AFS-BH430-IBF-ICA
Aerospace
Filtration Systems, Inc.
Revision: B
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11
AFS Bell 230 and 430 IBF
to the restrictions on the title page
Instructions for Continued Airworthiness
3.2.2
STRUCTURAL COMPONENT INSPECTIONS
VISUAL: All structural IBF components are to be inspected in accordance with Table 1
every 100 hours and annual inspection. These components include the following: Forward
Filter Assemblies, Upper Filter Assemblies, Side Closeout Assemblies, and Sensor mounting
components.
3.2.3
SYSTEMS AND ELECTRICAL COMPONENT INSPECTIONS
a.
VISUAL: The systems and electrical components are to be visually inspected in accordance
with Table 1 every 100 hours and annual inspection. These components include the following:
Wiring, Wiring Harnesses, Connectors, Backshells, Circuit Breakers, Cockpit Switch/
Indicators, Differential Pressure Switches, Filter Maintenance Aids, and Actuators.
b.
FUNCTION CHECK: Certain systems and electrical components are also to be function
checked in accordance with Table 1 every annual inspection. These components include the
following: Circuit Breakers, Cockpit Switch/Indicators, Differential Pressure Switches, Filter
Maintenance Aids, and Actuators.
c.
FMA CHECK: The FMA check is performed to ascertain the current condition of the filter or to
gage the trend in accumulation of dirt. The FMA check is only a check of the indicator reading
(See Picture 1). As such it is not considered an inspection of the FMA. The inspection Table 1
does not require a specific “inspection” interval of the FMA. The condition of the Filter
Assembly and its accumulation of dirt will show up as an indication on the FMA. Thus
operational environment, more so than time in service, dictate how often the FMA should be
checked in order to help determine the next Filter Assembly service requirement. It is an aid in
scheduling the Filter Assembly servicing. At any time prior to an FMA indication in the “RED”
(See Picture 1), a failed PAC, or a IBF “FILTER” indication on the cockpit indicator, when
maintenance or flight personnel see a trend based on the FMA readings over time that would
warrant servicing of the filter due to operational considerations, such as when the aircraft will
be operated in a remote or off-site location without the ability to readily service the filter, the
filter may be serviced, or replaced. See Section 7.2 for a further description of the use of the
FMA as it relates to the Filter Assembly service interval. See filter servicing Section 7.3.
NOTE
The Filter Maintenance Aid is designed to hold the highest differential
pressure measured across the filter assembly during the last flight, and
should be reset after servicing of the filter assembly by depressing the yellow
button marked “PUSH TO RESET” located on the end of the filter
maintenance aid (See Picture 1).
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