29 Airworthiness Directives: 21 airplane, 2 rotorcraft, 4 engine, 2 various.
AD 2016-22-09 · published Nov 4, 2016, effective Dec 9, 2016
The Boeing Company Airplanes
We are superseding Airworthiness Directive (AD) 2006-20-11 for certain The Boeing Company Model 757-200, -200CB, and -200PF series airplanes. AD 2006-20-11 required initial and repetitive detailed or high frequency eddy current (HFEC) inspections for cracks around the rivets at the upper fastener row of the skin lap splice of the fuselage, and repair of any crack found. This new AD no longer allows the detailed inspections and instead requires repetitive external HFEC inspections for cracking of the skin lap splices of the fuselage, and repair if necessary. This AD was prompted by an evaluation done by the design approval holder (DAH) indicating that the fuselage skin lap splice is subject to widespread fatigue damage (WFD). We are issuing this AD to detect and correct fatigue cracking at certain skin lap splice locations of the fuselage, which could result in reduced structural integrity and rapid decompression of the airplane.
AD 2016-22-12 · published Nov 4, 2016, effective Nov 4, 2016
Pilatus Aircraft Ltd. Airplanes
We are adopting a new airworthiness directive (AD) for all Pilatus Aircraft Ltd. Models PC-6, PC-6-H1, PC-6-H2, PC-6/350, PC-6/ 350-H1, PC-6/350-H2, PC-6/A, PC-6/A-H1, PC-6/A-H2, PC-6/B-H2, PC-6/B1- H2, PC-6/B2-H2, PC-6/B2-H4, PC-6/C-H2, and PC-6/C1-H2 airplanes. This AD results from mandatory continuing airworthiness information (MCAI) issued by the aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as wear and cracks on the stabilizer-trim attachment and structural components. We are issuing this AD to require actions to address the unsafe condition on these products.
AD 2016-22-15 · published Nov 4, 2016, effective Dec 9, 2016
Saab AB, Saab Aeronautics (Formerly Known as Saab AB, Saab Aerosystems) Airplanes
We are superseding Airworthiness Directive (AD) 2012-24-06 for certain Saab AB, Saab Aeronautics Model 340A (SAAB/SF340A) and SAAB 340B airplanes. AD 2012-24-06 required replacing the stall warning computer (SWC) with a new SWC that provides an artificial stall warning in icing conditions, and modifying the airplane for the replacement of the SWC. This new AD adds airplanes to the applicability, and adds requirements to replace the existing SWCs with new, improved SWCs, and to modify the airplane for the new replacement of the SWC. This new AD also reduces the compliance time for replacing the SWCs. This AD was prompted by a determination that airplanes with certain modifications were excluded from the applicability in AD 2012-24-06, and are affected by the identified unsafe condition; and that the SWC required by AD 2012-24-06 contained erroneous logic. We are issuing this AD to prevent natural stall events during operation in icing conditions, which could result in loss of control of the airplane.
AD 2016-22-18 · published Nov 4, 2016, effective Nov 21, 2016
The Boeing Company Airplanes
We are adopting a new airworthiness directive (AD) for all The Boeing Company Model MD-90-30 airplanes. This AD requires a detailed inspection of the forward and aft surfaces on the left and right sides at the cant station 1520 bulkhead for any crack in the upper cap and (cap) doubler, webs and doublers, stiffeners, and the lower tee cap between longerons 3 through 11, and repairs if necessary. This AD was prompted by a report of cracking in various structures in the fuselage cant station 1520 bulkhead. We are issuing this AD to detect and correct cracking in the bulkhead, which could result in reduced structural integrity of the airplane.
AD 2016-22-14 · published Nov 9, 2016, effective Dec 14, 2016
The Boeing Company Airplanes
We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 737-600, -700, -700C, -800, -900, and -900ER series airplanes. This AD was prompted by a report of wire chafing damage, which caused an electrical arc to an adjacent hydraulic tube located on the forward bulkhead of the main landing gear (MLG) wheel well, resulting in a hole in a hydraulic tube and consequent total loss of system B hydraulic fluid. This AD requires an inspection for chafing damage of wire bundles and a hydraulic tube in the right side of the MLG wheel well, and corrective action if necessary; and installation of clamps between the wire bundles and hydraulic tube. We are issuing this AD to prevent chafing damage, which could result in electrical arcing that can cause a hole in the hydraulic tube and consequent loss of hydraulic fluid, possibly resulting in a fire in the MLG wheel well.
