DOC AIRBUS | AMM A320FFORWARD FUSELAGE - DESCRIPTION AND OPERATION
** ON A/C NOT FOR ALL
** ON A/C NOT FOR ALL
1. General
Forward Fuselage - Section 13/14 ** ON A/C NOT FOR ALL
Forward Fuselage - Section 13/14 ** ON A/C NOT FOR ALL
Forward Fuselage - Section 13/14 and Section 14A ** ON A/C NOT FOR ALL
Forward Fuselage - Section 13/14 and Section 14A ** ON A/C NOT FOR ALL
Forward Fuselage - Section 13/14 ** ON A/C NOT FOR ALL Forward Fuselage - Section 13/14 ** ON A/C NOT FOR ALL Forward Fuselage - Section 13/14 and Section 14A ** ON A/C NOT FOR ALL Forward Fuselage - Section 13/14 and Section 14A ** ON A/C NOT FOR ALL A. Location
The section 13/14 is the intermediate part of the forward fuselage. It lies between the FR24 and FR35. The upper part contains the front section of the cabin. The lower part contains the forward cargo compartment. The opening for the cargo door is on the right side of the aircraft between FR24A and FR28.
The section 13/14 is the intermediate part of the forward fuselage. It lies between the FR24 and FR35. The upper part contains the front section of the cabin. The lower part contains the forward cargo compartment. The opening for the cargo door is on the right side of the aircraft between FR24A and FR28.
The section 14A is the intermediate part of the forward fuselage. It lies between the FR35 and FR35.8. The top part contains the front section of the cabin. The bottom part contains the forward cargo compartment. The opening for the emergency exit door is on each side of the aircraft between FR35.1 and FR35.2A.
Section 13/14 is the middle part of the forward fuselage. This section is between FR24 and FR35. The upper part contains the front section of the cabin. The lower part contains the forward cargo compartment. The opening for the cargo door is on the right side of the aircraft, between FR24A and FR28.
Section 14A is the middle part of the forward fuselage. This section is between FR35 and FR35.8. The top part contains the front section of the cabin. The bottom part contains the forward cargo compartment.
The section 13/14 is the intermediate part of the forward fuselage. It lies between the FR24 and FR35. The upper part contains the front section of the cabin. The lower part contains the forward cargo compartment. The opening for the cargo door is on the right side of the aircraft between FR24A and FR28.
The section 13/14 is the intermediate part of the forward fuselage. It lies between the FR24 and FR35. The upper part contains the front section of the cabin. The lower part contains the forward cargo compartment. The opening for the cargo door is on the right side of the aircraft between FR24A and FR28.
The section 14A is the intermediate part of the forward fuselage. It lies between the FR35 and FR35.8. The top part contains the front section of the cabin. The bottom part contains the forward cargo compartment. The opening for the emergency exit door is on each side of the aircraft between FR35.1 and FR35.2A.
Section 13/14 is the middle part of the forward fuselage. This section is between FR24 and FR35. The upper part contains the front section of the cabin. The lower part contains the forward cargo compartment. The opening for the cargo door is on the right side of the aircraft, between FR24A and FR28.
Section 14A is the middle part of the forward fuselage. This section is between FR35 and FR35.8. The top part contains the front section of the cabin. The bottom part contains the forward cargo compartment.
2. Description
(1) Frame 24
FR24 is the splice between sections 13/14 and 11/12 (Ref. AMM D/O 53-10-00-00). The core of the frame is made of curved members with L-section sheet metal connected in splices. The skin of the two sections is safetied with a T-section edging with lockbolts to the frame core and a splice.
FR24 is the splice between sections 13/14 and 11/12 (Ref. AMM D/O 53-10-00-00). The core of the frame is made of curved members with L-section sheet metal connected in splices. The skin of the two sections is safetied with a T-section edging with lockbolts to the frame core and a splice.
