NL2009395C2 - Locking assembly for locking an aircraft interior structure to an aircraft main support structure. - Google Patents

Locking assembly for locking an aircraft interior structure to an aircraft main support structure. Download PDF

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Publication number
NL2009395C2
NL2009395C2 NL2009395A NL2009395A NL2009395C2 NL 2009395 C2 NL2009395 C2 NL 2009395C2 NL 2009395 A NL2009395 A NL 2009395A NL 2009395 A NL2009395 A NL 2009395A NL 2009395 C2 NL2009395 C2 NL 2009395C2
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NL
Netherlands
Prior art keywords
eccentric
bushing
locking
bush
aircraft
Prior art date
Application number
NL2009395A
Other languages
Dutch (nl)
Inventor
Maarten Michiel Korenromp
Original Assignee
Driessen Aerospace Group Nv
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Driessen Aerospace Group Nv filed Critical Driessen Aerospace Group Nv
Priority to NL2009395A priority Critical patent/NL2009395C2/en
Priority to PCT/NL2013/050622 priority patent/WO2014035241A1/en
Application granted granted Critical
Publication of NL2009395C2 publication Critical patent/NL2009395C2/en

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Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D11/00—Passenger or crew accommodation; Flight-deck installations not otherwise provided for
    • B64D11/04—Galleys
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16B—DEVICES FOR FASTENING OR SECURING CONSTRUCTIONAL ELEMENTS OR MACHINE PARTS TOGETHER, e.g. NAILS, BOLTS, CIRCLIPS, CLAMPS, CLIPS OR WEDGES; JOINTS OR JOINTING
    • F16B2200/00—Constructional details of connections not covered for in other groups of this subclass
    • F16B2200/95—Constructional details of connections not covered for in other groups of this subclass with markings, colours, indicators or the like
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16B—DEVICES FOR FASTENING OR SECURING CONSTRUCTIONAL ELEMENTS OR MACHINE PARTS TOGETHER, e.g. NAILS, BOLTS, CIRCLIPS, CLAMPS, CLIPS OR WEDGES; JOINTS OR JOINTING
    • F16B5/00—Joining sheets or plates, e.g. panels, to one another or to strips or bars parallel to them
    • F16B5/02—Joining sheets or plates, e.g. panels, to one another or to strips or bars parallel to them by means of fastening members using screw-thread
    • F16B5/0216—Joining sheets or plates, e.g. panels, to one another or to strips or bars parallel to them by means of fastening members using screw-thread the position of the plates to be connected being adjustable
    • F16B5/0233—Joining sheets or plates, e.g. panels, to one another or to strips or bars parallel to them by means of fastening members using screw-thread the position of the plates to be connected being adjustable allowing for adjustment perpendicular to the plane of the plates

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  • Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Connection Of Plates (AREA)

Abstract

The invention relates to a locking assembly (16) for locking an aircraft interior structure, such as a galley, to an aircraft main support structure, such as a floor hard point, comprising : -a cylindrical adjustment bushing (4) having a hollow cylindrical space (15), the adjustment bushing having an outer thread (12) that engages an inner thread of a through-hole (3) arranged in a fitting (7) attachable to or part of the aircraft interior structure, wherein the adjustment bushing can be rotated around its centre line to adjust the height of the fitting in a Z-direction, -a cylindrical outer eccentric bushing (2) inserted in the hollow cylindrical space (So) of the adjustment bushing, the outer eccentric bushing having an eccentric longitudinal hollow cylindrical space whose centre line is placed at a distance from the centre line of the cylindrical outer eccentric bushing, -a cylindrical inner eccentric bushing (1) inserted in the hollow cylindrical space of the outer eccentric bushing, the inner eccentric bushing having an eccentric longitudinal hollow cylindrical space (Si) whose centre line is placed at a distance from the centre line of the inner eccentric bushing, the inner and outer eccentric bushings (1, 2) allowing adjustment of the fitting in a plane perpendicular to the Z-direction, -a locking bolt (8) inserted in the hollow cylindrical space of the inner eccentric bushing, the locking bolt engaging an elongated projection (18) to lock the assembly (16), wherein the adjustment bushing is provided with a visual indicator (17) for indicating its relative position in Z-direction with respect to the fitting. The invention also relates to an aircraft comprising such a locking assembly, as well as a method for locking an aircraft interior structure to an aircraft main support structure.

