Insulation package arrangement for insulating the interior of an aircraft fuselage

An insulation package system for insulating an interior of an aircraft, comprising:

• a fuselage, the fuselage including a plurality of stringers stiffening panels of an outer skin of the fuselage and a rib arranged substantially perpendicularly to a longitudinal direction along an axis of the fuselage of the aircraft, the rib being attached to one of the plurality of stringers at a first end of the rib and having a rib carrier integrated into the rib on an unattached end of the rib and a rib attachment region disposed between the first end and the rib carrier, the rib attachment region having a through-hole through the rib attachment region;
• and
• at least two fuselage insulation packages having an elongated package shape, and being situated in a direction of a longitudinal axis of the fuselage, each of the fuselage insulation packages comprising:
• a first flat insulation end section integrally extending outwardly from a first end of each of the at least two fuselage insulation packages and having a first length;
• a second flat insulation end section integrally extending outwardly from a second end of each of the at least two fuselage insulation packages opposite to the first end of each of the at least two fuselage insulation packages and having a second length shorter than the first length;
• and
• a foil enclosing a burn-through-proof insulation or a burn-through-proof barrier layer or both a burn-through-proof insulation having a first thickness and a burn-through-proof barrier layer having a second thickness less than the first thickness of the burn-through-proof insulation;
• and
• a burn-through-proof first attachment element having a first retainer end at one end of the first attachment element and a second retainer end at an opposite end of the first attachment element, the first attachment element being disposed through the through-hole of the rib attachment region such that the first retainer end is on one side of the rib attachment region and the second retainer end is on an opposite side of the rib attachment region,
• wherein the first retainer end of the first attachment element attaches both of the first flat insulation end section of a first of the at least two fuselage insulation packages and the second flat insulation end section of a second of the at least two fuselage insulation packages to one side of the rib attachment region of the rib via a hole in each of the first flat insulation end section of the first of the at last two fuselage insulation packages and the second flat insulation end section of the second of the at least two fuselage insulation packages such that a portion of the first of the at least two fuselage insulation packages overlaps with, or is overlapped by, the second of the at least two fuselage insulation packages, and the first of the at least two fuselage insulation packages is also retained on the opposite side of the rib attachment region by the second retainer end of the attachment element passing through a second hole formed in the first of the at least two fuselage insulation packages,
• wherein the first retainer end and the second retainer end are arranged on the inside of the aircraft with respect of the burn-through-proof insulation or the burn-through-proof barrier layer,
• the insulation package system further comprising:
• a second attachment element,
• wherein the second attachment element is shaped as a truncated-cone body and comprises_an insulated disc element and the insulated disc element comprises a disc-shaped core element, defining a hole in the center of the disc and being embedded in a casing such that the insulated disc element is burn through proof.