# TCDS A58NM: Airbus SAS

- Type: Type certificate data sheet
- Status: Current
- Holder: Airbus SAS
- Revision: 11
- Revised: July 25, 2024
- Product: Aircraft, Large Airplane
- Certification basis: Part 25, Part 21
- Registered aircraft: 4, by the registry models matched to it (OpenAirDocs)
- Data sheet PDF: https://openairdocs.org/files/sha256/32/9a/329a98798893eeb41bbe8a3e784996186b7da3a59510083d8e03df0aa21888ea
- FAA DRS: https://drs.faa.gov/browse/excelExternalWindow/DRSDOCID159945261520240731133746.0001
- Page: https://openairdocs.org/tcds/A58NM

## Models (3)

As the data sheet lists them.

- A380-841
- A380-842
- A380-861

## What the data sheet says

From the PDF's text layer, line by line; tables lose their columns. The PDF is the record.

```text
Page No. 1 2 3 4 5 6 7 8 9 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. 
 
 
Electrical Power Center Configuration Data File Tool 
An Airline Configuration Tool (ACTS) has been developed and qualified to allow airlines to manage the Configuration Data File  
of Secondary Power Distribution Boxes (SPDB). This ACTS tool shall be used in accordance with the SIL “Guidance on 
Electrical system Configuration Data File update” reference “SIL 24-085”. 
Applicable version of ACTS tool is version 2 (CSCI 51220010-7). 
 
 
Notes: 
 
Note 1:  A current weight and balance report including list of the equipment included in the certificated empty weight, and 
loading instructions, when necessary, must be provided for each aircraft at the time of original airworthiness certification and at 
all times thereafter. 
 
Note 2:    Airplane operation must be in accordance with the FAA approved Airplane Flight Manual.  All placards required by 
either the FAA approved AFM, the applicable operating rules, or the certification basis must be installed in the appropriate 
location in the airplane. 
 
Note 3:    Maintenance Instructions and Airworthiness Limitations: 
- Limitations applicable to Safe Life Airworthiness Limitation Items are provided in the A380 Airworthiness Limitations 
Section (ALS) Part 1, approved by EASA   
 
- Limitations applicable to Damage-Tolerant Airworthiness Limitation Items are provided in the A380 (ALS Part 2  , 
approved by EASA  
 
- Certification Maintenance Requirements are provided in the A380 ALS Part 3, approved by EASA  
 
- A380- 800 Ageing System Maintenance are provided in the A380 ALS Part 4, approved by EASA  
 
-  A380- 800 Fuel Airworthiness Limitations are provided in the A380 ALS Part 5, approved by EASA  
 
- Airworthiness corrective actions required by the EASA ADs listed in the A380 RAAL. 
 
 
Note 4: Per 14 CFR 21.50, the Instructions for Continued Airworthiness, as defined in 14 CFR 25.1529 and Appendix H, must be 
complete and accepted by the FAA prior to delivery of the first aircraft or issuance of a standard certificate of airworthine ss, 
whichever occurs later.   Contact the Seattle Aircraft Evaluation Group for information. 
 
...END...
```

