Tool for guiding a flexible cord of a boroscope and aircraft comprising at least one piece of equipment for carrying out a boroscope inspection

Abstract

Tool for guiding a flexible cord of a boroscope and aircraft comprising at least one piece of equipment for carrying out a boroscopic inspection The invention relates to a tool for guiding a flexible cord (34.3) of a boroscope for carrying out a boroscopic inspection by introducing the flexible cord (34.3) of the boroscope (34) into an orifice (36). This guiding tool comprises a body (80), a tubular end piece (86), connected to a first end (80.1) of the body (80), having an internal section for housing the flexible cord (34.3) of the boroscope (34) as well as a head (82) connected to a second end (80.2) of the body (80), the latter and the tubular end piece (86) being configured to pass through the orifice (36), the head (82) being configured not to pass through the orifice (36). The invention also relates to an aircraft comprising at least one piece of equipment for carrying out a boroscopic inspection as well as a boroscopic inspection method. Figure 11

Description

Title of the invention: Tool for guiding a flexible cord of a horoscope and aircraft comprising at least one piece of equipment for carrying out a horoscopic inspection

[0001] The present application relates to a tool for guiding a flexible cord of a horoscope as well as to an aircraft comprising at least one piece of equipment for carrying out a horoscopic inspection.

[0002] According to an embodiment visible in [Fig.l], an aircraft 10 comprises a fuselage 12, wings 14 positioned on either side of the fuselage 12 as well as propulsion units 16 positioned under the wings and connected to the latter by masts 18 which each comprise a fairing 20, forming an aerodynamic envelope, under which different equipment is positioned.

[0003] During operation of the aircraft, some of the equipment located under the fairing 20 must be regularly inspected, for example before each takeoff. Furthermore, in the case of a hydraulic leak at the mast 18, it is necessary to visually inspect the areas located under the fairing 20 in order to determine the origin of the leak and repair it.

[0004] For this purpose, as illustrated in [Fig.2], the fairing 20 comprises removable panels 22, 22' connected to the structure of the mast 18 by connecting elements, such as screws for example.

[0005] The operations of dismantling and reassembling these various removable panels 22, 22' are relatively long and tedious because it is necessary to unscrew several connecting elements for each of them. However, some of these connecting elements may be damaged, which tends to complicate their dismantling and increase the duration of the dismantling operation.

[0006] In the case of a maintenance operation aimed at determining the origin of a hydraulic leak, it is generally necessary to dismantle and reassemble a large number of panels, which further increases the intervention time.

[0007] In all cases, these operations of dismantling and reassembling the panels 22, 22' of the fairing 20 impact the operating time of the aircraft.

[0008] The present invention aims to remedy all or part of the drawbacks of the prior art.

[0009] To this end, the invention relates to a tool for guiding a flexible cord of a horoscope, said guiding tool making it possible to carry out a horoscopic inspection by introducing the flexible cord of the horoscope into an orifice.

[0010] According to the invention, the guide tool comprises a body extending between first and second ends, a head connected to the second end of the body and a tubular tip connected to the first end of the body and having an interior section for housing the flexible cord of the horoscope, the body and the tubular tip being configured to pass through the orifice, the head being configured not to pass through the orifice.

[0011] This solution makes it possible to correctly orient the horoscope camera located at the free end of its flexible cord by acting on the head of the guiding tool.

[0012] According to another characteristic, the body is bent.

[0013] According to another characteristic, the head is spherical.

[0014] According to another characteristic, the body comprises at least one groove which extends from one end to the other of the body, said groove being configured to accommodate the flexible cord of the horoscope.

[0015] According to another characteristic, the head comprises a slot, in the extension of the groove, which has a width allowing the flexible cord of the horoscope to be housed.

[0016] According to another characteristic, the groove opens into the tubular end piece.

[0017] The invention also relates to an aircraft comprising a fairing which has outer and inner faces as well as at least one piece of equipment making it possible to carry out at least one horoscopic inspection. This piece of equipment comprises an orifice passing through the fairing and configured to allow the introduction of a guide tool, according to one of the preceding characteristics, supporting a flexible cord of a horoscope.

[0018] According to another characteristic, the orifice comprises a widened, truncated cone-shaped zone at the level of the outer surface of the fairing.

[0019] According to another characteristic, the equipment making it possible to carry out at least one horoscopic inspection comprises a removable shutter configured to occupy a mounted state in which the removable shutter closes the orifice and a dismounted state in which the removable shutter clears the orifice.