Description

LOCKING ASSEMBLY FOR LOCKING AN AIRCRAFT INTERIOR STRUCTURE TO AN AIRCRAFT MAIN SUPPORT STRUCTURE
Field of the invention 5
[0001] The invention relates to an locking assembly for locking an aircraft interior structure, such as a galley, to an aircraft main support structure, such as a floor hard point.
10 Background of the invention
[0002] Such a locking assembly is known. The known locking assembly uses shim plates to position an aircraft interior structure, for example a galley or a similar monument, with respect to an aircraft’s floor hard point. After positioning, the galley is 15 locked to the hard point by using a locking bolt.
[0003] However, a disadvantage of the known way of locking the galley to the aircraft hard point, is that during positioning, which is usually done manually by an aircraft mechanic, shim plates may get lost. The aircraft mechanic may e.g. accidentally drop a 20 shim plate during installation, as a consequence of which the lost shim plate may enter a part of the aircraft cabin or another part of the aircraft where the shim plate may cause damage due to it being thrown around by subsequent aircraft movements during operation of the aircraft. Also, as it is not known beforehand how many shim plates or what size of shim plates are necessary, a plurality of shim plates needs to be available, 25 of which only a portion may be used. Furthermore, the shim plates that have been inserted successfully between the galley and the hard point may loosen during the life span of the aircraft. Another disadvantage is that the floor hard point may get damaged by the shim plates during installation.
30 [0004] Therefore, it is an object of the invention to provide an improved locking assembly that allows three-dimensional positioning and fixation of an aircraft interior structure with respect to the aircraft main support structure, without the need of shim plates.
2
Summary of the invention
[0005] This object is achieved by providing a locking assembly for locking an aircraft interior structure, such as a galley, to an aircraft main support structure, such as a floor 5 hard point, comprising: a cylindrical adjustment bushing having a hollow cylindrical space extending through the adjustment bushing in longitudinal direction, the adjustment bushing having an outer thread that engages an inner thread of a through-hole arranged in a 10 fitting attachable to or part of the aircraft interior structure, wherein the adjustment bushing can be rotated around its centre line to adjust the height of the fitting in a Z-direction, a cylindrical outer eccentric bushing inserted in the hollow cylindrical space of the adjustment bushing, the outer eccentric bushing having an eccentric longitudinal 15 hollow cylindrical space whose centre line is placed at a distance from the centre line of the cylindrical outer eccentric bushing, a cylindrical inner eccentric bushing inserted in the hollow cylindrical space of the outer eccentric bushing, the outer eccentric bushing having an eccentric longitudinal hollow cylindrical space whose centre line is placed at a distance from the 20 centre line of the cylindrical inner eccentric bushing, the inner and outer eccentric bushings allowing adjustment of the fitting in a plane perpendicular to the Z-direction, a locking bolt inserted in the hollow cylindrical space of the inner eccentric bushing, the locking bolt engaging an elongated projection of the aircraft main support structure to lock the assembly.
25
[0006] The fore mentioned adjustment bushing allows adjustment of the fitting attachable to the aircraft interior structure in Z-direction, i.e. the direction in line with the elongated projection. Subsequently, the inner and outer eccentric bushings allow the fitting to be adjusted with respect to the projection in a plane perpendicular to the Z- 30 direction, thus allowing the fitting and an aircraft interior structure attached thereto to be adjusted in a three-dimensional way, without needing any shim plates. After the aircraft interior structure is positioned, it can be secured by the locking bolt.
3
