DOC AIRBUS | AMM A320FFUSELAGE - DESCRIPTION AND OPERATION
** ON A/C NOT FOR ALL
1. General
The fuselage is a semi-monocoque structure. Light alloy circular frames and longitudinal stringers support and the primary fuselage skin stronger. There are no longitudinal stringers in the nose assembly.
The fuselage is made of different assemblies which are put together to make the complete fuselage shell. The assemblies are as follows:
Pressure bulkheads are installed at FR1 and FR70. The pressure bulkheads and the fuselage skin make the basic pressurized zone. The cockpit, cabin, avionics compartment and the FWD and AFT cargo-compartments are included in the pressurized zone.
The structure is made of frames, stringers and skin panels. They are riveted together to make the fuselage shell. Crossbeams make the shell stronger in the forward and aft fuselage. Support struts are attached to each end of the crossbeams (Ref. AMM 533300/534300). Longerons and seat tracks that are attached to the crossbeams make the cabin floor structure. The belly fairing primary structure (Ref. AMM 533500) is installed on the exterior of the lower fuselage between FR31/35 and FR48/FR53. It is an extension to the lower fuselage and contains the air-conditioning and hydraulic services equipment.
The cabin floor structure divides the fuselage into two areas, the upper fuselage and the lower fuselage. The upper fuselage includes the cockpit and the cabin. The lower fuselage includes the avionics compartments, nose and main gear bays and the FWD and AFT cargo-compartments. Crossbeams and support struts support the cabin floor structure at STGR23.
The floor panels are made of a honeycomb core which is bonded between Glass- fiber Reinforced Plastic (GFRP) sheets (Ref. AMM 533200/534200).
The radome, wing center box, nose and main gear bays, belly fairing and cone/rear fuselage are not in the pressurized zone.
Skin stiffeners make the fuselage skin stronger. They are riveted to the skin in areas of high stress (door openings, emergency exits, cabin windows, etc.).
The cabin windows are installed between STGR14 and STGR18 (Ref. AMM 562100).
** ON A/C NOT FOR ALL The fuselage is a semi-monocoque structure. Light alloy circular frames and longitudinal stringers support and the primary fuselage skin stronger. There are no longitudinal stringers in the nose assembly.
The fuselage is made of different assemblies which are put together to make the complete fuselage shell. The assemblies are as follows:
- nose forward fuselage,
- forward fuselage,
- center fuselage,
- rear fuselage,
- cone/rear fuselage.
Pressure bulkheads are installed at FR1 and FR70. The pressure bulkheads and the fuselage skin make the basic pressurized zone. The cockpit, cabin, avionics compartment and the FWD and AFT cargo-compartments are included in the pressurized zone.
The structure is made of frames, stringers and skin panels. They are riveted together to make the fuselage shell. Crossbeams make the shell stronger in the forward and aft fuselage. Support struts are attached to each end of the crossbeams (Ref. AMM 533300/534300). Longerons and seat tracks that are attached to the crossbeams make the cabin floor structure. The belly fairing primary structure (Ref. AMM 533500) is installed on the exterior of the lower fuselage between FR31/35 and FR48/FR53. It is an extension to the lower fuselage and contains the air-conditioning and hydraulic services equipment.
The cabin floor structure divides the fuselage into two areas, the upper fuselage and the lower fuselage. The upper fuselage includes the cockpit and the cabin. The lower fuselage includes the avionics compartments, nose and main gear bays and the FWD and AFT cargo-compartments. Crossbeams and support struts support the cabin floor structure at STGR23.
The floor panels are made of a honeycomb core which is bonded between Glass- fiber Reinforced Plastic (GFRP) sheets (Ref. AMM 533200/534200).
The radome, wing center box, nose and main gear bays, belly fairing and cone/rear fuselage are not in the pressurized zone.
Skin stiffeners make the fuselage skin stronger. They are riveted to the skin in areas of high stress (door openings, emergency exits, cabin windows, etc.).
The cabin windows are installed between STGR14 and STGR18 (Ref. AMM 562100).
