# TCDS A43NM: Airbus SAS

- Type: Type certificate data sheet
- Status: Current
- Holder: Airbus SAS
- Revision: 14
- Revised: October 22, 2024
- Product: Aircraft, Large Airplane
- Certification basis: Part 25, Part 21
- Registered aircraft: 10, by the registry models matched to it (OpenAirDocs)
- Data sheet PDF: https://openairdocs.org/files/sha256/4b/13/4b13901a62254f75b837bb4d08a84ebf4c0fd84d523b68b2bc803e700ba74931
- FAA DRS: https://drs.faa.gov/browse/excelExternalWindow/DRSDOCID106088071920241023134341.0001
- Page: https://openairdocs.org/tcds/A43NM

## Models (8)

As the data sheet lists them.

- A340-541
- A340-311
- A340-313
- A340-211
- A340-312
- A340-213
- A340-642
- A340-212

## 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 14 9 10 11 12 13 14 15 16 17 18 19 20 21 22 
Rev. no. 14 12 12 12 12 12 12 12 12 12 12 12 12 12 12 12 14 14 12 13 14 12 
DEPARTMENT OF TRANSPORTATION 
FEDERAL AVIATION ADMINISTRATION 
 
 
A43NM 
Revision 14 
Airbus 
A340-200 Series: 
Models: A340-211, -212, -213 
 
A340-300 Series: 
Models: A340-311, -312, -313 
 
A340-500 Series: 
Models: A340-541 
 
A340-600 Series: 
Models: A340-642 
October 22, 2024 
 
FAA TYPE CERTIFICATE DATA SHEET NO. A43NM 
 
This data sheet which is part of Type Certificate No. A43NM 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, 
 31700 Blagnac, 
 France. 
 
Type Certificate Holder Record - Name change from Airbus Industrie to Airbus SAS January 2002 
 
 
 
I. Type A340-200 Series Transport Category Airplanes 
 
Airbus A340-211 - approved May 27, 1993 
Airbus A340-212 - approved July 7, 1994 
Airbus A340-213 - approved October 2, 1994 
 
Model: Definition of Reference Airplane by Airbus Documents: 
A340-211 FAA A340-211 Type Design, ref. AI/EA -N 415.0266/96 Issue 4, dated June 11, 1997, for type definition and 
Type Certification Standard Equipment List, ref. 00F000A0101/C0S. 
A340-212 FAA A340-212 Type Design, ref. AI/EA -N 415.0269/96 Issue 4, dated June 11, 1997, for type definition and 
Type Certification Standard Equipment List, ref. 00F000A0102/C0S. 
A340-213 FAA A340-213 Type Design, ref. AI/EA -N 415.0271/96 Issue 4, dated June 11, 1997, for type definition and 
Type Certification Standard Equipment List, ref. 00F000A0103/C0S. 
 
 
Engines 
 
Airplane Model Engine Model: Engine Type Certificate: 
A340-211 Four CFMI-CFM 56-5C2 or four CFM 56 -5C2/F or four CFM 
56-5C2/G.  Engine intermix between 5C2 and 5C2/F and 5C2/G 
on the same aircraft is allowed. 
FAA-Type Certificate E37NE 
A340-212 Four CFMI -CFM 56 -5C3/F or four CFM 56 -5C3/G. Engine 
intermix between 5C3/F and 5C3/G on the same aircraft is 
allowed. 
FAA-Type Certificate E37NE 
A340-213 Four CFMI-CFM56-5C4 FAA-Type Certificate E37NE

A43NM Page 2 of 22  
Maximum Weight 
 
Model A340-200 Airplane A340-211/-212/-213 
Weight Variant 
000 
(Basic) 
kg / lb 
001 
(MOD 41302) 
kg / lb 
Maximum Taxi Weight 254,400 / 560,855 257,900 / 568,572 
Maximum Take-off Weight, MTOW 253,500 / 558,871 257,000 / 566,588 
Maximum Landing Weight, MLW 181,000 / 399,037 181,000 / 399,037 
Maximum Zero Fuel Weight, MZFW 169,000 / 372,581 169,000 / 372,581 
 
Model A340-200 Airplane A340-213 
Weight Variant 
021 
(MOD 44281) 
kg / lb 
Maximum Taxi Weight 275,900 / 608,255 
Maximum Take-off Weight, MTOW 275,000 / 606,271 
Maximum Landing Weight, MLW 185,000 / 407,855 
Maximum Zero Fuel Weight, MZFW 173,000 / 381,400 
 
 
Maximum Baggage 
 
Cargo Compartment Maximum Load (kg / lb) 
Forward 18,507 / 40,800 
Aft 15,241 / 33,600 
Rear   3,468 /   7,645 
 
For the positions and the loading conditions authorized in each position (references of containers, pallets and associated we ight) see 
weight and Balance Manual: 
- A340-211/-212 Airbus Document ref. 00F080A0002/C2S 
- A340-213 Airbus Document ref. 00F080A0004/C0S 
 
 
Airplane Flight Manual 
 
Airplane operation must be in accordance with the EASA -Approved Airplane Flight Manual (AFM), US version, listed below, or later 
EASA approved revision applicable to the specific airplane model, modification status and serial number. 
 
Model A340-200: Airbus Document Refr. Revision No. Date 
A340-211 AI/EV-O 34000  1 May 27, 1993 
A340-212 AI/EV-O 34000  1 February 3, 1997 
A340-213 AI/EV-O 34000 1 February 3, 1997 
 
 
Data Pertinent to All Model 
 
See Section III, Data Pertinent to All Model A340-200 and A340-300 Series Airplanes. 
for information on Fuel, Engine Limits, Airspeed Limits, Center of Gravity Limits, Datum, Leveling Means, Minimum Crew, Number 
Seats, Fuel Capacity, Maximum Operating Altitude, Control Surface Movements, Certification Basis, Production Basis, Equipment , 
Hydraulic Fluids, Auxiliary Power Unit (APU), Tires and Environmental requirements for noise. 
 
See section VII, Data Pertinent to All Model A340-200, A340-300, A340-500 and A340-600 Series Airplanes. 
for information on Import Requirements, Service Information and General Notes.

A43NM Page 3 of 22  
 
II. Type A340-300 Series Transport Category Airplanes 
 
Airbus A340-311 - approved May 27, 1993 
Airbus A340-312 - approved July 7, 1994 
Airbus A340-313 - approved October 2, 1997 
 
The A340-300 series differs from the A340-200 series aircraft by the addition of 8 fuselage frames. 
 
Model: Definition of Reference Airplane by Airbus Documents: 
A340-311 FAA A340-311 Type Design, ref. AI/EA-N 415.02695/96 Issue 4, dated June 11, 1997, for type definition and 
Type Certification Standard Equipment List, ref. 00F000A0101/C0S. 
A340-312 FAA A340-312 Type Design, ref. AI/EA -N 415.0270/96 Issue 4, dated June 11, 1997, for type definition and 
Type Certification Standard Equipment List, ref. 00F000A0102/C0S. 
A340-313 FAA A340-313 Type Design, ref. AI/EA -N 415.0272/96 Issue 4, dated June 11, 1997, for type definition and 
Type Certification Standard Equipment List, ref. 00F000A0103/C0S. 
 
 
Engines 
 
Airplane Model Engine Model: Engine Type Certificate: 
A340-311 Four CFMI-CFM 56-5C2 or four CFM 56 -5C2/F or four CFM 
56-5C2/G.  Engine intermix between 5C2 and 5C2/F and 5C2/G 
on the same aircraft is allowed. 
FAA-Type Certificate E37NE 
A340-312 Four CFMI -CFM 56 -5C3/F or four CFM 56 -5C3/G. Engine 
intermix between 5C3/F and 5C3/G on the same aircraft is 
allowed. 
FAA-Type Certificate E37NE 
A340-313 Four CFMI -CFM56-5C4 or four CFM 56-5C4/P or four CFM 
56-5C4/1P. Engine intermix between 5C4 and 5C4/P on the 
same aircraft is allowed. 
FAA-Type Certificate E37NE 
 
 
Maximum Weight 
 
Model A340-300 Airplane A340-311/-312/-313 
Weight Variant 
000 
(Basic) 
kg / lb 
001 
(MOD 41302) 
kg / lb 
Maximum Taxi Weight 254,400 / 560,855 257,900 / 568,572 
Maximum Take-off Weight, MTOW 253,500 / 558,871 257,000 / 566,588 
Maximum Landing Weight, MLW 186,000 / 410,059 186,000 / 410,059 
Maximum Zero Fuel Weight, MZFW 174,000 / 383,604 174,000 / 383,604 
 
Model A340-300 Airplane A340-313 
Weight Variant 
002 
(MOD 44228)  
kg / lb  
003 
(MOD 44102) 
kg / lb 
004 
(MOD 44230) 
kg / lb 
Maximum Taxi Weight 260,900/ 575,186 257,900 / 568,572 260,900/ 575,186 
Maximum Take-off Weight, MTOW 260,000 / 573,201 257,000 / 606,588 260,000 / 573,201 
Maximum Landing Weight, MLW 186,000 / 410,059 188,000 / 414,469 188,000 / 414,469 
Maximum Zero Fuel Weight, MZFW 174,000 / 383,604 178,000 / 392,422 178,000 / 392,422

A43NM Page 4 of 22  
 
Model A340-300 Airplane A340-313 
Weight Variant 
020 
(MOD 43500)  
kg / lb  
021 
(MOD 44135) 
kg / lb 
023 
(MOD 44625) 
kg / lb 
024 
(MOD 45738) 
kg / lb 
Maximum Taxi Weight 271,900 / 599,436 275,900 / 608,255 262,900 / 579,595 275,900 / 608,255 
Maximum Take-off Weight, MTOW 271,000 / 597,452 275,000 / 606,271 262,000 / 577,611 275,000 / 606,271 
Maximum Landing Weight, MLW 190,000 / 418,878 190,000 / 418,878 190,000 / 418,878 192,000 / 423,287 
Maximum Zero Fuel Weight, MZFW 178,000 / 392,422 178,000 / 392,422 178,000 / 392,422 180,000 / 396,832 
 
