EP0332870B1 - Dispositif de cintrage de panneaux, en particulier des panneaux pour l'habillage de cellules d'avions, de fusées et produits similaires - Google Patents

Dispositif de cintrage de panneaux, en particulier des panneaux pour l'habillage de cellules d'avions, de fusées et produits similaires Download PDF

Info

Publication number
EP0332870B1
EP0332870B1 EP89102671A EP89102671A EP0332870B1 EP 0332870 B1 EP0332870 B1 EP 0332870B1 EP 89102671 A EP89102671 A EP 89102671A EP 89102671 A EP89102671 A EP 89102671A EP 0332870 B1 EP0332870 B1 EP 0332870B1
Authority
EP
European Patent Office
Prior art keywords
deforming
forming
pivot
members
panels
Prior art date
Legal status (The legal status 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 status listed.)
Expired - Lifetime
Application number
EP89102671A
Other languages
German (de)
English (en)
Other versions
EP0332870A2 (fr
EP0332870A3 (fr
Inventor
Helmut Ing.-Grad. Reccius
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Dornier GmbH
Original Assignee
Dornier GmbH
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 Dornier GmbH filed Critical Dornier GmbH
Publication of EP0332870A2 publication Critical patent/EP0332870A2/fr
Publication of EP0332870A3 publication Critical patent/EP0332870A3/fr
Application granted granted Critical
Publication of EP0332870B1 publication Critical patent/EP0332870B1/fr
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

Links

Images

Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B21—MECHANICAL METAL-WORKING WITHOUT ESSENTIALLY REMOVING MATERIAL; PUNCHING METAL
    • B21D—WORKING OR PROCESSING OF SHEET METAL OR METAL TUBES, RODS OR PROFILES WITHOUT ESSENTIALLY REMOVING MATERIAL; PUNCHING METAL
    • B21D11/00—Bending not restricted to forms of material mentioned in only one of groups B21D5/00, B21D7/00, B21D9/00; Bending not provided for in groups B21D5/00 - B21D9/00; Twisting
    • B21D11/20—Bending sheet metal, not otherwise provided for