(2) Frame 24A
FR24A is a secondary frame which has the top part open. This secondary frame is the forward vertical member of the cargo door frame. It is made of a machined curved member (on the right side, between stringers 20 and 44) and a curved member made from Z-section sheet metal (on the left side, between stringers 31 and 44).
FR24A is a secondary frame which has the top part open. This secondary frame is the forward vertical member of the cargo door frame. It is made of a machined curved member (on the right side, between stringers 20 and 44) and a curved member made from Z-section sheet metal (on the left side, between stringers 31 and 44).
(3) Frames 25, 26 and 27
These frames are open at the cargo door. They are made of curved members made from sheet metal.
Three frame lower sections that are above the cargo door are the joint between the upper curved members of the frame, the cabin floor cross beams and the top frame of the cargo door.
These frames are open at the cargo door. They are made of curved members made from sheet metal.
Three frame lower sections that are above the cargo door are the joint between the upper curved members of the frame, the cabin floor cross beams and the top frame of the cargo door.
(4) Frames 29 to 34
These frames are closed. They are made of curved members made from Z-section sheet metal connected in splices.
These frames are closed. They are made of curved members made from Z-section sheet metal connected in splices.
(5) Frame 35
FR35 is the splice between sections 13/14 and 14A. The core of the frame is made of curved members made from L-section sheet metal connected in splices. The skin of the two sections is safetied with a T-section edging with lockbolts to the frame core and a splice.
FR35 is the splice between sections 13/14 and 14A. The core of the frame is made of curved members made from L-section sheet metal connected in splices. The skin of the two sections is safetied with a T-section edging with lockbolts to the frame core and a splice.
(6) Frames 35.1 to 35.2A
These frames are open at the emergency exit. They consist of curved members formed from sheet metal.
These frames are open at the emergency exit. They consist of curved members formed from sheet metal.
(7) Frames 35.1 to 35.2A
These frames are made of curved members made from sheet metal.
These frames are made of curved members made from sheet metal.
(8) Frames 35.3 to 35.8
These frames are closed. They are made of curved members made from Z-section sheet metal connected in splices.
These frames are closed. They are made of curved members made from Z-section sheet metal connected in splices.
B. Stringers
The fuselage stringers consist of folded aluminium alloy Z-section sheet metal. They are arranged longitudinally and, together with the frames, they stiffen the fuselage ; the skin is attached to them. At the stringer 18,added lockbolts in place of rivets
The fuselage stringers are made of folded aluminium-alloy Z-section sheet-metal They are put longitudinally and, together with the frames, they make the fuselage stronger. The skin is attached to them.
Between FR31 and FR35, the resistance of the left and right sides of stringer 41 is increased.
At FR24, titanium lockbolts replace the rivets.
The fuselage stringers consist of folded aluminium alloy Z-section sheet metal. They are arranged longitudinally and, together with the frames, they stiffen the fuselage ; the skin is attached to them. At the stringer 18,added lockbolts in place of rivets
The fuselage stringers are made of folded aluminium-alloy Z-section sheet-metal They are put longitudinally and, together with the frames, they make the fuselage stronger. The skin is attached to them.
Between FR31 and FR35, the resistance of the left and right sides of stringer 41 is increased.
At FR24, titanium lockbolts replace the rivets.
C. Skin
Forward Fuselage - Section 13/14 ** ON A/C NOT FOR ALL
Forward Fuselage - Section 13/14 ** ON A/C NOT FOR ALL
The outer skin comprises three upper panels extending from FR24 to FR35 and fire lower panels. The two upper lateral panels include the openings for the cabin windows. The forward right lower panel includes the opening for the cargo door. The forward wing to fuselage fairings are attached to the lower section of the skin (Ref. 53-25-11).
The skin panels are aluminium alloy sheets lightened by cut-outs formed by chemical milling. Skin joints are formed by overlapping the edges of the upper panel on the lower panels on stringers 6, 18, 32 and 41. They are reinforced by crack-stop plates on frame intersections. The skin is secured to the frame via frame doublers and to the stringers.
