US Pat. No. 9,073,767

WATER SUPPLY WITH A BIDIRECTIONAL UV DISINFECTION DEVICE

Airbus Operations GmbH, ...

1. A water disinfection system comprising:
a bidirectional water disinfection device, having a UV light generator for the UV treatment of water,
a water pipe, having a first pipe portion, a second pipe portion and a third pipe portion which branches off between the first
and the second pipe portion,

wherein the water disinfection device has a first water connection and a second water connection,
wherein the first water connection is connected to the first pipe portion,
wherein the second water connection is connectable to a water reservoir,
wherein the second pipe portion is connectable to a water source,
wherein the third pipe portion is connectable to a tap for water;
wherein the bidirectional water disinfection device is adapted for being flown through in a first direction during filling
of the reservoir in a first mode of operation;

wherein the bidirectional water disinfection device is adapted for being flown through in a second direction which is counter
to the first direction, during water drawing from the reservoir in a second mode of operation; and

wherein a higher light intensity is producible in the UV light generator in the first mode of operation than in the second
mode of operation.

US Pat. No. 9,221,549

METHOD AND SYSTEM FOR DISPLAYING INFORMATION ON A DISPLAY UNIT IN AN AIRCRAFT CABIN

AIRBUS OPERATIONS GMBH, ...

1. A method for displaying information on an electrical display unit in an aircraft cabin, the method comprising;
generating at least one signal unambiguously identifying the information,
acquiring, in particular wirelessly acquiring, the at least one signal,
controlling the display unit on the basis of the at least one signal,
displaying the information on the electrical display unit ,
acquiring at least one of departure and arrival location information of a flight, and
displaying the information depending on the at least one of the departure and arrival location information acquired in different
languages, wherein:

the acquiring of the at least one of departure and arrival location information is automaticallyried out by a computer system
based on a flight route for navigation of the flight that has been entered into the computer system by a pilot.

US Pat. No. 9,056,671

FIXED WING OF AN AIRCRAFT

Airbus Operations GmbH, ...

1. A wing of an aircraft that exhibits a main wing extending over a half-span,
wherein a wing chord of the main wing (M) at a location of an outermost rib (R5) of the main wing (M) viewed from the wing root measures 5% to 15% of the half-span of the main wing (M),

wherein the main wing (M) is comprised of a wing base area (10) and a wing adapter section (20), that forms the outer end area of the main wing (M), as viewed from the wing root, and is designed to secure a wing tip
device (W1, W2, W3),

wherein the wing adapter section (20) extends from an outer rib (R3) of the wing base area (10) and over 2% to 10% of the half-span of the main wing (M) up to an outer rib (R5) of the wing adapter section (20) forming the outermost rib (R5) of the main wing (M),

characterized in that the dihedral angle of the wing adapter section (20) that refers to the respective local spanwise direction continuously increases by between 10 and 60 degrees from the outer
rib (R3) of the wing base area (10) up to the outermost rib (R5) of the wing adapter section (20).

US Pat. No. 9,180,969

AIRCRAFT SEAT ASSEMBLY FOR AIRCRAFT PASSENGERS HAVING RESTRICTED MOBILITY

Airbus Operations GmbH, ...

1. A method of transferring a passenger in a wheelchair to a seating area of an aircraft, comprising:
moving a wheelchair sub-frame having subframe rail elements and a seat having seat rail elements slidingly engageable with
the wheelchair sub-frame rail elements along an aisle in a longitudinal direction of the aircraft;

moving the wheelchair sub-frame and seat within a space provided in front of a seating row in a direction perpendicular to
the longitudinal direction, the seating row comprising a seat base assembly adapted to receive the seat of the wheelchair
sub-frame wherein the seat faces in the longitudinal direction in a forward direction of the aircraft while moving within
said space by rolling the wheelchair sub-frame and seat on wheels of the wheelchair sub-frame laterally;

moving the wheelchair sub-frame and seat within said space past a seat of the seating row comprising the seat base assembly,
provided adjacent to the aisle until the wheelchair sub-frame and seat are positioned in front of the seat base assembly provided
to the row;

sliding the seat in a backward direction opposite the flight direction of the aircraft such that seat base rail elements provided
to the seat base assembly are engaged with the seat rail elements of the seat, wherein the subframe rail elements of the wheelchair
subframe and the seat base rail elements of the seat base assembly extend above the floor of the aircraft at substantially
the same height such that the seat remains substantially at the same height above the floor prior to and after sliding the
seat from the wheelchair sub-frame to sliding engagement with the seat base assembly.

US Pat. No. 9,234,813

METHOD AND AN ARRANGEMENT FOR PURPOSES OF DETERMINING AN INCIDENCE OF LOADING OF AN AIRCRAFT STRUCTURE

Airbus Operations GmbH, ...

1. A method for purposes of determining at least one incidence of loading of an aircraft structure comprising the steps:
optically registering at least one section of the aircraft structure for purposes of determining an “actual” optical state
of the aircraft structural section,

comparing the “actual” optical state with a stored “design” optical state of the aircraft structural section,
recording noises relating to at least one section of the aircraft structure for purposes of compiling an “actual” acoustic
image of the aircraft structural section,

comparing the “actual” acoustic image with a stored “design” acoustical image of the aircraft structural section,
assessing based on structural mechanics whether an overload of at least one part of the aircraft section has occurred, and
using an alien acoustic signal that has been determined as a starting point for the assessing step, wherein
optical markings are provided on a side of the fuselage near the cockpit and near the tail unit, and the markings on each
side of the fuselage together define an imaginary straight line extending in a longitudinal direction of the aircraft.

US Pat. No. 9,067,678

SIDE FEEDER AIR GUIDING ELEMENT FOR AN AIRCRAFT AIR-CONDITIONING SYSTEM

Airbus Operations GmbH, ...

1. An air guiding element for an aircraft air-conditioning system, comprising:
a distributing pipe having an air inlet opening arranged in the region of an end face of the distributing pipe and an air
discharge opening arranged in the region of a generated surface of the distributing pipe,

a flow diverting element having a first section connected to the air discharge opening of the distributing pipe and a second
section arranged downstream of the first section relative to the direction of the air flow through the air guiding element,
the second section being configured to deflect the air as it flows through the second section at an angle of approximately
45 to 135° relative to the direction of the air flow through the first section, and

a diffuser which is arranged downstream of the second section of the flow diverting element relative to the direction of the
air flow through the air guiding element and is connected to an air outlet opening,

wherein the diffuser has a flow cross-section widening in the direction of the air flow from the air discharge opening to
the air outlet opening,

wherein at least one of the flow diverting element and the diffuser includes a side wall that is composed at least in sections
of a sound-absorbing foam material, the side wall of sound-absorbing foam material defining a surface facing at least one
of an interior space of the flow diverting element and an interior space of the diffuser, the sound-absorbing foam material
being provided with a perforated cover in the form of a perforated laminate applied only to the surface of the sound-absorbing
foam material facing at least one of an interior space of the flow diverting element and an interior space of the diffuser
so as to protect the surface of the sound-absorbing foam material from damaging effects caused by air flow through the flow
diverting element and diffuser, wherein there are arranged in the flow diverting element a plurality of webs which extend
parallel to the flow direction of the air through the flow diverting element, and

wherein the webs are defined by elongated L-shaped plate elements extending across the interior space of the flow diverting
element to subdivide the interior space into a plurality of parallel guiding channels extending throughout the second section
to deflect the air flow through the angle of approximately 45 to 135°, the webs being oriented to block cross flow between
the guiding channels to minimize momentum of air flow in the direction of the air flow through the distributing pipe, and
the guiding channels delivering deflected air flow directly into the diffuser.

US Pat. No. 9,302,636

ELECTRICAL SYSTEM FOR AN AIRCRAFT

AIRBUS OPERATIONS GMBH, ...

1. An electrical system for an aircraft, the electrical system being configured to drive a group of electric motors which
drive a fluid conveying device, the electrical system comprising:
an inverter for transforming a first alternating current from an on-board network having a variable frequency into a second
alternating current;

at least a first electrical load and at least a second electrical load, which are operated simultaneously by the second alternating
current;

wherein the first electrical load comprises the group of electric motors;
wherein the electrical system is configured to, if an electric motor of the group of electric motors is out of operation,
increase the frequency of the second alternating current and operate the remaining electric motors at a higher frequency.

US Pat. No. 9,327,821

AIRCRAFT STRUCTURAL ASSEMBLY HAVING AN AREA ELEMENT WHICH COMPRISES A CORE AND AN OUTER LAYER

AIRBUS OPERATIONS GMBH, ...

1. Aircraft structural assembly having an area element which comprises a core and an outer layer, wherein:
a first surface of the area element, when seen from the outside of the area element, is convexly curved relative to an imaginary
central area of the area element extending through the core of the area element, and

a second surface of the area element located opposite the first surface is oriented parallel to the imaginary central area
of the area element extending through the core of the area element,

the area element being configured in the form of a floor panel of a floor system,
the second surface of the area element being structured to form a walkable floor surface of the floor system when the aircraft
structural assembly is mounted in an aircraft, and

the area element of the aircraft structural assembly being convexly curved in the region of the entire first surface of the
area element relative to the imaginary central area of the area element,

wherein the area element has at least one area region not provided with a core,
wherein the area region not provided with a core extends along a section of a peripheral edge of the area element,
wherein a plurality of fastening rails for fixing one of a seat and a structural monument to the area element is integrated
into the core of the area element, the plurality of fastening rails including one of the at least one outermost fastening
rails located closest to one of the area region not provided with a core, and

wherein the area element comprises a connecting device that connects the area element to a first end of a supporting rod for
connecting the area element to the aircraft structure, the connecting device being integrated into the core at a location
of the core that is adjacent to but spaced apart from the area region not provided with a core and between the one of the
at least one outermost fastening rails and the area region not provided with a core.

US Pat. No. 9,140,676

SMOKE DETECTION SYSTEM AND METHOD FOR OPERATING A SMOKE DETECTION SYSTEM

AIRBUS OPERATIONS GMBH, ...

1. Smoke detection system configured to monitor a region to be monitored in a vehicle cabin, comprising:
at least one smoke detector which is installed in a vehicle cabin, and
at least one fluid injection device disposed below and remotely from the smoke detector in a sidewall region of the vehicle
cabin and configured to inject a fluid into said region to be monitored in a direction of the at least one smoke detector
such that in an emergency case, when smoke is present in a region of said region to be monitored, the smoke is transported
by the injected fluid to the at least one smoke detector.

US Pat. No. 9,334,044

METHOD FOR GENERATING HYDRAULIC POWER IN AN AIRCRAFT, USE OF A HYBRID POWER CONTROL UNIT AND DRIVE SYSTEM

AIRBUS OPERATIONS GMBH, ...

1. A drive system for moving at least one control surface of an aircraft and for generating hydraulic power in an aircraft,
comprising:
at least one transmission shaft connected to a hybrid power control unit, the power control unit having an electric motor
and a hydraulic displacement machine coupled to a differential gear unit for driving a common output shaft, and a control
unit for controlling at least one of the speed of the electric motor and a displacement of the hydraulic displacement machine
for adjusting a resulting hydraulic pressure or flow rate,

wherein the drive system, through a control via the control unit, is adapted for:
arresting the output shaft;
rotating the electric motor such that the hydraulic displacement machine is driven due to the arrested output shaft; and
supplying fluid flow into a hydraulic system.

US Pat. No. 9,242,742

MEASUREMENT METHOD AND DEVICE FOR DETERMINING THE POSITION OF A PROFILE COMPONENT APPLIED TO A SHELL COMPONENT

Airbus Operations GmbH, ...

1. A measurement method for determining an ACTUAL position (5?) of an omega profile component (2) relative to a shell component (1), the method comprising:
optically acquiring, via a measuring unit, in a contactless manner, a profile cross section of the omega profile component
(2), the measuring unit frontally acquiring the profile cross section, the omega profile component (2) being placed on the shell component in the ACTUAL position;

establishing, by an evaluating unit (4) coupled to said measuring unit (3), a plurality of adjacently spaced apart measuring points (6, 6?) at first and second mutually opposing flank sides (7a, 7a?, 7b, 7b?) of the profile cross section of the omega profile component (2);

extending, via the evaluating unit (4), a first regression line (8a, 8a?), through the measuring points (6, 6?) on the first flank side (7a, 7a?);

extending, via the evaluating unit (4), a second regression line (8b, 8b?) through the measuring points (6, 6?) on the second flank side (7b, 7b?);

determining, via the evaluating unit (4), the point of intersection (9, 9?) of the first regression line (8a, 8a?) and the second regression line (8b, 8b?); and

determining, via the evaluating unit (4), the ACTUAL position (5?) of the omega profile component (2) relative to the shell component (1) from the point of intersection (9, 9?).

US Pat. No. 9,193,444

DEVICE AND METHOD FOR INCREASING THE AERODYNAMIC LIFT OF AN AIRCRAFT

Airbus Operations GmbH, ...

1. A lift arrangement for an aircraft, comprising:
an aircraft fuselage section with an outside,
an aerodynamic lift body attached to the outside of the aircraft fuselage section and extending from the aircraft fuselage
section outwardly,

a drive means, and
a pair of movably held add-on bodies arranged upstream of a leading edge of the aerodynamic lift body,
wherein the add-on bodies are connected to the drive means and are configured to be moved to a neutral position wherein the
add-on bodies finish off so as to be flush with the outside of the aircraft fuselage section and to be moved to at least one
activation position wherein the add-on bodies extend from the outside of the aircraft fuselage section outwardly,

wherein the add-on bodies comprise an aerodynamically effective surface and are equipped in the at least one activation position
with airflow to generate vortices that impinge on the aerodynamic lift body, thus leading to an increase in lift on the aerodynamic
lift body,

wherein the aerodynamic lift body is a moveable horizontal stabilizer attached to the aircraft fuselage section and is moveable
by a trimmable horizontal stabilizer actuator, and

wherein the drive means is coupled to the trimmable horizontal stabilizer actuator in such a manner that when the horizontal
stabilizer is moved from a neutral position to a desired adjustment position, movement of the add-on bodies from the neutral
position to the activation position takes place.

US Pat. No. 9,541,001

DRIVE UNIT, METHOD FOR PROVIDING POWER, AND USE OF A DRIVE UNIT

Airbus Operations GmbH, ...

1. A drive unit, comprising:
a combustion chamber for combusting a fuel/air mixture;
a ring-shaped fuel cell device
comprising at least one fuel cell comprising:
an anode couplable to a fuel line;
a cathode couplable to an air source; and
a fluid outlet, wherein the fuel cell is arranged upstream of the combustion chamber; and
at least one ring-shaped fuel converter arranged between the fuel line and the fuel cell device, the fuel converter adapted
to provide a gaseous fuel from a liquid fuel,

wherein the combustion chamber comprises;
a combustion chamber inlet for supplying the fuel/air mixture; and
a combustion chamber outlet for discharging exhaust gas, and the combustion chamber inlet is connected to the fluid outlet
of the fuel cell device, and

wherein the ring-shaped fuel cell device and the ring-shaped fuel converter are concentric.

US Pat. No. 9,167,720

AIRCRAFT ELECTRONICS COOLING APPARATUS FOR AN AIRCRAFT HAVING A LIQUID COOLING SYSTEM

Airbus Operations GmbH, ...

1. An aircraft electronics cooling apparatus comprising:
a liquid cooling system onboard the aircraft, including a coolant circulating therein;
an electronic device to be cooled, mounted within a housing, the housing comprising an inlet opening and an outlet opening;
and

a cooling conduit operatively connecting the electronic device to the liquid cooling system,
wherein the coolant exiting the liquid cooling system flows through an interior of the housing and around the electronic device
to cool the electronic device and the housing is flooded with the coolant in operation.

US Pat. No. 9,061,773

METHOD AND APPARATUS FOR THE FINAL ASSEMBLY OF AIRCRAFT

Airbus Operations GmbH, ...

1. A method for final assembly of at least two aircrafts comprising:
assembling the at least two aircrafts in a transverse direction on a carousel, the at least two aircrafts being disposed side-by-side;
accessing the at least two aircrafts by a work stage disposed at a center of the carousel, an entire circumference of the
carousel being accessible from the work stage, the work stage including at least two receiving devices which have a U-shaped
form open in a radial direction of the carousel into which the at least two aircrafts are partially inserted with their longitudinal
axes extending in the radial direction; and

rotating the carousel on a vertical rotation axis 360°.

US Pat. No. 10,018,600

SYSTEM FOR NON-DESTRUCTIVE INSPECTION OF STRUCTURAL COMPONENTS

AIRBUS OPERATIONS GMBH, ...

1. A system for non-destructive inspection of structural components comprising:an ultrasonic probe having a contact face configured to contact a surface of a structural component to be inspected and being adapted to emit ultrasonic energy in the form of ultrasonic waves into the structural component when the contact face abuts on a surface of the structural component,
a thermal imaging camera configured to inspect a portion of a surface of the structural component to detect a region of the surface of the structural component where an increase of the temperature occurs, and
a control unit connected to the ultrasonic probe and the thermal imaging camera,
wherein the contact face extends in a plane and is provided with at least two bars, which bars are arranged in parallel and wherein adjacent bars of the at least two bars have a common distance therebetween,
wherein the common distance between adjacent bars of the at least two bars is adjustable for matching the common distance between adjacent bars of the at least two bars to a wavelength of the ultrasonic waves emitted by the ultrasonic probe.

US Pat. No. 9,272,772

SURFACE ELEMENT FOR AN AIRCRAFT, AIRCRAFT AND METHOD FOR IMPROVING HIGH-LIFT GENERATION ON A SURFACE ELEMENT

Airbus Operations GmbH, ...

1. An aircraft wing comprising:
a leading edge,
a high lift device arrangement positioned along the leading edge,
at least one add-on body comprising an engine positioned in a leading edge region, the engine having an engine mounting center
line,

wherein the high lift device arrangement is interrupted in the region of at least one add-on body for preventing collision
with the add-on body,

wherein the wing comprises an arrangement of openings in a region covering the add-on body, said openings connected to an
air conveying device for conveying air through the openings, and

wherein the arrangement of openings extends for up to 20% of the wing span to each side of the engine mounting center line.

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. 9,319,108

SYSTEM FOR CONTACTLESS TRANSFER OF ENERGY AND DATA AND VEHICLE WITH SUCH A SYSTEM

Airbus Operations GmbH, ...

1. A system for the contactless transfer of energy and data,
comprising a transfer path with at least one primary coil, connected by way of a primary line to a primary control unit, and
at least one secondary coil connected by way of a secondary line to a secondary control unit,

wherein the primary control unit is configured to lead data-modulated first alternating-voltage signals of a first frequency
range into the primary coil, and

wherein the secondary control unit is configured to receive the first alternating-voltage signals of the first frequency range
from the secondary coil, and to demodulate the modulated-on data;

a feed-in line connected to the primary line,
an activation line connected to the secondary line, and
a first filter arranged between the secondary line and an activation connection,
wherein the first filter is permeable to second alternating-voltage signals of a second frequency range while blocking the
first alternating-voltage signals of the first frequency range.

US Pat. No. 9,457,303

PARTICLE SEPARATOR FOR AN AIR CONDUIT, AIR DISTRIBUTION SYSTEM, USE OF A PARTICLE SEPARATOR AND AIRCRAFT

AIRBUS OPERATIONS GMBH, ...

1. A particle separator, including a pipeline that allows a fluid to flow in a curved direction of flow, the pipeline comprising:
an inlet region;
a curved deflection region, which in the direction of flow follows on from the inlet region, with an inside wall and an outside
wall;

a plurality of particle reflection bodies; and
a delimitation body which at least in some sections extends between the inside wall and the outside wall in the interior of
the deflection region and is curved in the same direction as the deflection region,

wherein the delimitation body in the direction of flow is curved to a lesser extent than the outside wall so that between
the delimitation body and the outside wall a pocket for collecting particles forms, which pocket is open towards the inlet
region and which tapers off in the direction of flow, and

wherein the particle reflection bodies are arranged directly and only on an inside wall of the inlet region, the inside wall
of the inlet region makes a transition to the inside wall of the deflection region, and the particle reflection bodies are
designed to deflect impinging particles into the pocket.

US Pat. No. 9,469,403

MONUMENT FOR AN AIRCRAFT COMPRISING A LIFT APPARATUS

Airbus Operations GmbH, ...

1. A monument for an aircraft, the monument comprising:
a straight elongate cavity open at one of longitudinal ends thereof towards the exterior of the monument; and
a lift apparatus mounted to the monument and adapted for lifting goods from outside the monument along the longitudinal axis
of the cavity through the open end into the cavity,

wherein the monument is adapted to be mounted on a floor structure of an aircraft separating two compartments of the aircraft
from each other such that the longitudinal axis is oriented perpendicularly to the floor structure and the open end of the
cavity is facing the floor structure, the lift apparatus comprising:

a guide means extending parallel to the longitudinal axis of the cavity;
a conveying means disposed in the cavity and mounted to the guide means such that the conveying means is linearly moveable
along the guide means;

a moving means adapted for driving the conveying means to linearly move along the guide means;
a control means adapted for controlling the moving means; and
a gripping means disposed in the cavity, secured to the conveying means and adapted for selectively gripping and releasing
goods,

wherein the guide means comprises first and second straight guide members spaced from each other, each being attached to or
integrated into a different one of two spaced opposing wall portions of a sidewall arrangement defining the cavity and extending
parallel to the longitudinal axis of the cavity,

wherein the conveying means comprises first and second conveying members, each mounted to a different one of the guide members
such that the first and second conveying members are linearly moveable along the respective guide members,

wherein the moving means is adapted for driving the first and second conveying members to linearly move along the guide members,
wherein the control means is adapted for controlling the moving means to synchronize the linear movement of the first and
second conveying members effected by the moving means, and

wherein the gripping means is secured to the first and second conveying members such that the first and second guide members
are disposed on opposite sides of the gripping means.

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. 9,126,674

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. 9,079,657

WING OF AN AIRCRAFT AND ASSEMBLY OF A WING COMPRISING A DEVICE FOR INFLUENCING A FLOW

Airbus Operations GmbH, ...

1. A wing of an aircraft with an upper side and a lower side, the wing comprising:
a main wing, which has an upper surface positioned on the upper side, and a lower surface positioned on the lower side, which
surfaces in each case run along a main wing chordwise direction;

at least one high lift flap coupled to the main wing such that the at least one high lift flap is movable between a retracted
and an extended setting; and

at least one spoiler coupled to the main wing such that the at least one spoiler is rotatable and projects beyond a trailing
edge of the main wing;

wherein the main wing has a plurality of ejection openings, of which a plurality are arranged side-by-side along a main wing
spanwise direction, and which are connected in terms of flow via an air conduit with an outlet device of a flow delivery driver
device arranged on the main wing or on the spoiler;

wherein the spoiler has a plurality of inlet openings for intake of air, which are arranged side-by-side in a spoiler spanwise
direction, and which in each case are connected in terms of flow via an air conduit with an inlet device of the flow delivery
driver device; and

wherein the flow delivery driver device has a receiver device for reception of command signals for purposes of adjustment
of the flow delivery driver device in such a manner that air flowing around the wing is sucked in through the inlet openings
on the spoiler and said air is ejected through the ejection openings on the main wing.