2. Component Location
Fuselage - Component Location ** ON A/C NOT FOR ALL
Fuselage - Component Location ** ON A/C NOT FOR ALL
Fuselage - Component Location ** ON A/C NOT FOR ALL
Fuselage - Component Location ** ON A/C NOT FOR ALL
** ON A/C NOT FOR ALL Fuselage - Component Location ** ON A/C NOT FOR ALL Fuselage - Component Location ** ON A/C NOT FOR ALL Fuselage - Component Location ** ON A/C NOT FOR ALL Fuselage - Component Location ** ON A/C NOT FOR ALL 3. Description
A. Nose Forward Fuselage (Ref. AMM 531100)
(1) The nose forward fuselage extends from FR1 to FR24. The upper part of the assembly includes the cockpit and the entrance area for the two FWD passenger/crew doors (Ref. AMM 521100). The nose gear bay and the avionics compartment are installed in the lower part of the assembly.
(2) Longitudinal stringers are not included in the nose forward fuselage. More frames are installed at approximately half the distance of those installed in the other sections of the fuselage shell.
(3) Crossbeams make the shell stronger, they are attached to the frames. Support struts are attached to each end of the crossbeams. Longerons are attached to the crossbeams to make the cockpit and the entrance-area floor structure.
(4) The FWD pressure bulkhead is installed at FR1. The radome is installed on the forward face of FR1. The radome and the nose gear bay are not in the pressurized zone.
B. Forward Fuselage (Ref. AMM 532100)
(1) The forward fuselage extends from FR24 to FR35. The upper part of the assembly contains the forward cabin area. The FWD cargo-compartment is included in the lower part of the assembly. The upper and the lower parts of the assembly are in the pressurized zone.
(2) The structure of the FWD cargo-compartment floor is made of crossbeams which are attached to the frames at STGR37. Support struts are attached to the crossbeams. The cargo compartment door is installed on the right of the lower fuselage, between FR24A and FR28.
C. Center Fuselage (Ref. AMM 533100)
(1) The center fuselage extends from FR35 to FR47. The upper part of the assembly contains the center cabin area and the left and right overwing emergency exits between FR38 and FR41 (Ref. AMM 522100). The wing center box and the main gear bay are installed in the lower assembly, below the cabin floor. Only the cabin area of the assembly is in the pressurized zone.
(2) The wing center box is installed between FR36 and FR42. The structure extends across the width of the lower fuselage and is a continuation of the wing cantilever box. The main gear bay is installed between FR42 and FR46.
(3) A keel beam is installed in the bottom of the lower fuselage and extends from FR35 to FR46. The keel beam keeps the longitudinal structural strength of the lower fuselage and transmits the fuselage bending loads.
D. Rear Fuselage (Ref. AMM 534100)
(1) The rear fuselage extends from FR47 to FR70. It is made of two separate subassemblies which are then put together. The joint for the two subassemblies is made at FR64.
(2) The upper part of the complete assembly contains the rear cabin and the entrance area for the AFT passenger/crew doors (Ref. AMM 521300). The AFT cargo compartment is installed in the lower part of the assembly, between FR46/47 and FR65. The upper and the lower parts of the assembly are in the pressurized zone.
(3) The structure of the AFT cargo-compartment floor is made of crossbeams which are attached to the frames. Support struts are attached to the crossbeams. The cargo compartment door is installed on the right of the lower fuselage, between FR52A and FR56.
E. Cone/Rear Fuselage (Ref. AMM 535100)
(1) The cone/rear fuselage extends from FR70 to FR86. The assembly is made of two separate subassemblies. The joint for the two subassemblies is made at FR77.
NOTE: The specification given for the two subassemblies, and used in this topic, is cone/rear fuselage (FR70 to FR77) and tailcone (FR77 to FR86).
(2) The basic structure of both subassemblies is similar. They are made of frames, stringers and skin panels riveted together to make the cone/rear fuselage and tailcone shells.
(3) The rear pressure bulkhead is installed at FR70 in the cone/rear fuselage. The vertical stabilizer attach fittings are included on the top of FR70, FR72 and FR77 (Ref. AMM 553000). The trimmable horizontal stabilizer is installed between FR74 and FR77 (Ref. AMM 551000). Four tailcone attach fittings are included on the rear face of FR77.
(4) The Auxiliary Power Unit (APU) is installed in the tailcone (Ref. AMM 535800). The APU compartment is a specified fire zone and firewalls close the compartment on all sides. The firewalls are made of titanium sheets. You can remove the tailcone from the aircraft as one complete unit.
(5) Maintenance access doors are included in the lower right side of the two subassemblies (Ref. AMM 524100). The cone/rear fuselage access door 314AR is installed between FR78 and FR80; the APU access doors 315AL and 316AR are installed between FR80 and FR84.