US Pat. No. 9,299,150

RECORDING THE LOCATION OF A POINT OF INTEREST ON AN OBJECT

Airbus Operations Limited...

1. A method of recording the location of a point of interest on an object, the method comprising:
capturing a digital image of an object manufactured according to a design specification and having a point of interest;
marking the position of the point of interest on the captured image;
accessing a three-dimensional virtual design model of the object;
aligning the image with the model;
calculating the location of the point of interest with respect to the model based upon the position of the point of interest
marked on the captured image using an algorithm; and

recording the calculated point of interest location.

US Pat. No. 9,426,921

MULTI-INTERFACE

AIRBUS OPERATIONS LIMITED...

1. A line replaceable unit (LRU) for an integrated modular avionics architecture, the LRU comprising at least one input/output
interface and a plurality of connectors disposed within the LRU, wherein each connector includes at least one pin and said
at least one pin of each connector is either unused or is connected to a single wire route bundle segregated from dissimilar
wire route bundles according to segregation rules, and any other pins of each said connector that has a connected pin are
precluded from connection to a wire route bundle dissimilar to said wire route bundle of the connected pin, and wherein hardware
of one input/output interface is electrically connected within the LRU to one or more pins of each of at least two of the
connectors.

US Pat. No. 9,126,674

BEAM

Airbus Operations Limited...

1. A beam comprising first and second flanges, the beam having a first region extending between the flanges and a second region
extending between the flanges, the first region including a fitting configured to receive an applied concentrated shear load,
and the second region being designed to support a predominantly bending load, wherein the first region comprises a fan-shaped
truss comprising a hub adjacent the first flange and a plurality of struts which extend substantially radially from the hub,
and wherein the hub is aligned in a vertical direction with the fitting and the second region comprises either a truss structure
which is substantially regular in the longitudinal beam direction or a shear web.

US Pat. No. 9,169,000

LEADING EDGE RIB ASSEMBLY

AIRBUS OPERATIONS LIMITED...

1. A leading edge rib assembly for an aircraft wing, the assembly comprising a rib; and a gear train comprising two or more
cogs which are mounted to the rib and coupled in series so as to transmit torque from a first one of the cogs at a first end
of the gear train to a second one of the cogs at a second end of the gear train, the sizes of the cogs in the gear train being
selected so that the first cog rotates at a higher rate than the second cog, and wherein at least one of the cogs is housed
within a recess of the rib.

US Pat. No. 9,199,727

WING TIP DEVICE

Airbus Operations Limited...

1. A wing tip device for fixing to the outboard end of a wing, the wing defining a wing plane, the wing tip device comprising:
an upper wing-like element projecting upwardly with respect to the wing plane and having a trailing edge; and
a lower wing-like element fixed with respect to the upper wing-like element and having a root chord and a trailing edge, the
lower wing-like element root chord intersecting with the upper wing-like element, and the lower wing-like element projecting
downwardly from the intersection,

wherein the upper wing-like element is larger than the lower wing-like element and the trailing edge the lower wing-like element
is adjacent the trailing edge of the upper wing-like element at the intersection,

wherein an included angle between the upper and lower wing-like elements at the intersection is less than, or equal to, 160
degrees, and

wherein the lower wing-like element has an element planform area less than approximately 25% of the upper wing-like element
planform area.

US Pat. No. 9,169,004

SYSTEM FOR MOTORIZING A WHEEL CONNECTED TO A SUSPENSION

AIRBUS OPERATIONS LIMITED...

1. A motorizing system for powering a wheel associated with a suspension of an aircraft so that the aircraft can be moved
around on ground, the motorizing system comprising:
a motor unit;
a drive member that is attachable to the wheel, the wheel having a tire; and
a clutch device that enables movement of the motor unit relative to the drive member,
wherein the motor unit is a sprung mass of a suspension strut of the aircraft,
wherein the drive member is an unsprung mass of the suspension strut,
wherein the clutch device moves the motor unit to and from an engaged position, in which an output gear of the motor unit
is connected to the drive member, and a disengaged position, in which the output gear is separated from the drive member,
and

wherein a positive transmission occurs between the motor unit and the drive member.

US Pat. No. 9,193,445

WING TIP DEVICE

Airbus Operations Limited...

1. A wing tip device for fixing to the outboard end of a wing, the wing defining a wing plane, the wing tip device comprising:
an upper wing-like element projecting upwardly with respect to the wing plane and having a trailing edge; and
a lower wing-like element fixed with respect to the upper wing-like element and having a root chord and a trailing edge, the
lower wing-like element root chord intersecting with the upper wing-like element, and the lower wing-like element projecting
downwardly from the intersection,

wherein the upper wing-like element includes a substantially planar portion and an arcuate transition portion adapted to smoothly
blend the outboard end of the wing into the substantially planar portion, the transition portion having a lower surface, the
lower surface curving upwards such that the transition portion extends above the wing plane,

wherein the upper wing-like element is larger than the lower wing-like element and the trailing edge of the lower wing-like
element is adjacent the trailing edge of the upper wing-like element at the intersection,

wherein an included angle between the upper and lower wing-like elements at the intersection is less than, or equal to, 160
degrees,

wherein the intersection between the lower wing-like element and the upper wing-like element is on the lower surface of the
transition portion, outboard of the outboard end of the wing, such that the intersection is located above the wing plane,
and

wherein the wing tip device is configured to offset at least some of the decrease in wing span resulting from aeroelastic
deformation during flight, such that aeroelastic deformation during flight causes rotation of the wing tip device about a
wing root such that a tip of the lower wing-like element extends further outboard in the spanwise direction than a tip of
the upper wing-like element.

US Pat. No. 9,227,722

FLAP SUPPORT

AIRBUS OPERATIONS LIMITED...

1. A flap support structure for an aircraft wing having a trailing edge flap, the flap support structure comprising: a flap
support beam including an aerodynamic fairing; and a drive unit including a universal support bracket having a bearing which
rotatably receives a drive shaft connected to a drive arm for moving the trailing edge flap, wherein the universal support
bracket also forms part of the flap support beam and directly supports the aerodynamic fairing.

US Pat. No. 9,424,687

METHOD, APPARATUS AND COMPUTER PROGRAM PRODUCT FOR MODELLING THE NON-LINEAR STRUCTURAL RESPONSE OF A COMPONENT

Airbus Operations Limited...

1. A computer-implemented method of modelling the non-linear structural response of a stiffened panel, the method comprising:
determining one or more intermediate boundary conditions for application to an intermediate mesh by extracting in-plane nodal
forces from a linear finite element analysis of a global mesh subject to one or more global boundary conditions, wherein the
one or more global boundary conditions are determined based on an out-of-plane load;

performing a linear finite element analysis of the intermediate mesh subject to the one or more intermediate boundary conditions;
determining one or more local boundary conditions for application to a local mesh, the one or more local boundary conditions
being determined on the basis of the linear finite element analysis of the intermediate mesh and the out-of-plane load; and

performing a non-linear finite element analysis of the local mesh subject to the one or more local boundary conditions;
wherein the global mesh is associated with a global domain representing a real-world structure comprising the stiffened panel,
the intermediate mesh is associated with an intermediate domain which is a sub-domain of the global domain, and the local
mesh is associated with a local domain which is a sub-domain of the intermediate domain.

US Pat. No. 9,096,304

METHOD OF COUPLING AEROFOIL SURFACE STRUCTURES AND AN AEROFOIL ASSEMBLY

AIRBUS OPERATIONS LIMITED...

1. A method of attaching first and second aerofoil sections to each other comprising the steps of:
(a) positioning one aerofoil section in an initial assembly orientation with respect to the other aerofoil section so that
hinge elements on each aerofoil section are in alignment with each other,

(b) inserting a hinge shaft through said aligned hinge elements to initially couple the aerofoil sections together whilst
the aerofoil sections are in their initial assembly orientation;

(c) rotating one aerofoil section relative to the other aerofoil section about a compound angle defined by the hinge shaft
into a second orientation in which the aerofoil sections are in their final, assembled orientation relative to each other.

US Pat. No. 9,285,045

AIRCRAFT FUEL TANK VENT PROTECTOR

Airbus Operations Limited...

1. An aircraft fuel tank vent having a first interface for fluid communication with an aircraft fuel tank interior, and a
second interface for fluid communication with an aircraft fuel tank exterior, the vent comprising:
a first flow path between the first interface and the second interface, wherein the first interface is in fluid communication
with an aircraft fuel tank and the aircraft fuel tank vent includes a vent protector positioned in the first flow path, and,

a second flow path between the first interface and the second interface, the fuel tank vent having a valve positioned in the
second flow path,

wherein the first and second flow paths are common along at least a part of their length such that they are coincident at
the second interface.

US Pat. No. 9,096,308

WINGTIP FIN OF AN AIRCRAFT

AIRBUS OPERATIONS LIMITED...

1. A wingtip fin of an aircraft comprising an upstanding fin body, the fin body having an inboard face and an outboard face
and a recess defined within the fin body, a display screen assembly in the recess in the fin body, the display screen assembly
comprising a translucent face, substantially flush with and forming at least part of the inboard face or the outboard face
of the fin body, and a display screen arranged in the recess such that images displayed on the display screen are visible
through the translucent face.

US Pat. No. 9,090,333

SPLITTER PLATE FOR AIRCRAFT NOISE REDUCTION APPARATUS

Airbus Operations Limited...

1. An aircraft noise-reduction apparatus, the apparatus comprising:
an aircraft structural element of an aircraft landing gear, wherein the aircraft structural element forms a bluff body; and
a flow control device positioned downstream of the structural element and attached to a downstream side of the structural
element, wherein the flow control device is configured to reduce noise induced by unsteady flow downstream of the structural
element, wherein the flow control device is comprised of a pneumatic splitter plate.

US Pat. No. 9,085,030

HYBRID COMPONENT

AIRBUS OPERATIONS LIMITED...

1. A method of joining a hybrid component to another component, the hybrid component comprising at least two metallic parts,
the hybrid component being formed by a method comprising preparing a first metallic part by forming at least one macroscopic
interfacing feature on an interfacing surface of the part; positioning the first part in a mould tool; introducing a metallic
powder into the mould tool and around the interfacing feature(s); and consolidating the metallic powder by a Hot-Isostatic
Pressing (HIP) process to form a second metallic part which encapsulates the interfacing feature(s) to provide a mechanical
connection between the first and second parts of the component, the method of joining comprising forming an array of projections
extending from a second interfacing surface of the first part of the hybrid component; and embedding the projections in the
other component.

US Pat. No. 9,400,007

INJECTABLE NUT CAP

AIRBUS OPERATIONS LIMITED...

1. A cap for forming a sealed cavity around one end of a fastener, the cap comprising:
an inner cap member having an annular base terminating at an edge which surrounds an opening into an air cavity for enclosing
the one end of a fastener;

an outer cap member having an annular skirt or flange, the annular skirt or flange and annular base between them defining
an annular sealing cavity; and

a sealing material inlet comprising an opening in the outer cap member that is in fluid communication with the annular sealing
cavity, the opening being arranged to interconnect with a sealing material injection device to provide a flow of curable sealing
material from the sealing material inlet into the annular sealing cavity.

US Pat. No. 9,335,304

ULTRASONIC WHEEL SCANNER

AIRBUS OPERATIONS LIMITED...

1. An ultrasound scanner comprising:
an ultrasound array defining a scanning vector,
a coupling assembly having:
a first member mounted at a first end of the array for rotation about a first axis,
a second member mounted at a second, opposite end of the array for rotation about the first axis, and,
a flexible coupling component extending between the first and second members to form a closed volume around the array, the
coupling component having a workpiece contact surface intersected by the scanning vector,

wherein the drive mechanism comprises a drive shaft rotatable about a second axis parallel to and offset from the first axis
about which the first member and the second member are connected for synchronous rotation by a drive mechanism independent
of the flexible coupling component.

US Pat. No. 9,334,039

COMPOSITE LAMINATE STRUCTURE

AIRBUS OPERATIONS LIMITED...

1. A structure comprising a composite laminate having an edge; and an impact indicator which is carried by the edge and comprises
a resin which fractures upon impact, wherein the resin is un-reinforced, wherein the resin is configured to fracture and provide
permanent visible evidence of impact damage.

US Pat. No. 9,144,961

ORIENTATION OF INTERFACING PROJECTIONS

AIRBUS OPERATIONS LIMITED...

1. A method of joining a first component to a second component, the method comprising:
preparing the first component by forming an array of elongate projections on a bond surface of the component, each projection
having a centreline, a tip, and a base, wherein the centreline at the tip of each projection is oriented at an angle with
respect to the normal to the bond surface at its base, and wherein the angular orientation of the tip centerlines varies across
the array of projections;

bringing the first component and a plurality of hardenable flexible laminate ply layers together so as to embed the projections
in at least some of the hardenable flexible laminate ply layers; and

hardening the plurality of hardenable flexible laminate ply layers to form the second component after the array of projections
has been embedded into said at least some hardenable flexible laminate layers.

US Pat. No. 9,296,485

DISTRIBUTING GAS WITHIN AN AIRCRAFT

Airbus Operations Limited...

1. An aircraft comprising a Rubens' tube for distributing gas within the aircraft, wherein the Rubens' tube comprises a tube
with a plurality of outlets; an inlet for feeding the gas into the tube; and a loudspeaker arranged to set up a standing acoustic
wave within the tube.

US Pat. No. 9,090,341

AIRCRAFT LIGHTING DEVICE

AIRBUS OPERATIONS LIMITED...

1. A passenger aircraft winglet, comprising:
a wing tip attachment formation,
a first portion extending from the wing tip attachment formation and configured to extend in a substantially span wise direction
in use,

a blended curved section;
a second portion connected to the first portion via the blended curved section, the second portion extending to a free end
of the winglet and configured to extend at a non-zero angle relative to the first portion such that the second portion extends
substantially vertically in use and such that a surface of the second portion faces an aircraft fuselage in use,

a lighting device mounted with the first portion and arranged to project light onto the surface of the second portion such
that the surface is visible from the aircraft fuselage in use, and wherein the lighting device defines an external surface,
which external surface is flush with an external aerodynamic surface of the first portion.

US Pat. No. 9,085,350

AIRCRAFT WING COVER COMPRISING A SANDWICH PANEL AND METHODS TO MANUFACTURE AND DESIGN THE SAID WING COVER

Airbus Operations Limited...

1. An aircraft wing cover comprising an integrally stiffened sandwich panel including first and second skins sandwiching a
core layer, wherein at least one of the skins has a plurality of spanwise extending integral regions of increased thickness
accommodated by corresponding regions of decreased thickness in the core.

US Pat. No. 9,193,459

UNLOADING AND LOADING OF AIRCRAFT

Airbus Operations Limited...

1. An aircraft including a door opening for the conveying of passengers or cargo to or from the aircraft and an access platform,
said platform mounted on said aircraft for movement between stowed and deployed positions and comprising:
a first end;
a second end; and
a support surface extending between said first and second ends, wherein the door opening is proximate to an aircraft structure
that restricts access to the door opening, wherein the second end of said access platform, when in said deployed position
and viewed in plan, is non-parallel to said door opening.

US Pat. No. 9,162,417

METHOD OF MANUFACTURING A STRUCTURE

AIRBUS OPERATIONS LIMITED...

1. A structure comprising:
a panel assembly comprising a stack of thickness control plies of composite material bonded to a laminar composite panel,
the stack of thickness control plies having a first edge proximate an edge of the laminar composite panel, a second edge opposite
the first edge, a ramp where the thickness of the stack of thickness control plies decreases towards the first or second edge,
and an unramped section where the thickness of the stack of thickness control plies is substantially constant;

a first component attached to the panel assembly, the first component having a surface which engages the laminar composite
panel, a ramp which engages the ramp in the stack of thickness control plies, and an unramped surface which engages the unramped
section in the stack of thickness control plies; and

a further component attached to the laminar composite panel at or near its edge.

US Pat. No. 9,047,794

WINGTIP FIN OF AN AIRCRAFT

AIRBUS OPERATIONS LIMITED...

1. A wingtip fin of an aircraft comprising an upstanding fin body, the fin body having an inboard face and an outboard face,
a sign assembly in the fin body, the assembly comprising a translucent, graphic bearing face, substantially flush with and
forming at least part of the inboard face or the outboard face of the fin body, a recess in the fin body behind the graphic-bearing
face, and a light source arranged in the recess to illuminate the graphic-bearing face from inside the fin body.

US Pat. No. 9,334,041

AIRCRAFT GLAZING ATTACHMENT

AIRBUS OPERATIONS LIMITED...

1. An aircraft glazing apparatus comprising:
an aircraft glazing component defining a bore,
a bush located within the bore, the bush comprising a first part engaged with the aircraft glazing component to move with
the glazing component and a second part defining a fastener receiving formation,

in which, during use, the first part is movable together with the aircraft glazing component relative to the second part to
permit relative movement between the aircraft glazing component and the fastener receiving formation.

US Pat. No. 9,309,005

FASTENER ASSEMBLY

AIRBUS OPERATIONS LIMITED...

1. A fastener assembly for attaching a bracket to an inner surface of a skin of an aircraft wing, comprising a bolt having
a shaft and a bolt retaining member threadingly cooperating with the shaft to retain the bolt in a position in which it extends
through a hole in the skin of the aircraft wing, a collar freely locates over the bolt retaining member received on the shaft
to form an enclosed space around the bolt retaining member, the collar having a recess to contain plasma generated by out-gassing
due to electromagnetic energy tracking along a clearance gap present between the bolt and the skin of the aircraft wing through
which the bolt extends, wherein the collar has an aperture therein for the shaft to extend freely therethrough and an upper
mounting face to receive the bracket, and a collar and bracket retaining member threadingly cooperating with a portion of
the shaft protruding through the collar to attach the bracket and the collar to said inner surface of the skin of the aircraft
wing.

US Pat. No. 9,170,092

SYSTEM FOR DETECTING MISALIGNMENT OF AN AERO SURFACE

AIRBUS OPERATIONS LIMITED...

