Airworthiness Directive · Amendment 39-14944 · Stabilizers
Gippsland Aeronautics Pty. Ltd. Model GA8 Airplanes
Superseded. A later AD replaced this one: AD 2009-05-01. Comply with the one in force.
This AD applies to all Model GA8 airplanes, serial numbers GA8-00-004 and up, certificated in any category.
We are adopting a new airworthiness directive (AD) for the products listed above. This AD results from 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:
Unless already done, do the following actions.
(1) Within the next 10 hours time-in-service (TIS) after March 8, 2007 (the effective date of this AD):
(i) For all aircraft not incorporating CNC machined elevator hinges, inspect and repair as required, the left and right horizontal stabilizer rear pivot attachment installation following instruction “3. Rear Pivot Attachment Inspection,” of Gippsland Aeronautics Mandatory Service Bulletin SB-GA8-2002-02, Issue 4, dated January 4, 2007; and,
(ii) For all aircraft replace the left and right rear attach bolt following instruction “5. Rear Attach Bolt Replacement,” of Gippsland Aeronautics Mandatory Service Bulletin SB-GA8-2002-02, Issue 4, dated January 4, 2007.
(2) Within the next 10 hours TIS after March 8, 2007 (the effective date of this AD); and repetitively thereafter at intervals not to exceed 100 hours TIS or 12 months, whichever occurs first, for all aircraft:
(i) Inspect the horizontal stabilizer externally following instruction “2. External Inspection (Lower flange, Stabilizer rear spar),” of Gippsland Aeronautics Mandatory Service Bulletin SB-GA8-2002-02, Issue 4, dated January 4, 2007; and
(ii) Inspect the horizontal stabilizer internally following instruction “4. Internal Inspection,” of Gippsland Aeronautics Mandatory Service Bulletin SB-GA8-2002-02, Issue 4, dated January 4, 2007.
(3) Before further flight, if during the inspection required by paragraph (f)(2) of this AD any excessive local deflection or movement of the lower skin surrounding the lower pivot attachment, cracking, or working (loose) rivet is found, obtain an FAA-approved repair scheme from the manufacturer and incorporate this repair scheme. Continued operational flight with un-repaired crack damage is not permitted.
Note: This AD differs from the MCAI and/or service information as follows: (1) “Requirement: 1. Daily Inspection (Stabiliser attach bolt)” of the MCAI requires a daily inspection of the stabilizer attach bolt. The daily inspection is not a requirement of this AD. Instead of the daily inspection, we require you to perform, within 10 hours TIS, “Requirement 3. Rear Pivot Attachment Inspection” and “Requirement 5. Rear Attachment Bolt Replacement” of the MCAI. Compliance with requirement 3. and 5. is a terminating action for the daily inspection, and we are requiring these within 10 hours TIS after the effective date of this AD. (2) “Requirement: 2. External Inspection (Lower flange, Stabiliser rear spar)” of the MCAI does not specify any action if excessive local deflection or movement of lower skin, cracking, or working (loose) rivet is found. We require obtaining and incorporating an FAA-approved repair scheme from the manufacturer before further flight. (3) The MCAI does not state if further flight with known cracks is allowed. FAA policy is to not allow further flight with known cracks in critical structure. We require that if any cracks are found when accomplishing the inspection required in paragraph (f)(2) of this AD, you must repair the cracks before further flight.
