Patent ID: 7089747

Claim:
A high volume air sampler system for use on an aircraft comprising: an air source; a turbine engine bleed valve coupled to said air source; a source hose coupled to said bleed valve; a pressure reduction apparatus coupled to said source hose, the pressure reduction apparatus comprising: a hollow vessel coupled to said source hose, said hollow vessel including an interior and an exterior, an inlet, and a port to allow air to exit the vessel; and a valve affixed to said inlet to allow air to enter said vessel and to prevent air from exiting said vessel through said valve; and a high volume air sampler coupled to and disposed downstream of said pressure reduction apparatus, said high volume air sampler comprising: an adapter coupled to said pressure reduction apparatus, said adapter including a body having a first section, a second section, and an interior surface defining a cavity, said body first section having an opening formed therein that is in communication with said cavity, said body second section having a sample port formed therein that is in communication with said cavity, said sample port having a diameter that is smaller than the diameter of the opening; and a canister coupled to said adapter having an inlet opening, an exit opening, an interior region that defines a passage between said inlet and exit openings, and an adsorbent material disposed within said passage.