[0007] A preferred embodiment relates to a locking assembly, wherein the outer eccentric bushing is provided with an upper flange that is supported by the upper end of the adjustment bushing. The upper flange prevents the outer eccentric bushing from falling into the hollow cylindrical space of the adjustment bushing.
5
[0008] Another embodiment concerns a locking assembly, wherein the outer eccentric bushing is provided with a visual indicator on or in its flange for indicating its relative rotational position with respect to the adjustment bushing. Thus, the person installing the assembly is able to quickly obtain visual information on the positioning of the outer 10 eccentric bushing.
[0009] A further embodiment relates to a locking assembly, wherein the inner eccentric bushing is provided with an upper flange that is supported by the upper flange of the outer eccentric bushing. Analogously, the upper flange of the inner eccentric bushing 15 prevents it from disappearing into the outer eccentric bushing.
[0010] An embodiment relates to a locking assembly, wherein the inner eccentric bushing is provided with a visual indicator on or in its flange for indicating its relative rotational position with respect to the adjustment bushing. Again, the person installing 20 the assembly is enabled to obtain visual information on the positioning of the inner eccentric bushing with minimal effort.
[0011] In a further embodiment, the head of the locking bolt is supported by the upper flange of the inner eccentric bushing. The upper flange can be conveniently used to 25 support the locking bolt and, when the locking bolt is tightened, to transfer the compressive forces of the locking bolt to the other locking assembly parts.
[0012] The visual indicator can advantageously comprise a recess arranged in the upper flange. This recess can additionally be used for rotating the respective eccentric 30 bushing by means of a screw driver that can be inserted in the recess.
[0013] The adjustment bushing itself can also be provided with a visual indicator, for indicating its relative position in Z-direction with respect to the fitting, such that the 4 person installing the assembly is informed on the position of the adjustment bushing in Z-direction.
[0014] In a preferred embodiment, the visual indicator comprises a row of holes, preferably three holes, arranged in longitudinal direction in the outer thread of the 5 adjustment bushing, wherein the visibility of the holes indicates the position of the adjustment bushing with respect to the fitting in Z-direction.
[0015] In an embodiment, the lower end of the adjustment bushing is supported by a support member of the elongated projection. Such a support member is often used on 10 aircraft floor hard points, providing a convenient support location for the adjustment bushing.
[0016] Optionally, a nylon washer can be arranged on the elongated projection, below the lower end of the adjustment bushing to support the adjustment bushing. The nylon 15 washer prevents the occurrence of concentrated loads on the support member or elongated projection, or the lower end of the adjustment bushing.
[0017] Additionally, a steel ring can be arranged on the elongated projection, below the lower end of the adjustment bushing to support the adjustment bushing or the nylon 20 washer. The steel ring provides a larger surface for supporting the lower end of the adjustment bushing.
[0018] The invention also relates to an aircraft comprising an aircraft interior structure, such as a galley, that is attached to an aircraft main support structure, such as a floor 25 hard point, by using a locking assembly described above.
