within a surrounding casing in a gas turbine engine which involves inserting the fuel manifold into the casing with support elements positioned in a retracted position displacing the support elements into an extended position and fastening said support elements to mount the manifold to an inner surface of said casing application_number US 15164405 A description fig1 illustrates a gas turbine engine 10 of a type preferably provided for use in subsonic flight generally comprising in serial flow communication a fan 12 through which ambient air is propelled a multistage compressor 14 for pressurizing the air a combustor 16 defining a combustion chamber 17 within which the compressed air is mixed with fuel and ignited for generating an annular stream of hot combustion gases and a turbine section 18 for extracting energy from the combustion gases fuel is injected into the combustor 16 using a fuel injection system 20 which comprises a fuel manifold ring 22 disposed outside the combustor 16 and n internally mounted within the surrounding engine casing referring to fig2 and 3 the annular fuel manifold 22 is internally mounted within the gas generator casing 26 of the engine adjacent to an upstream or dome end 19 of the combustor 16 the fuel manifold 22 has a main ring body 23 defining at least one fuel flow passage 25 therein and preferably also includes an outer heat shield 27 which at least partially encloses the main ring body 23 the fuel passage 25 of the annular fuel manifold ring 22 is.