Commonwealth legislation

AD/CESSNA 337/22 Amdt 3 - Wing Front and Rear Spars - Inspection

In ForceCTH

Jurisdiction

Commonwealth

Collection

legislative instrument

Plain English Summary

4/10 complexity

Instructs owners/operators of specified Cessna 337-series aeroplanes (listed by model and serial number) to inspect wing front and rear spars for cracking using the Cessna SL ME78‑2 Supplement No.1 eddy‑current procedure, with prescribed test‑block and sensitivity settings. Owners bear inspection and repair costs; the Civil Aviation Safety Authority sets timing and allows a 1,000‑hour/100‑hour reduction for aircraft fitted with the Robertson STC. The requirement targets early detection of fatigue cracks to protect structural integrity.

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Current sections

Direct links to the current provisions in AD/CESSNA 337/22 Amdt 3 - Wing Front and Rear Spars - Inspection.

Cessna 337 Series Aeroplanes

AD/CESSNA 337/22 Amdt 3	Wing Front and RearSpars - Inspection	10/2005

Applicability:	Models 337, 337A, 337B, T337B, 337C, T337C, 337D and T337D with the following serial numbers 337-0001 through 337-1193; andModels 337E, T337E, 337F, T337F, 337G, 337H and T337H with the following serial numbers 33701194 through 33701852; andModels T337G and P337H with the following serial numbers P3370001 through P3370313.
Requirement:	Inspect the front and rear spars for cracking in accordance with Cessna SL ME78-2 Supplement No. 1 except that in connection with the front spar inspection the eddy current test sensitivity shall be established so that a 10% full scale meter deflection is obtained from a slot .030" + .003" deep, .060" + .003" long and .010" maximum width, machined in the wall of a 3/16" diameter hole in an aluminium alloy test block.Note 1: FAA AD 78-09-05 also refers.Note 2: A suitable test block is Nortec Part No. TB-12.Note 3: Scoring of bolt holes can cause spurious eddy current indications of cracking and may be the cause of future fatigue crack initiations. Great care must therefore be taken when removing the subject bolts.
Compliance:	Inspect both the front and rear spars in accordance with the times specified for the rear spar in “Action Required” Section of Cessna SL ME78-2 Supplement No. 1 except that for aircraft incorporating Robertson Aircraft Corporation Modification to United States STC 1627 WE a reduction of 1000 hours in the inspection threshold and 100 hours in inspection intervals shall apply. This exception is subject to change should fatigue substantiating data on the Robertson conversion be supplied to the Authority.
	This Amendment becomes effective on 29 September 2005.

Background:	Amendment 2 was issued to clarify the eddy current test block specifications.This amendment is issued to clearly define which serial numbered aircraft are affected by this AD.

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David Villiers
Delegate of the Civil Aviation Safety Authority

8 August 2005

AD/CESSNA 337/22 Amdt 3

Wing Front and RearSpars - Inspection

Wing Front and Rear

Spars - Inspection

10/2005

Source text

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

Cessna 337 Series Aeroplanes Cessna 337 Series Aeroplanes

Cessna 337 Series Aeroplanes

AD/CESSNA 337/22 Amdt 3	Wing Front and RearSpars - Inspection	10/2005

Applicability:	Models 337, 337A, 337B, T337B, 337C, T337C, 337D and T337D with the following serial numbers 337-0001 through 337-1193; andModels 337E, T337E, 337F, T337F, 337G, 337H and T337H with the following serial numbers 33701194 through 33701852; andModels T337G and P337H with the following serial numbers P3370001 through P3370313.
Requirement:	Inspect the front and rear spars for cracking in accordance with Cessna SL ME78-2 Supplement No. 1 except that in connection with the front spar inspection the eddy current test sensitivity shall be established so that a 10% full scale meter deflection is obtained from a slot .030" + .003" deep, .060" + .003" long and .010" maximum width, machined in the wall of a 3/16" diameter hole in an aluminium alloy test block.Note 1: FAA AD 78-09-05 also refers.Note 2: A suitable test block is Nortec Part No. TB-12.Note 3: Scoring of bolt holes can cause spurious eddy current indications of cracking and may be the cause of future fatigue crack initiations. Great care must therefore be taken when removing the subject bolts.
Compliance:	Inspect both the front and rear spars in accordance with the times specified for the rear spar in “Action Required” Section of Cessna SL ME78-2 Supplement No. 1 except that for aircraft incorporating Robertson Aircraft Corporation Modification to United States STC 1627 WE a reduction of 1000 hours in the inspection threshold and 100 hours in inspection intervals shall apply. This exception is subject to change should fatigue substantiating data on the Robertson conversion be supplied to the Authority.
	This Amendment becomes effective on 29 September 2005.

Background:	Amendment 2 was issued to clarify the eddy current test block specifications.This amendment is issued to clearly define which serial numbered aircraft are affected by this AD.

David Villiers
Delegate of the Civil Aviation Safety Authority

8 August 2005

AD/CESSNA 337/22 Amdt 3 - Wing Front and Rear Spars - Inspection

Plain English Summary

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Current sections

Cessna 337 Series Aeroplanes

Cessna 337 Series Aeroplanes