AD 84-24-53 R1
Applicability
| Type | Manufacturer | Model | Details |
|---|---|---|---|
| aircraft | Embraer S.A. | EMB-110P1 | Airworthiness Directives; EMBRAER Models EMB-110P1 and EMB-110P2 Airplanes |
| aircraft | Embraer S.A. | EMB-110P2 | Airworthiness Directives; EMBRAER Models EMB-110P1 and EMB-110P2 Airplanes |
Unsafe Condition
Possible structural failure of the empennage assembly due to loose rivets, cracks, excessive wear, corrosion, or structural deformation in components such as the horizontal stabilizer front attachment, fuselage bulkhead 33 area, elevator hinges, trim tab assemblies, and related hardware.
AI-generated summary from the source AD text. Verify against the official source before acting.
Required Actions
Inspect specified empennage components for loose attachments, wear, corrosion, cracks, and deformation; replace loose rivets and repair cracks found during inspections; correct unsatisfactory conditions per maintenance manual; report issues within 24 hours to FAA; use equivalent compliance if approved.
AI-generated summary from the source AD text. Verify against the official source before acting.
Compliance Time
within the next ten (10) hours time-in-service, unless previously accomplished within the last fifty (10) hours time-in-service
AI-generated summary from the source AD text. Verify against the official source before acting.
Affected Aircraft
Embraer S.A. Models EMB-110P1 and EMB-110P2 airplanes certificated in any category.
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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