1. A system for detecting misalignment of an aero surface of a wing relative to other aero surfaces during simultaneous deployment
of said aero surfaces during flight, comprising multiple generators spaced from each other along the wing, wherein each generator
is configured to shine a beam of light through aligned apertures in a series of aero surfaces towards a respective reflector
during deployment of said aero surfaces, multiple receptors, wherein each receptor to detect reflection of said beam of light
from each reflector back through said apertures towards the respective generator and, a controller operable to terminate further
deployment of said aero surfaces in the event that no reflection is detected by at least one receptor or, if an actual time
taken for the reflected beam of light to be detected by at least one receptor differs from a predetermined time, and wherein
the wing has leading and trailing edges lying in a first plane and, an axis that extends in substantially at right angles
to said first plane, the apertures having an elongate shape extending in the direction of said axis.

US Pat. No. 9,102,393

SEAL ASSEMBLY FOR AN AIRCRAFT WING

AIRBUS OPERATIONS LIMITED...

1. A wing assembly for an aircraft comprising:
a wing spar,
a wing cover and
a structural component attached to the wing spar;
wherein the wing spar has a web and a flange connected by a radius corner, and the flange is attached to the wing cover such
that a gap is formed at an interface between the spar, the wing cover and the structural component;

the assembly further comprising a seal member which substantially covers the gap, and sealant provided between the seal member
and at least one of the structural component, the wing cover and the wing spar; the wing spar, the wing cover, and the structural
component each being in contact with at least one of the seal member and sealant so as to seal the gap.

US Pat. No. 9,077,167

AIRCRAFT RACEWAY MOUNTING AND CLAMPING APPARATUS

AIRBUS OPERATIONS LIMITED...

1. An aircraft raceway mounting apparatus comprising:
a foot defining an attachment formation at a first end for attachment of the apparatus to an aircraft structure,
a body defining a raceway receiving formation for receiving a raceway, the raceway receiving formation comprising a snap fit
formation for retention of a raceway,

wherein the body is attached to the foot at a second end by a snap fit arrangement such that the body is spaced from the aircraft
structure in use,

wherein the raceway receiving formation comprises a body having a U-shaped channel for receiving a raceway, and
wherein the U-shaped channel comprises a base, a first sidewall and a second sidewall, and the snap fit formation comprises
lugs projecting into the U-shaped channel from the sidewalls.

US Pat. No. 9,372,174

ULTRASONIC INSPECTION TOOL

AIRBUS OPERATIONS LIMITED...

1. An ultrasonic inspection probe for scanning a radiused workpiece comprising:
a flexible ultrasonic array probe having:
a probe body; and,
a flexible ultrasonic transducer array extending from the probe body, the flexible ultrasonic transducer array comprising
a series of ultrasonic elements extending towards a free end of the flexible ultrasonic transducer array;

a flexible coupling component arranged to ultrasonically couple the flexible ultrasonic transducer array to the workpiece,
the flexible coupling component having:

a first leg, a second leg, and a radiused section therebetween; and
a cavity defined therein
a workpiece coupling surface; and,
a loading surface opposite thereto, and,
a loading component arranged to apply a pressure to the loading surface to maintain contact between the workpiece coupling
surface and the workpiece in use;

wherein the flexible ultrasonic transducer array is positioned at least partially within the cavity defined within the flexible
coupling components such that the ultrasonic elements extend around the radiused section of the flexible coupling component
to scan the radiused portion of the workpiece.

US Pat. No. 9,348,335

LANDING GEAR FORCE AND MOMENT DISTRIBUTOR

Airbus Operations Limited...

1. A landing gear force and moment distributor system for an aircraft having a longitudinal axis aligned in a forward-aft
direction, a vertical axis perpendicular to the longitudinal axis, and a landing gear including a pair of main landing gears
arranged symmetrically about the longitudinal axis, each main landing gear having an actuator arranged to brake and/or drive
one or more wheels of the main landing gear, the force distribution system comprising:
a distribution module arranged to:
receive an input demand including a longitudinal force input demand corresponding to a desired braking or driving force along
the longitudinal axis for the landing gear and a moment input demand corresponding to a desired moment about the vertical
axis for the landing gear; and

to use the received input demand to calculate an output command comprising, for each main landing gear, a longitudinal force
output command corresponding to a braking or driving force along the longitudinal axis to be applied to said main landing
gear to achieve the longitudinal force input demand, and a moment output command corresponding to a braking or driving force
along the longitudinal axis to be applied to said main landing gear to achieve the moment input demand; and

an error-based feedback loop module arranged to:
calculate an error difference between the output command and the input demand;
use the calculated error difference to calculate a corrected longitudinal force demand and corrected moment demand; and
output the corrected longitudinal force input demand and corrected moment input demand to the distribution module to be received
as the longitudinal force input demand and moment input demand, respectively, of the input demand.

US Pat. No. 9,278,750

AIRCRAFT RIB ASSEMBLY

Airbus Operations Limited...

1. An aircraft aerodynamic structure assembly, said assembly comprising:
a spar member having an interior facing side and an exterior facing side, and a first unitary flange,
a first rib attached to and extending from the exterior facing side of the spar member, and
a first stiffener positioned on the interior facing side of the spar member and connected to the first rib through the spar
member, said first stiffener comprising a first panel surface at least partially in abutment with said interior facing side
of said spar member, and a second panel surface unitary with the first panel surface and extending from a first end of the
first panel surface, wherein the second panel surface abuts the first unitary flange,

wherein said first rib and said first stiffener are directly connected through said spar member via at least one mechanical
fastener passing through the spar member.

US Pat. No. 9,260,177

JOINT

AIRBUS OPERATIONS LIMITED...

16. A method of forming a joint comprising first and second abutting components, and an adjustable strap assembly bridging
the abutting components, the strap assembly including a first strap part attached to one of the components, and a second strap
part attached to the other component, the second strap having a generally wedge shaped cross-section and an extending flange
portion in cross-section through which the second strap part is attached to the other component, the first and second strap
parts having mating inclined faces for adjustment of the second strap part with respect to the first strap part such that
the position of the second strap part is adjustable with respect to the first strap part in the direction of the incline;
the method comprising the steps of:
a) attaching the first strap part to the first component,
b) providing the second strap part such that the inclined faces of the first and second strap parts are in mating engagement,
c) adjusting the second strap part with respect to the first strap part in the direction of the incline to position the second
strap part in a desired relationship with respect to the first strap part,

d) setting the relative position of the first and second strap parts in a desired position selected from a plurality of different
possible relative positions in which the first and second strap parts may be set in the finally assembled joint, and

e) attaching the second strap part to the second component once the first and second strap parts are in the desired position.

US Pat. No. 9,172,197

METHOD OF ASSEMBLING AN AIRCRAFT

AIRBUS OPERATIONS LIMITED...

1. A method of assembling an aircraft comprising the steps of:
providing an aircraft fuselage having a fuselage wall,
providing an electrical connector in the fuselage wall, the connector having a first connection terminal facing outwardly
from the fuselage,

providing a wing assembly comprising an electrical cable,
connecting the electrical cable to the connection terminal, and,
assembling the wing to the fuselage over the connection terminal.

US Pat. No. 9,162,751

APPARATUS FOR USE ON AN AIRCRAFT

AIRBUS OPERATIONS LIMITED...

1. Apparatus for use on an aircraft, the apparatus comprising:
a component;
an actuator arranged to move the component between a first position and a second position, net load from external forces acting
on the component tending to drive it towards the first position, wherein the actuator comprises:

a threaded screw;
a threaded nut;
a main prime mover coupled to said screw or said nut in order to impart relative linear motion between the screw and the nut;
an emergency prime mover coupled to said screw or said nut in order to impart relative linear motion between the screw and
the nut;

a normal control system configured to energise the main prime mover under normal operating conditions so that it applies torque
to the screw or nut acting in opposition to the net load; and

an emergency control system configured to energise the emergency prime mover under emergency operating conditions so that
it applies torque to the screw or nut acting in the same sense as the net load thereby driving the component to the first
position,

wherein the emergency control system is configured so that under the normal operating conditions the emergency prime mover
is not energized by the emergency control system to apply torque to the screw or nut.

US Pat. No. 9,347,918

ULTRASONIC ARRAY FOCUSSING APPARATUS AND METHOD

AIRBUS OPERATIONS LIMITED...

1. A method of scanning a curved engineering component comprising the steps of:
providing a probe having a curved ultrasonic array having a plurality of elements arranged in a curved path having a geometric
focal point,

providing a control system configured to fire the elements of the array according to a predetermined focal law,
providing a curved engineering component having a radius and centre of curvature, which centre of curvature is outside the
component,

aligning the geometric focal point of the array and the centre of curvature of the curved engineering component,
using the control system to activate the elements of the array according to a focal law to move a focal point of the array
away from the geometric focal point into the curved engineering component.

US Pat. No. 9,242,718

SEAL ASSEMBLY

AIRBUS OPERATIONS LIMITED...

1. A seal assembly for closing an aperture in an aerodynamic surface of a structure, the seal assembly comprising: a track
for attachment to the structure; and a retractable seal including a flexible substrate and a plurality of rods connected to
the flexible substrate, wherein at least one of the rods is mounted for running movement along the track, and the retractable
seal is moveable between an extended position and a retracted position by moving the at least one rod along the track accompanied
by folding/unfolding of the flexible substrate, wherein the retractable seal folds in a concertina style as the seal moves
from the extended position towards the retracted position, and wherein the retractable seal is biased to its extended position.

US Pat. No. 9,228,604

CAP FOR FORMING SEALED CAVITY AROUND FASTENER

AIRBUS OPERATIONS LIMITED...

1. A cap for forming a sealed cavity around one end of a fastener, the cap comprising an inner cap member with an annular
base terminating at an edge which surrounds an opening into a central cavity; an outer cap member which fits over the inner
cap member and has an annular base which forms an annular flange extending outwardly from the inner cap member at a point
which is set back from the edge of the annular base of the inner cap member so as to define a pocket between the flange and
the base; and a sealant material between the inner cap member and the outer cap member.

US Pat. No. 9,193,470

AIRCRAFT FUEL TANK ACCESS COVER AND AN AIRCRAFT FUEL TANK

AIRBUS OPERATIONS LIMITED...

1. An aircraft fuel tank access cover comprising a first door part, a second door part and a clamping arrangement to allow
the first and second door parts to be clamped together about an aperture in the skin of an aircraft, the periphery of the
first door part and the periphery of the second door part each being configured substantially to overlap the skin of the aircraft
so as to close the aperture, the clamping arrangement comprising a screw-threaded fastener which is arranged generally centrally
of the door parts and extends from one door part through the other door part to secure the door parts together and at least
one of the door parts having a reinforcing rib which spreads the clamping load exerted by the clamping arrangement from the
centre of the door part outwardly to adjacent the edge of the door part.

US Pat. No. 9,168,997

AIRCRAFT CONDUIT HARNESS RETENTION SYSTEM

AIRBUS OPERATIONS LIMITED...

1. An aircraft conduit harness retention system comprising:
a base having a flange attachment formation for attachment to an aircraft component at a first end and a first mating formation
at a second end;

a spacer having a second mating formation at a first end and a mating formation identical to the base first mating formation
and a second end;

a cap having a mating formation identical to the spacer first end; and
a conduit harness separate from the base and the spacer, wherein said conduit harness includes a wire loom receiving portion
and a flange connected to the wire loom receiving formation, the flange having a bore defined therethrough,

wherein the bore of the flange is engaged by at least one of the first mating formation and second mating formation and the
first mating formation and the second mating formation are engaged via a snap-fit to clamp the flange of the conduit harness
between the base and spacer or cap such that the conduit harness is offset from the aircraft component.

US Pat. No. 9,079,386

HEIGHT TAILORING OF INTERFACING PROJECTIONS

AIRBUS OPERATIONS LIMITED...

1. A method of joining a first component to a second component, the method comprising forming an array of projections extending
from a bond surface of the first component, the projections having a plurality of different profiles; and embedding the array
of projections in the second component formed of a plurality of laminate plies laid over the bond surface of the first component,
wherein each projection has a height, and each projection profile has a different height such that the projections penetrate
through differing numbers of laminate plies depending on their height.

US Pat. No. 9,455,557

ELECTRICAL CABLE PROTECTOR

AIRBUS OPERATIONS LIMITED...

1. A cable protector for connection to an aircraft electrical cable raceway and configured to be disposed adjacent a cable
raceway, the protector comprising a flexible, electrically conductive body defining a conduit through which an electrical
cable can pass and an electrically conductive connection arrangement electrically connected to the raceway to enable connection
of the body of the protector to the raceway in an electrically conductive manner.

US Pat. No. 9,346,223

APPARATUS FOR AND METHOD OF INHIBITING DELAMINATION

Airbus Operations Limited...

1. An aerodynamic component of an aircraft comprising:
an aerodynamic panel having a first surface forming a portion of an outer surface of the aircraft and a second surface opposite
to the first surface;

a laminated spar including a flange attached to the second surface;
a curved region of a laminated spar, wherein the curved region includes a first curved surface forming a first arc and a second
curved surface opposite to the first curved surface;

the laminated spar includes a first planar surface adjacent the first curved surface;
a first compression member abutting the first curved surface, wherein the first compression member includes a curved surface
covering and extending an entirety of the first arc of the first curved surface, and a side of the first compression member
opposite to the curved surface includes a first planar surface in a plane of the first planar surface of the laminated spar;

a second compression member abutting the second curved surface, and
a fastener passing through the first and second compression members and the curved region of the laminated spar, wherein the
fastener is under tension and urges the first compression member towards the second compression member thereby compressing
the curved region of the laminated spar.

US Pat. No. 9,248,901

AIRFRAME STRUCTURAL ELEMENT

Airbus Operations Limited...

1. An airframe structural element comprising:
an airframe structural part; and
a pipe connector element including a conduit for fluid communication through the airframe structural part, wherein the airframe
structural part and the pipe connector element form a unitary and one-piece component, are integrally formed prior to the
assembly of said airframe structural element into an airframe, and the conduit includes an inner conduit surface configured
to be wetted by a fluid and ends of the conduit which are configured to connect to ends of sections of a pipe.

US Pat. No. 9,481,447

AIRCRAFT WING WITH SLOTTED HIGH LIFT SYSTEM

Airbus Operations Limited...

1. An aircraft wing comprising:
a main wing element;
a moveable element, wherein the moveable element comprises at least one of:
a leading element in front of the main wing element; or
a trailing element behind the main wing element relative to
a direction of flight of the aircraft,
wherein a front element is a forward one of the main wing element and the moveable element in the direction of flight, and
a rear element is a rearward one of the main wing element and the moveable element;

an actuation system configured to move the moveable element between a retracted position and an extended position in which
there is an air gap between a lower surface of the front element and the rear element, wherein the air gap has a length in
the direction of flight and a width defined by a shortest dimension between the lower surface of the front element and a surface
of the rear element adjacent the air gap and overlapped by the lower surface of the front element, at each point along the
length of the air gap; and

two or more elongate stiffening ridges extending downwards from the lower surface of the front element, wherein the two or
more elongate stiffening ridges overlap the rear element while the actuated system is in the retracted position,

wherein each adjacent pair of stiffening ridges is separated by a channel, and the volume of at least one of the ridges is
less than the 50% of the volume of the channel adjacent the at least one of the ridges,

wherein the actuation system is configured to orient the moveable element so that in at least one intermediate position of
the actuation system the width of the air gap is constant or convergent along the length of the air gap and the width of the
air gap is at a minimum at an outlet of the air gap.

US Pat. No. 9,228,496

BLEED AIR DUCT JOINT INSULATION MEANS

AIRBUS OPERATIONS LIMITED...

1. A bleed air duct for use with an overheat detection system, said bleed air duct comprising:
an insulation jacket arranged to encapsulate a bleed air duct joint;
a vent for providing fluid communication between an interior and an exterior of said insulation jacket;
a valve located in said vent, said valve comprises a body section defining one or more conduits providing fluid communication
through said valve, a valve member and a biasing member disposed sequentially within said body section with respect to a flow
direction through said one or more conduits, said valve being arranged so as to enable fluid flow from said interior to said
exterior of said insulation jacket when fluid pressure in said interior exceeds a predetermined positive pressure threshold.

US Pat. No. 9,145,195

AIRCRAFT PANEL STRUCTURE AND AIRCRAFT PANEL STRUCTURE MANUFACTURING METHOD FOR ALLEVIATION OF STRESS

Airbus Operations Limited...

2. An aircraft panel assembly comprising:
a first aircraft panel constructed from a first sheet material having a first thermal expansion coefficient, the first aircraft
panel comprising a first face,

a second aircraft panel constructed from a second sheet material having a second thermal expansion coefficient different from
the first thermal expansion coefficient, the second aircraft panel comprising a second face facing the first face,

the first and second aircraft panels being joined at a first discrete fastening point by at least one fastener and at a second
discrete fastening point by another fastener,

the first and second discrete fastening points being connected by a first notional panel join line describing the shortest
distance between the at least one fastener and the another fastener along the first face, and a second notional panel join
line describing the shortest distance between the fasteners along the second face, wherein said first notional panel join
line is shorter than said second notional panel join line,

in which the first aircraft panel comprises a stress relief feature between the fastening points, wherein the stress relief
feature includes the second notional panel join line diverging from the first notional panel join line between the first and
second discrete fastening points and converges with the first notional panel join line at each of the first and second discrete
fastening points, and

in which said first aircraft panel comprises a structural component of an aircraft and said second aircraft panel comprises
an aircraft skin or a second structural component of the aircraft.

US Pat. No. 9,140,672

CALIBRATION BLOCK AND METHOD

AIRBUS OPERATIONS LIMITED...

