Commonwealth legislation

AD/CHA/22 Amdt 2 - Front Spar Wing Strut Upper Attachment Fitting

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legislative instrument

Plain English Summary

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Requires removal and off-aircraft magnetic particle inspection of front-spar wing strut upper attachment fittings P/N 2‑1976 on 8KCAB (Decathlon) aircraft at set component‑time thresholds and thereafter every 250 hours, and mandates retirement of replacement fittings P/N 3‑1658 before 1500 hours. The AD cites five overseas fatigue‑cracking reports, including an in‑flight failure, as its rationale. Owners/operators bear inspection, re‑protection and replacement costs; aerobatic flight is discouraged until the initial inspection if fittings have exceeded 500 hours.

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AD/CHA/22 Amdt 2 - Front Spar Wing Strut Upper Attachment Fitting

COMMONWEALTH OF AUSTRALIA (Civil Aviation Regulations 1998), PART 39 - 105 CIVIL AVIATION SAFETY AUTHORITY

SCHEDULE OF AIRWORTHINESS DIRECTIVES

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American Champion (Aeronca, Bellanca) Series Aeroplanes

AD/CHA/22

Amdt 2

Front Spar Wing Strut Upper Attachment Fitting 11/90

Applicability: All model 8KCAB aircraft .

Note: Although the Applicability is limited to the 8KCAB, the requirement may in future be extended to other models (particularly the aerobatic 7 series) if subsequent service experience and/or analysis so indicates.

Requirement: 1. For P/N 2-1976 fittings. Remove the left and right front spar wing strut upper attachment fittings P/N 2-1976 from the aircraft and conduct a magnetic particle inspection in accordance with the procedures outlined in CAO 108-8 Issue 1, paying particular attention to the welds which connect the strut attachment bolt hole reinforcement plates to the forward and aft “U” channels.

Note : Ensure that the fitting is re-protected after inspection.

For P/N 3-1658 fittings. Retire P/N 3-1658 fittings from service.

Compliance: For Requirement 1: Prior to the accumulation of 500 hours component time in service or within 50 hours component time in service after 3 September 1990, whichever occurs later, and thereafter at intervals not exceeding 250 hours component time in service.

Note: For aircraft with fittings which have exceeded 500 hours, aerobatic manoeuvres should not be flown until the initial inspection has been carried out.

For Requirement 2: Prior to exceeding 1500 hours component time in service.

Background: There have been five reported overseas occurrences of fatigue cracking emanating from the weld area, including one in-flight failure in P/N 2-1976 fittings on 8KCAB aircraft. This amendment limits the Applicability to the Decathlon, replaces the previous one time fluorescent dye penetrant inspection with a repetitive off-aircraft magnetic particle inspection, and promulgates the recommended 1500 hour life limitation for the replacement fittings P/N 3-1658. FAA AD 90-15-15 and American Champion Aircraft Corporation Service Letter 402 refer.

Source text

Sourced from the Federal Register of Legislation (legislation.gov.au), CC BY 4.0.

1 AD/CHA/22 Amdt 2 - Front Spar Wing Strut Upper Attachment Fitting