TCDS A58NM

Page No. 1 2 3 4 5 6 7 8 9 10 Rev. No. 11 7 10 5 9 9 11 9 8 11 DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION A58NM Revision 11 Airbus A380-841 A380-842 A380-861 July 25, 2024 FAA TYPE CERTIFICATE DATA SHEET NO. A58NM This data sheet which is part of Type Certificate No. A58NM 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 SAS 2 , Rond-Point Emile Dewoitine, 31707 Blagnac France I. A380-800 Series Transport Category Airplanes Model A380-841, Approved December 12, 2006 Model A380-842, Approved December 12, 2006 Model A380-861, Approved December 14, 2007 Engines A380-841: Four Rolls Royce RB211 Trent 970-84 or RB211 Trent 970B-84 turbofan engines; Engine Type Certificate E00075EN A380-842: Four Rolls Royce RB211 Trent 972-84 or RB211 Trent 972B-84 turbofan engines; Engine Type Certificate E00075EN A380-861: Four (4) Engine Alliance GP7270 turbofan engines ; Engine Type Certificate E00072EN Fuel NOMENCLATURE SPECIFICATION FRANCE U.S.A. U.K. RUSSIA CHINA KEROSENE DCSEA 134 (JET A1 ) Kerosene ASTM D-1655- (Jet A), (Jet A1) DEF STAN 91- 91 AVTUR RJFS0 GOST 10227 – 86, (RT) (TS-1) PRC MPIS GB 6537-2006 (No3 Jet Fuel) USA Air Force MIL-DTL- 83133 (JP8) DEF STAN 91- 87 AVTUR FSII FAoTR&M GOST R 52050-2006 (JET A1) DCSEA 144 (JP 5 ) Kerosene US Navy MIL- DTL-5624 (JP5) DEF STAN 91- 86 AVTUR FSII Additives: See Rolls Royce Operating Instructions (OI-Trent-A380) or Engine Alliance Service Bulletin EAGP7-73-1. The above-mentioned fuels are also suitable for the Auxiliary Power Unit. Revision 11 Page 2 of 10 A58NM Engine Limits Engine Limitations (See FAA Engine Data Sheet E00075EN) A380-841 RB211 Trent 970B-84 A380-842 RB211 Trent 972B-84 Static Thrust at Sea Level - Take-off (5mn)1 (flat rated 30oC) 348.31 kN or 78,303 lbf 356.81 kN or 80,214 lbf Approved Oil Refer to the Engine Operating Instructions (OI-Trent-A380) for information on approved oil specifications for the Trent 900 Refer to the Engine Operating Instructions (OI-Trent-A380) for information on approved oil specifications for the Trent 900 Engine Limitations (See FAA Engine Data Sheet E00072EN) A380-861 Engine Alliance GP7270 Static Thrust at Sea Level - Take-off (5mn)2 (flat rated 30oC) 332.44 kN or 74,735 lbf Approved Oil Refer to the Engine Alliance Service Bulletin EAGP7-79-1 for the listing of approved oils for use in the GP7200 series turbofan engine Table references: (1) 10 minutes at take-off thrust allowed only in case of engine failure (at take-off or during go-around) (2) The normal 5-minute take-off rating may be extended to 10 minutes for engine out contingency in accordance with the FAA Engine TCDS Note 2. Other engine limitations: See the relevant Engine Type Certificate Data Sheet. Airspeed Limits Refer to the FAA approved Airbus Model A380-841, A380-842 and A380-861 U.S. Airplane Flight Manuals. Center of Gravity Limits Refer to the FAA approved Airbus Model A380-841, A380-842 and A380-861 U.S. Airplane Flight Manuals. Datum The airplane reference zero datum point is located 288.59 in. (7.3302 m) forward of the nose section, 257.59 in. (7.000 m) under the fuselage centerline (datum line). Leveling Means Inclinometer on cabin seat track rails (refer to AMM chapter 08.20.00). Revision 11 Page 3 of 10 A58NM Maximum Weights Variant 000 Basic kg (lb) 001 kg (lb) 002 kg (lb) Maximum Ramp Weight 562,000 (1,239,000) 512,000 (1,128,800) 571,000 (1,258,800) Maximum Take-off Weight, MTOW 560,000 (1,234,600) 510,000 (1,124,400) 569,000 (1,254,400) Maximum Landing Weight, MLW 386,000 (850,980) 394,000 (868,620) 391,000 (862,010) Maximum Zero Fuel Weight, MZFW 361,000 (795,870) 372,000 (820,120) 366,000 (806,890) Variant 003 kg (lb) 004 kg (lb) 005 kg (lb) Maximum