[0020] The invention also relates to a method for horoscopic inspection of an area located behind a fairing using a guide tool and a horoscope. According to the invention, the method comprises a step of introducing the flexible cord of the horoscope into the tubular end piece of the guide tool, a step of placing the flexible cord in the groove of the body of the guide tool up to its head, a step of introducing the guide tool into an orifice passing through the fairing as well as a step of orienting the free end of the flexible cord by modifying the orientation of the head of the guide tool.

[0021] Other characteristics and advantages will emerge from the description of the invention which follows, a description given by way of example only, with reference to the drawings. annexed among which:

[0022] [Fig-1] is a perspective view of an aircraft,

[0023] [Fig.2] is a perspective view of a fairing of an aircraft mast illustrating a embodiment of the prior art,

[0024] [Fig.3] is a perspective view of a portion of an aircraft fairing comprising equipment for performing a horoscopic inspection illustrating an embodiment of the invention,

[0025] [Fig.4] is a perspective view of a portion of an aircraft fairing comprising equipment for performing a horoscopic inspection which comprises a removable shutter in the mounted and locked state illustrating an embodiment of the invention,

[0026] [Fig.5] is a perspective view of the fairing portion of the aircraft visible on the [Fig.4], the removable shutter being in the dismantled state,

[0027] [Fig.6] is a perspective view of a removable shutter of an equipment for carry out a horoscopic inspection illustrating an embodiment of the invention,

[0028] [Fig.7] is a schematic sectional representation of part of a fairing provided with the removable shutter visible in [Fig.6], in the mounted and locked state on part (A) in the mounted and unlocked state on part (B),

[0029] [Fig.8] is a representation of the shutter visible in [Fig.6] at different stages of its assembly,

[0030] [Fig.9] is a perspective view of the shutter visible in [Fig.6] without a ring elastic,

[0031] [Fig.10] is a perspective view of a removable shutter illustrating another mode of carrying out the invention,

[0032] [Fig. 11] is a perspective view of a tool for guiding a flexible cord of a horoscope positioned at the level of an orifice of a fairing illustrating an embodiment of the invention,

[0033] [Fig. 12] is a perspective view of the guide tool visible in [Fig. 11] and of a horoscope.

[0034] An aircraft comprises at least one fairing 30 located for example at the level of its fuselage, one of its masts, one of its nacelles or any other part of the aircraft. This fairing 30 has outer and inner faces F30, F30'. In operation, when the aircraft is in flight, the outer face F30 is in contact with aerodynamic flows flowing around the aircraft.

[0035] According to one embodiment, the fairing 30 comprises several juxtaposed panels connected to a structure of the aircraft by fixing elements. The latter may be permanent (non-removable), such as rivets for example.

[0036] The fairing 30 may be metallic or made of composite material.

[0037] The aircraft comprises, at the level of the fairing 30, at least one item of equipment 32 allowing at least one horoscopic inspection to be carried out using a horoscope 34, as illustrated in [Fig.5]. According to one embodiment, a horoscope 34 comprises a body 34.1, a display system 34.2 such as a screen, a flexible cord 34.3 which has a free end 34.4 as well as at least one camera 34.5 positioned at the free end 34.4 of the flexible cord 34.3.

[0038] Horoscope 34 is not further described because it may be identical to those of the prior art.

[0039] Each piece of equipment 32 comprises an orifice 36 which passes through the fairing 30 and has a passage section allowing a flexible cord 34.3 of a horoscope 34 to pass through it.

[0040] The orifice 36 opens at the level of the outer and inner faces F30, F30' via respectively outer and inner ends 36.1, 36.2. According to one arrangement, the outer end 36.1 has a larger section than that of the inner end 36.2.

[0041] According to one embodiment, the orifice 36 comprises a first section 38.1 which extends from the outer face F30 as well as a second section 38.2 which extends from the inner face F30', to the first section 38.1.

[0042] According to one configuration, the first section 38.1 has a truncated cone shape which widens towards the outer face F30. The second section 38.2 is cylindrical. According to another configuration, the first and second sections 38.1, 38.2 are cylindrical and connected by a shoulder. According to these configurations, the orifice 36 has an axis of revolution A36, an enlarged zone 40 at the outer face F30 as well as a smaller passage section having a section smaller than that of the enlarged zone and greater than or equal to that of a flexible cord 34.3 of a horoscope 34. In Figures 7 to 11, the smallest passage section is located at the second end 36.2. However, it could be spaced from the second end 36.2 and the inner face F30'.

