GENERAL ARRANGEMENT GENERAL ARRANGEMENT SECTIONS BREAKDOWN SECTIONS BREAKDOWN
The fuselage is a semi-monocoque structure. Aluminum alloy circular frames and longitudinal stringers support and strengthen the main fuselage skin. The fuselage is divided into five main parts:
- the nose forward fuselage (section 11/12), - the forward fuselage (section 13), - the center fuselage (section 15/21), - the aft fuselage (section 18),
- the cone/rear fuselage (section 19/19.1),
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GENERAL ARRANGEMENT - SECTIONS BREAKDOWN
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FUSELAGE DESCRIPTION (3)
GENERAL ARRANGEMENT (continued) GENERAL ARRANGEMENT (continued)
SKIN PANEL MATERIALS SKIN PANEL MATERIALS
The A380-800 includes the use of new materials and processes on fuselage skin panels:
- The glare, which is a fiber metal laminated material built up from alternating layers of aluminum sheets and glass fibers,
- The 2XXX series aluminum alloys to which copper is the main chemical element,
- The 6XXX series aluminum alloys to which magnesium is the main chemical element; it is used on the welded skin/stringer assembly, - The 7XXX series aluminum alloys to which zinc is the main chemical element.
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GENERAL ARRANGEMENT - SKIN PANEL MATERIALS
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FUSELAGE DESCRIPTION (3)
NOSE FORWARD FUSELAGE NOSE FORWARD FUSELAGE
SECTION LAYOUT SECTION LAYOUT
The nose forward fuselage extends from frame (FR) 0 to FR 22. It includes section 11 from FR 0 to FR 15 and section 12 from FR 15 to FR 22.
The nose forward fuselage includes:
- the radome, - the nose lower fairing, - the nose lower unit,
- the nose forward unit (cockpit), - and the nose rear unit.
Pressure bulkheads separate the pressurized areas from the non-pressurized areas. The entire nose forward fuselage is pressurized except:
- the radome (protection for the ILS antenna and the weather radar), -the nose landing gear bay.
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NOSE FORWARD FUSELAGE - SECTION LAYOUT
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FUSELAGE DESCRIPTION (3)
NOSE FORWARD FUSELAGE (continued) NOSE FORWARD FUSELAGE (continued)
NOSE LOWER FAIRING NOSE LOWER FAIRING
The nose lower fairing is part of section 11; it is fitted on the cockpit structure, and contains the wheels in flying configuration and bears the forward nose landing gear doors. It also supports the radome attachment and the liner panels. The articulated liner panel give access to the radar area and to the radome b olts attachment. FR 2 struts h elp to withstand the loads of the doors actuators. They are attached onto the cockpit lower pressure bulkhead. All skin panels are made of aluminum alloy.
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NOSE FORWARD FUSELAGE - NOSE LOWER FAIRING
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FUSELAGE DESCRIPTION (3)
NOSE FORWARD FUSELAGE (continued) NOSE FORWARD FUSELAGE (continued)
NOSE LOWER UNIT NOSE LOWER UNIT
The nose lower unit is installed between FR 10B and FR 22. The skin panels of the nose lower unit are made of aluminum alloy. The nose lower unit houses:
- the nose landing gear bay,
- the electronic bay (with an access door cutout), - the nose jack fitting,
- and the external power receptacle housing.
The nose lower unit bears also the aft nose landing gear doors.
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NOSE FORWARD FUSELAGE - NOSE LOWER UNIT
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FUSELAGE DESCRIPTION (3)
NOSE FORWARD FUSELAGE (continued) NOSE FORWARD FUSELAGE (continued)
NOSE FORWARD UNIT NOSE FORWARD UNIT
The nose forward unit houses the flight deck compartment. The skin panels of the upper structure are made of aluminum alloy. The cockpit floor is located between FR 5 and FR 14. The cockpit floor structure has crossbeams (see illustration) and longitudinal beams (not shown) made of aluminum alloy. Front and curved bulkhead panels separate the pressurized and non-pressurized areas; they are made of aluminum alloy.
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NOSE FORWARD FUSELAGE - NOSE FORWARD UNIT
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FUSELAGE DESCRIPTION (3)
NOSE FORWARD FUSELAGE (continued) NOSE FORWARD FUSELAGE (continued)
NOSE REAR UNIT NOSE REAR UNIT
The nose rear unit extends from FR 15 to FR 22. This section bears passenger doors M1L and M1R, between FR 17 and FR 19. The upper deck floor structure extends from FR 17 to FR 20; it is made of aluminum alloy in this unit. The main deck floor structure extends from FR 16 to FR 21, and is also made of aluminum alloy.