US Pat. No. 9,248,912

METHOD AND SYSTEM FOR EMERGENCY VENTILATION OF AN AIRCRAFT CABIN

Airbus Operations GmbH, ...

1. A method for emergency ventilation of an aircraft cabin of an aircraft, the aircraft located in an external aircraft environment,
the method comprising:
controlling at least one first valve, the first valve being arranged in a first aircraft fuselage area in the underfloor area,
such that during normal operation the first valve serves as an air outlet valve of an aircraft cabin pressure control system,
such that air from inside the aircraft cabin is conducted to the first aircraft fuselage area of aircraft and is discharged
into the external aircraft environment through the opened first valve, and such that during an emergency ventilation operation
the first valve serves as an air inlet valve such that air is supplied from the external aircraft environment into the first
aircraft fuselage area through the opened first valve and is conducted from the first aircraft fuselage area into the aircraft
cabin;

controlling at least one second valve, the second valve being arranged in a second aircraft fuselage area in the underfloor
area spaced apart from the first aircraft fuselage area along a longitudinal axis of the aircraft, such that during the normal
operation and during the emergency ventilation operation the second valve serves as an additional air outlet valve of the
aircraft cabin pressure control system, such that air is conducted from the aircraft cabin into the second aircraft fuselage
area and is discharged into the external aircraft environment through the opened second valve; and

controlling at least one recirculation fan of an aircraft air-conditioning system, such that during the normal operation the
recirculation fan draws in air from the aircraft cabin and supplies the air to a mixing chamber of the aircraft air-conditioning
system, and such that during the emergency ventilation operation the recirculation fan directly draws ram air, supplied from
the external aircraft environment into the first aircraft fuselage area through the opened first valve, into the mixing chamber
of the aircraft air-conditioning system and conveys the ram air from the mixing chamber into the aircraft cabin.

US Pat. No. 9,481,116

METHOD AND MANUFACTURING DEVICE FOR MANUFACTURING A FIBER COMPOUND SANDWICH COMPONENT

Airbus Operations GmbH, ...

1. A method for manufacturing a defect-free sandwich component, the method comprising:
inserting a semifinished product arrangement comprising two layers, each of which comprises at least one dry semifinished
product tissue, and a closed-cell rigid foam between the two layers, as starting materials of the sandwich component in a
tool device;

in a first heating phase, heating the semifinished product arrangement to an infusion temperature;
introducing a matrix material flowable at the infusion temperature in the semifinished product arrangement during an infusion
phase;

in a second heating phase, stepwise increasing a temperature of the semifinished product arrangement to a curing temperature
in partial steps so that each partial step presents a temperature increasing portion and a temperature holding portion so
as to achieve a temperature equalization within the semifinished product arrangement;

during a curing phase, at least partially curing the matrix material before, during, and/or after the second heating phase
to form skin layers comprising at least parts of the dry semifinished product tissues and a connection area for a full-surface
connection of the closed-cell rigid foam and the skin layers, at least in portions thereof; and

cooling the semifinished product arrangement to ambient temperature during a cooling phase,
wherein the semifinished product arrangement is provided with a flowing aid and surrounded by an arrangement of sheets, and
the matrix material is introduced into the semifinished product arrangement by negative pressure.

US Pat. No. 9,469,052

METHOD AND APPARATUS FOR PRODUCING A FIBER-REINFORCED PLASTICS CASTING

Airbus Operations GmbH, ...

4. A method for producing a fiber-reinforced plastics casting, comprising:
filling an open moulding box with a free flowing moulding material comprising pellets;
inserting a textile preform in the moulding material to form a moulding cavity;
infiltrating the moulding material with high viscosity synthetic resin material to form a durable mould and curing the high
viscosity resin material;

infiltrating the textile preform with low viscosity synthetic resin material to form a fiber-reinforced plastics casting (FRP);
curing the low viscosity resin material; and
demoulding the cured moulding material after curing of the low viscosity resin material to separate the plastics casting.

US Pat. No. 9,086,399

DIAGNOSTIC SYSTEM AND DIAGNOSING METHOD, HOUSING COMPONENT OF A LUBRICANT CONTAINER

Airbus Operations GmbH, ...

1. A diagnostic system for detecting and transmitting a sensor value concerning an operational condition of a system component
to an external reception and/or transmission device, the diagnostic system comprising:
at least one sensor device comprising at least one sensor for generating sensor values corresponding to the respective first
operational condition,

a control device comprising a timer and a function for the performance of measurements by the sensor device at predetermined
points of time or within predetermined time intervals,

a signal transmission device for receiving the sensor signals from the sensor device and for signal transmission of the sensor
signals of the sensor device to an external reception and/or transmission device,

a power supply device for supplying electric energy to the sensor device and to the signal transmission device,wherein
the diagnostic system comprises a device for the determination of a second operational condition of the system component,
and

the control function is configured such that at the predetermined points of time or at the predetermined time intervals at
which it performs a detection of the second operational condition of the transmission mechanism, the control function compares
generated sensor values corresponding to the respective second operational condition to a predetermined comparative value
and only provides the sensor value corresponding to the respective second operational condition to the signal transmission
device if it is higher or lower than this comparative value.

US Pat. No. 9,073,621

AIRCRAFT COMPRISING AN INSULATION SYSTEM FOR THERMAL AND ACOUSTIC INSULATION

Airbus Operations GmbH, ...

1. An aircraft with an insulation system for thermal insulation and acoustic insulation, with the aircraft comprising:
a cabin;
an outer skin;
an acoustic insulation unit;
a thermal insulation unit;
wherein the acoustic insulation unit is configured for acoustically insulating the aircraft;
wherein the thermal insulation unit is configured for thermally insulating the aircraft;
wherein the acoustic insulation unit and the thermal insulation unit are arranged between the cabin and the outer skin, and
wherein the thermal insulation unit is formed from a coarsely-textured woven material with a coarse fiber pattern thereby
preventing the thermal insulation unit from soaking up water and comprises a plurality of strips and a connecting strip, wherein
the connecting strip is adapted to affix the strips.

US Pat. No. 9,090,349

BEARING APPLICATION FOR FASTENING STEP FLIGHTS IN AN AIRCRAFT

Airbus Operations GmbH, ...

1. A staircase in an aircraft, wherein the staircase connects at least two decks and the staircase comprises:
a lower staircase end; and
an upper staircase end,
wherein the lower staircase end has at least two lower bearings which connect to a lower deck, and the upper staircase end
has at least two upper bearings which connect to an upper deck, the lower deck and the upper deck being subject to movements
relative to each other during fuselage deformations of the aircraft;

wherein the lower and upper bearings of the staircase are rotatable about an x-axis, a y-axis and a z-axis to compensate for
said movements of the lower and upper decks.

US Pat. No. 9,380,647

HEATING CONTROL UNIT COMPRISING A SENSOR, ICE PROTECTION SYSTEM AND METHOD FOR CONTROLLING A HEATER

AIRBUS OPERATIONS GMBH, ...

1. A heating control unit for an airborne vehicle, comprising:
a controller housing;
a microcontroller arranged within the controller housing, the microcontroller being configured to control a heater;
at least one connection element for mechanically connecting the controller housing to a tube or conduit of the airborne vehicle;
and

a temperature sensor arranged within the controller housing and coupled to the microcontroller, the temperature sensor being
adapted to measure a temperature of the tube or conduit of the airborne vehicle and to relay the respective temperature value
signal to the microcontroller;

wherein an active sensor surface of the temperature sensor forms at least part of an outer surface of the controller housing.

US Pat. No. 9,090,340

HIGH LIFT SYSTEM FOR AN AIRCRAFT

Airbus Operations GmbH, ...

1. A high lift system comprising a main wing, control flaps, and guiding devices for the positioning of the control flaps,
wherein the guiding devices are at least partially provided with a fairing, the high lift system further comprising:
a flow control device for purposes of influencing the flow around the main wing and the control flaps, with at least one inlet
duct running along the main wing chordwise direction each with at least one inlet, which is located on or underneath a lower
surface of the main wing, and at least one outlet duct, which is connected with the at least one inlet duct in a fluid-communicating
manner, and has at least one outlet so that fluid which is streaming into the inlet duct can be discharged through the outlet,
wherein the outlet is located on at least one of an upper surface of the at least one control flap and on an upper side of
the main wing, on the main wing in the rear third of the length of the main wing with respect to the main wing chordwise direction;

wherein the flow control device is arranged at least partially within the fairing, and the inlet of the at least one inlet
duct is facing in opposition to the main wing chordwise direction; and

wherein at least one inlet per inlet duct is arranged in a range starting from the front of the fairing with respect to the
main wing chordwise direction and extending to over one third in the direction of the main wing chordwise direction.

US Pat. No. 9,376,212

AIRCRAFT WITH AT LEAST ONE PRESSURIZED FUSELAGE AREA AND AT LEAST ONE UNPRESSURIZED AREA AND METHOD FOR VENTILATING OF AN UNPRESSURIZED AREA OF AN AIRCRAFT

AIRBUS OPERATIONS GMBH, ...

1. An aircraft, comprising:
at least one fuselage with at least one pressurized fuselage region and at least one non-pressurized region comprising an
air inlet and an air outlet for discharging air to the surrounding of the aircraft from the non-pressurized region; and

at least one system for conditioning the at least one pressurized fuselage region; and an air source from the pressurized
fuselage region connected directly to the air inlet of the non-pressurized region to convey air into the non-pressurized region
to ventilate the non-pressurized region.

US Pat. No. 9,126,686

DRAINING SYSTEM HAVING AN ODOR SEAL FOR A VACUUM TOILET DRAIN SYSTEM

Airbus Operations GmbH, ...

1. A draining system for a vacuum toilet drain system for an aircraft, wherein the draining system comprises:
a first connection device for connection to a drain;
a second connection device for the downstream connection to a drain system; and
an odor seal arranged between the first connection device and the second connection device;
wherein the odor seal comprises a flexible hose with an inlet region, a middle region with two opposing interior wall regions,
and an outlet region, wherein the cross-sectional middle region of the hose, both in a state where there is no pressure difference
between the inlet region and the outlet region, and in a negative-pressure state in the outlet region, is present in a first
cross-sectional shape in which the two interior wall regions lie on top of each other such that the cross-sectional geometry
substantially does not permit a gas exchange, and the hose, as a result of an upstream hydrostatic pressure of the liquid,
is configured to be brought from the first cross-sectional shape to a second cross-sectional shape in which the two interior
wall regions are, at least in part, spaced apart from each other such that the passing of liquid in the downstream direction
is made possible,

wherein the outlet region of the flexible hose is connected to the second connection device,
wherein the hose is configured such that the first cross-sectional shape is taken up as a result of the intrinsic weight of
the hose,

wherein the flexible hose is inclined between the first connection device and the second connection device, and
wherein the weight of the flexible hose is adapted to force opposing interior wall surfaces of the flexible hose towards one
another.

US Pat. No. 9,048,586

EARTH CONNECTION FOR ELECTRICALLY AND MECHANICALLY CONNECTING EARTH WIRES

Airbus Operations GmbH, ...

1. An earth connection for electrically and mechanically connecting a plurality of earth wires to a structure, comprising
an angled element which is formed in one piece and is made of electrically conductive material, which element comprises a
first and a second fastening portion, it being possible to fasten the first fastening portion to the structure and the second
fastening portion comprising a plurality of electrical connections for connecting the earth wires, which connections comprise
socket contact elements which are formed so as to receive pin contact elements of the earth wires, wherein a housing is provided
which surrounds at least the second fastening portion, and wherein the housing comprises a strain relief for relieving a strain
of the earth wires which are connected to the angled element.

US Pat. No. 9,332,671

HEAT DISSIPATION OF POWER ELECTRONICS OF A COOLING UNIT

AIRBUS OPERATIONS GMBH, ...

1. A cooling unit for cooling one or more heat generating devices provided on board of a means of transport, the cooling unit
comprising:
power electronics for providing the cooling unit with electric power,
a heat exchanger for thermally coupling a cooling agent supplied by a central cooling system provided on board of the means
of transport with air supplied in and/or into the cooling unit in order to cool the air by means of the cooling agent to thereby
provide cooling energy in the form of cold air to the one or more heat generating devices, and

a heat pipe for heat dissipation of the power electronics, wherein, at a first portion of the heat pipe, at least some of
a working agent contained inside the heat pipe is in the liquid phase and, at a second portion of the heat pipe, at least
some of the working agent contained inside the heat pipe is in the gas phase, wherein the first portion of the heat pipe is
thermally coupled with the power electronics such that heat from the power electronics is absorbed by evaporating the working
agent being in the liquid phase and wherein the second portion of the heat pipe is thermally coupled with the cooling agent
such that heat is released to the cooling agent by condensing the working agent being in the gas phase.

US Pat. No. 9,371,131

FLOW BODY HAVING A LEADING EDGE, A SURFACE AND AN ACTIVE FLOW CONTROL SYSTEM AND VEHICLE COMPRISING AT LEAST ONE SUCH FLOW BODY AND AN AIR SOURCE

Airbus Operations GmbH, ...

1. A flow body having a surface, a leading edge and an active flow control system,
wherein the active flow control system comprises:
a plurality of openings;
at least one control pressure varying device; and
at least one fluidic actuator with:
an inlet connectable to an air source;
at least first and second outlets; and
at least first and second control pressure ports, wherein the fluidic actuator is configured such that air from the inlet
flows to the at least first and second outlets,

wherein the control pressure varying device comprises:
a flow dividing device with an inlet connectable to a control air source;
at least third and fourth outlets, the third outlet in fluidic communication with the first control pressure port and the
fourth outlet in fluidic communication with the second control pressure port; and

a first and a second feedback line associated with the third and fourth outlet, respectively, adapted for feeding back a part
of a control air flow into the flow dividing device,

wherein the openings are distributed along or parallel to the leading edge in a side-by-side relationship and extend through
the surface, and

wherein the control pressure varying device is adapted to bring about the flow of the fluid at least majoritarily into a respective
one of the first and second outlets, and

wherein each of the first and second outlets is connected to one individual opening of the plurality of openings.

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. 9,085,366

DEVICE FOR LYING OR SITTING ON

AIRBUS OPERATIONS GMBH, ...

1. A device for lying or sitting on, comprising:
a frame;
a covering which is stretched over said frame and defines a surface for lying or sitting on; and
a tensioner structured to interact with at least one of the frame and/or the covering in order to vary, locally, a pre-tensioning
force which acts upon said covering, wherein the tensioner is structured to vary dimensions of the frame in a locally limited
manner, to vary, locally, the pre-tensioning force which acts upon the covering.

US Pat. No. 9,366,618

STIFFENING COMPONENT AND METHOD AS WELL AS COMBING TOOL

AIRBUS OPERATIONS GMBH, ...

1. An arrangement for monitoring the functionality of a structural adhesive layer fabricated between a first surface of a
stiffening component and another component, comprising:
the stiffening component;
the structural adhesive layer fabricated between a first surface of the stiffening component and another component;
a sensor block bonded to a second surface of the stiffening component opposite to the first surface; and
a plurality of air openings and vacuum openings vertically extending through the stiffening component the structural adhesive
layer and the sensor block,

wherein the air openings are interconnected among each other by at least one air channel, and the vacuum openings are interconnected
among each other by at least one vacuum channel, and wherein the air and vacuum channels extend in the sensor block, and wherein
the channels pneumatically operatively interact with the structural adhesive layer between the stiffening components and another
component by way of the air and vacuum air openings, the arrangement further comprising an evaluator unit connected to at
least one of the channels to detect a failure of the structural adhesive layer,

wherein the arrangement further comprises a combing tool having a plurality of borehole pins which are spring-mounted in bearing
boreholes of a housing,

wherein the combing tool is configured to be inserted into the stiffening component such that the borehole pins penetrate
through the structural adhesive layer and scratch a surface of the additional component.

US Pat. No. 9,296,478

AIRCRAFT HAVING AT LEAST TWO AIRCRAFT FUSELAGES AND A FIRST WING ARRANGEMENT WITH AT LEAST TWO WING SECTIONS THAT ARE NOT CONNECTED TO EACH OTHER

AIRBUS OPERATIONS GMBH, ...

1. An aircraft, comprising:
at least two separate aircraft fuselages;
a first wing arrangement with at least two non-connected wing sections that extend outwardly from an exterior of one of the
at least two aircraft fuselages; and

a second wing arranged between the at least two aircraft fuselages,
wherein connecting regions of the first wing arrangement and of the second wing are arranged so as to be offset relative to
each other at least on an X-Z-plane of an aircraft-fixed coordinate system, and

wherein at least one engine is coupled to the second wing, and
wherein the first wing arrangement is arranged in a tail region of the at least two aircraft fuselages, and the second wing
is arranged in a forward-directed region of the aircraft, and the center of gravity of the aircraft is situated between the
first wing arrangement and the second wing.

US Pat. No. 9,216,829

SYSTEM AND METHOD FOR RIGGING A CONTROL SURFACE OF AN AIRCRAFT

AIRBUS OPERATIONS GMBH, ...

1. A system for rigging a control surface of an aircraft that is movable relative to a reference structure of the aircraft
by means of at least one actuator, the system comprising:
a mobile control unit connectable to the at least one actuator,
an input means providing a command signal for moving the control surface, and
an optical rigging apparatus having a first rigging component and a second rigging component, the first rigging component
fixed relative to the reference structure of the aircraft, and the second rigging component fixed relative to the control
surface,

wherein the optical rigging apparatus provides an indication of relative spatial positions of the first and second rigging
components, and the mobile control unit generates an actuator signal for inducing a motion of the control surface based on
the command signal of the input means.

US Pat. No. 9,045,229

SEALING SYSTEM

AIRBUS OPERATIONS GMBH, ...

1. Air-through cooling system for use in an aircraft galley which comprises:
an aircraft cooling system comprising a cooling air outlet that provides cooling air from the aircraft cooling system,
a trolley with a housing, in which a connecting opening is formed, wherein the connecting opening is directly connectable
to the cooling air outlet and serves to supply cooling air into the interior of the trolley or to discharge exhaust air from
the interior of the trolley, and wherein the connecting opening defines a sealing surface; and

a sealing system including:
a closing element which is releasably connectable to the connecting opening of the trolley in order to seal the connecting
opening formed in the housing of the trolley from the environment and which has a fluid passage opening connected in a fluid
conveying manner to the cooling air outlet of the aircraft cooling system,

a receiving device comprising a groove in the closing element of the aircraft cooling system, the groove extending around
the closing element,

a sealing element received in the receiving device of the aircraft cooling system, and
a transfer device which is adapted to transfer the sealing element of the aircraft cooling system between an inactive state,
in which the sealing element is configured such that the sealing element cannot be brought into sealing contact with the sealing
surface of the connecting opening of the trolley facing the receiving device, and an active state, in which the sealing element
is configured such that the sealing element can be brought into sealing contact with the sealing surface of the connecting
opening of the trolley facing the receiving device;

wherein the air-through cooling system is characterized in that the transfer device is coupled to a locking mechanism in such
a manner that the transfer device transfers the sealing element automatically from the inactive state into the active state
when the locking mechanism is in a locked position, in which the locking mechanism latches the closing element, when connected
to the housing, in the housing, and that the transfer device transfers the sealing element automatically from the active state
into the inactive state when the locking mechanism is in an open position, in which the locking mechanism unlatches the closing
element when connected to the housing, from the housing.

US Pat. No. 9,462,700

METHOD FOR PRODUCING AN AIRCRAFT STRUCTURE COMPONENT HAVING AN OUTER SKIN PROVIDED WITH ELECTRIC CONDUCTOR ELEMENTS

Airbus Operations GmbH, ...

1. A method for producing an aircraft structure component having an outer skin provided with electric conductor elements,
the method comprising:
a. providing the aircraft structure component having the outer skin,
b. applying particles of electrically conductive material onto an outer surface of the outer skin of the aircraft structure
component in a predetermined pattern, such that accumulated particles of the electrically conductive material form electric
conductor elements along the outer surface of the outer skin, and

c. applying particles of electrically insulating material onto the outer surface of the outer skin of the aircraft structure
component in a predetermined pattern, such that accumulated particles of the electrically insulating material form an insulating
layer for the electric conductor elements,

wherein the electric conductor elements are formed along the outer skin of the aircraft structure component such that the
electric conductor elements contact rivets received in the outer skin of the aircraft structure component, so that an electric
signal may be guided through the rivets to an inner surface of the outer skin of the aircraft structure component and into
an inside of the aircraft structure component,

wherein the rivets are connected to a computer or to a controlling device.

US Pat. No. 9,120,274

METHOD FOR PRODUCING A HOLLOW COMPONENT AND DEVICE

Airbus Operations GmbH, ...

1. A device for use in producing a hollow component, comprising:
an outer shell, which on its inner face forms an inner contour which is closed along its circumference, wherein said inner
contour forms the outer contour of said hollow component;

a laying device for laying fibre material over the inner contour;
a film capable of covering the inner face of fibre material laid by the laying device;
at least one cover for closing the outer shell in a pressure-tight manner at its end faces;
at least one inner shell arrangeable within the outer shell so as to form an annular gap between the outer shell and the at
least one inner shell that is closed by the at least one cover; and

a pressurization device for introducing a liquid into the annular gap between the at least one inner shell and the film for
a pressurization of the fibre material covered with the film, wherein said liquid is used as a temperature transmission means
to perform at least one of transferring and establishing the temperature necessary for a curing process during producing said
hollow component.

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. 9,375,882

METHOD FOR FORMING A STRUCTURAL COMPONENT OF AN AIRCRAFT OR SPACECRAFT, AND FORMING DEVICE

Airbus Operations GmbH, ...

1. A deformation device to form a structural component of an aircraft or spacecraft, the device comprising:
a tool body comprising a receiver for receiving a braided preform having at least one band;
at least one cutting device for introducing a severing cut at least in portions into the at least one band of the preform
in order to form two band portions of the at least one band; and

at least one deformation tool for guiding along the severing cut in the longitudinal direction of the tool body and of the
preform to deform the two formed band portions of the at least one band into a predetermined shape, the deformation tool comprising
the cutting device, and the deformation tool, in the form of a plough or a snowplough with lateral deformation surfaces which
taper towards each other in the longitudinal direction of the deformation tool at a predetermined angle, wherein they are
connected at a front face of the deformation tool to form the cutting device having a cutting edge, wherein said cutting edge
is oriented substantially perpendicular to a longitudinal axis of the at least one band of the preform and is adapted to introduce
said severing cut along the longitudinal axis of said at least one band of the preform, wherein the deformation surfaces of
the deformation tool each have a web with a channel, the channel merging at its upper end via a channel run-out into a guide
surface and in a downwards direction, the channel is formed with a channel run-in, wherein over a whole length of the deformation
tool, the channel forms together with the guide surface, the channel run-out and the channel run-in on each long side of the
deformation tool a respective deformation surfaces to deform a respective layer band portion.

US Pat. No. 9,073,619

SECURITY DOOR AND SECURITY AREA

Airbus Operations GmbH, ...