Model A340-300 Airplane A340-313 
Weight Variant 
025 
(MOD 44791)  
kg / lb  
026 
(MOD 46613) 
kg / lb 
028 
(MOD 49529) 
kg / lb 
Maximum Taxi Weight 260,900 / 575,186 275,900 / 608,255 277,400 / 611,562 
Maximum Take-off Weight, MTOW 260,000 / 573,201 275,000 / 606,271 276,500 / 609,578 
Maximum Landing Weight, MLW 190,000 / 418,878 192,000 / 423,287 190,000 / 418,878 
Maximum Zero Fuel Weight, MZFW 178,000 / 392,422 181,000 / 399,036 178,000 / 392,422 
 
 
Maximum Baggage 
 
Cargo Compartment Maximum Load 
(kg / lb) 
Forward 22,861 / 50,399 
Aft 18,507 / 40,800 
Rear   3,468 / 7,645 
 
For the positions and the loading conditions authorized in each position (references of containers, pallets and associated weight) see 
weight and Balance Manual: 
- A340-311/-312 Airbus Document ref. 00F080A0002/C3S 
- A340-313 Airbus Document ref. 00F080A0004/C0S 
 
 
Airplane Flight Manual 
 
Airplane operation must be in accordance with the EASA-Approved Airplane Flight Manual (AFM), US version, listed below, or later 
EASA approved revision applicable to the specific airplane model, modification status and serial number. 
 
Model A340-300 Airbus Document Refr. Revision No. Date 
A340-311 AI/EV-O 34000 1 May 27, 1993 
A340-312 AI/EV-O 34000 1 February 3, 1997 
A340-313 AI/EV-O 34000 1 February 3, 1997 
 
 
Data Pertinent to All Model 
 
See Section III, Data Pertinent to All Model A340-200 and A340-300 Series Airplanes. 
for information on Fuel, Engine Limits, Airspeed Limits, Center of Gravity Limits, Datum, Leveling Means, Minimum Crew, Number 
Seats, Fuel Capacity, Maximum Operating Altitude, Control Surface Movements, Certification Basis, Production Basis, Equipment , 
Hydraulic Fluids, Auxiliary Power Unit (APU), Tires and Environmental requirements for noise. 
 
See section VII, Data Pertinent to All Model A340-200, A340-300, A340-500 and A340-600 Series Airplanes. 
for information on Import Requirements, Service Information and General Notes.

A43NM Page 5 of 22  
 
III. Data Pertinent to All Model A340-200 and A340-300 Series Airplanes 
 
Fuel 
 
 Specification 
Nomenclature United Sates France United Kingdom 
Kerosene ASTM D 1655 
(JET A) (JET A1) 
AIR 3405C DERD 
2494/2453 
Wide Cut ASTM D 1655 
(JET B) 
AIR 3407B DERD 
2454/2486 
 MIL-T 5624 (JP4) 
MIL-T 83133 (JP8) 
AIR 3407B DERD 
2454/2486 
 
Additives: According to CFMI "Specific Operating Instructions", installation manual. The above-mentioned fuels are also suitable 
for the APU. 
 
Engine Limits 
 
Engine Limitations 
CFMI CFM 56 
-5C2 -5C2/4 
-5C2/F -5C2/F4 
-5C2/G -5C2/G4 
CFMI CFM 56 
-5C3/F -5C3/F4 
-5C3/G -5C3/G4 
CFMI CFM 56 
-5C4 
-5C4/P -5C4/1P 
See FAA Data Sheet E37NE 
Static Thrust at Sea Level 
• Take-off (5 mn)1 (flat rated 30º C) 
• Maximum continuous 
(flat rated 25º C) 
 
13878 daN  (31,200 lbs) 
 
12588 daN  (28,300lbs) 
 
14456 daN (32,500 lbs) 
 
13077 daN (29,400 lbs) 
 
15123 daN (34,000 lbs) 
 
13371 daN (30,060 lbs) 
Maximum Engine Speed 
• N1 rpm (%) 
• N2 rpm (%) 
 
4800 (100.3%) 
15,183 (105%) 
 
4800 (100.3%) 
15,183 (105%) 
 
4985 (104.2%) 
15,183 (105%) 
Maximum Gas Temperature 
• Take-off (5mn)1 
• Maximum Continuous 
• Starting2 
 
 
950º C 
915º C 
725º C 
 
 
965º C 
930º C 
725º C 
 
 
975º C 
940º C 
725º C 
Maximum Oil Temperature 
(Supply Pump Outlet) ºC 
• Take-off, Stabilized 
• Transient (15 mn max.) 
Minimum Pressure 
 
 
 
140º C 
155º C 
89.6 KPa differential 
 
 
 
140º C 
155º C 
89.6 KPa differential 
 
 
 
140º C 
155º C 
89.6 KPa differential 
Approved oils See CFMI Service Bulletin CFMI 79-001 or GE specification D50TF1, Type I and II 
Table references: 
(1) 10 minutes at take-off thrust allowed only in case of engine failure (at take-off or during go-around). 
(2) 4 consecutive cycles of 2 minutes each 
 
Airspeed Limits (Indicated Airspeed, IAS, unless otherwise stated) 
 
• Maximum Operating Limit Speed/Mach, VMO/MMO 330 KIAS / .86 M 
• Design Diving Speed, VD 365 KIAS / .93 M 
• Design Maneuvering Speed, VA Refer to AFM performance Section 
• Maximum Flaps/Slats Extended Speed or Operating Speed, VFE  
Configuration Slats/Flaps º VFE (kt)  
1 20/0  
20/17 
240 
215 
Intermediate Approach 
Take-off 
2 24/22 196 Take-off and Approach 
3 24/26 186 Take-off, Approach, and Landing 
FULL 24/32 180 Landing

A43NM Page 6 of 22  
• Minimum Control Speed, VMC  Refer to AFM performance Section 
 (Performance Engineering Program/OCTOPUS) 
Landing Gear Speeds: 
• Maximum Speed with Landing Gear Operating (Extension and Retraction), VL0 250 KIAS / .55 M 
• Maximum Speed with Landing Gear Locked Down, VLE 250 KIAS / .55M 
• Tire Limit Speed (Ground Speed) 204 KTS 
 
 
Center of Gravity Limits 
 
Refer to EASA-Approved AFM, US Version, Limitations Section for center of gravity envelope.  
Note:  0% MAC is located 1275.51 in from the datum line.  
 
 
Datum 
 
The aircraft reference zero datum point is located 251.37 in.  (6.38 m) forward of the fuselage nose, 275.8 in. (7 m) under the fuselage 
centerline (datum line). 
 
 
Leveling Means 
 
Inclinometer on cabin seat track rails (refer to AMM chapter 08.20.00). 
 
 
Minimum Crew 
 
2 - Pilot and copilot 
 
 
Number of Seats 
 
The maximum number of passengers approved for emergency evacuation is: 
375 passengers with a 3 pair Type A and 1 pair Type 1 exits configuration, and 
A340-200: 420 passengers with 4 pair Type A exits configuration. 
A340-300: 440 passengers with 4 pair Type A exits configuration. 
 
 
Fuel Capacity 
 
 3 Tank Airplane 
 Usable Fuel Unusable Fuel 
Tank Liters 
(kg) 
gallons 
(lb) 
Liters 
(kg) 
gallons 
(lb) 
Wing 91,056  
(72,845) 
24,054 
(164,052) 
245 
(196) 
70 
(41) 
Center 41,468 
(33,174) 
10,955 
(74,173) 
83 
(66) 
22 
(150) 
Trim Tank 6,114 
(4,891) 
1,615 
(11,014) 
6 
(5) 
1.6 
(11) 
Total 138,638 
(110,910) 
36,627 
(249,796) 
334 
 (267) 
88 
(600) 
 
 
Maximum Operating Altitude 
 
• Basic: 41,100 feet (12,527m) slats and flaps retracted (clean) 
• Option: 41,450 feet (12,634m) slats and flaps retracted (clean) with modification 52536 
• 20,000 feet (6,096 m) slats or slats/flaps extended

A43NM Page 7 of 22  
Control Surface Movements  (Total one-way travel in each direction of each movable control surface on the aircraft.) 
 
Control Surface Maximum Travel 
Aileron +25/-25 
#1 Spoiler Speed Brake 25 
 Lift Dumper 35 
#2,3 Spoilers Roll 35 
 Speed Brake 30 
 Lift Dumper 50 
#4,5 Spoilers Roll 35 
 Speed Brake 30 
 Lift Dumper 50 
Aileron Droop 10 
Flaps 32 
Slats 1 21 
Slats 2 to 7 24 
Stabilizers +2/-14 
Elevator +15/-30 
Rudder +31.6/-31.6 
 
 
Certification Basis (A340-200 and A340-300) 
 
a. 14 CFR part 25 effective February 1, 1965, including the following: 
• Amendments 25-1 through 25-63 and Amendments 25-65, 25-66 and 25-77. 
• §25.791 at Amendment 25-72 
 
b. 14 CFR part 25 at Amendment 25-64 with the following exceptions: 
• Cockpit seats will not meet § 25.562 Amendment 25-64 but will meet § 25.561 
• Compliance with § 25.785(a), at Amendment 25-64 for front row seats directly behind a bulkhead will be based on ensuring 
a 35 inch free head strike envelope. 
 
c. 14 CFR part 34, effective September 10, 1990. 
 
d. 14 CFR part 36 of the as amended by Amendments 36-1 through 36-20. 
 
e. Special conditions in accordance with 14 CFR part 21.16: 
 
1. FAA Special conditions issued for the A340 in accordance with 14 CFR part 21.16 and published in the Federal Register 
April 15, 1993, (Docket No. NM-75, Special Conditions No. 25-ANM-69), as follows: 
(1) Electronic Flight Control System (EFCS) failures and 
Mode Annunciation 
(8) Tail plane Tank Emergency Landing Loads 
(2) Command Signal Integrity (9) Limit Engine Torque 
(3) Protection From Lightning and Unwanted Effects of 
High Intensity Radiated Fields (HIRF) 
(10) Ground Load Conditions for Center Landing Gear 
(4) Interaction of Systems and Structures (11) Flight Characteristics 
(5) Design Dive Speed (12) Flight Envelope Protection 
(6) Design Maneuver Requirements (13) Side Stick Controllers 
(7) Limit Pilot Forces (14) Computerized Airplane Flight Manual (AFM) 
Performance Information 
2. Special Conditions 25-281-SC published in the Federal Register January 6, 2005 (Docket No. NM287: 
Lower Deck Mobile Crew Rest (LD–MCR) Compartment 
3.  Special Conditions 25-396-SC published in the Federal Register November 03, 2009 (Docket No. NM-419): 
Seats With Inflatable Lap Belts.

