Appeal No. 2004-0568
Application No. 09/229,547
backside fastening said plurality of single piece blind
fasteners to the aircraft structure.
8. An acoustic panel defining air flow direction in an
aircraft engine comprising:
a perforated inner sheet;
a honeycomb core arranged over said perforated inner
sheet;
an outer sheet attached to said honeycomb core; and,
blind bolts for backside fastening said acoustic panel
to aircraft engine structure.
13. In combination in an aircraft engine having an engine
inlet and a fan duct or thrust reverser:
an acoustical panel providing air flow direction;
said acoustical panel having an inner face sheet;
said inner face sheet having an entire perforated and
acoustically treated surface area;
a honeycomb core disposed over said perforated sheet;
and
an outer sheet attached to said honeycomb core;
said honeycomb core bonded to said perforated sheet;
and,
said outer sheet bonded to said honeycomb core.
In the rejection of the appealed claims, the examiner relies
upon the admitted prior art in addition to the following
references:
Dhoore et al. (Dhoore) 4,235,303 Nov. 25, 1980
Birbragher 4,759,513 Jul. 26, 1988
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