Definitions

  • the invention relates to a device for the bending deformation of panels, in particular panels for the planking or the constructive formation of the cell of aircraft, rockets or the like, with stiffening ribs arranged on one side on a molting layer, crossing stiffening ribs with the formation of node points, the device for achieving a Component curvature has force-actuated, mutually adjustable forming members, provided for a form-fitting attack in each case at adjacent nodes and change in length of the stiffening ribs running in the component curvature direction.
  • Such panels are made from materials with elastic and plastic forming behavior, such as aluminum. In the case of parts for the specified use, it is of particular importance, for reasons of reducing the air resistance, to make the panel exterior exposed to the air flow smooth and with a constant curvature. In addition, such components for aircraft, including general aviation, must be able to be produced with work equipment, that allow inexpensive production.
  • Such panels can either be of integral construction, consisting of planking with integrated, crossing reinforcing ribs (rib belts, stringers) or of differential construction, that is to say with reinforcing ribs riveted onto the skin.
  • EP-A-0 078 891 B1 (& US-A-4 498 325), which is considered to be the closest state of the art, has already disclosed a method and a device for bending the panels, in particular for cladding the cell of aircraft, have been proposed, according to which the deformation is brought about by a plastic, linear change in length of the stiffening ribs extending in the direction of the curvature, and the introduction of the deformation forces on the stiffening ribs takes place at such a distance from the molting that the panel has a stress curve with inside the molting is subject to lying neutral fiber.
  • a device for forming sheet metal profile strips of relatively small thickness which carries pivoting members pivotable about bearing axes on a fixed support member.
  • the forming members are inevitably controlled in the forming process as a function of a pivoting movement as a function of a cam having an cam, the forming members being attacked on the workpiece by means of frictional engagement.
  • Forming devices designed in this way do not allow the direction of action of the forming forces to be adapted to the changing curvature during the forming process due to the unchangeable bearing distances of the forming members.
  • a frictional Attack of the forming members does not transmit the forming forces sufficiently.
  • the invention is based on devices designed according to EP-A-0 078 891 B1 and aims to improve the known device designs, in such a way that between adjacent nodes of the stiffening ribs, components subjected to bending deformation, the components running in the direction of curvature , the rib belt subjected to the shaping after completion of the shaping process has a constant distribution of strain and thus internal stress distribution over its entire extent.
  • a forming device designed according to the invention allows the Introduction of the forming forces on the workpiece, in relation to the direction of force application, on the sections of the rib belts to be subjected to a change in length, and thus to bring about a force introduction from which a residual stress distribution in the rib belts results, which extends over the entire extension of the rib belts between each has two adjacent nodes uniform course.
  • the introduction of force can thus take place perpendicular to the stringers running transversely to the direction of curvature, that is to say at right angles to the line between the pivot axes of the pivotable shaping members and the force application points of the members on the workpiece.
  • an adaptation according to the respective degree of shaping during a shaping process, can be freely adjusted about its pivot axis. This enables force to be applied to the workpiece, which is able to compensate both compensatory movements of the tool, or the device and also the workpiece itself, and an adaptation of the clamping jaws to the direction or position of the stringer, which changes during the forming process.
  • the panel is generally designated 2, its skinning 3, and the crossing stiffening ribs 4 and 5.
  • the panel 2 is a cladding part for the cell of aircraft, the stiffening ribs 4 to be subjected to a change in length subsequently being referred to as rib belts and the stiffening ribs 5 which intersect with them being referred to as stringers.
  • the panel outer surface lying in the air flow in the installed state of the panel 2 bears the reference number 6 and the node locations formed by the crossing stiffening ribs the reference number 7.
  • the nodes 7 can also be formed so that instead the stringer 5 are only stubs of the same are combined with the rib belts 4, in order thus to obtain an approach for the form-fitting attack of the forming device.
  • FIG 2 a forming device according to the prior art is shown.
  • the forming device 10 contains forming members 11, 11a, at the free end of jaw pairs 12, 12 'are attached to the workpiece 2 for attack.
  • the forming members 11, 11a are arranged on a support axis 15 ', which at the same time forms the piston rod of the working piston 15 of a hydraulically operating servomotor 13.
  • the servo motor 13 receives the piston 15 in a cylinder housing 14 so as to be axially displaceable, forming cylinder chambers, the deforming member 11 being fixedly connected to the cylinder housing 14.
  • the second forming member 11a is in turn firmly connected to the piston rod 15, so that when the servomotor 13, which interacts with a pressure medium control device (not shown here), the two forming members are adjusted parallel and linearly to one another.
