TYPE CERTIFICATE DATA SHEET NO. A43NM

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TYPE CERTIFICATE DATA SHEET NO. A43NM

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DEPARTMENT OF TRANSPORTATION
FEDERAL AVIATION ADMINISTRATION
A43NM
Revision 4
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
March 19, 2007
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
1, Rond-Point Maurice Bellonte
31707 Blagnac
France
Type Certificate Holder Record - Name change from Airbus Industrie to Airbus 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, Revision 4 Page 2 of 18 March 19, 2007
Maximum Weight:
Variant 000
(Basic)
kg / lb
001
(MOD 41302)
kg / lb
Maximum Ramp Weight 254,400 / 560,952 257,900 / 568,670
Maximum Take-off Weight, MTOW 253,500 / 558,968 257,000 / 566,685
Maximum Landing Weight, MLW 181,000 / 399,105 181,000 / 399,105
Maximum Zero Fuel Weight, MZFW 169,000 / 372,645 169,000 / 372,645
Maximum Baggage:
Cargo Compartment Maximum Load
(kg / lb)
Forward 18,507 / 40,809
Aft 15,241 / 33,606
Rear 3,468 / 7,647
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 00F080A0002/C2S for A340-211 and A340-212 and
00F080A0004/C0S for A340-213.
Aircraft 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.
All placards required by either the AFM, the applicable operating rules, or the certification basis must be installed in the
airplane.
Model A340 Aircraft Airbus Document Refr. Revision No. Date
-211 AI/EV-O 34000 1 May 27, 1993
-212 AI/EV-O 34000 1 February 3, 1997
-213 AI/EV-O 34000 1 February 3, 1997
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 III, Data Pertinent to All Model A340-200 and A340-300 Series Airplanes.
For information on Import Requirements, Service Information and General Notes: See section VII, Data Pertinent to
All Model A340-200, A340-300, A340-500 and A340-600 Series Airplanes.
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:
A43NM, Revision 4 Page 3 of 18 March 19, 2007
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 FAA-Type Certificate E37NE
Maximum Weight:
Variant 000
(Basic)
kg / lb
001
(MOD 41302)
kg / lb
Maximum Ramp Weight 254,400 / 560,952 257,900 / 568,670
Maximum Take-off Weight, MTOW 253,500 / 558,968 257,000 / 566,685
Maximum Landing Weight, MLW 186,000 / 410,130 186,000 / 410,130
Maximum Zero Fuel Weight, MZFW 174,000 / 383,670 174,000 / 383,670
Maximum Baggage:
Cargo Compartment Maximum Load
(kg / lb)
Forward 22,861 / 50,409
Aft 18,507 / 40,808
Rear 3,468 / 7,647
For the positions and the loading conditions authorized in each position (references of containers, pallets and associated
weight) see weight and Balance Manual:
Ref. Airbus Document 00F080A0002/C3S for A340-311 and A340-312
Ref. Airbus Document 00F080A0004/C0S for A340-313
Aircraft 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.
All placards required by either the AFM, the applicable operating rules, or the certification basis must be installed in the
airplane.
Model A340 Aircraft Airbus Document Refr. Revision No. Date
-311 AI/EV-O 34000 1 May 27, 1993
-312 AI/EV-O 34000 1 February 3, 1997
-313 AI/EV-O 34000 1 February 3, 1997
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 :
A43NM, Revision 4 Page 4 of 18 March 19, 2007
See Section III, Data Pertinent to All Model A340-200 and A340-300 Series Airplanes.
For information on Import Requirements, Service Information and General Notes: See section VII, Data Pertinent to
All Model A340-200, A340-300, A340-500 and A340-600 Series Airplanes.
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
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).
A43NM, Revision 4 Page 5 of 18 March 19, 2007
(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
• 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. forward of the fuselage nose, 275.8 in. 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
379 passengers with 4 pair Type A exits configuration.
A43NM, Revision 4 Page 6 of 18 March 19, 2007
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
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. Part 25 of the FAR effective February 1, 1965, including amendments 25-1 through 25-63 and amendments 25-
65, 25-66 and 25-77.
b. Part 25 of the FAR amendment 25-64 with the following exceptions:
• Cockpit seats will not meet FAR 25.562 amendment 25-64 but will meet FAR 25.561
• Compliance with 25.785(a), (b), and (d) at amendment 25-64 for front row seats in front of a bulkhead will be
based on ensuring a 35 inch free head strike envelope.
c. Special Federal Aviation regulation FAR Part 34 as amended by Amendments 27-1, through 27-7.
d. Part 36 of the FAR as amended by amendments 36-1 through 36-20.