Forward Fuselage - Section 13/14 and Section 14A ** ON A/C NOT FOR ALL
Forward Fuselage - Section 13/14 and Section 14A ** ON A/C NOT FOR ALL
The outer skin has three upper panels from FR24 to FR35.8 and fire lower panels. The two upper lateral panels include the openings for the cabin windows. The forward right lower panel includes the opening for the cargo door. The forward wing to fuselage fairings are attached to the lower section of the skin (Ref. 53-25-11).
The skin panels are aluminium alloy sheets which are lighter because of the cut-outs made of chemical milling. The skin joints are made of the overlaps of the edges of the upper panel on the lower panels on stringers 6, 18, 32 and 41. Their resistance is increased with crack-stop plates on the frame intersections. The skin is safetied to the frame with the frame doublers and to the stringers.
Forward Fuselage - Section 13/14 ** ON A/C NOT FOR ALL Forward Fuselage - Section 13/14 ** ON A/C NOT FOR ALL The skin panels are aluminium alloy sheets lightened by cut-outs formed by chemical milling. Skin joints are formed by overlapping the edges of the upper panel on the lower panels on stringers 6, 18, 32 and 41. They are reinforced by crack-stop plates on frame intersections. The skin is secured to the frame via frame doublers and to the stringers.
Forward Fuselage - Section 13/14 and Section 14A ** ON A/C NOT FOR ALL Forward Fuselage - Section 13/14 and Section 14A ** ON A/C NOT FOR ALL The skin panels are aluminium alloy sheets which are lighter because of the cut-outs made of chemical milling. The skin joints are made of the overlaps of the edges of the upper panel on the lower panels on stringers 6, 18, 32 and 41. Their resistance is increased with crack-stop plates on the frame intersections. The skin is safetied to the frame with the frame doublers and to the stringers.
D. Cabin Floor Structure
Cabin Floor Structure - Section 13/14 ** ON A/C NOT FOR ALL
Cabin Floor Structure - Section 13/14 and Section 14A ** ON A/C NOT FOR ALL
Cabin Floor Structure - Section 13/14 ** ON A/C NOT FOR ALL
The structure of the cabin floor includes:
Cabin Floor Structure - Section 13/14 ** ON A/C NOT FOR ALL Cabin Floor Structure - Section 13/14 and Section 14A ** ON A/C NOT FOR ALL Cabin Floor Structure - Section 13/14 ** ON A/C NOT FOR ALL - Cross beams
- Seat tracks
- Dummy seat tracks
- Floor edgings
- Floor panels.
(1) Cross Beams
The cross beams are made of aluminium alloy extruded sections installed with rivets to the frames in the zones of stringers 23 and 24. They increase the resistance of the frames and the fuselage stability. The struts hold the cross beams on each side of the fuselage. These struts are installed with rivets to the lower part of the frame level with stringers 32.
The cross beams are made of aluminium alloy extruded sections installed with rivets to the frames in the zones of stringers 23 and 24. They increase the resistance of the frames and the fuselage stability. The struts hold the cross beams on each side of the fuselage. These struts are installed with rivets to the lower part of the frame level with stringers 32.
(2) Seat Tracks
The passenger seats are installed on the four seat tracks which are installed with bolts on the cross beams. They also hold the floor panels. The seat tracks are made of aluminium-alloy extruded sections.
The passenger seats are installed on the four seat tracks which are installed with bolts on the cross beams. They also hold the floor panels. The seat tracks are made of aluminium-alloy extruded sections.
(3) Dummy seat tracks
Two dummy seat tracks hold the floor panels in the center part of the floor. They are installed with bolts on the cross beams. These dummy seat tracks are made of aluminium alloy extruded sections.
