AD 2024-07-07 Airworthiness Directives; GA 8 Airvan (Pty) Ltd Airplanes

Models named: GA8, 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 GA8-TC320 airplanes, all serial numbers, certificated in any category.

Comply with this AD within the compliance times specified, unless already done.

Do the applicable actions specified in Table 1 to paragraph (g) of this AD at the times in Table 1 to paragraph (g) of this AD, in accordance with the Accomplishment Instructions of GippsAero Service Bulletin SB-GA8-2005-23, Issue 8, dated October 11, 2023 (GippsAero SB-GA8-2005-23, Issue 8). Table 1 to Paragraph ( g ) Paragraphs in Accomplishment Instructions of GippsAero SB-GA8-2005-23, Issue 8 Action Compliance time 12.1, A1, steps 1 and 2, for backing plate inspection, except where Figure 1 in step 1 specifies to remove and discard the vertical bolt, remove the vertical bolt from service Steps 3 through 7, if a backing plate is not installed Inspect for the existence of a backing plate on the forward slide of the cargo door. If a backing plate is not installed, install a backing plate on the forward slide of the cargo door, measure the groove width of the forward slide, and replace the slide if it exceeds 0.145 inch at any point or is cracked or worn beyond limits Inspect within 50 hours time-in-service (TIS) or 2 months after the effective date of this AD, whichever occurs first. Install, measure, and replace before further flight after the inspection. 12.2, A2, steps 1 and 2 for the inspection 12.2, A2, step 3 or 4, and 12.1, A1, steps 2 through 4, for the follow-on inspection and replacement Inspect for wear of the forward slide of the cargo door by inserting a slide gauge or feeler gauge to measure the clearance between the forward slide and the cargo door track. If a gap is found, measure the groove width of the forward slide and replace the slide if the groove width exceeds 0.145 inch at any point or is cracked or worn beyond limits Inspect for wear within 100 hours TIS or 2 months after the effective date of this AD, whichever occurs first, and thereafter at intervals not to exceed 100 hours TIS or 12 months, whichever occurs first after the most recent inspection. Measure the groove width and replace the slide before further flight after each inspection as necessary. 12.3, B1, steps 1 through 6 for the inspections 12.3, B1, steps 2, 3i, and 3ii; 12.4, B2, steps 1 through 5; and 12.5, B3, steps 1 through 12 for the corrective actions Inspect the cargo door mechanism for contact between the operating rod and cargo door handle pivot post, inspect the threaded studs and rod ends at both ends of the operating rod for bending, and inspect the cargo door handle engagement with the catch. Perform all applicable corrective actions Inspect within 50 hours TIS or 2 months after the effective date of this AD, whichever occurs first and thereafter at intervals not to exceed 100 hours TIS or 12 months, whichever occurs first after the most recent inspection. Perform all applicable corrective actions before further flight. 12.6, C, steps 1 through 6 Inspect the cargo door handle to determine if an integrated stop is installed and if an integrated stop is not installed, install a cargo door handle with an integrated stop. Inspect the cargo door handle for beyond normal play and replace the handle bush if the door handle has beyond normal play Within 150 hours TIS or 4 months after the effective date of this AD, whichever occurs first. Perform the installation and replacement, as necessary, before further flight after the inspection. 12.7, D1, steps 1 through 10 for the center rail cargo door inspection and installation 12.8, D2, steps 1 through 2, for any necessary follow-on rework Inspect the center rail of the cargo door to determine if a center rail aft stop is installed and if a center rail aft stop is not installed, install an aft stop before further flight Within 50 hours TIS or 2 months after the effective date of this AD, whichever occurs first.

This AD was prompted by reports of in-flight cargo door separation. The FAA is issuing this AD to detect and correct excessive wear in the forward cargo door slide, which could result in an in-flight separation of the cargo door, with possible loss of control of the airplane.

This AD replaces AD 2010-18-06, Amendment 39-16419 (75 FR 52253, August 25, 2010).