[0019] Furthermore, the invention relates to a method for locking an aircraft interior structure, such as a galley, to an aircraft main support structure comprising an elongated projection, such as a floor hard point, comprising the steps of: arranging a cylindrical adjustment bushing having a hollow cylindrical space and an outer thread over the elongated projection of the aircraft main support 30 5 structure until a lower end of the adjustment bushing is supported by a support member or support surface arranged on or near the elongated projection, causing the outer thread of the adjustment bushing to engage an inner thread of a through-hole of a fitting, that is attachable to the aircraft interior structure, and 5 rotating the adjustment bushing around its longitudinal axis to achieve a desired height of the fitting in a Z-direction, - inserting an outer eccentric bushing into the hollow cylindrical space of the adjustment bushing, - inserting an inner eccentric bushing into the hollow cylindrical space in the 10 outer eccentric bushing, - inserting a locking bolt into the hollow cylindrical space in the inner eccentric bushing and causing the locking bolt to loosely engage the elongated projection, adjusting the position of the fitting in a direction comprised by the plane perpendicular to the Z-direction using the inner and outer eccentric bushings, 15 - causing the locking bolt to firmly engage the elongated projection in order to lock the assembly.
Brief description of the drawings 20 [0020] An embodiment of a locking assembly according to the invention will by way of non-limiting example be described in detail with reference to the accompanying drawings. In the drawings:
[0021] Figure 1 shows an exploded view of an example of the locking assembly 25 according to the invention, and
[0022] Figure 2 shows the embodiment shown in figure 1 in an assembled condition.
Detailed description of the invention 30
[0023] Figure 1 shows an exploded view of an exemplary embodiment of a locking assembly 16 according to the invention. The embodiment will be discussed in relation to the normal order of assembly. The aircraft interior structure, in this example having 6 the form of a galley (the galley itself not being shown) is to be positioned on an aircraft main support structure in the form of an aircraft hard point on the aircraft floor, the hard point having an elongated projection 18 projecting downwards, into the floor, and having an inner screw thread for receiving a bolt 8 (see figure 2). The projection 18 is 5 usually provided with a support member on top in the form of a bushing 9 to support the locking assembly 16 and the galley, and is provided with an O-ring seal to prevent damage to the bushing 9 during installation of the galley. The bushing 9 is substantially flush with the aircraft floor. The bushing 9 is preferably provided with a low-friction layer, for example a washer 5.
10
[0024] An adjustment bushing 4 for changing the height of the galley in the Z-direction as shown is then positioned over the bushing 9 until a lower end of the adjustment bushing is supported by the bushing 9. The adjustment bushing 4 has a generally cylindrical shape, with the longitudinal axis of the adjustment bushing 4 being aligned 15 with the longitudinal axis of the projection 18. The adjustment bushing 4 is hollow, i.e. it has a hollow inner cylindrical space 15 that extends through the adjustment bushing 4 in longitudinal direction. The bolt 8 (see figure 2) is received in this cylindrical space 15.
20 [0025] The adjustment bushing 4 is provided with an outer screw thread so that it can be screwed into a through-hole 3 in a fitting 7 shown above the adjustment bushing 4, the through-hole 3 being provided with an inner screw thread. The fitting 7 can be attached to the galley or a similar “monument”. The fitting 7 is then supported by the bushing 9 and the adjustment bushing 4. By rotating the adjustment bushing 4 the 25 height of the fitting 7 with respect to the hard point projection 18 and the aircraft floor can be adjusted in Z-direction. The adjustment range is preferably 3 mm in each direction. The lower part of the adjustment bushing 4 comprises a hexagonal portion to facilitate rotation of the adjustment bushing 4 through the use of common-place tools, such as a wrench. After adjustment in Z-direction, the fitting 7 has to be adjusted in the 30 plane perpendicular to the Z-direction, i.e. the plane extending essentially parallel to the aircraft floor, since the adjustment bushing 4 can still move over the projecting hard point 18 in this plane. The adjustment range in this plane is preferably +/- 1.5 mm in perpendicular directions comprised by this plane.