1. A security door comprising:
a frame structure having a lateral surface in which a plurality of doorways is constructed, wherein a first doorway constructed
in the lateral surface of the frame structure has a first width along an inner circumference of the frame structure, and wherein
lateral surface portions delimiting the first doorway in a first direction and in a second direction along the inner circumference
of the frame structure have a second width, wherein the second direction opposes the first direction, and

a lock element received in the frame structure,
the lock element comprising a first segment, which is movable along the inner circumference of the frame structure relative
to the frame structure, and a second segment, wherein said second segment is movable independently of the first segment along
the inner circumference of the frame structure relative to the frame structure, and wherein said second segment is movable
to a position in which an end surface of the second segment directly contacts an end surface of the first segment,

wherein the first segment of the lock element is dimensioned so that, in a position in which the first segment closes the
first doorway, the first segment also closes a second doorway adjacent to the first doorway in the first direction along the
inner circumference of the frame structure.

US Pat. No. 9,100,994

HEATING SYSTEM HAVING AT LEAST ONE ELECTROTHERMAL HEATING LAYER, A STRUCTURAL COMPONENT HAVING SUCH A HEATING LAYER, A HEATING METHOD AND A METHOD FOR PRODUCING A SEMI-FINISHED COMPONENT OR A COMPONENT HAVING A HEATING DEVICE

Airbus Operations GmbH, ...

1. A structural component comprising a heating system with at least one energy supply device, wherein the heating system comprises:
a base heating device comprising an insulation layer, with an electrothermal base heating layer arranged thereon which comprises
at least one bundle of rovings, or at least one compound structure of rovings, or at least one ribbon of rovings, and with
an electrical connecting device connecting at least one energy supply device to the base heating layer, wherein the ends of
each roving in each case are connected to an electrode of the electrical connecting device,

an additional heating device comprising an insulation layer with an electrothermal additional heating layer arranged thereon
which comprises at least one bundle of rovings, or at least one compound structure of rovings, or at least one ribbon of rovings,
and with an electrical connecting device connecting the energy supply device to the additional heating layer thereby providing
a cohesive heating effect, the base heating device and the additional heating device are spatially associated with each other,
and in this arrangement the energy supply device is designed in such a manner that in an activation phase current is supplied
during at least a partial period of time to the additional heating layer to heat the structural component in the region of
the additional heating layer to a setpoint temperature, and that, above and beyond the activation phase, current is continuously
supplied to the base heating layer so that the base heating layer generates heat continuously during operation of the heating
system, while the additional heating layer generates heat in the partial period of time.

US Pat. No. 9,354,149

TEST METHOD, TEST RIGS AND CONTROL SYSTEM

Airbus Operations GmbH, ...

1. A method for load relieving a test object, wherein a load is applied by a multiplicity of hydraulic means positioned side
by side, each introducing a partial load into the test object such that the test object has a minimum deflection in an area
close to its fixation and a maximum deflection in an area far away from the fixation, comprising the step of reducing the
load sequentially from the maximum deflection to the minimum deflection.

US Pat. No. 9,252,420

METHOD AND DEVICE FOR FORMING AN ELECTROLYTE FILM ON AN ELECTRODE SURFACE

Airbus Operations GmbH, ...

1. A method for forming an electrolyte film on an electrode surface, comprising:
atomizing, by an atomizer, a liquid electrolyte contained in an electrolyte reservoir enclosed by a mist chamber into the
mist chamber located above the electrolyte reservoir to create an electrolyte mist, the atomizer being configured to provide
communication between the electrolyte reservoir and the mist chamber, wherein the electrolyte reservoir, the mist chamber,
and the chamber containing the electrode surface are housed within a closed chamber;

issuing the electrolyte mist from the mist chamber by way of a mist outlet and subsequently flowing over the electrode surface
aligned behind the opening diagonally downwards and affixed at a predeterminable angle of inclination by a holder; and

as a result of the aforesaid, forming an electrolyte film on the electrode surface,
wherein the thickness of the electrolyte film is set by the angle of inclination of the electrode surface.

US Pat. No. 9,144,949

MOLDING TOOL AND METHOD FOR MANUFACTURING A FIBER REINFORCED PLASTIC AERODYNAMIC AIRCRAFT COMPONENT

Airbus Operations GmbH, ...

1. A molding tool for manufacturing a fiber-reinforced plastic aerodynamic aircraft component comprising:
first and second core parts each having a triangular cross section and configured for arrangement along a first set of opposed
edges of a bay disposed within the fiber reinforced plastic aerodynamic aircraft component, the bay delimited by an outer
skin and a plurality of spars; and

third and fourth core parts each having a pentagonal cross section and being configured to interact with a second set of opposed
edges of the bay and fill a diagonally extending space formed between the first and second core parts when the first and second
core parts are arranged along the first set of opposed edges of the bay, the third core part having surface grooves defining
a first ramp-shaped chamfer corresponding to a second ramp-shaped chamfer of a skin reinforcement of the outer skin or spar
reinforcement of one of the plurality of spars, the first ramp-shaped chamfer being sloped such that the second ramp-shaped
chamfer allows removal of the third core part from the diagonally extending space in a direction transverse to the second
ramp-shaped chamfer.

US Pat. No. 9,156,543

CONTROL SYSTEM FOR AN AIRCRAFT

Airbus Operations SAS, T...

1. A control system for at least one controlled device of an aircraft, the control system being embedded onboard the aircraft
and comprising:
at least two distinct communication networks; and
at least one control unit associated with this at least one controlled device, this control unit being connected to at least
one of the said communication networks,

the control system being configured to determine and provide control commands to the controlled device, the determination
of the control commands corresponding to a first function of the aircraft having a DAL-A quality assurance level requirement,

the control system further comprising:
a set of at least three physical units each comprising an electrical power supply and a network interface device connected
to at least one of the communication networks of the aircraft, in which:

the electrical power supplies of the various physical units being of at least three different types;
the network interface devices of the various physical units being of at least three different types;
each of the physical units comprising at least two computers each comprising an operating system;
the various computers of the various units being of at least two different types;
the operating systems of the various computers being of at least two different types;
at least six of the computers being configured to independently determine control commands for the said controlled device,
these control commands corresponding to the said first function;

the various computers each having at least one of a DAL-C, DAL-D or DAL-E hardware and software quality assurance level; and
a selection logic unit whose hardware and software quality assurance level is DAL-A, the selection logic unit being connected
to the at least two communication networks and being configured to select valid control commands from among the control commands
determined by the computers,
the control unit associated with the said controlled device being configured to control the controlled device as a function
of the valid control commands selected by the selection logic unit.

US Pat. No. 9,139,994

TOILET SYSTEM WITH DECENTRALIZED FLUSHING FLUID SOURCE

AIRBUS OPERATIONS GMBH, ...

1. A toilet system for a vehicle, comprising:
a first toilet unit configured for installation in the vehicle;
a second toilet unit configured for installation in the vehicle;
a first decentralized supply device comprising a first flushing agent tank configured to supply the first toilet unit with
a first flushing agent, the first decentralized supply device including a housing and a first fresh-water tank configured
to supply a wash basin associated with the first toilet unit with fresh water, the first fresh-water tank and the first flushing
agent tank arranged in the housing;

a second decentralized supply device comprising a second flushing agent tank configured to supply the second toilet unit with
a second flushing agent; and

a central disposal device configured to receive wastewater from the first toilet unit and from the second toilet unit;
wherein the first flushing agent comprises gray water and the wash basin is configured to supply fresh water that has been
used in the wash basin as gray water to the first flushing agent tank.

US Pat. No. 9,451,732

MULTISTAGE COOLING OF ELECTRONIC COMPONENTS OF AN AIRCRAFT

Airbus Operations GmbH, ...

1. A multistage cooling system for an aircraft electronic system including a plurality of electronic components, the multistate
cooling system comprising,
a container containing the aircraft electronic system therein,
a heat exchanger, and
an inner circuit, partially defined by the container, in which a liquid or gas inner coolant in direct contact with at least
one of the plurality of electronic components of the aircraft electronic system circulates through the heat exchanger, the
inner circuit configured such that the inner coolant flows from the heat exchanger in the direction of the container,

an outer circuit in which a liquid outer coolant circulates through the heat exchanger,
a liquid cooling system, coupled to the outer circuit, to cool the liquid outer coolant, and
a valve, connectable between the outer circuit and a further water container, via which liquid outer coolant lost from the
outer circuit is at least partially replaced by water from the further water container during operation of the aircraft electronic
system,

wherein the heat exchanger is configured to deliver heat supplied thereto by the inner coolant to the liquid outer coolant
supplied thereto from outside of the aircraft electronic system,

and wherein the liquid outer coolant is fresh water supplied from a fresh water container which flows through the outer circuit
and to the further water container.

US Pat. No. 9,162,773

AIRCRAFT COMPRISING A REVERSIBLE ROTARY ELECTRICAL MACHINE

AIRBUS OPERATIONS SAS, T...

1. An aircraft comprising:
at least one rotary electrical machine;
at least one wheel for imparting movement to a stream of air, linked to said at least one rotary electrical machine;
at least one system to cool;
at least one first ventilation duct configured to supply said wheel with air;
an electricity distribution network;
at least one power converter connected to said at least one rotary electrical machine and to said electricity distribution
network; and

at least one control circuit configured to control said at least one power converter;
at least one second ventilation duct in which are disposed said at least one rotary electrical machine and at least partially
said at least one system to cool;

wherein said at least one rotary electrical machine is reversible and said at least one power converter is reversible, said
at least one control circuit being configured to control said at least one reversible power converter for:

in a first motor operating mode of said at least one reversible rotary electrical machine, taking a supply current from said
electricity distribution network to electrically supply said reversible rotary electrical machine and thereby drive said at
least one wheel for imparting movement to a stream of air, by virtue of which said at least one system to cool is cooled;
and

in a second alternator operating mode of said at least one reversible rotary electrical machine, in which a stream of air
flows in said at least one first ventilation duct and imparts movement to said at least one wheel, providing supply power
to said electricity distribution network, which power is generated by said reversible rotary electrical machine which is driven
by said wheel,

wherein said at least one first ventilation duct includes a device for regulating a rate of flow of the stream of air entering
that first duct, and the device for regulating is positioned at an entrance to the first ventilation duct, and

wherein said first ventilation duct is juxtaposed against said second ventilation duct and comprises an air inlet and an opposite
air outlet, which air outlet discharges into said second ventilation duct.

US Pat. No. 9,283,897

SEAT WITH UNIVERSAL DEVICE FOR RECEIVING AN ELECTRONIC GADGET FOR AN AIRCRAFT OR SPACECRAFT

Airbus Operations GmbH, ...

1. A seat for an aircraft or spacecraft comprising:
a headrest;
a receiving device integrated into said headrest, said receiving device comprising:
an upper rail spaced apart from and parallel to a lower rail, said upper rail and said lower rail on one end being joined
by a connecting element, said receiving device further comprising a pivotable closing element provided on a second end of
said upper rail and said lower rail, said pivotable closing element configured to be pivoted about an axis to a first position
wherein an opening is formed on said second end of said upper rail and said lower rail and a second position wherein the pivotable
closing element forms a closed side of the receiving device;

a safety screen;
said receiving device being configured to releasably receive sideways through said opening an electronic device fitted with
a screen, said electronic device being one of a tablet personal computer (PC) or a PDA such that said screen is configured
to be visible through said safety screen but inaccessible from an exterior of said seat.

US Pat. No. 9,266,601

METHOD AND SYSTEM FOR EMERGENCY VENTILATION OF AN AIRCRAFT CABIN IN THE CASE OF A LEAK IN THE AREA OF AN AIR MIXER

Airbus Operations GmbH, ...

7. A system for emergency ventilation of an aircraft cabin in an aircraft, comprising:
an electronic control unit, which detects a leak in the area of an air mixer of an aircraft air conditioning system, through
which air escapes from the air mixer into an aircraft area, the aircraft area being adjacent to the air mixer and within the
aircraft, and which electronically controls an emergency air flap, which in a closed position prevents an air exchange between
the aircraft area adjacent the air mixer and the aircraft cabin, into an open position, which allows air escaping from the
air mixer to flow out of the aircraft area adjacent the air mixer into the aircraft cabin, and

a device that causes air to be conveyed from the aircraft area adjacent the air mixer through the open emergency air flap
into the aircraft cabin.

US Pat. No. 9,227,779

CARGO CONTAINER FOR AN AIRCRAFT

Airbus Operations GmbH, ...

1. A cargo container for accommodating transport goods and for being arranged in a cargo compartment of an aircraft, the cargo
container comprising:
a housing configured to be closed so that the housing is airtight; and
an internal coating;
wherein the internal coating is fire resistant and is arranged on an internal surface of the housing;
wherein the housing comprises a first receiving space for a fire sensor and a fire sensor arranged therein;
wherein the housing comprises a second receiving space for a fire extinguishing agent and a fire extinguishing agent arranged
therein,

wherein the housing comprises a discharge element for the fire extinguishing agent, wherein the discharge element for the
fire extinguishing agent is configured in case of a fire in the cargo container to discharge the fire extinguishing agent
into an internal space of the housing, and wherein the first receiving space for the fire sensor, the second receiving space
for the fire extinguishing agent and the discharge element for the fire extinguishing agent are arranged in the internal space
of the housing.

US Pat. No. 9,260,190

SLIDING FLIGHT ATTENDANT SEAT

Airbus Operations GmbH, ...

1. A flight attendant seat for an aircraft, said seat comprising:
a backrest element;
a seat element; and
a guiding apparatus for holding the flight attendant seat in a starting position, wherein the guiding apparatus is also configured
so that said flight attendant seat is movable, in a direction transverse to a longitudinal axis of the backrest element, from
the starting position into at least one end position,

wherein the guiding apparatus is inclined at an obliquity relative to a normal of the longitudinal axis of the backrest element,
and

wherein the guiding apparatus is configured so that the flight attendant seat moves back automatically into the starting position
from the at least one end position due to a downhill force resulting from the obliquity of the guiding apparatus.

US Pat. No. 9,284,036

FLOOR PLATE FOR COVERING A FLOOR FRAMEWORK IN AN AIRCRAFT

Airbus Operations GmbH, ...

1. A floor plate for covering a floor framework in an aircraft, wherein the floor framework comprises a plurality of transverse
beams and with a plurality of longitudinal profiles extending at an angle of about 90° plurality of to the transverse beams,
the floor plate comprising:
at least one connecting point for fastening a sub-assembly to the floor plate independently of an installation point of the
floor plate to the floor framework,

a system port arranged in a center region of the floor plate for connecting the sub-assembly on the floor plate to a plurality
of systems on board the aircraft comprising sockets and couplings,

wherein the system port is integrated directly into the floor plate, and is configured to form a universal interfacing point
between the sub-assembly and the plurality of systems on board the aircraft, and

at least one of a plug and a coupling integrated into an underside of the sub-assembly capable of automatically making connections
or contacts to the sockets and couplings of the system port,

wherein the floor plate is configured to bear on the floor framework of the aircraft on at least four longitudinal profiles,
and

wherein the sub-assembly is directly fastenable to the floor plate, and the floor plate is connectable to the floor framework
with fastening devices.

US Pat. No. 9,274,523

AIRCRAFT WITH A DEVICE FOR DIRECTIONALLY STABILIZING THE AIRCRAFT, COMPUTER PROGRAM PRODUCT AND METHOD FOR DIRECTIONALLY STABILIZING THE AIRCRAFT

Airbus Operations GmbH, ...

1. A method for reducing yawing motions of an aircraft in-flight,
wherein a spoiler adjustment drive of a spoiler and a second regulating flap adjustment drive of a second regulating flap
of the same respective airfoil are adjusted in a time segment such that a motion of the spoiler being adjusted and a motion
of the second regulating flap of the same airfoil deflect in mutually opposite directions in the time segment,

identifying a predetermined characteristic of a Dutch Roll by comparing characteristics of yawing motions of the aircraft
with target specifications, and

adjusting the spoiler and the second regulating flap on the same airfoil in mutually opposite directions to counteract the
yawing motions of the aircraft.

US Pat. No. 9,212,680

TIE BAR FOR PURPOSES OF CONNECTING EQUIPMENT FITTING OF AN EQUIPMENT MODULE, IN PARTICULAR AN OVERHEAD COMPARTMENT, TO A STRUCTURE FITTING OF A FUSELAGE CELL STRUCTURE OF AN AERONAUTICAL VEHICLE

Airbus Operations GmbH, ...

1. A tie bar for purposes of connecting an equipment fitting of an equipment module to a structure fitting of a fuselage cell
structure of an aeronautical vehicle, comprising:
a fork head at each end of the tie bar, each fork head having two fork head holes for purposes of accommodating a bolt, and
a spacing between the fork heads that can be continuously adjusted,

the fork head holes of at least one fork head having a captive bushing for purposes of sound and vibration decoupling,
wherein each bushing has a hollow cylindrical base body having a shank with a peripheral annular bead in at least some sections
disposed approximately on the central region of the shank height of the base body such that the peripheral bead causes a snapping
into place of the bushing into the fork head holes, and

a structure fitting disposed between the fork heads and retained between the bushings, the structure fitting having cooperating
arcuate surfaces, wherein a relative movement between the arcuate surfaces allows an angular displacement between the structure
fitting and the associated fork head.

US Pat. No. 9,475,580

VEHICLE COMPRISING A TRANSPORT ARRANGEMENT

Airbus Operations GmbH, ...

1. A vehicle comprising a passenger compartment and a cargo compartment disposed below the passenger compartment and separated
from the passenger compartment by a floor structure having a through hole communicating the passenger compartment with the
cargo compartment, the vehicle further comprising:
a cargo unit comprising:
a housing including a base plate, a sidewall arrangement extending from the base plate and an upper cover and defining an
interior cavity, wherein the base plate defines a horizontal plane of the cargo unit and extends perpendicularly to a vertical
direction of the cargo unit, and the upper cover includes an access aperture;

at least one storage rack arrangement disposed in the cavity and adapted for storing a plurality of objects;
a transport arrangement disposed in the cavity and operable for selectively transporting objects between the storage rack
arrangement and a predetermined transfer position in the cavity, wherein the transport arrangement comprises a conveying apparatus
and a control unit adapted for automatically controlling and operating the conveying apparatus;

a mounting means disposed in the cargo compartment and adapted for fixedly or releasably securing the cargo unit in a predetermined
operating position inside the cargo compartment, in which the access aperture in the upper cover of the cargo unit is disposed
adjacent to and in alignment with the through hole in the floor structure; and

a lift apparatus comprising a gripping device suspended from a gripping device mounting means, wherein the lift apparatus
is disposed at least partially in the passenger compartment and arranged and adapted such that the lift apparatus is operable
to move the gripping device in a direction perpendicular to the floor structure and, when the cargo unit is secured by the
mounting means in the operating position, to thereby convey objects in the direction perpendicular to the floor structure
from the transfer position in the cargo unit through the access aperture in the upper cover and the through hole in the floor
structure between the cargo compartment and the passenger compartment and vice versa,

wherein the transport arrangement comprises a horizontal guide means defining a linear horizontal transport path extending
perpendicularly to the vertical direction of the cargo unit and supporting the conveying apparatus such that the conveying
apparatus is movable in a guided manner along the horizontal transport path, and a horizontal drive means operable for selectively
moving the conveying apparatus along the horizontal transport path,

wherein the conveying apparatus comprises at least one table unit adapted for supporting an object, a vertical guide means
defining a linear vertical transport path extending parallel to the vertical direction of the cargo unit and supporting the
at least one table unit such that the at least one table unit is movable in a guided manner along the vertical transport path,
and a vertical drive means operable for selectively moving the at least one table unit along the vertical transport path,

wherein each of the at least one storage rack arrangement comprises a plurality of rack compartments each adapted for storing
an object and having an access opening through which objects are insertable into and removable from the respective rack compartment,
wherein the access openings are provided in an access side of the storage rack arrangement extending parallel to the horizontal
transport path,

wherein the transport arrangement is disposed facing the access side of each of the at least one storage rack arrangement
in such a manner that by operating the horizontal and vertical drive means the at least one table unit is selectively movable
in front of each of the rack compartments and operable to move an object from the respective rack compartment onto the at
least one table unit and support the object on the at least one table unit and to release the object supported on the at least
one table unit and move the object from the at least one table unit into the respective rack compartment, and

wherein the gripping device can be selectively switched between a gripping state, in which, with respect to the gripping device
mounting means, the gripping device is movable along and rotatable about two perpendicular axes each perpendicular to the
direction perpendicular to the floor structure, and a lift state, in which the gripping device is locked in a predetermined
lift position against movement with respect to the gripping device mounting means.

US Pat. No. 9,266,605

AIRCRAFT HAVING A VERTICAL LIFT SYSTEM

Airbus Operations GmbH, ...

1. An aircraft having a high lift system, comprising:
a flight control computer installed in a cockpit of the aircraft;
at least one high lift body disposed on each respective wing of the aircraft, each high lift body being adjustable relative
to the respective aircraft wing;

a drive device coupled with the high lift bodies, which is configured such that it adjusts the high lift bodies between a
retracted position and an extended position on the basis of activation commands;

an activation device connected to the drive device via an analog data connection and including an activation function that
generates activation commands for setting an adjustment state of the high lift bodies and that generates monitoring and locking
commands for locking the high lift bodies in the event of a system failure, wherein the activation device is connected via
a digital data connection to the flight control computer for receiving flight state-related data;

an input device arranged in the cockpit of the aircraft, the input device receiving input of target commands for adjusting
the high lift bodies;

sensors configured to detect an adjustment state of the high lift bodies which are connected via analog signal lines to the
activation device; and
wherein
the input device is connected via a digital data connection to the activation device for the transmission of target commands
for adjusting the high lift bodies; and

the activation device of the high lift system is installed in a payload area of the aircraft's fuselage and in an area extending,
when viewed in a longitudinal direction of the aircraft's fuselage, from a location which is spaced apart from a front side
of a wingbox by a distance of one third of a fuselage length extending from the front side of the wingbox to a tip of the
aircraft, as far as a location which is spaced apart from a rear side of the wingbox by a distance of one third of a fuselage
length extending from the rear side of the wingbox to a fuselage end at a tail end of the aircraft, such that the flight control
computer and the activation device are installed in separate areas of the aircraft's fuselage in a decentralized arrangement.

US Pat. No. 9,243,151

AFTERGLOW COATING FOR CABINS

Airbus Operations GmbH, ...

1. An afterglow coating comprising:
a clear varnish and a photoluminescent pigment,
wherein the pigment comprises a white or whitish afterglow color and is distributed in the clear varnish, and
wherein the photoluminescent pigment is a mixture of at least two alkaline earth aluminates consisting of MeAl2O4:Eu, wherein Me is an alkaline earth metal selected from the group consisting of calcium, magnesium, strontium and barium.

US Pat. No. 9,199,717

CENTER FUSELAGE BELLOWS

AIRBUS OPERATIONS GMBH, ...