## ADs (23, in force first)

- [AD 2026-14-04](https://openairdocs.org/ad/2026-14-04): Fuselage · Airbus A319-111, A319-112, A319-113 and 56 more. Effective Aug 14, 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 2024-11-01](https://openairdocs.org/ad/2024-11-01): Electrical Power · Airbus A300 B4-2C, A300 B4-103, A300 B4-203 and 94 more. Effective Jul 3, 2024
- [AD 2024-08-08](https://openairdocs.org/ad/2024-08-08): Electrical Power · Airbus A300 B4-2C, A300 B4-103, A300 B4-203 and 94 more. Effective Jun 6, 2024
- [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 2021-22-07](https://openairdocs.org/ad/2021-22-07): Fire Bottle, Portable · Airbus A319-111, A319-112, A319-113 and 127 more. Effective Nov 18, 2021
- [AD 2021-02-12](https://openairdocs.org/ad/2021-02-12): Equipment/furnishings · Airbus A330-201, A330-202, A330-203 and 27 more. Effective Mar 30, 2021
- [AD 2018-23-12](https://openairdocs.org/ad/2018-23-12): Equipment/furnishings · Airbus A300 B2-1A, A300 B2-1C, A300 B2-203 and 180 more. Effective Dec 28, 2018
- [AD 2017-19-05](https://openairdocs.org/ad/2017-19-05): Smoke Detection · Airbus A330-201, A330-202, A330-203 and 30 more. Effective Oct 31, 2017
- [AD 2014-17-02](https://openairdocs.org/ad/2014-17-02): Communications · Airbus A300 B2-1A, A300 B2-1C, A300 B2-203 and 137 more. Effective Sep 9, 2014
- [AD 2011-12-01](https://openairdocs.org/ad/2011-12-01): Equipment/Furnishings · Airbus A300 B2-1A, A300 B2-1C, A300 B2-203 and 268 more. Effective Aug 1, 2011
- [AD 2011-01-09](https://openairdocs.org/ad/2011-01-09): Oxygen · Airbus A300 B2-1A, A300 B2-1C, A300 B2-203 and 290 more. Effective Feb 9, 2011
- [AD 2010-02-05](https://openairdocs.org/ad/2010-02-05): Equipment/furnishings · Airbus A300 B2-1A, A300 B2-1C, A300 B2-203 and 73 more. Effective Jan 18, 2011
- [AD 2010-23-18](https://openairdocs.org/ad/2010-23-18): Pneumatic · Airbus A380-841, A380-842 and A380-861. Effective Nov 24, 2010
- [AD 2010-17-04](https://openairdocs.org/ad/2010-17-04): Wings · Airbus A380-841, A380-842 and A380-861. Effective Sep 2, 2010
- [AD 2010-04-10](https://openairdocs.org/ad/2010-04-10): Wings · Airbus A380-841, A380-842 and A380-861. Effective Mar 10, 2010
- [AD 2009-26-10](https://openairdocs.org/ad/2009-26-10): Wings · Airbus A380-841, A380-842 and A380-861. Effective Jan 15, 2010
- [AD 2009-15-09](https://openairdocs.org/ad/2009-15-09): Pneumatic · Airbus A380-841, A380-842 and A380-861. Effective Aug 5, 2009
- [AD 2025-10-12](https://openairdocs.org/ad/2025-10-12) (historical): Fuselage · Airbus A319-111, A319-112, A319-113 and 55 more. Effective Jul 2, 2025
- [AD 2021-21-02](https://openairdocs.org/ad/2021-21-02) (historical): Electrical Power · Airbus A340-211, A340-212, A340-213 and 8 more. Effective Dec 20, 2021
- [AD 2021-20-08](https://openairdocs.org/ad/2021-20-08) (historical): Electrical Power · Airbus A318-111, A318-112, A318-121 and 72 more. Effective Nov 18, 2021
- [AD 2013-18-09](https://openairdocs.org/ad/2013-18-09) (historical): Communications · Airbus A300 B2-1A, A300 B2-1C, A300 B2-203 and 137 more. Effective Oct 3, 2013
- [AD 2009-10-07](https://openairdocs.org/ad/2009-10-07) (historical): Air Transport Association (ATA) of America Code 57: Wings. · Airbus A380-841, A380-842 and A380-861. Effective May 28, 2009

## Registered aircraft by registry model (OpenAirDocs)

- [Airbus S A S A380-841](https://openairdocs.org/model/airbus-s-a-s-a380-841): 4 aircraft (registry code 3940335)

