Results
2012-17-09: We are adopting a new airworthiness directive (AD) for Eurocopter France Model SA341G helicopters. This AD requires replacing any rotating star with more than 12,000 hours TIS. This AD was prompted by an analysis and tests performed by the manufacturer that indicate that the life limit of the rotating star should be 12,000 hours time- in-service (TIS). The actions of this AD are intended to prevent failure of the rotating star and subsequent loss of control of the helicopter.
2023-16-07: The FAA is adopting a new airworthiness directive (AD) for certain International Aero Engines, LLC (IAE LLC) Model PW1122G-JM, PW1124G1-JM, PW1124G-JM, PW1127G-JM, PW1127G1-JM, PW1127GA-JM, PW1129G- JM, PW1130G-JM, PW1133G-JM, PW1133GA-JM, PW1428G-JM, PW1428GA-JM, PW1428GH-JM, PW1431G-JM, PW1431GA-JM, and PW1431GH-JM engines. This AD was prompted by an updated analysis of an event involving an IAE LLC Model PW1127GA-JM engine, which experienced a high-pressure compressor (HPC) 7th-stage integrally bladed rotor (IBR-7) separation that resulted in an aborted takeoff. This AD requires performing an ultrasonic inspection (USI) of the high-pressure turbine (HPT) 1st- stage hub and HPT 2nd-stage hub for cracks and, depending on the results of the inspections, replacing the HPT 1st-stage hub or HPT 2nd- stage hub. The FAA is issuing this AD to address the unsafe condition on these products.
2000-17-08: This amendment supersedes an existing airworthiness directive (AD) that applies to Eurocopter Deutschland GMBH (ECD) Model BO-105A, BO-105C, BO-105 C-2, BO-105 CB-2, BO-105 CB-4, BO-105S, BO-105 CS-2, BO-105 CBS-2, BO-105 CBS-4, and BO-105LS A-1 helicopters. That AD requires creating a component log card or equivalent record and determining the calendar age and number of flights on each tension-torsion (TT) strap. That AD also requires inspecting and removing, as necessary, certain unairworthy TT straps. This amendment establishes a life limit for certain main rotor TT straps. This amendment is prompted by a need to establish a life limit for certain TT straps because of an accident in which a main rotor blade (blade) separated from an ECD Model MBB-BK 117 helicopter due to fatigue failure of a TT strap. The same part-numbered TT strap is used on the ECD Model BO-105 helicopters. The actions specified by this AD are intended to prevent fatigue failure of the TT strap, loss of a blade, and subsequent loss of control of the helicopter.
2000-17-04: This amendment adopts a new airworthiness directive (AD) that is applicable to certain Boeing Model 737-100, -200, and -200C series airplanes. This action requires repetitive inspections to detect discrepancies in the upper and lower skins of the fuselage lap joint, and repair, if necessary. This action is necessary to detect and correct such discrepancies, which could result in sudden fracture and failure of a lap joint and rapid decompression of the airplane fuselage.
2012-15-13: We are superseding an existing airworthiness directive (AD) for all Model 747-100B SUD, 747-300, 747-400, and 747-400D series airplanes; and Model 747-200B series airplanes having a stretched upper deck. The existing AD currently requires repetitively inspecting for cracking or discrepancies of the fasteners in the tension ties, shear webs, and frames at body stations 1120 through 1220; and related investigative and corrective actions if necessary. That AD requires modifying the frame-to-tension-tie joints at body stations 1120 through 1220 (including related investigative actions and corrective actions if necessary), which provides a terminating action for the repetitive inspections. That AD also requires new repetitive inspections after the modification, corrective actions if necessary, and additional modification requirements at a specified time after the first modification. That AD also removed certain airplanes from the applicability. That AD was prompted by reports of cracked and severed tension ties, broken fasteners, and cracks in the frame, shear web, and shear ties adjacent to tension ties for the upper deck. This AD revises the existing AD by adding repetitive open hole high frequency eddy current (HFEC) inspections for cracking in the forward and aft tension tie channels, and repair if necessary. For certain airplanes, this AD also requires a one-time angle inspection to determine if the angle is installed correctly, and re-installation if necessary; and a one-time open hole HFEC inspection at the fastener locations where the tension tie previously attached to the frame prior to certain modifications, and repair if necessary. This AD also, for the Stage 2 inspections, reduces the initial compliance times for those inspections. We are issuing this AD to detect and correct cracking of the tension ties, shear webs, and frames of the upper deck, which could result in rapid decompression and reduced structural integrity of the airplane.