A43NM Page 8 of 22  
4. Special Conditions 25-399-SC published in the Federal Register January 4, 2010 (Docket No. NM-423): 
Seats with Non-Traditional, Large, Non-Metallic Panels. 
5.  Special Conditions 25-759-SC published in the Federal Register October 31, 2019 (Docket No. FAA-2019-0814: 
 Seats With Inertia Locking Devices 
 
f. For precision approach and landing, the applicable technical requirements are complemented by AC 120-29 and AC 120-28C. 
 
g. For the automatic flight control system, the applicable technical requirements are complemented by  AC 20-57A for automatic 
landing and by AC 25.1329-1A for cruise. 
 
h. Equivalent safety findings have been made in accordance with § 21.21(b)(1) for the following paragraphs of the 14 CFR part 25: 
(1) § 25.335(d) for design airspeeds (7)    §§ 25.101(I); 25.105(c)(1); 25.109(a)(b)(c)(d)(e)(f); 25.113(a)(b)(c); 
25.115(a); 25.735(f)(g)(h)(b) for rejected takeoff and landing 
performance 
(2) § 25.345 for high lift devices (8) § 25.856(b), Improved Flammability standards for Thermal/acoustic 
insulation materials (documented in ELOS Memo TD0609IB-T-CI-5; 
Memo TD0609IB-T-CI-6 and Memo TD0609IB-T-CI-7). 
(3) § 25.349 for control surface loads (9) §§ 26.33, 26.35 Fuel Center Tank Flammability Red uction System 
(documented in ELOS Memo TD0547IB-T-P-1 
(4) § 25.351(b) for unsymmetrical loads (10) § 25.981(a)(3) Amendment. 25 -102  Fuel tank igniti on prevention 
(documented in ELOS Memo TD0764IB-T-P-1) 
(5) § 25.371 for gyroscopic loads (11) § 25.1443(c) Minimum mass flow of supplemental oxygen on model 
A330 and A340 airplanes (documented in ELOS Memo AT10356IB -
T-S-1) 
(6)    § 25.373 for speed control devices (12) § 25.1441(c) Crew determination of quantity of oxygen in passenger 
oxygen system on model A330 and A340 airplanes (documented in 
ELOS Memo AT10356IB-T-S-2) 
 (13) § 25.811(e)(4) Emergency Exit Marking on Airbus Model A330 and 
A340 airplanes (documented in ELOS Memo AT10899IB-T-CS-1) 
 
i.  Optional requirements elected: 
• § 25.801 at Amendment 25-72 for ditching. 
• § 25.1419 at Amendment 25-72 for icing. 
 
 
j. Exemptions: 
Exemptions from the applicable regulations has been processed in accordance with the provisions of 14 CFR 11.25. 
 
- Exemption18136, dated February 28, 2019, granted to Airbus for 14 CFR 25.813(e), amendment 25 -116, and 14 CFR 
121.310(f)(5) and (6) to the extent necessary to allow the installation of doors on mini-suites. 
 
The Direction Générale de l'Aviation Civile (DGAC) of France originally type certificated the Airbus Model A340 -200 and A340-300 
series airplanes under its type certificate number DGAC-F  TC 183. The FAA validated this product under U.S. Type Certificate Number 
A43NM. Effective September 28, 2003, the European Union Aviation Safety Agency (EASA) began oversight of this product on behalf 
of DGAC. 
 
Part 26 – Continued Airworthiness and Safety Improvements for Transport Category Airplanes: 
Based on § 21.29(a) for new import TCs, or § 21.101(g) for changes to TCs, applicable provisions of part 26 are included in t he 
certification basis.  For any future part 26 amendments, the holder of this TC must demonstrate compliance with the applicable sections. 
 
 
Production Basis 
 
From July 21, 2008, A340 aircraft, all series and models, are produced in France under production approval reference EASA.21G .0001 
issued by EASA, prior that date all A340 aircraft, all series and models, are produced in France under production approval FR.21G.0035 
(formerly FG 035) issued by the DGAC (on behalf of EASA) to Airbus.

A43NM Page 9 of 22  
 
Equipment 
 
• The basic required equipment as prescribed in the applicable airworthiness regulations (see Certification Basis) must be installed in the 
aircraft for certification. 
 
• Equipment approved for installation is listed in the Type Certification Standard Equipment Lists;  
- A340-211 and A340-311: 00F000A0101/C0S, 
- A340-212 and A340-312: 00F000A0102/C0S, 
- A340-213 and A340-313: 00F000A0103/C0S. 
 
• Cabin furnishings, equipment and arrangement shall conform to the following specification: 
- 00F252K0010/C01for cabin seats. 
- 00F252K0006/C01for galley. 
- 00F252K0020/C01for cabin attendant seats 
 
Hydraulic Fluids 
 
Fluid specifications: TYPE IV and TYPE V (NSA 307110) 
 
Auxiliary Power Unit (APU) 
 
Garrett Airesearch 
(Company name changed to Honywell International Inc. in 1999) 
GTCP 331-350C (Specification 31-7677A) 
Maximum Allowable Speed (107%) 41,730 RPM 
Maximum Gas Temperature: 
     Turbine Outlet Temperature 
     Starting 
 
650 C 
1250 C 
 
 
Approved oils: See Garrett report GT-7800 or Garrett Maintenance Manual. 
 
Tires 
 
Refer to Airbus Service Bulletin (SB) A340-32-4007. 
 
Environmental requirements for noise 
 
14 CFR part 36, effective December 1, 1969, including Amendments 36-1 through 36-21. Recertified to 14 CFR part 36 Stage 4, effective 
December 1, 1969, as amended by Amendments 36-1 through 36-28. 
A340-213 fitted with CFM56-5C4 engines are compliant with Stage 5 noise requirements of 14 CFR part 36 as amended by Amendments 
36-1 through 36-31. 
A340 -313 fitted with CFM56-5C4, or CFM56-5C4/P, or CFM56-5C4/1P engines are compliant with Stage 5 noise requirements of 14 
CFR part 36 as amended by Amendments 36-1 through 36-31.

A43NM Page 10 of 22  
 
IV. Type A340-600 Series Transport Category Airplanes 
 
Airbus Model A340-642 - approved July 22, 2002 
 
The A340-600 series differs from the A340 -300 series aircraft by the addition of 20 fuselage frames with corresponding increases in 
weight, thrust, horizontal stabilizer area and wing area. Full electrical control of the rudder replaces the previous mechan ical linkage 
between computer and actuators for both primary and backup systems 
 
Model: Definition of Reference Airplane by Airbus Documents: 
A340-642 FAA A340-642 Type Design, ref. EAL 415.0363/02 Issue 02, dated July 19, 2002, for type definition. 
 
 
Engines 
 
Airplane Model Engine Model: Engine Type Certificate: 
A340-642 Four Rolls-Royce– Trent 556-61 turbojet engines  FAA-Type Certificate E00066NE  
 
 
Maximum Weight 
 
Model A340-600 Airplane A340-642 
Weight Variant 
000 
(Basic) 
kg / lb 
001 
(Mod 50312) 
kg / lb 
Maximum Taxi Weight 366,200 / 807,332 369,200 / 813,946 
Maximum Take-off Weight, MTOW 365,000 / 804,687 368,000 / 811,301 
Maximum Landing Weight, MLW 256,000 / 564,383 259,000 / 570,997 
Maximum Zero Fuel Weight, MZFW 242,000 / 533,518 245,000 / 540,132 
 
Model A340-600 Airplane A340-642 
Weight Variant 
101 
(MOD 53043) 
kg / lb 
102 
(Mod 54805) 
kg / lb 
Maximum Taxi Weight 381,200 / 840,401 369,200 / 813,946 
Maximum Take-off Weight, MTOW 380,000 / 837,756 368,000 / 811,301 
Maximum Landing Weight, MLW 265,000 / 584,224 259,000 / 570,997 
Maximum Zero Fuel Weight, MZFW 251,000 / 553,360 245,000 / 540,132 
 
 
Number of Seats 
 
The maximum number of passengers approved for emergency evacuation is 440 passengers with a 4 pair of Type A and 1 pair of oversize 
Type III exits configuration. 
 
 
Maximum Baggage 
 
Cargo Compartment Maximum Load 
(kg / lb) 
Forward 30,482 / 67,201 
Aft 22,861 / 50,399 
Rear   3,468 /   7,645 
 
For the positions and the loading conditions authorized in each position (references of containers, pallets and associated we ight) see 
weight and Balance Manual: 
- A340-642 Airbus Document ref. 00F080A0601/C6S

A43NM Page 11 of 22  
Fuel Capacity 
 
   Tank Capacity  
  Usable Fuel Unusable Fuel 
Tank Liters 
(kg) 
gallons 
(lb) 
Liters 
(kg) 
gallons 
(lb) 
Wing 
Tank 1 / 4  49,002 
(39,202) 
12,945 
(86,426) 
68 
(54) 
18 
(120) 
Tank 2 / 3 69,514 
(55,611) 
18,364 
(122,601) 
230 
(184) 
61 
(406) 
Outer 12,290 
(9,832) 
3,247 
(21,676) 
34 
(27) 
9 
(60) 
Total 130,806 
(104,645) 
34,556 
(230,703) 
332 
(266) 
88 
(586) 
Center 54,969 
(43,975) 
14,521 
(96,842) 
404 
(323) 
107 
(713) 
Trim Tank 8,361 
(6,689) 
2,209 
(14,747) 
25 
(20) 
7 
(44) 
Total 194,136  
(155,309) 
51,286 
(342,386) 
761 
(609) 
201 
(1,343) 
 
 
Airplane Flight Manual 
 
Airplane operation must be in accordance with the EASA -Approved Airplane Flight Manual (AFM), US version, listed below, or later 
EASA approved revision applicable to the specific airplane model, modification status and serial number. 
 
