DOC AIRBUS | AMM A320FNOSE FORWARD FUSELAGE - DESCRIPTION AND OPERATION
** ON A/C NOT FOR ALL
** ON A/C NOT FOR ALL
1. General
A. Location
The nose forward fuselage extends from STA254 to FR24. It is divided into two zones : non-pressurized zone and pressurized zone.
The nose forward fuselage extends from STA254 to FR24. It is divided into two zones : non-pressurized zone and pressurized zone.
(1) The non-pressurized zone forward of FR1 includes the radome which houses the radar and the ILS antennas.
(2) The pressurized zone extends between FR1 and FR24 and comprises:
- the cockpit at the upper part between FR1 and FR13 forward of STA621 and the forward section of the cabin aft of STA621,
- the avionics compartment and the nose landing gear well at the lower part.
2. Description
A. Main Structure
The structure of the nose forward fuselage comprises three parts:
The structure of the nose forward fuselage comprises three parts:
- the forward upper structure between FR1 and FR11,
- the aft upper structure between FR12 and FR23,
- the lower structure between FR1 and FR23.
Forward Upper Structure - FR1 to FR11(1) The forward upper structure between FR1 and FR11 comprises:
- four closed frames and bulkheads FR1, FR2, FR8 and FR11,
- four open frames comprising the openings for the windshield and the side windows ; FR3, FR4, FR5, FR6, FR7, FR9, FR10,
- a windshield and side window frame to which the structural frames are attached,
- two lateral boxes at floor level,
- a forward pressure bulkhead,
- a floor support structure,
(2) The aft upper structure between FR12 and FR23 comprises:
- an assembly of closed frames,
- the passenger/crew door frames between FR16 and FR20,
- three open frames FR17A, FR18 and FR19A in the zone of the passenger/crew door,
- stringers,
- a floor support structure.
(3) The lower structure between FR1 and FR23 comprises:
- a landing gear well which consists of three machined panels reinforced by extruded sections attached by rivets in the frame plane,
- an assembly of frame curved members two of which, FR9 and FR20, are main frames and which make the forward and aft limit of the landing gear well,
- two lower stringers which provide the joint between the lower skin panel and the lateral panels,
- a lifting ring attached to the front of FR9,
- four access door frames,
- external power receptacle.
B. Skin
The skin panels are formed from aluminium alloy sheets and include cut-outs and reinforcement obtained through chemical milling.
The central panel has an opening for access between frames 3 and 5 and the opening for the nose landing gear between frames 9 and 20. The lower right panel has two access openings between FR12 and FR14 and FR21 and FR23.
The lower left panel has an access opening between FR13 and FR15.
The forward upper part of the fuselage (FR1 to FR12) comprises the lateral skin panels and five upper skin panels. These panels are secured to the windshield and side window frames.
The aft upper part of the fuselage section (FR12 to FR24) consists of lateral skin panels and an upper skin panel. The lateral panels contain the frames of the passenger/crew doors between FR16 and FR20. A channel is installed above the doors.
All the skin panels are riveted together with an application of sealant.
The skin panels are made of aluminum alloy sheets and include cut-outs and reinforcements made by chemical milling.
The central panel has an opening for access between FR3 and FR5 and an opening for the nose landing gear between FR9 and FR20. The lower right panel has two access openings between FR12 and FR14 and between FR21 and FR23.
The lower left panel has an access opening between FR13 and FR15.
The forward top part of the fuselage (FR1 to FR12) includes the lateral skin panels and three upper skin panels. These skin panels are attached to the windshield and side window frames.
The aft top part of the fuselage (FR12 to FR24) includes the lateral skin panels and an upper skin panel. The lateral skin panels contain the frames of the passenger/crew doors between FR16 and FR20. A channel is installed above the doors.
All the skin panels are riveted together with application of sealant.
The skin panels are formed from aluminium alloy sheets and include cut-outs and reinforcement obtained through chemical milling.
NOTE: The skin panels above and below the windshield are made of titanium to provide improved protection against bird impact.
The lower section of the fuselage comprises three skin panels extending from FR1 to FR24. The central panel has an opening for access between frames 3 and 5 and the opening for the nose landing gear between frames 9 and 20. The lower right panel has two access openings between FR12 and FR14 and FR21 and FR23.
The lower left panel has an access opening between FR13 and FR15.
