Results
2015-03-02: We are adopting a new airworthiness directive (AD) for certain Airbus Model A319-115, A319-133, A320-214, A320-232, and A320-233 airplanes. This AD requires repetitive detailed inspections of the outboard main landing gear (MLG) support rib lower flange fasteners for discrepancies, and corrective actions if necessary. This AD was prompted by reports of failure of certain fasteners on the MLG support rib lower flange. We are issuing this AD to detect and correct discrepancies of the fasteners at the outboard MLG support rib lower flange, which could result in an airplane not meeting its maximum loads expected in service. This condition could result in structural failure.
2014-12-11 R1: We are revising Airworthiness Directive (AD) 2014-12-11 for Sikorsky Aircraft Corporation (Sikorsky) Model S-92A helicopters. AD 2014-12-11 required revising the Rotorcraft Flight Manual (RFM) to include the appropriate operating limitations for performing Class D external load-combination operations. As published, AD 2014-12-11 referenced an incorrect date for Revision No. 12 of Sikorsky RFM SA S92A-RFM-003, Part 1. This AD corrects the error while retaining the requirements of AD 2014-12-11. These actions are intended to require appropriate operating limitations to allow operators to perform Class D external load-combination operations, including human external cargo, in this model helicopter that now meets the Category A performance standard.
59-25-06: 59-25-06 MOONEY: Applies to M-20A Aircraft Serial Numbers 1201 Through 1500. Compliance required not later than December 30, 1959. In order to minimize the possibility of icing of the induction system alternate air source, relocate the carburetor alternate air source to a more sheltered location and omit the screen covering this opening. (a) Remove the engine side cowls and the landing light. (b) Disconnect air hose P/N 6064-19 from present alternate air inlet. Remove screen and air inlet and patch hole. (c) Cut hole in landing light housing in the upper inboard quadrant to match hose connecting assembly P/N 6354. (d) Position P/N 6354 inlet on outer side of light housing to match hole cut per item (c). Self-locking nuts and bolts should be used to attach P/N 6354 to landing light housing, in lieu of Tinnerman fasteners furnished with kit. (e) Attach hose P/N 6064-19 to P/N 6354 with existing clamp and reinstall light and cowling. (Mooney Service Letter 20-50covers this same alteration.)
2025-04-14: The FAA is adopting a new airworthiness directive (AD) for certain Schempp-Hirth Flugzeugbau GmbH Model Duo Discus and Duo Discus T gliders. This AD was prompted by reports of gliders' canopies opening during air tow. This AD requires modifying the canopy locking mechanism. The FAA is issuing this AD to address the unsafe condition on these products.
2015-02-19: We are superseding Airworthiness Directive (AD) 95-24-04 for all Airbus Model A300 series airplanes; Model A300 B4-600, B4-600R, and F4-600R series airplanes; and Model A300 C4-605R Variant F airplanes. AD 95-24-04 required inspections to detect cracks at the aft spar web of the wings, and repair if necessary. This new AD reduces certain compliance times, and expands the applicability. This AD was prompted by a determination that the inspection threshold and interval must be reduced to allow timely detection of cracks and accomplishment of applicable repairs, because of cracking in the rear spar web of the wings between certain ribs due to fatigue-related high shear stress. We are issuing this AD to detect and correct fatigue-related cracking, which could result in reduced structural integrity of the wing.
2015-02-20: We are superseding airworthiness directive (AD) 2013-15-10 that applies to certain Rolls-Royce plc (RR) RB211 turbofan engines. AD 2013-15-10 required inspecting the intermediate-pressure compressor (IPC) rotor shaft rear balance land for cracks. This AD requires inspecting the IPC rotor shaft rear balance land for cracks, eliminates a terminating action, expands one inspection, and eliminates certain other inspections. We are issuing this AD to detect cracking on the IPC rotor shaft rear balance land, which could lead to uncontained engine failure and damage to the airplane.
2015-02-26: We are superseding Airworthiness Directive (AD) 2013-24-13 for certain The Boeing Company Model 737-100, -200, -200C, -300, \n\n((Page 5916)) \n\n-400, -500, -600, -700, -700C, -800, and -900 series airplanes. AD 2013-24-13 required replacing the pivot link assembly for certain airplanes, replacing the seat track link assemblies or modifying the existing seat track link assembly for certain airplanes, or modifying the existing seat track link assembly fastener for certain other airplanes. AD 2013-24-13 also required inspecting, changing, or repairing the seat track link assembly for certain other airplanes. Since we issued AD 2013-24-13, a certain paragraph reference in that AD was found to be mis-identified; this AD corrects this paragraph reference. We are issuing this AD to prevent seat detachment in an emergency landing, which could cause injury to occupants of the passenger compartment and affect emergency egress.
2015-02-07: We are adopting a new airworthiness directive (AD) for certain serial number (S/N) Lycoming Engines reciprocating engines. This AD was prompted by propeller governor shaft set screws coming loose due to improper installation. We are issuing this AD to prevent the propeller governor shaft set screw from coming loose, causing damage to the engine and damage to the airplane.
2015-02-23: We are adopting a new airworthiness directive (AD) for certain Bombardier, Inc. Model CL-600-1A11 (CL-600), CL-600-2A12 (CL-601), and CL-600-2B16 (CL-601-3A, and CL-601-3R Variants) airplanes. This AD requires repetitive inspections for fractured or incorrectly oriented fasteners on the inboard flap hinge-box forward fittings on both wings, and replacement of all fasteners, if necessary. This AD was prompted by several reports of incorrectly oriented and fractured fasteners found on the inboard flap hinge-box forward fitting at wing station (WS) 76.50. We are issuing this AD to detect and correct incorrectly oriented or fractured fasteners, which could result in detachment of the flap hinge-box and the flap surface, and consequent reduced controllability of the airplane.
2015-02-22: We are superseding airworthiness directive (AD) 2012-14-06 for certain Rolls-Royce Corporation (RRC) 250-C20, -C20B, and -C20R/2 turboshaft engines. AD 2012-14-06 required a one-time visual inspection and fluorescent-penetrant inspection (FPI) on certain 3rd-stage and 4th-stage turbine wheels for cracks in the turbine blades. This new AD replaces the one-time visual inspection and FPI with repetitive visual inspections and FPIs. This AD also adds certain engine models to the applicability. This AD was prompted by the determination that the one- time inspections required by AD 2012-14-06 should be changed to repetitive inspections. We are issuing this AD to prevent failure of 3rd-stage and 4th-stage turbine wheel blades, which could cause engine failure and damage to the aircraft.