Results
2006-01-11 R1: This document clarifies the intent of AD 2006-01-11, which was published in the Federal Register on January 12, 2006 (71 FR 1941). AD 2006-01-11 applies to Cessna Models 208 and 208B airplanes and requires the installation of a pilot assist handle and deicing boots on the cargo pod and landing gear fairings; and the incorporation of changes to the Pilot's Operating Handbook (POH) and FAA-Approved Airplane Flight Manual (AFM). The compliance time for the AFM/POH change currently reads "prior to further flight'' after the installation of the pilot assist handle, which is required within 125 days after the effective date. The AFM/POH change is related to operation in ground icing conditions and should not be attributed to the pilot assist handle installation. Therefore, the compliance time should also be within 125 days after the effective date. Additionally, the requirement of installing the accessory kit or installing a placard should only apply to those airplanes equipped witha cargo pod and pneumatic deicing boots. The way it currently is written makes it apply to all airplanes equipped with pneumatic deicing boots. This AD action rewords the compliance time and the wording for the installation or placard requirement to reflect the above concerns.
2009-12-04: We are adopting a new airworthiness directive (AD) for the products listed above. This AD results from mandatory continuing airworthiness information (MCAI) originated by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as: Incidents have been reported on Britten-Norman BN-2 aircraft, where cracks were found in the inner shell of the pitot/static pressure heads. The investigation concluded that these pitot tubes, supplied by Thales Optronics, could be operated outside their voltage specification. On December 15th, 2005, CAA [Civil Aviation Authority] United Kingdom issued AD G-2005-0034 (EASA approval number 2005-6447), later superseded by EASA AD 2006-0143, to require inspections and leak tests on Britten-Norman aircraft. Subsequently, it has been discovered that the same tubes are supplied to EADS-CASA for installation on C-212 aircraft, one for the pilot side and one forthe co-pilot side. So far, EADS-CASA has not received any report of cracked pitot tubes from C-212 operators. This condition, if not corrected, could result in incorrect readings on the pressure instrumentation, e.g., altimeters, vertical speed indicators (rate of climb) and airspeed indicators, potentially leading to navigational errors. * * * * * The unsafe condition could reduce the ability of the flightcrew to maintain the safe flight and landing of the airplane. We are issuing this AD to require actions to correct the unsafe condition on these products.
2003-13-14: This amendment adopts a new airworthiness directive (AD) for the specified Bell Helicopter Textron Canada (BHTC) model helicopters that requires performing a continuity test, temporarily repairing any unairworthy chip detector, and replacing any repaired chip detectors. This amendment is prompted by reports of poor or no continuity between the insert and the chip detector housing on certain chip detectors. The actions specified by this AD are intended to prevent failure of a chip detector indication, loss of a critical component, and subsequent loss of control of the helicopter.
99-23-22 R1: This amendment revises an existing airworthiness directive (AD), applicable to various transport category airplanes equipped with certain Mode "C" transponder(s) with single Gillham code altitude input. That AD currently requires repetitive tests to detect discrepancies of the Mode "C" transponder(s), air data computer, and certain wiring connections; and corrective actions, if necessary. The existing AD is prompted by reports that, during level flight, the Traffic Alert Collision Avoidance System (TCAS II) issued false advisories that directed the flightcrew to change course and either climb or descend. The actions specified by that AD are intended to prevent such false advisories due to inaccurate airplane altitude reporting, which could result in the flightcrew deviating the airplane from its assigned flight path and a possible mid-air collision. This new action revises certain compliance times and limits the applicability of the existing AD.
99-25-14: This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model MD-11 and MD-11F series airplanes, that requires a one-time inspection to determine if metallic transitions are installed on wire harnesses of the tail tank fuel transfer pumps, and to determine if damaged wires are present; and repair, if necessary. This amendment also would require repetitive inspections of the repaired area; and a permanent modification of the wire harnesses if metallic transitions are not installed, which terminates the repetitive inspections. This amendment is prompted by a report of chafing and damage to a wire harness of a tail tank fuel transfer pump. The actions specified by this AD are intended to prevent wire chafing and damage, which could result in an inoperative fuel transfer pump and/or an increased risk of a fire or explosion from a fuel leak.
2008-23-12: We are adopting a new airworthiness directive (AD) for the products listed above. This AD results from mandatory continuing airworthiness information (MCAI) issued by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as: It has been found cases of corrosion at the regions of Wings-to- Fuselage attachments, Vertical Stabilizer to Fuselage attachments, Rib 1 Half wing and Passenger Seat Tracks. Such corrosion may lead to subsequent cracking of the affected parts, compromising the aircraft structural integrity, which may in turn lead to structural failure and/or loss of some control surface. We are issuing this AD to require actions to correct the unsafe condition on these products.
54-15-01: 54-15-01 de HAVILLAND: Applies to All Model DHC-2 (Beaver) Aircraft, Serial Numbers 1 to 680 Inclusive. Compliance required by August 30, 1954. Inspect all rudder, elevator and aileron control cable terminals for damaged threads at the turnbuckle. Most reported defects have concerned the right-hand threads on turnbuckle terminals but all threaded terminals at turnbuckles should be inspected at the following locations: Control Cable Circuit Location Number of turn-Buckles 1. Base of control column. 2 Ailerons 2. Outboard wing inspection panels. 4 Elevators 3. Hatch on underside of rear fuselage. 2 Rudder 4. Rear fuselage interior. 2 Damaged or defective cables must be replaced. If any evidence of defects is found, de Havilland will supply replacement cables. The FAA concurs in this mandatory action by the Canadian Department of Transport. (de Havilland Technical News Sheet Series B, No. 76 dated June 23, 1954, available from de Havilland Aircraft of Canada, Limited, Postal Station "L," Toronto, Canada, covers this same subject.)
2020-17-09: The FAA is adopting a new airworthiness directive (AD) for GA8 Airvan (Pty) Ltd Models GA8 and GA8-TC320 airplanes. This AD results from mandatory continuing airworthiness information (MCAI) issued by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as a design change to the fuselage strut pick up ribs No. 5 and 6 that requires a reduced life limit. The FAA is issuing this AD to require actions to address the unsafe condition on these products.
2020-17-12: The FAA is adopting a new airworthiness directive (AD) for certain Dassault Aviation Model MYSTERE-FALCON 900, FALCON 900EX, FALCON 2000, and FALCON 2000EX airplanes. This AD was prompted by reports of loose or missing nuts on the pilot and co-pilot ventral seat belt attachment points. This AD requires a detailed inspection of certain seat belt attaching point nuts for any loose or missing nuts and replacement, as specified in a European Union Aviation Safety Agency (EASA) AD, which is incorporated by reference. The FAA is issuing this AD to address the unsafe condition on these products.
2020-16-18: The FAA is adopting a new airworthiness directive (AD) for all Airbus SAS Model A310 series airplanes. This AD was prompted by reports of cracking found at certain fuselage frames. This AD requires repetitive inspections for discrepancies of certain locations in and around the fuselage and applicable corrective actions, as specified in a European Union Aviation Safety Agency (EASA) AD, which is incorporated by reference. The FAA is issuing this AD to address the unsafe condition on these products.