EASA SIB CE-14-07: [Correction] Piper PA-31 Series — Main Wing Spar Lower Cap Cracks

What to do

Operators of Piper PA-31, PA-31-300, PA-31-325, and PA-31-350 airplanes should inspect the wing main spar lower cap at specified intervals: initially during or within 250 flight hours after compliance with AD 98-09-25, then repetitively every 6,000 hours for PA-31, PA-31-300, PA-31-325, and every 13,000 hours for PA-31-350. Use eddy current inspection methods as detailed in DOT/FAA/AR-07/64. Repair or replace any damaged components and report findings to the FAA via Malfunction/Defect or Service Difficulty Reports.

Summary

The FAA Special Airworthiness Information Bulletin SAIB: CE-14-07 addresses cracking found in the main wing spar lower cap of Piper Aircraft Models PA-31, PA-31-300, PA-31-325, and PA-31-350. It provides inspection guidance for the wing main spar lower cap at the centerline spar splice plate to detect fatigue and stress corrosion cracks. This bulletin is informational and does not mandate regulatory action.

What changed

This corrected bulletin updates the labels in Figures 2 and 3 to accurately identify the damage locations on the wing spar lower cap. It also clarifies inspection recommendations and methods for affected Piper PA-31 series airplanes. No new mandatory requirements or Airworthiness Directives are introduced.

Why it matters

This information is critical for operators and maintenance personnel to identify potential fatigue and stress corrosion cracks in the wing spar lower cap, which could affect structural integrity. Early detection through recommended inspections helps maintain aircraft safety and prevents costly repairs or failures. Compliance teams benefit from clear guidance on inspection intervals and methods aligned with existing AD 98-09-25.

What to do

Summary

What changed

Why it matters

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