DOC AIRBUS | AMM A320FWINGS - DESCRIPTION AND OPERATION
** ON A/C NOT FOR ALL
1. General
The aircraft wing is a continuous structure which goes through the fuselage between Frames 36 and 42. It is made in three parts:
The center wing is part of the fuselage and gives attachment points for the outer wings. Each outer wing has a wingbox, leading and trailing edges and a wing tip. The leading edge has attachments for the slats and the trailing edge has attachments for the main landing gear, aileron, flaps and spoilers. A wingtip fence is installed on the wingtip.
** ON A/C NOT FOR ALL 
Wing - GeneralThe aircraft wing is a continuous structure which goes through the fuselage between Frames 36 and 42. It is made in three parts:
- the center wing (zone 140)
- the left outer wing (zone 500)
- the right outer wing (zone 600).
The center wing is part of the fuselage and gives attachment points for the outer wings. Each outer wing has a wingbox, leading and trailing edges and a wing tip. The leading edge has attachments for the slats and the trailing edge has attachments for the main landing gear, aileron, flaps and spoilers. A wingtip fence is installed on the wingtip.
2. Component Location
The main components of the wing are:
** ON A/C NOT FOR ALL The main components of the wing are:
- the center wing (Ref. AMM D/O 57-10-00-00)
- the outer wing (Ref. AMM D/O 57-20-00-00)
- the wingbox (Ref. AMM D/O 57-21-00-00)
- the wing tip (Ref. AMM D/O 57-30-00-00)
- the leading edge and leading edge devices (Ref. AMM D/O 57-40-00-00)
- the trailing edge and trailing edge devices (Ref. AMM D/O 57-50-00-00)
- the aileron (Ref. AMM D/O 57-60-00-00)
- the spoilers (Ref. AMM D/O 57-70-00-00).
- the center wing (Ref. AMM D/O 57-10-00-00)
- the outer wing (Ref. AMM D/O 57-20-00-00)
- the wingbox (Ref. AMM D/O 57-21-00-00)
- the sharklet (Ref. AMM D/O 57-30-00-00)
- the leading edge and leading edge devices (Ref. AMM D/O 57-40-00-00)
- the trailing edge and trailing edge devices (Ref. AMM D/O 57-50-00-00)
- the aileron (Ref. AMM D/O 57-60-00-00)
- the spoilers (Ref. AMM D/O 57-70-00-00).
3. Description
A. Center Wing
The center wing is installed in the center fuselage between Frames 36 and 42 and includes:
The center wing has attachments for the left and the right outer wings at the left RIB1 and the right RIB1. The center wing-box has an integral fuel tank. Access to this fuel tank is through the access doors in Frame 42.
The center wing is installed in the center fuselage between Frames 36 and 42 and includes:
- the front and rear spars (at Frames 36 and 42)
- the upper and lower skin-panels
- the two main frames (Frames 36 and 42)
- a set of 38 aluminium alloy rods (four assemblies of six rods and two assemblies of seven rods)
- the left RIB1 and the right RIB1.
The center wing has attachments for the left and the right outer wings at the left RIB1 and the right RIB1. The center wing-box has an integral fuel tank. Access to this fuel tank is through the access doors in Frame 42.
B. Outer Wing
Each outer wing includes:
Each outer wing includes:
Each outer wing includes:
- the wing box
- the sharklet
- the leading edge and the leading edge devices
- the trailing edge and the trailing edge devices.
Each outer wing includes:
- the wing box
- the wing tip
- the leading edge and the leading edge devices
- the trailing edge and the trailing edge devices.
(1) Wing Box
The main structure of each outer wing is the wing box which tapers from the wing root to the sharklet. Its front and rear spars extend from RIB1 to RIB27. The rear spar is made in three parts and has joints at RIB6 and RIB22.