Ramp Weight 512,000 (1,128,766) 562,000 (1,239,000) 562,000 (1,239,000) Maximum Take-off Weight, MTOW 510,00 (1,124,400) 560,000 (1,234,600) 560,000 (1,234,600) Maximum Landing Weight, MLW 395,000 (870,826) 391,000 (862,010) 386,000 (850,980) Maximum Zero Fuel Weight, MZFW 373,000 (822,324) 366,000 (806,890) 366,000 (806,890) Variant 006 kg (lb) 007 kg (lb) 008 kg (lb) Maximum Ramp Weight 575,000 (1,267,657) 492,000 (1,084,674) 577,000 (1,272,066) Maximum Take-off Weight, MTOW 573,000 (1,260,600) 490,000 (1,078,000) 575,000 (1,265,000) Maximum Landing Weight, MLW 393,000 (864,600) 395,000 (869,000) 394,000 (866,800) Maximum Zero Fuel Weight, MZFW 368,000 (809,600) 373,000 (820,600) 369,000(811,800) Variant 009 kg (lb) 010 kg (lb) 011 kg (lb) Maximum Ramp Weight 512,000 (1,128,766) 482,000 (1,062,627) 577,000 (2,272,066) Maximum Take-off Weight, MTOW 510,000 (1,124,400) 480,000 (1,056,000) 575,000 (1,265,000) Maximum Landing Weight, MLW 386,000 (850,980) 386,000 (850,980) 395,000 (869,000) Maximum Zero Fuel Weight, MZFW 361,000 (794,200) 361,000 (794,200) 369,000 (811,800) Variant 012 kg (lb) 013 kg (lb) Maximum Ramp Weight 571,000 (1,258,839) 494,000 (1,089,083) Maximum Take-off Weight, MTOW 569,000 (1,251,800) 492,000 (1,084,674) Maximum Landing Weight, MLW 395,000 (869,000) 386,000 (850,984) Maximum Zero Fuel Weight, MZFW 366,000 (809,600) 361,000 (795,868) Minimum Crew Two (2): Pilot and Co-pilot Maximum Passenger Seating Capacity The maximum eligible passenger seating capacity is 538 on the main deck and 330 on the upper deck for a total of868. Maximum Compartment Weights Cargo Compartment Maximum Load (kg) or (lb) Forward 28,577 Kg or 63,000 lb Aft 20,310 Kg or 44,775 lb Rear (bulk) 2,515 Kg or 5,540 lb For the positions and the loading conditions authorized in each position (references of containers, pallets and associated weight) see Weight and Balance Manual, Airbus Document 00L080H0001/C0S, chapter 1.10. Revision 11 Page 4 of 10 A58NM Fuel Capacity Tanks Usable Fuel Unusable Fuel Liters (Kg) Gallons (lb) Liters (Kg) Gallons (lb) Wing Outer Left 10,340 (8,272) 2,732 (18,237) 38 (30) 10 (66) Feed 1 27,632 (22,106) 7,302 (48,735) 82 (66) 22 (145.5) Mid Left 36,461 (29,169) 9,635 (64,307) 50 (40) 13.2 (88.2) Inner Left 46,142 (36,914) 12,193 (81,381) 70 (56) 18.5 (123.5) Feed 2 29,349 (23,479) 7,756 (51,762) 88 (70) 23.3 (154.3) Feed 3 29,349 (23,479) 7,756 (51,762) 88 (70) 23.3 (154.3) Inner Right 46,142 (36,914) 12,193 (81,381) 70 (56) 18.5 (123.5) Mid Right 36,461 (29,169) 9,635 (64,307) 50 (40) 13.2 (88.2) Feed 4 27,632 (22,106) 7,302 (48,735) 82 (66) 22 (145.5) Outer Right 10,340 (8,272) 2,732 (18,237) 38 (30) 10 (66) Trim 23,698 (18,958) 6,262 (41,795) 49 (39) 13 (86) Systems 793 (634) 210 (1398) 382 (305) 101 (672.4) Total 324339 (259471) 85,707 (572,035) 1086 (869) 287 (1915.8) Maximum Operating Altitude 43,000 feet Control Surface Movements INBOARD / MEDIAN / OUTBOARD AILERONS (surface deflection angles) DOWN POSITION UP POSITION Maximum operational deflections (computer software limitations) 20° -30° Actuator stops (min/max) 23.6°/24.7° -34.2°/-35.5° Structural stops > 25.7° <-36.5° SPOILERS 1 to 8 (extended positions Spoilers 1 and 2 Spoilers 3 to 6 Spoilers 7 and 8 Maximum operational deflections (computer software limitations) 35° 50° 50° Actuator stops (min/max) 39.6°/39.9° 52.7°/53.2° 53.7°/54.3° Structural stops >40.9° >54.2° >55.3 INBOARD / OUTBOARD ELEVATORS (surface deflection angles) DOWN POSITION UP POSITION Maximum operational deflections (computer software limitations) 20° -30° Actuator stops (min/max) 22.8°/23.6° -33.1°/-33.9° Structural stops > 24.6° <-34.9° Revision 11 Page 5 of 10 A58NM THS (surface deflection