Steve
En-Route
AD NUMBER: 2007-06-01
MANUFACTURER: Raytheon
SUBJECT: Airworthiness Directive 2007-06-01
SUMMARY: We are adopting a new airworthiness directive (AD) that
supersedes AD 62-24-01, which applies to all Raytheon Aircraft
Company (RAC) Beech Models 45 (YT-34), A45 (T-34A, B45), and D45(T-
34B ) airplanes. AD 62-24-01 currently requires you to repetitively
inspect, using the dye penetrant method, the front and rear
horizontal stabilizer spars for cracks and replace any cracked
stabilizer. Since we issued AD 62-24-01, we determined that using
the dye penetrant inspection method may not detect cracks before the
crack grows to a critical length and causes failure of the
horizontal stabilizer spars. Therefore, we are requiring the surface
eddy current inspection method to detect cracks in the horizontal
stabilizer spars. Consequently, this AD retains the actions required
in AD 62-24-01 and changes the required inspection method from dye
penetrant to surface eddy current. We are issuing this AD to prevent
failure of the front and/or rear horizontal stabilizer spars caused
by fatigue cracks. This failure could result in stabilizer
separation and loss of control of the airplane.
FMI: www.faa.gov/regulations_policies/airworthiness_directives/
Refer to the AD for required inspection intervals (basically 200 hrs since the last acceptable dye penetrant inspection and every 500 hrs thereafter).
MANUFACTURER: Raytheon
SUBJECT: Airworthiness Directive 2007-06-01
SUMMARY: We are adopting a new airworthiness directive (AD) that
supersedes AD 62-24-01, which applies to all Raytheon Aircraft
Company (RAC) Beech Models 45 (YT-34), A45 (T-34A, B45), and D45(T-
34B ) airplanes. AD 62-24-01 currently requires you to repetitively
inspect, using the dye penetrant method, the front and rear
horizontal stabilizer spars for cracks and replace any cracked
stabilizer. Since we issued AD 62-24-01, we determined that using
the dye penetrant inspection method may not detect cracks before the
crack grows to a critical length and causes failure of the
horizontal stabilizer spars. Therefore, we are requiring the surface
eddy current inspection method to detect cracks in the horizontal
stabilizer spars. Consequently, this AD retains the actions required
in AD 62-24-01 and changes the required inspection method from dye
penetrant to surface eddy current. We are issuing this AD to prevent
failure of the front and/or rear horizontal stabilizer spars caused
by fatigue cracks. This failure could result in stabilizer
separation and loss of control of the airplane.
FMI: www.faa.gov/regulations_policies/airworthiness_directives/
Refer to the AD for required inspection intervals (basically 200 hrs since the last acceptable dye penetrant inspection and every 500 hrs thereafter).
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