The forward upper part of the fuselage (FR1 to FR12) comprises the lateral skin panels and five upper skin panels. These panels are secured to the windshield and side window frames.
The aft upper part of the fuselage section (FR12 to FR24) consists of lateral skin panels and an upper skin panel. The lateral panels contain the frames of the passenger/crew doors between FR16 and FR20. A channel is installed above the doors.
All the skin panels are riveted together with an application of sealant.
The skin panels are made of aluminum alloy sheets and include cut-outs and reinforcements made by chemical milling.
NOTE: The skin panel below the windshield is made of titanium to give better protection against bird strike.
The bottom section of the fuselage includes three skin panels installed between FR1 and FR24. The central panel has an opening for access between FR3 and FR5 and an opening for the nose landing gear between FR9 and FR20. The lower right panel has two access openings between FR12 and FR14 and between FR21 and FR23.
The lower left panel has an access opening between FR13 and FR15.
The forward top part of the fuselage (FR1 to FR12) includes the lateral skin panels and three upper skin panels. These skin panels are attached to the windshield and side window frames.
The aft top part of the fuselage (FR12 to FR24) includes the lateral skin panels and an upper skin panel. The lateral skin panels contain the frames of the passenger/crew doors between FR16 and FR20. A channel is installed above the doors.
All the skin panels are riveted together with application of sealant.
(1) Frame 1 Pressure Bulkhead
Frame 1 which provides the forward pressure bulkhead of the fuselage, is made with an aluminium alloy sheet reinforced by stiffeners riveted to the forward and aft surfaces of the bulkhead. The forward stiffeners are arranged horizontally and the aft stiffeners are arranged horizontally and vertically.
The joint between the pressure bulkhead and the outer skin is provided by edging made from formed metal sheet riveted to the edge of the frame and to the skin. The bulkhead attachment is reinforced by webs riveted to the skin and to aft stiffeners of the bulkhead, and by a box in the cockpit floor. The center part of the pressure bulkhead is thus secured to the support structure of the floor. The two radome hinge fittings and the radome latch and support fittings are attached to the upper and lower sections of the frame respectively.
A protective bird-impact screen made of a honeycomb structure is secured to the forward face of the pressure bulkhead.
New supports are installed on the honeycomb panel structure. A ballast of 200 kg (440.9244 lb) can be fitted to these supports.
Frame 1 which provides the forward pressure bulkhead of the fuselage, is made with an aluminium alloy sheet reinforced by stiffeners riveted to the forward and aft surfaces of the bulkhead. The forward stiffeners are arranged horizontally and the aft stiffeners are arranged horizontally and vertically.
The joint between the pressure bulkhead and the outer skin is provided by edging made from formed metal sheet riveted to the edge of the frame and to the skin. The bulkhead attachment is reinforced by webs riveted to the skin and to aft stiffeners of the bulkhead, and by a box in the cockpit floor. The center part of the pressure bulkhead is thus secured to the support structure of the floor. The two radome hinge fittings and the radome latch and support fittings are attached to the upper and lower sections of the frame respectively.
A protective bird-impact screen made of a honeycomb structure is secured to the forward face of the pressure bulkhead.
New supports are installed on the honeycomb panel structure. A ballast of 200 kg (440.9244 lb) can be fitted to these supports.
(2) Frame 2
The top of the frame is closed by a machined curved member the upper section of which is straight. This provides a forward attachment point for the instrument panel and the frame for the windshield. The lateral and lower curved members are formed from folded Z-section sheet.
The top of the frame is closed by a machined curved member the upper section of which is straight. This provides a forward attachment point for the instrument panel and the frame for the windshield. The lateral and lower curved members are formed from folded Z-section sheet.
(3) Frame 3
Consists of machined lateral and lower curved members. Its upper section is open.
Consists of machined lateral and lower curved members. Its upper section is open.
(4) Frame 4
Consists of folded sheet lateral and lower curved members. Its upper and lower sections are open.
Consists of folded sheet lateral and lower curved members. Its upper and lower sections are open.
(5) Frame 5
The lower curved member is machined and the lateral curved members are formed from folded sheet.
The lower curved member is machined and the lateral curved members are formed from folded sheet.
(6) Frames 6 and 7
These frames consist of two lateral curved members and a lower curved member formed from folded sheet.
These frames consist of two lateral curved members and a lower curved member formed from folded sheet.
