Results
97-02-07: This amendment adopts a new airworthiness directive (AD), applicable to Airbus Model A300-600 and Model A310 series airplanes, that requires testing to verify if the smoke detection system can detect smoke within 60 seconds; and cleaning the installation and duct, if necessary. It also requires operators to submit a report of the test findings to the manufacturer. This amendment is prompted by a report that, during testing of the smoke detection system on in-service airplanes, the system failed to detect smoke within 60 seconds due to dust accumulation in the extraction ducts. The actions specified by this AD are intended to ensure that dust accumulation does not reduce the effectiveness of the smoke detection system and, consequently, lead to undetected smoke or fire in the lavatory of the airplane.
96-09-02: This amendment supersedes two existing airworthiness directives (AD), that are applicable to Airbus Model A310 and A300-600 series airplanes. One AD currently requires repetitive operational tests of feel and limitation computers (FLC) 1 and 2; the other AD requires replacement of certain FLC's on Model A300-600 series airplanes. Those AD's were prompted by reports indicating that the elevator control operated with stiffness. The actions specified by those AD's are intended to prevent stiff operation of the elevator control and undetected loss of rudder travel limitation function, which could adversely affect the controllability of the airplane. This new amendment requires installation of new FLC's, which terminates the currently required repetitive operational tests. This amendment also revises the applicability of the rule to delete airplanes on which these new FLC's have been installed previously.
96-09-07: This amendment supersedes an existing airworthiness directive (AD) that is applicable to Boeing Model 757 series airplanes equipped with certain Abex spoiler actuator electro-hydraulic servo valves (EHSV) installed in certain spoiler actuators. The existing AD currently requires a one- time inspection of the spoiler actuator to determine if a suspect EHSV is incorrectly installed, and replacement of the EHSV, if necessary. That amendment was prompted by reports that a bias spring in the EHSV of certain spoiler actuators was found to be incorrectly installed. The actions specified by that AD are intended to prevent a significant control upset of the airplane as a result of problems associated with an incorrectly installed EHSV in the spoiler actuator assembly. This amendment adds additional suspect EHSV's that require inspection; it also corrects the actuator manufacturer's name and corrects the serial number of one EHSV.
2021-05-01: The FAA is adopting a new airworthiness directive (AD) for all Airbus Helicopters Model SA330J helicopters. This AD was prompted by report of failure of a second stage planet gear of the main gear box (MGB). This AD requires replacement of the MGB particle detector assembly with an improved, elongated MGB particle detector assembly, 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.
95-23-08: This amendment adopts a new airworthiness directive (AD), applicable to certain Avro Model BAe 146 series airplanes. This action requires inspections to detect cracking and damage of the fastener holes in the butt strap at rib 2 at the lower surface of the right-hand wing; repair of discrepancies; and replacement of the fastener bolts. This amendment is prompted by a report that certain wings were manufactured with a reduction in the amount of edge margin between the fastener hole centers and the edge of the butt strap; this condition can result in a decrease in the long-term damage tolerance residual strength of the wing. The actions specified in this AD are intended to prevent cracking and other problems associated with a such decrease in the long-term damage tolerance residual strength of the wing.
96-01-07: This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A330 and A340 series airplanes. This action requires a one-time inspection to verify that the attachment screws at a pressure switch located on the trim tank fuel transfer line are properly torqued, and that lockwires are installed. This amendment is prompted by reports of loose screws and missing lockwires at this attachment. The actions specified in this AD are intended to prevent loose or missing screws, which could allow fuel to leak from the pressure switch connection; if a leak were to occur during flight with a full trim tank, there would be no warning indication to the flight crew, and the airplane may not have enough fuel to complete the flight safely.
96-07-15: This amendment supersedes an existing airworthiness directive (AD), applicable to certain McDonnell Douglas Model DC-9-80 series airplanes and Model MD-88 airplanes, that currently requires an inspection to detect chafing of or damage to the wire bundle in the overhead switch panel of the cockpit, application of spiral wrap to the wire bundle, and corrective actions, if necessary. That AD was prompted by reports of chafed and shorted wires that resulted in smoke emanating from the overhead switch panel of the cockpit. This amendment expands the applicability of the rule to include certain Model DC-9 and MD-90-30 series airplanes, and C-9 (military) series airplanes. This amendment also adds a requirement to reroute the wire bundle to preclude chafing and damage. The actions specified by this AD are intended to prevent the potential for fire and uncontrolled smoke throughout the cockpit as a result of chafing and shorting in the electrical wire bundles.
2009-04-04: The FAA is adopting a new airworthiness directive (AD) for certain Cessna Aircraft Company (Cessna) Models 401, 401A, 401B, 402, 402A, and 402B airplanes. This AD requires an inspection of the auxiliary wing spar near the location where the main landing gear trunnion is mounted for cracks; immediate replacement if cracks of 0.5 inch or more are found; repetitive inspections with replacement at a later time as long as cracks of less than 0.5 inch are found; and a report to the FAA and Cessna if any cracks are found. This AD results from several reports of fatigue cracking on the affected airplanes in the auxiliary wing spar. We are issuing this AD to detect and correct such cracks, which, if not corrected, could result in failure of the wing auxiliary spar web and cause landing gear collapse during normal landing. This could lead to loss of control and passenger injury.
2021-05-05: The FAA is superseding Airworthiness Directive (AD) 2016-23- 05, which applied to certain Airbus Helicopters Model SA-365N1, AS- 365N2, AS 365 N3, SA-366G1, EC 155B, and EC155B1 helicopters. AD 2016- 23-05 required repetitive checks of the oil level of the tail rotor gearbox and, if necessary, filling the oil to the maximum level; and replacement of a certain control rod double bearing (bearing) with a new bearing. This AD retains the requirements of AD 2016-23-05 and also requires modifying the helicopter by replacing the tail gearbox (TGB) control shaft guide bushes; repetitive inspections of the TGB magnetic plug and corrective actions if necessary; repetitive replacements of the bearing; and modifying the helicopter by replacing the TGB; as specified in a European Aviation Safety Agency (now European Union Aviation Safety Agency) (EASA) AD, which is incorporated by reference. This AD also adds helicopters to the applicability. This AD was prompted by reports of occurrencesof loss of yaw control due to failure of the TGB bearing. The FAA is issuing this AD to address the unsafe condition on these products.
98-08-02: This amendment adopts a new airworthiness directive (AD), applicable to all Airbus Model A300-600 series airplanes, that requires repetitive replacement of the universal joints and steady bearings of the flap transmission system with new parts at regular intervals, or overhaul. This amendment is prompted by a report of a malfunction of a universal joint in the flap transmission system on one wing due to fatigue failure. The actions specified by this AD are intended to ensure replacement or overhaul of certain universal joints and bearings of the transmission system when they have reached their maximum life limit. Failure of universal joints and bearings could lead to an asymmetric condition of the flaps, which could adversely affect controllability of the airplane.