1. Use of a calibration block for calibrating the signal sensitivity and/or gain of an angular scanning phased array ultrasonic
testing scanner arranged to generate a primary wave front at a plurality of contiguous beam angles across a scanning envelope,
the calibration block being formed of an acoustically transmissive material and comprising: first major surface having a peripheral
edge; a second major surface; a calibration surface disposed between general planes of the first and second major surfaces
and configured to extend in a generally circular arc so as to be generally equidistant from a central axis, the peripheral
edge of the first surface being spaced further from the central axis than the calibration surface; and an input surface for
acoustically coupling to an ultrasound transducer of the ultrasonic testing scanner and being arranged to position the transducer
such that the path length of the primary wave front from the transducer to the calibration surface is generally equal for
each beam angle across the scanning envelope.

US Pat. No. 9,052,035

SHAFT LOCKING DEVICE

Airbus Operations Limited...

1. A shaft locking device, comprising a locking element configured to be mounted on a shaft in a first position so that the
locking element is free to rotate with the shaft, wherein the locking element is configured to be mounted on the shaft in
a second position so that the locking element is locatable against a stop to prevent rotation of the shaft, wherein the locking
element comprising a locking portion configured to locate against said stop to prevent rotation of the shaft, wherein the
radial distance from the rotational axis of the shaft and the locking portion when the locking element is configured to be
mounted on the shaft in its first position is less than the radial distance from the rotational axis of the shaft and the
locking portion when the locking element is configured to be mounted on the shaft in its second position.

US Pat. No. 9,289,706

FILTER FOR A PIPE

AIRBUS OPERATIONS LIMITED...

1. A filter for a pipe, the filter comprising:
an attachment portion for attaching to the pipe, and
a filter surface for presentation to and filtering of an oncoming flow of the pipe,wherein the filter surface has at least one pointed apex for protruding into the oncoming flow, wherein the filter surface
is in the form of a pyramidal shape with a number of substantially triangular faces, and wherein at least one of the faces
of the filter surface is open to allow the oncoming flow to pass through that face of the filter surface and wherein at least
one of the faces is substantially solid, thereby deflecting debris from the filter surface.

US Pat. No. 9,211,957

AIRCRAFT FUEL TANK VENTILATION

AIRBUS OPERATIONS LIMITED...

1. An aircraft fuel tank ventilation system, comprising a refrigerative dehumidifying device having a refrigerating element
in contact with air flowing between a vent open to ambient atmosphere and a fuel tank, the refrigerating element is coupled
in a refrigeration cycle, the refrigeration cycle for cooling the refrigerating element.

US Pat. No. 9,193,447

LANDING GEAR WITH NOISE REDUCTION APPARATUS

Airbus Operations Limited...

1. An aircraft landing gear assembly comprising:
a landing gear arranged to be moveable between a stowed position and a deployed position, wherein the landing gear assembly
includes landing gear structure carrying aircraft landing loads, said structure including at least one void having a volume,
and where the at least one void is defined at least in part by two walls in the structure, each wall having an edge defining
at least in part a rim of the at least one void; and

a removably mounted cover plate that substantially overlies and closes off the at least one void, wherein the removably mounted
cover plate extends to the two walls or over the edges of the two walls, and wherein the cover plate covers the void without
filling a majority of the volume of the at least one void.

US Pat. No. 9,164,050

THERMAL TEST APPARATUS AND METHOD

Airbus Operations Limited...

1. A method of conducting a thermal test on a specimen, comprising:
supporting a specimen,
providing a thermal shroud comprising a flexible insulating fabric forming an enclosure around at least a portion of the specimen,
an interior of said enclosure comprised of space between said specimen and said enclosure,

delivering a supply of temperature controlled air into the interior of said enclosure via an opening formed in the enclosure,
and

conducting a thermal test on the specimen.

US Pat. No. 9,139,286

HINGE ASSEMBLY FOR ROTATABLY MOUNTING A CONTROL SURFACE ON AN AIRCRAFT

AIRBUS OPERATIONS LIMITED...

1. An aileron assembly comprising an aileron body, a first spoileron configured to extend from a first surface of the aileron
body, a second spoileron configured to extend from a second surface of the aileron body, and a hinge assembly configured to
move the first and second spoilerons between a retracted position, in which the first and second spoilerons are disposed in
the aileron body, and a deployed position, in which the first and second spoilerons extend from the aileron body, the hinge
assembly comprising a support member on the aileron body, a first hinge member on the first spoileron, a second hinge member
on the second spoileron and an actuating shaft slidably mounted to the support member and configured to slide along a longitudinal
axis of the actuating shaft relative to the support member, wherein the first hinge member is engaged with the actuating shaft
so that the first hinge member is urged to rotate about the actuating shaft in one direction when the actuating shaft is urged
to slide along the longitudinal axis, and the second hinge member is engaged with the actuating shaft so that the second hinge
member is urged to rotate about the actuating shaft in an opposing direction to the first hinge member when the actuating
shaft is urged to slide along the longitudinal axis such that the first and second spoilerons are urged to rotate in opposing
directions about said longitudinal axis.

US Pat. No. 9,416,811

INJECTABLE NUT CAP

AIRBUS OPERATIONS LIMITED...

1. A method of forming a seal around an end of a fastener protruding from a structure, a cap comprising a cap body with a
cavity; a sealing material inlet comprising an opening in the cap body; three or more ridges protruding from the cap body
into the cavity; and three or more channels between the ridges, the method comprising:
installing the cap body over the end of the fastener so that it is enclosed within the cavity and contacted by the ridges;
injecting sealing material into the cavity via the sealing material inlet so that the sealing material flows along the channels,
fills the cavity, contacts the end of the fastener, and contacts the structure; and

curing the sealing material to form the seal;
wherein the cap body and the cavity terminate at an annular rim; the cap body is installed over the end of the fastener with
an annular gap between the annular rim and the structure; and the sealing material flows from the sealing material inlet to
the annular rim and out of the annular gap to form an annular bead in contact with the structure.

US Pat. No. 9,334,045

AERODYNAMIC STRUCTURE WITH NON-UNIFORMLY SPACED SHOCK BUMPS

Airbus Operations Limited...

1. An aerodynamic structure having a surface with air flowing over said surface in a streamwise direction, said structure
comprising a series of shock bumps extending from said surface, wherein the shock bumps are distributed across the structure
with a non-uniform spacing between adjacent bumps.

US Pat. No. 9,335,144

HOLE DEPTH MEASUREMENT DEVICE

AIRBUS OPERATIONS LIMITED...

1. A hand-held measuring device for measuring both the depth of a hole and the length of a fixing for such a hole, wherein
the measuring device comprises
an elongate portion terminating with a hook, the hook being arranged for engaging with a far end of a hole whilst the elongate
portion is located within the hole,

a first measurement scale from which the depth of the hole may be determined when the hook is engaged with the far end of
the hole,

a first formation arranged to engage with a corresponding formation on a fixing for such a hole, and
a second measurement scale from which the length of a fixing may be determined when the first formation is engaged with the
fixing,

wherein the origin of the second measurement scale being displaced from the origin of the first measurement scale in a direction
substantially parallel to the longitudinal axis of the device,

the first measurement scale, second measurement scale and hook are provided on a single unitary main body,
and wherein
the measuring device is made from plastic.

US Pat. No. 9,296,473

SLAT SUPPORT ASSEMBLY

AIRBUS OPERATIONS LIMITED...

1. A slat support assembly comprising a slat support arm which is movable to deploy a slat from a leading edge of an aircraft
wing about an axis of rotation of the arm and a slat mount on a slat which is coupled to one end of said slat support arm
by a joint, the joint comprising a bearing element, wherein the bearing element comprises a shaft having a longitudinal axis
parallel to said axis of rotation of the arm, and a bearing sleeve, the shaft being slidable in the bearing sleeve in a direction
along said longitudinal axis of the shaft together with the slat mount, thereby allowing the slat mount to slide in a direction
of the axis of rotation of the arm.

US Pat. No. 9,174,724

DEPLOYMENT MECHANISM

Airbus Operations Limited...

1. An aircraft wing comprising:
a wing body;
an auxiliary wing surface device,
linkages between the auxiliary wing surface device and the wing body, the linkages defining a travel path of the auxiliary
wing surface device in relation to the wing body and the linkages include a first linkage configured to react to lateral loads
applied by the auxiliary wing surface device and a second linkage configured to react to shear loads applied by the auxiliary
wing surface device, and

a deployment mechanism for deploying the auxiliary wing surface device from the wing body along the travel path, wherein the
deployment mechanism includes:

a first connector portion for connecting the deployment mechanism to the wing body,
a second connector portion for connecting the deployment mechanism to the auxiliary wing surface device, and
a telescopic rod assembly linking the first and second connector portions, wherein the telescopic rod assembly comprises an
inner rod and an outer rod, wherein the inner rod is extendable from inside of the outer rod to increase the length of the
telescopic rod assembly and thereby increase a distance between the first and second connector portions, wherein the increase
of the distance between the first and second connector portions increases a distance between the wing body and the auxiliary
wing surface device and causes the auxiliary wing surface device to deploy along the travel path.

US Pat. No. 9,168,702

COMPOSITE STRUCTURAL MEMBER

Airbus Operations Limited...

1. A method of manufacturing a composite longitudinal stringer having a run out region, the method comprising:
laying up a stack of fiber reinforced laminate plies, wherein at least one of the reinforced laminate plies is laid up as
discrete first and second ply portions, and fibers of the second ply portion have a different characteristic from fibers of
the first ply portion, and

wherein the second ply portion extends up to a longitudinal end of the stringer at the run out region and the first portion
is disposed inboard of the longitudinal end in the stringer longitudinal direction, such that the stringer has a lower axial
stiffness at the run out region compared with the remainder of the stringer due to the different characteristic of the fibers
of the second ply portion.

US Pat. No. 9,371,127

COMPOSITE STRUCTURE COMPRISING A STRINGER WITH A PAD EMBEDDED IN THE RECESS OF A PANEL AND METHOD OF TRANSMITTING FORCES

Airbus Operations Limited...

1. A composite structure comprising:
a panel; and
a stringer bonded to a surface of the panel, the stringer having an end surface and a pair of sides extending lengthwise along
the stringer away from the end surface, wherein the surface of the panel is formed with a first wall which abuts the end surface
of the stringer and a second wall opposite to said first wall, said second wall abuts another part of the stringer.

US Pat. No. 9,347,597

AIRCRAFT TOOL

Airbus Operations Limited...

1. A guidance tool for restricting the potential angular misalignment between the axial centerlines of a pipe end and corresponding
socket arrangement during a pipe installation process, the guidance tool comprising:
a sleeve assembly including sleeve segments, wherein each sleeve segment has side edges, is arc shaped in cross section and
has a radially outwardly extending ridge perpendicular to the axial centerline, and wherein the sleeve segments are configured
to be arranged on pipe end such that the side edge of one of the sleeve segment is adjacent the side edge of another one of
the sleeve segments; and

a clamp including a radially inwardly facing clamping surface configured to extend circumferentially around the sleeve assembly
while arranged on the pipe end, the clamping surface including a circumferential groove configured to receive the ridges of
the sleeve segments, and the clamp is configured to removably engage the sleeve with an external surface of a pipe end, such
that at least part of the sleeve assembly and the pipe end may be inserted into a corresponding socket arrangement and wherein
the clamp is configured to allow removal of the sleeve assembly from engagement with the external surface of a pipe end, once
the pipe end has been inserted into a corresponding socket arrangement.

US Pat. No. 9,303,693

BUSH ASSEMBLY

AIRBUS OPERATIONS LIMITED...

1. A bush assembly comprising a component having a bore, a bush fitted in the bore and having a flange that extends radially
outwardly over a surface of the component surrounding the bore, and a seal assembly for forming a sealing arrangement between
the flange and the surface of the component, wherein the seal assembly includes a seal member, and a layer of sealant between
a first interface formed between the seal member and the flange, and a second interface formed between the seal member and
the surface of the component.

US Pat. No. 9,242,715

JOINT BETWEEN AIRCRAFT COMPONENTS

Airbus Operations Limited...

1. A joint between a pair of aircraft components comprising:
a first component;
a second component bonded to the first component over a bonded area, the bonded area terminating at an edge;
a non-bonded area between said first and second components located between the edge of the bonded area and an edge of the
second component, the components not being bonded over the non-bonded area and said non-bonded area not transferring substantial
shear forces between said components, wherein a shim layer confined to the non-bonded area is between the first and second
components and has a coefficient of friction with respect to the first or second components which is less than a coefficient
of friction between the first and second components in the bonded area; and

one or more fasteners passing through the non-bonded area and fastening the first component to the second component, wherein
each of the components is formed from a composite material, and the one or more fasteners passes through the first and second
components.

US Pat. No. 9,162,775

VENTING GAS FROM A TANK

Airbus Operations Limited...

1. A method of venting gas from a tank, wherein the method includes the steps of:
providing a tank vent assembly including:
a gas inlet for receiving gas from a vent outlet of a tank;
a gas outlet for discharging the gas received from a vent outlet of the tank;
a pressure valve connecting the gas inlet and gas outlet, wherein the pressure valve is connected to a control pressure input
and is controllable by control pressure supplied at the control pressure input, and

a coaxial pipeline connected to the gas outlet of the tank vent device, wherein the coaxial pipeline is configured to be connected
to a low pressure and control pressure supply;

connecting the tank vent assembly to a vent tank, and
venting gas from the vent tank through the gas inlet and gas outlet of the tank vent assembly.

US Pat. No. 9,469,190

AIRCRAFT FUEL TANK SYSTEM

AIRBUS OPERATIONS LIMITED...

1. A flame barrier device for use with the vent tank of an aircraft fuel tank system, the flame barrier device comprising:
a body comprising a first port and a second port and defining a conduit through the body arranged to provide fluid communication
between the first and second ports; and

a flame barrier disposed within the conduit and arranged to resist the passage of a flame front through the conduit; and the
conduit further including a valve apparatus,

wherein the body comprises a connector part arranged to substantially sealingly engage with an ullage vent of a vent tank
of an aircraft fuel tank system so that the vent tank is vented to atmosphere via the flame barrier device, and wherein the
valve apparatus is configured to open in response to the engagement of the connector part with the ullage vent of the vent
tank.

US Pat. No. 9,457,458

FASTENER REMOVAL

AIRBUS OPERATIONS LIMITED...

1. A method for removing a fastener from a component, the fastener comprising an end portion exposed from the component, the
end portion having a threaded section, the method comprising the following steps;
providing a cap with a threaded opening,
screwing the threaded opening of the cap onto the threaded section of the exposed end portion of the fastener, and
securing a percussive tool to the cap, such that repeated impacts from the percussive tool are directed onto the exposed end
portion of the fastener, wherein the percussive tool is secured to the cap by securing an impact member, which is secured
to the percussive tool, in a hollow section of the cap, such that the impact member is adjacent to the exposed end portion
of the fastener, and, whereby the impact member is rotatable inside the hollow section of the cap.

US Pat. No. 9,346,554

VENT FOR AN AIRCRAFT WING FUEL TANK

Airbus Operations Limited...

1. An aircraft wing having a fuel tank vent, the vent terminating at an opening in a wing surface, the fuel tank vent having
a liquid separation nozzle, the liquid separation nozzle extending from an inside surface of the fuel tank vent at a position
inward of the opening, and terminating substantially in line with the opening, a gap being defined between the nozzle and
the opening such that migration of fuel escaping from the vent from the liquid separation nozzle to the wing surface, is inhibited.

US Pat. No. 9,201,417

METHOD OF MANUFACTURING AN ELONGATE COMPONENT

Airbus Operations Limited...

1. A method of manufacturing an elongate component comprising:
providing a punching apparatus configured to apply a differential contact three point bending load to the elongate component
by advancing a punch by a punch travel dpunch at a punch location between two discrete supports by a punch distance,

calculating the punch travel dpunch based on a second moment of inertia Ixx of the elongate component at the punch location,
the location of the neutral axis Y of the elongate component at the punch location, and a desired plastic deformation dplastic
of the component at the punch location, wherein second moment of inertia Ixx, the neutral axis Y and the desired plastic deformation
dplastic are related as follows:


wherein Bi is calculated based on the following relationship:

where BBij are constants, delastic is an elastic punch limit of the elongate component.

US Pat. No. 9,157,541

VALVE APPARATUS

AIRBUS OPERATIONS LIMITED...

1. A valve apparatus comprising a water drain valve arranged to be attached to an outer wall of a fluid containing vessel,
the outer wall of the fluid containing vessel having a recess formed in a surface thereof providing a recessed surface, and
an aperture formed through the recessed surface, the water drain valve including a body arranged to be received in the aperture
and a non-circular flange of the body arranged to be received in the recess such that the non-circular configuration of the
flange in combination with the recess limits rotation between the water drain valve and the outer wall of the fluid containing
vessel, wherein the body has a conduit for providing an outlet from the fluid vessel, and wherein the valve apparatus includes
a cap having a circumferential sidewall including an inner surface, a closed end, an open end, a fluid volume space and a
fluid transfer aperture for fluid to enter the fluid volume space and the open end being configured to encapsulate a portion
of the valve body such that at least a portion of the fluid volume space forms a substantially fluid-tight passageway between
the fluid transfer aperture and the conduit, the substantially fluid-tight passageway being defined between the inner surface
of the cap and an outer surface of the valve body.

US Pat. No. 9,346,534

SUPPORT ASSEMBLY

AIRBUS OPERATIONS LIMITED...

1. An assembly to support a wing leading or trailing edge device during deployment and retraction of said wing leading or
trailing edge device from a wing of an aircraft, the assembly comprising a fixed support member attachable to the support
structure of an aircraft wing, an intermediate link arm having one end pivotally mounted to the support member for rotation
relative to the support member about a first axis and, a primary link arm having a first end attached to the opposite end
of the intermediate link arm such that the primary link arm and intermediate link arm are movable relative to each other,
a second end of the primary link arm being configured for attachment to a wing leading or trailing edge device, wherein said
first end of the primary link arm is attached to said opposite end of the intermediate link arm via a part-spherical bearing
element so that the part-spherical bearing element allows the primary link arm, together with a wing leading or trailing edge
attached to the second end of the primary link arm to move relative to the intermediate link arm in any direction during deployment
or retraction of said wing leading or trailing edge device from an aircraft wing about said part-spherical bearing element.