1. A sealing assembly comprising:
an elongate bellows body having a first end portion and a second end portion coupled together to form a closed ring and the
ring forms a bellows, the bellows configured to attach to an airframe of an aircraft, the bellows further configured to seal
off a gap in the airframe to allow pressurizing the airframe, when attached to the airframe;

a first mounting member;
a second mounting member;
a first side portion of the bellows configured to attach via the first mounting member to the airframe;
a first contoured portion of the first mounting member configured to accommodate the first side portion of the bellows;
a mounting portion of the first mounting member configured to attach to the airframe;
a second side portion of the bellows configured to attach via the second mounting member to the airframe;
a second contoured portion of the second mounting member configured to accommodate the second side portion of the bellows;
and

a second mounting portion of the second mounting member configured to attach to the airframe,
wherein the first contoured portion and the second contoured portion each comprise a crimped terminal portion, the crimped
terminal portion crimped to curl away from the bellows when the bellows is attached to the airframe.

US Pat. No. 9,145,196

AIRCRAFT FUSELAGE WITH DOOR STOPPERS ATTACHED TO A DOOR FRAME BULKHEAD

Airbus Operations GmbH, ...

1. An aircraft fuselage comprising:
at least one opening configured to be closed by a flap or a door,
wherein the flap or the door is configured to abut against at least one door stopper arranged on a fuselage-side door frame
bulkhead and to transfer impact forces into an intermediate costal for diversion into an aircraft structure encompassing bulkheads,

wherein the door frame bulkhead comprises an opening, through which an impact section of the door stopper extends,
wherein a fastening plate section adjoining the door stopper abuts a rear side of the door frame bulkhead interacting with
means for directly introducing the impact forces from the door stopper into the intermediate costal.

US Pat. No. 9,334,577

MULTIFUNCTIONAL COATING OF ALUMINIUM PIECES

Airbus Operations GmbH, ...

1. A method for applying a multifunctional coating to the surface of an untreated workpiece made of aluminium or of an aluminium
alloy, wherein the method comprises the following:
a) treating a surface of the untreated workpiece made of aluminium or of an aluminium alloy with an acidic solution which
contains rare-earth metal ions, to produce a treated workpiece with a first oxide layer thereon, wherein the acidic solution
has a pH of <1 and the treating of step a) occurs at a processing temperature of 50° C. to 80° C; and

b) anodising the treated workpiece to produce a second oxide layer, the treated workpiece serving as anode of an electrical
cell in the presence of an aqueous sulphuric acid-containing solution and the first oxide layer produced in step a) being
retained, wherein the anodising of step b) occurs at a processing temperature of 15 to 35° C.

US Pat. No. 9,221,212

METHOD FOR PRODUCTION OF COMPOSITE PREFORM

AIRBUS OPERATIONS GMBH, ...

1. A method of producing a composite preform having a preform profile of variable profile height or width, the method comprising:
providing a plurality of first fibre layers arranged upon or overlapping one another substantially parallel to a primary plane;
inserting at least one second fibre layer between two of the plurality of first fibre layers at an edge region of the preform
profile, whereby the second fibre layer extends substantially parallel to the first fibre layers; and

positioning the edge region of the preform profile, and thereby respective edge regions of the plurality of first fibre layers,
out of the primary plane to set or determine a dimension of the preform profile in the primary plane;

wherein inserting at least one second fibre layer between two of the plurality of first fibre layers at the edge region of
the preform profile comprises: guiding or feeding the at least one second fibre layer via a guide member arranged between
said two of the plurality of first fibre layers at the edge region of the preform profile.

US Pat. No. 9,175,695

FLUID-COOLING DEVICE FOR A TURBINE ENGINE PROPULSIVE UNIT

AIRBUS OPERATIONS S.A.S.,...

1. A fluid cooling device for a propulsion unit of a propfan type aircraft, said propulsion unit comprising a turbomachine
that drives in rotation at least one rotor comprising a plurality of fan blades, said turbomachine being supplied with outside
air by an air inlet, said turbomachine comprising a compressor, disposed upstream of the rotor and the fan blades, with at
least two stages, and generating heating of a lubricant during operation thereof, the fluid cooling device comprising:
a pressurized air intake;
a volumetric/surface cooler which cools the lubricant;
an air vein which conveys pressurized air to the cooler;
a regulator valve which regulates a flow of pressurized air into the air vein; and
a controller configured to control the regulator valve,
wherein the cooler includes
a matrix body provided with a plurality of ducts for a cooling agent, said ducts extending along a first inner surface of
the matrix body up to a second outer surface of the matrix body, and

a set of fins extending from the outer surface of the matrix body towards an outside of the propulsion unit, and oriented
mainly parallel to a direction of airflow when the aircraft is in flight,

wherein the cooler is disposed downstream of the air inlet, and disposed upstream of the fan blades such that the set of fins
is disposed upstream of the fan blades, and

wherein the controller is configured to set the regulator valve in an open position when a speed of the aircraft is below
a first predetermined value such that the pressurized air flowing into the air vein passes through the ducts of the matrix
body, and the controller is configured to set the regulator valve in a closed position when the speed of the aircraft is above
a second predetermined value and an outside temperature is below a predetermined temperature.

US Pat. No. 9,139,282

FASTENING ARRANGEMENT FOR ATTACHING A FLOOR

AIRBUS OPERATIONS GMBH, ...

1. A fastening arrangement for attaching a floor to a support structure, the fasting arrangement comprising:
at least one cross beam;
a floor panel of the floor deposited on the at least one cross beam;
a fork bolt attached to the at least one cross beam via a barrel nut, the fork bolt having a foot with a thread to be screwed
into a thread of the barrel nut; and

a lug bolt rotatably connected to the fork bolt and adapted for attaching an attachment element to the at least one cross
beam,

wherein the fork bolt has a head with a slit for accommodating an end of the lug bolt, such that the lug bolt is rotatable
in the direction of the slit,

wherein the floor panel has an opening for accommodating the head of the fork bolt, such that the floor panel is attached
to the at least one cross beam by the head of the fork bolt, and

wherein the head of the fork bolt is rotatable in the opening of the floor panel for screwing the fork bolt into the barrel
nut by rotating the lug bolt.

US Pat. No. 9,187,167

METHOD FOR JOINING TWO FUSELAGE SECTIONS BY CREATING A TRANSVERSE BUTT JOINT AS WELL AS TRANSVERSE BUTT JOINT CONNECTION

Airbus Operations GmbH, ...

1. A method for connecting two fuselage sections formed from a fibre-reinforced plastics material, with a number of stringers
arranged uniformly spaced out parallel to one another on an inside of an outer skin to produce a transverse butt joint, the
method comprising the steps of:
a) aligning a first and a second fuselage section relative to one another,
b) connecting at least one transverse butt strap to an end area of the first fuselage section,
c) only heating at least one end area of the second fuselage section, which is formed from a fibre-reinforced thermosoftening
plastics material, until a temperature corresponding at least to a softening temperature of the fibre-reinforced thermosoftening
plastics material is reached,

d) pushing the at least one heated end area of the second fuselage section onto the transverse butt strap connected to the
first fuselage section,

e) compensating for tolerances by one or more of expanding or compressing the heated end area of the second fuselage section,
and

f) joining the two fuselage sections together.

US Pat. No. 9,149,990

APPARATUS FOR THE FORMING OF A LAY-UP OF FIBRE COMPOSITE MATERIAL

Airbus Operations GmbH, ...

1. An apparatus to form a lay-up of a carbon fibre reinforced plastic composite material, said apparatus comprising:
a tool carrier;
at least one forming tool having a surface contour corresponding to a desired geometry of a formed lay-up of said fibre composite
material; releasably fastened to the tool carrier by at least one of a vacuum clamping device and a locking device;

said locking device comprising at least one locking element, configured to provide a locking state for the forming tool in
one plane, wherein during the locking state the forming tool is not movable in the plane but is movable in a direction perpendicular
to the plane;

a device for generating microwaves,
wherein a plurality of carbon fibres of said carbon fibre reinforced plastic composite material absorb microwaves;
wherein the device for generating said microwaves is configured such that to feed said microwaves directly into said plurality
of microwave absorbing carbon fibres of said carbon fibre composite material, thereby heating said plurality of microwave
absorbing fibres;

wherein said heated plurality of microwave absorbing carbon fibers are adapted to heat and softening said lay-up; and
wherein said apparatus is formed at least from a non microwave absorbing material.

US Pat. No. 9,888,604

SUPPORT RACK FOR AT LEAST ONE ITEM OF AIRCRAFT ELECTRONICS, CORRESPONDING SUPPORT DEVICE AND AIRCRAFT

Airbus Operations (S.A.S....

1. A support rack for at least one item of aircraft electronics, wherein the support rack comprises:
a rectangular frame formed by four essentially straight beam segments and having an essentially planar upper surface; and
four feet each having an essentially planar upper surface which is in the essentially planar upper surface of the rectangular
frame, wherein each of said feet are joined to a corner of said frame, and each of said feet extend in a direction forming
an angle between 90° and 180° with a lengthwise direction of each of the beam segments of said frame forming the corner of
the frame, wherein the rectangular frame, the four essentially straight beam segments and the feet are a one-piece assembly;

a first set of holes configured to attach at least one item of electronic equipment to the rectangular frame, wherein the
first set of holes are in the essentially planar upper surfaces of said rectangular frame or of said feet, and

at least one second set of attachment holes configured to anchor the rectangular frame to the structure of an aircraft, wherein
the at least one second set of attachment holes are in a sidewall of one of the beam segments or the feet and in a surface
of the support rack out of the essentially planar upper surface and include a first group of holes and a second group of holes
such that the first group of holes are a first distance from the upper surface less than a distance between the upper surface
and a bottom edge of a narrowest portion of a sidewall of the one of the beam segments and the second group of holes are a
second distance from the upper surface greater than the distance between the upper surface and the bottom edge of the narrowest
portion of the sidewall of the one of the beam segments.

US Pat. No. 9,315,255

AIRCRAFT COMPRISING A DEVICE FOR INFLUENCING THE DIRECTIONAL STABILITY OF THE AIRCRAFT, AND A METHOD FOR INFLUENCING THE DIRECTIONAL STABILITY OF THE AIRCRAFT

Airbus Operations GmbH, ...

1. An aircraft comprising a device for influencing the directional stability of the aircraft, with the aircraft comprising:
wings with ailerons and a rudder, with the device for influencing the directional stability of the aircraft comprising:
a control-input device for inputting control demands for controlling the flight path of the aircraft,
a flight control device that is functionally connected with the control-input device,
a sensor device that is functionally connected with the flight control device, for acquiring the rotation rates, including
the yaw rates, of the aircraft,

in each case at least one actuator, which is functionally connected with the flight control device, for adjusting the ailerons
and for adjusting the rudder, wherein the flight control device comprises a control function that is designed in such a manner
that from the control demands and the rotation rates said flight control device generates adjusting commands for the actuators
for controlling the aircraft and transmits them to said actuators, wherein:

the aircraft comprises two tail-mounted flaps, situated behind the connecting region of the wings and on opposite sides of
the fuselage, each tail-mounted flap being coupled to an actuator that is functionally connected with the flight control device
for moving the tail-mounted flaps between a retracted and an extended position,

the control function is designed in such a manner that for lateral control of the aircraft, on the basis of rotation rates
about a z-axis of the aircraft acquired by the sensor device, the control function generates commands for actuating of at
least one of the tail-mounted flaps and transmits the commands to said actuator for actuating the tail-mounted flaps such
that a moment about the z-axis of the aircraft is effected, and

in response to a deflection of at least one of the tail-mounted flaps, additional drag is generated which in turn generates
the moment about the z-axis of the aircraft.

US Pat. No. 9,284,658

PROCESS FOR SELECTIVE ISOLATION OF CFRP PARTS BY ELECTRODEPOSITION COATINGS

Airbus Operations GmbH, ...

1. A process for repairing defects on a carbon fiber reinforced plastic, CFRP, component, wherein defects on the CFRP component
are selectively repaired by electrodeposition coating using an insulating coating material, wherein the insulating coating
material is deposited specifically at locations where carbon fibers of the CFRP component are exposed to the surrounding on
the CFRP component and are near the surface of the CFRP component.

US Pat. No. 9,227,730

SYSTEM AND METHOD FOR AIR CONDITIONING AT LEAST ONE PARTIAL REGION OF AN AIRPLANE

Airbus Operations GmbH, ...

1. An aircraft, comprising:
a system for air conditioning at least one partial region of the aircraft, the system comprising:
an air providing device for providing cooled air to be supplied to a region of the aircraft to be ventilated at a desired
temperature and pressure;

a supply air duct which is connected at a first end to the air providing device;
an air inlet which is connected to a second end of the supply air duct and opens near a floor of the aircraft into the aircraft
region to be ventilated;

a control device which is set up to ensure at least in selected operational situations of the air conditioning system that
the cooled air provided by the air providing device enters the aircraft region to be ventilated via the air inlet at a speed
of 0.1 to 0.5 meters/second such that the cooled air is distributed in the aircraft region to be ventilated over the entire
floor area and forms a climatization air layer near the floor and then rises at heat sources present in the aircraft region
to be ventilated due to free convection, thereby ventilating the aircraft region to be ventilated by the principle of displacement
ventilation, wherein the control device further is adapted such that the cooled air provided by the air providing device enters
the aircraft region to be ventilated via the air inlet at such a temperature that the desired temperature is achieved in the
aircraft region to be ventilated;

an air outlet for removing exhaust air from the aircraft region to be ventilated, the air outlet arranged in the region of
a ceiling of the aircraft region to be ventilated; and

a pressure regulating valve for setting a desired pressure in the aircraft region to be ventilated, the pressure regulating
valve connecting the pressurized aircraft region to be ventilated to the outside atmosphere via the air outlet, and the pressure
regulating valve arranged in a side region of an aircraft fuselage upper shell or an aircraft fuselage lower shell.

US Pat. No. 9,272,788

AIRCRAFT COOLING SYSTEM AND METHOD FOR OPERATING AN AIRCRAFT COOLING SYSTEM

Airbus Operations GmbH, ...

1. An aircraft cooling system comprising:
a cooler comprising a cold transfer circuit, in which a cold transfer medium circulates, and which is adapted to supply cooling
energy to an aircraft device to be cooled, and

a heat transfer arrangement comprising a heat transfer circuit, in which a heat transfer medium circulates and which is thermally
coupled to the heat transfer circuit of the cooler via a heat exchanger, in order to absorb waste heat generated by the cooler
and transfer it to a cabin air extraction system,

the heat transfer arrangement further comprising at least one heat pump which is adapted to bring about an increase of the
heat energy transfer from the cold transfer medium circulating in the cold transfer circuit of the cooler to the heat transfer
medium circulating in the heat transfer circuit, at least in certain operating phases of the aircraft cooling system.

US Pat. No. 9,199,716

AIRCRAFT DOOR SYSTEM HAVING A DOOR ACTUATOR AND MOVEMENT DETECTOR

Airbus Operations GmbH, ...

1. A door system for an aircraft or spacecraft, the door system comprising:
a door;
an actuator for actuating the door;
a door frame which receives the door in a closed state; and
a door fixing arm, which is pivotably attached to the door frame about a first hinge and is pivotably attached to the door
about a second hinge;

wherein the actuator comprises:
an actuator drive which moves the door in relation to the aircraft or spacecraft by driving an output shaft, which is rotatably
mounted on the door fixing arm and a pivot axis of the output shaft is coaxial with a pivot axis of the first hinge or the
second hinge;

a detection device which determines movement information of at least one of the door and the actuator;
an actuator control unit which controls the actuator based on the movement information; and
a common actuator housing which surrounds the actuator drive and the actuator control unit, wherein the common actuator housing
is connected to the door fixing arm in a non-rotational manner by a fastening bracket at an upper end of the common actuator
housing, and wherein the output shaft is protruding from the upper end of the common actuator housing and is mounted on the
door fixing arm in an upper bearing.

US Pat. No. 10,543,922

FLIGHT ATTENDANT SEAT, SYSTEM COMPRISING FLIGHT ATTENDANT SEAT AS WELL AS ARRANGEMENT AND AIRCRAFT AREA COMPRISING SYSTEM

AIRBUS OPERATIONS GMBH, ...

1. A flight attendant seat comprising:a carrier device having guiding means with opposed first and second ends, and a storage compartment within which the first end of the guiding means is disposed, the guiding means adapted to provide guidance along their longitudinal extension between their first and second ends,
a plurality of segments each of which slidingly mounted to the guiding means so as to allow a sliding movement of said plurality of segments along the guiding means and relative to the carrier device between a stored position of the plurality of segments, in which the plurality of segments is received within the storage compartment of the carrier device, and an exposed position of the plurality of segments wherein the plurality of segments are removed from the storage compartment,
a seat element pivotally mounted to a first segment of said plurality of segments so as to be pivotable between an inoperative position and an operative position in which a flight attendant may sit down on the seat element, and
at least one backrest element respectively mounted to at least one second segment of said plurality of segments,
wherein, with the plurality of segments being in its exposed position, the seat element, when pivoted to its operative position, and the at least one backrest element together, are adapted to be used by the flight attendant as a flight attendant seat,
wherein the guidance means guides the plurality of segments on a non-linear guiding path, and
wherein the seat element and the at least one backrest element are located within the storage compartment in the stored position and slidingly removed from the storage compartment in the exposed position.

US Pat. No. 9,180,628

METHOD AND DEVICE FOR THE PRODUCTION OF TUBULAR STRUCTURAL COMPONENTS

Airbus Operations GmbH, ...

1. A method for producing a tubular structural component, comprising the steps of:
providing a tubular moulding tool which has an inner mould surface shaped corresponding to an outer surface of the structural
component;

covering a support surface of an expandable support, which is formed corresponding to the shape of the moulding tool such
that in an unexpanded state the support fills the moulding tool while the support surface and the mould surface run parallel
to one another leaving an expansion spacing of the support surface to the mould surface, with a tubular non-crimp fibre fabric,
such that fibres of a fibre layer of the non-crimp fibre fabric run diagonally around the support;

arranging the support in the moulding tool;
pressing the non-crimp fibre fabric against the mould surface by expanding the support with radial expansion of the non-crimp
fibre fabric; and

infiltrating the non-crimp fibre fabric with a curable matrix.

US Pat. No. 9,382,005

CABIN SEGMENT, CABIN AND VEHICLE WITH A CABIN

Airbus Operations GmbH, ...

1. A cabin segment for a vehicle, comprising:
at least first and second parking spaces, arranged side by side and separated from each other by at least one intermediate
wall, for accommodating serving trolleys, and

a vehicle attendant seat which on one side is held on the at least one intermediate wall so as to be pivotable on an axis,
wherein the vehicle attendant seat is pivotable to an in-use position and to an out-of-the-way position,
wherein the in-use position and the out-of-the-way position are situated apart by 90° or more relative to the pivoting of
the vehicle attendant seat

wherein the first parking space comprises a first receiving opening extending so as to be substantially parallel to a width
of the cabin segment, and wherein the second parking position, arranged width-wise of the cabin segment so as to be adjacent
to the first parking space, comprises a second receiving opening extending so as to be substantially parallel to the width
of the cabin segment, the cabin segment further comprising:

between the first receiving opening and the second receiving opening, a projection extending in a depth of the cabin segment,
wherein an outer edge of the vehicle attendant seat is held, so as to be pivotable on an axis, on the intermediate wall separating
the first receiving opening from the second receiving opening.

US Pat. No. 9,267,715

ICING PROTECTION SYSTEM FOR AN AIRCRAFT AND METHOD FOR OPERATING AN ICING PROTECTION SYSTEM

Airbus Operations GmbH, ...

1. An icing protection system, comprising:
a fuel cell;
an evaporative cooling system,
a thermal deicing device with a condenser and steam conduits for supplying steam into the condenser,
a control unit, and
a device adapted to measure a pressure in the steam conduits and positioned in a wing nose,
wherein the evaporative cooling system is in thermal contact with the fuel cell to conduct heat from the fuel cell to the
evaporative cooling system for the evaporation of a cooling medium and to route the evaporated cooling medium to the condenser
via the steam conduits,

wherein the condenser is configured to condense the cooling medium evaporated during the operation of the fuel cell to cool
the fuel cell while simultaneously emitting heat in the region to be deiced, and

wherein the control unit is configured to control the electrical power demanded from the evaporatively cooled fuel cell in
dependence on a deviation of the pressure in the steam conduits measured with the pressure measuring device from a predetermined
nominal pressure in such a way that the thermal cooling capacity of the evaporative cooling system of the evaporatively cooled
fuel cell corresponds to the condensation capacity of the thermal deicing device.

US Pat. No. 9,187,166

SUPPORTING PILLAR FOR AN AIRCRAFT'S STRUCTURAL COMPONENT MANUFACTURED BY A SELECTIVE LASER MELTING PROCESS

Airbus Operations GmbH, ...

1. A curved elongated supporting pillar for a high strength structural component, which is configured to absorb bending forces
that act transversely to a longitudinal direction of the supporting pillar, the supporting pillar comprising:
a wall at least partially enclosing an elongated cavity of the supporting pillar and forming a tubular structure;
a disc-shaped reinforcement structure arranged within the elongated cavity and transversely to the longitudinal direction
of the elongated supporting pillar to improve flexural rigidity;

wherein the reinforcement structure is formed integrally with the wall;
wherein both the wall and the reinforcement structure are formed from a meltable material;
wherein the supporting pillar has a conical shape, and wherein a first end of the supporting pillar is wider than a second
end of the supporting pillar.

US Pat. No. 9,278,751

HIGH LIFT SYSTEM FOR AN AIRCRAFT

AIRBUS OPERATIONS GMBH, ...

1. A high lift system for an aircraft, the high lift system comprising:
a fully electric drive including an electric motor which drives a landing flap of the high lift system,
wherein the electric motor has internal redundancy due to redundant windings,
wherein the internal redundancy is configured as an m×n phase topology,
wherein n phases of the electric motor are combined into a phase group in each case, resulting in m submotors,
wherein the electric motor is configured in such a way that all m submotors are connected, without a gear unit, to a single
shaft of the electric motor,

wherein the drive further comprises control electronics of the electric motor, and the control electronics are configured
in such a way that if at least one of the submotors and the phase groups fail, they bring about an increase in current within
the remaining intact submotors and phase groups, and

wherein the control electronics are configured to carry out the current increase in such a way that it does not cause the
torque to fall below a nominal torque.

US Pat. No. 9,389,137

PRESSURISED HOT AIR DUCT OF AN AIRCRAFT EQUIPPED WITH A DEVICE FOR DETECTING AIR LEAKAGE

AIRBUS OPERATIONS (SAS), ...

1. A pipe configured to channel pressurized air into an aircraft, comprising:
an inner tube;
an outer tube that is essentially coaxial to the inner tube;
an insulating material inserted between the inner tube and the outer tube and that is made of a heat-insulating and gas-porous
material;

a leak detection device arranged at least in part between the inner tube and the outer tube and in that at least at one end,
the leak detection device held in position by the insulating material follows a concentric trajectory to the inner tube, said
insulating material filling the space between the inner tube and the outer tube, the leak detection device comprising two
leak detection elements, each leak detection element forming a concentric loop; and

a ring with a number of circular openings distributed over a circumference of the ring between the end and the concentric
trajectory of the detection device, the circular openings being a distance from an edge of the ring, the ring being inserted
between the inner tube and the outer tube and that, in case of a leak, hot air flows in the direction of the leak detection
device by passing through the openings of the ring.

