713(a)(c) ELOS memorandum AT11003IB-T-CS-1015 for Type A plus emergency exits for 25.807 (g) 14 CFR part 26 at Amendment 26-6 Installed Physical Secondary Barrier (IPSB) modification number: 120762 Issue 1 25.795(a)(4) at Amendment 25-150 Environmental Standards: 14 CFR part 34, effective September 10, 1990, including Amendments 34-1 through 34-5A. Revision 28 Page 8 of 16 T00063IB 14 CFR part 36, Stage 4, effective December 1, 1969, including Amendments 36-1 through 36-28: or 14 CFR part 36, Stage 5, effective December 1, 1969, including Amendments 36-1 through 36-31, only for airplanes where Airbus Airplane Flight Manual CP81, Issue 1.0, dated September 14, 2018, or later approved revision, is installed on the airplane. Optional Requirements Elected: (1) Sections 25.801, 25.1411 and 25.1415 for ditching (2) Section 25.1419 for ice protection (3) The type-design reliability and performance of the A350-941 has been evaluated in accordance with 14 CFR 25.1535 and found suitable for 180-minute maximum diversion time extended operations (ETOPS) when the configuration, maintenance, and procedures standards contained in the applicable revision of Airbus document reference, “XWB/FAA: 14 CFR 25.1535/CMP” are met. This finding does not constitute approval to conduct ETOPS. The type-design reliability and performance of the A350 -941 has been evaluated in accordance with 14 CFR 25.1535 and found suitable for greater than 180-minute extended operations (ETOPS) as follows: For aircraft equipped with Modification 107318: The type-design reliability and performance of the A350-941 has been evaluated in accordance with 14 CFR 25.1535 and found suitable for 300- minute maximum diversion time extended operations (ETOPS) when the configuration, maintenance, and procedures standard contained in the applicable revision of Airbus document reference, “XWB/FAA: 14 CFR 25.1535/CMP,” are met. This finding does not constitute approval to conduct ETOPS. For aircraft equipped with Modification 107319: The type-design reliability and performance of the A350-941 has been evaluated in accordance with 14 CFR 25.1535 and found suitable for 370- minute maximum diversion time extended operations (ETOPS)