(7) Frame 8
This frame is closed and consists of machined upper, lateral and lower curved members. The upper curved members form the posts between the side windows. The frame supports a cross beam of the cockpit floor. This cross beam is also supported by two rods which are themselves supported by the lower section of the frame.
This frame is closed and consists of machined upper, lateral and lower curved members. The upper curved members form the posts between the side windows. The frame supports a cross beam of the cockpit floor. This cross beam is also supported by two rods which are themselves supported by the lower section of the frame.
(8) Frame 9
The frame which is open at the level of the side windows consists ; of an upper curved member formed from folded sheet, and machined lateral and upper curved members. The lower section provides the forward bulkhead of the nose landing gear box. Two reinforcement rods are attached to the top corners of the landing gear box and to the lateral curved members of the frame.
The frame which is open at the level of the side windows consists ; of an upper curved member formed from folded sheet, and machined lateral and upper curved members. The lower section provides the forward bulkhead of the nose landing gear box. Two reinforcement rods are attached to the top corners of the landing gear box and to the lateral curved members of the frame.
(9) Frame 10
Consists of an upper curved member and lateral curved members formed from folded sheet and two machined lower curved members attached to the landing gear well.
Consists of an upper curved member and lateral curved members formed from folded sheet and two machined lower curved members attached to the landing gear well.
(10) Frame 11
The upper lateral and lower curved members are machined. The upper curved members provide the aft posts of the side windows. A floor cross beam is secured to the frame. This cross beam is supported by two rods which are supported by the landing gear well.
The upper lateral and lower curved members are machined. The upper curved members provide the aft posts of the side windows. A floor cross beam is secured to the frame. This cross beam is supported by two rods which are supported by the landing gear well.
(11) Frame 12
The upper and lateral curved members are formed from folded sheet. They comprise an extruded T-section and a splice which provide the skin joint. The lower curved members are machined. This frame supports a cross beam of the floor reinforced by two rods attached to the landing gear well.
The upper and lateral curved members are formed from folded sheet. They comprise an extruded T-section and a splice which provide the skin joint. The lower curved members are machined. This frame supports a cross beam of the floor reinforced by two rods attached to the landing gear well.
(12) Frames 13 and 14
The upper and lateral curved members are formed from folded sheet. The lower curved members are machined. These frames have an opening in the lower right (FR13) or left (FR14) section for the cargo compartment doors. Frame 14 also supports a cross beam of the cabin floor.
The upper and lateral curved members are formed from folded sheet. The lower curved members are machined. These frames have an opening in the lower right (FR13) or left (FR14) section for the cargo compartment doors. Frame 14 also supports a cross beam of the cabin floor.
(13) Frames 15 and 16
These reinforced frames form the forward frames of the passenger/crew doors. All curved members are machined. Frame 16 supports a cross beam of the floor.
These reinforced frames form the forward frames of the passenger/crew doors. All curved members are machined. Frame 16 supports a cross beam of the floor.
(15) Frame 18
The upper curved member is formed from folded sheet and the lower curved members are machined.
The upper curved member is formed from folded sheet and the lower curved members are machined.
(16) Frames 20 and 21
These reinforced frames form the aft frames of the passenger/crew doors. All curved members are machined. The frames support a cross beam of the floor. Frame 20 closes the rear of the landing gear well and is reinforced by rods attached to the top corners of the landing gear well.
These reinforced frames form the aft frames of the passenger/crew doors. All curved members are machined. The frames support a cross beam of the floor. Frame 20 closes the rear of the landing gear well and is reinforced by rods attached to the top corners of the landing gear well.
(17) Frame 23
This frame is closed. The upper and lateral curved members are formed from folded sheet and the lower curved member is machined. This frame supports a cross beam of the floor reinforced by two struts.
This frame is closed. The upper and lateral curved members are formed from folded sheet and the lower curved member is machined. This frame supports a cross beam of the floor reinforced by two struts.
D. Floors
The cockpit, cabin and avionics compartment floors consists mainly of honeycomb panels attached to the floor support structure with screws
In the forward avionics compartment the floor panels are installed to protect the structure and systems when an operator gets access to the compartment.
The cockpit, cabin and avionics compartment floors consists mainly of honeycomb panels attached to the floor support structure with screws
In the forward avionics compartment the floor panels are installed to protect the structure and systems when an operator gets access to the compartment.