US Pat. No. 9,316,606

SENSORS FOR LAYOUT VALIDATION OF AN OXYGEN MODULE

AIRBUS OPERATIONS GMBH, ...

1. A sensor device for an oxygen module mountable on board an aircraft, the sensor device comprising:
an electrical conducting element;
a defining device for defining at least one measurement section, assigned to the oxygen module, on the electrical conducting
element; and

an evaluating unit for determining an electrical resistance present along the at least one measurement section, the evaluating
unit further being configured to ascertain, based on the determined electrical resistance, whether the oxygen module is present,
and the evaluating unit further being configured to ascertain that the oxygen module is present when the determined electrical
resistance is less than a predetermined reference resistance by at least a pre-set deviation from the predetermined reference
resistance.

US Pat. No. 9,395,230

FILL LEVEL MEASUREMENT SYSTEM AND METHOD FOR DETERMINING A FILL LEVEL

Airbus Operations GmbH, ...

1. A measurement system for determining a liquid fill level of a tank, comprising:
a floating sensor configured to float on the surface of a liquid contained in the tank;
at least three reference sensors mounted at a hull of the tank in a spatially fixed arrangement; and
a control device configured to control the floating sensor and the reference sensors,
wherein at least one of the floating sensor and the reference sensors is configured to emit an acoustic signal to the remaining
sensors,

wherein the remaining sensors are each configured to receive the emitted acoustic signal, and
wherein the control device is configured to determine signal travelling times of the acoustic signal from the emitting sensor
to the receiving sensor, to compute a spatial position of the floating sensor with respect to the reference sensors using
the signal travelling times of the acoustic signal, to determine the liquid fill level on the basis of the computed spatial
position of the floating sensor, to control a first one of the at least three reference sensors to emit a test acoustic signal
which is received by a second of the at least three reference sensors, to determine a travelling time of the test acoustic
signal between the first and the second one of the at least three reference sensors, and to compute a speed of sound in the
tank using the travelling time of the test acoustic signal.

US Pat. No. 9,365,280

GUTTER PROFILE AND AIRCRAFT

Airbus Operations GmbH, ...

1. A gutter profile for draining liquids on an aircraft, comprising a connecting section for connecting the gutter profile
to an outer skin of the aircraft and comprising a drain section for forming a drain cross-section of the gutter profile, wherein
the drain section is pre-tensioned into a ground position which opens the drain cross-section and has a flow guiding device
configured to transfer the drain section, with an increase of inflow air pressure on the flow guiding device, into a flight
position which closes the drain cross-section, wherein the inflow air pressure is dependent on an aircraft speed and increases
with increasing aircraft speed.

US Pat. No. 9,266,143

FIREPROOF BULKHEAD OF A HIGHLY POROUS STRUCTURE WITH INTUMESCENT COATING AND METHOD FOR ITS PRODUCTION

Airbus Operations GmbH, ...

1. A fireproof bulkhead comprising a highly porous structure with an intumescent coating, the highly porous structure being
formed as a highly porous pimple or nub structure, and the coating being applied to an inner surface of cell walls of the
highly porous structure, wherein the highly porous structure has a high level of permeability to gases, and wherein the highly
porous pimple or nub structure is produced by forming over a template.

US Pat. No. 9,302,851

FASTENING DEVICE FOR RELEASABLY FASTENING A MECHANISM IN THE REGION OF A FLOOR OF AN AIRCRAFT OR SPACE CRAFT AND ARRANGEMENT FOR A CARGO LOADING SYSTEM

Airbus Operations GmbH, ...

1. A fastening device for releasably fastening a mechanism in the region of a floor, in particular a cargo hold floor, of
an aircraft or spacecraft,
comprising a base component, which is provided so as to be rigidly coupled to a floor component which is formed for introducing
a load into the floor; and

comprising a latch component, which comprises at least one holding portion comprising a latch-component-side holding face
and is coupled to the base component such that the latch component is movable between an unlocked position and a locked position
with respect to the base component;
wherein the latch component is formed such that, when the mechanism is positioned in part in a predefined mounting position
on the floor component and/or on the base component, the holding portion engages around a fastening portion, which is formed
on the mechanism and which comprises at least one mechanism-side holding face, in the region of the mechanism-side holding
face during the passage of the latch component into the locked position, such that the latch-component-side holding face faces
the mechanism-side holding face; and
the latch-component-side holding face is formed such that during passage of the latch component from the locked position into
the unlocked position a gap between the latch-component-side holding face and the mechanism-side holding face continuously
widens;

wherein the base component is formed such that it can be brought into positive engagement with the fastening portion of the
mechanism, when the mechanism is laid in part on the floor component and/or on the base component in the predefined mounting
position, such that it is made possible for tensile loads to be transferred between the mechanism and the base component in
a first direction, the first direction extending substantially perpendicular to a second direction, along which the fastening
portion of the mechanism can be fixed by the cooperation of the latch-component-side holding face and the mechanism-side holding
face; and

wherein the base component comprises a projection which is formed and arranged such that the projection can be introduced
into an associated opening of the mechanism, when the mechanism is laid on the floor component and/or on the base component,
so as to bring about the positive engagement.

US Pat. No. 10,027,113

HIGH-VOLTAGE DC VOLTAGE UNIT AND METHOD FOR OPERATING A HIGH-VOLTAGE DC VOLTAGE UNIT

Airbus Operations GmbH, ...

1. An aircraft having a high-voltage DC voltage unit, the high-voltage DC voltage unit, comprising:a first DC voltage apparatus which is configured to provide a first high-voltage DC voltage between a first output connection and a second output connection of the first DC voltage apparatus or is configured to be fed with a first high-voltage DC voltage;
a second DC voltage apparatus which is configured to independently provide a second high-voltage DC voltage between a first output connection and a second output connection of the second DC voltage apparatus or is configured to be fed with an independent second high-voltage DC voltage;
a first DC voltage connection which is coupled with the first output connection of the first DC voltage apparatus;
a second DC voltage connection which is coupled with the second output connection of the second DC voltage apparatus; and
a reference potential connection which is coupled with the second output connection of the first DC voltage apparatus, with the first output connection of the second DC voltage apparatus and with an earth potential, wherein the first and second high-voltage DC voltages realise a bipolar power supply.

US Pat. No. 9,447,530

METHOD FOR PRODUCING A COMPONENT FOR CONNECTING STRUCTURES AND DEVICE

Airbus Operations GmbH, ...

1. A method for producing a component for connecting structures at crossing regions thereof, the method comprising:
depositing first fibres and second fibres on an underlay, wherein the first fibres and the second fibres are deposited in
a direction transverse to a longitudinal direction of the underlay and in parallel to each other, such that each respective
first fibre has an offset in the longitudinal direction of the first fibres or the second fibres with respect to each respective
second fibre producing a first and second projection region, wherein the first projection region only has ends of the first
fibres and the second projection region only has ends of the second fibres;

connecting the first fibres and the second fibres along a region between the first and second projection regions; and
pivoting the first fibres and the second fibres with respect to one another to form the component.

US Pat. No. 9,174,740

SYSTEM FOR SUPPLYING AN AIRCRAFT WITH INERT GAS, METHOD FOR SUPPLYING AN AIRCRAFT WITH INERT GAS, USE OF A MEMBRANE AND AIRCRAFT

AIRBUS OPERATIONS GMBH, ...

1. A system for supplying an aircraft with inert gas, comprising:
at least one fuel cell with an air inlet and an exhaust air outlet;
a membrane device with an inlet, an outlet and a vapor-permeable membrane,
wherein the exhaust air outlet is in fluid communication with the inlet of the membrane device, and
wherein the membrane device is adapted for guiding a gas from the inlet to the outlet and to give off to an outside through
the membrane any water vapor contained therein;

wherein the membrane device is constructed as an exhaust air pipe,
wherein the membrane is arranged on the external surface of the exhaust air pipe and is in fluid communication with a flow
cross-section of the exhaust air pipe, and

wherein a fuel line is arranged within the exhaust air pipe.

US Pat. No. 9,365,368

NOISE REDUCTION UNIT FOR VACUUM SUCTION DRAINS

Airbus Operations GmbH, ...

1. A noise reduction unit for inserting in a vacuum suction drain, wherein the noise reduction unit is adapted to be flown
through by a material to be conveyed through the vacuum suction drain extending between a suction point and a collection point,
the noise reduction unit comprising:
an inlet section with a first diameter, the inlet section configured to be connected to an inlet section of the vacuum suction
drain;

a middle section with a second diameter; and
an outlet section with a third diameter, the outlet section configured to be connected to an outlet section of the vacuum
suction drain;

wherein the middle section is arranged between the inlet section and the outlet section in a longitudinal direction of the
noise reduction unit;

wherein the middle section is adapted to affect a flow velocity reduction of the material to be conveyed from the inlet section
to the outlet section by causing turbulences therein, thereby reducing an effective cross-section of the vacuum section drain;

wherein the second diameter differs from both the first diameter and the third diameter;
wherein the second diameter is smaller than the first diameter;
wherein, in the longitudinal direction of the noise reduction unit, the middle section narrows towards a central axis of the
noise reduction unit from the first diameter to the second diameter and subsequently broadens from the second diameter to
the third diameter such that the middle section is adapted to the outlet section.

US Pat. No. 9,203,220

INSTALLATION ASSEMBLY FOR BRIDGING A CABLE HARNESS OR THE LIKE BETWEEN TWO AIRCRAFT STRUCTURE ELEMENTS

AIRBUS OPERATIONS GMBH, ...

1. An installation assembly for bridging a cable harness between two aircraft structure elements of an aircraft, the installation
assembly comprising:
an elongated connecting rod having two end sections for attaching the connecting rod onto two adjacent aircraft structure
elements; and

at least one cable guidance element having at least one receiving section for receiving a cable harness and an attachment
section for circumferentially surrounding the connecting rod, wherein locking means are provided to form a connection between
the attachment section and the connecting rod,

wherein a polygonal cross section of the connecting rod corresponds to a recess of the attachment section in order to form
a positive locking engagement between the at least one cable guidance element and the connecting rod, and

wherein the U-shaped recess corresponds to a clip element snapped in the opening of the U-shaped recess in order to form a
clip connection.

US Pat. No. 9,315,272

SYSTEM AND METHOD FOR COOLING AND/OR HEATING AIRCRAFT DEVICES

AIRBUS OPERATIONS GMBH, ...

1. A system for cooling and/or heating aircraft devices to be cooled and/or heated, comprising:
a first individual cooling and/or heating system associated with a first aircraft device to be cooled and/or heated;
a second individual cooling and/or heating system associated with a second aircraft device to be cooled and/or heated;
a cooling and/or heating energy supply apparatus which is adapted to supply cooling and/or heating energy generated by the
first and/or the second individual cooling and/or heating system to the first and/or the second aircraft device to be cooled
and/or heated; and

a control device which is adapted to receive and process signals characteristic of cooling and/or heating requirements of
the first and/or the second aircraft device to be cooled and/or heated and of a load condition of the first and/or the second
individual cooling and/or heating system, and which is further adapted to control, on the basis of said signals, an operation
of the first and/or the second individual cooling and/or heating system and/or the supply of cooling and/or heating energy
generated by the first and/or the second individual cooling and/or heating system to the first and/or the second aircraft
device to be cooled and/or heated.

US Pat. No. 9,321,543

METHOD AND DEVICE FOR CONDITION MONITORING

Airbus Operations GMBH, ...

1. A computer-implemented method for monitoring a component or system of an aircraft or spacecraft, comprising:
generating an optimized decision tree, using the computer, nodes of which contain attributes of a respective input vector,
leaves of which each contains a classification function and associated connections of which between the nodes of the decision
tree are weighted;

providing the input vector which is derived from a data signal received from a sensor that monitors the component or system
of the aircraft or spacecraft;

storing the data signal received from the sensor in a memory for subsequent retrieval for evaluation;
implementing a condition monitoring, using the computer, based on the evaluation of the data signal stored in the memory,
in which a condition of the component or system is determined using the weighted decision tree and on the basis of the attributes
of the input vector, in that an item of information concerning which of the classification functions of the decision tree
best corresponds to the input vector based on the weighted decision tree, is calculated and output;

calculating, using the computer, a probability of an applicability of the corresponding classification function for each leaf
of the weighted decision tree; and

delivering, using the computer, a result stating the probability at an output of the weighted decision tree that corresponds
to the leaf of the weighted decision tree,

wherein the data signal is determined by at least one of a continuous-time and discrete-time measurement of a physical variable
at the component or system.

US Pat. No. 9,267,863

PROPELLER SYSTEM WITH TWO COUNTER-ROTATING PROPELLERS, A METHOD FOR MEASURING THE THRUST OF A PROPELLER SYSTEM WITH TWO COUNTER-ROTATING PROPELLERS AND WIND TUNNEL WITH A MODEL POSITIONED THEREIN HAVING A PROPELLER SYSTEM

Airbus Operations GmbH, ...

1. A propeller system comprising:
first and second propellers positioned one behind the other and separated by a first propeller gap, and having a first and
a second propeller hub, respectively, and at least a first and a second rotating force measuring device, respectively,

at least first and second differential pressure sensors, and
an evaluation unit,
wherein the first and second rotating force measuring devices are mechanically connected to the respective first and second
propellers and are so configured that they can measure the individual thrust force of the respective propeller;

wherein at least one of the first and second differential pressure sensors is arranged on or in each of the first and second
propellers and is configured for measuring a differential pressure between the first propeller gap positioned between the
first and second propellers and a second and a third propeller gap on an opposing side of the respective first and second
propellers, and

wherein the evaluation unit is configured for determining a total thrust force of the propeller system by adding the measured
individual thrust forces of the first and second propellers and by subtracting the gap area forces based on the respectively
measured differential pressures.

US Pat. No. 9,483,057

FUNCTION-MONITORED GUIDANCE SYSTEM FOR ADJUSTING AT LEAST ONE SYSTEM COMPONENT AND METHOD FOR MONITORING THE FUNCTION OF SUCH A GUIDANCE SYSTEM

Airbus Operations GmbH, ...

1. A function-monitored guidance system comprising:
a mechanical adjustment component attached to a system component, wherein the adjustment component is operable to adjust or
move portions of the system component;

a sensor device attached to the system component, wherein the sensor device is configured to detect a load state of the adjustment
component during movement thereof; and

a monitoring device connected to the sensor device via a communication line, wherein the monitoring device comprises a processor
and an operating state determination function executed by the processor for determining an operating state and in particular
a maintenance state of the adjustment component;
wherein the operating state determination function:
provides at least one predefined or determined detection time period for capturing sensor signals detected by the sensor device;
provides at least one predefined or determined threshold value based on amplitudes of sensor signals; and
determines a number of overshoots of at least one threshold value by a captured sensor signal or a number of undershoots of
at least one further threshold value by the captured sensor signal, in each case within the at least one detection time period,
and from this determines a value for the operating state of the adjustment component; and

comprises a start function for initiating the determination of the operating state, which provides a predefined start level
and a comparison of captured sensor signal values with the start level and is designed in such a way that onset of determination
of the operating state is initiated when the start function determines that the captured sensor signal values are above the
start level above a predefined initiation time period.

US Pat. No. 9,217,699

METHOD AND A DEVICE FOR THE REPRODUCTION OF AN IMPACT EVENT

Airbus Operations GmbH, ...

1. A method for reproduction of an impact event of a projectile, comprising the steps of: positioning a test piece relative
to an impress element, extending the impress element with an advance velocity in the direction of the test piece to introduce
the impact event on a surface of the test piece, measuring a resistance force of the test piece when the impress element impinges
on the surface of the test piece, determining a variation in velocity of the impress element, wherein the variation in velocity
is proportional to the quotient of the resistance force and any freely selectable projectile mass, and thereafter reducing
the advance velocity of the impress element according to the determined variation in velocity of said impress element, said
variation being proportional to the quotient of the resistance force and any projectile mass; reducing a feed rate of the
impress element in accordance with an alteration of the velocity of said impress element, such that the impress element is
actively braked to match the impulse experienced by the projectile in order to simulate the impact of different projectiles
having different masses.

US Pat. No. 9,126,685

REGULATING SYSTEM FOR THE CABIN PRESSURE OF AN AIRPLANE AND METHOD FOR REGULATING THE CABIN PRESSURE OF AN AIRPLANE

Airbus Operations GmbH, ...

1. A regulating system for regulating an absolute cabin pressure Pc of an aircraft, the system comprising:
at least one cabin pressure regulator unit, which is so configured that, by controlling at least one of an air outflow device
and an air inflow device of the aircraft, the regulator unit can adjust the absolute cabin pressure Pc within a fuselage of the aircraft, which fuselage is supplied with fresh air and subjected to pressure, to a predetermined
pressure level indicated by the cabin pressure regulator unit, or the regulator unit can set a predetermined cabin height
and,

when changes of the pressure level or the cabin height have to be made, a quotient of the time-related deviation dPc/dt of the absolute cabin pressure Pc in the fuselage of the aircraft and the absolute cabin pressure Pc can be kept constant.

US Pat. No. 9,126,228

METHOD FOR ACCELERATED DRYING OF POLYMERS AND DEVICE

Airbus Operations GmbH, ...

1. A method for accelerated drying of at least one polyurethane paint which is located at least partially on an aircraft component
formed from a material mixture comprising different absorption and reflection properties, comprising the steps of:
a) at least partially applying the at least one polyurethane paint, to an upper side of the aircraft component formed from
the material mixture comprising different absorption and reflection properties, wherein the polyurethane paint is a three
component paint which contains a base as a first component, a hardener as a second component and a thinning agent as a third
component, and

b) at least partially drying the polyurethane paint in a drying operation by means of infrared radiation with a wavelength
range of between 1550 nm and 3000 nm, wherein the at least one polyurethane paint is hardened from the upper side of the at
least one component in such a way that the polyurethane paint is polishable, wherein the power applied per surface-area by
a radiator is in a range of between 75.1 W/m2 to 159.0 W/m2 and wherein a spacing between the polyurethane layer of paint and the radiator is between 60 cm to 100 cm.

US Pat. No. 9,126,684

HABITATION AND SLEEPING MODULE FOR ACCOMMODATING AT LEAST ONE MEMBER OF A FLIGHT CREW

Airbus Operations GmbH, ...

1. An aircraft with a passenger cabin and a module for accommodating at least one member of a flight crew, the module being
arranged on a floor of the passenger cabin, the module comprising:
a first sleeping area;
a work area comprising a work area floor arranged above the floor of the passenger cabin and configured for accommodating
at least one member of the flight crew;

a left outside wall parallel to a longitudinal direction of the aircraft and a right outside wall parallel to the longitudinal
direction of the aircraft, between which the work area floor is arranged; and

an ascent region for ascending from the floor of the passenger cabin up and into the work area of the module;
wherein the ascent region comprises an ascent device laterally vertically arranged on the left or the right outside wall of
the module and comprising steps arranged at the left or the right outside wall one above the other such that the ascent device
leads a user in a vertical direction while the user faces a transverse direction of the aircraft; and

wherein the module is configured such that a volume underneath the work area floor and between the left and the right outside
walls is available in a full width, a full depth and a full height thereof as an area for a placement of items and is configured
to be accessed from a front or a rear side of the module.

US Pat. No. 9,150,941

METHOD FOR PREVENTING CRACK FORMATION AND FOR SLOWING DOWN THE ADVANCEMENT OF A CRACK IN METAL AIRCRAFT STRUCTURES BY MEANS OF LASER SHOCK RAYS

Airbus Operations GmbH, ...

1. A method of repairing superficial damage to an aircraft structural part for preventing crack formation and for slowing
down advancement of a crack in metal aircraft structures by laser shock beams, comprising: (a) providing an aircraft structural
part which has a damaged area, the damaged area being superficial damage comprising a scratch; (b) treating the damaged aircraft
structural part by laser shock irradiating a first superficial region of the aircraft structural part close to the damaged
area with a first pulsed laser beam of a first wavelength and a first pulse frequency, wherein the laser shock irradiating
is performed locally in a region of the scratch, wherein energy from the first pulsed laser beam is absorbed by the aircraft
structural part, and wherein a pressure wave passes through the aircraft structural part which generates a compressive pre-stress
in the aircraft structural part in order to prevent crack formation and to slow down advancement of a crack.

US Pat. No. 9,352,519

METHOD FOR MANUFACTURING A LINING ELEMENT, A LINING ELEMENT AND A VEHICLE

AIRBUS OPERATIONS GMBH, ...

1. A method for manufacturing a lining element, comprising:
laying an elastic textile membrane onto a positive molding tool;
applying first fibers and a matrix material onto all outer edges the textile membrane such that a semi-finished product of
a fully circumferential framework is created and configured as a support for the textile membrane, wherein textile membrane
is pre-tensioned before the applying the first fibers onto the textile membrane;

providing at least one sealing element along outer edges of the molding tool;
covering the textile membrane and the at least one sealing element in an air tight manner by a covering means;
evacuating the space between the molding tool and the covering, means;
curing the matrix material by heating the semi finished product; and
removing the lining element comprising an integral compound of the elastic textile membrane and cured fully circumferential
framework from the positive molding tool,

wherein the material of the textile membrane prevents the absorption of resin.

US Pat. No. 9,193,478

FLIGHT RECORDER, AIRCRAFT WITH FLIGHT RECORDER AND METHOD FOR READING OUT FLIGHT DATA FROM A FLIGHT RECORDER

Airbus Operations GmbH, ...

1. A flight recorder, comprising:
a memory;
a control device, which is coupled to the memory and which is configured to record flight data during the flight of an aircraft
and to store said flight data in the memory;

a transceiver device, which is coupled to the control device and which is configured to accept stored flight data signals
from the control device and to convert them into acoustic signals; and

an acoustic transducer, which is coupled to the transceiver device and which is configured to emit the acoustic signals of
the transceiver device into a body of water, the control device being configured to receive control signals via the transceiver
device and, depending on the control signals, to retrieve partial data areas of the stored flight data from the memory and
to transfer them to the transceiver device;

wherein the control device is configured to be operated in an energy-saving state until a control signal puts the control
device into a normal operating state, the control device being configured to transfer flight data signals to the transceiver
device only in the normal operating state.

US Pat. No. 9,840,335

FOOLPROOFING SYSTEM FOR PIPES BY MEANS OF AN OBSTACLE INSIDE A CONNECTOR IN AN AIRCRAFT DUCT

Airbus SAS, Blagnac (FR)...