The wing box has 27 ribs. The ribs are continuous between the front and the rear spars. The top surface of the wing box has two skin panels, and the bottom surface has three panels. Each of the wing panels extends forward of the front spar and aft of the rear spar. The leading and the trailing edge structures attach to these projections and to the front and rear spars. Stringers give strength to the top and the bottom skin panels.
The wing box makes an integral fuel tank and a vent surge tank. 21 access panels in the lower skin give access to the fuel tank and the vent surge tank. The wing box also has attachments for:
The main structure of each outer wing is the wing box which tapers from the wing root to the sharklet. Its front and rear spars extend from RIB1 to RIB27. The rear spar is made in three parts and has joints at RIB6 and RIB22.
The wing box has 27 ribs. The ribs are continuous between the front and the rear spars. The top surface of the wing box has two skin panels, and the bottom surface has three panels. Each of the wing panels extends forward of the front spar and aft of the rear spar. The leading and the trailing edge structures attach to these projections and to the front and rear spars. Stringers give strength to the top and the bottom skin panels.
The wing box makes an integral fuel tank and a vent surge tank. 21 access panels in the lower skin give access to the fuel tank and the vent surge tank. The wing box also has attachments for:
- the leading edge and the leading edge devices
- the sharklet
- the trailing edge and the trailing edge devices
- the engine mounting pylons
- the main landing gear.
(2) Wing Box
The main structure of each outer wing is the wing box which tapers from the wing root to the wing tip. Its front and rear spars extend from RIB1 to RIB27. The rear spar is made in three parts and has joints at RIB6 and RIB22.
The wing box has 27 ribs. The ribs are continuous between the front and the rear spars. The top surface of the wing box has two skin panels, and the bottom surface has three panels. Each of the wing panels extends forward of the front spar and aft of the rear spar. The leading and the trailing edge structures attach to these projections and to the front and rear spars. Stringers give strength to the top and the bottom skin panels.
The wing box makes an integral fuel tank and a vent surge tank. 21 access panels in the lower skin give access to the fuel tank and the vent surge tank. The wing box also has attachments for:
The main structure of each outer wing is the wing box which tapers from the wing root to the wing tip. Its front and rear spars extend from RIB1 to RIB27. The rear spar is made in three parts and has joints at RIB6 and RIB22.
The wing box has 27 ribs. The ribs are continuous between the front and the rear spars. The top surface of the wing box has two skin panels, and the bottom surface has three panels. Each of the wing panels extends forward of the front spar and aft of the rear spar. The leading and the trailing edge structures attach to these projections and to the front and rear spars. Stringers give strength to the top and the bottom skin panels.
The wing box makes an integral fuel tank and a vent surge tank. 21 access panels in the lower skin give access to the fuel tank and the vent surge tank. The wing box also has attachments for:
- the leading edge and the leading edge devices
- the wing tip and the wingtip fence
- the trailing edge and the trailing edge devices
- the engine mounting pylons
- the main landing gear.
(3) Sharklet
The sharklet is installed at Rib 27.
The sharklet is installed at Rib 27.
(4) Wing Tip
The wing tip is installed at Rib 27. The wingtip fence attaches to the outboard end of the wing tip.
The wing tip is installed at Rib 27. The wingtip fence attaches to the outboard end of the wing tip.
(5) Leading Edge and Leading Edge Devices
The leading edge assembly is forward of the front-spar of the wing-box. It includes the inboard and the outboard leading-edge assemblies and the top and the bottom panels. The inboard and outboard leading-edge assemblies have their D-noses and panels installed on ribs which attach to the front spar. The hold-down devices and the rotary actuators (for Slat 1 tracks 2 and 3) are on other ribs. The leading edge devices are the five slats.
The leading edge assembly is forward of the front-spar of the wing-box. It includes the inboard and the outboard leading-edge assemblies and the top and the bottom panels. The inboard and outboard leading-edge assemblies have their D-noses and panels installed on ribs which attach to the front spar. The hold-down devices and the rotary actuators (for Slat 1 tracks 2 and 3) are on other ribs. The leading edge devices are the five slats.
