Significant Regulatory Activity

Air Safety Week,  May 14, 2007  

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Aircraft: AD 2007-09-51  MD369 helos
Effect: To prevent the loss of a tail rotor blade and subsequent loss of control
of the helicopter?inspect the bore of the tail rotor blade root fitting for a
smooth radius (a sharp transition in the tapered end of the root fitting bore
can cause the tail rotor blade root fitting to fail).  Emergency AD 27 Apr eff
on receipt

Aircraft: AD 2007-10-04  MD81 thru MD88
Effect: Results from reports of cracks found in the horizontal stabilizer--in
the upper and lower aft skin panels at the aft inboard corner at station XH =
8.2, and in the rear spar upper caps?. to detect and correct cracks in the upper
and lower aft skin panels and rear spar upper caps, which, if not corrected,
could lead to the loss of overall structural integrity of the stabilizer.  final
rule eff 23 May

Aircraft: 2006-NM-258-AD ERJ170 / ERJ190
Effect: Results from a report that an engine shut down during flight due to the
failure of the low-stage check valve engine bleed system to close. Requires
valve and seal replacement.  NPRM comments by 7 June

Aircraft: AD 2007-10-03  767-200 / 300
Effect: Results from a report indicating a hole in the discharge tube assembly
for the metered fire extinguishing system; and another report indicating that an
operator found chafing of the fire extinguishing tube against the APU duct that
resulted in a crack in the tube?.. to prevent fire extinguishing agent from
leaking out of the tube assembly in the aft cargo compartment which, in the
event of a fire in the aft cargo compartment, could result in an insufficient
concentration of fire extinguishing agent, and consequent inability of the fire
extinguishing system to suppress the fire.  Final rule eff 13 Jun

Aircraft: AD 2007-10-05 GE90-110B1, -113B, and  -115B
Effect: To prevent structural failure of the Turbine Center Frames  with
uncontained failure of low pressure turbine (LPT) rotating parts. Uncontained
failure of the LPT rotating parts could result in damage to the airplane and
possible loss of control of the airplane.  Final Rule eff 14 June

Aircraft: AD 2007-10-02 Reims 406
Effect: Corrosion on the bearings with propagation to the bracket-hinge of the
rudder (discovered after rudder removals). Condition, if left uncorrected, could
result in the loss of the rudder control on the airplane. Final Rule eff 13 June

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