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An aircraft auxiliary power unit assembly includes an aircraft skin that provides a cavity. It is secured to a structure in an assembled condition and it provides an opening. An auxiliary power unit is arranged within the cavity and is secured to the structure. The aircraft skin substantially covers

An aircraft auxiliary power unit assembly includes an aircraft skin that provides a cavity. It is secured to a structure in an assembled condition and it provides an opening. An auxiliary power unit is arranged within the cavity and is secured to the structure. The aircraft skin substantially covers the auxiliary power unit in the assembled condition. An inlet duct that is removable is secured within the opening and is selectively connected to the auxiliary power unit between the installed and service positions. The installed and service positions are with the aircraft skin in the assembled condition.

대표청구항 ▼

1. An aircraft auxiliary power unit assembly comprising: an auxiliary power unit configured to be installed within a cavity provided by an aircraft skin and the auxillary power unit configured to be secured to an aircraft structure with the aircraft skin substantially covering the auxiliary power un

1. An aircraft auxiliary power unit assembly comprising: an auxiliary power unit configured to be installed within a cavity provided by an aircraft skin and the auxillary power unit configured to be secured to an aircraft structure with the aircraft skin substantially covering the auxiliary power unit;an inlet duct configured to be removably secured within a fixed opening in the aircraft skin and selectively connected to the auxiliary power unit between installed and service positions;wherein the installed and service positions are within the aircraft skin, and the service position is further configured to have the inlet duct detached from the aircraft skin and the structure, wherein the inlet duct is configured to be removed and installed through the opening as an assembled unit. 2. The assembly according to claim 1, wherein the aircraft skin provides a tail cone and an outer surface is provided on an exterior side opposite the cavity, the aircraft skin including a skin flange defining the opening, and the inlet duct having a duct flange secured to the skin flange in the installed position with fastening elements. 3. The assembly according to claim 2, wherein the inlet duct includes a passage and a screen is arranged over the passage, the outer surface providing a contour and the screen generally arranged along the contour and affixed within the opening in the installed position. 4. The assembly according to claim 2, wherein the opening includes an opening perimeter circumscribing a portion of the duct, and the duct defines a passage and includes first and second flanges arranged on the duct at opposite ends of the passage, the first flange arranged exteriorly of the aircraft skin on a side opposite the cavity, the first flange having an outer perimeter larger than the opening perimeter. 5. The assembly according to claim 4, comprising a screen supported by the first flange. 6. The assembly according to claim 4, wherein the first flange includes apertures configured to receive fastening elements that are removably secured to the aircraft skin between the installed and the service positions. 7. The assembly according to claim 1, the auxiliary power unit includes line replaceable units that include at least one of a fuel control unit, a speed sensor, and an igniter, the line replaceable units removable through the opening with the inlet duct removed to the service position. 8. An inlet duct for an auxiliary power unit comprising: an inlet duct configured to be removably secured within an opening in an aircraft skin and selectively connected to an auxiliary power unit between installed and service positions;the inlet duct defining a passage and including first and second flanges arranged on the duct at opposite ends of the passage, the first flange including apertures configured to receive fastening elements, the first flange having an outer perimeter configured to be larger than the opening within which the first flange is to be secured relative to in the installed position, wherein the inlet duct is configured to be removed and installed through the opening as an assembled unit;a seal secured to the second flange; andsilencing elements arranged within the passage.