Commonwealth legislation

AD/GROB 115/13 - Rear Fuselage Bulkhead

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Commonwealth

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legislative instrument

Plain English Summary

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This Airworthiness Directive requires operators of Grob G115C2 and G115D aircraft to remove under-tail fairings, inspect the rear fuselage bulkhead upper edge for cracking, disbonding or crazing within 50 hours (unless already done), and repeat inspections every 100 hours until an approved repair/modification is fitted. It responds to discovered bulkhead cracks and disbonds that can weaken the tail attachment; compliance creates inspection labour and downtime, possible repair costs, and dependence on Grob or a CAR 35 delegate to approve any design fix.

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AD/GROB 115/13 - Rear Fuselage Bulkhead

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

SCHEDULE OF AIRWORTHINESS DIRECTIVES

View image in the official source
Grob G115 Series Aeroplanes

AD/GROB 115/13 Rear Fuselage Bulkhead 1/99 DM

Applicability: All Grob models G115C2 and G115D.

Requirement: 1. Remove the Antispin strake and fuselage closure fairing from under the horizontal stabiliser to gain access to the rear fuselage bulkhead. See Figure 1.

View image in the official source2. Inspect along the upper edge of the bulkhead, looking for cracking, disbonding and crazing in the shaded areas shown in Figure 2. Using a light and a mirror through the access hole in the bulkhead, similarly inspect the upper edge on the front of the bulkhead.

View image in the official source

Figure 1

Figure 2

Compliance: Unless inspected within the last 50 hours time in service, inspect within 50 hours time in service after the effective date of this AD. Re-inspect every 100 hours time in service, until the whole upper edge of the bulkhead, including its attachment to the fuselage skin, is modified or repaired in accordance with a design approved by Grob or a CAR 35 delegate or authorised person.

This Airworthiness Directive becomes effective on 25 November 1998.

Background: Aircraft have been found with cracks in the bulkhead and disbonding of the flange of the bulkhead from the fuselage skin. Such defects weaken the attachment of the whole tail assembly.

Source text

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

1 AD/GROB 115/13 - Rear Fuselage Bulkhead