angles) NOSE UP NOSE DOWN Maximum operational deflections (computer software limitations) -10° 2° THSA stops -10.44°/-10.56° 2.94°/3.06° Interference between THS and the tail cone -10.7° 3.3° UPPER AND LOWER RUDDERS (surface deflection angles) RH turn LH turn Maximum operational deflections (computer software limitations) -30° 30° Actuator stops (min/max) -32.3°/-33.2° 32.3°/33.2° Interference between the rudders and VTP <-34.2° >34.2° Manufacturer’s Serial Numbers Import Requirements The FAA can issue a U.S. airworthiness certificate based on an NAA Export Certificate of Airworthiness (Export C of A) signed by a representative of the exporting foreign civil airworthiness authority on behalf of the European Community. The Export C of A should contain the following statement: ‘The aircraft covered by this certificate has been examined, tested, and found to conform with the Type Design approved under U.S. Type Certificate No. A58NM, and is in a condition for safe operation. Compliance with Airworthiness Directives (ADs) has been checked only for ADs issued by EASA, ADs adopted by EASA and ADs published by FAA.’ At the time of the first airplane import the latest approved Revision of each Airworthiness Limitation Section (ALS) listed under the Note 3 must be incorporated in the maintenance program. After the first airplane import the later revision of an ALS will be mandated by Airworthiness Directive. 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 an A380 aircraft is in a condition for safe operation under the provisions of 14 CFR 21.183, the FAA certificating inspector or other authorized person must contact the Manager, Europe, Middle East, & African Section, International Validation Branch, Compliance & Airworthiness ,Division, Aircraft Certification Service; 2200 South 216th Street Des Moines, Washington 98198; telephone (206)-231-3645, prior to issuance of the U.S. airworthiness certificate to obtain the FAA Required Airworthiness Action List (RAAL) for the A380. After the first airplane is imported to the U.S. the RAAL will be finalized and published in the TCDS. When the TCDS is amended to include the RAAL, a notice will be published in the Federal Register, to inform the public of this amendment. The RAAL contains a list of type design modifications and inspections that have been determined by the European Aviation Safety Agency (EASA), which is the state of design authority for the Airbus A380, to be required to correct unsafe conditions discovered on the original type design of the A380. EASA has issued Airworthiness Directives that require the accomplishment Revision 11 Page 6 of 10 A58NM 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 A380 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 Airworthiness Certificate on any Airbus A380 model aircraft, all airworthiness actions listed in the Model A380 RAAL must be accomplished in accordance with the compliance times listed in each 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 Standard Airworthiness Certificate. Any deviation from the requirements of the MCAIs, listed in the RAAL, must be approved by the Manager, Europe, Middle East, & African Section, International Validation Branch, Compliance & Airworthiness Division, Aircraft Certification Service. 