1. An aircraft portion, comprising:
a structure, and
a duct configured to circulate a fluid and comprising a plurality of pipes and a plurality of connectors fixed to the structure
and connecting the pipes two-by-two,

the plurality of pipes includes pipes of different lengths, each pipe having a first end situated on a first side of the duct
and a second end, and

a first abutment situated on a second side of the duct,
each connector including a connector internal passage that fluidically connects two pipe internal passages respectively belonging
to the two pipes that the connector connects to each other;

each connector including two cavities surrounding the connector internal passage and in which are respectively inserted respective
ends of two consecutive pipes, namely a first cavity situated on the second side of the duct and a second cavity situated
on the first side of the duct;

the first and second cavities of each connector having respective axes;
the first and second cavities of each connector being delimited internally by respective radially internal walls of annular
shape respectively centered on the respective axes of the first and second cavities;

the first and second cavities of each connector being delimited externally by respective radially external walls also of annular
shape and respectively centered on the respective axes of the first and second cavities;

each connector including an internal support delimiting the first and second cavities of the connector and connecting the
respective radially internal walls of the first and second cavities to the respective radially external walls of the first
and second cavities,

each pipe being movable in axial translation relative to the two connectors that the pipe connects to each other;
each connector including a second abutment that limits the travel in translation of the pipe received in the first cavity
of the connector towards the first side of the duct by cooperating with the first end of the pipe and a third abutment that
limits the travel in translation of the pipe received in the second cavity of the connector towards the second side of the
duct by cooperating with the first abutment of the pipe;

wherein the plurality of connectors comprises at least a first connector and a second connector such that:
the respective internal supports of the first and second connectors have the same conformation;
the first cavity of the first connector and the second cavity of the second connector respectively receive the first and second
ends of a first pipe of the plurality of pipes;

the first end and the first abutment of the first pipe are separated from each other by a first distance;
the internal support of the first connector and the third abutment that is part of the second connector are separated from
each other by a second distance measured parallel to the respective axes of the first cavity of the first connector and the
second cavity of the second connector;

the first connector and the second connector are positioned so that the plurality of pipes comprises a second pipe the first
end and the first abutment of which are separated from each other by a third distance strictly greater than the first distance
and strictly less than the second distance;

wherein the first connector includes a first obstacle arranged in the first cavity of this first connector, the first obstacle
forming the second abutment of the first connector and being separated from the third abutment of the second connector by
a fourth distance less than or equal to the third distance and measured parallel to the respective axes of the first cavity
of the first connector and the second cavity of the second connector, and

wherein the second abutment of said second connector is formed by the internal support of the second connector or by a second
obstacle arranged so that the relative position of the second obstacle and the internal support of the second connector is
different from the relative position of the first obstacle and the internal support of the first connector.

US Pat. No. 9,403,465

CREW REST COMPARTMENT AND MEANS OF TRANSPORT

Airbus Operations GmbH, ...

1. A means of transport comprising:
a cargo area;
a cargo container located in the cargo area, wherein a crew rest compartment is arranged in the cargo container and the cargo
container is delimited by sidewalls;

the crew rest compartment comprising:
a first bunk and a second bunk, the first bunk and the second bunk each comprising a sleeping area adapted for accommodating
a sleeping member of a crew;

a floor;
wherein the first bunk and the second bunk are located above the floor and the first bunk and the second bunk are both accessible
from the floor;

wherein each sleeping area has a longitudinal direction which defines a longitudinal direction of the corresponding bunk;
wherein the first bunk is located above the second bunk; and
wherein the longitudinal direction of the first bunk and a longitudinal direction of the crew rest compartment enclose an
angle which differs from 0° and 90°, the longitudinal direction of the crew rest compartment being parallel to the longitudinal
direction of the means of transport when the crew rest compartment is mounted in the means of transport; and

wherein the longitudinal direction of the first bunk is oblique to each of the sidewalls of the cargo container.

US Pat. No. 9,377,039

FORCE INTRODUCTION FITTING FOR LIGHTWEIGHT COMPONENTS

AIRBUS OPERATIONS GMBH, ...

1. A force introduction fitting for lightweight components, the force introduction fitting comprising:
two disc-shaped radial force introduction plates;
an axial force introduction surface in a form of a cylinder jacket having a first end and a second end, with one of the two
disc-shaped radial force introduction plates connected to the first end and the other of the two disc-shaped radial force
introduction plates connected to the second end, the second end being opposite to the first end;

an anchor part; and
at least one receiving means for mounting the anchor part,
wherein the radial force introduction plates and the axial force introduction surface enclose a cavity, and
wherein the force introduction fitting is formed as a one-piece component without joints, and the at least one receiving means
is formed as a wall between and attached to at least one of the radial force introduction plates and is enclosed by the axial
force introduction surface, extends non-parallel to the axial force introduction surface, at least in portions, and comprises
a bearing face for fitting a retaining face of the anchor part,

wherein the anchor part extends through an opening in one of the two disc-shaped radial force introduction plates to the outside.

US Pat. No. 9,139,285

WING WITH RETRACTABLE WING END PIECE

Airbus Operations GmbH, ...

1. A wing for use in an aircraft, the wing comprising:
a main wing with a supporting main wing structure;
a wing end piece with a supporting wing end piece structure; and
lever kinematics for performing a pivoting motion of the wing end piece relative to the main wing between an extended state
in which the wing end piece and the main wing form a continuous aerodynamic body and a retracted state in which the wing end
piece is folded inward with regard to the main wing from the extended state, the lever kinematics comprising:

at least a first and a second lever arrangement, which are mounted with a respective first hinged device on the main wing
structure, and with a respective second hinged device on the wing end piece structure, each hinged device forming a rotational
axis,

wherein the second hinged device of the first lever arrangement and the second hinged device of the second lever arrangement
are offset in a wingspan direction of the wing end piece with regard to each other, and the first hinged device of the first
lever arrangement and the second hinged device of the second lever arrangement are offset in a wingspan direction of the main
wing with regard to each other;

wherein the wing end piece structure is expanded in a wingspan direction by at least one extension along the main wing structure,
at the end of which, in the wingspan direction of the wing end piece structure opposite a wing tip of the wing, one of the
two hinged devices of the lever kinematics being arranged on the wing end piece structure; and

wherein the at least one extension lengthens the wing end piece structure, thereby generating an intersection between the
wing end piece structure and the main wing structure.

US Pat. No. 9,375,781

RIVETING DEVICE AND RIVETING METHOD

Airbus Operations GmbH, ...

1. A riveting device for the connection of components in an overlap joint, comprising:
an upper tool for driving a rivet into a rivet hole passing through the components, and
a lower tool as a dolly, which has a deforming section for purposes of plastically deforming the end of a rivet shaft driven
through the rivet hole,

the riveting device having a magazine with a feed device for purposes of feeding a rivet into a shot passage of the upper
tool, an actuator for purposes of accelerating the rivet introduced into the shot passage in the direction of the components,
and an adjustment system for purposes of aligning the shot passage with the rivet hole.

US Pat. No. 9,316,562

SYSTEM AND METHOD FOR MONITORING THE STATE OF STRUCTURAL COMPONENTS

Airbus Operations GmbH, ...

1. A system for monitoring the integrity of a structure or of a structural component in an aircraft, comprising:
at least one vacuum source;
at least one device for acquiring at least one of an air volume flow or the air pressure,
at least one structural component manufactured by extrusion or extrusion molding with at least one elongated air duct which
by leaving out material in the profile cross section of the structural component is integrated in the structural component
as a continuous hollow space in the manufacture of the structural component,

wherein the air duct is connectable to the vacuum source and the at least one device for acquiring the at least one of the
air volume flow or the air pressure in the at least one elongated air duct,

wherein in the case of a structure that is intact in the region of the at least one elongated air duct, the air pressure in
the air duct substantially corresponds to the air pressure of the vacuum source, and essentially no air volume flow passes
through the air duct, while if a structural defect occurs in the region of the air duct, air from the surroundings of the
structure or of the structural component enters the air duct and detectably increases the air pressure and the air volume
flow in the at least one elongated air duct; and

a plurality of valves for blocking the air flow and for narrowing down a region comprising a structural defect,
wherein, in a case of a damage to an airduct, the damage dividing airduct into a first segment and a second segment, the first
segment having a first end and a second end, the second segment having a third end and a fourth end, the second and the third
ends being adjacent to the damage being sealed off and the first end and the fourth end interconnected by a bridge line for
restoring a function of the damaged airduct.

US Pat. No. 9,284,039

RUDDER SYSTEM FOR AN AIRCRAFT

Airbus Operations GmbH, ...

1. A rudder system for an aircraft, comprising:
a centre box;
a rudder; and
a plurality of actuators;
wherein the rudder is pivoted around a hinge line relative to the centre box,
wherein the actuators are arranged at an acute angle relative to the hinge line, and connected with at least one pivoted pivot
lever, and

wherein a first end of one of the plurality of actuators is connected by a first push rod to an aircraft structure to resemble
a pendulum support, and a second end is configured to use the at least one pivot lever to move an end of a flange, the flange
being pivotable in the aircraft structure and connected with the rudder,

wherein the first end of the actuator is joined by a second push rod with a second pivot lever, the second pivot lever rotatably
mounted on the aircraft structure, and moving the other end of the flange.

US Pat. No. 9,409,321

MOULDED BODY FOR PRODUCING A FIBRE COMPOSITE COMPONENT

Airbus Operations GmbH, ...

9. A support core for producing a fibre composite component, comprising:
a plurality of contact surfaces situated at least in certain regions of the support core, wherein said plurality of contact
surfaces are provided for shaping a component to be cured being formed by a curable fibre composite material, and at least
in regions of said support core a functional layer integrated in said support core, wherein said functional layer is a non-stick
layer and a gastight sealing layer,

wherein the support core is formed using at least one of a cardboard and a paper, and
wherein the support core can be collapsed due to a shape change by deformation of the at least one cardboard and paper and
removed from a finished fibre composite component, and

wherein the gastight sealing layer provides a gastight sealing of the supporting core, wherein the gastight sealing in conjunction
with a sealing surrounding the fibre composite component to be cured provides a gastight enclosure of the fibre composite
component to be cured on the plurality of contact surfaces of the support core capable of applying a pressure differential
between the curable fibre composite component and the surrounding atmosphere during the curing process.

US Pat. No. 9,352,842

WIRELESS NETWORK FOR CONTROLLING THE OXYGEN SYSTEM OF AN AIRCRAFT

Airbus Operations GmbH, ...

1. A control device for activating an oxygen system of a means of transport, the control device comprising:
a first activation unit which is configured to activate at least a part of the oxygen system by wireless transmission of a
first activation signal;

a second activation unit which is configured to activate said at least part of the oxygen system by wired transmission of
a second activation signal; and

a controller is configured to send an activation instruction to the first activation unit and the second activation unit;
wherein, upon the controller sending an activation instruction the first activation unit and the second activation unit, the
first activation signal and the second activation signal are transmitted to said at least part of the oxygen system.

US Pat. No. 9,289,102

DISPOSABLE SEATING-SURFACE COVER FOR A TOILET-SEAT FLAP, AND TOILET MODULE

AIRBUS OPERATIONS GMBH, ...

7. A toilet module, for installation in an aircraft, comprising:
a toilet-seat flap with a seating surface; and
a retaining apparatus which is configured to retain a disposable seating-surface cover;
wherein the disposable seating-surface cover is configured to cover a seating surface of the toilet-seat flap in order to
avoid contact between a user and said toilet-seat flap, wherein the disposable seating-surface cover comprises a deformable
or foldable base with an aperture;

wherein the base comprises at least one adhesive section made of a paramagnetic or ferromagnetic material; and
wherein, in a state of use, for the purpose of retaining said disposable seating-surface cover in the state of use, a magnetic
force operates between the adhesive section of the disposable seating-surface cover and the retaining apparatus.

US Pat. No. 9,156,554

SYSTEM COMPONENT MODULE AND METHOD FOR MOUNTING IN AN AIRCRAFT CABIN

AIRBUS OPERATIONS GMBH, ...

1. An aircraft system component module for mounting in an aircraft cabin, comprising:
a support, the support comprising:
a duct configured to receive at least one corresponding Personal Service Unit (PSU);
an individual air supply system; and
at least one opening formed in an upper surface of the support;
at least one mounting element fastenable to a bottom of a luggage compartment installed in the aircraft cabin; and
at least one fastener;
wherein the at least one mounting element is fastenable to and dimensioned along the bottom of the luggage compartment such
that the at least one opening, corresponding in number and dimension on the support to the at least one mounting element,
is configured to allow the support to be installed on the bottom of the luggage compartment by:

fastening the at least one mounting element to the bottom of the luggage compartment;
positioning the support below the bottom of the luggage compartment so that at least one mounting element and at least one
opening align;

moving the support toward the bottom of the luggage compartment so that at least one mounting element passes through the at
least one corresponding opening;

displacing the support substantially parallel to the bottom of the luggage compartment to a final assembly position in the
aircraft cabin; and

fastening the support to the at least one mounting element with the at least one fastener.

US Pat. No. 9,067,611

SEAT BENCH TRANSPORT DEVICE

Airbus Operations GmbH, ...

1. A seat bench transport device for transporting a seat bench for a vehicle, comprising:
a chassis,
a retaining rail pair disposed on the chassis and including two retaining rails that extend parallel to one another to accommodate
seat bench feet, the lengthwise sides of the rails that face one another being open at least in sections and the lengthwise
sides of the rails that face away from one another each having at least one locking section, and

a displacement mechanism for moving the retaining rails transversely relative to one another, wherein the displacement mechanism
comprises:

two threaded rods aligned in a direction of displacement, each of which is allocated to one of the retaining rails,
a gearwheel that is disposed between the threaded rods and meshes with the threaded rods, and
an actuating element for driving the gearwheel.

US Pat. No. 9,452,823

LIFT FLAP BEARING APPARATUS, LIFT FLAP ASSEMBLY, AIRFOIL AND AIRCRAFT

EADS Deutschland GmbH, O...

1. A lift flap bearing apparatus for guiding and adjusting a first lift flap and a second lift flap, the lift flap bearing
apparatus comprising
a first guiding device configured to guide the first lift flap and a second guiding device configured to guide the second
lift flap, the first and the second guiding devices each having a first curved guide rail and a second curved guide rail.

US Pat. No. 9,279,055

CHROMATE-FREE CORROSION PROTECTION FOR FUEL TANKS

Airbus Operations GmbH, ...

1. A coated fuel tank consisting of
a fuel tank having an inner surface, said fuel tank made of aluminum metal or made of an aluminum metal alloy;
a coating on said inner surface of said fuel tank; and
said coating consisting of a composition consisting of
at least one binding agent,
at least one curing agent,
at least one chromate-free corrosion inhibitor which is selected from the group consisting of zinc phosphate, aluminum triphosphate,
a borate and a molybdate,

at least one quaternary ammonium compound, in which said composition contains an amount of at least 0.1% by weight, based
on the total weight of the composition, of quaternary ammonium compound; and

said composition being chromate-free.

US Pat. No. 9,242,731

HOUSING-FREE HATRACK

Airbus Operations GmbH, ...

1. A hatrack for a passenger cabin of an aircraft, comprising:
a hatrack body;
at least one fixing brace with a fixing end, a support end and at least one roller extending at the support end; and
a support;
wherein the support is arranged between the hatrack body and the support end of the fixing brace in such a way that the hatrack
body is pivotable about a pivot axis;

wherein the pivot axis is arranged parallel to the longitudinal direction of the passenger cabin;
wherein the fixing end of the fixing brace is connectable to a frame of an aircraft structure of the aircraft, and
wherein the hatrack body comprises a first and a second opposing lateral walls configured to releasably engage the corresponding
at least one roller in such a way that the hatrack body is pivotable about an axis defined by the roller.

US Pat. No. 9,494,185

SUPPORT STRUT FOR SUPPORTING PRIMARY COMPONENTS AS WELL AS GUIDING SYSTEMS WITH SUCH A SUPPORT STRUT AND METHOD FOR MANUFACTURING SUCH A SUPPORT STRUT

Airbus Operations GmbH, ...

1. A support strut for use as a primary load-bearing structural component for hinged coupling of at least one additional primary
load-bearing structural component for an aircraft, wherein the support strut comprises:
a rod-shaped base body extending in a longitudinal direction and comprising a fiber composite, with an end section lying at
a first end of the base body and at least sectionally exhibiting an annular cross section along the longitudinal direction,
which defines a first central hole originating from the first end of the base body, and with first annular holes spaced apart
relative to each other in a circumferential direction of the annular cross section and originating from the first end of the
base body as well as running along the longitudinal direction in the base body;

first roving bundles, of which at least one lies in a respective one of the first annular holes and is imbedded in a matrix
material that fills up a respective one of the first annular holes; and

a first connecting part that is held at the first end of the base body at a predetermined distance from the base body by the
first roving bundles, which are imbedded in the matrix material, where a first end of each first roving bundle lies in one
of the first annular holes, and a second end of each first roving bundle lies in another one of the first annular holes;

wherein the first roving bundles are configured to be wound around the first connecting part between the first end and the
second end of each of the first roving bundles.

US Pat. No. 9,459,303

METHOD AND DEVICE FOR IDENTIFYING AN ALLOCATION OF CONTROL CIRCUITS TO AT LEAST ONE CONTROL DEVICE

Airbus Operations GmbH, ...

1. A method for identifying an allocation of control circuits, which each comprise an actuator and a sensor, to at least one
control device comprising:
providing a first actuation pattern which is suitable for actuating a plurality of individual control circuits simultaneously
via the control device, comprising a plurality of actuation phases which each describe the plurality of individual control
circuits which are to be actuated in the corresponding actuation phase simultaneously, the number of actuation phases being
less than the number of control circuits;

actuating the actuators of the plurality of individual control circuits in accordance with one of the plurality of actuation
phases by the control device;

reading out the sensors of the actuated plurality of individual control circuits in accordance with the one of the plurality
of actuation phases;

repeating the steps of actuating and reading out for each of the plurality of actuation phases so as to measure a second actuation
pattern; and

identifying the allocation of each of the plurality of individual control circuits to the at least one control device by comparing
the provided actuation pattern and the measured actuation pattern, wherein the provided actuation pattern and/or the measured
actuation pattern is represented by at least one binary code, wherein every digit of the binary code represents one activated
or deactivated control circuit respectively, wherein the number of positions in at least one binary code is equal to the number
of actuation phases, and wherein the number of binary codes which represent the provided actuation pattern and/or the measured
actuation pattern is equal to the number of control circuits.

US Pat. No. 9,260,850

VACUUM TOILET HAVING A URINAL FUNCTION

Airbus Operations GmbH, ...

1. A vacuum toilet unit having a urinal function, comprising:
a sit-down toilet,
a urinal,
a main discharge,
a shared vacuum valve, and
a lockable triggering device for triggering the shared vacuum valve,
wherein the sit-down toilet has a toilet wastewater discharge,
wherein the urinal has a urinal water discharge,
wherein the toilet wastewater discharge and the urinal water discharge are connected to the main discharge,
wherein the main discharge is connected, via the shared vacuum valve, to a vacuum wastewater system such that the shared vacuum
valve controls flows, into the vacuum wastewater system, from the toilet wastewater discharge and the urinal water discharge
through the main discharge,

wherein the triggering device for triggering the shared vacuum valve is adapted in such a manner that the triggering unit
may not be triggered when a person is seated on the sit-down toilet.

US Pat. No. 9,261,150

DRIVE SYSTEM FOR A HIGH LIFT SYSTEM OF AN AIRCRAFT AND METHOD FOR DETECTING A MISALIGNMENT BETWEEN A TRANSMISSION SHAFT AND AN OPENING IN A DRIVE SYSTEM FOR A HIGH LIFT SYSTEM OF AN AIRCRAFT

AIRBUS OPERATIONS GMBH, ...

1. A drive system for a high lift system of an aircraft, comprising:
an opening,
a transmission shaft being rotatable about an axis and extending through the opening with a radial play,
at least one first engaging element being located at the transmission shaft and protruding radially outward into the opening,
at least one second engaging element being located at the opening and protruding radially inward into the opening,
wherein the at least one first engaging element and the at least one second engaging element engage each other and in case
a relative radial displacement between the transmission shaft and the opening exceed the radial play, the engagement prevents
further rotation of the transmission shaft.

US Pat. No. 9,169,016

METHOD AND DEVICE FOR THE INSTALLATION OF SYSTEMS, AND A FREIGHT LOADING SYSTEM

AIRBUS OPERATIONS GMBH, ...

6. A freight loading system for an aeroplane, comprising:
a rail-type longitudinal guideway arranged in an aeroplane; and
a multiplicity of sledges routed on the rail-type longitudinal guideway for the accommodation of cargo, wherein the rail-type
longitudinal guideway has a curved section for the purpose of altering the direction of the sledges, and wherein the rail-type
longitudinal guideway has two parallel guideway sections, which are connected with one another via the curved section, wherein
at least one sledge of the multiplicity of sledges is able to enter into an opening of an aeroplane fuselage along one of
the two parallel guideway sections, is able to alter direction along the curved section, and is able to exit from the aeroplane
fuselage through the opening along the other of two parallel guideway sections.

US Pat. No. 9,090,331

AIRCRAFT FLOOR SUPPORT STRUT WITH DESIGN FAILURE POINT

Airbus Operations GMBH, ...

1. A support strut for the support of a floor structure of an aircraft, comprising:
a strut section having a region forming a design fracture point for improving the safety of the occupants of the aircraft;
and

a head section attached to the floor structure of the aircraft;
wherein the head section forms an overlap joint with the strut section;
wherein the region of the strut section forming the design fracture point is positioned outside of the overlap joint;
wherein the strut section and the head section each have a U-shaped cross-section with two parallel flanges connected by a
web;

wherein the flanges of the strut section have a uniform height and a uniform thickness along an entire length of the strut
section;

wherein the cross-section of the strut section is reduced in size relative to the cross-section of the head section; and
wherein the strut section is arranged in a central profile region of the support strut.

US Pat. No. 9,300,079

DEVICE FOR ELECTRICALLY CONNECTING AND ATTACHING AN ELECTRICAL DEVICE TO A WALL IN A VEHICLE

AIRBUS OPERATIONS GMBH, ...

1. An apparatus for electrically connecting and attaching an electrical device to a wall in a vehicle, comprising:
a substantially planar universal base plate including a first connection region with a first electrical connector arranged
therein and an attachment means for attachment to the wall in a vehicle; and

a substantially planar universal rear wall including a second connection region with a second electrical connector positioned
therein, the universal rear wall designed to form part of the electrical device or to be attached to the electrical device;

wherein the universal rear wall and the universal base plate comprise largely corresponding directions of extension and are
designed to be brought into mechanical engagement with each other, and during mechanical engagement the first connection region
and the second connection region are arranged adjacent to each other in such a manner that the first electrical connector
and the second electrical connector establish a mutual electrical connection; and

wherein the universal base plate and the universal rear wall are configured to be mechanically affixed with a force that has
a direction parallel to the direction of mechanical engagement;

wherein the universal base plate in the first connection region comprises a first recess in which the first electrical connector
is arranged, and the universal rear wall in the second connection region comprises a second recess in which the second electrical
connector is arranged;

wherein the first recess is arranged in a first flange that extends at an angle from the universal base plate;
wherein the second recess is arranged in a second flange that extends at an angle from the universal rear wall;
wherein the universal base plate comprises at least one first engagement means, and the universal rear wall comprises at least
one second engagement means that is designed so as to correspond to the first engagement means, wherein the first engagement
means and second engagement means are designed to mechanically engage each other; and

wherein one of the first engagement means and second engagement means is an attachment hook, and the respective other of the
first engagement means and second engagement means is a corresponding hook recess into which the attachment hook is insertable.

