WO2003024699A1

WO2003024699A1 - Method for repairing an aircraft door pressure seal and device therefor

Info

Publication number: WO2003024699A1
Application number: PCT/FR2002/003152
Authority: WO
Inventors: Hervé Rouland
Original assignee: Concept Maintenance Profil Engineering
Priority date: 2001-09-17
Filing date: 2002-09-16
Publication date: 2003-03-27
Also published as: FR2829722A1; FR2829722B1

Abstract

The invention concerns a device (1) comprising: a heating clamp (3) whereof the jaws (10, 11) include recesses which jointly define, when said jaws (10, 11) are brought closer to each other, a housing corresponding to the seal portion (20) to be repaired, the dimensions of said housing being, however, slightly greater than those of said portion so that said portion and a repair part (21) enclosing it can be tightly engaged in said housing; means for heating said heating clamp (3); and means for controlling and monitoring said heating.

Description

METHOD FOR REPAIRING A SEAL FOR AN AIRCRAFT DOOR AND DEVICE FOR CARRYING OUT SAID METHOD

The present invention relates to a method for repairing a seal on an aircraft door and to a device for implementing this method.

To date, a fundamental problem exists on aircraft doors with a pressurized cabin, namely the problem of the poor sealing of a door (hold, passengers and cargo, etc.) due to the degradation of the elastomer seal. silicone. This problem has been identified, but no reliable solution has been found to date.

The consequences of such a leak are, when the aircraft has reached a cruising altitude, the diversion of the flight path to reach the nearest airport, a loss of time of the order of 2 to 3 hours in addition to the time established on the flight plan, consumption 2 to 3 times higher during the time of altitude climb, various stopover airport taxes, an additional cost of fuel and possibly passenger accommodation if the service do not have the skills or qualifications required to operate on the aircraft. When the problem was detected on takeoff, there is no possibility of climbing above 600 feet and the emergency takeoff procedure orders the immediate release of 150 tonnes of kerosene (i.e.

400,000 F), the return to the airport and the unloading of passengers. This results in layover costs, aircraft immobilization costs and additional fuel costs, all of which goes to airline maintenance services.

Despite all these problems, the manufacturers operate a method of repairing the aircraft door seal which is as follows. In the case of a small tearing of the sealing profile, a canvas can be glued with a silicone sealant which dries in 1 hour, but short-term reliability is not guaranteed.

If the damage is greater, there is immobilization of the aircraft for 48 hours, and the repair amounts to 560 Francs excluding VAT per hour multiplied by 2 people and from 2300 to 4600 Euros for a new joint, depending on the door size, for a BOEING 747-400.

The object of the present invention is to solve this fundamental problem.

The process it relates to includes the following steps: - transport the device to the repair site;

- extract the deteriorated portion of the seal to be repaired from the seat in which this seal is normally mounted;

- Apply on this damaged portion a repair part formed by a flexible support frame, such as a synthetic fabric, coated with an elastomer material, so that this repair part surrounds said damaged portion;

- Place this deteriorated portion and this repair part between the two jaws of a heating pliers adapted to repair the type of joint concerned, these jaws comprising recesses which jointly define a housing suitable for receiving closely said deteriorated portion thus coated with said repair part;

- close said heating clip on the damaged portion and the repair part; heating the jaws for a sufficient time for the vulcanization of said elastomer material;

- open and remove said heating clip, and

- replace the seal thus repaired in its mounting seat. The device according to the invention comprises: - a heating clamp, the jaws of which comprise recesses which jointly define, when said jaws are in the approaching position, a housing of shape corresponding to the portion of the joint to be repaired, the dimensions of this housing being however slightly greater than those of this portion so that this portion and a repair piece which wraps it can be tightly engaged in this housing;

means for heating said heating clip, and

- means of command and control of this heating. The invention thus makes it possible to carry out an over-molding of said repair part on said deteriorated portion of the seal on the repair site. The device according to the invention can advantageously be in the form of a suitcase containing:

- a connection wire to a source of electrical energy from the mains or available on the aircraft, - said command and control means, - A housing for receiving the heating pliers and the wire connecting this pliers to said command and control means.

The repair piece may include a strip of synthetic textile previously coated with silicone. This part can be presented in plastic bag with expiration date.

The clamp may include a bottom and a cover articulated by a hinge and closed by spring clips, these clips allowing the repair part to be crushed on the joint in the clamp.

The clamp being closed and pressurized by the flaps, the vulcanization of the mixture on the damaged joint profile is carried out.

This vulcanization is done by thermal operation with an integrated control of two heating cartridges equipped with integrated control probes and connected by a cable to the suitcase.