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. Certification Basis For model A380-841/842 series airplanes, the certification basis is 14 CFR part 25, effective February 1, 1965, including Amendments 25-1 through 25-98, with elected Amendments 25-101, 25-103 through 25-106, 25-108, 25-109, 25-113 and 25- 114. For Model A380-841/842 series airplanes with modification 78298, extended operation (ETOPS) with 280 Minutes Capability Airbus elected to comply with CFR 14 part 25 sections 25.1535 at Amendment 25-120. For Model A380-861 Series Airplanes, the certification basis is revised to require 14 CFR Part 25 at the following amendment levels: Amendment 99 for § 25.2 Amendment 100 for §§ 25.903, 25.1091 Amendment 101 for § 25.1183, with elected Amendments 25-103 through 25-106, 25-108, 25-109, 25-113 and 25-114. Special Conditions: (1) No. 25-315-SC Discrete Gust Requirements (2) No. 25-333-SC Transient Engine Failure Loads (3) No. 25-321-SC Crashworthiness (4) No. 25-322-SC Airplane Jacking Loads (5) No. 25-326-SC Stairways Between Decks (6) No. 25-327-SC Emergency Exit Arrangement (Outside Viewing) (7) No. 25-330-SC Escape System Inflation System (8) No. 25-329-SC Escape Systems in non-Pressurized compartments (9) No. 25-323-SC Extendable-Length Escape Slides (10) No. 25-328-SC Flotation and Ditching (11) No. 25-340-SC Fire Protection (12) No. 25-316-SC Dynamic Braking (13) No. 25-324-SC Loading Conditions for Multi-Leg Landing Gear (14) No. 25-316-SC Interaction of Systems and Structure (15) No. 25-316-SC Limit Pilot Forces (16) No. 25-316-SC Dive Speed Definition (17) No. 25-338-SC Ground Turning Loads (18) No. 25-318-SC Design Roll Maneuver (19) No. 25-316-SC Flight Envelope Protection: High Incidence Protection and Alpha Floor Systems (20) No. 25-316-SC Electronic Flight Control System: Control Surface Awareness (21) No. 25-316-SC Flight Envelope Protection: General Limiting Requirements (22) No. 25-316-SC Flight Envelope Protection: Normal Load Factor (G) Limiting (23) No. 25-316-SC Flight Envelope Protection: High Speed Limiting (24) No. 25-316-SC Flight Envelope Protection: Pitch and Roll Limiting (25) No. 25-316-SC Side Stick Controllers Revision 11 Page 7 of 10 A58NM (26) No. 25-316-SC Electronic Flight Control System: Flight Characteristics Compliance via the Handling Qualities Rating Method (27) No. 25-316-SC Operation Without Normal Electrical Power (28) No. 25-316-SC Electronic Flight Control System: Lateral-Directional Stability, Longitudinal Stability, and Low Energy Awareness (29) No. 25-316-SC High Intensity Radiated Fields (HIRF) Protection (30) No. 25-335-SC Reinforced Bulkhead (31) No. 25-339-SC Lithium-Ion Battery Installations (32) No. 25-672-SC, Non-Rechargeable Lithium Batteries, effective to design changes applied for after May 16, 2017. See the applicability section of this special condition for more information on which design changes must meet it. (33) No. 25-832-SC Electronic System Security Protection From Unauthorized External Access (34) No. 25-833-SC Electronic System Security Protection From Unauthorized Internal Access NOTE: The FAA Special Conditions referenced above may be accessed at internet location: https://drs.faa.gov/browse/SCFINAL/doctypeDetails Equivalent Level of Safety Findings: (1) Section 25.629, Aeroelastic Stability Requirements (documented in TAD ELOS Memo CP101-A-5) (2) Section 25.331(c)(2), Checked Maneuver Loads (documented in TAD ELOS Memo CP101-A-7) (3) Sections 25.341(a)(i) and (b), 25.343(b)(1)(ii), 25.345(c)(2), 25.371, 25.373(a), 25.391 and 25.1517, Continuous Turbulence Loads (documented in TAD ELOS Memo CP101-A-09) (4) Section 25.963(d), Fuel Tank Loads (documented in TAD ELOS Memo CP101-A-10) (5) Section 25.963(e), Fuel Tank Access Covers (documented in TAD ELOS Memo CP101-A-11) (6) Section 25.671(c)(2), Flight Control System Failure Criteria (documented in TAD ELOS Memo CP101-A-21) (7) Section 25.810(a)(1)(ii) and (b), Escape System Inflation Time (documented in TAD ELOS Memo CP101-C-11) (8) Section 25.107(e)(1)(iv), Reduced Margins between Minimum Liftoff Speed and Minimum Safe