(6) Leading Edge Slats
The leading edge slats are installed on the wing as follows:
The leading edge slats are installed on the wing as follows:
- Slat 1 is between RIB2 and RIB7
- Slat 2 is between RIB8 and RIB12
- Slat 3 is between RIB12 and RIB17
- Slat 4 is between RIB17 and RIB22
- Slat 5 is between RIB22 and RIB27.
(7) Trailing Edge and Trailing Edge Devices
The trailing edge structure is aft of the rear spar of the wing box and includes the inner, mid and outer rear-spar trailing-edges.
The inner rear-spar trailing-edge includes:
The trailing edge devices are:
The trailing edge structure is aft of the rear spar of the wing box and includes the inner, mid and outer rear-spar trailing-edges.
The inner rear-spar trailing-edge includes:
- the shroud box
- the overwing panel
- the fixed shroud
- the underwing panel.
- the hinge ribs
- the intermediate ribs
- the actuating-cylinder brackets
- the top and bottom panels
- the trailing-edge support structures.
The trailing edge devices are:
- the two trailing edge flaps
- the aileron
- the five spoilers.
(8) Trailing Edge and Trailing Edge Devices
The trailing edge structure is aft of the rear spar of the wing box and includes the inner, mid and outer rear-spar trailing-edges.
The inner rear-spar trailing-edge includes:
The trailing edge devices are:
The trailing edge structure is aft of the rear spar of the wing box and includes the inner, mid and outer rear-spar trailing-edges.
The inner rear-spar trailing-edge includes:
- the shroud box
- the overwing panel
- the fixed shroud
- the underwing panel.
- the hinge ribs
- the intermediate ribs
- the actuating-cylinder brackets
- the top and bottom panels
- the trailing-edge support structures.
The trailing edge devices are:
- the two trailing edge flaps with tabs
- the aileron
- the five spoilers.
(9) Trailing Edge Flaps
The inboard and the outboard flaps are installed on the trailing edge of the wing. The inboard flap is between RIB1 and RIB9 and the outboard flap is between RIB9 and RIB22.
The inboard and the outboard flaps are installed on the trailing edge of the wing. The inboard flap is between RIB1 and RIB9 and the outboard flap is between RIB9 and RIB22.
(10) Aileron
The aileron is installed on the trailing edge of the wing, between RIB22 and RIB27.
The aileron is installed on the trailing edge of the wing, between RIB22 and RIB27.
(11) Spoilers
There are five spoilers installed on the upper surface of each wing, forward of the trailing edge flaps. Spoiler 1 is installed between RIB5 and RIB9. Spoilers 2 thru 6 are installed between RIB10 and RIB22.
There are five spoilers installed on the upper surface of each wing, forward of the trailing edge flaps. Spoiler 1 is installed between RIB5 and RIB9. Spoilers 2 thru 6 are installed between RIB10 and RIB22.
C. Wing Main Data
Wing reference area ...... ........................ 122.40 m2 (1318.00 ft2)
Aerodynamic mean chord ... ........................ 4.19 m (13.75 ft.)
Geometric mean chord...... ........................ 3.62 m (11.88 ft.)
Span ..................... ........................ 33.91 m (111.26 ft.)
Aspect ratio ............. ........................ 9.40
Taper ratio (tip chord/root chord)................. 0.25
Root chord................ ........................ 6.07 m (19.92 ft.)
Kink chord................ ........................ 3.76 m (12.34 ft.)
Tip chord................. ........................ 1.50 m (4.92 ft.)
Sweep angle (25%)......... ........................ 24 deg. 58 min.
Relative thickness:
Dihedral of wing reference plane................... 5.11 degrees
Dihedral of trailing edge inboard of kink.......... 8.65 degrees
Dihedral of trailing edge outboard of kink ........ 5.35 degrees
Wing reference area ...... ........................ 126.0 m2 (1318.00 ft2)
Aerodynamic mean chord ... ........................ 4.34 m (14.24 ft.)