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NOSE FORWARD FUSELAGE - NOSE REAR UNIT
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FUSELAGE DESCRIPTION (3)
FORWARD FUSELAGE FORWARD FUSELAGE SECTION LAYOUT SECTION LAYOUT
The forward fuselage, section 13, extends from FR 2 2 to FR 38. This assembly bears the passenger doors M2L, M2R, and the forward cargo door on the right hand side of the fuselage. The main sub-assemblies of this section are:
- the upper shell, from FR 22 to FR 38, between stringers (STGR) 22LH and STGR 22RH where skin panels are made of GLARE, - side shells, from FR 22 to 38, between STGR 22LH and STGR 53LH and between STGR 22RH and STGR 53RH, where most of skin panels are made of GLARE, except between FR 22 and FR 31, from STGR 39RH to STGR 53RH. Around the cargo door, skin panels are made of aluminum alloy,
- the lower shell, from FR 22 to FR 38, between STGR 53LH to STGR 53RH, where the skin panels are made of aluminum alloy with welded stringers.
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FORWARD FUSELAGE - SECTION LAYOUT
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FUSELAGE DESCRIPTION (3)
FORWARD FUSELAGE (continued) FORWARD FUSELAGE (continued)
TYPICAL FUSELAGE CROSS SECTION TYPICAL FUSELAGE CROSS SECTION
The typical fuselage with constant section starts after FR 30. In this typical section, the upper deck floor i s located at STGR 26 level. The main deck floor is located at STGR 43 level, and the cargo floor at STGR 62 level. The main deck floor structure is reinforced by CFRP rods.
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FORWARD FUSELAGE - TYPICAL FUSELAGE CROSS SECTION
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FUSELAGE DESCRIPTION (3)
FORWARD FUSELAGE (continued) FORWARD FUSELAGE (continued)
FLOOR STRUCTURE FLOOR STRUCTURE
The main deck floor has a classical structure with crossbeams made of aluminum alloy supporting the seat tracks. The upper deck structure bears the staircase torsion box u p to FR 26. Crossbeams are made of:
- aluminum alloy from FR 21 to FR 26,
- Carbon Fiber Reinforced Plastic (CFRP) after FR 26. The cargo floor structure is also made with aluminum alloy crossbeams. It supports the roller tracks and the cargo loading system.
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FORWARD FUSELAGE - FLOOR STRUCTURE
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FUSELAGE DESCRIPTION (3)
CENTER FUSELAGE CENTER FUSELAGE SECTION LAYOUT SECTION LAYOUT
The center fuselage, section 15/21, extends from FR 38 to FR 74. All this section is pressurized, except the center wing box and the landing gear bays.
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CENTER FUSELAGE - SECTION LAYOUT
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FUSELAGE DESCRIPTION (3)
CENTER FUSELAGE (continued) CENTER FUSELAGE (continued) STRUCTURE ARRANGEMENT STRUCTURE ARRANGEMENT The main components of this section are:
- the upper forward unit, - the upper middle shell, - the door M3 panels, - the upper rear unit, - the lower forward unit, - the rear lateral gear bays, - the rear lower shell, - and the belly fairing.
The upper shell of section 15/21 has the upper forward unit, the upper middle shell, the doors M3 panels and the upper rear unit.
The upper forward unit bears the passenger door U1L and U1R cutouts.
There are two door M3 panels; they bear the passenger doors M3L and M3R.
The upper rear unit bears the passenger doors U2L and U2R.
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CENTER FUSELAGE - STRUCTURE ARRANGEMENT
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FUSELAGE DESCRIPTION (3)
CENTER FUSELAGE (continued) CENTER FUSELAGE (continued) LOWER CENTER FUSELAGE LOWER CENTER FUSELAGE
The lower center fuselage has the lower forward unit, the center wi ng box, the rear lateral gear bays and the rear lower shell. The center wing box is not described in ATA 53 chapter as it is a part of the wing (ATA 57 chapter).
The lower center fuselage hosts the rear lateral gear bays from FR 56 to FR 72, at each side of the aft cargo compartment. The gear bays are limited on the inboard side by the landing gear bays walls/cargo compartment lateral walls, which are pressurized bulkheads. On the outboard side, they are limited by canted beams and stiffened skin panels. The rear lateral gear bays have on each side of the fuselage, one wing gear bay from FR 56 to the center bulkhead at FR 63, and one body gear bay from the center bulkhead at FR 63 to the rear pressure bulkhead at FR 72.
All skin panels of the lower center fuselage are made of aluminum alloy.