[0043] According to one arrangement, the outer and inner faces F30, F30' are substantially perpendicular to the axis of revolution A36.

[0044] According to one configuration, the equipment 32 for carrying out at least one horoscopic inspection comprises a removable shutter 42 configured to occupy a mounted state in which it closes the orifice 36, as illustrated in FIGS. 4 and 7, and a disassembled state in which it clears the orifice 36, as illustrated [Fig. 5]. Thus, outside of an inspection operation, the orifice 36 is closed by the removable shutter 42. During an inspection operation, the removable shutter 42 is removed and the flexible cord 34.3 of a horoscope is introduced into the orifice 36, as illustrated in [Fig. 5]

[0045] Thus, it is no longer necessary to dismantle panels to view the area located under the fairing. It is sufficient to remove the removable shutter 42 positioned in the orifice 36 in order to be able to inspect the area located under the fairing using a horoscope 34. This solution makes it possible to reduce the intervention time for visual inspections under the fairing 30.

[0046] The orifice 36 and the removable shutter 42 are configured so that the removable shutter 42 is flush with the outer face F30 of the fairing when it is in the mounted state. This arrangement makes it possible to reduce aerodynamic disturbances in flight.

[0047] According to one embodiment, the removable shutter 42 comprises an enlarged portion 44, configured to cooperate with the enlarged zone 40 of the orifice 36, which has a section greater than that of the smallest passage section of the orifice 36 as well as at least one expandable portion 46 configured to occupy a first state, called the retracted state, in which the expandable portion 46 has a first section less than or equal to that of the smallest passage section of the orifice 36, as illustrated in part (B) of [Fig. 7], as well as a second state, called the expanded state, in which the expandable portion 46 has a second section greater than the first section and that of the smallest passage section of the orifice 36 as illustrated in part (A) of [Fig. 7].When the removable shutter 42 is in the mounted state, the enlarged part 44 and the expandable part 46 of the removable shutter 42 are positioned on either side of the smaller passage section of the orifice 36.

[0048] When the expandable portion 46 is in the retracted state, the removable shutter 42 is inserted into the orifice 36 until the enlarged portion 44 abuts against the fairing 30 and is positioned in the enlarged area 40, which corresponds to the mounted state of the removable shutter 42. The expandable portion 46 then projects relative to the inner face F30' of the fairing 30. As long as the expandable portion 46 is in the retracted state, the removable shutter 42 is in the mounted and unlocked state, as illustrated in part (B) of [Fig.7], and can be removed from the orifice 36.

[0049] When the expandable part 46 is in the expanded state, the latter has a section greater than that of the smallest passage section of the orifice 36. It is then in contact with the inner face F30' of the fairing 30 so that the removable shutter 42 can no longer be removed from the orifice 36. The removable shutter 42 is thus in the mounted and locked state.

[0050] According to one embodiment, the expandable portion 46 comprises an elastic ring 48 which extends between first and second annular faces 46.1, 46.2 and has a first section when it is not compressed, in the absence of constraints, as well as a second section greater than the first section when it is compressed between the first and second annular faces 46.1, 46.2. Thus, the first section corresponds to the retracted state and the second section corresponds to the expanded. For example, the elastic ring 48 is made of elastomer.

[0051] The removable shutter 42 comprises a compression system 50 configured to occupy an inactivated state in which the compression system 50 does not compress the expandable portion 46, in particular the elastic ring 48, as well as an activated state in which the compression system 50 compresses the expandable portion 46, in particular the elastic ring 48.

[0052] The compression system 50 comprises on the one hand a screw 52 which has a head 54 as well as a rod 56 comprising at least one threaded section and, on the other hand, a compression nut 58 immobilized in rotation relative to the fairing 30 and comprising a tapped hole 58.1 into which the threaded section of the rod 56 of the screw 52 is screwed, the elastic ring 48 being interposed between the head 54 of the screw 52 and the compression nut 58.

[0053] According to one embodiment, the head 54 of the screw 52 has a conical lateral face and a transverse face at the level of which is provided at least a first imprint 60 to pivot the screw 52 using a tool such as a screwdriver for example. When the removable shutter 42 is positioned in the orifice 36, the rod 56 of the screw 52 has an axis A56 coinciding with the axis of revolution A36 of the orifice 36.

[0054] According to a simplified configuration, the head 54 of the screw 52 corresponds to the enlarged part 44 of the removable shutter 42.

