AD 91-09-04
Applicability
| Type | Manufacturer | Model | Details |
|---|---|---|---|
| aircraft | ATR - GIE Avions de Transport R gional | ATR42-300 | AEROSPATIALE Models ATR42-300 and ATR42-320 Series Airplanes |
| aircraft | ATR - GIE Avions de Transport R gional | ATR42-320 | AEROSPATIALE Models ATR42-300 and ATR42-320 Series Airplanes |
Unsafe Condition
Reduced structural integrity of the fuselage due to potential cracks in the webs of main Frame 25 and Frame 27 between Stringer 6 and Stringer 7.
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Required Actions
Perform a high frequency eddy current (HFEC) inspection of the webs of main Frame 25 and Frame 27 within 250 hours time-in-service after the effective date. If cracks are found, stop drill holes at the ends of cracks under 50.8 mm and perform a detailed visual inspection within 250 hours post-repair. For cracks over 50.8 mm, repair per approved method. Modification 15 S 535 R 00 38 must be done within 425 hours post-repair. Alternative compliance may be approved.
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Compliance Time
Within 250 hours time-in-service after the effective date of this AD
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Affected Aircraft
All ATR42-300 and ATR42-320 series airplanes post Modification 1572, as listed in Aerospatiale Service Bulletin ATR42-53-0057, Revision 2.
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Source: Official FAA Source ↗
Retrieved: Apr 8, 2026
Rights: U.S. Government Public Domain
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