  • the forming forces F in the point of action A are effective at mutually adjacent nodes 7 of the panel 2 in a coaxially directed manner.
  • the direction of attack of the forming forces F acting coaxially opposite one another on the workpiece 2 remains unchanged, regardless of the bending state of the workpiece 2.
  • the linear transfer of the forming forces F to the workpiece 2 results in an uneven distribution of the bending moment at the sections of the ribbed belts 5 which are to be subjected to a change in length and which lie between two adjacent node points. This results in a concentration of the internal stresses in the workpiece in conjunction with an uneven one Curvature course the skinning 3 and thus the outer surface 6 around which the panel 2 is in the installed state.
  • the shaping members designated 111, 111a are arranged such that they can pivot relative to one another.
  • the pairs of clamping jaws 112 which can be brought into engagement with the workpiece 2, 112 'arranged, which grasp the rib belts 4 to be subjected to a deformation between them and which engage in a form-fitting manner at adjacent nodes 7 of the panel.
  • the servo motor designated here 113 acts in the area of the opposite end of the shaping members. Its working piston 115 is supported in an articulated manner on the forming member 111 and the working cylinder 114 on the forming member 111a.
  • the bearing eye of the working piston is designated by 123 here.
  • an anchor part 130 is arranged between the pairs of jaws 112, 112 'and the servo motor 113, which serves as a support and as a separate pivot bearing for an independent relative pivoting movement of the forming members 111, 111a in the direction of the pivoting plane EE ( Figure 1) is used.
  • Both the cylinder 114 and the working piston 115 of the servo motor 113 engage in an articulated manner on the shaping members 111, 111a by means of a pivot bearing 120, 121.
  • the anchor part 130 pivotally supports the forming members 111, 111a by means of bearings 134, 134a.
  • the armature part 130 also contains adjusting means for changing the distance L of the axes of the bearings 134, 134a, as can be seen from the structural design according to the embodiment of the device according to FIGS. 5 and 6 described below.
  • FIGS. 5 and 6 show an exemplary embodiment according to the invention, parts corresponding to parts in FIGS. 1 to 4 having the same names and having the same reference numerals.
  • the shaping members 111, 111a are designed here in the manner of a closed frame, the opening 150 of which serves to receive parts of the servo motor 113 and parts of the armature 130.
  • the pairs of clamping jaws 112, 112 ′ are supported on the frame forming the forming members 111, 111a.
  • the adjusting device 140 contains a threaded ring 142 which can be screwed onto the thread of the anchor rod 131 of the anchor part 130 and which can be locked. This is supported on the shoulder 144 which supports the bearing bush 143 which carries the pins of the bearings 134, 134a and can be displaced on the anchor rod 131 in such a way that each after setting the threaded ring 142 a corresponding setting of the distance L of the axes of the bearings 134, 134a on the two forming members 111, 111a and thus a change in the direction of the force application of the forming force F 'is effected.
  • the forming force F ' corresponding to the design of the component 2 during the forming process, or in the final forming position of the links 111, 111a to one another, perpendicular to the extension of the stringers 5 or at right angles to the pivot radius R, about which the forming members 111, 111a can be pivoted are attacking the rib belts 4 in the force application point A.
  • the adjustment device 142, 143, 131 shown for changing the distance L an embodiment is also conceivable with the aid of which it is possible to change the position 134, 134a with the anchor part 130 in the direction of the longitudinal extension of the forming members 111, 111a.
  • Such a change in the distance between the points of application A of the forming force F 'and the axes of the pivot bearings 134, 134a, that is to say a change in the radius R allows the device to be used on components of different dimensions.
  • the device also has a stroke limiter 160 which contains a screw 161 which is firmly inserted into the shaping member 111a and an adjusting nut 162 which can be screwed onto the thread and locked.
  • a suspension device 170 is provided which is supported on the adjusting nut 162 of the stroke limiter 160.
  • the spring serves to hold the forming members 111, 111a in a predetermined opening position when the actuator 113 is depressurized. This results in an easier placement of the device on the component.
  • the device can be designed as a mobile tool or as a component of a fixed processing unit.
  • the pairs of clamping jaws 112, 112 'on the forming members 111, 111a are arranged freely pivotable about axes 180 transversely to the direction of the forming force F'.
  • the pairs of jaws 112, 112 'mounted in this way an automatic adaptation to the position or the degree of deformation of the stringer 5 is ensured during the entire forming process and thus enables a perfect transfer of the forming force F to the component 2.
  • an adjustment screw is also designated, which is used for the adjustable limitation of the opening path of the device.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Bending Of Plates, Rods, And Pipes (AREA)
  • Application Of Or Painting With Fluid Materials (AREA)
  • Moulding By Coating Moulds (AREA)
  • Shaping Metal By Deep-Drawing, Or The Like (AREA)