Model A340-600 Airbus Document Refr. Revision No. Date 
A340-642 STL 34000 1 July 22, 2002 
 
 
Data Pertinent to All Model 
 
See Section VI, Data Pertinent to All Model A340-500 and A340-600 Series Airplanes. 
for information on Fuel, Engine Limits, Airspeed Limits, Center of Gravity Limits, Datum, Leveling Means, Minimum Crew, Maximum 
Operating Altitude, Control Surface Movements, Certification Basis, Production Basis, Equipment, Hydraulic Fluids, Auxiliary Power 
Unit (APU), Tires and Environmental requirements for noise. 
 
See section VII, Data Pertinent to All Model A340-200, A340-300, A340-500 and A340-600 Series Airplanes. 
for information on Import Requirements, Service Information and General Notes.

A43NM Page 12 of 22  
V. Type A340-500 Series Transport Category Airplanes 
 
Airbus A340-541 - approved January 27, 2003 
 
The A340-500 series is shorter than the A340-600 by 14 frames.  It is intended for long range operations having additional fuel capacity 
over that of the A340-600 with the installation of a rear center tank (RCT). 
 
Model: Definition of Reference Airplane by Airbus Documents: 
A340-541 FAA A340-541 Type Design, ref. EAL 415.1445/02 Issue 01, dated November 28, 2002, for type definition. 
 
The following table provides a list of required design improvement modifications for the 5-frame RCT (defined by Airbus modification 
no. 47020) on Model A340-500 series aircraft. The modifications extend the Kevlar liner in the RCT and improve the RCT fuel jettison 
rate. Airbus modifications 51344 and 51452 are required as a condition for type certification and must be installed prior to issuance of a 
standard U.S airworthiness certificate. 
 
Airbus Modification  No. Airbus Modification Title 
51344 Install Liners between RCT Forward and Rear Pressure Bulkheads (5 inter-frames)  
51452 Relocate RCT Transfer/Refuel Restrictors to increase Jettison rate  
 
Engines 
 
Airplane Model Engine Model: Engine Type Certificate: 
A340-541 Four Rolls-Royce– Trent 553-61 turbojet engines  FAA-Type Certificate E00066NE  
 
Maximum Weight 
 
Model A340-500 Airplane A340-541 
Weight Variant 
000 
(Mod 51000) 
kg / lb 
001 
(Mod 51080) 
kg / lb 
002 
(Mod 50791) 
kg / lb 
003 
(Mod 54237) 
kg / lb 
Maximum Taxi Weight 369,200 / 813,946 373,200 / 822,765 373,200 / 822,765 375,200 / 827,174 
Maximum Take-off Weight, MTOW 368,000 / 811,301 372,000 / 820,119 372,000 / 820,119 374,000 / 824,528 
Maximum Landing Weight, MLW 240,000 / 529,109 243,000 / 535,723 243,000 / 535,723 231,000 / 509,267 
Maximum Zero Fuel Weight, MZFW 225,000 / 496,040 230,000 / 507,063 229,000 / 504,858 218,000 / 480,607 
 
Model A340-500 Airplane A340-541 
Weight Variant 
101 
(MOD 53039) 
kg / lb 
102 
(Mod 54806) 
kg / lb 
Maximum Taxi Weight 381,200 / 840,401 373,200 / 822,746 
Maximum Take-off Weight, MTOW 380,000 / 837,756 372,000 / 820,119 
Maximum Landing Weight, MLW 246,000 / 542,337 243,000 / 535,723 
Maximum Zero Fuel Weight, MZFW 232,000 / 511,472 230,000 / 507,063 
 
Number of Seats 
 
The maximum number of passengers approved for emergency evacuation is 375 passengers with a 3 pair of Type A and 1 pair of Type I 
exits configuration. 
 
Maximum Baggage 
 
Cargo Compartment Maximum Load 
(kg / lb) 
Forward 24,494 / 54,000 
Aft 16,330 / 36,001 
Rear   3,458 /   7,623 
For the positions and the loading conditions authorized in each position (references of containers, pallets and associated we ight) see 
weight and Balance Manual: 
 
-  A340-541  Airbus Document 00F080A0501/C5S

A43NM Page 13 of 22  
 
Fuel Capacity 
 
   Tank Capacity  
  Usable Fuel Unusable Fuel 
Tank Liters 
(kg) 
gallons 
(lb) 
Liters 
(kg) 
gallons 
(lb) 
Wing 
Tank 1 / 4  49,002 
(39,202) 
12,945 
(86,421) 
68 
(54) 
18 
(120) 
Tank 2 / 3 69,514 
(55,611) 
18,364 
(122,598) 
230 
(184) 
61 
(406) 
Outer 12,290 
(9,832) 
3,247 
(21,677) 
34 
(27) 
9 
(60) 
Total 130,806 
(104,645) 
34,556 
(230,696) 
332 
(265) 
88 
(586) 
Center 
(with jet pumps : modification 
50812) 
55,133 
(44,106) 
14,566 
(97,254) 
240 
(192) 
63 
(423) 
Rear Center 5 frame 
(with liner: modification 51344) 
19,741 
(15,793) 
5,216 
(34,824) 
100 
(80) 
26 
(176) 
Trim Tank 7,886 
(6,309) 
2,083 
(13,911) 
25 
(20) 
7 
(44) 
Total 213,566 
(170,853) 
56,421 
(376,685) 
697 
(557) 
184 
(1,229) 
 
 
Airplane Flight Manual 
 
Airplane operation must be in accordance with the EASA-Approved Airplane Flight Manual (AFM), US version, listed below, or later 
EASA approved revision applicable to the specific airplane model, modification status and serial number. 
 
Model A340-500 Airbus Document Refr. Revision No. Date 
A340-541 STL 34000 1 January 16, 2003 
 
 
Data Pertinent to All Model 
 
See Section VI, Data Pertinent to All Model A340-500 and A340-600 Series Airplanes. 
for information on Fuel, Engine Limits, Airspeed Limits, Center of Gravity Limits, Datum, Leveling Means, Minimum Crew, Maximum 
Operating Altitude, Control Surface Movements, Certification Basis, Production Basis, Equipment, Hydraulic Fluids, Auxiliary Power 
Unit (APU), Tires and Environmental requirements for noise. 
 
See section VII, Data Pertinent to All Model A340-200, A340-300, A340-500 and A340-600 Series Airplanes. 
for information on Import Requirements, Service Information and General Notes.

A43NM Page 14 of 22  
VI. Data Pertinent to All Model A340-500 and A340-600 Series Airplanes: 
 
Fuel 
 
  Specification  
Nomenclature United Sates France United Kingdom 
Kerosene ASTM D 1655 
(JET A) (JET A1) 
AIR 3405C DERD 
2494/2453 
Wide Cut ASTM D 1655 
(JET B) 
91056 
(72845) 
DERD 
2454/2486 
 MIL-T-5624 (JP 4) 
MIL-T-83133 (JP 8) 
AIR 3407B DERD 
2454/2486 
Additives: According to RR "Specific Operating Instructions", OI-Trent-A340. The above-mentioned fuels are also suitable for the 
APU. 
Engine Limits 
 
Engine Limitations 
Rolls-Royce 
RB 211 Trent 556-61 
Rolls-Royce 
RB 211 Trent 553-61 
See FAA Data Sheet E00066NE See FAA Data Sheet E00066NE 
Static Thrust at Sea Level 
• Take-off (5 mn)1 (flat rated 30º C) 
• maximum continuous 
(flat rated 25º C) 
 
 
58,462 lbs (26,004 daN) 
 
44,359 lbs (19,731 daN) 
 
 
55,780 lbs (24,811 daN) 
 
44,359 lbs (19,731 daN) 
Maximum Engine Speed 
• N1 rpm (%) 
• N2 rpm (%) 
 
3,900 (100%) 
9,100 (100%) 
 
3,900 (100%) 
9,100 (100%) 
Maximum Gas Temperature 
• Take-off (10mn)
1
 
• Maximum Continuous 
• Starting 
- Ground 
- Inflight 
 
900º C 
850º C 
 
700º C 
850° C 
 
900º C 
850º C 
 
700º C 
850° C 
Maximum Oil Temperature 
(Combined scavenge temperature) 
ºC 
 
Minimum Pressure 
 
196º C 
 
 
25 psi (172 kPa) 
 
196° C 
 
 
25 psi (172 kPa) 
Approved oils Refer to the Engine Operating 
Instructions for A330/A340 for 
information on approved oil 
specifications for Trent 500 
Refer to the Engine Operating Instructions for 
A330/A340 for information on approved oil 
specifications for Trent 500 
Table references: 
(1) 10 minutes at take-off thrust allowed only in case of engine failure (at take-off or during go-around). 
 