AD 2016-23-03 · published Nov 9, 2016, effective Nov 29, 2016
Diamond Aircraft Industries GmbH Airplanes
We are adopting a new airworthiness directive (AD) for all Diamond Aircraft Industries GmbH Model DA 40 NG airplanes. This AD results from mandatory continuing airworthiness information (MCAI) issued by the aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as possible loss of engine power and emergency landing with consequent damage to the airplane and occupant injury caused by a manufacturing quality deficiency in a batch of V-clamps that could cause the V-clamp to crack and fail. We are issuing this AD to require actions to address the unsafe condition on these products.
AD 2016-23-01 · published Nov 10, 2016, effective Dec 15, 2016
Airbus Airplanes
We are superseding Airworthiness Directive (AD) 2010-04-03 for all Airbus Model A310 series airplanes. AD 2010-04-03 required accomplishing repetitive detailed inspections for cracking around the fastener holes in certain wing top skin panels between the front and rear spars on the left- and right-hand sides of the fuselage, and repair if necessary. This new AD continues to require the repetitive detailed inspections, and also requires supplemental repetitive ultrasonic inspections for cracking around the fastener holes in wing top skin panels 1 and 2 at ribs 2 and 3, and repair if necessary. This AD was prompted by development of an ultrasonic inspection program to allow for earlier crack detection and extended repetitive inspection intervals. We are issuing this AD to detect and correct fatigue cracking around the fastener holes, which could result in reduced structural integrity of the airplane.
AD 2016-21-05 · published Nov 14, 2016, effective Dec 19, 2016
The Boeing Company Airplanes
We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 777-200, -200LR, -300, and -300ER series airplanes. This AD was prompted by a report indicating that the manufacturer discovered locations where the control components and wiring of the left and right engine fuel spar valves do not have adequate physical separation to meet the redundant system separation requirements. This AD requires modifying the wiring, and installing a new relay bracket and new location for the relay on the left and right engine fuel spar valves. This AD also requires an inspection to identify the part number of the motor operated valve (MOV) actuators for the left and right engine fuel spar valves; replacement of specified MOV actuators with new MOV actuators; certain bonding resistance measurements; and applicable corrective actions. We are issuing this AD to prevent loss of control of both the left and right engine fuel spar valves during a single event, such as local wire bundle damage or a wire bundle fire, which could cause both engines to shut down or result in the inability to control an engine fire.
AD 2016-21-06 · published Nov 14, 2016, effective Dec 19, 2016
Bombardier, Inc. Airplanes
We are superseding Airworthiness Directive (AD) 2015-02-23, 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. AD 2015-02-23 required 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 new AD also requires replacement of the fasteners, which terminates the requirements of this AD. This AD was prompted by reports of incorrectly oriented fasteners. We are issuing this AD to prevent 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.
AD 2016-21-08 · published Nov 22, 2016, effective Dec 27, 2016
Airbus Airplanes
We are superseding Airworthiness Directive (AD) 2013-25-08 for all Airbus Model A330-200, -200 Freighter, and -300 series airplanes; and Model A340-200 and -300 series airplanes. AD 2013-25-08 required a repetitive inspection program on certain check valves in the hydraulic systems that includes, among other things, inspections for lock wire presence and integrity, traces of seepage or black deposits, proper torque, alignment of the check valve and manifold, installation of new lock wire, and corrective actions if needed. This new AD removes airplanes from the applicability, and requires modifying the green, blue, and yellow high pressure hydraulic manifolds by replacing certain check valves with improved check valves, which terminates the repetitive inspections required by this AD. This AD was prompted by multiple reports of hydraulic line check valves loosening. We are issuing this AD to address the unsafe condition on these products.
AD 2016-22-04 · published Nov 22, 2016, effective Dec 27, 2016
Gulfstream Aerospace Corporation Airplanes
We are adopting a new airworthiness directive (AD) for certain Gulfstream Aerospace Corporation Model GV and GV-SP airplanes. This AD was prompted by a new revision to the Airworthiness Limitations Section (ALS) of the Aircraft Maintenance Manual (AMM) based on fatigue and damage tolerance testing, and updated analysis. This AD requires revising the maintenance or inspection program to incorporate updated inspection requirements and life limits that address fatigue cracking of principal structural elements (PSEs). We are issuing this AD to ensure that fatigue cracking of PSEs is detected and corrected; such fatigue cracking could result in reduced structural integrity of the PSEs and critical components.
AD 2016-22-13 · published Nov 22, 2016, effective Dec 27, 2016
The Boeing Company Airplanes
We are adopting a new airworthiness directive (AD) for all The Boeing Company Model 737-600, -700, -700C, -800, -900, and -900ER series airplanes. This AD was prompted by an evaluation by the design approval holder (DAH) indicating that lap splices for certain stringers are subject to widespread fatigue damage (WFD). This AD requires repetitive inspections for cracking in the lower fastener row of the lap splices of certain stringers, and repair if necessary. We are issuing this AD to address the unsafe condition on these products.
