Results
2018-19-08: We are adopting a new airworthiness directive (AD) for Leonardo S.p.A. (Leonardo) Model AW189 helicopters. This AD requires inspecting the tail gearbox (TGB) fitting for a crack. This AD was prompted by a report of a crack on a TGB fitting that was found during a scheduled inspection. The actions of this AD are intended to prevent an unsafe condition on these products.
2006-20-12: The FAA is adopting a new airworthiness directive (AD) for certain McDonnell Douglas Model 717-200 airplanes. This AD requires replacing the lightning critical clamp bases of the fuel tank vent system with improved clamp bases; and checking the electrical bond of the modified self-bonding mounting clamps and corrective action if necessary. This AD results from an investigation that revealed the aluminum foil strip on the nylon base of the ground clamps can fracture or separate from the base. We are issuing this AD to ensure that the fuel pipes are properly bonded to the airplane structure. Improper bonding could prevent electrical energy from a lightning strike from dissipating to the airplane structure, which could result in a fuel tank explosion.
2000-10-15: This amendment supersedes two existing airworthiness directives (AD), applicable to certain Airbus Model A320 series airplanes, that currently require modification of the rear spar web of the wing and cold expansion of certain attachment holes for the forward pintle fitting and certain holes at the actuating cylinder anchorage of the main landing gear (MLG). This amendment adds a requirement for repetitive inspections to detect fatigue cracking in certain areas of the rear spar of the wing, and corrective action, if necessary. This amendment also provides for optional terminating action for the requirements of this AD. This amendment is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified by this AD are intended to detect and correct fatigue cracking, which may lead to reduced structural integrity of the wing and the MLG.
2006-11-05: The FAA is superseding an existing airworthiness directive (AD) for Rolls-Royce plc (RR) RB211-22B series, RB211-524B, -524C2, - 524D4, -524G2, -524G3, and -524H series, and RB211-535C and -535E series turbofan engines with high pressure compressor (HPC) stage 3 disc assemblies, part numbers (P/Ns) LK46210, LK58278, LK67634, LK76036, UL11706, UL15358, UL22577, UL22578, and UL24738 installed. This AD requires removing from service certain disc assemblies before they reach their full published life if not modified with anticorrosion protection. This AD results from the manufacturer's reassessment of the corrosion risk on HPC stage 3 disc assemblies that have not yet been modified with sufficient application of anticorrosion protection. We are issuing this AD to prevent corrosion-induced uncontained disc failure, resulting in damage to the airplane. The Director of the Federal Register previously approved the incorporation by reference of certain publications listed in the regulations as of February 24, 2004 (69 FR 2661, January 20, 2004).
2021-10-27: The FAA is adopting a new airworthiness directive (AD) for all BAE Systems (Operations) Limited Model BAe 146 and Model Avro 146-RJ series airplanes. This AD was prompted by a report indicating that during a routine battery capacity check on the emergency light power units, the printed circuit boards (PCBs) for certain power units were found to show signs of burning. This AD requires replacing each Honeywell emergency light power unit having a certain part number with a serviceable emergency light power unit. The FAA is issuing this AD to address the unsafe condition on these products.
2021-07-09: The FAA is superseding Airworthiness Directive (AD) 2007-07- 03, which applied to certain The Boeing Company Model 747-100, 747- 100B, 747-100B SUD, 747-200B, 747-200C, 747-200F, 747-300, 747-400, 747-400D, 747-400F, 747SR, and 747SP series airplanes. AD 2007-07-03 required repetitive tests to detect hot air leaking from the trim air diffuser ducts or sidewall riser duct assemblies (collectively referred to as TADDs), related investigative actions, and corrective actions if necessary. AD 2007-07-03 also provided an optional terminating action for the repetitive tests. This AD requires repetitive inspections of all TADD material for damage and applicable on-condition actions. This AD was prompted by reports that high temperature composite material TADDs installed as specified in AD 2007-07-03 have also failed. The FAA is issuing this AD to address the unsafe condition on these products.
2018-18-21: We are adopting a new airworthiness directive (AD) for all Airbus SAS Model A300 B4-600, B4-600R, and F4-600R series airplanes, and Model A300 C4-605R Variant F airplanes (collectively called Model A300-600 series airplanes), and Model A310 series airplanes. This AD was prompted by a determination that new or more restrictive maintenance requirements and airworthiness limitations are necessary. This AD requires revising the maintenance or inspection program, as applicable, to incorporate new or more restrictive maintenance requirements and airworthiness limitations. We are issuing this AD to address the unsafe condition on these products.
86-03-04: 86-03-04 FOKKER B.V.: Amendment 39-5220. Applies to Model F27 airplanes, certificated in any category, serial numbers 10102 to 10642 inclusive, and 10644. Compliance required within 60 days after the effective date of this AD, unless already accomplished: A. To prevent unselected flap extension, isolate the prestall warning power supply wires from the flap down limit switch in accordance with Fokker Service Bulletin F27/34-52, dated March 23, 1983. B. Alternate means of compliance which provide an acceptable level of safety may be used when approved by the Manager, Standardization Branch, ANM-113, FAA, Northwest Mountain Region. C. Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes to a base for the accomplishment of inspections and/or modifications required by this AD. All persons affected by this directive who have not already received the appropriate service documents from the manufacturer may obtain copies uponrequest to the Manager, Maintenance and Engineering, Fokker B.V., Product Support, P.O. Box 7600, 11172J Schiphol Oost, The Netherlands. These documents may be examined at the FAA, Northwest Mountain Region, 17900 Pacific Highway South, Seattle, Washington, or the Seattle Aircraft Certification Office, 9010 East Marginal Way South, Seattle, Washington. This amendment becomes effective February 28, 1986.
2000-10-05: This amendment adopts a new airworthiness directive (AD) that applies to Eurocopter France Model SE.3160, SA.316B, SA.316C, SA.319B, SA330F, SA330G, SA330J, SA341G, and SA342J helicopters. This AD requires inspecting each inflation head and union nut on certain emergency flotation gear nitrogen cylinders and replacing each cracked inflation head with an airworthy inflation head. This amendment is prompted by the discovery of cracked inflation heads during routine maintenance inspections of emergency flotation systems. The actions specified by this AD are intended to prevent an emergency flotation gear nitrogen cylinder from exploding with resultant high velocity shrapnel, which could cause airframe damage or personal injury and subsequent loss of control of the helicopter.
2000-10-11: This amendment adopts a new airworthiness directive (AD), applicable to certain Gulfstream Model G-159 series airplanes, that requires an inspection to determine the type of pneumatic deicing boots, and an Airplane Flight Manual (AFM) revision only for those airplanes equipped with "modern" boots. This amendment is prompted by reports of inflight incidents and an accident that occurred in icing conditions where the airframe pneumatic deicing boots were not activated. The actions specified by this AD are intended to ensure that flightcrews activate the pneumatic wing and tail deicing boots at the first signs of ice accumulation. This action will prevent reduced controllability of the aircraft due to adverse aerodynamic effects of ice adhering to the airplane prior to the first deicing cycle.