US Pat. No. 9,321,522

PLAIN JOURNAL BEARING

AIRBUS OPERATIONS LIMITED...

1. A plain journal bearing coupling a first component to a second component, the bearing comprising:
a pin which passes through the first component and the second component;
a clamping bush which surrounds the pin and has a cylindrical inner surface, a cylindrical outer surface, and an end face;
and

a clamping member which is mounted on the pin and provides a clamping force between the end face of the clamping bush and
the first component,

wherein the bearing has a primary slip path between the outer surface of the clamping bush and the second component, the primary
slip path having an initial coefficient of friction sufficiently low that, when the first and second component rotate relative
to each other, the second component and the clamping bush rotate relative to each other about the primary slip path and the
clamping bush remains in clamping engagement with the first component; and

wherein the pin has a cylindrical outer surface which provides a subsidiary slip path which is arranged to operate when the
coefficient of friction of the primary slip path has been sufficiently increased due to use that a friction force between
the clamping bush and the second component overcomes the clamping force, whereby when the first and second component rotate
relative to each other, the pin and the clamping bush rotate relative to each other about the subsidiary slip path.

US Pat. No. 9,261,489

TOOL AND METHOD FOR MANIPULATING A TRANSDUCER ASSEMBLY

AIRBUS OPERATIONS LIMITED...

1. An apparatus, comprising a transducer assembly and a tool for manipulating the transducer assembly, the transducer assembly
having an emission face from which, in use, an analysis signal is emitted, the tool comprising an elongate shaft coupled to
a transducer receiving portion, the transducer receiving portion being rotatably coupled to the transducer assembly, and a
guide member arranged to project beyond the emission face of the transducer assembly, wherein the emission face of the transducer
assembly has a concave outer profile, which conforms to an arcuate scanning surface of an aircraft component.

US Pat. No. 9,140,287

FASTENER ASSEMBLY

AIRBUS OPERATIONS LIMITED...

1. A fastener assembly for mounting a component to a bracket attached to an inner surface of a skin of an aircraft wing such
that the component is thermally and electrically isolated from the bracket, the component and bracket each having mounting
holes, wherein the fastener assembly comprises a fastening element having a shaft to extend through said holes, first and
second isolating members mountable on the shaft on either side of the bracket such that the bracket is sandwiched between
said first and second isolating members and, a retaining element threadingly engageable with the shaft protruding through
the second isolating member to clamp said first and second isolating members together against said bracket, wherein one of
said isolating members has a central portion that protrudes through said mounting hole in the bracket and the other isolating
member comprises a recess to receive said central portion.

US Pat. No. 9,102,102

COMPOSITE STRUCTURE

Airbus Operations Limited...

1. A structure comprising a plurality of plies of fiber reinforced composite material, each ply having a ply orientation defined
by a principal stiffness direction of the ply, the structure having a first region and a second region, each region comprising
N1 primary plies, N4 cross plies with a ply orientation substantially perpendicular to the primary plies, N2 positive-angled
bias plies with a ply orientation at a positive acute angle to the primary plies, and N3 negative-angled bias plies with a
ply orientation substantially perpendicular to the positive-angled bias plies;
wherein the ply orientation of the primary plies in each region is more closely aligned with a primary axis of the structure
than the cross plies or the bias plies;

wherein N1=N4 in the first region but not in the second region;
wherein N2=N3 in the second region but not in the first region; and
wherein N3/N2 decreases in successive steps across the first region.

US Pat. No. 9,506,565

METHOD OF SEALING A GAP

AIRBUS OPERATIONS LIMITED...

11. A method of sealing a gap between first and second aerodynamic surfaces, the method comprising providing a nozzle, two
or more rollers, an endless track which passes round the rollers, and a curing device; moving the nozzle, rollers and curing
device at the same time along the length of the gap; and as they move along the gap:
a. injecting a liquid sealant directly into the gap from the nozzle;
b. rotating the track around the rollers;
c. pressing the track onto the first and second surfaces so the sealant in the gap is constrained by the track to lie substantially
flush with the first and second surfaces; and

d. directing energy into the sealant with the curing device, the curing energy accelerating cure of the sealant;
wherein the sealing unit is moved along the length of the gap at a rate such that the sealant becomes sufficiently cured when
it is in contact with the track so that the track peels off from the sealant as it moves away from the first and second surfaces.

US Pat. No. 9,272,791

AIRCRAFT REFUEL SYSTEM PIPING

Airbus Operations Limited...

1. A pipe for an aircraft refuel system, the pipe comprising:
an outer section making up a pipe wall, the pipe wall having an outer pipe wall surface and an inner pipe wall surface,
a surface texture on the inner pipe wall surface, the surface texture comprising projections projecting inwards from the inner
pipe wall surface towards a center of the pipe, wherein the cross sectional shape of at least one of the projections varies—along
the length of the projection, and wherein the peak of at least one projection varies position transversely with respect to
the projection, along the length of the projection, such that the peak of the at least one projection undulates sideways along
the pipe.

US Pat. No. 9,254,908

FIXING MEANS

Airbus Operations Limited...

1. A fixing assembly to fix an equipment element to a substrate, said fixing assembly comprising:
a first part comprising a support collar configured to extend around and support an equipment element, flanges each extending
from an end of the support collar, and male clip parts extending from each of the flanges, wherein the male clip parts extend
from each flange from opposite sides of the flange; and

a second part comprising a securing device configured to secure the fixing assembly to a substrate and a female clip part,
wherein the female clip part includes a socket forming a receptacle having an open end and recesses to receive projections
on the male clip parts, wherein said collar fits around the support equipment element such that the flanges come together
and allow the male clip parts to be received by the recesses of the socket,

wherein each of the recesses receive the projection of one of the male clip parts from one of the flanges and the projection
of one of the male clip parts from the other one of the flanges while the male clip parts are received by the receptacle of
the socket.

US Pat. No. 9,354,099

AIRCRAFT FUEL LEVEL MEASUREMENT APPARATUS AND METHOD

AIRBUS OPERATIONS LIMITED...

1. A method of detecting boundaries within a stratified substance in an aircraft fuel tank comprising:
providing a capacitive fuel probe comprising a plurality of discrete capacitive sections,
immersing the capacitive fuel probe in a stratified substance in an aircraft fuel tank,
sequentially measuring a capacitance of each of the plurality of discrete capacitive sections at predetermined time intervals
to create a time-domain output signal,

providing a reference capacitor at a known position on the capacitive fuel probe, the reference capacitor having a capacitance
outside of an expected capacitive range of each element of the stratified substance, and,

detecting the reference capacitor by detecting the capacitance outside of the expected capacitive range of the stratified
substance,

detecting a change in the time-domain output signal,
calculating a location of a boundary along the fuel probe within the stratified substance based on a time of the change in
the time-domain output signal,

in which the location of the boundary is calculated by determining the time between the detection of the reference capacitor
and the detection of the change in the capacitance in the time-domain output signal.

US Pat. No. 9,260,178

PACKER ASSEMBLY

AIRBUS OPERATIONS LIMITED...

1. An aircraft wing assembly comprising:
a wing box having a lower cover and a rear spar disposed at an aft side of the wing box;
a cantilevered flap support rib which supports a moveable wing flap, the flap support rib being fixed to the rear spar;
a rib-to-cover attachment bracket having a substantially planar upper mounting surface for attachment to a substantially planar
lower surface of the flap support rib and a convex part-spherical upper mounting surface;

a packer having an upper surface for mounting against the lower cover of the wing box and a concave part-spherical lower surface
mating with and of substantially the same spherical radius as the part-spherical mounting surface of the attachment bracket;

at least one fastener extending through aligned holes in the attachment bracket and the packer and into the lower cover of
the wing box so as to non-moveably fix the wing box and the attachment bracket relative to one another; and

at least one fastener extending through aligned holes in the attachment bracket and the flap support rib;
wherein the mating part-spherical surfaces of the attachment bracket and the packer permit sliding adjustment between the
attachment bracket and the packer prior to fixing the attachment bracket and wing box to one another via the fasteners.

US Pat. No. 9,459,190

FUEL TANK CONTAMINANT PREDICTION

AIRBUS OPERATIONS LIMITED...

1. A method for predicting a quantity of a contaminant in a fuel tank at the end of a time period, the method comprising the
steps of:
determining a quantity of the contaminant in the fuel tank at the start of the time period;
determining at least one operating condition of the fuel tank during the time period which affects the quantity of the contaminant
in a known manner;

using information relating to the at least one operating condition of the fuel tank to generate a predicted quantity of the
contaminant accumulated in the fuel tank during the time period; and

calculating, based upon the quantity of the contaminant at the start of the time period and the predicted quantity of the
contaminant accumulated during the time period, a predicted quantity of the contaminant at a future point of time at the end
of a time period.

US Pat. No. 9,422,049

JOINT

Airbus Operations Limited...

1. A joint comprising first and second rib components, the first rib having an abutment surface and a plurality of lugs disposed
adjacent to the abutment surface; and the second rib having an abutment surface and a plurality of lugs disposed adjacent
to the abutment surface, wherein the abutment surfaces of the respective ribs are abutting and joined with a tension joint,
wherein the tension joint includes a tension bolt, and wherein the lugs are pinned to form a pinned lug joint by aligning
respective holes in the plurality of lugs such that the lugs of the first and second ribs are interleaved and have one or
more pins passing through the aligned lug holes, and wherein the tension bolt is transverse to the one or more pins.

US Pat. No. 9,097,621

TEST APPARATUS FOR PROVIDING AXIAL STRESSES IN A STRUCTURE

AIRBUS OPERATIONS LIMITED...

1. A test apparatus for providing axial stresses in a structure, the structure having a first surface on one side and a second
surface on an opposite side, wherein the test apparatus comprises:
a first set of formations for abutting the first surface of the structure at a first plurality of locations on the structure,
a second set of formations for abutting the second surface of the structure at a second plurality of locations on the structure,
the first and second plurality of locations defining different footprints, and

a force actuator for applying a force which urges at least one of the first and second set of formations towards the other
set, and

wherein each set of formations comprises at least three formations and wherein at least two formations in each set of formations
are aligned with a notional alignment line along the structure and at least one formation in each set of formations is out
of alignment along the structure with said notional alignment line,

such that when the force actuator applies the force which urges at least one of the first and second set of formations towards
the other set, loads are applied at different locations over each notional alignment line and at a further location out of
alignment with each notional alignment line, causing the structure to bend biaxially and thereby providing biaxial stresses
in the structure, wherein each set of formations comprises four formations and wherein the four formations comprise a first
pair of formations aligned along a first notional alignment line and a second pair of formations aligned along a second notional
alignment line, and wherein the first and second alignment lines are at an angle to each other, and wherein each formation
is arranged to provide a line of contact with the structure and wherein the line of contact of each formation is approximately
perpendicular to its notional alignment line.

US Pat. No. 9,845,148

AIRCRAFT LANDING GEAR LONGITUDINAL FORCE CONTROL

Airbus Operations Limited...

1. A landing gear force control system for an aircraft having a longitudinal axis and a plurality of landing gears having
one or more braking and/or driving wheels, the force control system is operative at landing gear level and comprises an error-based
force control module adapted to:
receive an input signal representative of a longitudinal force demand to be achieved by the force control system;
receive an input signal representative of an actual measure of all longitudinal force acting upon one or more landing gears;
calculate any error between the force demand signal and the actual force signal; and
output a longitudinal force command for the one or more landing gears so as to minimize any error between the demanded force
and the actual force.

US Pat. No. 9,424,391

INSTALLATION OPTIMISATION

AIRBUS OPERATIONS LIMITED...

1. A computer-implemented method for determining a set of possible configurations of a user-selected set of aircraft components
in an aircraft installation which satisfy a set of constraints, the method comprising:
receiving a set of physical properties associated with each of the plurality of aircraft components;
receiving the set of constraints relating to arranging the set of aircraft components, the set of constraints including at
least relative positioning constraints, component intersection constraints, fragment trajectory constraints, maximum size
constraints, and safety constraints;

determining a set of possible configurations of the set of aircraft components that satisfies the received set of constraints;
generating a single representation of at least one of the determined configurations of the set of aircraft components that
satisfies the received set of constraints;

displaying the single representation to a user; and
indicating, in the single representation, for at least one aircraft component in the set of aircraft components, corresponding
volumes within the aircraft installation into which the at least one aircraft component could be moved while satisfying the
received set of constraints.

US Pat. No. 9,809,302

DIFFERENTIAL BRAKING OF AIRCRAFT LANDING GEAR WHEELS

AIRBUS OPERATIONS LIMITED...

1. A method of braking left and right landing gear wheels on respective left and right sides of an aircraft, the method comprising:
receiving a desired left braking hydraulic pressure, braking torque, or angular deceleration (L) for the left wheel; receiving
a desired right braking hydraulic pressure, braking torque, or angular deceleration (R) for the right wheel; braking the left
wheel with a reduced left braking hydraulic pressure, braking torque, or angular deceleration (L?) which is less than the
desired left braking hydraulic pressure, braking torque, or angular deceleration (L); and braking the right wheel with a reduced
right braking hydraulic pressure, braking torque, or angular deceleration (R?) which is less than the desired respective right
braking hydraulic pressure, braking torque, or angular deceleration (R), wherein L??R?=L?R.

US Pat. No. 9,449,123

STRESSES INDUCED BY RANDOM LOADING

Airbus Operations Limited...

1. A computer-implemented method of modelling a root-mean-square stress in a structure induced by a random load applied to
the structure, the method comprising:
storing, in a non-transitory memory of an analysis engine, data representing an eigensolution of the structure in free vibration
in a first mode of vibration;

storing in the non-transitory memory, data representing a modal stress in the structure induced by the free vibration in the
first mode of vibration;

determining, by a processor of the analysis engine, a modal correction factor which characterizes a proportion of the random
load contributing to a response of the structure in the first mode of vibration, wherein the determination of the modal correction
factor includes the processor accessing the stored data representing the eigensolution of the structure in the first mode
of vibration and analyzing the data to determine the modal correction factor;

generating, by the processor, data representing a stress in the structure induced by a forced vibration in the first mode
of vibration, based on the data representing the modal stress in the structure induced by the free vibration in the first
mode of vibration;

generating, by the processor, data representing a root-mean-square stress in the structure induced by the random load by applying
the modal correction factor to the data representing the stress in the structure induced by the forced vibration in the first
mode of vibration;

applying the data representing the root-mean-square stress to determine a strength or fatigue endurance of the structure,
and

determining whether the structure is worthy for service based on the strength or fatigue endurance of the structure.

US Pat. No. 9,802,696

METHOD AND APPARATUS FOR CONTROL OF A STEERABLE LANDING GEAR

Airbus Operations Limited...

1. A slip-reduction control unit configured to be employed on an aircraft having a longitudinal axis and a steerable landing
gear including one or more steerable wheels, wherein the slip-reduction control unit is configured to (i) receive a steering
input signal from which a target steering command output is ascertained, and (ii) receive one or more additional input signals
concerning at least one of (a) the motion of the aircraft, (b) a steering angle, and (c) a parameter relating to the slip
sustained by the steerable landing gear, and
the slip-reduction control unit is configured so that, in dependence on the one or more additional input signals, a rate of
change of an angle of the one or more steerable wheels that would otherwise be commanded is reduced.

US Pat. No. 9,506,493

CAP FOR FORMING SEALED CAVITY AROUND FASTENER

AIRBUS OPERATIONS LIMITED...

1. A joint comprising:
a. a structure;
b. a fastener passing through the structure;
c. a cap comprising:
i. an inner body portion with an annular base terminating at an edge, the body portion forming an enclosure around an end
of the fastener, and

ii. an outer body portion with an annular flange which extends outwardly from the inner body portion and is set back from
the edge of the base so as to define a pocket between the flange and the base; and

d. a sealant in the pocket between the flange and the base, the sealant bonding the cap to the structure via a sealant/cap
interface with the cap and a sealant/structure interface with the structure,

wherein the surface area of the sealant/cap interface is greater than the surface area of the sealant/structure interface.

US Pat. No. 9,440,728

AIRCRAFT FUEL TANK SYSTEM

AIRBUS OPERATIONS LIMITED...

1. An aircraft fuel tank system comprising:
one or more aircraft fuel tanks for holding and supplying aircraft fuel to aircraft engines within said aircraft;
an aircraft vent tank comprising an inlet connected to said one or more fuel tanks and an ullage vent means in a lower surface
of said aircraft fuel tank, said aircraft vent tank being arranged to provide a predetermined maximum fuel capacity and having
a minimal ullage at said maximum fuel capacity;

a vent pipe having a first open end in fluid communication with said ullage vent means and a second open end positioned within
said minimal ullage of said aircraft vent tank, said vent pipe being arranged to provide a substantially direct nominally
vertical fluid flow path between said minimal ullage and said ullage vent means; and

flame barrier means arranged within said vent pipe so as to provide a barrier to ingress to said vent tank of a flame front
external to said vent tank and to enable egress of liquid fuel from said vent tank though said ullage vent means via said
vent pipe.

US Pat. No. 9,120,558

ELECTRICAL POWER TRANSMITTING TELESCOPIC STRUT

Airbus Operations Limited...

1. A method of electrically connecting a fixed aerofoil structure to a control surface moveable between a retracted and an
extended position with respect to the fixed aerofoil structure in an aircraft, the method comprising:
physically and electrically connecting a telescopic strut between the fixed aerofoil structure and the control surface; and
moving the control surface between its retracted and extended positions accompanied by corresponding telescoping of the telescopic
strut, wherein the telescopic strut includes one or more electrical connector assemblies, each having an electrically conductive
pad in sliding contact with an electrically conductive strip for maintaining the electrical connection during telescoping
of the strut.

US Pat. No. 9,061,755

AIRCRAFT WING ASSEMBLY

AIRBUS OPERATIONS LIMITED...