AD 2016-22-16 · published Nov 22, 2016, effective Dec 27, 2016
Bombardier, Inc. Airplanes
We are adopting a new airworthiness directive (AD) for certain Bombardier, Inc. Model CL-600-2C10 (Regional Jet Series 700, 701, and 702), CL-600-2D15 (Regional Jet Series 705), CL-600-2D24 (Regional Jet Series 900), and CL-600-2E25 (Regional Jet Series 1000) airplanes. This AD was prompted by a determination that wear and possible leakage of the high-pressure seal in the cylinder of the No. 3 hydraulic system reservoir could occur and cause high hydraulic fluid temperature and/or prevent the system from reaching normal operating pressure. This AD requires repetitive operational checks for wear and leakage of the high-pressure seal in the cylinder of the reservoir of the No. 3 hydraulic system, and corrective actions if necessary. We are issuing this AD to address the unsafe condition on these products.
AD 2016-22-17 · published Nov 22, 2016, effective Dec 27, 2016
The Boeing Company Airplanes
We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 787-8 airplanes. This AD was prompted by a report that the grounding jumpers between the environmental control system (ECS) bracket and the current return network (CRN) straps near certain passenger entry doors were not bonded correctly during manufacturing. This AD requires changing the configuration of the grounding jumpers connecting the ECS brackets and CRN straps; measuring the bond resistance; and doing related investigative and corrective actions if necessary. We are issuing this AD to address the unsafe condition on these products.
AD 2016-23-02 · published Nov 25, 2016, effective Dec 30, 2016
The Boeing Company Airplanes
We are superseding Airworthiness Directive (AD) 2006-19-12 for certain The Boeing Company Model 777-200 and -300 series airplanes. AD 2006-19-12 required inspecting the lower web of the aft fairing of the engine struts for any discoloration, and doing related investigative and corrective actions if necessary; inspecting the heat shield castings for any damage and doing corrective action if necessary; installing gap cover strips; and replacing insulation blankets with new insulation blankets. This new AD retains those requirements and also requires, depending on airplane configuration, one-time or repetitive detailed inspections for cracking and deformation, as applicable, of the aft fairing lower structure, and one-time or repetitive conductivity inspections of the aft fairing lower structure, and related investigative and corrective actions if necessary. This new AD also adds airplanes to the applicability. This AD was prompted by a report that an aft fairing lower spar web exceeded the allowable conductivity limits. We are issuing this AD to address the unsafe condition on these products.
AD 2016-23-07 · published Nov 25, 2016, effective Dec 30, 2016
Bombardier, Inc. Airplanes
We are superseding Airworthiness Directive (AD) 2013-02-08 for all Bombardier, Inc. Model CL-600-2B19 (Regional Jet Series 100 & 440) airplanes. AD 2013-02-08 required inspection of the trunnions and upper and lower pins of the horizontal stabilizer trim actuator (HSTA), and replacement or re-identification if necessary; and revision of the maintenance program to include safe life limits and inspection requirements for the HSTA. This new AD requires certain actions related to the trunnions and pins for the HSTA, revising the maintenance or inspection program, and removing certain airplanes from the applicability. This AD was prompted by a determination that not all affected attachment pins and trunnions were included in the inspections required by AD 2016-02-08, and that incorrect attachment hardware may have been used in replacements on certain airplanes. We are issuing this AD to address the unsafe condition on these products.
AD 2016-23-08 · published Nov 25, 2016, effective Dec 30, 2016
The Boeing Company Airplanes
We are adopting a new airworthiness directive (AD) for all The Boeing Company Model 737-400 series airplanes. This AD was prompted by reports of cracks in the upper chord of the overwing stub beams at body station (STA) 578 emanating from the rivet location common to the crease beam inner chord and the overwing stub beam upper chord. This AD requires repetitive inspections for cracking, and related investigative and corrective actions if necessary. We are issuing this AD to prevent the unsafe condition on these products.
AD 2016-24-01 · published Nov 25, 2016, effective Dec 30, 2016
Bombardier, Inc. Airplanes
We are adopting a new airworthiness directive (AD) for certain Bombardier, Inc. Model DHC-8-102, -103, and -106 airplanes; and Model DHC-8-200 and -300 series airplanes. This AD was prompted by a report of heat damage found on a nacelle firewall after an unsuccessful engine ground start and several events of heat damage found on direct current starter/generator terminal block assemblies. This AD requires an inspection to detect damage on the nacelle firewalls and the terminal block assemblies and to make sure the insulating sleeves are installed and have no damage, and corrective action if necessary. We are issuing this AD to address the unsafe condition on these products.
