in accordance with preferred embodiments of the invention , an acoustic liner inlet barrel is formed as one continuous piece when viewed in cross - section facing the longitudinal direction of the barrel , rather than three pieces with splices as shown in fig1 ( a ), 1 ( b ), and 1 ( c ). this one - piece acoustic liner inlet barrel design is schematically depicted in fig2 ( a ) and 2 ( b ). essentially , the liner inlet barrel shown in fig2 ( a ) and 2 ( b ) is formed by manufacturing a continuous one - piece inner back facesheet and either splicing the ends of the core and perforated microporous facesheet together , at splice 19 as shown in fig2 ( a ), or using a variety of techniques which result in a finished product which has no splice at all , as shown in fig2 ( b ). the one - piece liner 18 of fig2 ( a ) is substantially cylindrical and includes , as illustrated in greater detail in fig3 and 4 , a perforate and / or microporous facesheet 23 , a honeycomb core 24 and a solid backing facesheet 25 constructed in a conventional manner except that the structure is continuous in the circumferential direction over an angle of 360 °. the splice area 19 of fig2 ( a ) is formed in such a manner that the resulting splice is as narrow as possible so that it approaches the limit of no splice as shown in fig2 ( b ). the preferred method of making the single - splice barrel differs from the method taught in u . s . pat . no . 4 , 826 , 106 in that it is for an engine inlet barrel rather than an aircraft engine translating aft cowling , and in that instead of forming sections of less than 180 ° each , the barrel is formed in one piece which extends over an angle of 360 °. while the materials may be the same as disclosed in u . s . pat . no . 4 , 826 , 106 , other suitable composite or metallic materials will occur to those skilled in the art and are intended to be included within the scope of the invention . in practice , construction of embodiments that do not require inclusion of a separate microporous layer will consist of , from the inside out , the perforated laminate 23 , a layer of glue ( not shown ), the honeycomb core 24 , a layer of glue ( not shown ), and the nonporous , continuous , backing facesheet 25 . the layers of glue on the inside and outside of the core may be brought to the assembly as discrete layers , or , under controlled conditions , the bond between core and either facesheet can be made with the resin from the contiguous laminates . if a microporous facesheet is required , it may be incorporated either as the air passage ( first ) layer or just beneath the air passage perforate . in either case , if the microporous layer ( which may be made for example of a woven mesh and which is used to obtain desired acoustic properties of the liner ) is only available in sheet form , its ends must be joined on the circumference in a manner that results in a discontinuity of material physical and mechanical properties , i . e ., a splice . this is a concession to practicality that may have to be accepted for reasons of cost , but there are also methods of weaving cylindrical geometries that may be employed , at additional cost , to obviate the need for a splice even in this layer . the perforate facesheet can be a fiber reinforced laminate such as graphite / epoxy , graphite / bismalyimide , glass / epoxy or other such material that might occur to those skilled in the art . the holes may be molded into the lamate in a separate curing process or molded into the facesheet during a co - curing / bonding operation that includes the core and / or the solid back facesheet . one form of the construction may use a metallic porous facesheet made circumferentially continuous by some form of welding and subsequently formed to near - cylindrical shapes by magnaforming or other similar processes . in order to eliminate the facesheet seams , the facesheets may , for example , be formed by wrapping the facesheet material around a form to an angle of greater than 360 ° before curing . the core structure may be formed by applying pressure to ends of a honeycomb to thereby push them together until no seam is apparent . in the preferred embodiment of the invention , shown in fig3 and 5 ( b ), integral fittings are provided by weaving or braid graphite yarn into a preform , for example in the manner taught in u . s . pat . no . 4 , 826 , 106 . these preforms are then impregnated with an epoxy or other resin so that they can easily and quickly be added to the wet barrel assembly and cured simultaneously with the acoustic sandwich to create a non - splice continuous structure without the need for separate discrete fastener attachment . this results in a lighter weight , more durable structure . these include an integral engine mounting flange 20 to which engine frame 30 is attached at an aft end of the barrel , a firewall ring frame attachment flange 21 , and an leading edge ( l . e .) ring frame attachment flange 22 at the forward end . fig3 and 5 ( b ) also show the perforated facesheet 23 , honeycomb core 24 , and non - porous facesheet 25 . the barrel structure of fig3 and 5 ( b ) may either have a sing splice or no splice . a portion of the structure has been cut away to reveal the co 24 . in another preferred embodiment , it is possible to add the firewall ring frame 26 and the l . e . ring frame 27 by building up the attachment flanges , as shown in fig4 and 5 ( c ), in order to replace the conventional ring structures 28 and 29 shown in fig5 ( a ) by a firewall ring 26 and an l . e . ring 27 . as a result , even with an increased acoustic area , the weight of the barrel including anti - ice installation is actually reduced , as is the cost , relative to the acoustic inlet barrel shown in fig5 ( a ), which is a state - of - the - art construction with non - integral fittings 31 to 35 . having thus described in detail specific preferred embodiments of the invention , it is nevertheless intended that the invention not be limited by the above description , but rather that it be interpreted solely in accordance with the appended claims .