## STCs approved under this data sheet (26)

- [STC ST00885LA](https://openairdocs.org/stc/ST00885LA): Installation of fire extinguisher cartridges as replacements for Pacific Scientific fire extinguisher cartridges in fire extinguisher bottles.. AMETEK AMERON, LLC d/b/a MASS Systems
- [STC ST04254NY](https://openairdocs.org/stc/ST04254NY): Installation of Viasat Satcom Software. ALOFT AeroArchitects
- [STC ST12185SE](https://openairdocs.org/stc/ST12185SE): Installation of SpaceX Starlink Aero Terminal. Space Exploration Technologies Corp./Starlink Aviation
- [STC ST12324SE](https://openairdocs.org/stc/ST12324SE): Installation of SpaceX Starlink Aviation System. Space Exploration Technologies Corp./Starlink Aviation
- [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 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 ST00079IB](https://openairdocs.org/stc/ST00079IB): Integration of Halon-free Portable Fire Extinguisher HAFEX. UMLAUT ENGINEERING GMBH
- [STC ST04075NY](https://openairdocs.org/stc/ST04075NY): Installation of a Panasonic Avionics In-Flight Entertainment (IFE) System. Delta Engineering Corporation
- [STC ST04441CH](https://openairdocs.org/stc/ST04441CH): Installation of Honeywell RESCU 406AFN2 Emergency Locator Transmitter (ELT) System Upgrade. Honeywell International Inc.
- [STC ST03422NY](https://openairdocs.org/stc/ST03422NY): Update of Intelsat components. Delta Engineering Corporation
- [STC ST01963WI](https://openairdocs.org/stc/ST01963WI): Installation of Integra Pulse Portable Oxygen Bottle. B/E Aerospace
- [STC ST11214DS](https://openairdocs.org/stc/ST11214DS): Installation of Dukane underwater acoustic beacon. VT DRB Aviation Consultants
- [STC ST03884NY](https://openairdocs.org/stc/ST03884NY): Installation of VC on A380. Lufthansa Technik AG
- [STC ST03769NY](https://openairdocs.org/stc/ST03769NY): Installation of Data Broadband System. Lufthansa Technik AG
- [STC ST03723NY](https://openairdocs.org/stc/ST03723NY): Installation of Aviation Traders Limited's SmartCart Galley Carts. Aviation Traders Limited (Trading as ATL)
- [STC ST03710NY](https://openairdocs.org/stc/ST03710NY): Installation of 1000 Series photo luminescent floor path marking. Lufthansa Technik AG
- [STC ST09859AC](https://openairdocs.org/stc/ST09859AC): Installation of a SkyTender Beverage Trolley. ASIG LLC
- [STC ST03791NY](https://openairdocs.org/stc/ST03791NY): Installation of new Premium Economy Class in the main cabin of the main floor. Lufthansa Technik AG
- [STC SA7076NM](https://openairdocs.org/stc/SA7076NM): Installation of Stretcher Carrier.. Air Medic LLC
- [STC ST02540LA](https://openairdocs.org/stc/ST02540LA): Installation of Telair International LLC light weight P/Ns PMC100 and PAG100 series cargo pallets. Telair International LLC
- [STC ST02489LA](https://openairdocs.org/stc/ST02489LA): Installation of Telair International Inc. light weight LD3 (NAS3610 / SAE36100 - 2K2) cargo container P/N LD3100-31000ZZZ. Telair International LLC
- [STC ST02515LA](https://openairdocs.org/stc/ST02515LA): Installation of Thales Avionics In-flight Entertainment (IFE) Systems. Thales Avionics Inc
- [STC ST03453NY](https://openairdocs.org/stc/ST03453NY): Installation of Data Broadband Transceiver System with full provisions for On-Board Mobile Telephony System. Lufthansa Technik AG
- [STC ST00526WI-D](https://openairdocs.org/stc/ST00526WI-D): Modification of Collins VHF COMM Receiver Installation. Rockwell Collins Inc
- [STC ST02146NY](https://openairdocs.org/stc/ST02146NY): Installation of EMS Technologies Ltd. Cabin Network Xcelerator (CNX).. EMS Technologies Canada Ltd

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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.