7
[0026] Thereto, a cylindrical outer eccentric bushing 2 is to be inserted from above into the hollow cylindrical space 15. The outer eccentric bushing 2 is also provided with a hollow cylindrical space S0 extending along the length of the cylindrical inner eccentric bushing 2. This space S0 is also intended to enclose the bolt 8 (see figure 2). However, 5 the centre line of this hollow cylindrical space S0 is not aligned with the centre line of the cylindrical outer eccentric bushing 2 itself, but is placed at a certain distance (dl, not shown) there from. Therefore, the bushing 2 is called an “eccentric” bushing 2. Within the hollow cylindrical space S0 of the outer eccentric bushing 2 a similar, (cylindrical) inner eccentric bushing 1 is to be inserted. This inner eccentric bushing 1 10 is also provided with a hollow cylindrical space Si whose centre line is offset with respect to the centre line of the cylindrical inner eccentric bushing 1 itself over a distance (d2, not shown). The outer eccentric bushing 2 is provided with an upper flange 10 that supports the inner eccentric bushing 1 and prevents the outer eccentric bushing 2 from falling into the hollow cylindrical space 15. The inner eccentric bushing 15 1 is analogously provided with an upper flange 11 to prevent the inner eccentric bushing 1 from falling into the outer eccentric bushing 2 (and, consequently, from disappearing into the hollow cylindrical space 15), and to support the locking bolt 8 (see figure 2). Note that during adjustment the bolt 8 extends through the inner eccentric bushing 1, outer eccentric bushing 2, adjustment bushing 4, washer 5 and O-20 ring 6 and loosely engages the inner screw thread of the projection 18 in order to allow adjustment.
[0027] Both flanges 10, 11 can be provided with visual position indicators 13, 14 so that the person installing the galley can see, from the outside, how the eccentric 25 bushings 1, 2 are positioned, i.e. rotated, with respect to each other and how they are positioned with respect to the adjustment bushing 4. Such a visual position indicator 13, 14 can for example be formed by a small recess in the respective flange 10, 11. Similarly, the adjustment bushing 4 itself can also be provided with such a visual position indicator 17, for example embodied by a row of holes, such as three holes, the 30 row of holes extending in longitudinal direction of the adjustment bushing 4, wherein the amount of holes visible to the person installing the galley indicates the position of the adjustment bushing 4 in Z-direction.
8
[0028] Figure 2 shows the embodiment shown in figure 1 in an assembled and locked condition. Figure 2 essentially shows the exploded-view assembly 16 as shown in figure 1 with the locking bolt 8 inserted into the hollow space Si of the inner eccentric bushing assembly 16 and firmly engaging the inner thread of the hard point projection 5 18 of the aircraft floor, thereby locking the position of the assembly’s elements with respect to each other.
[0029] Thus, the invention has been described by reference to the embodiment discussed above. It will be recognized that this embodiment is susceptible to various 10 modifications and alternative forms well known to those of skill in the art without departing from the spirit and scope of the invention. Accordingly, although a specific embodiment has been described, this is an example only and is not limiting upon the scope of the invention.
15 9
Reference numerals 1. Inner eccentric bushing 2. Outer eccentric bushing 5 3. Through-hole in fitting 4. Adjustment bushing with outer thread 5. Washer 6. Ring 7. Fitting with threaded through-hole 10 8. Locking bolt 9. O-ring and bushing 10. Flange of outer eccentric bushing 11. Flange of inner eccentric bushing 12. Outer thread of adjustment bushing 15 13. Position indicator on outer adjustment bushing 14. Position indicator on inner adjustment bushing 15. Hollow cylindrical space in adjustment bushing 16. Locking assembly 17. Position indicator on adjustment bushing 20 18. Aircraft hard point proj ection provided with inner screw thread