The case can be divided into two parts, the first being the dashboard of the device. The device can be equipped with a temperature regulator with a setpoint that can vary depending on the weather climate and the place where the repair will be carried out. It can also be equipped with three indicator lights summarizing and controlling the intervention method and the aforementioned hardening step, namely: - a first power-on indicator;

- a second temperature rise indicator, and

- a third warning light at the end of the vulcanization cycle, possibly accompanied by an audible warning.

The second part of the suitcase will consist of a storage space that can receive the clamp, the electrical connection cables between the clamp and the dashboard as well as the cables and plugs for power connection on aircraft or on mains (220 volts ).

For a good understanding, the invention is again described below with reference to the appended diagrammatic drawing representing, by way of nonlimiting example, a preferred embodiment of the device which it concerns.

Figure 1 is a very simplified view from above, and Figures 2 and 3 are very simplified views of the jaws of a heating clamp that it comprises, respectively in the open position and in the closed position. FIG. 1 schematically shows a device 1 for repairing a seal for an aircraft door, which comprises an assembly 2 in the form of a suitcase and a heating clamp 3.

The assembly 2 comprises a dashboard 5 for controlling the operation of the heating clip 3, and a wire (not shown) which can be connected to a source of electrical energy, from the mains or available on the airplane.

The suitcase further delimits a storage space 6 in which the clamp 3 and the wire 7 can be placed connecting the dashboard 5 to this clamp 3. The clamp 3 comprises two pairs of jaws 10, 11 which can be placed in the extension one of the other. The jaws 10, 11 of the same pair comprise recesses which jointly define a housing suitable for closely receiving the deteriorated part of the seal 20 to be repaired and a repair part 21 in the form of a fabric coated with silicone elastomer. In the example shown in the drawing, the seal 20 has a cross section substantially in the form of an inclined "T", as shown in FIGS. 2 and 3.

It appears from the above that the invention brings a decisive improvement to the prior art, by providing a method for definitive repair of a seal for an aircraft door and a device for implementing this method. making it possible to carry out an over-molding of said repair part 21 on said damaged portion of seal 20 at the repair site.

It goes without saying that the invention is not limited to the embodiment described as well as of materials used by way of example but that, on the contrary, it embraces all the variant embodiments falling within the protective field defined by the appended claims.

Claims

1 - Method for repairing a seal on an aircraft door, characterized in that it comprises the following steps: - transporting the device (1) to the repair site;

- extract the damaged portion of the seal (20) to be repaired out of the seat in which this seal (20) is normally mounted;

- Apply on this damaged portion a repair part (21) formed by a flexible support frame, such as a fabric, coated with an elastomer material, so that this repair part (21) surrounds said damaged portion;

- Place this damaged portion and this repair part (21) between the two jaws (10, 11) of a heating pliers (3) suitable for repairing the type of seal (20) concerned, these jaws (10, 11) comprising recesses which jointly define a housing suitable for receiving said deteriorated portion thus coated with said repair part (21);

- close said heating clip (3) on the damaged portion and the repair part (21);

- Realize the heating of the jaws (10, 11) for a sufficient time for the vulcanization of said elastomer material;

- open and remove said heating clip (3), and

- replace the seal (20) thus repaired in its mounting seat.

2 - Device (1) for implementing the method according to claim 1, characterized in that it comprises:

- a heating clip (3) whose jaws (10, 11) include recesses which jointly define, when said jaws (10, 11) are in the approximation position, a housing of shape corresponding to the portion of the joint (20) to repair, the dimensions of this housing being however slightly greater than those of this portion so that this portion and a repair piece (21) which envelops it can be engaged closely in this housing;

means for heating said heating clip (3), and

- means of command and control of this heating. 3 - Device (1) according to claim 2, characterized in that it is in the form of a suitcase containing: - a connection wire to an electrical energy source on the mains or available on the aircraft,

the said command and control means, and

- A housing (6) for receiving the heating clamp (3) and the wire (7) connecting this clamp (3) to said control means.

4 - Device (1) according to claim 2 or claim 3, characterized in that said repair part (21) comprises a strip of synthetic textile previously coated with silicone.

5 - Device (1) according to one of claims 2 to 4, characterized in that the clamp (3) comprises a bottom and a cover hinged by a hinge and closed by spring loaded lugs, these lugs allowing the crushing of the repair part (21) on the seal (20) in the clamp (3).

6 - Device (1) according to one of claims 2 to 5, characterized in that it is equipped with a temperature regulator with a setpoint which may vary according to the weather climate and the place where the repair is carried out.

7 - Device (1) according to one of claims 2 to 6, characterized in that it is equipped with three indicator lights summarizing and controlling the intervention method and the aforementioned hardening step, namely:

- a first power-on indicator; - a second temperature rise indicator, and