Results
2014-01-05: We are adopting a new airworthiness directive (AD) for certain the Boeing Company Model 737-100, -200, -200C, -300, -400, and -500 series airplanes. This AD was prompted by a report of cracks in stringer splices at body station STA 360 and STA 908, between stringer (S) S-10L and S-10R; cracks in butt straps between S-5L and S-3L, and S-3R and S-5R; vertical chem-mill fuselage skin cracks at certain butt joints; and an instance of cracking that occurred in all those three structural elements on one airplane. This AD requires repetitive inspections for any cracking of stringer splices and butt straps, and related corrective and investigative actions if necessary. We are issuing this AD to detect and correct cracking in the three structural elements, which could result in the airplane not being able to sustain limit load requirements and possibly result in uncontrolled decompression.
2025-05-01: The FAA is adopting a new airworthiness directive (AD) for certain 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). This AD was prompted by a determination that new or more restrictive airworthiness limitations are necessary. This AD requires revising the existing maintenance or inspection program, as applicable, to incorporate new or more restrictive airworthiness limitations, 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.
2014-02-09: We are adopting a new airworthiness directive (AD) for Eurocopter Model EC225LP and AS332L1 helicopters with emergency floatation gear. The AD requires, before the next overwater flight, inspecting the strap installation on the hinged rods of the emergency flotation gear on both rear cradles for correct installation. If a strap is installed under the hinged rod median plate rather than over it, reinstalling the strap is required. The AD is prompted by incorrect routing of the straps on the hinged rods of the emergency flotation gear rear cradles. The actions are intended to detect incorrect strap installation and prevent failure of the rods or straps upon deployment of the emergency flotation gear, incorrect float position, and subsequent capsizing of the helicopter.
2025-05-07: The FAA is adopting a new airworthiness directive (AD) for all Airbus Canada Limited Partnership (ACLP) Model BD-500-1A10 and BD-500- 1A11 airplanes. This AD was prompted by a design review of aircraft structural and stress reports that resulted in a revision of operational loads for some aircraft flight phases. This AD requires using a certain version of the aircraft structural repair manual (ASRP) and a review and disposition of repairs based on previous versions, as specified in a Transport Canada AD, which is incorporated by reference. The FAA is issuing this AD to address the unsafe condition on these products.
2013-24-04: We are superseding Airworthiness Directive (AD) 2003-19-11 for certain Learjet Inc. Model 60 airplanes. AD 2003-19-11 required determining if a certain fuel crossflow tube is installed; and follow- on/corrective actions, as applicable. This new AD requires retaining all actions in AD 2003-19-11, and it also requires determining if a certain fuel crossflow tube is installed, performing repetitive measurements of the fuel crossflow tube and surrounding valves and cables, and doing corrective actions if necessary. In addition, this new AD expands the applicability of AD 2003-19-11. This AD was prompted by a report that airplanes produced since 2003 might also be subject to the unsafe condition; and that the minimum allowable clearance is not established in the airplane maintenance information. We are issuing this AD to prevent chafing and consequent failure of the fuel crossflow tube due to inadequate clearance between the tube and the flight control cables, which could result inloss of fuel from one fuel tank during normal operating conditions or loss of fuel from both main fuel tanks during fuel cross-feeding operations.
