Commonwealth legislation

AD/CESSNA 320/30 Amdt 1 - Wing Front Spar Lower Attachment Fittings

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Commonwealth

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legislative instrument

Plain English Summary

2/10 complexity

This airworthiness directive requires operators of all Cessna 320 series aeroplanes to remove the wing-to-carry‑through fairing and visually inspect the wing front spar lower attachment fittings (P/N 0822550) for cracks and surface pitting, including inspections from inside the wheel well; primer need not be removed. Operators must comply before the fitting exceeds 5,000 hours component time or by the next Maintenance Release after 15 June 1989, and then at each scheduled inspection. Operators bear inspection and any corrective costs; CASA enforces compliance.

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AD/CESSNA 320/30 Amdt 1 - Wing Front Spar Lower Attachment Fittings

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

SCHEDULE OF AIRWORTHINESS DIRECTIVES

View image in the official source Cessna 320 Series Aeroplanes

AD/CESSNA 320/30

Amdt 1

Applicability: All models.

Wing Front Spar Lower Attachment Fittings 6/89

Requirement: 1. Remove the fairing between the wing and carry-thru and gain access to the wing front spar lower attachment fittings P/N 0822550.

2. Visually inspect the upper and lower edges of the lug of each wing fitting, looking for cracks as shown in the figure below.

3. From inside the wheel well, visually inspect each visible wing fitting for cracks and surface pitting in the area shown in the figure.

Note: It is not necessary to remove the primer for any of the above inspections.

View image in the official source

Wing Fitting Showing Typical Cracking

Note: Fitting Shown removed from aircraft for clarity

Compliance: Before exceeding 5000 hours component time in service or before the issue of the next Maintenance Release after 15 June 1989, whichever is the later. Thereafter, reinspect at each scheduled inspection for issue of a new Maintenance Release.

Background: Fatigue cracking has been discovered in the wing fitting from an Australian-registered Cessna 310R with 6500 hours time in service. No abnormality could be found in the fitting or the aircraft’s history. Since then stress corrosion cracking has been found in a similar wing fitting in a Cessna 402C with 6400 hours time in service.

There is insufficient evidence to regard either of these as isolated occurrences: either or both may be expected to occur at a later time elsewhere in the fleet of Cessna twins which use the same generic wing fitting. A simple repetitive visual inspection has therefore been introduced.

Source text

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