Two dummy seat tracks hold the floor panels in the center part of the floor. They are installed with bolts on the cross beams. These dummy seat tracks are made of aluminium alloy extruded sections.
(4) Floor Edgings
Two Z-section edgings safetied to the cross beams hold the sides of the cabin floor. A rods assembly safetied with rivets connects stringer 26 to the floor edge, along the length of the fuselage.
Two Z-section edgings safetied to the cross beams hold the sides of the cabin floor. A rods assembly safetied with rivets connects stringer 26 to the floor edge, along the length of the fuselage.
(5) Floor panels
The floor is made of NOMEX honeycomb sandwich-panels with a glass fiber skin and a Alutisse strip as a protective cover. The panels are installed with screws on the seat tracks, the dummy seat tracks and the floor edge. The supports that are installed with bolts on the cross beams hold the center sections of the panels between the seat tracks dummy and the floor edge.
The floor is made of NOMEX honeycomb sandwich-panels with a glass fiber skin and a Alutisse strip as a protective cover. The panels are installed with screws on the seat tracks, the dummy seat tracks and the floor edge. The supports that are installed with bolts on the cross beams hold the center sections of the panels between the seat tracks dummy and the floor edge.
E. Structure of Cargo Compartment Floor
The structure of the cargo compartment floor is made of cross beams made from folded sheet installed with rivets to the frames. Folded sheet struts installed with rivets to the lower part of the frames hold the cross beams.
The structure of the cargo compartment floor is made of cross beams made from folded sheet installed with rivets to the frames. Folded sheet struts installed with rivets to the lower part of the frames hold the cross beams.
F. Cabin Windows
Forward Fuselage - Section 13/14 ** ON A/C NOT FOR ALL
Forward Fuselage - Section 13/14 and Section 14A ** ON A/C NOT FOR ALL
Forward Fuselage - Section 13/14 ** ON A/C NOT FOR ALL
Forward Fuselage - Section 13/14 and Section 14A ** ON A/C NOT FOR ALL
The cabin windows are installed in the drop-forged frames with rivets, on the two sides of the fuselage, between stringers 14 and 18.
There are no stringers at the window level.
Forward Fuselage - Section 13/14 ** ON A/C NOT FOR ALL Forward Fuselage - Section 13/14 and Section 14A ** ON A/C NOT FOR ALL Forward Fuselage - Section 13/14 ** ON A/C NOT FOR ALL Forward Fuselage - Section 13/14 and Section 14A ** ON A/C NOT FOR ALL There are no stringers at the window level.
G. Cargo Door Frame
Forward Fuselage - Section 13/14 ** ON A/C NOT FOR ALL
Forward Fuselage - Section 13/14 and Section 14A ** ON A/C NOT FOR ALL
Forward Fuselage - Section 13/14 ** ON A/C NOT FOR ALL
Forward Fuselage - Section 13/14 and Section 14A ** ON A/C NOT FOR ALL
The sides of the cargo door opening are made of FR24A and FR28. FR24A is attached to FR24 on attach-fittings with rivets.
The top and bottom zones of the door are made of stringers 23 and 29.
The door edging plates hold the lower sections of FR25, FR26 and FR27 attached to the cross beams. This increases the resistance of the top of the door opening.
A door threshold box safeties the door latch fittings and increases the resistance of the bottom of the door opening.
Forward Fuselage - Section 13/14 ** ON A/C NOT FOR ALL Forward Fuselage - Section 13/14 and Section 14A ** ON A/C NOT FOR ALL Forward Fuselage - Section 13/14 ** ON A/C NOT FOR ALL Forward Fuselage - Section 13/14 and Section 14A ** ON A/C NOT FOR ALL The top and bottom zones of the door are made of stringers 23 and 29.
The door edging plates hold the lower sections of FR25, FR26 and FR27 attached to the cross beams. This increases the resistance of the top of the door opening.
A door threshold box safeties the door latch fittings and increases the resistance of the bottom of the door opening.