67-28-04: 67-28-04 GENERAL ELECTRIC ENGINES: Amdt. 39-489 Part 39 Federal Register October 5, 1967. Applies to Type CJ805-3, 3A, 3B, 23, 23B and 23C Turbojet Engines. Compliance required as indicated. To prevent failure of the eighth stage compressor disc P/N 106R682P1 and 108R619P1 accomplish the following: (a) Remove from service eighth stage compressor discs with 12,000 or more cycles on the effective date of this AD within the next 50 cycles. (b) Remove from service eighth stage compressor discs with 11,000 or more cycles on the effective date of this AD within the next 250 cycles. (c) Remove from service eighth stage compressor discs with less than 11,000 cycles but more than 9500 cycles on the effective date of this AD within the next 600 cycles. (d) Remove from service eighth stage compressor discs with less than 9500 cycles on the effective date of this AD within the next 1250 cycles or at 8000 cycles, whichever occurs later. (e) Remove from serviceeighth stage compressor discs installed into engines on or after the effective date of this AD at or before 8000 cycles. (f) For the purpose of this AD, the number of cycles equals the number of flights that involve an engine operating sequence consisting of engine starting, take off operation, landing, and engine shutdown. The number of cycles may be determined by actual count or, subject to acceptance by the assigned FAA Maintenance Inspector, may be calculated by dividing each eighth stage compressor disc's time in service by the operator's fleet average time per flight (involving an engine operating sequence consisting of engine starting, take off operation, landing and engine shutdown). (General Electric Alert Service Bulletins A72-254 and A72-261 cover the same subject.) This amendment effective October 5, 1967.
2014-02-03: We are superseding Airworthiness Directive (AD) 2011-27-51 for certain Beechcraft Corporation Models 1900, 1900C, and 1900D airplanes. AD 2011-27-51 required inspecting the elevator bob-weight and attaching linkage for correct installation and for damage or deformation to the weight and/or weight bracket with corrective action as necessary. This AD requires installation of the secondary elevator bob-weight stop bolt. The elevator bob-weight (stabilizer weight) traveling past its stop bolt may allow the attaching linkage to move over-center and lead to reduced nose down elevator control. We are issuing this AD to correct the unsafe condition on these products.
2017-17-03: The FAA is superseding Airworthiness Directive (AD) 2017-12- 13, which applied to certain Airbus SAS Model A320-212, -214, -232, and -233 airplanes. AD 2017-12-13 required repetitive low frequency eddy current inspections or repetitive high frequency eddy current inspections of the pocket radius at certain areas of the fuselage frame, and repair if necessary. This AD requires new repetitive inspections at the left- (LH) and right-hand (RH) sides of the fuselage skin at certain frames for any cracking, and repair if necessary, as specified in a European Union Aviation Safety Agency (EASA) AD, which is incorporated by reference. This AD was prompted by a report of a crack found during an inspection of the pocket radius of the fuselage frame, and a determination that similar cracks may develop in nearby areas of the fuselage frame and that additional airplanes are subject to the unsafe condition. The FAA is issuing this AD to address the unsafe condition on these products.
2013-25-03: We are superseding Airworthiness Directives (ADs) AD 2000-17- 05 and AD 2001-04-09 for all the Boeing Company Model 767 airplanes. AD 2000-17-05 required a functional check of the shear rivets in all six elevator power control actuator (PCA) bellcrank assemblies to determine the condition of the shear rivets; and replacement or rework of the bellcrank assemblies, if necessary. AD 2001-04-09 required repetitive testing of the elevator control system to determine if an elevator PCA is rigged incorrectly due to yielded or failed shear rivets in a bellcrank assembly for the elevator PCA, and follow-on actions if necessary. Since we issued ADs 2000-17-05 and 2001-04-09, a terminating modification has been designed. This new AD requires an inspection to determine the part numbers and condition of the bellcrank assemblies; modification or replacement of the PCA bellcrank assembly, if necessary; and a repetitive functional test and mis-rig check, and corrective actions if necessary. We are issuing this AD to prevent continued operation with yielded or failed shear rivets in the elevator PCA bellcrank assemblies, and to prevent certain failures or jams in the elevator system from causing a hardover of the elevator surface, resulting in a significant pitch upset and possible loss of control of the airplane.
2013-26-11: We are adopting a new airworthiness directive (AD) for Eurocopter France (Eurocopter) Model EC225LP helicopters. This AD requires inspecting the swashplates for corrosion or a crack, and making the appropriate repairs or replacement of parts. This AD was prompted by the discovery of corrosion on the swashplates when the main rotor hub (MRH) assemblies were reconditioned. The actions of this AD are intended to detect corrosion or a crack in the swashplates, which could lead to failure of the swashplates and subsequent loss of helicopter control.