Airspeed Limits (Indicated Airspeed, IAS, unless otherwise stated) 
 
• Maximum Operating Limit Speed/Mach, VMO/MMO 330 KIAS / .86 M 
• Design Diving Speed, VD 365 KIAS / .93 M 
• Design Maneuvering Speed, VA Refer to AFM performance Section 
• Maximum Flaps/Slats Extended Speed or Operating Speed, VFE  
Configuration Slats/Flaps º VFE (kt)  
1 20/0 
20/17 
280 
233 
Intermediate Approach 
Take-off 
2 23/22 216 Take-off and Approach 
3 23/29 206 Take-off and Approach 
FULL 23/34 200 Landing

A43NM Page 15 of 22  
 
• Minimum Control Speed, VMC  Refer to AFM performance Section 
 (Performance Engineering Program/OCTOPUS) 
Landing Gear Speeds: 
• Maximum Speed with Landing Gear Operating (Extension and Retraction), VL0 250 KIAS / .55 M 
• Maximum Speed with Landing Gear Locked Down, VLE 250 KIAS / .55 M 
• Tire Limit Speed (Ground Speed) 204 KIAS 
 
Center of Gravity Limits 
 
Refer to EASA-Approved AFM, US Version, Limitations Section for center of gravity envelope. 
Note: For A340-600, the 0% MAC is located 1,617 inch (41.034 m) from the datum line. 
 For A340-500, the 0% MAC is located 1,408 inch (35.734 m) from the datum line. 
 
Datum 
 
The aircraft reference zero datum point is located 251.37 inch (6.38 m) forward of the fuselage nose, 275.8 inch (7 m) under the fuselage 
centerline (datum line). 
 
Leveling Means 
 
Inclinometer on cabin seat track rails (refer to AMM chapter 08.20.00). 
 
Minimum Crew 
 
2 – Pilot and copilot 
 
Maximum Operating Altitude 
 
• Basic: 41,100 feet (12,527m) slats and flaps retracted (clean) 
• Option: 41,450 feet (12,634m) slats and flaps retracted (clean) with modification 52536 
• 20,000 feet (6,096 m) slats or slats/flaps extended 
 
 
Control Surface Movements  (Total one-way travel in each direction of each movable control surface on the aircraft.) 
 
Control Surface Maximum Travel 
Inner Aileron +20/-30 
Outer Aileron +25/-25 
Ailerons Maneuver Load Alleviation 11° 
#1 Spoiler Speed Brake 25 
 Lift Dumper 35 
#2,3 Spoilers Roll 35 
 Speed Brake 35 
 Lift Dumper 50 
#4,5,6 Spoilers Roll 40 
 Speed Brake 40 
 Lift Dumper 50 
 Maneuver Load Alleviation 9° 
Aileron Droop 10 
Flaps 33.7 
Slats 1 21 
Slats 2 to 7 24 
Stabilizers +2/-14 
Elevator +17/-30 
Rudder +35/-35

A43NM Page 16 of 22  
Certification Basis (A340-600 and A340-500) 
 
The reference date for the determination of the certification basis was December 31, 1997. 
 
a. 14 CFR part 25, dated February 1, 1965, including the following: 
• Amendments 25-1 through Amendment 25-95 inclusive plus Amendments 25-97, 25-98 and 25-104  
• §25.791 at Amendment 25-72 
 
with the following exceptions:  
 
Excepted 14 CFR part 25 Allowed Amendment Level Comments 
§ 25.562(b)(2) Pre-amendment 25-64 Allowance for compliance to pre-amdt 
25-64 only applies to crew seat floor 
warpage test requirements 
§ 25.365(g) Amendment 25-54 Allowance for compliance to amdt 25-
54 applies only to design of the cockpit 
wall 
§§ 25.831(g), 25.831(a), 25.841(a)  
 
§§ 25.831(g) and 25.831(a) at 
Amendment 25-41 
§ 25.841(a) at Amendment 25-38. 
 
 
b. 14 CFR part 36, effective December 1, 1969, as amended by Amendments 36-1 through 36-23. 
 
c. 14 CFR part 34, effective September 10, 1990, including all Amendments effective on the TC date. 
 
d. Special conditions in accordance with 14 CFR 21.16. 
 
(i) Basic A340 Special Conditions also applicable to the A340-500 and A340-600: 
Note 1: Refer to TCDS section III certification basis for the A340-200 and A340-300  
Note 2: Special conditions issued for the A340 in accordance with 14 CFR part 21.16 and published in the Federal Register 
Special Vol. 58, No. 71, dated April 15, 1993 
(1) Electronic Flight Control System (EFCS) failures and Mode Annunciation 
(2) Command Signal Integrity 
(3)(a) Protection From Lightning and Unwanted Effects of High Intensity Radiated Fields (HIRF) 
(5) Design Dive Speed 
(6) Design Maneuver Requirements 
(7) Limit Pilot Forces 
(11)(a) Flight Characteristics Characteristic - Compliance Determination By handling Qualities rating System for EFCS 
Failure Cases 
(11)(c) Flight Characteristic – Lateral Directional Stability 
(12)(a) Flight Envelope Protection – General Limiting Requirements 
(12)(c) Flight Envelope Protection – Normal Load Factor g Limiting 
(12)(d) Flight Envelope Protection – High Speed Limiting 
(12)(e) Pitch and Roll Limiting 
(13) Side Stick Controllers 
 
(ii) Special Conditions applicable to the A340-500 and A340-600: 
Docket No. NM211; Special Conditions No. 25-200-SC 
 “Airbus, Model A340-500 and A340-600 Airplanes; Ground Loads and Conditions for Center Landing Gear with four 
Wheels and Braking Capability,” Federal Register Vol. 67 No. 98, May 21, 2002.  
Docket No. NM213; Special Conditions No. 25-201-SC 
“Airbus, Model A340-500 and A340-600 Airplanes; Interaction of Systems and Structure…”, Federal Register Vol. 67 
No. 126, July 1, 2002.

A43NM Page 17 of 22  
Docket No. NM213; Special Conditions No. 25-201-SC 
“Airbus, Model A340-500 and A340-600 Airplanes; “…Electronic Flight Control System: Longitudinal Stability and 
Low Energy Awareness…” Federal Register Vol. 67 No. 126, July 1, 2002. 
Docket No. NM213; Special Conditions No. 25-201-SC,  
“Airbus, Model A340-500 and A340-600 Airplanes; “…Use of High Incidence Protection and Alpha Floor Systems”, 
Federal Register Vol. 67 No. 126, July 1, 2002. 
Docket No. NM212; Special Conditions No. 25-02-04-SC 
“Airbus, Model A340-500 and A340-600 Airplanes; Sudden Engine Stoppage,” Federal Register Vol. 67 No. 81, April 
26, 2002. 
Docket No. NM-419, Special Conditions No. 25-396-SC 
“Airbus Model A340 Series Airplanes; Seats With Inflatable Lap Belts”, Federal Register Vol. 74 No. 211, November 
03, 2009. 
Docket No. NM-423, Special Conditions No. 25-399-SC 
“Airbus Model A340 Series Airplanes; Seats with Non-Traditional, Large, Non-Metallic Panels”, Federal Register Vol. 
75 No. 1, January 04, 2010 
 
Docket No. FAA-2019-0814, Special Conditions No. 25-759-SC 
Airbus Model A340 Series Airplanes; Seats With Inertia Locking Devices 
 
e. Equivalent safety findings have been made in accordance with 14 CFR part 21.21(b)(1) for the following 14 CFR part 25 
paragraphs: 
§ 25.621(c) Casting factors. The ESF is only applicable to the Inner Flap – Flap Rib Fitting of the A340-500 and –600. For all 
other castings on the aircraft, as defined by the certification basis, the requirements of § 25.621(c) Amendment 25-0 apply 
§§ 25.473, 25.723: Landing Gear Drop Tests  
§§ 25.341(a)(5),(b),(c), 25.345(c)(2), 25.371, 25.373(a), 25.1517: Continuous Turbulence Loads 
§ 25.331(c)(2): Checked Maneuver Loads 
§ 25.107(e)(1)(iv): Reduced Margins between VMU and VLOF for Geometry Limited Airplanes 
§§ 25 (All 14 CFR part 25 sections, except structural, dealing with stall speeds and related factors): Use of 1-g Stall Speeds 
Instead of Minimum Speed in the Stall as a Basis for Determining Compliance 
§ 25.831(a): Airplane Operation with Air Conditioning Packs Off During Takeoff 
§§ 25.933(a)(1), 25.1585(a)(9): Flight Critical Thrust Reverser (documented in ELOS Memo CP50-T-P-609) 
§ 25.963(d) first sentence: Fuel Tank Loads. The ESF is to the first sentence of § 25.963(d); “Fuel tanks within the fuselage 
contour must be able to resist rupture and to retain fuel, under the inertia forces prescribed for emergency landing conditions 
in § 25.561.” 
§ 25.1203(d): Rolls-Royce Trent 500 Turbine Overheat Detection (documented in ELOS Memo CP50-T-P-611) 
§§ 25.1305, 251501(b): Auxiliary Power Unit (APU) Instrumentation and Monitoring Requirements (documented in ELOS 
Memo CP50-T-P-612) 
§ 25.1305(c)(6), Warning Means for Engine Fuel Filter Contamination  (documented in ELOS Memo CP50-T-P-615) 
§ 25.856(b), Improved Flammability standards for Thermal/acoustic insulation materials (documented in ELOS Memo 
TD0609IB-T-CI-5; Memo TD0609IB-T-CI-6 and Memo TD0609IB-T-CI-7). 
§ 25.981(a)(3) Amendment. 25-102  Fuel tank ignition prevention (documented in ELOS Memo TD0764IB-T-P-1) 
§ 25.1443(c) Minimum mass flow of supplemental oxygen on model A330 and A340 airplanes (documented in ELOS Memo 
AT10356IB-T-S-1) 
§ 25.1441(c) Crew determination of quantity of oxygen in passenger oxygen system on model A330 and A340 airplanes 
(documented in ELOS Memo AT10356IB-T-S-2) 
§ 25. 811(e)(4) Emergency Exit Marking on A330 and A340 airplanes (documented in ELOS Memo AT10899IB-T-CS-1) 
 
f. Optional Design Regulations  
• §25.801 at Amendment 25-72 Ditching Provisions 
• §25.1411(d)(e)(f)(g) at Amendment 25-70 General Safety Equipment

A43NM Page 18 of 22  
• §25.1415 at Amendment 25-72 Ditching Equipment 
• §25.1419 at Amendment 25-72 Ice Protection 
 
g. Exemptions: 
Exemptions from the applicable regulations has been processed in accordance with the provisions of 14 CFR 11.25. 
 
