Aviat/Pitts Special

Airworthiness Directives; Aviat Aircraft, Inc. Models S-1S, S-1T, S-2, S-2A, S-2S, and S-2B Airplanes

This amendment revises Airworthiness Directive (AD) 96-12-03 R1, which applies to Aviat Aircraft, Inc. (Aviat) Models S-1S, S-1T, S- 2, S-2A, S-2S, and S-2B airplanes that are equipped with aft lower fuselage wing attach fittings incorporating part number (P/N) 76090, P/ N 2-2107-1, or P/N 1-210-102. AD 96-12-03 R1 currently requires repetitively inspecting the aft lower fuselage wing attach fitting on both wings for cracks, and modifying any cracked aft lower fuselage wing attach fitting. Modifying both aft lower fuselage wing attach fittings eliminates the repetitive inspection requirement of AD 96-12- 03. Aviat started incorporating modified aft lower fuselage wing attach fittings on newly manufactured airplanes beginning with serial number 5337, instead of 5349 as referenced in the existing AD. This AD retains the repetitive inspection and possible modification requirements of AD 96-12-03 R1, and will change the applicability accordingly. The actions specified by this AD are intended to prevent possible in-flight separation of the wing from the airplane caused by a cracked fuselage wing attach fitting.

Airworthiness Directives; Aviat Aircraft Inc. Models S-2A, S-2B, and S-2S Airplanes (formerly Pitts Models S-2A, S-2B, and S-2S airplanes)

This amendment supersedes Airworthiness Directive AD 96-09-08 R1, which applies to Aviat Aircraft Inc. (Aviat) Models S-2A, S-2B, and S-2S airplanes (formerly Pitts Models S-2A, S-2B, and S-2S), and currently requires repetitively inspecting the upper longerons just aft of the rear cabane struts for cracks and repairing any cracks. This action retains the same actions as the current AD; lengthens the time interval between repetitive inspections; requires either installing a marked accelerometer in order to continue to perform acrobatic maneuvers and installing a placard that specifies gravity (``g'') force limitations, or installing a placard prohibiting acrobatic maneuvers; and, requires inserting revisions into the Airplane Flight Manual (AFM). This action is the result of reports of cracking in the upper longerons caused by operating the airplane outside of the certificated design limits and the availability of a design modification that, when incorporated, repairs the damaged upper longeron area. The actions specified by this AD are intended to prevent cracking and subsequent failure of the longerons with consequent loss of control of the airplane.

Airworthiness Directives; Aviat Aircraft, Inc. Models S-1S, S-1T, S-2, S-2A, S-2S, and S-2B Airplanes (Formerly Known as Pitts Models S- 1S, S-1T, S-2, S-2A, S-2S, and S-2B Airplanes)

This amendment revises AD 96-12-03, which applies to Aviat Aircraft, Inc. (Aviat) Models S-1S, S-1T, S-2, S-2S, and S-2B airplanes that are equipped with aft lower fuselage wing attach fittings incorporating either part number (P/N) 76090, 2-2107-1, or 1-210-102. That AD currently requires repetitively inspecting the aft lower fuselage wing attach fitting on both wings for cracks, and modifying any cracked aft lower fuselage wing attach fitting. Modifying both aft lower fuselage wing attach fittings eliminates the repetitive inspection requirement of AD 96-12-03. Aviat recently started incorporating modified aft lower fuselage wing attach fittings on newly manufactured airplanes. This AD retains the requirements of AD 96-12- 03, but exempts airplanes that had the modified aft lower fuselage wing attach fittings incorporated at manufacture. The actions specified by this AD are intended to prevent possible in-flight separation of the wing from the airplane caused by a cracked fuselage wing attach fitting.

Airworthiness Directives; Aviat Aircraft, Inc. Models S-1S, S-1T, S-2, S-2A, S-2S, and S-2B Airplanes (Formerly Known as Pitts Models S- 1S, S-1T, S-2, S-2A, S-2S, and S-2B Airplanes)

This amendment adopts a new airworthiness directive (AD) that applies to certain Aviat Aircraft, Inc. (Aviat) Models S-1S, S-1T, S-2, S-2A, S-2S, and S-2B airplanes that are equipped with aft lower fuselage wing attach fittings incorporating either part number (P/N) 76090, 2-2107-1, or 1-210-102. This action requires repetitively inspecting the aft lower fuselage wing attach fitting on both wings for cracks and modifying any cracked aft lower fuselage wing attach fitting. Modifying the aft lower fuselage wing attach fitting on both wings eliminates the repetitive inspection requirement of the AD. Several reports of cracked fuselage wing attach fittings on the affected airplanes prompted this action. The actions specified by this AD are intended to prevent possible in-flight separation of the wing from the airplane caused by a cracked fuselage wing attach fitting.

Airworthiness Directives; Aviat Aircraft, Inc. Models S-1S, S-1T, S-2, S-2A, S-2S, and S-2B Airplanes (Formerly Known as Pitts Models S- 1S, S-1T, S-2, S-2A, S-2S, and S-2B Airplanes)

This amendment adopts a new airworthiness directive (AD) that applies to Aviat Aircraft, Inc. (Aviat) Models S-1S, S-1T, S-2, S-2A, S-2S, and S-2B airplanes that are equipped with a flight control stick with a wall thickness of .035 inch. This action requires repetitively inspecting the flight control stick for cracks, and replacing any cracked flight control stick with one with a wall thickness of .058 inch. An incident on an Aviat Model S-2A airplane where the flight control stick fractured in flight prompted this action. The actions specified by this AD are intended to prevent the inability to maneuver the airplane because of a cracked flight control stick, which, if not detected and corrected, could result in loss of control of the airplane.

Airworthiness Directives; Aviat Aircraft Inc. Models S-2A, S-2B, and S-2S Airplanes (Formerly Pitts Models S-2A, S-2B, and S-2S Airplanes)

This amendment adopts a new airworthiness directive (AD) that is applicable to Aviat Aircraft Inc., Models S-2A, S-2B, and S-2S airplanes (formerly Pitts Models S-2A, S-2B, and S-2S airplanes). This action requires inspecting the longerons aft of the rear cabane struts for cracks, and if cracked, prior to further flight, repairing the cracks. Reports of longeron failure caused by fatigue aft of the rear cabane struts prompted this action. The actions specified by this AD are intended to prevent cracking and subsequent failure of the longerons resulting in possible loss of control of the airplane.