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CENTER FUSELAGE - LOWER CENTER FUSELAGE
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FUSELAGE DESCRIPTION (3)
CENTER FUSELAGE (continued) CENTER FUSELAGE (continued)
BELLY FAIRING BELLY FAIRING
The belly fairing structure is located at the bottom part of the fuselage between FR 35 and FR 81 and bears the wing and body landing gear doors, external access panels and access doors for maintenance.
It is made of:
- a metallic framework that gives shape to the structure and holds the panels
- belly fairing panels attached to the framework, to give a soft aerodynamic surface to the air-stream. Panels are sandwich panels made of sandwich Nomex honeycomb core on CFRP skins.
The panels are held by a longitudinal and a transversal framework made of aluminum alloy sheet metal. On the lower area, the frame foots and the stringers of the framework are made of titanium alloy, due to high exposure to corrosion.
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CENTER FUSELAGE - BELLY FAIRING
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FUSELAGE DESCRIPTION (3)
AFT FUSELAGE AFT FUSELAGE
SECTION LAYOUT SECTION LAYOUT
The aft fuselage section extends from FR 74 to FR 95. This section is constant up to FR 79. It bears, on the right hand side, the aft and bulk cargo doors. The aft fuselage bears also the passenger door M4L/R, M5L/R, and U3L/R cutouts. The upper skin panels from STGR 39LH to STGR 39RH are made of GLARE and the lower skin panels from STGR 39 on each side are made of aluminum alloy. The cross-section is a typical structure with upper deck crossbeams made of CFRP, and main deck crossbeams made o f aluminum alloy.
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AFT FUSELAGE - SECTION LAYOUT
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FUSELAGE DESCRIPTION (3)
CONE/REAR FUSELAGE CONE/REAR FUSELAGE
SECTION LAYOUT SECTION LAYOUT
The cone/rear fuselage, section 19/19.1 is a non-pressurized area, which extends from FR 95 to FR 120. This section is divided into two sub sections:
- first, section 19 from FR 95 to FR 110; the rear pressure bulkhead makes the junction between section 18 and 19 at FR 95. It also bears the Vertical Tail Plane (VTP) and the Trimmable Horizontal Stabilizer (THS). This section is made of CFRP excepted the frames and the fittings at attachment areas of VTP and THS, made of aluminum alloy.
- the last part of the aircraft is the tail cone section, section 19.1, from FR 110 to FR 120. It bears the Auxiliary Power Unit. This section is made of CFRP excepted the rear fairing made of titanium alloy.
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CONE/REAR FUSELAGE - SECTION LAYOUT
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FUSELAGE DESCRIPTION (3)
CONE/REAR FUSELAGE (continued) CONE/REAR FUSELAGE (continued)
SECTION 19 - REAR PRESSURE BULKHEAD SECTION 19 - REAR PRESSURE BULKHEAD The rear pressure bulkhead is made of monolithic CFRP construction.
It has 15 radial aligned stiffeners on its outer side, and cutouts for pressure discharge valves. The rear pressure bulkhead is attached to the fuselage skin and the frame 95 through tension struts and by titanium alloyed finger straps.
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CONE/REAR FUSELAGE - SECTION 19 - REAR PRESSURE BULKHEAD
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FUSELAGE DESCRIPTION (3)
CONE/REAR FUSELAGE (continued) CONE/REAR FUSELAGE (continued)
SECTION 19 - VTP AND THS ATTACHMENT SECTION 19 - VTP AND THS ATTACHMENT The VTP is attached to section 19 through 12 fail-safe fittings made of aluminum alloy. They are installed between FR 98 and FR 104. At FR 98 and FR 103, lateral load fittings carry a part of lateral loads coming from the VTP front and rear spars. The cutout for the THS is located between FR 102 and FR 108.
The THS is attached (at the rear spar) to section 19 by means of THS hinge fittings; lateral load fittings carry a part of loads coming from THS. It is installed in the LH and RH sides of the center frame part of frame 108.
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CONE/REAR FUSELAGE - SECTION 19 - VTP AND THS ATTACHMENT
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FUSELAGE DESCRIPTION (3)
CONE/REAR FUSELAGE (continued) CONE/REAR FUSELAGE (continued)
SECTION 19.1 - TAIL CONE SECTION 19.1 - TAIL CONE
The tail cone section (section 19.1) extends from FR 110 to the end of the aircraft. It houses the APU between FR 112 and FR 117, in a special fire proof compartment made of CFRP with a special resin.
The exhaust muffler is installed at the rear fairing zon e of the section.
Skin panels of this section are made of laminated CFRP, and two maintenance doors at the lower part of the section give access for maintenance operations. The rear fairing is made of titanium and is removable.
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CONE/REAR FUSELAGE - SECTION 19.1 - TAIL CONE
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