- Airbus petitioned for an exemption to §25.807(f)(4) with letter dated May 9, 2000 (the “60 foot rule” was relocated to this 
section as of amdt 25-94).  In reply issued on December 11, 2000, the FAA denied the petition for exemption (ref. Exemption 
No. 7404). 
- Exemption 7840, dated July 19, 2002, was issued to Airbus for non -compliance to §25.901(c) as it relates to uncontrollable 
high thrust failure conditions. 
- Exemption18136, dated February 28, 2019, granted to Airbus for 14 CFR 25.813(e), amendment 25 -116, and 14 CFR 
121.310(f)(5) and (6) to the extent necessary to allow the installation of doors on mini-suites. 
 
The Direction Generale de 'Aviation Civile  (DGAC) of France originally type certificated the Airbus Model A340 -500 and A340-600 
series airplanes under its type certificate number DGAC-F  TC 183. The FAA validated this product under U.S. Type Certificate Number 
A43NM. Effective September 28, 2003, the European Union Aviation Safety Agency (EASA) began oversight of this product on behalf 
of DGAC. 
 
Part 26 – Continued Airworthiness and Safety Improvements for Transport Category Airplanes: 
 
Based on § 21.29(a) for new import TCs, or § 21.101(g) for changes to TCs, applicable provisions of part 26 are included in the 
certification basis.  For any future part 26 amendments, the holder of this TC must demonstrate compliance with the applicable sections. 
 
Production Basis 
 
From July 21, 2008, A340 aircraft, all series and models, are produced in France under production approval reference EASA.21G .0001 
issued by EASA, prior that date all A340 aircraft, all series and models, are produced in France under production approval FR.21G.0035 
(formerly FG 035) issued by the DGAC (on behalf of EASA) to Airbus.  
 
Equipment 
 
• The basic required equipment as prescribed in the applicable airworthiness regulations (see Certification Basis) must be installed in the 
aircraft for certification.   
 
• Cabin furnishings, equipment and arrangement shall conform to the following specification: 
- 00F252K0010/C01for cabin seats. 
- 00F252K0006/C01for galley. 
- 00F252K0020/C01for cabin attendant seats 
 
 
Hydraulic Fluids 
 
Fluid specifications: TYPE IV and TYPE V (NSA 307110) 
 
 
Auxiliary Power Unit (APU) 
 
Honeywell E. & S. 331-600[A] (Model Specification 31-15857-01A) 
Maximum Allowable Speed (100%) 39,044 rpm 
Maximum Gas Temperature: 
     Turbine Outlet Temperature 
     Starting 
 
650 C 
1250 C 
 
 
Approved oils: See also Model Specification 31-15857-01A for approved oils. 
 
 
Tires 
 
Refer to Airbus Service Bulletin A340-35-5023

A43NM Page 19 of 22  
 
Environmental requirements for noise 
 
14 CFR Part 36, effective December 1, 1969, as amended by amendments 36-1 through 36-23.  
Recertified to 14 CFR part 36 Stage 4, effective December 1, 1969, as amended by Amendments 36-1 through 36-28. 
Recertified to 14 CFR part 36 Stage 4, effective December 1, 1969, as amended by Amendments 36-1 through 36-31: 
• A340-541 fitted with Rolls-Royce– Trent 553-61 engines are compliant with Stage 5 noise requirements of 14 CFR part 36 
as amended by Amendments 36-1 through 36-31. 
 
• A340-642 fitted with Rolls-Royce– Trent 556-61 engines are compliant with Stage 5 noise requirements of 14 CFR part 36 
as amended by Amendments 36-1 through 36-31.

A43NM Page 20 of 22  
VII. Data Pertinent to All Model A340-200, A340-300, A340-500 and A340-600 Series Airplanes 
 
Import Requirements 
 
 
Refer to the applicable bilateral agreement to verify eligibility for import based on the scope of the agreement, to identify any required 
statements on the export certificate of airworthiness (or equivalent document), and for procedures for coordinating exception s to 
conformity statements on these documents. Refer to FAA Order 8130.2, Airworthiness Certifi cation of Aircraft, provisions for Import 
Aircraft, for requirements for issuance of an airworthiness certificate. 
 
The U.S. airworthiness certification basis for aircraft type certificated under 14 CFR 21.29 and exported by the country of m anufacture 
is 14 CFR 21.183(c) or 21.185(c).  The U.S. airworthiness certification basis for aircraft type certificated under 14 CF R 21.29 exported 
from countries other than the country manufacture (e.g., third party country) is 14 CFR 21.183(d) or 21.183(b). 
 
FAA Required Airworthiness Action List for Airbus Model A340 Aircraft 
 
In order for the FAA to determine that an A340 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, Large Aircraft Se ction, International Validation  
Branch, Compliance & Airworthiness Division, Aircraft Certification Service, 2200 South 216th Street Des Moines, Washington  98198, 
telephone (206)-231-3219, prior to issuance of the U.S. airworthiness certificate to obtain the FAA Required Airw orthiness Action List 
(RAAL) for the A340.  
Based on the FAA’s policy regarding foreign mandatory continuing airworthiness information (MCAI), when no aircraft of the affected 
design is currently registered in the U.S. (ref. Fed eral Register Volume 63, No. 84, May 1, 1998, docket 98 -11648) the A340 Required 
Modification List (RML) is removed from the A340 TCDS at revision 10. Modifications defined in the A340 RML are transferred into 
A340 Required Airworthiness Action List (RAAL).  The RAAL is maintained by the Large Aircraft Se ction, International Validation  
Branch, Compliance & Airworthiness Division, Aircraft Certification Service, 2200 South 216th Street Des Moines, Washington  98198, 
telephone (206)-231-3219. 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 Union Aviation Safety 
Agency (EASA), which is the state of design authority for the A340, to be required to correct unsafe conditions discovered on the original 
type design of the A340. EASA has issued Airworthiness Directives – MCAI - that require the accomplishment of these modifications 
and inspections to correct the identified unsafe conditions, and has advised the FAA of this MCAI. Based on t his MCAI the FAA has 
determined that the airworthiness actions identified in the EASA MCAI listed in A340 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 A340 model aircraft, all airworthiness actions listed in the A340 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 s urpassed 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, Large Aircraft Se ction, 
International Validation Branch, Compliance & Airworthiness Division, Aircraft Certification Service , 2200 South 216th Street Des 
Moines, Washington  98198, telephone (206)-231-3219.  
 
Service Information 
 
Each of the documents listed below that contain a statement that it is approved by the European Union Aviation Safety Agency (EASA) 
- or for approvals made before September 28, 2003 - by the DGAC France, 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 - or for approvals 
made before September 28, 2003 - under the authority of by DGAC Design Organization Approval No. C01 or JAA Design Organization 
Approval No. F.JA.02 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 
• US version of Aircraft flight manuals, 
• Repair Instructions. 
 
Design changes that are contained in Airbus Service Bulletins and that are classified as Level 1 Major or Non Basic in accordance with 
the Technical implementation procedures for airworthiness and environmental certification between the FAA of the USA and the EASA 
of the European Union must be approved by the FAA. 
 
VIII. General Notes: (All Models of A340 Series Airplanes)

A43NM Page 21 of 22  
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. 
Refer to Airbus Documents: 
- 00F080A0002/C2S for A340-211 and -212; 
- 00F080A0001/C3S for A340-311 and -312; 
- 00F080A0004/C0S for A340-213 and -313; 
- 00F080A0601/C6S for A340-642; 
- 00G080A0006/C3S for A340-541. 
 
Note 2: 
All placards required by either the AFM, the applicable operating rules, or the certification basis must be installed in the airplane. 
 
Note 3: 
Instructions for Continued Airworthiness required under § 21.50: 
 
• Initial minimum maintenance requirements and their frequencies to be used in the development of an approved maintenance 
program for the aircraft: 
- A340 Maintenance Review Board Report (Certification Document 00F050A0002/C01) approved by FAA. 
 
• Instructions for Continued Airworthiness and airworthiness limitations: 
- Instructions and airworthiness limitations applicable to Safe Life Airworthiness Limitation Items (SL ALI) are provided in 
the Airbus A340 Airworthiness Limitations Section (ALS) Part 1: 
ALS Part 1: Safe Life Airworthiness Limitation Items (SL-ALI).  
- Instructions and airworthiness limitations applicable to Damage Tolerant Airworthiness Limitation Items (DT ALI) are 
provided in the Airbus A340 Airworthiness Limitations Section (ALS) Part 2: 
ALS Part 2: Damage Tolerant Airworthiness Limitation Items (DT - ALI). 
- Certification Maintenance Requirements (CMR’s) are provided in the A340 Airworthiness Limitations Section (ALS) Part 3 
ALS Part 3: Certification Maintenance Requirements (CMR).  
- Instructions and airworthiness limitations applicable to Aging Systems Maintenance (ASM) are provided in the Airbus A340 
Airworthiness Limitations Section (ALS) Part 4 
ALS Part 4: System Equipment Maintenance Requirements (SEMR). 
- Fuel Airworthiness Limitations (FAL) are provided in the A340 Airworthiness Limitations Section (ALS) Part 5 
ALS Part 5: Fuel Airworthiness Limitations (FAL). 
 
 
Note 4: 
Compliance with the FAA Required Modification List (RML) is necessary for an A340-200, A340-300, A340-500 or A340-600 aircraft 
to be found in a condition for safe operation.  (See Import Requirements in TCDS section VII  Data Pertinent to All Model A34 0-200, 
A340-300, A340-500 and A340-600 Series Airplanes). 
 