[0055] According to another configuration visible in Figures 6 to 10, the removable shutter 42 comprises at least a first sleeve 62 positioned around the head 54 of the screw 52. When the removable shutter 42 is in the mounted state, the first sleeve 62 is inserted into the orifice 36 and interposed between the fairing 30 and the screw 52. Thus, the screw 52 is not in contact with the fairing 30. The screw 52 and the first sleeve 62 can be designed so as to limit the friction between the screw 52 and the first sleeve 62. Alternatively, the screw 52 and the first sleeve 52 respectively comprise first and second contact surfaces configured to allow screwing of the screw 52 and block or slow down its unscrewing when the first and second contact surfaces are in contact with each other.

[0056] According to one embodiment, the first sleeve 62 extends between first and second transverse faces 62.1, 62.2 and comprises a first section 64.1, which extends from the first transverse face 62.1, configured to cooperate with the first section 38.1 of the orifice 36 as well as a second section 64.2, which extends from the second transverse face 62.2 to the first section 64.1, configured to cooperate with the second section 38.2 of the orifice 36. Thus, the first section 64.1 is conical and has a conical outer surface substantially identical to the first section 38.1 of the orifice 36 as well as a conical inner surface identical to the lateral face of the head 54 of the screw 52. The second section 64.2 is tubular and has a cylindrical external surface substantially identical to the second section 38.2 of the orifice 36 as well as a cylindrical internal surface identical to that of the rod 56 of the screw 52.

[0057] According to this embodiment, the first sleeve 62 and the orifice 36 are configured so that when the removable shutter 42 is in the mounted state, the first transverse face 62.1 of the first sleeve 62 is flush with the outer face F30 of the fairing 30. The first sleeve 62 and the screw 52 are configured so that the transverse face of the head 54 of the screw 52 is flush with the first transverse face 62.1 of the first sleeve 62. In addition, the second transverse face 62.2 of the first sleeve 62 can be flush with the inner face F30' of the fairing 30.

[0058] In operation, the first annular face 46.1 of the elastic ring 48 is in contact with the second transverse face 62.2 of the first sleeve 62. The second annular face 46.2 of the elastic ring 48 is in contact with the compression nut 58.

[0059] According to one configuration, the first sleeve 62 is configured to be immobile relative to the fairing 30. Thus, the first sleeve 62 may comprise at least a first shape which cooperates with a second shape of the fairing 30, the first and second shapes being designed to immobilize the first sleeve 62 in rotation relative to the fairing 30.

[0060] According to another configuration, the first sleeve 62 comprises, at its first transverse face 62.1, at least one second imprint 66 configured to allow rotational immobilization of the first sleeve 62 relative to the fairing 30 using a tool. According to one arrangement, the second imprint 66 comprises two diametrically opposed blind holes 66.1, 66.1' provided at the first transverse face 62.1.

[0061] Of course, the invention is not limited to these solutions for immobilizing the first sleeve 62 in rotation relative to the fairing 30. In addition, the removable shutter 42 may comprise several sleeves. Thus, as illustrated in [Fig. 10], the removable shutter 42 comprises first and second coaxial sleeves 62, 68, the second sleeve 68, positioned around the first sleeve 62 (between the latter and the fairing 30 when the removable shutter 42 is in the mounted state), comprising radial fins 68.1 at the periphery. This solution is more particularly suitable when the fairing 30 is a panel made of composite material comprising a cellular core positioned between two skins. In this case, the radial fins 68.1 of the second sleeve 68 are positioned at the level of the cellular core of the fairing 30, between the two skins.

[0062] According to one embodiment, the removable shutter 42 comprises a connection slide 70 connecting the first sleeve 62 and the compression nut 58. According to one configuration, the slide connection 70 comprises first and second tubular extensions 70.1, 70.2, secured respectively to the first sleeve 62 and the compression nut 58, configured to slide one inside the other. The first tubular extension 70.1 has an axis substantially coincident with the axis A56 of the rod 56 of the screw 52 when the removable shutter 42 is assembled. The second tubular extension 70.2 is coaxial with the tapped hole 58.1 of the compression nut 58 which has an axis coincident with the axis A56 of the rod 56 of the screw 52 when the rod 56 of the screw 52 is screwed into the tapped hole 58.1 of the compression nut 58.