US Pat. No. 9,205,606

METHOD FOR REINFORCING A FIBER COMPOSITE COMPONENT AND ARRANGEMENT FOR PRODUCING A REINFORCED FIBER COMPOSITE COMPONENT

Airbus Operations GmbH, ...

1. An arrangement for producing a reinforced fibre composite component for the aviation and aerospace industry, comprising:
a skin laminate in the form of the fibre composite component portion
a reinforcing element comprising a receiving region, a cover wall, side walls and a foot portion;
a pressure element adapted to the geometry of the receiving region for inserting the pressure element into the receiving region;
a reversible fastening device for fastening the reinforcing element and the inserted pressure element relative to one another
in a reproducible manner, the reversible fastening device comprising at least a first fastening portion mounted on the pressure
element and at least a second fastening portion, wherein the first fastening portion is a ferromagnetic element;

a transport device which comprises a support device for receiving the reinforcing element and the pressure element inserted
in the receiving region of the reinforcing element, for applying the reinforcing element, together with the pressure element
fastened thereto, in a reproducible manner to the fibre composite component to be reinforced, to form a moulding portion,
wherein the support device comprises a support body and engages the reinforcing element provided with the pressure element,
in that the support body is mounted on the cover wall of the reinforcing element, wherein the support device comprises the
second fastening portion and wherein the second fastening portion is formed as a magnet arranged in a cavity of the support
body and positioned adjacent to the cover wall of the reinforcing element when transporting the reinforcing element together
with the pressure element;

a curing device configured to cure the formed moulding portion, to connect the reinforcing element to the fibre composite
component; and

a removal device configured to remove the reversible fastening device and the pressure element from the reinforced fibre composite
component.

US Pat. No. 9,180,629

METHOD FOR PRODUCING AN INTEGRAL FIBER COMPOSITE PART

AIRBUS Operations GmbH, ...

1. A method for producing an integral fibre composite component with a plurality of stiffening members surrounded by an outer
skin, comprising the following steps:
producing a plurality of removable cores in a core mould, the cores substantially forming an inner surface geometry of the
fibre composite component, the inner surface geometry corresponding to the plurality of stiffening members and the outer skin,
wherein the cores are produced in the core mould by filling the core mould with at least one of a soluble or meltable core
material which is then cured;

applying preforms made from reinforcing fibres to the cores to form the stiffening members and arranging the cores to form
an overall structure;

coating the cores with a fibre product to create the outer skin, a cross section of the overall structure being completely
surrounded by the fibre product, wherein the fibre product is a web of reinforcing fibres configured to be infiltrated with
a curable plastics material;

incorporating the overall structure into a closed moulding tool and infiltrating the overall structure with the curable plastics
material;

curing the overall structure to create the integral fibre composite component by applying at least one of pressure or temperature;
making at least one hole in the outer skin of the integral fibre composite component; and
removing of the cores by at least one of heating or applying a solvent, so that the core material is dissolved and flows out
through the at least one hole made in the outer skin of the integral fibre composite component.

US Pat. No. 9,065,981

PASSENGER MONITORING AND DIRECTING SYSTEM FOR USE IN AN AIRCRAFT CABIN

AIRBUS OPERATIONS GMBH, ...

1. Passenger monitoring and directing system for use in an aircraft cabin, comprising:
at least one information means to be arranged in the aircraft cabin and
at least one passenger monitoring device,the information means comprising at least one monitoring portion, and the passenger monitoring device being assigned to the
information means and arranged relative to its monitoring portion in order to monitor the passengers through the monitoring
portion of the information means.

US Pat. No. 9,056,682

INTEGRATED MONUMENT

AIRBUS OPERATIONS GMBH, ...

1. A monument for an aircraft, comprising:
a base module, comprising:
a first toilet;
a system connection arrangement including a fresh water connection; and
a line arrangement including a first forked line and an interface;
an expansion module comprising a second toilet, separate from the first toilet,
a dividing wall dividing the base module and the expansion module,
a control device wherein the control device prevents concurrent flushing of the first toilet and of the second toilet such
that said first and second toilets do not request more than a predetermined maximum quantity of water per unit of time from
a water supply of the aircraft;

wherein the monument is an on-board toilet monument, and
wherein the monument is configured as a combi module sized to replace two substantially identical single monuments of a same
volume,

wherein the interface is arranged in or on the dividing wall,
wherein the fresh water connection of the system connection arrangement of the base module is configured to connect the first
toilet of the base module and the second toilet of the expansion module to a fresh water supply line of the aircraft via the
first forked line,

wherein the first forked line includes a first branch that connects the fresh water connection of the system connection arrangement
to the first toilet and the first forked line includes a second branch that connects the fresh water connection of the system
connection arrangement to the second toilet, and

wherein the second toilet of the expansion module is connected to the second branch of the first forked line of the base module
via the interface of the base module.

US Pat. No. 9,311,312

PROCESS FOR ELECTRONIC ARCHIVING OF DATA OBJECTS AND COMPUTER PROGRAM PRODUCT

cp.media AG, Baar (CH) A...

1. A method for the electronic archiving of data objects by means of a data processing device, wherein the method comprises
the following steps:
receipt of a hash value tuple comprising one or a plurality of hash values, wherein each hash value is assigned to a data
object,

receipt of time information on the hash value tuple indicating a time period within which the hash values of the hash value
tuple are electronically archived and

comparison of the time information with a predetermined time specification, wherein the following steps are carried out if
the time information specifies a time period for electronic archiving that is shorter than the predetermined time specification:

a) generation and assignment of a first time stamp to a hash value,
b) generation of a queue for further processing of hash values,
c) determination of a processing time for electronic archiving of hash values in the queue, wherein the processing time is
obtained from the total time required for electronic archiving of hash values already in the queue and the time required for
electronic archiving of an additional hash value,

d) placing of a hash value in the queue when the processing time is shorter than the predetermined time specification,
e) repetition of steps c) and d) until a processing time is determined at step c) which is greater than the predetermined
time specification, then

f) generation and assignment of an archive time stamp for the hash values in the queue.

US Pat. No. 9,252,532

DEVICE FOR ATTACHING AN AIRCRAFT CABIN MODULE

Airbus Operations GmbH, ...

1. A device for attaching at least one aircraft cabin module, said device comprising:
a component with a center portion and two limbs, the component being configured in U shape as a rail component, the limbs
having locking recesses for the releasable locking of spring-loaded locking projections being fitted on a plug pin of an aircraft
cabin module and catching into the locking recesses, and the center portion connecting the two limbs; and

a plurality of electrical contacts for the voltage supply and for the exchange of data with said aircraft cabin module, the
electrical contacts exerting a supporting function for moving the plug pin in a longitudinal direction of the rail component
before the locking of the locking projections;

wherein the plurality of electrical contacts comprise a group of direct voltage contacts configured for connecting to a direct
voltage supply for supplying a direct voltage, a group of alternating voltage contacts configured for connecting to an alternating
voltage supply for supplying an alternating voltage, and a group of data contacts configured for connecting the aircraft cabin
module to an aircraft cabin server for exchanging data between the aircraft cabin module and the aircraft cabin server,

wherein the data contacts each have a predetermined characteristic impedance which amounts to 100 ohm/meter or corresponds
to the characteristic impedance of a data bus used.

US Pat. No. 9,209,614

LINE BRACKET FOR MOUNTING ON A SUPPORT STRUCTURE OF AN AIRPLANE

Airbus Operations GmbH, ...

1. A line bracket for mounting on a support structure of an airplane, the line bracket comprising:
a mounting section for attachment to the support structure;
a U-shaped bracket section for receiving at least one line;
a cover part, wherein the U-shaped bracket section is configured to be closed by the cover part by a clip-on connection,
wherein the mounting section comprises a flat surface for resting against the support structure,
wherein a floor region of the U-shaped bracket section extends essentially at a right angle away from the mounting section,
wherein a first leg region of the bracket section is formed by part of the mounting section and corresponds to an opposite
second leg region for forming an insertion opening for the line, which insertion opening is closeable by way of the cover
part hinged at an end of one of the first and second leg regions, to install the line from a side of the bracket section,

wherein the first leg region inside of the bracket section includes a pre-determined V-shaped supporting surface beveled on
both sides for guiding the line, the pre-determined V-shape of the supporting surface of the first leg region inside of the
bracket section being formed prior to reception of the line.

US Pat. No. 9,108,740

METHOD FOR GENERATING HYDRAULIC POWER IN AN AIRCRAFT, USE OF A HYBRID POWER CONTROL UNIT AND DRIVE SYSTEM

AIRBUS OPERATIONS GMBH, ...

1. A method for generating hydraulic power in an aircraft, the aircraft having a drive system comprising at least one transmission
shaft connected to a hybrid power control unit, the power control unit having an electric motor and a hydraulic displacement
machine connected to a differential gear unit for driving a common output shaft, the method comprising:
arresting the output shaft;
rotating the electric motor such that the hydraulic displacement machine is driven due to the arrested output shaft; and
supplying the fluid flow into a hydraulic system of said aircraft.

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. 9,449,274

METHOD AND DEVICE FOR PREDICTING THE CONDITION OF A COMPONENT OR SYSTEM, COMPUTER PROGRAM PRODUCT

Airbus Operations GmbH, ...

1. A computer-implemented method for predicting the condition of a component or system, in particular for an aircraft or spacecraft,
by trend prediction of the course of a time-dependent series of data points determined at the component or system by measuring,
the method comprising:
providing an optimised decision tree, the input node of which is provided for inputting an input vector, the nodes of which
contain the attributes of the respective input vector and the leaves of which each contain an extrapolation function provided
for trend prediction;

iteratively calculating future data points by an input vector being derived from a time-dependent series of data points and
the decision tree calculating a data point subsequent to the last data point of the time-dependent series of data points from
the input vector in an automated manner, the calculated subsequent data point being added to the time-dependent series of
data points in order to be used for forming a new input vector for the next iteration step.

US Pat. No. 9,193,443

AIR SUCKING VEHICLE TAIL SECTION COMPONENT OR WING SECTION COMPONENT, METHOD FOR PRODUCING AN AIR SUCKING VEHICLE TAIL SECTION COMPONENT AND A WING SECTION COMPONENT AND A VEHICLE, ESPECIALLY AN AIRCRAFT, WITH AN AIR SUCKING VEHIC

Airbus Operations GmbH, ...

1. An air-sucking vehicle tail section component or wing section component, having
an outer delimitation part having microperforation comprising boreholes,
an inner delimitation part having a plurality of suction boreholes comprising fluid connections to the microperforation boreholes,
and

a plurality of connecting webs,
wherein the inner delimitation part is connected via the plurality of connecting webs to the outer delimitation part,
wherein the outer delimitation part comprises a continuously curved shape,
wherein the inner delimitation part is constructed from two or more planar inner delimitation part components connected to
one another on one edge each to form a connection edge, the connection edge being attached to the outer delimitation part,
and

wherein each of the planar inner delimitation part components extends from a front edge of the outer delimitation part such
that the connection edge is formed on an inner side of the front edge.

US Pat. No. 9,046,118

FASTENING DEVICE FOR A MODULE ELEMENT IN AN AIRPLANE

Airbus Operations GmbH, ...

1. A fastening device for attaching a module element to a support structure in an aircraft, the fastening device comprising:
a stud having a first end defining a broadened head configured to engage in a support recess of the support structure and
a section which adjoins the head and defines adjacent to the head first and second lateral dimensions, the second lateral
dimension larger than the first lateral dimension and disposed at least substantially perpendicularly to the first lateral
dimension, the stud further having a second end opposite the first end, the second end connected to a lever which is movable
between open and closed positions relative to the stud,

a bushing provided on and longitudinally movable along the stud, the bushing supporting an electrically conductive leaf spring
and configured to support an outer wall of the module element, the leaf spring configured to contact an outside of the outer
wall of the module element, the leaf spring having, outside of the bushing, one of a surface contact means and at least one
bearing point configured to contact the support structure, wherein the bushing defines an outer circumference between the
broadened head and the second end of the stud, at least a portion of the outer circumference having a flattened locking portion,
wherein the outer circumference of the bushing form-fittingly receives the leaf spring and is configured to receive the outer
wall of the module element in a form-fitting manner, and wherein the flattened locking portion produces the form-fitting between
the bushing and the outer wall of the module element and the leaf spring, and

an eccentric actuated by the lever and responsive to movement of the lever into the closed position to move the bushing along
the stud towards the head.

US Pat. No. 10,111,283

ACTIVE TEMPERATURE CONTROL FOR INDUCTION HEATING

AIRBUS OPERATIONS GMBH, ...

1. An induction heating system for controlling a process temperature for induction heating of a workpiece, the induction heating system comprising:an inductor configured to generate an alternating magnetic field in response to an alternating current supplied thereto;
a magnetic load comprising a magnetic material, the magnetic material having a Curie temperature and being configured to generate heat in response to the alternating magnetic field being applied thereto, the magnetic load being connectable to the workpiece in a heat-conducting manner so as to transfer the generated heat to the workpiece; and
a control unit configured to control the process temperature by adjusting the alternating magnetic field when the temperature of the magnetic material is in a temperature control range around or below the Curie temperature of the magnetic material,
wherein the control unit is further configured to adjust a variable size of the temperature control range dependent on the magnetic material of the magnetic load, wherein the control unit is further configured to refrain from controlling the process temperature, when the temperature of the magnetic material is outside the temperature control range, and wherein the temperature control range is defined by a range in which a change of magnetic permeability of the magnetic material over temperature is higher than a predetermined value.

US Pat. No. 9,364,967

DEVICE FOR CUTTING TO SIZE AND HANDLING A SUBSTANTIALLY EXTENSIVE BLANK FROM A CFK SEMI-FINISHED PRODUCT AND METHOD

Airbus Operations GmbH, ...

1. A method for cutting and lifting a blank out of Carbon Fibre Reinforced Polymer (CFRP) semi-finished product by a device,
comprising:
depositing a substantially planar CFRP semi-finished product onto a cutting table,
cutting a blank which has a predetermined peripheral contour out of the CFRP semi-finished product,
lowering a vacuum effector for drawing up the blank by suction and depositing it, at least one blank electrode contacting
the blank and at least one peripheral electrode contacting a separated or separate peripheral portion of the CFRP semi-finished
product,

raising the blank by the vacuum effector above a measuring height, and
measuring a current flowing between the at least two electrodes by a measuring means, a measurement of the current of more
than 0 mA indicating an incomplete separation of the blank from the CFRP semi-finished product; wherein the current is increased
for a short time to a maximum value upon the blank reaching the measuring height and when the current has a measured value
of more than 0 mA, to produce a complete separation between the blank and the CFRP semi-finished product by the melting of
at least one carbon fibre bridge connecting the blank with the CFRP semi-finished product;

positioning the completely separated blank; and
delivering the completely separated blank to a mould in an Resin Transfer Moulding (RTM) process.

US Pat. No. 9,340,287

PASSENGER SERVICE SYSTEM WITH IMPROVED AIR GUIDANCE

AIRBUS OPERATIONS GMBH, ...

1. A passenger service system comprising:
an individual ventilation arrangement, wherein at least one air nozzle of the individual ventilation arrangement is disposed
in the region of a service surface of the passenger service system,

wherein the service surface of the passenger service system comprises a substantially flat portion as well as a buckled portion,
which is curved convexly relative to the substantially flat portion and extends along a longitudinal axis of the passenger
service system.

US Pat. No. 9,327,836

CABIN ATTENDANT SEAT, ARRANGEMENT COMPRISING A CABIN ATTENDANT SEAT AND AIRCRAFT AREA

Airbus Operations GmbH, ...

1. A cabin attendant seat comprising:
a carrier element which comprises a backrest section and a base section that carries said backrest section; and
a seat element fastened to a front side of said carrier element,
wherein at least one first stowage compartment is integrated into the carrier element, an inclined section of a rear wall
of the carrier element being inclined, at least along a section of the first stowage compartment integrated into said carrier
element, in such a way that a cross-sectional area of said carrier element increases in the direction of the base section
of said carrier element,

wherein the shape of the inclined section of the rear wall of the carrier element is permanently adapted to the shape of a
rear side of a backrest of a passenger seat in an inclined position.

US Pat. No. 9,321,535

SYSTEM AND PROCESS FOR COOLING AN AIRCRAFT ZONE USING AN AIRCRAFT-EXTERNAL AIR ASSEMBLY

Airbus Operations GmbH, ...

1. System for cooling an aircraft zone, with:
a mixing chamber which is connected to an air-conditioning assembly for making cool air available and to a recirculated-air
conveying device for supplying recirculated air into the mixing chamber wherein in the mixing chamber the air made available
by the air conditioning assembly and recirculated air are mixed, and

an aircraft-side air-distribution system which includes at least one line connecting the mixing chamber to the aircraft zone
to be cooled and also at least one line that is connectable to an aircraft-external air-generating assembly in order to route
air made available by the aircraft-external air-generating assembly into the aircraft-side air-distribution system, characterized
in that the system includes a detection device including at least one temperature sensor and at least one pressure sensor
for detecting a temperature and pressure in the aircraft-side air-distribution system and/or in the mixing chamber and also
a control unit which is set up to receive and evaluate signals made available by the detection device and, when the system
is connected to the aircraft-external air-generating assembly, to control the operation of the aircraft-external air-generating
assembly in a manner depending on the signals made available by the detection device.

US Pat. No. 9,315,256

FLAP ARRANGEMENT AND AIRCRAFT WITH AT LEAST ONE FLAP ARRANGEMENT

Airbus Operations GmbH, ...

1. A flap arrangement, comprising:
a basic body,
a hinge arrangement, and
a flap movably held on the basic body by the hinge arrangement,
wherein the hinge arrangement comprises at least first, second, and third points of articulation spaced apart from each other
at a predetermined distance from one another and arranged on a shared hinge line such that, in an absence of a load acting
on the flap arrangement, the hinge line is a straight line,

wherein, at the first and second points of articulation, the flap is rigidly connected to the basic body such that a deformation
of the flap at the first and second points of articulation is congruent to a deformation of the basic body, and

wherein, at remaining one or more non-rigid points of articulation, in each case allow a local relative movement between the
basic body and the flap in at least one first spatial direction perpendicularly to the hinge line is allowed such that the
deformation of the flap at the remaining one or more non-rigid points of articulation is not congruent to the deformation
of the basic body.

US Pat. No. 9,279,669

OPTICAL MEASURING DEVICE WITH A SLIDER AND OPTICAL MEASUREMENT METHOD

Airbus Operations GmbH, ...

1. An optical measuring device for measuring a surface contour of an object, comprising:
a tripod;
a camera platform mounted on the tripod;
at least first and second photo cameras arranged on the camera platform for imaging the object comprising marking elements,
wherein the at least first and second photo cameras are arranged on the camera platform to carry out imaging the object from
first and second different perspectives; and

a displacement device arranged between the platform and the tripod for the linear displacement of the camera platform in three
directions independent of each other,

wherein the displacement device comprises first, second and third precision slide guides operating perpendicularly in relation
to each other, wherein each of the first, second and third precision slide guides comprises a calibrated measuring system
for measuring the displacement path.

US Pat. No. 9,211,945

INSULATION ARRANGEMENT WITH VENTILATION OPENINGS FOR AIRCRAFT

AIRBUS OPERATIONS GMBH, ...

1. An insulation arrangement for thermally and acoustically insulating an aircraft, comprising:
a plurality of insulation packages that are arrangeable in an intermediate space enclosed by a cabin paneling and a fuselage
wall of the aircraft and comprise an insulating material and welded cover films,

wherein all cover films are realized in an airtight and waterproof fashion, and the plurality of insulation packages comprise
ventilation openings that penetrate the cover films and are arranged in such a way that they are fluidically connected to
a gap formed between the insulation arrangement and the fuselage wall;

wherein cover flaps are arranged on at least one of the plurality of insulation packages for covering ventilation openings
of the at least one insulation package; and

wherein the cover flaps are made of a flat, film-like material and comprise an attachment surface, as well as a bend arranged
in between.

US Pat. No. 9,205,909

AIRCRAFT DOOR ARRANGEMENT

Airbus Operations GmbH, ...

1. An aircraft door arrangement comprising
a door hingedly mounted to the fuselage of an aircraft such that it is selectively pivotally movable into a closed position
in which it closes an aperture in the fuselage and into an open position in which it provides access through the aperture,

a linear actuating mechanism adapted to be operable for selectively moving the door between its open and closed positions,
wherein the linear actuating mechanism comprises an elongate straight casing and a rod which is disposed in the casing and
extends partially from a longitudinal end of the casing and which is selectively extendable and retractable by operating the
linear actuating mechanism, and

the casing being mounted by an actuator mounting between and supported by two spaced elements of the primary structure of
the aircraft such that it is pivotable about a rotation axis,

wherein the longitudinal end of the rod extending from the casing is pivotally coupled to the door, such that upon extending
the rod from the casing the door is moved into its open position and upon retracting the rod into the casing the door is moved
into its closed position,

the actuator mounting comprising a rigid mounting component comprising three elongate legs extending in a common plane together
with the casing and the rotation axis and each having a first and a second longitudinal end, wherein the three elongate legs
include a first leg and a second leg of equal length and shape and a third leg, and wherein

each of the first and second legs is connected with its respective first end to the casing such that the first leg and the
second leg symmetrically extend at an angle away from the casing at opposite sides thereof, and that loads acting on the casing
upon operating the linear actuating mechanism are transferred to and along the first and second legs,

the first end of the third leg is connected to the second end of the first leg and the second end of the third leg is connected
to the second end of the second leg such that the third leg is connected between the second ends of the first and second legs,
and

each of the second ends of the first and second legs is rotatably coupled on the rotation axis to another one of the spaced
elements of the primary structure of the aircraft such that the mounting component is pivotable about the rotation axis.

US Pat. No. 9,180,968

PARTITION WALL FOR AN AEROPLANE CABIN, AND AN AEROPLANE

Airbus Operations GmbH, ...

1. A partition wall configured to separate cabin areas of an aeroplane, wherein the partition wall has a sandwich-type planar
structure, and wherein the partition wall comprises:
a multiplicity of defined zones,
holding fixtures selectively positioned in a desired configuration in each of the defined zones to connect accessories to
the partition wall,

the planar structure being dimensioned and provided with sufficient holding fixtures to allow for a maximum number of accessories
to be connected for the dimension of the planar structure,

wherein the planar structure has a core having at least one folded cell-type sheet with a multiplicity of ventilation passages,
the ventilation passages being open at least at one end to an open border region of the partition wall.

US Pat. No. 9,073,640

DISPOSITION ZONE IN AN AIRCRAFT PASSENGER CABIN

Airbus Operations GmbH, ...