Note 5: 
For Airbus model A340 -541: Airbus modifications 51344 and 51452 that extend the Kevlar liner in the Rear Center Tank ( RCT) and 
improve the RCT fuel jettison rate are required as a condition for type certification and must be installed prior to issuance  of a standard 
U.S airworthiness certificate. 
 
Note 6: 
If modification FG-FRS 58723 Issue 2 “Install fuel tank flammability reduction system on A330/A340” is embodied on A340 -200 or 
A340-300 airplanes, the airplane is compliant with 14 CFR Part 25 appendix M & N at amendment 25 -125, and Section 26.33 at 
amendment 26-3, and design changes to the fuel system introduced with modification FG-FRS 58723 Issue 2 are in compliance with 14 
CFR Section 25.981(a) & (b) at amendment 25-102.

A43NM Page 22 of 22  
Note 7: 
If modification 58724 Issue 1 “Install fuel center tank flammability reduction system on A340 -500/600” is embodied on A340 -541 or 
A340-642 airplanes, the airplane is compliant with 14 CFR Part 25 appendix M & N at amendment 25 -125, and Section 26.33 at 
amendment 26-3, and design changes to the fuel system introduced with modification FG-FRS 58724 Issue 1 are in compliance with 14 
CFR Section 25.981(a) & (b) at amendment 25-102. 
 
Note 8: 
If modifications ## 52873 issue 1, 53321 issue 1, 53322 issue 1, 53323 issue 1, 53324 issue 2, 53325 issue 4, 53326 issue 1, 53541 issue 
1, 53815 issue 2, 54302 issue 1 and 54566 issue 1 are embodied on A340 -211/-212/-213, or A340 -311/-312/-313, or A340 -541/-642 
airplanes, the airplane is compliant with 14 CFR Section 25.856 (a) at Amendment 25 -111, Improved Flammability standards for 
Thermal/acoustic insulation materials. (FAA project AT10215IB-T) 
 
Note 9: 
If modification # 204093 Issue 1 is embodied, only one HF remains available on the aircraft instead of two as defined in the applicable 
Type design definition. 
 