Geometric mean chord...... ........................ 3.76 m (12.34 ft.)
Span ..................... ........................ 34.1 m (111.88 ft.)
Aspect ratio ............. ........................ 9.10
Taper ratio (tip chord/root chord)................. 0.24
Root chord................ ........................ 6.26 m (20.54 ft.)
Kink chord................ ........................ 3.94 m (12.93 ft.)
Tip chord................. ........................ 1.50 m (4.92 ft.)
Sweep angle (25%)......... ........................ 24 deg. 58 min.
Relative thickness:
Dihedral of wing reference plane................... 5.11 degrees
Dihedral of trailing edge inboard of kink.......... 8.65 degrees
Dihedral of trailing edge outboard of kink ........ 5.35 degrees
Wing reference area ...... ........................ 122.40 m2 (1318.00 ft2)
Aerodynamic mean chord ... ........................ 4.19 m (13.75 ft.)
Geometric mean chord...... ........................ 3.62 m (11.88 ft.)
Span ..................... ........................ 33.91 m (111.26 ft.)
Aspect ratio ............. ........................ 9.40
Taper ratio (tip chord/root chord)................. 0.25
Root chord................ ........................ 6.07 m (19.92 ft.)
Kink chord................ ........................ 3.76 m (12.34 ft.)
Tip chord................. ........................ 1.50 m (4.92 ft.)
Sweep angle (25%)......... ........................ 24 deg. 58 min.
Relative thickness:
- root ................... ........................ 15.15%
- kink ................... ........................ 11.75%
- tip .................... ........................ 10.84%
Dihedral of wing reference plane................... 5.11 degrees
Dihedral of trailing edge inboard of kink.......... 8.65 degrees
Dihedral of trailing edge outboard of kink ........ 5.35 degrees
Wing reference area ...... ........................ 126.0 m2 (1318.00 ft2)
Aerodynamic mean chord ... ........................ 4.34 m (14.24 ft.)
Geometric mean chord...... ........................ 3.76 m (12.34 ft.)
Span ..................... ........................ 34.1 m (111.88 ft.)
Aspect ratio ............. ........................ 9.10
Taper ratio (tip chord/root chord)................. 0.24
Root chord................ ........................ 6.26 m (20.54 ft.)
Kink chord................ ........................ 3.94 m (12.93 ft.)
Tip chord................. ........................ 1.50 m (4.92 ft.)
Sweep angle (25%)......... ........................ 24 deg. 58 min.
Relative thickness:
- root ................... ........................ 14.70%
- kink ................... ........................ 11.20%
- tip .................... ........................ 10.84%
Dihedral of wing reference plane................... 5.11 degrees
Dihedral of trailing edge inboard of kink.......... 8.65 degrees
Dihedral of trailing edge outboard of kink ........ 5.35 degrees
(1) Movable Control Surfaces for each Outer Wing
Leading edge:
Leading edge:
- Slats 1 thru 5
- Aileron
- Spoilers 1 thru 5
- Inboard and outboard flaps
(2) Control Surface Areas
Aileron ................ ................ ............. 1.37 m2 (14.75 ft2)
Spoiler 1 .............. ................ ............. 1.18 m2 (12.70 ft2)
Spoiler 2 .............. ................ ............. 1.17 m2 (12.60 ft2)
Spoiler 3 .............. ................ ............. 1.11 m2 (11.95 ft2)
Spoiler 4 .............. ................ ............. 1.02 m2 (11.98 ft2)
Spoiler 5 .............. ................ ............. 1.02 m2 (11.98 ft2)
Aileron ................ ................ ............. 1.37 m2 (14.75 ft2)
Spoiler 1 .............. ................ ............. 1.18 m2 (12.70 ft2)
Spoiler 2 .............. ................ ............. 1.17 m2 (12.60 ft2)
Spoiler 3 .............. ................ ............. 1.11 m2 (11.95 ft2)
Spoiler 4 .............. ................ ............. 1.02 m2 (11.98 ft2)
Spoiler 5 .............. ................ ............. 1.02 m2 (11.98 ft2)
NOTE: For surface movements of the Flight Controls (Ref. AMM D/O 27-00-00-00).