Claims (6)

  1. Dispositif de cintrage de panneaux, en particulier de panneaux pour l'habillage ou la réalisation structurale des cellules d'aéronefs ou de fusées, l'habillage présentant des nervures de renfort disposées unilatéralement, se croisant les unes les autres, avec formation de points nodaux, comprenant,
    - des éléments de formage mûs mécaniquement, déplaçables les uns par rapport aux autres (111, 111a) pour s'appliquer en correspondance de formes sur des points nodaux voisins les uns des autres et pour modifier la longueur des nervures de renfort s'étendant dans le sens de la courbure de la pièce d'ouvrage,
    caractérisé en ce que les éléments de formage (111, 111a) sont supportés, chacun, sur une partie d'ancrage (130) commune au moyen de coussinets pivotants (134, 134a) de manière à pivoter relativement et indépendamment les uns des autres en direction de l'allure de courbure de la pièce d'ouvrage (2), l'écart (L) entre les coussinets pivotants (134, 134a) étant réglable.
  2. Dispositif selon la revendication 1, caractérisé en ce que la modification de l'écart (L) des coussinets pivotants (134, 134a) sur la partie d'ancrage (130) s'effectue au moyen d'un dispositif de réglage par asservissement durant le déroulement du processus de formage en vue du maintien d'une application constamment perpendiculaire des forces de formage (F') sur la pièce d'ouvrage (2).
  3. Dispositif selon la revendication 1 ou 2, caractérisé en ce que des moyens de modification du rayon de pivotement (R) des éléments de formage (111, 111a) entre les coussinets pivotants (134, 134a) et les points d'application (A) des forces de formage (F, F') sur la pièce d'ouvrage (2) sont prévus.
  4. Dispositif selon l'une quelconque des revendications précédentes, caractérisé en ce que sur les éléments de formage (111, 111a) sont disposées, s'appliquant en des points nodaux (7) adjacents, des paires de mâchoires de serrage (112, 112') enserrant entre elles, en correspondance de formes, les membrures des nervures (4) devant être soumises à une variation de longueur par formage.
  5. Dispositif selon l'une quelconque des revendications précédentes, caractérisé en ce que les paires de mâchoires de serrage (112, 112') sont disposées réglables librement automatiquement sur les éléments de cintrage (111, 111a), au moyen de pivots (180) disposés perpendiculairements au plan de pivotement (E-E), en fonction de l'état de déformation de la pièce d'ouvrage (2).
  6. Dispositif selon l'une quelconque des revendications précédentes, caractérisé en ce qu'à proximité des extrémités libres des éléments de formage (111, 111a) s'appliquent au moyen de paliers à rotule (120, 121) les éléments (114, 115, 115', 123) d'un servomoteur (113) générant les forces de formage (F').
EP89102671A 1988-03-16 1989-02-16 Dispositif de cintrage de panneaux, en particulier des panneaux pour l'habillage de cellules d'avions, de fusées et produits similaires Expired - Lifetime EP0332870B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE3808763 1988-03-16
DE3808763A DE3808763A1 (de) 1988-03-16 1988-03-16 Einrichtung zur biegeumformung von paneelen, insbesondere paneele fuer die beplankung der zelle von luftfahrzeugen, raketen oder dergleichen

Publications (3)

Publication Number Publication Date
EP0332870A2 EP0332870A2 (fr) 1989-09-20
EP0332870A3 EP0332870A3 (fr) 1991-01-02
EP0332870B1 true EP0332870B1 (fr) 1993-07-28

Family

ID=6349868

Family Applications (1)

Application Number Title Priority Date Filing Date
EP89102671A Expired - Lifetime EP0332870B1 (fr) 1988-03-16 1989-02-16 Dispositif de cintrage de panneaux, en particulier des panneaux pour l'habillage de cellules d'avions, de fusées et produits similaires

Country Status (4)

Country Link
US (1) US4955222A (fr)
EP (1) EP0332870B1 (fr)
JP (1) JPH0225222A (fr)
DE (1) DE3808763A1 (fr)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN102922183A (zh) * 2012-11-02 2013-02-13 无锡华联科技集团有限公司 桥梁u肋焊接机升降摇摆横梁机构

