Results
2016-03-01: We are adopting a new airworthiness directive (AD) for all The Boeing Company Model 737-100, -200, -200C, -300, -400, and -500 series airplanes. This AD was prompted by a report of a crack of the forward leg of the left front spar lower chord and cracks on the lower wing skin at three fastener holes common to the nacelle outboard side load fitting. This AD requires repetitive inspections for cracks on the front spar lower chord, inspar skin, and wing skin, and corrective action if necessary. We are issuing this AD to detect and correct fatigue cracking of the forward leg of the front spar lower chord, inspar skin, and wing skin common to the nacelle outboard side load fitting, which could adversely affect the structural integrity of the wing.
2016-01-10: We are superseding Airworthiness Directive (AD) 2004-20-14, for all Airbus Model A300 B4-2C, B4-103, and B4-203 airplanes; and all Airbus Model A300 B4-600, B4-600R, and F4-600R series airplanes. AD 2004-20-14 required repetitive inspections to detect cracking of the splice fitting at fuselage frame (FR) 47 between stringers 24 and 26 (left- and right-hand sides), and corrective actions if necessary. This new AD reduces the inspection compliance time and repetitive inspection intervals, and adds Airbus Model A300 C4-605R Variant F airplanes to the applicability. This AD was prompted by a determination that the inspection compliance time and repetitive inspection interval must be reduced to allow timely detection of cracks in the splice fitting at fuselage FR 47. We are issuing this AD to detect and correct cracking of the splice fitting at fuselage FR 47; such cracking could result in reduced structural integrity of the airplane.
47-21-21: 47-21-21 REPUBLIC: (Was Service Note 1 of AD-769-2.) Applies to Model RC-3 Aircraft Serial Numbers 5 to 236, Inclusive. Inspection required immediately and periodically as noted below. Inspect two slots at upper end of each tip float strut (P/N 17W23001) very carefully for cracks. Slots are located inside of wing contour, therefore, struts must be removed from wing at upper attachment for proper inspection. If any cracks are present, strut shall be replaced prior to further operation. All struts without relief holes at ends of slots as recommended by manufacturer shall be inspected for cracks at 50-hour intervals. (Republic Seabee Service Bulletin No. 12 covers this same subject.)
47-06-10: 47-06-10 CESSNA: (Was Mandatory Note 6 of AD-768-4.) Applies to 120 and 140 Aircraft Serial Numbers Up to and Including 9669. Compliance required prior to April 1, 1947. Install carry-through bar between the ends of the aileron control chain that is installed at the top of the control "T" to make a continuous loop at this chain installation so that both control wheels operate positively in the same direction. This is necessary to prevent possible locking of aileron system at full throw. (Cessna Service Letter No. 17 dated September 19, 1946, covers this same subject.)
2003-01-01: This amendment supersedes Airworthiness Directive (AD) 2000- 26-16, which applies to certain Raytheon Aircraft Company (Raytheon) Beech Models A36, B36TC, and 58 airplanes. AD 2000-26-16 requires you to inspect for missing rivets on the right hand side of the fuselage and, if necessary, install rivets. AD 2000-26-16 resulted from Raytheon identifying several instances of missing rivets on these airplanes. AD 2000-26-16 incorporated an incorrect listing of serial numbers for the affected model airplanes and omitted certain airplane models from the applicability section of AD 2000-26-16. This AD retains the actions required in AD 2000-26-16 and corrects the applicability section. The actions specified by this AD are intended to detect and correct missing rivets in the right hand fuselage panel assembly in the area above the right wing and below the cabin door threshold. These rivets must be present for the fuselage to carry the ultimate load and prevent critical structural failure with loss of airplane control. DATES: This AD becomes effective on February 27, 2003. The Director of the Federal Register previously approved the incorporation by reference of Raytheon Mandatory Service Bulletin SB 53-3341, Rev. 1, Revised May, 2000, as of February 16, 2001 (66 FR 1253, January 8, 2001). The Director of the Federal Register approved the incorporation by reference of Raytheon Mandatory Service Bulletin SB 53-3341, Rev. 2, Revised October, 2002, as of February 27, 2003.
2015-22-51: We are publishing a new airworthiness directive (AD) for Agusta S.p.A. (Agusta) Model A109A and A109AII helicopters, which was sent previously to all known U.S. owners and operators of these helicopters. This AD requires checking and inspecting each main rotor blade (blade) for a crack and replacing any cracked blade before further flight. This AD is prompted by abnormal vibrations leading to a precautionary landing and a post-flight inspection finding of a crack in a blade. These actions are intended to detect a crack in a blade and prevent failure of a blade and subsequent loss of control of the helicopter.
48-08-02: 48-08-02 AERONCA, CHAMPION AND SILVAIRE: Applies to all Aeronca 11 Series, Champion (Aeronca) 7 Series, and Silvaire (Luscombe) 8 Series Aircraft Equipped with Cleveland Model 6:00 DMB Wheels, Assembly No. C-38500. Compliance required after initial 500 hours of operation and each 100 hours of operation thereafter. Remove the tires and inspect the wheel flanges for fatigue cracks. The wheel should be replaced if cracks are found.
2016-02-02: We are adopting a new airworthiness directive (AD) for all Airbus Model A318-111 and -112 airplanes; Model A319-111, -112, and - 115 airplanes; Model A320-214 [[Page 4170]] airplanes; and Model A321-111, -112, -211, -212, and -213 airplanes. This AD was prompted by reports of cracked cadmium-plated lock nuts that attach the hinge to the fan cowl door. This AD requires inspecting to determine the serial number of each engine fan cowl door, inspecting for cracking of the hinge lock nuts of any affected door, and replacing the lock nuts if necessary. We are issuing this AD to detect and correct cracking of the hinge lock nuts, which could result in separation of the hinge from the fan cowl door, in-flight loss of the door, and consequent damage to the airplane.
2024-25-08: The FAA is adopting a new airworthiness directive (AD) for all The Boeing Company Model 767-200, -300, and -300F airplanes. This AD was prompted by a report of a main landing gear (MLG) collapse event following maintenance where a grinder was operating outside of its input parameters, resulting in possible heat damage to the outer cylinder of the MLG. This AD requires replacing affected outer cylinders. The FAA is issuing this AD to address the unsafe condition on these products.
2024-25-07: The FAA is adopting a new airworthiness directive (AD) for certain General Electric Company (GE) Model GEnx-1B64, GEnx-1B64/P1, GEnx-1B64/P2, GEnx-1B67, GEnx-1B67/P1, GEnx-1B67/P2, GEnx-1B70, GEnx- 1B70/75/P1, GEnx-1B70/75/P2, GEnx-1B70/P1, GEnx-1B70/P2, GEnx-1B70C/P1, GEnx-1B70C/P2, GEnx-1B74/75/P1, GEnx-1B74/75/P2, GEnx-1B76/P2, GEnx- 1B76A/P2, GEnx-2B67, GEnx-2B67B, and GEnx-2B67/P engines. This AD was prompted by a manufacturer evaluation that determined a lower life limit may be necessary for certain stages 6-10 compressor rotor spools than allowed by the engine shop manual (ESM). This AD requires a one- time inspection of the stages 6-10 spools for previously accomplished blend repairs, a one-time inspection of the blend repairs on the stages 6-10 spools for compliance with the updated allowable limits, and replacement if necessary. The FAA is issuing this AD to address the unsafe condition on these products.