AD 2019-07-08 Airworthiness Directives; GA 8 Airvan (Pty) Ltd Airplanes

Models named: GA8, Model GA8-TC320. Read the applicability below — it usually turns on serial or part numbers too.

This AD applies to GA 8 Airvan (Pty) Ltd Model GA8 and Model GA8-TC320 airplanes, certificated in any category, with a strut or strut fitting installed that has a part number and serial number listed in table 1 of GippsAero Service Bulletin SB-GA8-2017-174, Issue 2, dated May 23, 2018 (GippsAero SB-GA8-2017-174, Issue 2).

Unless already done, do the following actions in paragraphs (f)(1) through (7) of this AD: (1) Within 3 months after May 23, 2019 (the effective date of this AD) or within 100 hours time-in-service (TIS) after May 23, 2019 (the effective date of this AD), whichever occurs first, with the wing struts removed, visually inspect each forward and aft wing strut fitting and fuselage attachment point for cracks, corrosion, and damage. If there is a crack, any corrosion, or any damage, before further flight, do the applicable corrective actions (including checking torque, restoring surface protection, reworking areas with fouling, and replacing any part with a crack, corrosion, or damage). Follow the procedures in Parts C1, C2, and D or E, as applicable, in the Accomplishment Instructions in GippsAero SB-GA8-2017-174, Issue 2. (2) Within 3 months after May 23, 2019 (the effective date of this AD) or within 100 hours TIS after May 23, 2019 (the effective date of this AD), whichever occurs first, and thereafter at intervals not to exceed 100 hours TIS, visually inspect each strut and strut fitting for cracks, corrosion, and damage. If there is a crack, any corrosion, or any damage, before further flight, do the applicable corrective actions (including checking torque, restoring surface protection, and replacing any part with a crack, corrosion, or damage). Follow the procedures in Parts B and D or E, as applicable, in the Accomplishment Instructions of GippsAero SB-GA8-2017-174, Issue 2. (3) Within 1,000 hours TIS after doing the inspections required in paragraph (f)(1) of this AD and thereafter at intervals not to exceed 1,000 hours TIS, with the wing struts installed, visually inspect each forward and aft wing strut, strut fitting, and strut fitting lug hole for cracks, corrosion, and damage. If there is a crack, any corrosion, or any damage, before further flight, do the applicable corrective actions (including additional inspections, replacing hardware, and replacing any part with a crack, corrosion, or damage). Follow the procedures in Parts C3 and D or E, as applicable, in the Accomplishment Instructions of GippsAero SB-GA8-2017-174, Issue 2. (4) To use an eddy current or fluorescent liquid penetrant inspection method instead of a visual inspection for the requirements in paragraph (f)(1) of this AD, the Manager, Small Airplane Standards Branch, FAA must approve your inspection method, and the Manager's approval letter must specifically refer to this AD. Send your approval request to the contact information found in paragraph (g)(1) of this AD. (5) As of May 23, 2019 (the effective date of this AD), remove from service each part on or before exceeding its replacement time listed in Parts D and E of table 3 of GippsAero SB-GA8-2017-174, Issue 2, and replace with an airworthy part by following the procedures in Part D or Part E, as applicable, in the Accomplishment Instructions of GippsAero SB-GA8-2017-174, Issue 2. (6) For each part that has, on May 23, 2019 (the effective date of this AD), exceeded its replacement time listed in Parts D and E of table 3 of GippsAero SB-GA8-2017-174, Issue 2, you may comply with the requirements in paragraph (f)(5) of this AD within 100 hours TIS after May 23, 2019 (the effective date of this AD) or within 12 months after May 23, 2019 (the effective date of this AD), whichever occurs first. (7) Within 24 hours after each inspection required in paragraphs (f)(1) and (2) of this AD, submit a report of the inspection results as specified in the Document Compliance Notice of GippsAero SB-GA8-2017-174, Issue 2, even if no damage is found, to the Civil Aviation Safety Authority (CASA) and GA 8 Airvan (Pty) Ltd. Also include in the report the total hours TIS on the airplane and the type of operation. You may use the contact information found in paragraph (i)(3) of this AD to contact GA 8 Airvan (Pty) Ltd. To contact CASA, use the online CASA Defect Reporting Service at the following internet address: https://drs.casa.gov.au/.

The following provisions also apply to this AD: (1) Alternative Methods of Compliance (AMOCs): The Manager, Small Airplane Standards Branch, FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. Send information to ATTN: Doug Rudolph, Aerospace Engineer, FAA, Small Airplane Standards Branch, 901 Locust, Room 301, Kansas City, Missouri 64106; telephone: (816) 329-4059; fax: (816) 329-4090; email: doug.rudolph@faa.gov. Before using any approved AMOC on any airplane to which the AMOC applies, notify your appropriate principal inspector (PI) in the FAA Flight Standards District Office (FSDO), or lacking a PI, your local FSDO. (2) Contacting the Manufacturer: For any requirement in this AD to obtain corrective actions from a manufacturer, the action must instead be accomplished using a method approved by the Manager, Small Airplane Standards Branch, FAA; or CASA. (3) Reporting Requirements: A federal agency may not conduct or sponsor, and a person is not required to respond to, nor shall a person be subject to a penalty for failure to comply with a collection of information subject to the requirements of the Paperwork Reduction Act unless that collection of information displays a currently valid OMB Control Number. The OMB Control Number for this information collection is 2120-0731. Public reporting for this collection of information is estimated to be approximately 1 hour per response, including the time for reviewing instructions, searching existing data sources, gathering and maintaining the data needed, completing and reviewing the collection of information. All responses to this collection of information are voluntary; the nature and extent of confidentiality to be provided, if any. Send comments regarding this burden estimate or any other aspect of this collection of information, including suggestions for reducing this burden to: Information Collection Clearance Officer, Federal Aviation Administration, 10101 Hillwood Parkway, Fort Worth, TX 76177-1524.

This AD was prompted by mandatory continuing airworthiness information (MCAI) issued by the aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as certain wing strut fittings manufactured with incorrect grain orientation, which has an unknown effect on fatigue-related concerns. We are issuing this AD to detect and address fatigue-related damage to the wing strut fittings, which could lead to failure of the wing with consequent loss of control of the airplane.

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