A43NM, Revision 4 Page 7 of 18 March 19, 2007
e. FAA Special conditions issued for the A340 in accordance with Section 21.16 of the FAR 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
(2) Command Signal Integrity
(3) Protection From Lightning and Unwanted Effects of High Intensity Radiated Fields (HIRF)
(4) Interaction of Systems and Structures
(5) Design Dive Speed
(6) Design Maneuver Requirements
(7) Limit Pilot Forces
(8) Tail plane Tank Emergency Landing Loads
(9) Limit Engine Torque
(10) Ground Load Conditions for Center Landing Gear
(11) Flight Characteristics
(12) Flight Envelope Protection
(13) Side Stick Controllers
(14) Computerized Airplane Flight Manual (AFM) Performance Information
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 FAR 21.21(b)(1) for the following paragraphs of
the FAR:
(1) 25.335(d) for design airspeeds
(2) 25.345 for high lift devices
(3) 25.349 for control surface loads
(4) 25.351(b) for unsymmetrical loads
(5) 25.371 for gyroscopic loads
(6) 25.373 for speed control devices
(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
i. Optional requirements elected:
• 25.801 for ditching.
• 25.1419 for icing.
The Direction Generale de '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 Aviation Safety Agency (EASA)
began oversight of this product on behalf of DGAC.
Production Basis:
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.
• Equipment approved for installation is listed in the Type Certification Standard Equipment Lists; 00F000A0101/C0S for
the A340-211 and A340-311, 00F000A0102/C0S for the A340-212 and A340-312, and 00F000A0103/C0S for the A340-
213 and A340-313.
A43NM, Revision 4 Page 8 of 18 March 19, 2007
• Cabin furnishings, equipment and arrangement shall conform to the following specification:
• 00F252K0010/C01 for cabin seats.
• 00F252K0006/C01 for galley.
• 00F252K0020/C01 for cabin attendant seats
Hydraulic Fluids:
Type IV - Specification NSA 30.7110
Auxiliary Power Unit (APU):
Garrett Airesearch 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:
ICAO Annex 16 Volume 1 – Chapter 3, or Chapter 4 with Modification 55005.
IV. Type A340-600 Series Transport Category Airplanes:
Airbus Model A340-642 - approved July 22, 2002
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.
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 mechanical linkage between computer and actuators for both primary and backup systems
Engines
Airplane Model Engine Model: Engine Type Certificate:
A340-642 Four Rolls-Royce– Trent 556-61 turbojet engines FAA-Type Certificate E00066NE
Maximum Weight:
Variant 000
(Basic)
kg / lb
001
(Mod 50312)
kg / lb
Maximum Ramp Weight 366,200 / 807,471 369,200 / 814,086
Maximum Take-off Weight, MTOW 365,000 / 804,825 368,000 / 811,440
Maximum Landing Weight, MLW 256,000 / 564,480 259,000 / 571,095
Maximum Zero Fuel Weight, MZFW 242,000 / 533,610 245,000 / 540,225
A43NM, Revision 4 Page 9 of 18 March 19, 2007
Number of Seats:
The maximum number of passengers approved for emergency evacuation is 379 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 / 67,213
Aft 22,861 / 50,409
Rear 3,468 / 7,647
For the positions and the loading conditions authorized in each position (references of containers, pallets and associated
weight) see weight and Balance Manual:
Ref. Airbus Document 00F080A0601/C6S for A340-642
Fuel Capacity
Tank Capacity
Usable Fuel Unusable Fuel
Tank liters
(kg)
gallons
(lb)
Liters
(kg)
gallons
(lb)
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)
Wing
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.
All placards required by either the AFM, the applicable operating rules, or the certification basis must be installed in the
airplane.
Model A340 Aircraft Airbus Document Refr. Revision No. Date
-642 STL 34000 1 July 22, 2002
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 III, Data Pertinent to All Model A340-200 and A340-300 Series Airplanes.
For information on Import Requirements, Service Information and General Notes: See section VII, Data Pertinent to
All Model A340-200, A340-300, A340-500 and A340-600 Series Airplanes.