1. An aircraft wing assembly, comprising a wing having a fixed leading edge, a slat mounted upon a slat deployment mechanism
for moving the slat between a retracted position and an extended position with respect to the fixed leading edge, the fixed
leading edge having an aperture to accommodate the slat deployment mechanism, and a closing plate mounted off the slat deployment
mechanism for closing a gap between a lower trailing edge of the slat and a lower edge of the aperture when the slat is retracted,
wherein the closing plate includes a first portion and a second portion, and further comprising a hinge pivotally connecting
the first and the second portions.

US Pat. No. 9,600,944

AIRCRAFT AERODYNAMIC AUDIT SYSTEM FOR ENHANCED FUEL EFFICIENCY

Airbus SAS, Blagnac (FR)...

1. An aerodynamic audit system for performing an audit process of an aircraft using a computing device via a network, comprising:
an inspection module for inspecting at least a portion of the aircraft for locating and measuring any aerodynamic defects
present by generating an inspection list having a predetermined inspection path;

a display device that displays the inspection path and accepts a measurement of any located aerodynamic defect;
a fuel penalty estimation module that calculates an estimated fuel penalty of the aerodynamic defect based on the measurement
of the corresponding aerodynamic defect;

a defect correction analysis module that analyzes the aerodynamic defect based on a cost and benefit assessment;
a findings collection module that generates an audit report based on the inspection and analysis of the aerodynamic defect;
and

a database that stores data associated with the aerodynamic defect and the corresponding fuel penalty based on the cost and
benefit assessment.

US Pat. No. 9,509,129

BRACKET FOR ATTACHING AN ELECTRICAL CABLE TO A VEHICLE

Airbus Operations Limited...

14. A bracket for attaching a cable to a vehicle, the bracket comprising;
(i) a vehicle attachment portion for attaching the bracket to a bracket attachment surface of the vehicle, and
(ii) a cable abutment portion for securing the cable to the bracket, the cable abutment portion comprising;
a front surface against which the cable can be secured by a cable-tie forming a closed loop around the cable and cable abutment
portion, and

a non-planar rear surface at least partially defining a path of the closed loop of the cable-tie behind the cable abutment
portion, the path passing first and second regions on opposing sides of the non-planar rear surface and the non-planar rear
surface directly supports the cable-tie at a third region along the path of the closed loop between the first and second regions,
wherein the front of the cable abutment portion is offset in a direction parallel to the bracket attachment surface of the
vehicle, away from the vehicle attachment portion.

US Pat. No. 9,428,266

AIRCRAFT LANDING GEAR

AIRBUS OPERATIONS LIMITED...

1. An aircraft landing gear comprising:
an axle carrying at least one wheel, the wheel having a hub and a toothed ring gear mounted to the hub;
a drive transmission having at least one motor and a drive pinion for meshing with the toothed ring of the wheel; and
an actuator for lifting via pivoting the drive transmission into and out of driving engagement with the toothed ring.

US Pat. No. 9,469,397

LANDING GEAR DRIVE SYSTEMS

AIRBUS OPERATIONS LIMITED...

1. A drive system for rotating a wheel of an aircraft landing gear, the drive system including a motor operable to rotate
a first drive pinion via a first drive path, and a driven gear adapted to be fixed to the wheel, wherein the drive system
has a first configuration in which the first drive pinion is capable of meshing with the driven gear to permit the motor to
drive the driven gear via the first drive path, and wherein one of the first drive pinion and the driven gear comprises a
first sprocket and the other of the first drive pinion and the driven gear comprises a series of rollers arranged to form
a ring, each roller being rotatable about a roller axis at a fixed distance from an axis of rotation of the first drive pinion
or driven gear, respectively.

US Pat. No. 9,810,601

AIRCRAFT STRUCTURE

AIRBUS OPERATIONS LIMITED...

1. An aircraft structure comprising:
an aircraft structural component having a first outer surface, and
a set of reinforcing straps for reinforcing the aircraft structural component, wherein the set comprises:
a first reinforcing strap having an inner and outer surface, wherein the inner surface is attached to the outer surface of
the aircraft structural component such that the first reinforcing strap extends longitudinally along the aircraft structural
component,

a second reinforcing strap having an inner and outer surface, wherein the inner surface is attached to the outer surface of
the first reinforcing strap and the inner surface does not contact the outer surface of the aircraft structural component
such that the second reinforcing strap extends longitudinally along the first reinforcing strap,

wherein over at least a portion of the length of the reinforcing straps, the second reinforcing strap has an average thickness
between the inner and outer surfaces of the second reinforcing strap that is larger than the average thickness of the first
reinforcing strap between the inner and outer surfaces of the first reinforcing strap,

wherein the thickness of the first reinforcing strap varies along its height,
wherein the aircraft structural component is a stringer, and
wherein the aircraft structure further comprises a rib extending across the stringer and wherein the rib is provided with
a hole for the stringer to pass through and wherein the reinforcing straps also pass through the hole.

US Pat. No. 10,029,779

WINGLET

AIRBUS OPERATIONS LIMITED...

1. A winglet, comprising:a tubular main spar with forward and aft main spar webs joined by upper and lower main spar caps;
a front spar with a front spar web, an upper front spar cap, and a lower front spar cap;
an upper skin joined to the upper main spar cap and the upper front spar cap; and a lower skin joined to the lower main spar cap and the lower front spar cap,
wherein the main spar has a tapered portion in which a height of the main spar reduces and a fore-and-aft width of the main spar increases as the tapered portion extends toward a tip of the main spar, and
wherein the front spar is C-shaped with the upper and lower front spar caps terminating at forward edges.

US Pat. No. 9,499,255

WING TIP DEVICE ATTACHMENT APPARATUS AND METHOD

Airbus Operations Limited...

1. A wing tip device for attachment to a wing tip of a powered aircraft, the wing tip device comprising:
a first mounting formation,
a second mounting formation spaced apart in a spanwise direction relative to the first mounting formation,
a third mounting formation spaced apart in a chordwise direction relative to the first and second mounting formations,
wherein each of the first, second and third mounting formations are configured for attachment to at least one of a wing spar
and a wing rib,

at least one of said mounting formations is configured to permit sliding movement of a portion of the wing tip device in the
spanwise direction relative to a portion of the wing tip, and the at least one of the mounting formations is a spigot for
insertion into an orifice of said wing tip rib.

US Pat. No. 9,809,319

AIRCRAFT FUEL SYSTEM

AIRBUS OPERATIONS LIMITED...

1. A method of operating an aircraft, comprising:
supplying fuel to a fuel storage facility of an aircraft fuel system of the aircraft,
transferring at least some ullage from the fuel storage facility, through a transfer arrangement, to a separate ullage storage
facility, based on a pressure input to the transfer arrangement,

storing at least some of the transferred ullage in the ullage storage facility, and
transferring at least some of the stored ullage from the ullage storage facility, through the transfer arrangement, to the
fuel storage facility, based on the pressure input to the transfer arrangement,

descending the aircraft to a reduced altitude level, thereby decreasing the pressure in the fuel storage facility relative
to atmospheric pressure, and, at the reduced altitude level, transferring at least some ullage from the ullage storage facility,
through the transfer arrangement, to the fuel storage facility, based on a pressure input to the transfer arrangement, and
in-taking atmospheric air from outside the aircraft into the fuel storage facility at a first altitude and then allowing transfer
of the at least some of the stored ullage from the ullage storage facility, through the transfer arrangement, to the fuel
storage facility at a second, lower altitude.

US Pat. No. 9,517,836

METHOD OF OPERATING AN AIRCRAFT FUEL MANAGEMENT SYSTEM

AIRBUS OPERATIONS LIMITED...

1. A method, comprising:
automatically managing fuel, in an aircraft including an automatic aircraft fuel management system, the aircraft having at
least one fuel tank, each fuel tank having an associated fuel quantity indicator arranged to provide an indication of the
amount of fuel in the associated fuel tank, the method including:

experiencing a failure of at least one of the fuel quantity indicators during a first temporal period such that at least one
of the fuel quantity indicators no longer works;

during the first temporal period, automatically calculating, by a processor, a value for the amount of fuel on board (FOB_FailedFQI)
the aircraft to be utilised by the fuel management system, the amount of fuel on board being calculated as a value for the
initial amount of fuel on board (FOBinit) minus the amount of fuel used; and

flying the aircraft in the air during the first temporal period while experiencing the failure of the at least one of the
fuel quantity indicators, wherein the action of flying the aircraft in the air occurs at least one of during or after the
action of automatically calculating, by a processor, the value for the amount of fuel on board the aircraft, wherein

the value for the initial amount of fuel on board (FOBinit) is determined at the time when all the aircraft engines are running
as the sum of an assigned value of fuel for each fuel tank having an associated failed fuel quantity indicator plus the sum
of fuel in each of the remaining fuel tanks provided by each associated fuel quantity indicator, wherein the assigned value
is manually entered.

US Pat. No. 9,463,870

AERODYNAMIC STRUCTURE WITH SERIES OF SHOCK BUMPS

Airbus Operations Limited...

1. A method of operating an aerodynamic structure comprising a leading edge, a trailing edge and series of 3-D shock bumps
extending from a surface of said structure, wherein the aerodynamic structure has a fifty percent chord line half way between
the leading edge and the trailing edge, the fifty percent chord line has a first angle of sweep, each of the 3-D shock bumps
have an apex positioned towards the trailing edge and aft of the fifty percent chord line, and the 3-D shock bumps are distributed
along a line with a mean angle of sweep which is less than the first angle of sweep of the fifty percent chord line, wherein
the method comprises:
flying the aerodynamic structure at a speed sufficient to form a shock on the wing, and
perturbing the shock at the surface with the series of 3-D shock bumps.

US Pat. No. 9,192,990

PREPARATION OF A COMPONENT FOR USE IN A JOINT

Airbus Operations Limited...

1. A method of joining a pair of components, the method comprising the steps of:
preparing a first component of said pair of components by growing an array of projections on a bond region of the first component,
wherein each projection is grown in a series of layers by an additive fabrication process, each of said layers is grown by
at least one of directing energy and material from a head to at least one selected part of the bond region;

joining the components by embedding the array of projections from said first component in the second of said components; and
hardening the second of said components after the array of projections has been embedded.

US Pat. No. 9,150,302

PINNED LUG JOINT

Airbus Operations Limited...

1. A pinned lug joint comprising:
a first part comprising two first lugs projecting from a lug bridge which extends between them;
a second part pivotally coupled to the first part, the second part comprising a second lug positioned between the two first
lugs; and

a sealing member, the sealing member being mounted to the two first lugs, and extending from the lug bridge to contact the
second lug to seal an air gap between the second lug and the lug bridge at least when the second part is in a first position,

the sealing member includes two mounting portions each mounted to a respective one of the two first lugs and a sealing member
bridge connecting the two mounting portions, wherein the mounting portions each include a web seated on an outer surface of
the respective one of the two first lugs and a flange extending from an edge of the web between the respective one of the
two first lugs and the second lug, and

the sealing member bridge includes a web extending between the two mounting portions and extending between the lug bridge
and second lug when the second part is in the first position.

US Pat. No. 9,783,280

DOUBLE-DECK AIRPLANE

Airbus Operations (SAS), ...

1. A double-deck airplane for transporting passengers and/or cargo comprising a fuselage, a upper deck, a lower deck, a movable
partition wall on the upper deck or the lower deck, a lifting structure, landing gears and a propulsion system, wherein:
floors of the upper and lower decks are planar surfaces extending continuously inside the fuselage in at least an inner space
of the fuselage configured for a payload, wherein the upper and lower decks each extends in a plane continuously from a front
section of the fuselage to an empennage section of the airplane;

the lower deck is located at a height from the ground, while the aircraft is on the ground, configured to carry out passenger
embarking/disembarking via equipment incorporated in the airplane without any external airport ground equipment;

passenger or cargo compartments are distributed on the upper and lower decks;
the lifting structure is disposed in the airplane in a manner that no component of the lifting structure crosses the upper
and lower decks;

the movable partition wall is configured to separate the passenger compartment from the cargo compartment, the movable partition
wall extends from the floor of the lower or upper deck to a ceiling of the lower or upper deck and extends transversely from
a left wall to a right wall of the fuselage, and the movable partition wall is movable along a longitudinal direction of the
fuselage; and

a distribution of the inner space allocated to the passengers and/or cargo compartments is changeable by locating the partition
wall at different positions along the longitudinal direction of the fuselage.

US Pat. No. 9,650,126

TELESCOPIC STRUT

AIRBUS OPERATIONS LIMITED...

1. A telescopic strut for electrically connecting a fixed structure of an aircraft to a movable structure mounted to the fixed
structure, wherein the strut is adapted to be mechanically connected to the fixed structure by its one end and to be mechanically
connected to the movable structure by its opposite end, the strut comprising a plurality of telescopic elements and containing
a helically coiled electrical cable, wherein the cable is adapted to move between retracted and extended positions with the
telescoping of the strut.

US Pat. No. 9,599,143

LOCKING APPARATUS FOR NUT

Airbus Operations Limited...

1. A locking apparatus for a nut comprising:
an annular tab washer and an arcuate tab plate, wherein the annular tab washer is configured to engage one side face of the
nut,

the annular tab washer includes a first radially inner tab configured for engagement with an element adjacent the nut and
a radially outer tab configured for engagement with the radially outer circumference of the nut, and

the arcuate tab plate includes a planar face configured for engagement with the other side face of the nut, a second radially
inner tab configured for engagement with the element, and an arcuate slot in the planar face configured to facilitate fixing
of the tab plate to the nut.

US Pat. No. 9,517,832

AIRCRAFT WING WITH WING TIP DEVICE

Airbus Operations Limited...

1. An aircraft wing assembly, comprising:
a wing having a wing box structure including an upper wing cover and a lower wing cover;
a wing tip device attached to the outboard end of the wing, wherein the wing tip device includes an upper cover and a lower
cover;

a gap of at least 5 mm between opposing edges of the lower cover of the wing tip device and the lower wing cover;
a seal assembly configured to aerodynamically seal the gap, wherein the seal assembly includes a bridging component on an
interior side of the gap and a seal, wherein the seal fills the gap and is supported by the bridging component;

wherein the bridging component has a generally T-shaped profile and includes an upright flange abutting the edge of the wing
tip device lower cover, an outboard flange abutting the interior surface of the wing tip device lower cover, and an inboard
flange extending to contact the interior surface of the lower wing cover.

US Pat. No. 9,487,287

WING LEADING EDGE VENTING

Airbus Operations Limited...

1. A wing comprising:
an airfoil section including a leading edge, a trailing edge, an upper surface and a lower surface,
wherein a region within the airfoil section immediately adjacent the leading edge is ventilated via one or more vent openings
which open in the upper surface to establish a sub-static pressure in the region during flight and the sub-static pressure
is immediately adjacent the leading edge, wherein the region within the airfoil section is bounded, in a chordwise direction,
by a front spar of the wing and a nose panel of the wing, and wherein the one or more vent openings are configured to discharge
a gas from within the airfoil section into a predominately turbulent air flowing over the vent openings in the upper surface
during flight, and

each of the one or more vent openings are disposed at one or more locations on the upper surface where airflow is predominantly
turbulent during flight.

US Pat. No. 9,487,082

AIRCRAFT FUEL TANK SYSTEM

AIRBUS OPERATIONS LIMITED...

1. An aircraft fuel tank system, comprising:
one or more aircraft fuel tanks holding and supplying aircraft fuel to aircraft engines within said aircraft;
an aircraft surge tank comprising an ullage vent and an inlet from the one or more aircraft fuel tanks;
a vent pipe arranged to provide fluid communication between the ullage of said aircraft surge tank and said ullage vent;
a flame barrier operable between a closed state in which said flame barrier is arranged as a barrier to flame fronts entering
said aircraft surge tank via said aircraft vent pipe and an open state in which said flame barrier is arranged so as to enable
fluid flow between said ullage and said ullage vent to bypass said flame barrier means;

a coupling mechanism sealingly externally coupling an external flame barrier to said ullage vent so as to provide fluid communication
between said aircraft vent pipe and atmosphere via the coupled external flame barrier; and

an actuator arranged to operate said flame barrier into said open state in response to the coupling of an external flame barrier
via said coupling, said actuator being further operable to operate said flame barrier into said closed state in response to
the decoupling of said external flame barrier from said coupling.

US Pat. No. 9,452,846

WATER SCAVENGING SYSTEM

Airbus Operations Limited...

1. A method of removing water from a fuel tank using a water scavenging line which has an inlet immersed in the water and
an outlet coupled to a water tank, the method comprising the steps of:
filling the fuel tank with fuel whereby the fuel exerts hydrostatic pressure on the water, the hydrostatic pressure driving
the water up the water scavenging line against the force of gravity and into the water tank; and

feeding water from the water tank through a water output line and into an engine.

US Pat. No. 9,387,935

AIRCRAFT POWER DISTRIBUTION NETWORK

AIRBUS OPERATIONS LIMITED...

1. An aircraft power distribution network comprising first and second galvanically isolated power bus bars, and first and
second remote data concentrators (RDCs), each RDC having an input/output interface (I/O) and a power supply, the power supply
of the first RDC being connected to the first galvanically isolated power bus bar, the power supply of the second RDC being
isolated from the power supply of the first RDC and being connected to the second galvanically isolated power bus bar, an
input/output device being connected to the I/O of the first RDC and to the I/O of the second RDC, each RDC being adapted to
supply electrical power to the input/output device through its respective I/O, wherein each RDC includes a switch for isolating
the input/output device, and the switches being operatively coupled such that electrical power cannot be supplied to the input/output
device by both RDCs simultaneously.

US Pat. No. 9,387,936

FUEL PRESSURE SENSOR LINE RESERVOIR

Airbus Operations Limited...