Claims (14)

1. Vergrendel samenstel (16) voor het vergrendelen van een vliegtuiginterieurconstructie, zoals een boordkeuken, aan een 5 vliegtuighoofdconstructie, zoals een vloerbevestigingspunt, omvattende: een cilindrische instelbus (4) met een holle cilindrische ruimte (15) die zich uitstrekt door de instelbus (4) in een lengterichting, waarbij de instelbus (4) een buitenschroefdraad (12) heeft die aangrijpt op een binnenschroefdraad van een 10 doorgaand gat (3) dat aangebracht is in een montagestuk (7) dat bevestigbaar is aan een deel van de vliegtuiginterieurconstructie, waarbij de instelbus (4) geroteerd kan worden rondom zijn hartlijn om de hoogte van het montagestuk (7) in een Z-richting in te stellen, een cilindrische, excentrische buitenbus (2) die ingebracht is in de holle 15 cilindrische ruimte (15) van de instelbus (4), waarbij de excentrische buitenbus (2) een excentrische holle cilindrische ruimte (So) in lengterichting heeft waarvan de hartlijn op een afstand (dl) vanaf de hartlijn van de cilindrische, excentrische buitenbus (2) is geplaatst, een cilindrische, excentrische binnenbus (1) die is ingebracht in de holle 20 cilindrische ruimte (So) van de excentrische buitenbus (2), waarbij de excentrische buitenbus (2) een excentrische, holle cilindrische ruimte (Si) in 1 engterichting heeft waarvan de hartlijn op een afstand (d2) van de hartlijn van de cilindrische, excentrische binnenbus (1) is geplaatst, waarbij de binnen- en buitenbussen (1, 2) het instellen van het montagestuk (7) in een vlak loodrecht op 25 de Z-richting toestaan, een vergrendelbout (8) die ingebracht is in de holle cilindrische ruimte (Si) van de excentrische binnenbus (1), waarbij de vergrendelbout (8) op een langwerpig uitsteeksel (18) van de vliegtuighoofdconstructie (9, 18) aangrijpt om het samenstel (16) te vergrendelen. 30A locking assembly (16) for locking an aircraft interior structure, such as an on-board kitchen, to an aircraft main structure, such as a floor attachment point, comprising: a cylindrical adjusting bush (4) with a hollow cylindrical space (15) extending through the adjusting bush ( 4) in a longitudinal direction, wherein the adjusting bush (4) has an external thread (12) which engages an internal thread of a through hole (3) arranged in a mounting piece (7) that can be attached to a part of the aircraft interior construction, the adjusting bush (4) being rotatable about its axis to adjust the height of the mounting piece (7) in a Z direction, a cylindrical eccentric outer bush (2) inserted into the hollow cylindrical space (15) of the adjustment bush (4), wherein the eccentric outer bush (2) has an eccentric hollow cylindrical space (S0) in the longitudinal direction, the axis of which is at a distance (d1) from the axis of the cylindrical eccentric outer sleeve (2), a cylindrical eccentric inner sleeve (1) inserted into the hollow cylindrical space (S0) of the eccentric outer sleeve (2), the eccentric outer sleeve (2) being an eccentric, has a hollow cylindrical space (Si) in 1 narrow direction whose axis is spaced (d2) from the axis of the cylindrical eccentric inner sleeve (1), the inner and outer sleeves (1, 2) adjusting the mounting piece (7) in a plane perpendicular to the Z direction, allow a locking bolt (8) inserted into the hollow cylindrical space (Si) of the eccentric inner sleeve (1), the locking bolt (8) on an elongated protrusion ( 18) of the aircraft main structure (9, 18) engages to lock the assembly (16). 30 2. Vergrendel samenstel (16) volgens conclusie 1, waarbij de excentrische buitenbus (2) is voorzien van een bovenflens (10) die ondersteund is door het bovenuiteinde van de instelbus (4).Locking assembly (16) according to claim 1, wherein the eccentric outer sleeve (2) is provided with an upper flange (10) supported by the upper end of the adjusting sleeve (4). 3. Vergrendel samenstel (16) volgens conclusie 2, waarbij de excentrische buitenbus (2) is voorzien van een visuele indicator (13) op of in zijn flens (10) voor het aangeven van zijn relatieve positie ten opzichte van de instelbus (4).Locking assembly (16) according to claim 2, wherein the eccentric outer sleeve (2) is provided with a visual indicator (13) on or in its flange (10) for indicating its relative position with respect to the adjusting sleeve (4) . 4. Vergrendel samenstel (16) volgens een van de conclusies 2-3, waarbij de excentrische binnenbus (1) is voorzien van een bovenflens (11) die ondersteund is door de bovenflens (10) van de excentrische buitenbus (2).A locking assembly (16) according to any of claims 2-3, wherein the eccentric inner sleeve (1) is provided with an upper flange (11) supported by the upper flange (10) of the eccentric outer sleeve (2). 