A43NM, Revision 4 Page 10 of 18 March 19, 2007
V. Type A340-500 Series Transport Category Airplanes:
Airbus Model A340-541 - approved January 27, 2003
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 A340-500 series is shorther than the A340-600 by 14 frames. It is intended for long range operations having
additional fuel capacity over that of the –600 with the installation of a rear center tank (RCT).
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:
Variant 000
(Mod 51000)
kg / lb
001
(Mod 51080)
kg / lb
Maximum Ramp Weight 369,200 / 814,086 373,200 / 822,906
Maximum Take-off Weight, MTOW 368,000 / 811,440 372,000 / 820,260
Maximum Landing Weight, MLW 240,000 / 529,200 243,000 / 535,815
Maximum Zero Fuel Weight, MZFW 225,000 / 496,125 230,000 / 507,150
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 / 54,009
Aft 16,330 / 36,008
Rear 3,458 / 7,625
For the positions and the loading conditions authorized in each position (references of containers, pallets and associated
weight) see weight and Balance Manual:
A43NM, Revision 4 Page 11 of 18 March 19, 2007
Ref. Airbus Document 00F080A0501/C5S for A340-541
Fuel Capacity:
Tank Capacity
Usable Fuel Unusable Fuel
Tank liters
(kg)
gallons
(lb)
Liters
(kg)
gallons
(lb)
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)
Wing
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.
All placards required by either the AFM, the applicable operating rules, or the certification basis must be installed in the
airplane.
Model A340 Aircraft Airbus Document Refr. Revision No. Date
-541 STL 34000 1 January 16, 2003
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 VI, Data Pertinent to All Model A340-500 and A340-600 Series Airplanes.
For information on Import Requirements, Service Information and General Notes: See section VII, Data Pertinent to
All Model A340-200, A340-300, A340-500 and A340-600 Series Airplanes.
A43NM, Revision 4 Page 12 of 18 March 19, 2007
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:
Rolls-Royce
RB 211 Trent 556-61
Rolls-Royce
RB 211 Trent 553-61
Engine Limitations
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 - Aeroshell Turbine Oil (Royco
Turbine Oil) 555
- Mobil Jet Oil II, 254, 291
- Aeroshell Turbine Oil (Royco
Turbine Oil) 555
- Mobil Jet Oil II, 254, 291
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
A43NM, Revision 4 Page 13 of 18 March 19, 2007
• 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
• Minimum Control Speed, VMC Refer to AFM performance Section
(Performance Engineering Program/OCTOPUS)
Landing Gear Speeds:
• Maximum Speed with Landing Gear 250 KIAS/.55 M
Operating (Extension and Retraction), VL0
• Maximum Speed with Landing Gear 250 KIAS/.55 M
Locked Down, VLE
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°
A43NM, Revision 4 Page 14 of 18 March 19, 2007
Manoeuvre 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°
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 as amended by Amendments 25-1 through Amendment 25-95 inclusive plus
Amendments 25-97, 25-98 and 25-104 with the following exceptions:
Excepted FAR 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 Section 21.16 of the FAR 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) Flight Envelope Protection
(12)(e) Pitch and Roll Limiting
(13) Side Stick Controllers
A43NM, Revision 4 Page 15 of 18 March 19, 2007
(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.
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.
e. Equivalent safety findings have been made in accordance with FAR 21.21(b)(1) for the following FAR 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
§§ FAR 25 (All FAR 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
§ 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
§§ 25.1305, 251501(b): Auxiliary Power Unit (APU) Instrumentation and Monitoring Requirements
§ 25.1305(c)(6), Warning Means for Engine Fuel Filter Contamination
f. Optional Design Regulations
(a) §25.801: Ditching Provisions
(b) §25.1411(d),(e),(f),(g): General Safety Equipment
(c) §25.1415: Ditching Equipment
(d) §25.1419: Ice Protection
g. Exemptions: Exemptions from the applicable regulations has been processed in accordance with the provisions of 14
CFR 11.25.
A43NM, Revision 4 Page 16 of 18 March 19, 2007
• 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.
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 Aviation Safety Agency (EASA) began oversight of this product on
behalf of DGAC.
Production Basis:
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:
Type IV - Specification 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
Environmental requirements for noise:
ICAO Annex 16 Volume 1 – Chapter 3, or Chapter 4 with Modification 55005.
