Auxiliary power unit inlet
An aircraft auxiliary power unit assembly includes an aircraft skin providing a cavity. The aircraft skin is secured to a structure in an assembled condition and provides an opening. An auxiliary power unit is arranged within the cavity and secured to the structure. The aircraft skin substantially covers the auxiliary power unit in the assembled condition. An inlet duct is removably secured within the opening and is selectively connected to the auxiliary power unit between installed and service positions. The installed and service positions are with the aircraft skin in the assembled condition. A method of servicing the auxiliary power unit includes removing the auxiliary power unit inlet duct from the opening in the aircraft skin. The auxiliary power unit that is arranged within the cavity of the aircraft skin is exposed. A portion of the auxiliary power unit is serviced through the opening.
1. A method of servicing an auxiliary power unit comprising the steps of:
removing an auxiliary power unit inlet duct from an opening in an aircraft skin without disassembling the aircraft skin;
exposing through the opening, an auxiliary power unit arranged within a cavity of the aircraft skin; and
servicing a portion of the auxiliary power unit through the opening without removing the auxiliary power unit.
2. The method according to claim 1 , wherein the removing step includes removing fastening elements that secure the auxiliary power unit inlet duct to the aircraft skin.
3. The method according to claim 2 , wherein the removing step includes unseating an inlet duct flange from a skin flange that is provided around the opening.
4. The method according to claim 3 , wherein the removing step includes withdrawing an inlet duct neck, which is connected to the inlet duct flange, through the opening to an exterior side of the aircraft skin opposite the cavity.
5. The method according to claim 4 , wherein the removing step includes unseating a seal arranged between the auxiliary power unit inlet duct and the auxiliary power unit.
6. The method according to claim 1 , wherein the exposing step includes withdrawing the auxiliary power unit inlet duct through the opening to an exterior side of the aircraft skin opposite the cavity.
7. The method according to claim 6 , wherein the exposing step includes detaching a screen arranged in the opening from the aircraft skin.
8. The method according to claim 1 , wherein the servicing step includes manipulating an auxiliary power unit component with the auxiliary power unit secured within the cavity and the aircraft skin in an assembled condition.
9. The method according to claim 8 , wherein the servicing step includes replacing a line replaceable unit including at least one of a fuel control unit, a speed sensor, and an igniter.
10. The method according to claim 8 , wherein the servicing step includes accessing at least one of a clamp and an oil cooler.