2023-16-05: The FAA is adopting a new airworthiness directive (AD) for certain De Havilland Aircraft of Canada Limited Model DHC-8-401 and - 402 airplanes. This AD was prompted by reports of the main landing gear (MLG) aft door not opening when using the alternate extension system. This AD requires a one-time inspection of the spring box assembly, repetitive inspections of the cam assembly and alternate release cable assembly, corrective actions if necessary, and a replacement of certain alternate release cable assemblies. In addition, this AD requires certain aircraft maintenance manuals tasks when installing the cam assembly or alternate release cable assembly. This AD also prohibits the installation of affected parts. The FAA is issuing this AD to address the unsafe condition on these products.
78-20-08: 78-20-08 BEECH: Amendment 39-3311. Applies to Model 76 (Serial Numbers ME-1 through ME-62 and ME-66) airplanes. To preclude failure of the rudder and elevator trim tab push rods, prior to further flight: A) If not previously accomplished, replace Beech Part Number 105-520024-5 rudder trim tab push rod with new Beech Part Number 105-520045-9 rudder trim tab push rod and rebalance the rudder control surface, where necessary, in accordance with Beechcraft Liberal Service Letter No. 78-4 dated September 14, 1978, or later approved revisions. B) If not previously accomplished, replace Beech Part Number 105-520024-1 elevator trim tab push rod with new Beech Part Number 105-520048-1 elevator trim tab push rod and rebalance the elevator control surfaces, where necessary, in accordance with Beechcraft Liberal Service Letter No. 78-4 dated September 14, 1978, or later approved revisions. C) Aircraft may not be flown in accordance with FAR 21.197 to a base to accomplish this AD, unless authorized by the Chief, Engineering and Manufacturing Branch, FAA, Central Region. D) Any equivalent method of compliance with this AD must be approved by the Chief, Engineering and Manufacturing Branch, FAA, Central Region. This amendment becomes effective October 12, 1978, to all persons except those to whom it has already been made effective by telegram from the FAA dated September 9, 1978.
2000-16-10: This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model DC-10-10, -15, -30, -30F (KC-10A military), and -40 series airplanes, and Model MD-10-10F and MD-10-30F series airplanes that requires performing repetitive ultrasonic inspections of the attaching bolts on the inboard and outboard support on the inboard and outboard flap assembly to detect failed bolts, or verifying the torque of the attaching bolts on the inboard support on the outboard flap; and follow-on actions. This AD also requires replacing all bolts with bolts made from Inconel, which constitutes terminating action for the repetitive inspection requirements. This amendment is prompted by an in-flight loss of the inboard flap assembly on an airplane during approach for landing. The actions specified by this AD are intended to prevent in-flight loss of inboard and outboard flap assemblies due to failure of H-11 attaching bolts, which could result in reduced controllability of the airplane.
2005-03-07: This amendment adopts a new airworthiness directive (AD) for Bell Helicopter Textron Canada (Bell) Model 407 helicopters that requires creating a component history card or equivalent record for each crosstube assembly, converting accumulated run-on landings to an accumulated Retirement Index Number (RIN) count, and establishing a maximum accumulated RIN for certain crosstube assemblies. This amendment is prompted by fatigue testing, analysis, and evaluation by the manufacturer that determined that run-on landings impose a high stress on landing gear or crosstubes and may cause cracking in the area above the skid tube saddle. The actions specified by this AD are intended to prevent fatigue failure in a crosstube assembly due to excessive stress during run-on landings and subsequent loss of control of the helicopter.
2023-08-08: The FAA is adopting a new airworthiness directive (AD) for all Airbus SAS Model A330-201, -202, -203, -301, -302, and -303 airplanes. This AD was prompted by reports of corrosion and cracks found on engine inlet attach fittings. This AD requires an inspection to determine whether affected engine inlet attach fittings are installed, and replacement of those affected engine inlet attach fittings or replacement with and inlet cowl having no affected engine inlet attach fittings, as specified in a European Union Aviation Safety Agency (EASA) AD, which is incorporated by reference. This AD also prohibits the installation of affected parts. The FAA is issuing this AD to address the unsafe condition on these products.