[0063] In addition, a first element among the first and second tubular extensions 70.1, 70.2 comprises a slot 72 oriented in a direction parallel to the axis A56 of the rod 56 of the screw 52. In addition, a second element, different from the first element, among the first and second tubular extensions 70.1, 70.2 comprises a lug 74 configured to slide in the slot 72 of the first element.

[0064] According to one arrangement, the first tubular extension 70.1 secured to the first sleeve 62 slides inside the second tubular extension 70.2 secured to the compression nut 58. In addition, the slot 72 is provided at the level of the first tubular extension 70.1 secured to the first sleeve 62 and the lug 74 is provided at the level of the second extension 70.2 secured to the compression nut 58.

[0065] Of course, the invention is not limited to this embodiment for the sliding connection 70. Other solutions are conceivable for the sliding connection or for immobilizing the compression nut 58 in rotation.

[0066] According to one embodiment, the removable shutter 42 comprises a removable stop 76 provided at the level of the rod 56 of the screw 52 and configured to prevent the compression nut 58 from becoming detached from the rod 56 of the screw 52. According to one configuration, this removable stop 76 is an elastic ring positioned in a groove provided at the level of the free end of the rod 56 of the screw 52.

[0067] According to an assembly method visible in [Fig.8], the elastic ring 48 is positioned against the second tubular extension 70.2 of the compression nut 58, as illustrated in part (A) of [Fig.8]. Next, the first sleeve 62 is positioned by introducing its first tubular extension 70.1 into the elastic ring 48 and into the second tubular extension 70.2 secured to the compression nut 58 as well as by inserting the lug 74 into the slot 72, as illustrated in part (B) of [Fig.8]. Next, the rod 56 of the screw 52 is screwed into the compression nut 58 until the head 54 of the screw 52 is in contact with the first sleeve 62 as illustrated in part (C) of [Fig.8] and the elastic ring 48 either simultaneously in contact or almost in contact with the compression nut 58 and the first sleeve 62 without however being compressed. Finally, the elastic ring 76 is mounted on the rod 56 of the screw 52, as illustrated in part (D) of [Fig.8].

[0068] Of course, the invention is not limited to this method of assembly for the removable shutter 42.

[0069] When the removable shutter 42 is in the disassembled state, the flexible cord 34.3 of a horoscope 34 can be introduced via the orifice 36.

[0070] To correctly orient the flexible cord 34.3 under the fairing 30, the equipment 32 for carrying out a horoscopic inspection comprises a guide tool 78 visible in FIGS. 11 and 12, insertable into an orifice 36 and configured to guide a flexible cord 34.3 of a horoscope 34.

[0071] When the orifice 36 is closed by a removable shutter 42, the latter is removed, prior to each inspection, to be able to introduce the guide tool 78 into the orifice 36.

[0072] According to one embodiment, the guide tool 78 comprises a body 80, which has a section less than or equal to the smallest passage section of the orifice 36 and extends between first and second ends 80.1, 80.2, as well as a head 82, having a section greater than the smallest passage section of the orifice 36, connected to the second end 80.2 of the body 80. According to one arrangement, the body 80 is bent and forms an L.

[0073] According to one configuration, the head 82 is spherical and configured to be housed at least partially in the enlarged zone 40 of the orifice 36, in particular in the first frustoconical section 38.1.

[0074] According to one embodiment, the body 80 comprises an outer surface F80 which has a substantially constant circular cross-section between the first and second ends 80.1, 80.2. To guide the flexible cord 34.3 of a horoscope 34, the body 80 comprises at least one groove 84 hollow relative to the outer surface F80, which extends from one end to the other of the body 80, configured to house the flexible cord 34.3 of a horoscope 34. This groove 84 has a cross-section greater than or equal to that of the flexible cord 34.3. According to one configuration, the groove 84 has a U-shaped cross-section.

[0075] According to one configuration, the head 82 comprises a slot 82.1, in the extension of the groove 84, which has a width greater than or equal to the section of a flexible cord 34.3 of a horoscope 34.

[0076] According to a characteristic of the invention, the guide tool 78 comprises a tubular end piece 86, connected to the first end 80.1 of the body 80, having an internal section greater than the section of the flexible cord 34.3 of a horoscope 34 to allow its passage. This tubular end piece 86 ensures the guidance of the flexible cord 34.3 under the fairing 30 when the guide tool 78 has been introduced into the orifice 38.