(3) High Lift Surface Areas
Slat 1 ................. ................ ............. 1.58 m2 (17.00 ft2)
Slat 2 ................. ................ ............. 1.41 m2 (15.18 ft2)
Slat 3 ................. ................ ............. 1.19 m2 (12.81 ft2)
Slat 4 ................. ................ ............. 1.12 m2 (12.06 ft2)
Slat 5 ................. ................ ............. 1.02 m2 (11.98 ft2)
Inboard Flap ........... ................ ............. 4.65 m2 (50.05 ft2)
Outboard Flap .......... ................ ............. 5.90 m2 (63.51 ft2)
Slat 1 ................. ................ ............. 1.58 m2 (17.00 ft2)
Slat 2 ................. ................ ............. 1.41 m2 (15.18 ft2)
Slat 3 ................. ................ ............. 1.19 m2 (12.81 ft2)
Slat 4 ................. ................ ............. 1.12 m2 (12.06 ft2)
Slat 5 ................. ................ ............. 1.02 m2 (11.98 ft2)
Inboard Flap ........... ................ ............. 4.65 m2 (50.05 ft2)
Outboard Flap .......... ................ ............. 5.90 m2 (63.51 ft2)
NOTE: For surface movements of the Flight Controls (Ref. AMM D/O 27-00-00-00).
(4) High Lift Surface Areas
Slat 1 ................. ................ ............. 1.58 m2 (17.00 ft2)
Slat 2 ................. ................ ............. 1.41 m2 (15.18 ft2)
Slat 3 ................. ................ ............. 1.19 m2 (12.81 ft2)
Slat 4 ................. ................ ............. 1.12 m2 (12.06 ft2)
Slat 5 ................. ................ ............. 1.02 m2 (11.98 ft2)
Inboard Flap ........... ................ ............. 4.36 m2 (46.91 ft2)
Outboard Flap .......... ................ ............. 4.85 m2 (52.19 ft2) Inboard Tab ............ ................ ............. 1.45 m2 (15.60 ft2)
Outboard Tab ........... ................ ............. 2.27 m2 (24.43 ft2)
Slat 1 ................. ................ ............. 1.58 m2 (17.00 ft2)
Slat 2 ................. ................ ............. 1.41 m2 (15.18 ft2)
Slat 3 ................. ................ ............. 1.19 m2 (12.81 ft2)
Slat 4 ................. ................ ............. 1.12 m2 (12.06 ft2)
Slat 5 ................. ................ ............. 1.02 m2 (11.98 ft2)
Inboard Flap ........... ................ ............. 4.36 m2 (46.91 ft2)
Outboard Flap .......... ................ ............. 4.85 m2 (52.19 ft2) Inboard Tab ............ ................ ............. 1.45 m2 (15.60 ft2)
Outboard Tab ........... ................ ............. 2.27 m2 (24.43 ft2)
NOTE: For surface movements of the Flight Controls (Ref. AMM D/O 27-00-00-00).
D. Materials
The outer-wing main-box structure and the slats are made of high-grade aluminium alloys.
The ailerons, flaps, spoilers and fairings are made of Carbon Fiber Reinforced Plastic (CFRP).
Titanium alloys and steel alloys are used where necessary.
The outer-wing main-box structure and the slats are made of high-grade aluminium alloys.
The ailerons, flaps, spoilers and fairings are made of Carbon Fiber Reinforced Plastic (CFRP).
Titanium alloys and steel alloys are used where necessary.
G. Outer Wing Tank Sealing
The illustration that follows shows the way that the fuel tanks are sealed, while the outer wing is being assembled.
The illustration that follows shows the way that the fuel tanks are sealed, while the outer wing is being assembled.