Flyaway Speed (documented in TAD ELOS Memo CP101-F-17) (9) Section 25.933(a)(1)(ii), Flight Critical Thrust Reverser (documented in TAD ELOS Memo CP101-P-02) (10) Part 25 subpart E, F and G requirements applicable to APU installations, Adoption of Draft Harmonized Rules for APU Certification (documented in TAD ELOS Memo CP101-P-05) (11) Section 25.1305(c)(6), Trent 900 Warning Means for Engine Fuel Filter Contamination (documented in TAD ELOS Memo CP101-P-11) for A380-841/-842 models only (12) Section 25.1203(d), Trent 900 Overheat Detection (documented in TAD ELOS Memo CP101-P-13) for A380-841/-842 models only (13) Section 25.1549(a), Oil Temperature Indication (documented in TAD ELOS Memo CP101-P-15) (14) Section 841(b)(1), Tests for Pressurized Cabins (documented in TAD ELOS Memo CP101-S-15) (15) Section 831(g), Ventilation System Failures/Cabin Temperature and Humidity (documented in TAD ELOS Memo CP101-S-22) (16) Section 25.1383(b), Landing Light Switches (documented in TAD ELOS Memo CP101-S-23) (17) Section 25.841(b)(6), Cabin Pressurization – High Altitude Airfield Operations (documented in TAD ELOS Memo CP101-S-27) (18) Section 25.865, APU Mounting System Fireproofness (documented in TAD ELOS Memo CP101-P-18) (19) Section 25.1415(c), Ditching Equipment (documented in TAD ELOS Memo CP101-C-14) (20) Section 25.1305(c)(6), 997(d), Warning Means for Engine Fuel Strainer/Filter Contamination on GP7200 Engine Installation (documented in TAD ELOS Memo CP-101-T-P-17) for A380-861 model only (21) Section 25.856(b), Improved Flammability standards for Thermal/acoustic insulation materials (documented in TAD ELOS Memo TD0794IB-T-CI-5; Memo TD0794IB-T-CI-6 and Memo TD0794IB-T-CI-7). (22) Sections 25.811(g) and 25.812(b)(1), Symbolic Exit Sign (documented in TAD ELOS Memo TD01007IB-T-C-16) . (23) Section 25.1195(c). Fire Extinguishing Agent Concentration (documented in TAD ELOS Memo AT10272IB-T-P-1). (24) Section 25.779(b)(1). Throttle Motion During Go-around Operations (documented in TAD ELOS Memo AT10197IB-T-P-2). (25) Section 25.1457(d)(5). Cockpit Voice Recorder - (documented in TAD ELOS Memo TD00823IB-T-SE-32). NOTE: The FAA Equivalent Level of Safety Memos referenced above may be accessed at internet location: http://www.airweb.faa.gov/Regulatory_and_Guidance_Library/rgELOS.nsf/MainFrame?OpenFrameSet Elect to Comply: The following paragraph of 14 CFR Part 25 at amendment 111, dated September 2, 2003, is elected to comply by Airbus for A/C fitted with modification 67860: 14 CFR Part 25.856(b) Revision 11 Page 8 of 10 A58NM Exemptions: (1) Exemption No. 8538 for 14 CFR part 25 section 25.562(b)(2) Emergency Landing Dynamic Conditions (2) Exemption No. 8695A (Partial) for 14 CFR part 25 section 25.841(a)(2)(i), (ii), and (3), per Amendment 25-87, Pressurized Cabins NOTE: The FAA Exemptions referenced above may be accessed at internet location: http://www.airweb.faa.gov/Regulatory_and_Guidance_Library/rgEX.nsf/MainFrame?OpenFrameSet Environmental Standards: 14 CFR part 34, effective September 10, 1990, including Amendments 34-1 through 34-3. 14 CFR part 36, effective December 1, 1969, including Amendments 36-1 through 36-27, at Stage 4. 