[0077] To allow the insertion of the body 80 into the orifice 36, the tubular end piece 86 is located in the extension of the body 80 and has an external surface F86 of section smaller than the smallest passage section of the orifice 36. According to one configuration, the external surface F86 has the same section as the external surface F80 of the body 80. Whatever the embodiment, the body 80 and the tubular end piece 86 are configured to pass through the orifice 36, the head 82 being configured not to pass through the orifice 36.

[0078] According to one embodiment, the groove 84 opens into the tubular end piece 86. Thus, a flexible cord 34.3 of a horoscope 34 housed in the groove 84 can continuously pass through the tubular end piece 86.

[0079] As illustrated in [Fig. 12], a method for horoscopic inspection of an area located behind the fairing 30 comprises a step of introducing a flexible cord 34.3 of a horoscope 34 into the tubular end piece 86, a step of placing the flexible cord 34.3 in the groove 84 of the body up to the head 82, a step of introducing the guide tool 78 into the orifice 36 via the tubular end piece 86 until the head 82 is in contact with the fairing 30 and cooperates with the enlarged area 40 of the orifice 36 as well as a step of orienting the free end 34.4 of the flexible cord 34 by modifying the orientation of the head 82 of the guide tool 78.

[0080] The spherical shape of the head 82 combined with the truncated cone shape of the widened zone 40 of the orifice 36 makes it possible to orient the head 82 along three axes of rotation and to optimize the orientation of the free end 34.4 of the flexible cord 34.3 of the horoscope 34 under the fairing 30.

[0081] Of course, the invention is not limited to this embodiment for the guide tool 78.

[0082] Although described as applied to the horoscopic inspection of an area located behind a fairing 30 of an aircraft, the invention can be applied to other walls.

Claims

Claims

1. A tool for guiding a flexible cord (34.3) of a horoscope, said guiding tool making it possible to carry out a horoscopic inspection by introducing the flexible cord (34.3) of the horoscope (34) into an orifice (36; characterized in that the guiding tool comprises a body (80) extending between first and second ends (80.1, 80.2), a head (82) connected to the second end (80.2) of the body (80) and a tubular end piece (86), connected to the first end (80.1) of the body (80), which has an inner section making it possible to house the flexible cord (34.3) of the horoscope (34), the body (80) and the tubular end piece (86) being configured to pass through the orifice (36), the head (82) being configured not to pass through the orifice (36).

2. Guiding tool according to claim 1, characterized in that the body (80) is bent.

3. Guiding tool according to one of the preceding claims, characterized in that the head (82) is spherical.

4. Guiding tool according to one of the preceding claims, characterized in that the body (80) comprises at least one groove (84) which extends from one end to the other of the body (80), said groove (84) being configured to house the flexible cord (34.3) of the horoscope (34).

5. Guiding tool according to the preceding claim, characterized in that the head (82) comprises a slot (82.1), in the extension of the groove (84), which has a width allowing the flexible cord (34.3) of the horoscope (34) to be housed.

6. Guiding tool according to one of claims 4 to 5, characterized in that the groove (84) opens into the tubular end piece (86).

7. Aircraft comprising a fairing (30) which has outer and inner faces (F30, F30'), characterized in that the aircraft comprises at least one piece of equipment (32) making it possible to carry out at least one horoscopic inspection and comprising an orifice (36) which passes through the fairing (30), configured to allow the introduction of a guidance tool according to one of the preceding claims, supporting a flexible cord (34.3) of a horoscope (34).

8. Aircraft according to the preceding claim, characterized in that the orifice (36) comprises a widened, frustoconical zone (40) at the level of the external surface (F30) of the fairing (30).

9. Aircraft according to the preceding claim, characterized in that the equipment (32) for performing at least one horoscopic inspection comprises a removable shutter (42) configured to occupy a mounted state in which the removable shutter (42) closes the orifice (36) and a dismounted state in which the removable shutter (42) clears the orifice (36).

10. A method for horoscopic inspection of an area located behind a fairing (30) using a guide tool (78) according to one of claims 1 to 6 and a horoscope (34) which comprises a flexible cord (34.3) having a free end (34.4) as well as at least one camera (34.5) positioned at the free end (34.4), characterized in that the method comprises a step of introducing the flexible cord (34.3) of the horoscope (34) into the tubular end piece (86) of the guide tool (78), a step of placing the flexible cord (34.3) in the groove (84) of the body (80) of the guide tool (78) up to its head (82), a step of introducing the guide tool (78) into an orifice (36) passing through the fairing (30) as well that a step of orienting the free end (34.4) of the flexible cord (34) by modifying the orientation of the head (82) of the guide tool (78).

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