- END -
```

## ADs (394, first 50, in force first)

- [AD 2026-21-03](https://openairdocs.org/ad/2026-21-03): Fuel · Airbus A330-243, A330-243F, A330-341 and 12 more. Effective Nov 23, 2026
- [AD 2026-10-05](https://openairdocs.org/ad/2026-10-05): Equipment/furnishings · Goodrich A340-641, A340-542, A330-743L and 27 more. Effective Jul 6, 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 2025-25-09](https://openairdocs.org/ad/2025-25-09): Doors · Airbus A330-201, A330-202, A330-203 and 23 more. Effective Feb 9, 2026
- [AD 2025-18-03](https://openairdocs.org/ad/2025-18-03): Oxygen · Airbus A318-111, A318-112, A318-121 and 70 more. Effective Oct 20, 2025
- [AD 2025-20-13](https://openairdocs.org/ad/2025-20-13): Landing Gear · Airbus A330-201, A330-202, A330-203 and 21 more. Effective Oct 17, 2025
- [AD 2024-26-05](https://openairdocs.org/ad/2024-26-05): Oxygen · Airbus A300 B4-601, A300 B4-603, A300 B4-620 and 87 more. Effective Mar 11, 2025
- [AD 2024-26-06](https://openairdocs.org/ad/2024-26-06): Flight Controls · Airbus A330-201, A330-202, A330-203 and 20 more. Effective Mar 11, 2025
- [AD 2025-03-08](https://openairdocs.org/ad/2025-03-08): Flight Controls · Airbus A318-111, A318-112, A318-121 and 70 more. Effective Feb 26, 2025
- [AD 2024-19-15](https://openairdocs.org/ad/2024-19-15): Oxygen · Safran Aerosystems Oxygen Cylinder, Valve Assembly, Oxygen Valve and 103 more. Effective Nov 26, 2024
- [AD 2024-16-15](https://openairdocs.org/ad/2024-16-15): Landing Gear · Airbus A330-201, A330-202, A330-203 and 14 more. Effective Oct 30, 2024
- [AD 2024-17-05](https://openairdocs.org/ad/2024-17-05): Stabilizers · Airbus A330-201, A330-202, A330-203 and 21 more. Effective Sep 20, 2024
- [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 2024-01-10](https://openairdocs.org/ad/2024-01-10): Fuel · Airbus A330-201, A330-202, A330-203 and 17 more. Effective Feb 6, 2024
- [AD 2023-19-03](https://openairdocs.org/ad/2023-19-03): Airborne Auxiliary Power · Airbus A330-201, A330-202, A330-203 and 18 more. Effective Nov 6, 2023
- [AD 2023-19-01](https://openairdocs.org/ad/2023-19-01): Airborne auxiliary power · Airbus A330-201, A330-202, A330-203 and 21 more. Effective Oct 30, 2023
- [AD 2023-17-03](https://openairdocs.org/ad/2023-17-03): Pneumatic · Airbus A330-201, A330-223, A330-203 and 19 more. Effective Oct 19, 2023
- [AD 2023-12-19](https://openairdocs.org/ad/2023-12-19): Landing gear · Airbus A330-201, A330-202, A330-203 and 21 more. Effective Aug 23, 2023
- [AD 2023-13-04](https://openairdocs.org/ad/2023-13-04): Fuel · Airbus A330-223F, A330-243F, A330-201 and 23 more. Effective Aug 23, 2023
- [AD 2023-10-06](https://openairdocs.org/ad/2023-10-06): Wings · Airbus A330-223F, A330-243F, A330-201 and 21 more. Effective Jul 11, 2023
- [AD 2023-07-02](https://openairdocs.org/ad/2023-07-02): Equipment/furnishings · Airbus A330-201, A330-202, A330-203 and 15 more. Effective May 30, 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 2023-06-07](https://openairdocs.org/ad/2023-06-07): Airborne Auxiliary Power · Airbus A330-202, A330-203, A330-223 and 18 more. Effective May 18, 2023
- [AD 2023-05-10](https://openairdocs.org/ad/2023-05-10): Windows · Airbus A330-201, A330-202, A330-203 and 23 more. Effective May 12, 2023
- [AD 2023-01-03](https://openairdocs.org/ad/2023-01-03): Landing gear · Airbus A330-201, A330-202, A330-203 and 21 more. Effective Mar 9, 2023
- [AD 2022-15-08](https://openairdocs.org/ad/2022-15-08): Information systems · Airbus A318-111, A318-112, A319-111 and 49 more. Effective Aug 12, 2022
- [AD 2021-22-25](https://openairdocs.org/ad/2021-22-25): Navigation · Airbus A330-201, A330-202, A330-203 and 22 more. Effective Jan 5, 2022
- [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 2021-15-07](https://openairdocs.org/ad/2021-15-07): Flight controls · Airbus A330-201, A330-202, A330-203 and 21 more. Effective Sep 9, 2021
- [AD 2021-15-11](https://openairdocs.org/ad/2021-15-11): Oxygen · Airbus A330-201, A330-202, A330-203 and 21 more. Effective Sep 9, 2021
- [AD 2021-12-18](https://openairdocs.org/ad/2021-12-18): Fuel system · Airbus A330-201, A330-202, A330-203 and 19 more. Effective Aug 4, 2021
- [AD 2021-11-20](https://openairdocs.org/ad/2021-11-20): Equipment/furnishings · Airbus A330-201, A330-202, A330-203 and 19 more. Effective Jul 16, 2021
- [AD 2021-01-06](https://openairdocs.org/ad/2021-01-06): Hydraulic power · Airbus A330-201, A330-202, A330-203 and 17 more. Effective Mar 30, 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 2021-02-05](https://openairdocs.org/ad/2021-02-05): Navigation · Airbus A330-201, A330-202, A330-203 and 23 more. Effective Jan 29, 2021
- [AD 2020-24-11](https://openairdocs.org/ad/2020-24-11): Landing gear · Airbus A330-201, A330-202, A330-203 and 21 more. Effective Jan 5, 2021
- [AD 2020-20-15](https://openairdocs.org/ad/2020-20-15): Equipment/Furnishings · Airbus A330-202, A330-203, A330-223 and 11 more. Effective Nov 12, 2020
- [AD 2020-17-16](https://openairdocs.org/ad/2020-17-16): Flight Controls · Airbus A330-202, A330-203, A330-223 and 14 more. Effective Oct 8, 2020
- [AD 2020-06-17](https://openairdocs.org/ad/2020-06-17): Doors · Airbus A330-201, A330-202, A330-203 and 22 more. Effective May 14, 2020
- [AD 2020-04-10](https://openairdocs.org/ad/2020-04-10): Stabilizers · Airbus A330-201, A330-202, A330-203 and 19 more. Effective Apr 17, 2020
- [AD 2020-01-16](https://openairdocs.org/ad/2020-01-16): Navigation · Airbus A330-201, A330-202, A330-203 and 21 more. Effective Feb 21, 2020
- [AD 2019-24-01](https://openairdocs.org/ad/2019-24-01): Fuel · Airbus A318-111, A318-112, A318-121 and 38 more. Effective Feb 19, 2020
- [AD 2019-13-01](https://openairdocs.org/ad/2019-13-01): Landing gear · Airbus A330-201, A330-202, A330-203 and 17 more. Effective Dec 17, 2019
- [AD 2019-21-05](https://openairdocs.org/ad/2019-21-05): Oxygen · Airbus A330-201, A330-202, A330-203 and 21 more. Effective Nov 21, 2019
- [AD 2019-16-07](https://openairdocs.org/ad/2019-16-07): Wings · Airbus A330-201, A330-202, A330-203 and 19 more. Effective Oct 22, 2019
- [AD 2019-17-05](https://openairdocs.org/ad/2019-17-05): Wings · Airbus A330-201, A330-202, A330-203 and 21 more. Effective Oct 15, 2019
- [AD 2019-14-10](https://openairdocs.org/ad/2019-14-10): Stabilizers · Airbus A330-223, A330-243, A330-301 and 13 more. Effective Aug 23, 2019
- [AD 2019-06-03](https://openairdocs.org/ad/2019-06-03): Hydraulic power · Airbus A330-201, A330-202, A330-203 and 18 more. Effective May 9, 2019
- [AD 2019-03-23](https://openairdocs.org/ad/2019-03-23): Flight controls · Airbus A330-201, A330-202, A330-203 and 21 more. Effective Apr 3, 2019

All 394: https://openairdocs.org/tcds/A43NM/ads.md

## Registered aircraft by registry model (OpenAirDocs)

- [Airbus A340-642](https://openairdocs.org/model/airbus-a340-642): 3 aircraft (registry code 3940038)
- [Airbus A340-600](https://openairdocs.org/model/airbus-a340-600): 2 aircraft (registry code 3940137)
- [Airbus A340-300](https://openairdocs.org/model/airbus-a340-300): 1 aircraft (registry code 3930379)
- [Airbus A340-313](https://openairdocs.org/model/airbus-a340-313): 1 aircraft (registry codes 3930355, 3940317)
- [Airbus A340-541](https://openairdocs.org/model/airbus-a340-541): 1 aircraft (registry code 3940139)
- [Airbus Industrie A340-313](https://openairdocs.org/model/airbus-industrie-a340-313): 1 aircraft (registry code 3930337)
- [Airbus S A S A340-642](https://openairdocs.org/model/airbus-s-a-s-a340-642): 1 aircraft (registry code 3940316)
- [Airbus A340-211](https://openairdocs.org/model/airbus-a340-211): 0 aircraft (registry code 3930448)
- [Airbus A340-312](https://openairdocs.org/model/airbus-a340-312): 0 aircraft (registry code 3930348)
- [Airbus Industrie A340-300](https://openairdocs.org/model/airbus-industrie-a340-300): 0 aircraft (registry code 3930380)
- [Airbus Industrie A340-311](https://openairdocs.org/model/airbus-industrie-a340-311): 0 aircraft (registry code 3930346)
- [Airbus Industrie A340-313X](https://openairdocs.org/model/airbus-industrie-a340-313x): 0 aircraft (registry code 3930373)

## STCs approved under this data sheet (137, first 50)

- [STC ST12461IB](https://openairdocs.org/stc/ST12461IB): Installation of Cockpit Voice Recorder with optional RIPS Upgrade. Mid- Canada Mod Center
- [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 ST04474NY](https://openairdocs.org/stc/ST04474NY): Activation of Wireless Local Area Network (WLAN) system. Jet Aviation AG
- [STC ST00588AT](https://openairdocs.org/stc/ST00588AT): Installation of Collins SAT-906 SATCOM with an AlliedSignal/ Dassault SAT-48 antenna system.. AIRCRAFT RECONFIG TECHNOLOGIES, LLC
- [STC ST00952LA](https://openairdocs.org/stc/ST00952LA): Installation of Mass Systems fire extinguisher cartridges as replacements for Kidde fire extinguisher cartridges in fire extinguisher bottles.. AMETEK AMERON LLC d/b/a MASS Systems
- [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 ST03326CH](https://openairdocs.org/stc/ST03326CH): Installation of an advertisement container on the bottom of a seat back tray table. Atin OOH LLC
- [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 ST00826LA](https://openairdocs.org/stc/ST00826LA): Installation of Lower Deck Mobile Crewrest.. Safran Cabin 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 ST02171SE](https://openairdocs.org/stc/ST02171SE): Installation of stowage bins and provisions for the installation of a new cabin interior. B/E Aerospace Inc. - FSI
- [STC ST04573CH](https://openairdocs.org/stc/ST04573CH): Installation of ARINC 791 SATCOM Structural Provisions. Amphenol Cable and Interconnect Technologies Inc.
- [STC ST00079IB](https://openairdocs.org/stc/ST00079IB): Integration of Halon-free Portable Fire Extinguisher HAFEX. UMLAUT ENGINEERING GMBH
- [STC ST01433LA](https://openairdocs.org/stc/ST01433LA): Installation of AirWorks Cockpit Door Surveillance Systems.. Aero Technik Inc.
- [STC ST00215IB](https://openairdocs.org/stc/ST00215IB): Installation of saf-Tglo ECO Photoluminescent Aisle Path Marking Systems. STG AEROSPACE GERMANY GmbH
- [STC ST01936WI](https://openairdocs.org/stc/ST01936WI): Installation of LED lights. AeroLED's Holdings LLC
- [STC ST00691SE](https://openairdocs.org/stc/ST00691SE): Installation of lightweight window plugs. LiteAir Aviation Products Inc
- [STC ST02664AT](https://openairdocs.org/stc/ST02664AT): Installation of SafTGlo Inc. Photoluminescent floor proximity emergency escape path marking system (FPEEPMS).. STG Aerospace 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 ST02302CH](https://openairdocs.org/stc/ST02302CH): Install ERDA model 7004 HI-LO table with slide top. Collins Aerospace
- [STC ST02643NY](https://openairdocs.org/stc/ST02643NY): Installation of Panasonic In-Flight Entertainment System. Delta Engineering Corporation
- [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 ST09092AC-D](https://openairdocs.org/stc/ST09092AC-D): Installation of executive interior, avionics, and various electronic equipment.. L3Harris Technologies Integrated Systems L.P.
- [STC ST09095AC-D](https://openairdocs.org/stc/ST09095AC-D): Installation of executive interior and various electrical equipment.. L3Harris Technologies Integrated Systems L.P.
- [STC ST09096AC-D](https://openairdocs.org/stc/ST09096AC-D): Installation of 480 gallons potable water.. L3Harris Technologies Integrated Systems L.P.
- [STC ST09099AC-D](https://openairdocs.org/stc/ST09099AC-D): Installation of executive interior and various electronic equipment. Approved for installation in Airbus A340-213, serial number 151, ONLY.. L3Harris Technologies Integrated Systems L.P.
- [STC ST9759SC-D](https://openairdocs.org/stc/ST9759SC-D): Installation of a ground intrusion detection and recording system.. L3Harris Technologies Integrated Systems L.P.
- [STC ST00105IB](https://openairdocs.org/stc/ST00105IB): Introduction of Activation of Wireless Charging Systems for Portable Electronic Devices. AMAC AEROSPACE SWITZERLAND AG
- [STC ST00100IB](https://openairdocs.org/stc/ST00100IB): Installation of New Premium Economy Class Seats. Lufthansa Technik AG
- [STC ST01987CH](https://openairdocs.org/stc/ST01987CH): Installation of a Honeywell RESCU 406AF Emergency Locator Transmitter (ELT) system.. Honeywell International Inc.
- [STC ST03422NY](https://openairdocs.org/stc/ST03422NY): Update of Intelsat components. Delta Engineering Corporation
- [STC ST01030SE](https://openairdocs.org/stc/ST01030SE): Installation of the Honeywell DAA-4A Dual Antenna Drive Unit. Honeywell International Inc
- [STC ST01963WI](https://openairdocs.org/stc/ST01963WI): Installation of Integra Pulse Portable Oxygen Bottle. B/E Aerospace
- [STC ST04352AT](https://openairdocs.org/stc/ST04352AT): Installation of a Talon Aerospace LED Replacement Navigation / Position Light. Aaxico Technical Services Inc.
- [STC ST03574AT](https://openairdocs.org/stc/ST03574AT): Installation of a Talon Aerospace Anti-Collision Light. Aaxico Technical Services Inc.
- [STC ST04002AT](https://openairdocs.org/stc/ST04002AT): Installation of a Talon LED Replacement Wing and Tail Mounted Anti-Collision Lights. Aaxico Technical Services Inc.
- [STC ST04177AT](https://openairdocs.org/stc/ST04177AT): Installation of a Talon Aerospace LED Replacement General Purpose Lamps. Aaxico Technical Services Inc.
- [STC ST02056LA](https://openairdocs.org/stc/ST02056LA): Installation of Rockwell Collins Total Entertainment System.. Burrana Inc.
- [STC ST01644WI-D](https://openairdocs.org/stc/ST01644WI-D): Installation of a Honeywell Enhanced Ground Proximity Warning Computer (EGPWC) and Activation of the Smart Runway/Smart Landing Features in accordance with Honeywell Master Drawing List 756-0236-001, revision A, dated August 19, 2011, or later FAA approved revision.. Honeywell International Inc
- [STC ST00151LA](https://openairdocs.org/stc/ST00151LA): Installation of Honeywell/Racal Aeronautical satellite communication system.. Honeywell International Inc
- [STC ST02378LA](https://openairdocs.org/stc/ST02378LA): Installation of Monogram Systems' In-Flight Trash Compactor. Safran Cabin Galleys US Inc.
- [STC ST04372NY](https://openairdocs.org/stc/ST04372NY): Installation of saf-Tglo® SSUL23 Photoluminescent Aisle Path Marking System. STG Aerospace Ltd
- [STC ST04049NY](https://openairdocs.org/stc/ST04049NY): Installation of a Hoffman Engineering LLC LED Landing Light to replace the OEM Q4559 Series Incandescent Lamp, used as a Landing/Takeoff Light. Hoffman Engineering LLC
- [STC ST00950LA](https://openairdocs.org/stc/ST00950LA): Installation of passenger entertainment system.. Burrana Inc.
- [STC ST01891LA-D](https://openairdocs.org/stc/ST01891LA-D): Installation of a Commercial Medical Stretcher.. LifePort LLC
- [STC ST03419NY](https://openairdocs.org/stc/ST03419NY): Installation of Bruce Aerospace Cabin Lighting. Delta Engineering Corporation
- [STC ST03162NY](https://openairdocs.org/stc/ST03162NY): Installation of a Panasonic Global Communication Suite System. Delta Engineering Corporation
- [STC ST03848NY](https://openairdocs.org/stc/ST03848NY): Installation of SuperSeal UltraLite (SSUL) PHOTOLUMINESCENT AISLE PATH MARKING SYSTEM. STG Aerospace Ltd

All 137: https://openairdocs.org/tcds/A43NM/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.