1. An aircraft fuel pump system comprising:
an aircraft fuel pump;
a pressure sensor connected to the aircraft fuel pump via a sensor line, wherein the sensor line includes a reservoir located
between the aircraft fuel pump and the pressure sensor and the sensor line is arranged to pass a fuel and water fluid mix
towards the pressure sensor when the aircraft fuel pump is in operation;

the reservoir comprising an input, a sump, and an outlet, wherein the input and the outlet are separate and distinct from
each other;

the sensor line comprising a wet sensor line between the aircraft fuel pump and the input to the reservoir and a dry sensor
line between the outlet from the reservoir and the pressure sensor; and

wherein the reservoir is configured such that there is no linear fluid path extending from the inlet to the outlet of the
reservoir, which is aligned with an axis of the inlet or an axis of the outlet, and

wherein the reservoir is configured such that the sump must be substantially full of the fuel and water fluid mix before the
fuel and water mix can pass through reservoir from the inlet to the outlet.

US Pat. No. 9,372,667

ONTOLOGY DRIVEN REQUIREMENTS ENGINEERING SYSTEM AND METHOD

AIRBUS OPERATIONS LIMITED...

1. A computer system comprising a processor and memory,
wherein the system is programmed to provide a first metamodel comprising a plurality of predefined fields relating to requirements
engineering wherein the predefined fields of the metamodel define the requirements and goals in a requirement engineering
process thereby providing a framework for the inputting of data,

and ontological relationships between at least some of the predefined data entry fields in the metamodel and to store one
or more further metamodels and the ontological relationships in the memory,

and to enable a user to enter information into one or more of the predefined fields of the first metamodel
and the computer system configured to identify one or more instances of a previously completed predefined field having the
same ontological relationship in a metamodel stored in the memory, and automatically entering the information in the predefined
field of the first metamodel in order to enable the automatic generation of one or more of: a requirements specification and
the steps for creating a requirements specification, wherein the automatically generated requirements specification or steps
for creating the requirements specification are based on the information entered into the predefined fields.

US Pat. No. 9,701,392

JOINT

Airbus Operations Limited...

1. A joint comprising:
first and second rib components,
the first rib component having an abutment surface and a plurality of lugs disposed adjacent to the abutment surface; and
the second rib component having an abutment surface and a plurality of lugs disposed adjacent to the abutment surface,
wherein the abutment surfaces of the respective first and second rib components are abutting and joined with a tension fitting
wherein at least a member of the tension fitting is under tension, and

wherein the lugs are pinned to form a pinned lug joint by aligning respective holes in the plurality of lugs such that the
lugs of the first and second rib components are interleaved and have one or more pins passing through the aligned lug holes.

US Pat. No. 9,599,141

CAP WITH CHANNELS FOR FORMING A SEALED CAVITY AROUND FASTENER

AIRBUS OPERATIONS LIMITED...

1. A cap for forming a sealed cavity around one end of a fastener, the cap comprising an inner cap member with a base terminating
at an edge which surrounds an opening into a central cavity; an outer cap member which fits over the inner cap member and
has a base; wherein either: the inner cap member has side walls with a uniform wall thickness around an entire circumference
of the inner cap member and a plurality of channels formed in an outer surface of the inner cap member and a plurality of
corresponding ridges formed in an inner surface of the inner cap member, the channels and the ridges extending longitudinally
along a substantial portion of the inner cap member; or the outer cap member has side walls with a substantially uniform wall
thickness and a plurality of channels formed in an inner surface of the outer cap member and a corresponding plurality of
ridges formed in an outer surface of the outer cap member, the channels and the ridges extending longitudinally along a substantial
portion of the outer cap member.

US Pat. No. 9,586,243

SELF-REGENERATING BIOCATALYTIC AND/OR ANTI-ICING SURFACES

AIRBUS OPERATIONS LIMITED...

1. A self-regenerating surface structure comprising at least one of molecules from the group consisting of biocatalytic molecules
and anti-icing molecules, said at least one of said molecules located on an exposed surface of said surface structure and
at least one of said molecules from said group are embedded or contained in said surface structure so as to form a self-regenerating
surface structure.

US Pat. No. 9,533,770

AIRCRAFT BONDING NETWORK

AIRBUS OPERATIONS LIMITED...

1. An aircraft assembly comprising a plurality of structural components and an electrically conductive bonding network, wherein
at least one of the structural components is formed of material of low electrical conductivity, and the bonding network includes
at least one substantially planar strip of highly electrically conductive material attached to at least the one structural
component, wherein a portion of the strip is formed as a substantially omega-shaped loop extending outwardly in a direction
away from a surface of the structural component, and wherein the strip has a first end and a second end opposite the first
end and the strip is attached to the structural component by at least one fastener at the first end and by at least one fastener
at the second end.

US Pat. No. 9,517,834

INTERFACE FOR CONTROL OF A FOLDABLE WING ON AN AIRCRAFT

AIRBUS OPERATIONS LIMITED...

1. An aircraft comprising a foldable wing, the wing comprising an inner region and an outer region, the outer region being
moveable relative to the inner region between:
a) a flight configuration for use during flight, and
b) a ground configuration for use during ground-based operations, in which ground configuration the outer region is moved
relative to the inner region such that the span of the wing is reduced,

wherein the aircraft further comprises a control system arranged to control movement of the outer region between the flight
configuration and the ground configuration, and a control interface for interfacing with the control system,

the control interface comprising a selector for selecting the desired configuration of the outer region, and the control interface
being arrange to provide:

a first output when the flight configuration is selected and the outer region is in the flight configuration;
a second output when the ground configuration is selected and the outer region is in the ground configuration; and
a third output when the outer region is not in the selected configuration.

US Pat. No. 9,487,081

AIRCRAFT FUEL TANK SYSTEM

AIRBUS OPERATIONS LIMITED...

1. An aircraft fuel tank system, comprising:
one or more aircraft fuel tanks holding and supplying aircraft fuel to aircraft engines within said aircraft;
an aircraft surge tank comprising a first ullage vent and an inlet from said one or more aircraft fuel tanks;
a vent pipe arranged to provide fluid communication between the ullage of said surge tank and said ullage vent;
a flame barrier arranged within said vent pipe arranged as a barrier to flame fronts entering said surge tank via said vent
pipe, said flame barrier dividing the interior space of said vent pipe into an exterior section between said flame barrier
means and said first ullage vent and an interior section between said flame barrier means and the interior of said surge tank;

a second ullage vent operable between a sealed state and an open state in which said second ullage vent is arranged to provide
fluid communication between said interior section of said vent pipe and atmosphere; and

a coupling mechanism sealingly coupling an external flame barrier to said second ullage vent so as to provide fluid communication
between said vent pipe and atmosphere via the coupled open structured external flame barrier, wherein said external flame
barrier is permanently open to fluid flow.

US Pat. No. 9,334,038

APPARATUS FOR ATTACHMENT OF WING PANELS

Airbus Operations Limited...

1. An aircraft fixed aerodynamic structure assembly comprising:
a fixed aerodynamic structure component;
a shroud panel;
attachment members interconnecting the shroud panel and the fixed aerodynamic structure component, each attachment member
connected to at least one of the shroud panel and the fixed aerodynamic structure component by an articulated joint;

where each of the articulated joints is a pivot joint rotatable about an axis normal to at least one of the shroud panel and
the fixed aerodynamic structure, and

a non-pivotable butt strap rotationally fixed to the at least one of the shroud panel and fixed aerodynamic structure component.

US Pat. No. 9,829,030

INJECTABLE CAP

AIRBUS OPERATIONS LIMITED...

1. A cap for forming a sealed cavity around one end of a fastener, the cap comprising:
an inner cap member having an annular base terminating at an edge which surrounds an opening into an air cavity for enclosing
the one end of a fastener;

an outer cap member having an annular skirt or flange, the annular skirt or flange and annular base between them defining
an annular sealing cavity; and

a sealing material inlet comprising an opening in the outer cap member that is in fluid communication with the annular sealing
cavity, the opening being arranged to interconnect with a sealing material injection device to provide a flow of curable sealing
material from the sealing material inlet into the annular sealing cavity,

wherein the outer cap member has an inner surface formed with a first locking feature, and the inner cap member has an outer
surface formed with a second locking feature which forms a snap-fit joint with the first locking feature.

US Pat. No. 9,599,241

CLACK VALVE ASSEMBLY

AIRBUS OPERATIONS LIMITED...

1. A clack valve assembly, comprising:
a. a valve base member having a base plate and a valve seat comprising an opening, wherein the base plate includes an attachment
surface;

b. a bearing comprising a recess with a base, a mouth, and a pair of side walls between the base and the mouth;
c. a lid comprising a lid plate and a shaft, the shaft being received in the recess of the bearing, wherein the shaft and
the lid plate are integrally formed elements of a single part; and

d. a shaft retaining member which is placed over the mouth of the recess to close the mouth of the recess in the bearing and
is attached to the attachment surface of said base plate of the valve base member, thus retaining the shaft within the recess,
wherein said shaft retaining member is disposed between said attachment surface of said base plate and said lid plate,

wherein the shaft can rotate within the recess to enable the lid to rotate from a closed position in which the lid engages
the valve seat and covers the opening, to an open position in which the lid lifts away from the valve seat enabling fluid
to flow through the opening in the valve seat, and wherein the shaft retaining member comprises a stop feature which engages
the lid when the lid opens beyond a stop angle to hinder the lid from opening beyond the stop angle.

US Pat. No. 9,581,252

FLUID FLOW CONTROL VALVE AND ACTUATOR

Airbus Operations Limited...

1. A valve assembly comprising:
a blind canister defining an insertion axis passing centrally through the internal volume and open end thereof;
a blind valve housing slidable into said canister on said axis and defining an open mouth and a circular chamber about said
axis;

a valve member insertable through said mouth and pivotable in said chamber;
an actuator insertable through said mouth for operational engagement with said valve member, and
a closure plate assembly configured as a barrier between the valve member and the actuator, the closure plate assembly comprising
closure plate, a bearing and a drive pin configured to engage the actuator and the valve member to provide the operational
engagement between the valve member and the actuator, wherein the drive pin is supported by the bearing to permit the drive
pin to pivot relative to the closure plate, and wherein the closure plate assembly provides a wet-dry interface between the
actuator and the valve member to permit disengagement of the actuator from the drive pin without leakage of fluid from the
valve housing chamber; and

said canister and housing define aligned inlet and outlet ports, and said valve member includes a through passage configured
to allow connection of said inlet and outlet ports in one orientation thereof, and configured to obstruct connection of said
inlet and outlet ports in another orientation thereof.

US Pat. No. 9,568,035

FASTENER JOINT WITH SEALING GASKET

AIRBUS OPERATIONS LIMITED...

5. A method of manufacturing a joint, the method comprising:
mounting a substantially disk-shaped gasket on a fastener; the fastener comprising a tapered head and a shaft protruding from
the tapered head, and the gasket comprising a fully or partially cured polysulphide sealing material which is in contact with
the head of the fastener, wherein the gasket further comprises a fabric impregnated with the sealing material, and a protrusion
which is positioned towards an inner periphery of the gasket and contains substantially none of the fabric;

inserting the shaft of the fastener through a first component and at least partially through a second component until the
sealing material of the gasket engages the first component;

compressing the gasket between the tapered head of the fastener and a tapered opening of the first component whereby the sealing
material in the protrusion flows along the shaft of the fastener and forms a collar between the shaft of the fastener and
the first component; and,

wherein the protrusion engages the tapered opening of the first component before the gasket is compressed between the tapered
head of the fastener and the first component.

US Pat. No. 9,567,093

TIME DOMAIN REFLECTOMETRY AIRCRAFT FUEL GAUGE

AIRBUS OPERATIONS LIMITED...

1. An aircraft fuel tank system comprising an aircraft fuel tank;
and a time domain reflectometry (TDR) fuel gauge installed in the aircraft fuel tank for measuring a filling level of fuel
in the aircraft fuel tank, the TDR fuel gauge comprising an electromagnetic signal generator and a cable, the cable comprising
a first cable part a second cable part and a third cable part which are coupled in series to the signal generator, wherein:

the first cable part extends downwardly within the fuel tank and the second cable part extends upwardly within the fuel tank;
the first and second cable parts are arranged such that for at least one filling level of the fuel in the fuel tank the first
cable part extends down into the fuel from an ullage space at a first location and the second cable part extends up out of
the fuel into an ullage space at a second location which is spaced apart from the first location; and

the fuel tank has two opposite side walls and an upper or lower wall extending between the side walls, and each of the first,
second and third cable parts of the cable runs substantially along the length of a respective one of the two opposite side
walls and the upper or lower wall.

US Pat. No. 9,567,094

AIRCRAFT INERTING SYSTEM

AIRBUS OPERATIONS LIMITED...

1. A method of controlling a flow rate of inerting gas introduced into an ullage, U, of a vented aircraft fuel tank, the method
comprising:
monitoring changes in a quantity of a fuel in the aircraft fuel tank;
monitoring changes in an ambient air pressure external to the aircraft fuel tank;
calculating a net volume flow rate, Q(UP), of ambient air into the fuel tank ullage, U, via its vent system due to changes in ambient air pressure, P; and

actively controlling the flow rate of inerting gas introduced into the aircraft fuel tank based upon changes in the quantity
of fuel in the fuel tank and the net volume flow rate, Q(UP) of ambient air into the fuel tank ullage, U, via its vent system due to changes in ambient air pressure, P.

US Pat. No. 9,555,782

AIRCRAFT ELECTRIC BRAKING SYSTEM

Airbus Operations Limited...

1. An electrically actuated braking system for an aircraft, comprising:
an electro-mechanical brake actuator (EMAbrake) proximate a wheel of the aircraft, the EMAbrake including a motor;
an electro-mechanical actuator controller (EMAC) including a motor controller for generating a drive signal for the EMAbrake;
a braking control unit (BCU) configured to generate a braking force command signal for the EMAC during a normal mode of operation;
and

an emergency braking control unit (eBCU) for generating a braking force command signal for the EMAC during an emergency operating
mode,

wherein the eBCU is disposed together with the EMAC in a common line replaceable unit (LRU).

US Pat. No. 9,512,940

MOUNT FOR CABLE HARNESS

Airbus Operations Limited...

1. A mount for mounting a cable harness to a support, said mount comprising:
a harness receiving portion;
a support attachment comprising a support receiving space between a base and a support locating element, the support attachment
configured to retain a support received in the support receiving space;

a fastener attachment portion; and
a fastener extending from said fastener attachment portion, said fastener securing the mount to said support, said fastener
attachment portion having an aperture configured to receive the fastener while the mount is secured to the support by the
fastener, wherein the mount is configured to orientate said fastener to extend about the harness receiving portion to secure
said cable harness to the mount when the mount is secured to said support by the fastener

wherein the support attachment is configured as a first mount securing device retaining the mount to said support while the
support is received in the support receiving space, and the fastener is configured as a second mount securing the mount to
said support.

US Pat. No. 9,409,328

MICROWAVE CURING OF COMPOSITE MATERIAL

Airbus Operations Limited...

1. A method of curing a composite material comprising:
heating a tool by applying microwaves to the tool;
shielding from the microwaves a composite material in an un-cured or partially cured state, wherein the shielding includes
positioning a microwave reflecting shield between the microwaves and the composite material while the microwaves are heating
the tool;

curing the composite material in a sealed chamber including a hole, wherein gases flow from the sealed chamber through the
hole and out of the chamber during the curing, and

transferring heat generated by the microwaves from the tool through the shield to the composite material while the composite
material is being cured.

US Pat. No. 9,358,707

DEVICE FOR LOCATING A FIRST AEROSPACE COMPONENT RELATIVE TO A SECOND AEROSPACE COMPONENT

Airbus Operations Limited...

1. An assembly comprising:
a first aerospace component including a first surface;
a second aerospace component slidably engaged with the first aerospace component and including a second surface opposite to
the first surface;

a bladder with a flexible membrane positioned between the first surface and the second surface, said membrane defines a fluid
receiving space, wherein the membrane has an unfilled state in which the membrane is separated from at least one of the first
and second surfaces and a filled state in which the membrane abuts both of the first and second surfaces; and

a hardenable hydraulic fluid injectable into the fluid receiving space of said bladder, wherein the membrane transitions from
the unfilled to the filled state upon injection of said fluid under pressure into said fluid receiving space, said membrane
in the filled state is in abutment with each of said first and second surfaces to thereby fixedly locate the first and second
aerospace components relative to each other, and said hydraulic fluid hardens after said membrane is placed in the filled
state.

US Pat. No. 9,308,982

COMPOSITE JOINT PROTECTION

Airbus Operations Limited...

1. A method of manufacturing an aircraft joint between a laminar composite cover and a second cover, the method comprising:
providing said laminar composite cover comprising a stack of layers, substantially all of the layers being shaped to form
a joggle, each joggle comprising

a first portion having a plurality of said layers,
a second portion having a plurality of said layers where the second portion layers extend substantially parallel with the
first portion layers, and

a ramp having a plurality of layers located between the first and second portions where the plurality of layers extend at
an angle to the first and second portions, the number of layers in said first and second portions are substantially the same
on both sides of the ramp;

partially overlapping said second cover with said composite cover;
holding the covers together where they overlap with a clamp or fastener;
substantially aligning external sides of the covers with each other so as to form a smooth aerodynamic surface;
pre-forming a protector with a tapered shape; and
attaching said pre-formed protector to one of the covers before the covers are overlapped, wherein said protector and said
external sides of said covers form a substantially continuous external aerodynamic surface.

US Pat. No. 9,102,398

DEPLOYMENT SYSTEM

Airbus Operations Limited...

1. A deployment system for deploying a deployable member relative to a base member, said deployment mechanism comprising:
a base member;
a deployable member for deployment relative to said base member;
a plurality of tracks fixed to said deployable member, supported by said base member and operable for parallel simultaneous
movement relative to said base member and along a deployment direction;

an actuator configured to drive said tracks so as to deploy said deployable member;
a sensor configured to detect a skew of at least one of said tracks, wherein said sensor is positioned adjacent the at least
one of said tracks, said sensor includes an element abutting the at least one of said tracks and the element is displaced
in a direction transverse to the deployment direction by skewing of the at least one of said tracks; and

a brake positioned adjacent the at least one of said tracks and connected to the element of the sensor, wherein the displacement
of the element moves the brake to slidably engage the at least one of said tracks in response to detection of said relative
skew by said sensor to brake said track so as to suppress the skewing of said tracks.