14 CFR part 36, effective December 1, 1969, including Amendments 36-1 through 36-31, at Stage 5 - Only Airbus individual aircraft of model A380-841 with TRENT 970 or TRENT 970 EP engines, A380-842 with TRENT 972/972E or TRENT 972/972E EP engines, or A380-861 with GP7270 or GP7270E engines that have Airbus Airplane Flight Manual CP63, Revision 1.0, dated August 9, 2018, or later approved revision installed and on board are considered certificated to 14 CFR part 36, Amendment 36-31 and compliant with Stage 5 noise limits. Optional Requirements Elected: (1) Sections 25.801, 25.1411 and 25.1415 for ditching (2) Section 25.1419 for ice protection (3) For aircraft equipped with Modification 78298: The type-design reliability and performance of the A380-841 and the A380-842 has been evaluated in accordance with 14 CFR 25.1535 and found suitable for 280-minute maximum diversion time extended operations (ETOPS) when the configuration, maintenance, and procedures standard contained in the applicable revision of Airbus document reference, “VL4/FAA: 14 CFR25.1535/CMP,” are met. This finding does not constitute approval to conduct ETOPS. Part 26 of the Federal Aviation Regulations: Based on 14 CFR Section 21.29(a) for new import Type Certificates (TCs), (or Section 21.101(g) for changes 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. Production Basis A380 airplanes, all series and models, are produced in France or Germany under production approval EASA.21G.0001 issued by the European Aviation Safety Agency, (EASA). Equipment The basic required equipment as prescribed in the applicable airworthiness regulations (see the Certification Basis) must be installed in the aircraft. Equipment approved for installation is listed in the following documents: - See A380-841/-842/-861 Type design definition Cabin furnishings, equipment and arrangement must conform to the following specification: - 00L252C0028/C01 for cabin seats, - 00L252C0027/C01 for galleys, - 00L252C0032/C01 for cabin attendant seats. Hydraulic Fluids Fluid specifications: Type IV LD (Low Density) and Type V LD as per NSA 307-110. Auxiliary Power Unit (APU) One Pratt & Whitney Canada PW980A Revision 11 Page 9 of 10 A58NM Tires The main wheels can be fitted with tires from two manufacturers: Michelin (Radial); 1400 x 530 R23 Bridgestone (Radial); 1400 x 530 R23 Tires mixability: See Service Bulletin A380-32-8021 (Landing Gear – Tires – General Procedures) for allowable combinations. The nose wheels can be fitted with tires from two manufacturers: Michelin (Radial) 1270 x 455 R22 Bridgestone (Radial) 1270 x 455 R22 Tire Loads and Pressures LOAD RATING RATED PRESSURE Service Pressure UNLOADED Service Pressure LOADED bar PSI bar PSI bar PSI WLG & BLG Tire 33336 daN 17.2 249 14.4 209 15.0 218 NLG Tire 24380 daN 16.2 235 13.3 193 13.9 202 Weather Capabilities The Model A380-800 is qualified to Cat. III precision approaches and autoland. Airplane Flight Manual Refer to A380-841 and A380-842 US Airplane Flight Manuals, Revision 0.3, Issue 1, both dated December 7, 2006, applicable to A380-841 and A380-842 airplanes. Refer to A380-861 US Airplane Flight Manual, Revision CP2, Issue 1.1, dated November 22, 2007, applicable to A380-861 airplane. Service Information Each of the documents listed below that contain a statement that it is approved by the European Aviation Safety Agency (EASA) are accepted by the FAA and are considered FAA approved. Additionally, approvals issued by Airbus under the authority of EASA approved Design Organization EASA.21J.031 are considered FAA approved. These approvals pertain to the type design only. • Airbus Service Bulletins, except as noted below, • Structural repair manuals, • Vendor manuals referenced in Airbus service bulletins, • Aircraft flight manuals, • Repair Instructions. Tire Type Size Ply Rating BLG & WLG: RADIAL 1400x530 R23 40PR NLG: RADIAL 1270x455 R22 32PR Revision 11 Page 10 of 10 A58NM Note: Design changes that are contained in Airbus Service Bulletins and that are classified as Level 1 Major or Non-Basic in accordance with either the US/France or US/EASA Bilateral Aviation Safety Agreement Implementation Procedures for Airworthiness must be approved by the FAA.