1. An aircraft having at least one passenger cabin comprising:
a door entry area or door exit area for passengers and for flight attendants to enter or exit the aircraft, the area being
visually separated from the rest of the at least one passenger cabin; and

at least one multifunctional disposition zone,
the multifunctional disposition zone comprising the door entry area or door exit area and a module comprising at least one
flexible, variable or mobile element assigned to at least one partition wall or monument in the multifunctional disposition
zone, said module being integrated with at least one partition wall or monument,

wherein the module assumes at least one of a closed state and an open state;
wherein in the open state of the module, the door entry area or door exit area is used as the multifunctional disposition
zone while cruising such that the module at least partly obstructs the entry and exit through the door entry area or door
exit area, and the multifunctional disposition zone forms a plurality of different working areas configured in the form of
service and/or comfort facilities for passengers or flight attendants during a flight phase;

wherein in the open state of the module, the multifunctional disposition zone is enclosed on one side by a door adjacent to
the door entry area or door exit area; and

wherein in the closed state of the module, the at least one flexible, variable or mobile element is placed in a space-saving
and secure fashion during takeoff and landing phases of the aircraft, and the multifunctional disposition zone forms an unobstructed
entry and exit for the passengers and for flight attendants into and out of the aircraft.

US Pat. No. 9,463,877

MOUNTING DEVICE FOR SUSPENDING A VISUAL BARRIER OF A PASSENGER CABIN OF A MEANS OF TRANSPORT

AIRBUS OPERATIONS GMBH, ...

1. A mounting device for mounting a visual barrier of two areas of a passenger cabin of a transport, the mounting device comprising:
a rail;
a coupling device; and
a mounting module configured for mounting the visual barrier,
wherein the mounting module is movably attached to the rail with the coupling device so that the mounting module is configured
to carry out a sliding movement from a retracted position along a longitudinal axis of the rail, and

wherein the mounting module is configured with the coupling device, to carry out a movement after sliding, which movement
after sliding does not take place along the longitudinal axis of the rail, and which movement after sliding ends in an extended
position of the mounting module.

US Pat. No. 9,394,055

MIXER ASSEMBLY FOR AN AIRCRAFT AIR CONDITIONING SYSTEM

AIRBUS OPERATIONS GMBH, ...

1. A mixer assembly for an aircraft air conditioning system, comprising:
first and second fresh air lines, which are configured to be flowed-through with cold fresh air during operation of the mixer
assembly,

first and second recirculation air lines, which are configured to be flowed through with recirculation air discharged from
an aircraft cabin during operation of the mixer assembly,

a first premixer, which is connected to the first fresh air line and the first recirculation air line and is adapted configured
to mix the fresh air conveyed through the first fresh air line into the first premixer with the recirculation air conveyed
through the first recirculation air line into the first premixer,

a second premixer, which is connected to the second fresh air line and the second recirculation air line and is configured
to mix the fresh air conveyed through the fresh air line into the second premixer with the recirculation air conveyed through
the second recirculation air line into the second premixer,

a main mixer, which is connected by a first premixed air line to the first premixer and by a second premixed air line to the
second premixer, wherein the main mixer is configured to be supplied through the first premixed air line and the second premixed
air line exclusively with premixed air from the first and/or the second premixer,

a first filter device disposed in the first recirculation air line, and
a second filter device disposed in the second recirculation air line,
a first connection line, which branches off from the first recirculation air line downstream of the first filter device disposed
in the first recirculation air line and opens out into the second recirculation air line downstream of the second filter device
disposed in the second recirculation air line.

US Pat. No. 9,248,911

VARIABLE-LENGTH RAIL COVER

Airbus Operations GmbH, ...

1. A seat arrangement for a passenger cabin of a means of transport, with the seat arrangement comprising:
a seat rail;
a first seat and a second seat;
a rail cover, the rail cover comprising:
a cover element for completely covering a longitudinal portion of the seat rail;
wherein the cover element extends at least in part in a plane of extension formed by a longitudinal direction and a transverse
direction of the rail cover;

wherein the cover element comprises a first, rigid, longitudinal portion and a second longitudinal portion;
wherein the first longitudinal portion and the second longitudinal portion are mechanically coupled together by a flexible
portion, the flexible portion being flexible relative to the first rigid longitudinal portion;

wherein the second longitudinal portion is configured to carry out a pivoting movement in a direction across the plane of
extension;

wherein the second seat is arranged behind the first seat in the longitudinal direction of the seat rail;
wherein the first seat and the second seat are configured to be moved in an accommodation space of the seat rail in the longitudinal
direction of the seat rail; and

wherein the rail cover is arranged to completely cover the accommodation space of the seat rail on a seat-rail longitudinal
portion extending from the first seat to the second seat;

wherein the first seat comprises a first leg mechanically coupling the first seat to the seat rail and the second seat comprises
a second seat leg mechanically coupling the second seat to the seat rail;

wherein the first longitudinal portion of the rail cover extends in the direction of the seat leg of the first seat;
wherein the second longitudinal portion of the rail cover extends in the direction of the seat leg of the second seat; and
wherein the second longitudinal portion of the rail cover is arranged to carry out the pivoting movement when the second seat
is moved in the direction of the first seat, so that as a result of the pivoting movement the second longitudinal portion
is moved from a state in which the second longitudinal portion covers the seat rail to state in which the second longitudinal
portion does not cover the seat rail;

wherein during the pivoting movement the second longitudinal portion of the rail cover is configured to move along the seat
leg of the second seat in the direction of a seat surface of the second seat and pivots about a pivot axis transverse to the
longitudinal direction.

US Pat. No. 9,394,691

FLOOR PANEL WITH INTEGRATED CABLE CHANNEL

AIRBUS OPERATIONS GMBH, ...

1. A floor panel for a floor of a passenger cabin of a mobile platform, the floor panel comprising:
a base body having a cable channel extending along a longitudinal direction of the base body for accommodating electric cables;
and

a planar cover element arranged on top of the cable channel and a part of the top surface of the base body for covering the
cable channel, the cover element firmly attached to the base body at positions left and right of the cable channel;

wherein the base body comprises a sandwich component that includes a first honeycomb structure and a second honeycomb structure,
the first honeycomb structure extending from a left edge of the base body to a left side of the cable channel and the second
honeycomb structure extending from a right edge of the base body to a right side of the cable channel, the cable channel being
arranged between the first and second honeycomb structures;

wherein both the first honeycomb structure and the second honeycomb structure share a common top cover layer and a common
bottom cover layer;

wherein the top cover layer and the bottom cover layer meet each other in the region of the cable channel to form the bottom
of the cable channel; and

wherein the floor panel is self-supporting when being supported along its left and right edges only if the cover element is
attached to the base body.

US Pat. No. 9,376,047

TRAY ARRANGEMENT FOR A VEHICLE, PASSENGER SEAT AND AIRCRAFT

AIRBUS OPERATIONS GMBH, ...

1. A tray arrangement, comprising:
a tray element having a first side and a second side;
a bearing arrangement for supporting the tray element; and
a holding arrangement configured to securely hold a mobile device on the second side and receiving the mobile device therein;
wherein the bearing arrangement is configured to pivot the tray element about an axis which lies in a plane of or parallel
to the tray element;

wherein the holding arrangement comprises at least one elongate holding element; and
wherein when the tray is in an upright position, the holding arrangement positions the mobile device to face substantially
upward and when the tray is rotated to face substantially downward, the holding arrangement retains the mobile device on the
tray.

US Pat. No. 9,371,126

AIRCRAFT FUSELAGE

Airbus Operations GmbH, ...

1. An aircraft fuselage comprising:
an outer skin stiffened by a backing structure, the outer skin delimits at least one passenger cabin and one cargo hold,
the cargo hold is arranged below the at least one passenger cabin in a vertical direction of the fuselage,
the backing structure located in the cargo hold and above a cargo-hold floor framework comprises at least two lateral quasi-joints,
and the backing structure located below the cargo-hold floor framework comprises at least one further quasi-joint,

a multitude of energy absorption devices located in the cargo hold are arranged in a longitudinal direction of the fuselage,
the multitude of energy absorption devices are arranged one behind the other and act in a transverse direction of the fuselage
and are arranged for absorbing tensile loads,

at least two structural components of the backing structure that are each pivotable about their respective lateral quasi-joints,
wherein in the event of a crash the at least two structural components can be freely pivoted on the axes of rotation of the
respective lateral quasi-joints.

US Pat. No. 9,340,286

AUTOMATIC TRANSPORT DEVICE FOR CARGO LOADING SYSTEM

Airbus Operations GmbH, ...

1. An automated transport device for moving a cargo unit within a cargo compartment of an aircraft, comprising:
a base body to carry the cargo unit;
a shifting device to generate a movement of the base body along a floor of the cargo compartment perpendicular to a longitudinal
axis of the aircraft and, after that, along the longitudinal axis of the aircraft without rotation of the base body;

a coupling for providing at least one of an electrical, a mechanical and a fluid link to a second transport device;
wherein a position of the coupling is displaceable along at least a section of an edge of the base body.

US Pat. No. 9,309,913

FASTENING ARRANGEMENT AND FASTENING FITTING FOR FASTENING A COMPONENT TO A STRUCTURAL COMPONENT OF AN AIRCRAFT OR SPACECRAFT

Airbus Operations GmbH, ...

1. A fastening arrangement for fastening a component, in particular a cabin component, to a structural component of an aircraft
or spacecraft, comprising:
a structural component with a geometrical shape and which comprises a connection surface;
a fastening fitting which has a geometry matched to the geometrical shape of the structural component, has a connection portion
associated with the connection surface of the structural component and is produced from a thermoplastic injection-molding
material, wherein the fastening fitting and the structural component have matched trapezium-shaped cross-sectional geometries
and matched foot portions; and

an elastomeric adhesive joint for stable fastening of the connection portion of the fastening fitting to the associated connection
surface of the structural component.

US Pat. No. 9,305,731

SUPPLY SYSTEM FOR AN AIRCRAFT, USE OF A SHIELDED SUPPLY LINE IN AN AIRCRAFT AND AN AIRCRAFT WITH A SUPPLY SYSTEM

Airbus Operations GmbH, ...

1. A supply system for supplying energy in an aircraft, the supply system comprising:
at least one electrical line,
a source of direct electrical current connected to the at least one electrical line,
an electrically conductive shield, and
a detection unit having at least first and second electrical inputs,
wherein the at least one electrical line comprises at least one core connectable to a pole of the current source,
wherein the shield surrounds the at least one core under a distance and creates an intermediate space between the at least
one core and the shield,

wherein at least one port of the detection unit is connected to the at least one core,
wherein said detection unit is adapted for detecting a differential current over the at least one core or an absolute current
between two of the shield, the at least one core and a ground potential;

wherein said detection unit is adapted for generating a warning signal if a predetermined threshold value for the detected
current value is exceeded; and

wherein the detection unit is coupled with at least one switch in the at least one core for interrupting the current transferred
by the at least one core if the warning signal is generated.

US Pat. No. 9,434,484

TRANSPORT DEVICE FOR USE WHEN MOUNTING INTERIOR COMPONENT MODULES IN AN AIRCRAFT

Airbus Operations GmbH, ...

1. A transport device for use when mounting interior component modules in an aircraft, comprising:
an undercarriage having a plurality of wheels coupled thereto, and
an interior component module carrier unit, which is supported on the undercarriage and adapted to be connected to an interior
component module, which has been preassembled outside of the aircraft, in order to transport the interior component module
with the aid of the transport device into a final assembly position in an aircraft fuselage element, the interior component
module carrier unit having a two-piece construction comprising an L-shaped carrier unit connected to the undercarriage and
a C-shaped carrier unit connected to the L-shaped carrier unit,

wherein at least a part of the interior component module carrier unit is movable in such a way relative to the undercarriage
that the interior component module connected to the interior component module carrier unit is movable horizontally and vertically
relative to the undercarriage,

and wherein the transport device is provided with a guide device in the form of a projection, separate from the plurality
of wheels, coupled to the undercarriage, which during the positioning of the interior component module in its final assembly
position in the aircraft fuselage element, is adapted to interact with a complementary guide device that is provided in the
aircraft fuselage element.

US Pat. No. 9,358,733

METHOD AND A DEVICE FOR THE MANUFACTURE OF A FIBRE COMPOSITE COMPONENT, AND A FIBRE COMPOSITE COMPONENT

Airbus Operations GmbH, ...

1. A method for the manufacture of at least one fibre composite component, comprising the steps:
preparing a mould core with at least one convexity,
arranging fibre material on the mould core to form a body of material, wherein a bulge-form body section is formed in the
region of the convexity,

impregnating the body of material with a resin,
curing the resin to form a cured body of material,
removing the cured body of material from the mould core,
opening the bulge-form body section after removing the cured body of material from the mould core such that a hole is formed,
while allowing an integral collar surrounding the hole to remain in position.

US Pat. No. 9,211,954

AIR SUPPLY SYSTEM OF AN AIRCRAFT AND METHOD FOR MIXING TWO AIR STREAMS IN AN AIR SUPPLY SYSTEM

Airbus Operations GmbH, ...

1. An air supply system of an aircraft, in particular of a passenger aircraft, comprising:
a fresh air system, through which fresh air can be supplied to an aircraft cabin, the fresh air system including a fresh air
blower,

an aircraft air conditioning system, including a heat exchanger, disposed in an installation space of the air conditioning
system,

a circulating air system, which is coupled to the fresh air system and through which used cabin air can be supplied to the
fresh air system,

a cooling air system for cooling the air conditioning system, the cooling air system including a cooling air blower disposed
upstream of and fluidly coupled to the heat exchanger such that cooling air supplied by the cooling air blower flows through
the heat exchanger,

a ventilation system for ventilating the installation space of the air conditioning system,
a device for fluidically coupling the cooling air system and the ventilation system disposed downstream of the installation
space such that the cooling air flowing through the heat exchanger also flows through the device, the device configured inside
the fuselage such that a flow of ventilation air through the installation space is driven by a suction effect brought about
by the cooling air flowing through the device, and

a common motor configured to drive both the cooling air blower in the cooling air system and the fresh air blower in the fresh
air system.

US Pat. No. 9,180,957

METHOD FOR INSTALLING A DOME-SHAPED PRESSURE BULKHEAD IN A REAR SECTION OF AN AIRCRAFT, AND DEVICE FOR CARRYING OUT THE METHOD

Airbus Operations GmbH, ...

1. A method for assembling a dome-shaped pressure bulkhead on a one-piece, substantially conical tail section for an aircraft,
wherein the tail section has a connection region and an end region, the method comprising:
a) connecting an edge angle formed by a plurality of edge angle segments to the pressure bulkhead;
b) horizontally receiving a prefabricated tail section in a horizontal placement area, wherein the tail section comprises
a longitudinal axis;

c) introducing the tail section into a swivel frame, wherein the tail section is rotatable by the swivel frame about its longitudinal
axis from its horizontal position to a vertical position, wherein the swivel frame receives and holds the tail section inside
a portion of the frame;

d) swivelling the tail section using the swivel frame from the horizontal position into the vertical position, with the connection
region of the tail section pointing upwards

e) horizontally positioning and centering the pressure bulkhead on the connection region; and
f) joining the pressure bulkhead to the tail section in the area of the connection region, wherein a transverse butt strap
formed by a plurality of transverse butt strap segments is connected to the connection region of the tail section and the
pressure bulkhead is centered and connected to the transverse butt strap, and wherein immediately after horizontally positioning
and centering the pressure bulkhead on the connection region the transverse butt strap is partially fastened to the edge angle
of the pressure bulkhead to fix the position.

US Pat. No. 9,096,021

METHOD AND SHAPING DEVICE FOR PRODUCING A COMPOSITE FIBER COMPONENT FOR AIR AND SPACE TRAVEL

Airbus Operations GmbH, ...

1. A method for producing a reinforced fibre composite component for aviation and aerospace with the following steps:
(i) providing a forming tool with a predefined mould portion, wherein the mould portion is formed at an edge region of the
forming tool and comprises a first recess parallel to a width direction of the forming tool formed in a horizontal section
of said forming tool and a second recess parallel to a height direction of the forming tool formed in a vertical section of
said forming tool, a junction of said first and second recess being rounded;

(ii) moulding a forming/support element comprising one of a metal material and a composite material by means of the mould
portion of the forming tool, by bending the forming/support element around the mould portion, wherein said forming/support
element corresponds in thickness to a depth of the first and second recess in the mould portion respectively and wherein an
outer surface of the bent forming/support element runs level with adjacent surfaces of the forming tool;

(iii) depositing a semi-finished fibre product at least in portions on the shaped forming/support element;
(iv) moulding the deposited semi-finished fibre product by means of the forming/support element to form at least one reinforcing
portion;

(v) removing the forming/support element together with the reinforcing portion formed on this element from the forming tool;
(vi) defined positioning of the reinforcing portion thus formed with respect to an associated fibre composite component portion
by supporting with the forming/support element; and

(vii) curing the reinforced portion to form the reinforced fibre composite component.

US Pat. No. 9,502,787

METALLIC PRIMARY-STRUCTURE ELEMENT FOR POTENTIAL EQUALIZATION IN AN AIRCRAFT

AIRBUS OPERATIONS GMBH, ...

1. An electrically conductive metallic primary-structure element for an aircraft, comprising:
a recess; and
a ground connection that is attached to the metallic primary-structure element in the recess, the ground connection couples
in an electrically conductive manner to the metallic primary-structure element, and configured to receive a connector.

US Pat. No. 9,308,996

LUGGAGE COMPARTMENT AND MEANS OF TRANSPORT

AIRBUS OPERATIONS GMBH, ...

1. A luggage compartment for being mounted in a means of transport, the luggage compartment comprising:
a housing for storing luggage, the housing comprising a top wall, a rear wall, a bottom wall and an opening;
a connecting element for mounting the housing to a first structural element of the means of transport, the connecting element
pivotably attached to the top wall or the side wall of the housing at a first section of the connecting element;

a sliding element attached to an edge defined by the top wall and the rear wall of the housing;
wherein the connecting element is adapted for being pivotably attached to the first structural element of the means of transport
at a second section of the connecting element; and

wherein the sliding element is adapted for being movably connected to a rail, and the rail is attached to a second structural
element of the means of transport.

US Pat. No. 9,227,728

AIRCRAFT CABIN PARTITION MONUMENT WITH STOWAGE COMPARTMENT

Airbus Operations GmbH, ...

1. An aircraft cabin partition monument comprising:
a partition wall element, and
a stowage compartment,
the stowage compartment comprising a cover plate element and at least one sidewall element,
the stowage compartment being convertible between a state of rest, wherein the cover plate element and the sidewall element
extend substantially parallel to the partition wall element, and a state of operation, wherein the cover plate element and
the sidewall element extend relative to the partition wall element such that the cover plate element and the sidewall element
define a stowage space arranged adjacent to the partition wall element, wherein the stowage compartment, in its state of operation,
includes at least one trolley.

US Pat. No. 9,903,019

COMPOSITION FOR THE LOCAL APPLICATION OF CHEMICAL CONVERSION LAYERS

Airbus Operations GmbH, ...

1. A method for using a composition containing at least one active component chosen from chromium(III) compounds, vanadium(IV)
compounds, phosphomolybdic acid, titanium compounds, zirconium compounds, lanthanum compounds and their combinations and mixtures,
as well as at least one thickener, and having a viscosity in the range of from 10 mPa*s to 10000 mPa*s for the diffusion-controlled
formation of a conversion layer, comprising:
(i) providing a composition containing at least one active component chosen from chromium(III) compounds, vanadium(IV) compounds,
phosphomolybdic acid, titanium compounds, zirconium compounds, lanthanum compounds and their combinations and mixtures, as
well as at least one thickener, and having a viscosity in the range of from 10 mPa*s to 10000 mPa*s;

(ii) applying the composition onto a metal surface in a quantity of from 9 mg to 200 mg per cm2;

(iii) leaving the composition on the metal surface for a time of exposure of 1-30 min. and then rinsing the composition off,
wherein the composition is applied onto the metal surface by wiping onto the metal surface.

US Pat. No. 9,720,011

MONITORING DEVICE AND METHOD FOR MONITORING A MOVEMENT PROFILE OF A USER IN THE REGION OF AN ACTUATING ELEMENT OF AN AIRCRAFT OR SPACECRAFT

Airbus Operations GmbH, ...

1. A monitoring device for monitoring a movement profile of a user in the region of an actuating element of an aircraft or
spacecraft, comprising:
at least one movement sensor which is configured to detect a first monitoring space of the monitoring device and at the same
time a second monitoring space of the monitoring device which differs from the first monitoring space;

a first detection region, which is elliptically shaped; and
a second detection region, which is elliptically shaped, the first detection region and the second detection region extending
from the monitoring device along their respective major axes and overlapping each other at least in portions, the first detection
region representing the first monitoring space of the monitoring device, and a differential region of the first detection
region and of the second detection region, which can only be detected by the second detection region, representing the second
monitoring space of the monitoring device;

wherein the detection regions are configured spatially with a length along the respective major axis of the second detection
region being greater than a length along the respective major axis of the first detection region, and

wherein the major axis of the first detection region is arranged coaxially to the major axis of the second detection region.

US Pat. No. 9,458,866

STRUCTURAL ELEMENT FOR AN AIRCRAFT AND/OR SPACECRAFT AND METHOD FOR PRODUCING SUCH A STRUCTURAL ELEMENT

Airbus Operations GmbH, ...

1. A structural element for an aircraft and spacecraft, the structural element comprising:
a core having core regions which are uncoupled from one another by an expansion joint arranged between the core regions;
wherein the expansion joint comprises a silicone material or a rubber-like material such that the expansion joint is adapted
to mechanically uncouple the core regions from one another such that stresses occurring in a core region are not transmitted
to further core regions.

US Pat. No. 9,452,901

SYSTEM AND METHOD FOR LOADING AND UNLOADING A CARGO COMPARTMENT

AIRBUS OPERATIONS GMBH, ...

1. A system for loading and unloading cargo into and from a cargo compartment of a vehicle, comprising:
a cargo receiving device configured to receive and secure items of packed or bulk cargo, said cargo receiving device comprising:
a base structure arrangement having a lower contact surface, and
a locking mechanism configured to engage one or more corresponding holding members provided in the cargo compartment, and
a transport device for transporting the cargo receiving device to a desired position in or out of the cargo compartment of
the vehicle, said transport device comprising:

a transport structure arrangement having a upper contact surface configured to be disposed in abutting contact to said lower
contact surface of the cargo receiving device and to support the cargo receiving device by the abutting contact,

a drive unit configured to effect movement of the transport device relative and parallel to a surface on which the transport
device is disposed,

a lift unit configured to effect movement of the transport structure arrangement relative and transversely to a surface on
which the transport device is disposed, and

an actuating unit configured to actuate the locking mechanism of the cargo receiving device.

US Pat. No. 9,316,267

UNIVERSAL JOINT ASSEMBLY

Airbus Operations GmbH, ...

1. A universal joint member for transmitting torque between first and second shafts of a drive mechanism, the joint member
comprising:
a first pivot axis for pivoting connection to the first shaft of the drive mechanism, whereby the first pivot axis extends
substantially perpendicular to a rotational axis of the first shaft; and

a second pivot axis for pivoting connection to the second shaft of the drive mechanism, whereby the second pivot axis extends
substantially perpendicular to the first pivot axis and substantially perpendicular to a rotational axis of the second shaft,

wherein a cavity extends through the universal joint member for receiving a pivot pin along the second pivot axis, and
wherein the pivot pin is configured to connect the universal joint member to the second shaft.