Families Citing this family (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE4413369C2 (de) * 1994-04-19 1996-08-29 Hornauer Klaus Peter Dr Ing Schalenförmiges Werkstück
US6338383B1 (en) 1999-12-22 2002-01-15 Visteon Global Technologies, Inc. Heat exchanger and method of making same
AU2001282858A1 (en) * 2000-06-19 2002-01-02 Ceilings Plus Panel curving machine
DE102006008237A1 (de) * 2006-02-22 2007-08-23 Volkswagen Ag Vorrichtung zum Umformen eines bandförmigen Werkstücks
CN113460264B (zh) * 2021-06-25 2022-06-17 沪东中华造船(集团)有限公司 一种船舶曲面板压模装置及压模方法

Family Cites Families (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US791032A (en) * 1904-06-03 1905-05-30 Milo M Smith Locomotive cellar-puller.
US2560929A (en) * 1947-09-11 1951-07-17 Crane Co Tool for assembling radiator sections or the like
US2958242A (en) * 1957-05-31 1960-11-01 Marchant Lee Lloyd Metal forming machine
DE1197841B (de) * 1963-02-14 1965-08-05 Ver Flugtechnische Werke Ges M Verfahren und Vorrichtung zur Verformung von Honigwabenmatten
US3296119A (en) * 1964-01-08 1967-01-03 Universal Oil Prod Co Catalytic reforming process and catalyst therefor
DE1527404A1 (de) * 1965-04-22 1969-08-21 Erich Ribback Verstellvorrichtung fuer die Hublage der Werkzeuge von schnellschlagenden Haemmermaschinen
DE2301537A1 (de) * 1973-01-12 1974-07-18 Bernd Ribback Haemmermaschine
US3927548A (en) * 1973-12-28 1975-12-23 Stanray Corp Apparatus for forming arched roof sheets for automotive carrier vehicle
SU755376A1 (ru) * 1978-02-21 1980-08-15 Vitalij S Shelkov Способ гибки панелей одинарной кривизны с продольно-поперечным оребрением 1
DE3139836A1 (de) * 1981-10-07 1983-04-21 Dornier Gmbh, 7990 Friedrichshafen "verfahren und einrichtung zur biegeumformung von paneelen, insbesondere fuer die beplankung der zelle von luftfahrzeugen"
US4498325A (en) * 1982-09-29 1985-02-12 Walter Eckold Gmbh & Co. Kg Method for shaping panels by a bending operation, in particular panels for aircraft fuselage skin, and apparatus for implementing such method
JPH0777656B2 (ja) * 1986-08-05 1995-08-23 博康 塩川 相打ちハンマ

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN102922183A (zh) * 2012-11-02 2013-02-13 无锡华联科技集团有限公司 桥梁u肋焊接机升降摇摆横梁机构
CN102922183B (zh) * 2012-11-02 2014-11-19 无锡华联科技集团有限公司 桥梁u肋焊接机升降摇摆横梁机构

Also Published As

Publication number Publication date
JPH0225222A (ja) 1990-01-26
US4955222A (en) 1990-09-11
DE3808763C2 (fr) 1991-08-14
EP0332870A2 (fr) 1989-09-20
DE3808763A1 (de) 1989-10-05
EP0332870A3 (fr) 1991-01-02

