Requirement:
1. For aircraft listed in Group A of the applicability part of this
Directive, with the exception of aircraft listed in Group A that
are already modified in accordance with the New Piper Aircraft
Service Bulletin (SB) No. 1139, dated 28 August 2003; accomplish
the following in accordance with Part I of SB No.1139 dated 9 April
2004:
a. Inspect the control wheel attachment screw for proper thread
engagement
(minimum one thread showing past the end of the nut plate), and
replace the
screw before further flight if insufficient thread engagement is
found.
b. Inspect the nut plate for sufficient locking characteristics.
If the screw can
be fully inserted into the nut plate by hand (one thread showing
past end of
nut), then replacement of the nut plate is required before further
flight.
c. Reassemble the control wheel onto the control wheel shaft and
install the
attachment screw using Loctite thread-locking compound.
2. For aircraft listed in Group A or Group B of the
applicability part of this
Directive, install retainer clip part number 104687-002 in
accordance with Part II
of SB No. 1139A, dated 9 April 2004.
Note: FAA AD 2004-14-12 Amdt 39-13721
refers.
Compliance:
Within 25 hours time in service after 11 August 2004.
Within 100 hours time in service after 11 August 2004.
This Airworthiness Directive becomes effective on 11 August
2004.
Background: The FAA received a report that a
Model PA-28-181 aircraft crashed after the pilot lost control of
the ailerons and elevator. Investigation revealed that the left
control wheel single attachment screw had unscrewed from its nut
plate, which resulted in the control wheel spinning freely on the
control column. Further investigation revealed the screw was too
short and the nut plate lacked proper locking characteristics.
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