US Pat. No. 9,067,371

WRINKLE CONTROL METHOD AND TOOL THEREFOR

AIRBUS OPERATIONS LIMITED...

1. A method for forming a composite spar comprising:
a) providing an elongate tool having a moulding surface comprising an edge and a corner and a recess and/or protrusion wrinkle
control feature in the moulding surface extending from the edge and tapering toward the corner;

b) arranging a stack of ply layers on the moulding surface of the tool;
c) moulding the stack of ply layers over the moulding surface in a moulding process; and
d) curing the stack of ply layers to form a composite spar;
wherein the wrinkle control feature cooperates with the stack of ply layers during the moulding process to produce a local
surface undulation only in the surface of the stack of ply layers moulded against the moulding surface that either prevents
wrinkling in the ply layers or initiates wrinkling in one or more of the ply layers at a predetermined location.

US Pat. No. 10,086,929

AIRCRAFT AUTONOMOUS PUSHBACK

AIRBUS OPERATIONS LIMITED...

1. A method of controlling speed of an aircraft during backwards motion of the aircraft when in contact with the ground, the method comprising:applying a torque to at least one landing gear wheel of the aircraft, the torque is in a direction opposite to the backwards rolling direction of rotation of the landing gear wheel, wherein the step of applying torque to the landing gear wheel comprises applying a braking torque to the wheel using a friction brake assembly, the braking torque is effected by a braking control system, and the aircraft has N braking wheels and the braking control system sends a braking command to a number n of the braking wheels where n wherein the torque applied does not exceed a limit for ensuring aircraft longitudinal stability.

US Pat. No. 9,557,204

METERING APPARATUS FOR AND METHOD OF DETERMINING A CHARACTERISTIC OF A FLUID FLOWING THROUGH A PIPE

AIRBUS OPERATIONS LIMITED...

1. A metering apparatus for determining a characteristic of a fluid flowing through a non-linear section of a pipe, the metering
apparatus comprising:
a first strain gauge mountable to the non-linear section of the pipe offset from the bending neutral axis of the non-linear
section of the pipe, configured to detect a strain indicative of a bending force on the non-linear section of the pipe induced
by the inertia of the fluid flowing through the pipe,

a second strain gauge mountable to the pipe on the bending neutral axis of non-linear section of the pipe, configured to detect
at least one of the hoop strains, longitudinal strains and radial strains imparted on the pipe by the pressure of the fluid
flowing through the pipe,

a controller configured to determine the mass flow rate of fluid flowing through the pipe based on the bending force determined
by the first strain gauge and the at least one of the hoop strains, longitudinal strains and radial strains determined by
the second strain gauge.

US Pat. No. 9,506,587

CONNECTOR FOR AN AIRCRAFT FUEL PIPE

AIRBUS OPERATIONS LIMITED...

1. A pipe connector, comprising:
a first connector element comprising a generally cylindrical body member having a central axis and providing a connection
for a pipe at one end, said first connector element having a first female sub-element including a first opening and a second
opening defining a first passageway therebetween, and a concentric second female sub-element including a third opening and
a fourth opening defining a second passageway therebetween;

a terminal connector attached to said first female sub-element for connecting said first connector element to a terminal,
wherein said terminal connector includes a first port and a concentric second port;

a first seal seat recessed within an inner surface of said first female sub-element;
a second seal seat recessed within an inner surface of said concentric second female sub-element;
a first seal retained within said first seal seat;
a second seal retained within said second seal seat;
a second connector element comprising a generally cylindrical body member having a central axis and providing a connection
for a pipe at one end and connection to said first connector element at a second end,

said second connector element having first male sub-element and a concentric second male sub-element each having a bearing
surface being radially disposed and configured such that said second connector concentric male sub-element bearing surface
maintains sealing engagement with said second seal within a predetermined range of relative movement of the first and second
connector elements, and said second connector first male sub-element bearing surface maintains sealing engagement with said
first seal within said predetermined range of relative movement, wherein said predetermined range of relative movement comprises
relative movement longitudinally along said central axis, wherein said predetermined range of relative movement also comprises
relative rotation about said central axis and in planes parallel with said central axis, and wherein a first fluid flow path
exists within said first female sub-element through said first passageway, and a second separate fluid flow path exists within
said concentric second female sub-element through said second passageway.

US Pat. No. 9,481,115

MOULDING TOOL AND METHOD OF MANUFACTURING A PART

Airbus Operations Limited...

2. A method of manufacturing a wing box, the method comprising:
arranging a first set of components in a first set of recesses on an outer face of a first inner mold line tool, the first
inner mold line tool having an inner face;

arranging a second set of components in a second set of recesses on an outer face of a second inner mold line tool, the second
inner mold line tool having an inner face;

fitting at least one spacer between the inner mold line tools, with the spacer engaging inner faces of the inner mold line
tools so as to maintain a desired spacing between the inner mold line tools, wherein each of said at least one spacer has
an upper face and a lower face, said lower face opposite to said upper face, and each of said at least one spacer is fitted
with the upper face and the lower face engaging the inner faces of the inner mold line tools;

forming a layer around the inner mold line tools and forming a tubular part, said part having first and second open ends;
fitting outer mold line tools on opposite sides of the inner mold line tools;
molding the wing box by compressing the layer and the components between the inner and outer mold line tools;
removing the at least one spacer;
disengaging the inner mold line tools from the wing box after the at least one spacer have been removed; and
removing the inner mold line tools from the wing box through at least one of the open ends.

US Pat. No. 9,452,588

ADJUSTABLE SHIM

Airbus Operations Limited...

1. A method of filling a void between two structural components each component having at least a partial mating surface, said
void existing when said mating surfaces are joined together in a predetermined orientation, the method comprising:
attaching an adjustable shim to said mating surface of one of the components, wherein the adjustable shim comprises a stack
of plies comprising plastic material reinforced with a three-dimensional fibre layer, the plastic material flowable under
compressive force prior to cure for adjusting the thickness of the shim;

after attaching said shim, aligning the two components to said predetermined orientation to compress the shim and fill said
void between the two components; and

curing the shim with said components in said predetermined orientation.

US Pat. No. 9,425,600

AIRCRAFT ELECTRICAL CABLE RACEWAY

AIRBUS OPERATIONS LIMITED...

1. An aircraft electrical cable raceway comprising a body defining a plurality of separate cable pathways, the pathways being
formed, at least in part from a ceramic material, in which one of the cable pathways is formed at least in part from the ceramic
material and another of the cable pathways does not include the ceramic material in which the body of the raceway comprises
a metallic material frame and a U-shaped ceramic material liner, the ceramic material liner forming a layer corresponding
to a U-shaped channel of the metallic material frame.

US Pat. No. 9,409,651

AIRCRAFT AERIAL REFUELLING SYSTEM

Airbus Operations Limited...

1. An aircraft aerial refuelling system, comprising:
a plurality of aircraft fuel tanks,
at least one aerial refuelling dispense station,
a plurality of pressure controlled fuel pumps each having an outlet and a fuel pick-up,
each of said plurality of fuel tanks in fluid communication with at least one of said fuel pick-ups of said plurality of pressure
controlled fuel pumps, and each outlet including a pressure sensor configured to transmit an outlet fuel pressure signal,

a fuel pipe fluidically connecting the outlet of each of the plurality of pressure controlled fuel pumps to the at least one
aerial refuelling dispense station, and

a pump control system configured to:
receive a demand fuel pressure signal, and
compare the demand fuel pressure signal with the outlet fuel pressure signal.

US Pat. No. 10,112,703

DRIVE SYSTEM FOR LANDING GEAR AND DRIVE SYSTEM CONTROL METHOD

AIRBUS OPERATIONS LIMITED...

1. A drive system for an aircraft landing gear comprising:first and second gears for engagement to transfer a drive input to the system between the first and second gears;
an actuator for adjusting a distance between rotational axes of the first and second gears;
a sensor configured to detect at least one parameter indicative of a transmission error through the first and second gears; and
a controller configured to control the actuator to adjust a distance between respective rotational axes of the gears, in response to the detected parameter, when the first and second gears are engaged to minimise the transmission error.

US Pat. No. 10,093,413

DRIVE SYSTEM FOR AIRCRAFT LANDING GEAR

AIRBUS OPERATIONS LIMITED...

1. A drive system for rotating a wheel of an aircraft landing gear, the drive system including:a motor operable to rotate a drive pinion via a drive path; and
a driven gear adapted to be attached to the wheel so as to be capable of rotating the wheel,
wherein:
the drive system has a drive configuration in which the drive pinion is capable of meshing with the driven gear to permit the motor to drive the driven gear via the drive path;
the drive path comprises a first compensating gear and a second compensating gear which is meshed with the first compensating gear;
one of the drive pinion and the driven gear comprises a roller gear having a series of rollers arranged to form a ring, each roller being rotatable about a roller axis, and the other of the drive pinion and the driven gear comprises a sprocket; and
one of the first compensating gear and the second compensating gear comprises a roller gear having a series of rollers arranged to form a ring, each roller being rotatable about a roller axis, and the other of the first compensating gear and the second compensating gear comprises a sprocket.

US Pat. No. 9,884,677

WING TIP POD

Airbus Operations Limited...

1. A natural-laminar-flow swept transonic wing for an aircraft, said wing including an upper surface, a lower surface, a leading
edge, a trailing edge, an inboard root and an outboard tip, said wing including a wing tip pod, said pod including an elongate
body which tapers forwardly to a nose and tapers rearwardly to a tail, the nose is located forward of the wing tip leading
edge and the tail is located aft of the wing tip trailing edge, wherein the pod has a body with a convex outer surface facing
said inboard root from an intersection of the pod body and the wing tip upper surface, and the pod body has an edge profile
adjacent the wing upper surface extending in plan view in a continuously convex curve from nose to tail and, during flight
at a Mach number substantially close to a transonic design point of the wing, a region of natural-laminar-flow over the wing
upper surface extends aerodynamically forward of a generally spanwise shock and extends outboard substantially to the wing
tip pod where said spanwise shock does not substantially sweep forward toward the wing tip leading edge.

US Pat. No. 9,884,679

AIRCRAFT STEERING SYSTEM CONTROLLER

Airbus Operations Limited...

1. An aircraft steering system comprising:
a steerable nose-landing gear, and
controller configured:
to receive a steering input representative of a desired direction of travel of the steerable nose landing gear, and
to receive one or more force-based inputs representative of lateral forces acting upon the nose landing gear,
wherein the lateral forces are forces with a component in a lateral direction perpendicular to a longitudinal axis and a vertical
axis of the aircraft, and

wherein the controller is adapted to automatically adjust the steering input based upon the one or more force-based inputs
and output an adjusted steering command for a steering actuator of the nose landing gear.

US Pat. No. 9,862,478

MODULAR STRUCTURAL ASSEMBLY

Airbus Operations Limited...

1. A modular structural assembly to form part of an aircraft wing, the modular structural assembly having a plurality of upper
panels, each comprising an upper outer skin portion comprising an edge, the edges of adjacent upper outer skin portions being
attachable to each other, and a plurality of lower panels each comprising a lower outer skin portion comprising an edge, the
edges of adjacent lower outer skin portions being attachable to each other, wherein at least two adjacent upper panels each
comprise at least one stringer integrally formed with said upper outer skin portion as a single piece component, and at least
two adjacent lower panels comprise at least one stringer integrally formed with said lower outer skin portion as a single
piece component;
wherein each of the at least one stringer of each of the upper panels and each of the lower panels comprises a remote end
and extends from the upper or lower outer skin portions to the remote end; and

a cover plate is attached to the remote ends of at least two of the stringers on adjacent ones of the upper or lower panels,
such that an enclosed cell is formed by the cover plate, the at least two of the stringers, and the upper or lower outer skin
portions of the two adjacent upper or lower panels.

US Pat. No. 9,833,738

AIRCRAFT FUEL TANK INERTING SYSTEM

AIRBUS OPERATIONS LIMITED...

1. A method of generating oxygen depleted air on an aircraft comprising the steps of: taking air from a source, wherein the
air source is a ram air inlet, such that, in use, atmospheric air collected from the ram air inlet is supplied to both sides
of the air separation module;
passing a first proportion of the atmospheric air through an air pressure reduction device to produce a supply of reduced
pressure atmospheric air; passing a second proportion of the atmospheric air through a filter to produce a filtered atmospheric
air supply, the first proportion of atmospheric air bypassing the filter; passing the filtered atmospheric air along one side
of a membrane of an air separation module, so that a filtered air supply is passed along one side of the membrane of the air
separation module; exposing the other side of the membrane of the air separation module to the reduced pressure atmospheric
air, so that oxygen passes from the filtered atmospheric air on said one side of the membrane to the reduced pressure atmospheric
air on said other side of the membrane, exhausting the filtered atmospheric air from the air separation module as filtered
oxygen depleted atmospheric air; and

passing the filtered oxygen depleted atmospheric air exhausted from the air separation module to a fuel tank on the aircraft
for inerting the fuel tank.

US Pat. No. 9,745,048

MORPHING AEROFOIL

Airbus Operations Limited...

1. A morphing airfoil comprising:
a leading edge; a trailing edge; upper and lower surfaces extending between the leading and trailing edges;
an upper thermal actuation member proximate the upper surface; and
a lower thermal actuation member proximate the lower surface opposite the upper thermal actuation member,
wherein the upper and lower thermal actuation members have different thermal expansion coefficients and are positioned such
that they cause the trailing edge to deflect when the upper and lower thermal actuation members expand or contract by different
amounts in response to a change in ambient temperature caused by a change in altitude thereby changing a camber of the airfoil,

wherein the morphing airfoil does not include a heating system arranged to heat the upper and lower thermal actuation members
to cause the trailing edge to deflect.

US Pat. No. 9,745,049

SEAL ASSEMBLY

AIRBUS OPERATIONS LIMITED...

1. A seal assembly for closing an aperture in an aerodynamic surface of a structure, the seal assembly comprising: a track
for attachment to the structure; and a retractable seal including a flexible substrate and a plurality of rods connected to
the flexible substrate, wherein at least one of the rods is mounted for running movement along the track, the seal is moveable
between an extended position and a retracted position by moving the at least one rod along the track accompanied by folding/unfolding
of the flexible substrate, and wherein the seal is biased to its extended position, and wherein the seal is self-biasing to
the extended position.

US Pat. No. 9,764,518

COMPOSITE MANUFACTURING METHOD

Airbus Operations Limited...

1. A method of manufacturing a composite panel, the method comprising:
fitting a control member through the panel;
fitting a plug through a compaction tool;
compacting the panel with the compaction tool to form a compacted panel;
controlling thickness of said panel during compaction with the compaction tool by engaging the control member with the plug;
engaging the plug with a datum surface of the compaction tool;
disengaging the plug from the control member after the panel has been compacted without removing the control member from the
compacted panel; and

subsequently to the disengagement of the plug, removing the control member from the compacted panel by drilling through the
control member and an area of the compacted panel surrounding the control member to form a hole through the compacted panel.

US Pat. No. 9,616,989

BEARING BLOCK FOR A SLAT SUPPORT ASSEMBLY

AIRBUS OPERATIONS LIMITED...

1. A bearing block to support and guide movement of a slat support arm forming part of a slat support assembly in which the
slat support arm is movable to deploy a slat attached to one end of said slat support arm from a leading edge of an aircraft
wing, the bearing block comprising a plurality of bearings mountable therein so as to lie in rolling contact with an associated
bearing track on a slat support arm extending through the bearing block, wherein each bearing comprises a bearing element
rotatable about a shaft having an axis fixed to the bearing block, each bearing being configured so that an axis of rotation
of each bearing element angularly adjusts, relative to said axis of the shaft on which it is rotatably mounted, to compensate
for misalignment between said shaft and an associated bearing track.

US Pat. No. 9,611,027

RAMPED STIFFENER AND APPARATUS AND METHOD FOR FORMING THE SAME

AIRBUS OPERATIONS LIMITED...

1. A method of forming a T-shaped stiffener having an elongate web element and at least one elongate foot element, the web
element and foot element being connected by a curved elbow, the method comprising feeding a solid elongate member through
a roll forming die comprising first and second rollers, the first roller having a shaped section arranged to be located within
a correspondingly shaped recess in a circumferential surface of the second roller, the first and second rollers defining a
gap between them corresponding to a desired shape to be imparted on an elongate member passed between the rollers, the desired
shape including a curved elbow between a web and a foot portion, wherein:
the shape of the recess in the second roller and the shape of the corresponding section of the first roller vary around a
portion of the rollers circumference such that a radius of curvature of the gap between the rollers corresponding to the curved
elbow varies between a minimum and a maximum value; and

the method further comprises:
holding the first and second rollers stationary while feeding the solid elongate member between the first and second rollers
as a first portion of the solid elongate member is fed between the first and second rollers, whereby a radius of the curved
elbow formed in the stiffener is constant along that first portion, and then

rotating the first and second rollers between a first and a second position while feeding the solid elongate member between
the first and second rollers as a further portion of the solid elongate member is fed between the first and second rollers,
whereby a radius of the curved elbow formed in the stiffener is varied along that further portion, wherein the stiffener formed
is C-shaped which is transformed into T-shape by folding along a central axis of the C-shaped stiffener.

US Pat. No. 9,611,035

AIRCRAFT ELECTRIC BRAKING SYSTEM

Airbus Operations Limited...

1. An electrically actuated braking system for an aircraft, comprising:
an electro-mechanical brake actuator proximate a wheel of the aircraft, the electro-mechanical brake actuator including a
motor;

an electro-mechanical actuator controller (EMAC) including a first motor controller for generating a first drive signal for
the electro-mechanical brake actuator, and a second motor controller for generating a second drive signal for the electro-mechanical
brake actuator,

wherein the first motor controller and the second motor controller are dissimilar so as to provide protection against common
mode failure of the first and second motor controllers.

US Pat. No. 9,580,058

DETERMINING INTEGRITY OF BRAKING CONTROL SYSTEM

AIRBUS OPERATIONS LIMITED...