Similar Documents

Publication Publication Date Title
DE2738895C2 (fr)
DE3113791C2 (fr)
DE102008020347B4 (de) Vorrichtung zur Herstellung eines Bauteils und Verfahren
WO1999061313A1 (fr) Ailes adaptatives pneumatiques pour appareils volants a voilure fixe
DE102009057726A1 (de) Radialpresse
WO2005108019A2 (fr) Systeme de positionnement et d'usinage et procede approprie pour positionner et usiner au moins une piece
DE1602452A1 (de) Blechabgratvorrichtung
DE102017130884B4 (de) Luftfahrzeug und Verfahren zum Herstellen eines Luftfahrzeugs
DE60011923T2 (de) Scharnier für flugzeugsteuerflächen und verbindungselement zur verwendung mit einem solchen scharnier
EP0332870B1 (fr) Dispositif de cintrage de panneaux, en particulier des panneaux pour l'habillage de cellules d'avions, de fusées et produits similaires
DE3539276C1 (fr)
EP1666354A1 (fr) Composant structurel, procédé de fabrication d'un composant structurel et utilisation d'un composant structurel dans le revêtement d'un aéronef
DE112004000508T5 (de) Verfahren zum Auftragen von Schutzschicht bildendem Material
DE2755669B1 (de) Verfahren zur Herstellung eines waermegedaemmten Verbundprofiles und Vorrichtung zur Durchfuehrung des Verfahrens
AT409733B (de) Positioniervorrichtung und verfahren zum schweissen von türen und klappen
EP0074542A2 (fr) Mandrin en particulier pince de serrage
DE2814507A1 (de) Verfahren zur herstellung eines festsitzenden uebergangsrohres fuer verstellgestaenge und danach hergestelltes verstellgestaenge
DE2848309A1 (de) Laminiertes plattenteil, insbesondere flugzeugsteuersystemteil, und damit ausgeruestetes flugzeugsteuersystem
EP0078891B1 (fr) Procédé et dispositif pour la déformation par flexion de panneaux en particulier pour le bordé de cellules d'avion
DE2824945C2 (de) Stanzvorrichtung für die rohrförmigen Stützen von Metalleitern
DE706014C (de) Metallprofilstab fuer Luftfahrzeuge
DE2635631C3 (de) Vorrichtung zur schwenkbaren Auflage eines Rahmens, insbesondere fur Führungswalzen für dünne Materialbahnen, der gegenüber einer Bezugsebene verdrehbar ist
EP0489304A2 (fr) Ressort à lame composite
EP0756526B1 (fr) Piece en forme generale de coque
DE19627454C2 (de) Verfahren zum Fügen von Bauteilen durch Preßpassung

Legal Events

Date Code Title Description
PUAI Public reference made under article 153(3) epc to a published international application that has entered the european phase

Free format text: ORIGINAL CODE: 0009012

AK Designated contracting states

Kind code of ref document: A2

Designated state(s): FR GB IT NL

PUAL Search report despatched

Free format text: ORIGINAL CODE: 0009013

AK Designated contracting states

Kind code of ref document: A3

Designated state(s): FR GB IT NL

17P Request for examination filed

Effective date: 19910207

17Q First examination report despatched

Effective date: 19911112

GRAA (expected) grant

Free format text: ORIGINAL CODE: 0009210

AK Designated contracting states

Kind code of ref document: B1

Designated state(s): FR GB IT NL

GBT Gb: translation of ep patent filed (gb section 77(6)(a)/1977)

Effective date: 19930729

ET Fr: translation filed
ITF It: translation for a ep patent filed

Owner name: JACOBACCI CASETTA & PERANI S.P.A.

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: NL

Payment date: 19940228

Year of fee payment: 6

PLBE No opposition filed within time limit

Free format text: ORIGINAL CODE: 0009261

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: NO OPPOSITION FILED WITHIN TIME LIMIT

26N No opposition filed
PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: GB

Payment date: 19950130

Year of fee payment: 7

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: FR

Payment date: 19950203

Year of fee payment: 7

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: NL

Effective date: 19950901

NLV4 Nl: lapsed or anulled due to non-payment of the annual fee

Effective date: 19950901

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: GB

Effective date: 19960216

REG Reference to a national code

Ref country code: GB

Ref legal event code: 732E

REG Reference to a national code

Ref country code: FR

Ref legal event code: TP

GBPC Gb: european patent ceased through non-payment of renewal fee

Effective date: 19960216

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: FR

Effective date: 19961031

REG Reference to a national code

Ref country code: FR

Ref legal event code: ST

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: IT

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES;WARNING: LAPSES OF ITALIAN PATENTS WITH EFFECTIVE DATE BEFORE 2007 MAY HAVE OCCURRED AT ANY TIME BEFORE 2007. THE CORRECT EFFECTIVE DATE MAY BE DIFFERENT FROM THE ONE RECORDED.

Effective date: 20050216