layup 56 the consolidated layup 56 may then be cured at 110 optionally using autoclave processing at 112 the forming mandrel 68 is removed from the cured layup 56 and the layup 56 is removed from the mold 60 finally at 114 endwalls 34 and one or more pressure fittings 36 may be installed on the cured bladder embodiments of the disclosure may find use in a variety of potential applications particularly in the transportation industry including for example aerospace marine and automotive applications thus referring now to fig2 and 27 embodiments of the disclosure may be used in the context of an aircraft manufacturing and service method 120 as shown in fig2 and an aircraft 122 as shown in fig2 aircraft applications of the disclosed embodiments may include for example a wide variety of structural and non structural composite parts and components that are generally tubular during pre production exemplary method 120 may include specification and design 124 of the aircraft 122 and material procurement 126 during production component and subassembly manufacturing 128 and system integration 130 of the aircraft 122 takes place thereafter the aircraft 122 may go through certification and delivery 132 in order to be placed in service 134 while in service by a customer the aircraft 122 is scheduled for routine maintenance and service 136 which may also include modification reconfiguration refurbishment and so on each of the processes of method 120 may be performed or carried out by a system.