5. Vergrendel samenstel (16) volgens conclusie 4, waarbij de excentrische binnenbus 10 (1) is voorzien van een visuele indicator (14) op of in zijn flens (11) voor het aangeven van zijn relatieve rotationele positie ten opzichte van de instelbus (4).A locking assembly (16) according to claim 4, wherein the eccentric inner sleeve 10 (1) is provided with a visual indicator (14) on or in its flange (11) for indicating its relative rotational position with respect to the adjusting sleeve ( 4). 6. Vergrendel samenstel (16) volgens een van de conclusies 4-5, waarbij de kop van de vergrendelbout (8) ondersteund is door de bovenflens (11) van de excentrische 15 binnenbus (1).6. Locking assembly (16) according to any of claims 4-5, wherein the head of the locking bolt (8) is supported by the upper flange (11) of the eccentric inner sleeve (1). 7. Vergrendel samenstel (16) volgens conclusie 3 of 5, waarbij de visuele indicator (13; 14) een uitsparing omvat die aangebracht is in de bovenflens (10; 11).A locking assembly (16) according to claim 3 or 5, wherein the visual indicator (13; 14) comprises a recess arranged in the upper flange (10; 11). 8. Vergrendel samenstel (16) volgens een van de voorgaande conclusies, waarbij de instelbus (4) is voorzien van een visuele indicator (17) voor het aangeven van zijn relatieve positie in Z-richting ten opzichte van het montagestuk (7).Locking assembly (16) according to one of the preceding claims, wherein the adjusting bush (4) is provided with a visual indicator (17) for indicating its relative position in Z direction relative to the mounting piece (7). 9. Vergrendel samenstel (16) volgens conclusie 8, waarbij de visuele indicator (17) 25 een rij gaten omvat, bij voorkeur drie gaten, die aangebracht zijn in lengterichting in de buitenschroefdraad (12) van de instelbus (4), waarbij de zichtbaarheid van de gaten de positie van de instelbus (4) ten opzichte van het montagestuk (7) in de Z-richting aangeeft.9. Locking assembly (16) as claimed in claim 8, wherein the visual indicator (17) comprises a row of holes, preferably three holes, which are arranged in the longitudinal direction in the outer thread (12) of the adjusting bush (4), the visibility of the holes indicates the position of the adjusting bush (4) relative to the mounting piece (7) in the Z direction. 10. Vergrendel samenstel (16) volgens een van de voorgaande conclusies, waarbij een benedenuiteinde van de instelbus (4) is ondersteund door een steunorgaan (9) van het langwerpige uitsteeksel (18).A locking assembly (16) according to any one of the preceding claims, wherein a lower end of the adjusting bush (4) is supported by a support member (9) of the elongate protrusion (18). 11. Vergrendel samenstel (16) volgens een van de voorgaande conclusies, waarbij een nylon ring (5) is aangebracht op het langwerpige uitsteeksel (18), onder het benedenuiteinde van de instelbus (4) ter ondersteuning van de instelbus (4).Locking assembly (16) according to one of the preceding claims, wherein a nylon ring (5) is arranged on the elongated protrusion (18), below the lower end of the adjusting bush (4) to support the adjusting bush (4). 12. Vergrendel samenstel (16) volgens een van de voorgaande conclusies, waarbij een stalen ring (6) is aangebracht op het langwerpige uitsteeksel (18), onder het benedenuiteinde van de instelbus (4) ter ondersteuning van de instelbus (4) of de nylon ring (5).A locking assembly (16) according to any one of the preceding claims, wherein a steel ring (6) is provided on the elongated protrusion (18), below the lower end of the adjusting bush (4) to support the adjusting bush (4) or the nylon ring (5). 13. Vliegtuig omvattende een vliegtuiginterieurconstructie, zoals een boordkeuken, die is bevestigd aan een vliegtuighoofdconstmctie, zoals een vloerbevestigingspunt, onder gebruikmaking van een vergrendel samenstel (16) volgens een van de voorgaande conclusies.An aircraft comprising an aircraft interior construction, such as an on-board kitchen, which is attached to an aircraft main construction, such as a floor attachment point, using a locking assembly (16) according to any of the preceding claims. 