VII. Data Pertinent to All Model A340-200, A340-300, A340-500 and A340-600 Series Airplanes:
Import Requirements
The FAA can issue a U.S. airworthiness certificate based on an French Export Certificate of Airworthiness (Export C of A)
signed by a representative of the Direction Generale de 'Aviation Civile (DGAC) of France on behalf of the European
Community. The Export C of A should contain the following statement (in the English language): “The aircraft covered
by this certificate has been examined, tested, and found to conform to the Type Design approved under FAA Type
Certificate No. A43NM as defined in TCDS A43NM and to be in condition for safe operation."
A43NM, Revision 4 Page 17 of 18 March 19, 2007
The regulatory basis U.S. airworthiness certification basis for aircraft type certificated under FAR Section 21.29 and
exported by the country of manufacture is FAR Sections 21.183(c) or 21.185(c). The U.S. airworthiness certification basis
for aircraft type certificated under FAR Section 21.29 exported from countries other than the country manufacture (e.g.,
third party country) is FAR Sections 21.183(d) or 21.183(b). These sections provide that U.S. airworthiness certificates
are issued only if the Administrator finds “that the aircraft conforms to the type design and is in a condition for safe
operation.”
In order for the FAA to make the finding that an A340 aircraft is in a condition for safe operation, the FAA certificating
inspector or other authorized person must contact the Manager, International Branch, ANM-116, FAA Transport Airplane
Directorate; 1601 Lind Avenue Southwest; Renton, Washington 98055; telephone (425) 227-1263; fax (425) 227-1149,
prior to issuance of the U.S. airworthiness certificate to obtain the FAA Required Modification List (RML) for the A340.
Prior to issuance of a Standard Airworthiness Certificate on any Airbus A340 model aircraft, all modifications shown in
the Model A340 RML must be accomplished in the interest of safety before the aircraft can be found to be in a condition
for safe operation.
Authority for these required modifications is given per the airworthiness certification provisions of 49 U.S.C. 44704 (c),
which states "the Administrator may include in an airworthiness certificate terms required in the interest of safety".
“Terms required in the interest of safety” include actions to correct unsafe conditions issued by the foreign authority of the
state of design that also meet FAA criteria for corrective action. This law also gives the FAA the authority to adopt FAR §
21.183(c) and (d), which form the regulatory basis for the issue of standard U.S. airworthiness certificates on imported
products. 14 CFR §21.183(c) and (d) provide that airworthiness certificates are issued only if the Administrator finds “that
the aircraft conforms to the type design and is in a condition for safe operation.” The modifications identified in the Model
A340 RML are required in the interest of safety and are necessary for this airplane to be in a condition for safe operation.
A Notice of Policy Statement announcing the FAA’s policy with respect to foreign mandatory continued airworthiness
information, when no aircraft of the affected design are currently operating in the U.S. was published in the Federal
Register on May 11, 1998. 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.
Service Information:
Each of the documents listed below that contain a statement that it is approved by the European 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.
Note: Design changes that are contained in Airbus Service Bulletins and that are classified as Level 1 Major in accordance
with the US/France Bilateral Aviation Safety Agreement Implementation Procedures for Airworthiness must be
approved by the FAA.
General Notes: (All Models of A340 Series Airplanes)
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;
A43NM, Revision 4 Page 18 of 18 March 19, 2007
• 00F080A0004/C0S for A340-213 and -313;
• 00F080A0601/C6S for A340-642;
• 00G080A0006/C3S for A340-541.
Note 2: Instructions For Continued Airworthiness required under § 21.50 for service life limits on components,
required inspections and inspection intervals, and certification maintenance requirements:
• Safe Life Airworthiness Limitation Items are provided in the A340 Airworthiness Limitations Section (ALS) sub
parts 1-2 and 1-3 approved by EASA (Document 00F050AM091/C01);
• Damage-Tolerant Airworthiness Limitation Items are provided in the A340 Airworthiness Limitations Section
(ALS) part 2 approved by EASA (Document 00F050A3401/C01);
• Certification Maintenance Requirements (CMR’s) are provided in the A340 Airworthiness Limitations Section
(ALS) Part 3 approved by EASA (Document 00F050A0003/C01);
• A340 Maintenance Review Board Report 00F050A0002/C01 aproved by FAA.
• Fuel Airworthiness Limitations are provided in the A340 Airworthiness Limitations Section (ALS) Part 5
approved by EASA (Document 95A.1933/05)
Note 3: 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 A340-200, A340-300, A340-500 and A340-600 Series Airplanes).
Note 4: For Airbus model A340-541: Airbus modifications 51344 and 51452 that extend the Kevlar liner in the 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.
….END….

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