AD 97-01-01 R1
Applicability
| Type | Manufacturer | Model | Details |
|---|---|---|---|
| aircraft | Piper Aircraft Inc. | PA-24 | Airworthiness Directives; The New Piper Aircraft, Inc. PA-24, PA-28R, PA-30, PA-32R, PA-34, and PA-39 Series Airplanes |
| aircraft | Piper Aircraft Inc. | PA-24-250 | Airworthiness Directives; The New Piper Aircraft, Inc. PA-24, PA-28R, PA-30, PA-32R, PA-34, and PA-39 Series Airplanes |
| aircraft | Piper Aircraft Inc. | PA-24-260 | Airworthiness Directives; The New Piper Aircraft, Inc. PA-24, PA-28R, PA-30, PA-32R, PA-34, and PA-39 Series Airplanes |
| aircraft | Piper Aircraft Inc. | PA-24-400 | Airworthiness Directives; The New Piper Aircraft, Inc. PA-24, PA-28R, PA-30, PA-32R, PA-34, and PA-39 Series Airplanes |
| aircraft | Piper Aircraft Inc. | PA-28R-180 | Airworthiness Directives; The New Piper Aircraft, Inc. PA-24, PA-28R, PA-30, PA-32R, PA-34, and PA-39 Series Airplanes |
| aircraft | Piper Aircraft Inc. | PA-28R-200 | Airworthiness Directives; The New Piper Aircraft, Inc. PA-24, PA-28R, PA-30, PA-32R, PA-34, and PA-39 Series Airplanes |
| aircraft | Piper Aircraft Inc. | PA-28R-201 | Airworthiness Directives; The New Piper Aircraft, Inc. PA-24, PA-28R, PA-30, PA-32R, PA-34, and PA-39 Series Airplanes |
| aircraft | Piper Aircraft Inc. | PA-28R-201T | Airworthiness Directives; The New Piper Aircraft, Inc. PA-24, PA-28R, PA-30, PA-32R, PA-34, and PA-39 Series Airplanes |
| aircraft | Piper Aircraft Inc. | PA-30 | Airworthiness Directives; The New Piper Aircraft, Inc. PA-24, PA-28R, PA-30, PA-32R, PA-34, and PA-39 Series Airplanes |
| aircraft | Piper Aircraft Inc. | PA-32R-300 | Airworthiness Directives; The New Piper Aircraft, Inc. PA-24, PA-28R, PA-30, PA-32R, PA-34, and PA-39 Series Airplanes |
Unsafe Condition
Main landing gear collapse caused by main gear sidebrace stud cracks, which could result in loss of control of the airplane during landing operations.
AI-generated summary from the source AD text. Verify against the official source before acting.
Required Actions
Inspect both left and right main gear sidebrace studs for cracks using Type I liquid penetrant or magnetic particle inspection methods. Replace any cracked stud with an FAA-approved serviceable part and accomplish one of the specified actions in the AD. Request alternative methods of compliance for modified airplanes.
AI-generated summary from the source AD text. Verify against the official source before acting.
Compliance Time
Within the next 100 hours time-in-service after the effective date of this AD; or, if the main gear sidebrace stud has already been inspected or replaced, within 500 hours TIS (for PA-28R, PA-32R, PA-34 models) or 1,000 hours TIS (for PA-24, PA-30, PA-39 models) after the last inspection or replacement; whichever occurs later.
AI-generated summary from the source AD text. Verify against the official source before acting.
Source: Official FAA Source ↗
Retrieved: Apr 8, 2026
Rights: U.S. Government Public Domain
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