14. Werkwijze voor het vergrendelen van een vliegtuiginterieurconstructie, zoals een boordkeuken, aan een vliegtuighoofdconstmctie (9, 18) omvattende een langwerpig uitsteeksel (18), zoals een vloerbevestigingspunt, omvattende de stappen van: het aanbrengen van een cilindrische instelbus (4) met een holle cilindrische 20 ruimte (15) en een buitenschroefdraad (12) over een langwerpig uitsteeksel (18) totdat een benedenuiteinde van de instelbus (4) wordt ondersteund door een steunorgaan (9) of een steunoppervlak van het langwerpige uitsteeksel (18), bewerkstelligen dat de buitenschroefdraad (12) van de instelbus (4) aangrijpt op een binnenschroefdraad van een doorgaand gat (3) van een montagestuk (7), 25 welke bevestigbaar is aan een vliegtuiginterieurconstructie, en het roteren van de instelbus (4) rond zijn langsas om een gewenste hoogte van het montagestuk (7) in een Z-richting te bereiken, het inbrengen van een excentrische buitenbus (2) in de holle cilindrische ruimte (15) van de instelbus (4), 30. het inbrengen van een excentrische binnenbus (1) in een holle cilindrische ruimte (So) in de excentrische buitenbus (2), het inbrengen van een vergrendelbout (8) in de holle cilindrische ruimte (Si) in de excentrische binnenbus (1) en bewerkstelligen dat de vergrendelbout (8) losjes aangrijpt op het langwerpige uitsteeksel (18), het instellen van de positie van het montagestuk (7) in een richting omvat door 5 het vlak loodrecht op de Z-richting door gebruik te maken van de binnen- en buitenbussen (1,2), bewerkstelligen dat de vergrendelbout (8) stevig aangrijpt op het langwerpige uitsteeksel (18) teneinde het samenstel (16) te vergrendelen.A method for locking an aircraft interior construction, such as an on-board kitchen, to an aircraft main construction (9, 18) comprising an elongated protrusion (18), such as a floor attachment point, comprising the steps of: arranging a cylindrical adjustment bush (4) with a hollow cylindrical space (15) and an external thread (12) over an elongated protrusion (18) until a lower end of the adjustment bush (4) is supported by a support member (9) or a support surface of the elongated protrusion (18), causing that the external thread (12) of the adjusting bush (4) engages an internal thread of a through hole (3) of a mounting piece (7), which is attachable to an aircraft interior construction, and rotating the adjusting bush (4) about its longitudinal axis about achieve a desired height of the mounting piece (7) in a Z direction, inserting an eccentric outer sleeve (2) into the hollow cylindrical space (15) of the adjusting bush (4), 30. inserting an eccentric inner bush (1) into a hollow cylindrical space (So) in the eccentric outer bush (2), inserting a locking bolt (8) into the hollow cylindrical space (Si) in the eccentric inner sleeve (1) and causing the locking bolt (8) to loosely engage the elongated protrusion (18), including adjusting the position of the mounting piece (7) in a direction through the plane perpendicular to the Z direction by use making the inner and outer bushes (1,2) cause the locking bolt (8) to engage securely on the elongated protrusion (18) to lock the assembly (16).
NL2009395A 2012-08-30 2012-08-30 Locking assembly for locking an aircraft interior structure to an aircraft main support structure. NL2009395C2 (en)

Priority Applications (2)

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NL2009395A NL2009395C2 (en) 2012-08-30 2012-08-30 Locking assembly for locking an aircraft interior structure to an aircraft main support structure.
PCT/NL2013/050622 WO2014035241A1 (en) 2012-08-30 2013-08-29 Locking assembly for locking an aircraft interior structure to an aircraft main support structure

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
NL2009395 2012-08-30
NL2009395A NL2009395C2 (en) 2012-08-30 2012-08-30 Locking assembly for locking an aircraft interior structure to an aircraft main support structure.

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Citations (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102004012262A1 (en) * 2004-03-12 2005-09-29 Airbus Deutschland Gmbh Mounting plate e.g. for galley fitting in airplane, has arrangement having horizontal surface assigning thread with horizontal surface has recess where mounting plate covers thread for screwing into thread of arrangement

Patent Citations (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102004012262A1 (en) * 2004-03-12 2005-09-29 Airbus Deutschland Gmbh Mounting plate e.g. for galley fitting in airplane, has arrangement having horizontal surface assigning thread with horizontal surface has recess where mounting plate covers thread for screwing into thread of arrangement

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