15. A controller configured to determine the integrity of a braking control system comprising an electric or hydraulic energy
source, the method comprising: charging or discharging the energy source; taking two or more measurements of voltage or hydraulic
pressure from the electric or hydraulic energy source; analysing at least two of the measurements in order to determine a
change or rate of change in voltage or hydraulic pressure caused by the charging or discharging of the energy source; and
determining the integrity of the system by checking whether the change or rate of change in voltage or hydraulic pressure
meets predetermined criteria, wherein said charging of the energy source causes an increase in voltage or hydraulic pressure
and wherein said discharging of the energy source causes a decrease in voltage or hydraulic pressure.

US Pat. No. 9,527,576

METHOD AND ASSEMBLY FOR ATTACHING FUEL SYSTEM COMPONENTS TO A RIB BEFORE THE ASSEMBLY IS JOINED TO AN AIRCRAFT WING

Airbus Operations Limited...

5. A preinstalled structural rib configured for delivery to an aircraft wing assembly location at which ribs and other structural
elements of an aircraft wing assembly are located for the manufacture of an aircraft wing assembly using said preinstalled
structural rib, the ribs and the other structural elements, wherein the preinstalled structural rib comprises:
a pair of rib portions each having a wall, the wall of one of the rib portions facing and being attached to the wall of the
other rib portion, wherein the rib portions each have a height corresponding to a thickness of the aircraft wing assembly;

a space between the rib portions; and
a fuel system component mounted to at least one of the walls and in the space between the rib portions.

US Pat. No. 9,527,583

LANDING GEAR WITH A BI-DIRECTIONAL CLUTCH

AIRBUS OPERATIONS LIMITED...

1. An aircraft landing gear, including:
a wheel rotatable about an axle;
a motor; and
a bi-directional clutch operable to connect the wheel with the motor, the bi-directional clutch comprising a ring-shaped overrunning
track connected to the wheel, a ring-shaped drive track connected to the motor and concentrically aligned with the overrunning
track, and a plurality of movable elements retained between the overrunning track and the drive track, the movable elements
being movable between: a driven configuration in which the movable elements prevent relative rotation between the drive track
and the overrunning track to thereby permit the wheel to be driven by the motor; and an overrunning configuration in which
the movable elements permit relative rotation between the drive track and the overrunning track to thereby disconnect the
wheel from the motor;

wherein the drive track is positioned radially outwardly from the overrunning track.

US Pat. No. 9,365,283

SEAL

AIRBUS OPERATIONS LIMITED...

1. A foldable seal, comprising:
an elastomeric seal substrate and at least two moulded-in stiffener plates embedded within the elastomeric seal substrate,
wherein the foldable seal is adapted to fold along fold axes at one or more discrete locations between adjacent ones of moulded-in
stiffener plates, wherein the adjacent stiffener plates include a gap therebetween, and the fold axis passes through said
gap,

the foldable seal further comprises a plurality of elastomeric stiffening webs integrally moulded with the elastomeric seal
substrate, and

wherein the elastomeric stiffening webs extend generally perpendicular to the fold axes.

US Pat. No. 9,248,903

AIRCRAFT ASSEMBLY AND SPAR

Airbus Operations Limited...

1. An aircraft wing assembly, said assembly comprising:
a pair of covers;
a spar web extending between the covers in a thickness direction, the spar web having a length which extends in a span-wise
direction and separating a fuel tank space from a non-fuel space; and

a container which extends into said fuel tank space from the spar web and is configured to house at least part of a moveable
leading edge slat track, wherein the container comprises:

a container flange integrally formed as a single piece with said spar web and extending into said fuel tank space; and
a container body joined to said container flange and extending into said fuel tank space and enclosing said at least part
of a moveable leading edge slat track.

US Pat. No. 9,862,480

AERODYNAMIC DEVICE

AIRBUS OPERATIONS LIMITED...

1. An aerodynamic device, wherein the device is a leading edge device configured for use as a leading edge device of a wing,
horizontal tailplane or vertical tailplane structure of an aircraft, the aerodynamic device having:
a spanwise length,
a chordwise width,
a leading edge section along a leading edge of the device, for being mounted to the wing, horizontal tailplane or vertical
tailplane of the aircraft, and

a trailing edge section along a trailing edge of the device, for providing a required aerodynamic profile,
wherein a first chordwise extending segment of the trailing edge section is moveable in a spanwise direction with respect
to the leading edge section or with respect to a second chordwise extending segment of the trailing edge section.

US Pat. No. 9,834,314

AIRCRAFT FUEL TANK INERTING SYSTEM

AIRBUS OPERATIONS LIMITED...

1. An aircraft fuel tank inerting system having an on-board inerting gas generation system arranged in fluid communication
between a fuel tank vent system and the aircraft fuel tank, wherein the fuel tank vent system includes a NACA duct arranged
to supply the on-hoard inerting gas generation system with atmospheric air and wherein the on-board inerting gas generation
system additionally comprises an air pressure reduction device.

US Pat. No. 9,802,912

CYCLIC ORTHO ESTER FUEL ADDITIVE

AIRBUS OPERATIONS LIMITED...

1. A liquid hydrocarbon comprising a dehydrating icing inhibitor selected from Formula I and Formula II, salts thereof or
mixtures thereof;

where:
R1 and R3 are independently selectable and are selected from a C1 to C6 substituted or non-substituted, branched or straight chain, alkyl or ether;

R2 and R4 are independently selectable and are selected from a C1 to C7 substituted or non-substituted, straight or branched chain, alkyl;

Y is independently selectable and is a substituted or non-substituted alkyl;
y is an integer of 1 to 3;
z is an integer of 2 to 6; and,wherein liquid hydrocarbon is a hydrocarbon fuel selected from an aviation fuel, gasoline, diesel and heating oil, a lubricant
or a hydraulic fluid.

US Pat. No. 9,784,326

AIRCRAFT LANDING GEAR WITH A BI-DIRECTIONAL CLUTCH

AIRBUS OPERATIONS LIMITED...

1. An aircraft landing gear, including:
a wheel rotatable about an axle;
a motor; and
a bi-directional clutch operable to connect the wheel with the motor, the bi-directional clutch comprising a ring-shaped overrunning
track connected to the wheel, a ring-shaped drive track connected to the motor and concentrically aligned with the overrunning
track, and a plurality of movable elements, each individually movable, retained between the overrunning track and the drive
track, the movable elements being movable between: a driven configuration in which the movable elements prevent relative rotation
between the drive track and the overrunning track to thereby permit the wheel to be driven by the motor; and an overrunning
configuration in which the movable elements permit relative rotation between the drive track and the overrunning track to
thereby disconnect the wheel from the motor; wherein the overrunning track is connected to the wheel by a plurality of drive
keys.

US Pat. No. 9,738,376

LANDING GEAR DRIVE SYSTEMS

AIRBUS OPERATIONS LIMITED...

1. A drive system for rotating a wheel of an aircraft landing gear, the drive system including a motor operable to rotate
a first drive pinion via a first drive path, and a driven gear adapted to be fixed to the wheel, wherein the drive system
has a first configuration in which the first drive pinion is capable of meshing with the driven gear to permit the motor to
drive the driven gear via the first drive path, and wherein the driven gear comprises a series of rollers arranged to form
a ring, each roller being rotatable about a roller axis at a fixed distance from an axis of rotation of the first drive pinion
or driven gear, respectively.

US Pat. No. 9,729,973

WIRELESS POWER TRANSMISSION

Airbus Operations Limited...

1. A method for wireless power transmission between a plurality of piezoelectric power harvesting devices attached to a structure
and a wireless transmission device comprising a piezoelectric generator attached to said structure, said piezoelectric generator
being arranged to generate vibrations in said structure, said method comprising the steps of:
controlling the piezoelectric generator to generate vibrations in said structure at a first test generation frequency to power
the plurality of piezoelectric harvesting devices;

receiving, at the wireless power transmission device, a first plurality of response messages from the plurality of piezoelectric
power harvesting devices, each response messages in the first plurality of response messages being indicative of a harvested
voltage generated by a respective piezoelectric harvesting device in the plurality of piezoelectric power harvesting devices
in response to the vibrations in said structure at the first test generation frequency generated by said piezoelectric generator;

controlling the piezoelectric generator to generate vibrations in said structure at a second test generation frequency to
power the plurality of piezoelectric harvesting devices, the second test generation frequency being different to the first
test generation frequency;

receiving, at the wireless power transmission device, a second plurality of response messages from the plurality of piezoelectric
power harvesting devices, each response message in the second plurality of response messages being indicative of a harvested
voltage generated by a respective piezoelectric harvesting device in the plurality of piezoelectric power harvesting devices
in response to the vibrations in said structure at the second test generation frequency generated by said piezoelectric generator;

selecting a generation frequency from one of said first test generation frequency and said second test generation frequency
based on said first plurality of response messages and said second plurality of response messages, and in accordance with
a predetermined formula applied to the first plurality of response messages and the second plurality of response messages;
and

controlling said piezoelectric generator to generate vibrations in said structure at said generation frequency.

US Pat. No. 9,718,262

ROLL FORMING COMPOSITE COMPONENTS

AIRBUS OPERATIONS LIMITED...

1. A method of roll forming a plurality of composite components, the method including the steps:
(a) laying a plurality of blanks onto a carrier strip, each blank including a stack of sheets of uncured composite material
contacting a respective contact part of the carrier strip;

(b) after step (a), forming the blanks and their respective contact parts of the carrier strip with a desired cross-sectional
profile by passing the carrier strip carrying the blanks through a series of sets of rollers, each set of rollers performing
an incremental part of a bending operation until the desired cross-sectional profile is obtained;

(c) after step (b), separating each blank along with its respective contact part of the carrier strip from the rest of the
carrier strip; and

(d) before or after step (c), curing the blanks.

US Pat. No. 9,718,540

AIRCRAFT LANDING GEAR ARRANGEMENT AND A NOSE LANDING GEAR ASSEMBLY

AIRBUS OPERATIONS LIMITED...

1. An aircraft landing gear arrangement, comprising:
a nose landing gear assembly having a nose landing gear wheel with a brake apparatus configured for landing or rejected take-off
braking arranged therein,

the nose landing gear wheel includes a hub offset relative to a rotational centreline of the wheel in an axial direction,
and a rim co-axial with the hub and the brake apparatus fully disposed within the nose landing gear wheel, wherein the nose
landing gear wheel comprises a first part and a second part attached to the first part, where the first part includes a cylindrical
wall which is deeper than a cylindrical wall of the second part.

US Pat. No. 9,701,391

AIRCRAFT STRUCTURE COMPRISING A SKIN PANEL

Airbus Operations Limited...

1. An aircraft structure comprising;
(i) a skin panel, having;
an outer surface forming an external face of the structure, and
an inner surface internal to the structure;
(ii) a plurality of stringers extending along a length of the inner surface of the skin panel, wherein each stringer is a
discrete element of the structure; and

(iii) an inner panel spaced apart from the inner surface of the skin panel and being internal to the structure, so as to form
an internal cavity adjacent to the skin panel, wherein the stringers are located within the cavity.

US Pat. No. 9,523,606

METHOD AND APPARATUS FOR TESTING MATERIALS

Airbus Operations Limited...

1. A method of testing an aircraft or aircraft component comprising composite material, the method comprising:
calibrating an infrared spectrometer by selecting a plurality of variables which have the potential to influence the physical
characteristics of a composite used in the aerospace industry, the calibration further comprises:

selecting a plurality of values for each variable;
inputting the variables and values into a design of experiments model, thereby obtaining a sample test matrix;
testing a plurality of composite samples according to the test matrix, thereby obtaining a number of infrared spectra;
testing a physical characteristic of the composite samples;
collating the infrared spectra detected by the infrared spectrometer with the measured physical characteristic of a sample,
and

correlating of infrared spectra and measured physical characteristics to form a database of measurement results, wherein the
database of measurement results represents a calibration of the infrared spectrometer;

the method further comprising:
taking a measurement of the aircraft or aircraft component comprising composite material using the infrared spectrometer,
thereby obtaining an infrared spectrum,

comparing the infrared spectrum to the database of infrared spectra and correlated physical characteristics; and
based on the comparison, providing a value relating to a measurement of a physical characteristic of the composite material.

US Pat. No. 9,475,383

AIRCRAFT FUEL TANK SYSTEM

AIRBUS OPERATIONS LIMITED...

1. An aircraft fuel tank system, comprising:
one or more aircraft fuel tanks holding and supplying aircraft fuel to aircraft engines within said aircraft;
an aircraft surge tank comprising an inlet from said one or more aircraft fuel tanks and a first ullage vent opening and a
second ullage vent opening, said aircraft surge tank being arranged to provide a predetermined maximum fuel capacity and having
a minimal ullage at said maximum fuel capacity;

a first vent pipe having a first open end in fluid communication with said first ullage vent opening and a second open end
positioned within said minimal ullage of said surge tank, said first vent pipe being arranged to provide fluid communication
between said minimal ullage and said first ullage vent opening;

a second vent pipe having a first open end in fluid communication with said second ullage vent opening and a second open end
positioned within said minimal ullage of said surge tank, said second vent pipe being arranged to provide fluid communication
between said minimal ullage and said second ullage vent opening; and

a coupling mechanism sealingly externally coupling an external flame barrier to said second ullage vent opening so as to provide
fluid communication between said second vent pipe and atmosphere via the coupled external flame barrier, and wherein said
external flame barrier is permanently open to fluid flow.

US Pat. No. 9,079,365

CURABLE ASSEMBLY AND A FILLER COMPONENT

AIRBUS OPERATIONS LIMITED...

1. A curable assembly, which, upon the application of curing conditions will form a completed component or part component,
the assembly comprising:
a first curable sub-assembly part of composite fibre-reinforced, resin matrix material,
a second curable sub-assembly part of composite fibre-reinforced, resin matrix material arranged against the first curable
piece,

a filler component arranged between the first and the second curable sub-assembly parts, the filler component formed from
a material which is rigid relative to the material of the first and second curable sub-assembly parts before curing, whereby
the filler component is arranged to be secured between the first and second curable sub-assembly parts on application of curing
conditions so as to form the completed component or part component,

the filler component having a first elongate member which has a cross section in the form of a concave ogive defining a first
surface having a first profile and a second substantially opposite surface having a second profile, the first surface profile
being shaped to fit against the first curable sub-assembly part, the second surface profile being shaped to fit against the
second curable sub-assembly part, the filler component having a second elongate member arranged at a right angle to the first
elongate member and having a cross section in the form of a part annulus such that the first elongate member and the second
elongate member share a common plane, the filler component being arranged to apply or to react to a tooling load of at least
one of the first or second surfaces during curing.

US Pat. No. 10,336,440

CURVED WINGLET

Airbus Operations Limited...

1. An aircraft wing and a winglet on the tip thereof, the winglet comprising:an inner end and an outer end, and
the winglet having a varying radius of curvature (R) extending from the inner end to the outer end, and wherein the radius of curvature of the winglet:
(i) decreases along the winglet over a first distance d1 from the inner end to a first location along the winglet; wherein over the first distance d1 the radius of curvature varies according to an equation R=k1/dn, where k1 is a constant, d is a distance along the winglet measured in an outward direction, and n is greater than zero;
(ii) remains constant over a second distance d2 from the first location to a second location along the winglet; and
(iii) increases along the winglet over a third distance d3 from the second location to a third location along the winglet, wherein the sum of the first and third distances (d1+d3) is greater than the second distance (d2).

US Pat. No. 10,144,506

DRIVE SYSTEM FOR AIRCRAFT LANDING GEAR

AIRBUS OPERATIONS LIMITED...

1. A drive system for rotating a wheel of an aircraft landing gear, the drive system comprising: a drive pinion; a motor operable to rotate the drive pinion via a drive path; a rotary damper in the drive path between the motor and the drive pinion; and a driven gear adapted to be attached to the wheel so as to be capable of rotating the wheel, wherein the drive system has a drive configuration in which the drive pinion is capable of meshing with the driven gear to permit the motor to drive the driven gear via the drive path.

US Pat. No. 10,086,222

CONDITIONING SYSTEM FOR FUEL CELL EXHAUST

AIRBUS OPERATIONS LIMITED...

2. A method of conditioning oxygen depleted air (ODA) exhausted from a fuel cell comprising the steps of:taking exhaust ODA from a fuel cell,
passing the ODA through a primary heat exchanger,
the primary heat exchanger is located in a collector cell of an aircraft fuel tank,
wherein the primary heat exchanger is a condenser,
wherein the ODA passes through the fuel in the collector cell to transfer any water from the ODA to the fuel, and
using the cooled, dried ODA to inert the fuel in the aircraft fuel tank.

US Pat. No. 9,862,477

AIRCRAFT STRUCTURE

AIRBUS OPERATIONS LIMITED...

1. An Aircraft structure having a panel, a stringer and a rib, wherein the stringer includes a stringer flange joined to the
panel and a stringer web extending away from the stringer flange; and the rib includes a rib web having first and second faces
which meet at an edge, and a rib foot having a first rib foot flange joined to the stringer web, a second rib foot flange
joined to the panel or to the stringer flange, and a rib foot web joined to the first face of the rib web adjacent to the
edge of the rib web; wherein the first rib foot flange is connected to the rib foot web by a first corner including at least
one layer which runs continuously from the first rib foot flange into the rib foot web via the first corner, the second rib
foot flange is connected to the rib foot web by a second corner including at least one layer which runs continuously from
the second rib foot flange into the rib foot web via the second corner, one of the rib foot flanges extends away from the
first face of the rib web, and the other of the rib foot flanges passes across the edge of the rib web and extends away from
the second face of the rib web.

US Pat. No. 9,845,160

AIRCRAFT AERIAL REFUELLING SYSTEM

AIRBUS OPERATIONS LIMITED...

1. An aircraft aerial refueling system including at least one pressure controlled fuel pump, the fuel pump comprising:
a pump outlet and
a control system including a control loop feedback mechanism adapted to regulate a pump outlet fuel pressure at the pump outlet
using an outlet fuel pressure signal as control feedback.