AD 2016-24-02 · published Nov 25, 2016, effective Dec 30, 2016
The Boeing Company Airplanes
We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 747-8 and 747-8F series airplanes. This AD was prompted by a report that static strength analysis has shown that the aluminum transmission aft bearing plate assemblies have inadequate structural strength for one or more of the required load cases. This AD requires removing aluminum transmission aft bearing plate assemblies from the flap track and installing titanium transmission aft bearing plate assemblies to the flap track. We are issuing this AD to address the unsafe condition on these products.
AD 2016-20-07 · published Nov 29, 2016, effective Jan 3, 2017
Fokker Services B.V. Airplanes
We are adopting a new airworthiness directive (AD) for certain Fokker Services B.V. Model F28 airplanes. This AD was prompted by reports indicating that the main landing gear (MLG) could not be extended and locked down during approach. This AD requires inspection of the restrictor check valve filter screens to detect any degraded or failed filter screens, and installation of serviceable parts. We are issuing this AD to address the unsafe condition on these products.
AD 2016-20-11 · published Nov 29, 2016, effective Jan 3, 2017
Airbus Airplanes
We are superseding Airworthiness Directive (AD) 2014-12-06 for certain Airbus 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 Airbus Model A310 series airplanes. AD 2014-12-06 required repetitive ultrasonic or detailed inspections of the external area of the aft cargo door sill beam for cracking, and repair if necessary, and provided an optional one-time high frequency eddy current (HFEC) inspection that would terminate the repetitive inspections. This new AD requires the previously optional terminating HFEC inspection, and requires that it be done repetitively. This AD was prompted by findings of multiple fatigue cracks in the aft cargo door that indicated the need for additional, repetitive, HFEC inspections. We are issuing this AD to address the unsafe condition on these products.
AD 2016-23-05 · published Nov 25, 2016, effective Dec 12, 2016
Airbus Helicopters (Previously Eurocopter France) Helicopters
We are superseding Airworthiness Directive (AD) 2007-25-08 for Eurocopter France (now Airbus Helicopters) Model SA-365N1, AS-365N2, AS 365 N3, SA-366G1, EC 155B, and EC155B1 helicopters. AD 2007-25-08 required checking the tail rotor gearbox (TGB) oil, inspecting the magnetic plug, and either replacing the TGB or performing additional inspections. This AD was prompted by reports of new occurrences of loss of yaw control due to failure of the control rod bearing. This AD requires checking the TGB oil level and replacing the bearing with a new part-numbered bearing. These actions are intended to detect and prevent damage to the bearing resulting in end play, loss of tail rotor pitch control, and subsequent loss of control of the helicopter.
AD 2016-23-10 · published Nov 25, 2016, effective Dec 12, 2016
Sikorsky Aircraft Corporation Helicopters
We are adopting a new airworthiness directive (AD) for Sikorsky Aircraft Corporation Model S-76D helicopters. This AD requires revising the rotorcraft flight manual (RFM) to prohibit Barometric Altitude Hold (ALT) mode beyond a certain rate of climb or descent. This AD is prompted by a report of the autopilot being unable to maintain level flight during certain flight conditions. The actions specified by this AD are intended to prevent a significant pilot workload increase, pilot disorientation, and subsequent loss of control of the helicopter.
AD 2016-22-05 · published Nov 1, 2016, effective Dec 6, 2016
Pratt & Whitney Division Turbofan Engines
We are adopting a new airworthiness directive (AD) for certain Pratt & Whitney (PW) PW4164, PW4164-1D, PW4168, PW4168-1D, PW4168A, PW4168A-1D, and PW4170 turbofan engines. This AD was prompted by several instances of fuel leaks on PW engines installed with the Talon IIB combustion chamber configuration. This AD requires initial and repetitive inspections of the affected fuel nozzles and their replacement with parts eligible for installation. We are issuing this AD to prevent failure of the fuel nozzles, which could lead to engine fire and damage to the airplane.
AD 2016-22-10 · published Nov 1, 2016, effective Dec 6, 2016
Turbomeca S.A. Turboshaft Engines
We are adopting a new airworthiness directive (AD) for certain Turbomeca S.A. Arriel 1, 1A, 1A1, 1A2, 1B, 1B2, 1C, 1C1, 1C2, 1D, 1D1, 1E, 1E2, 1K1, 1S, and 1S1 turboshaft engines. This AD requires removing the centrifugal impeller and replacing with a part eligible for installation. This AD was prompted by an anomaly that occurred during the grinding operation required by modification TU376, which increases the clearance between the rear curvic coupling of the centrifugal impeller and the fuel injection manifold. We are issuing this AD to prevent failure of the centrifugal impeller, uncontained centrifugal impeller release, damage to the engine, and damage to the helicopter.
AD 2016-22-11 · published Nov 1, 2016, effective Nov 16, 2016
Engine Alliance Turbofan Engines
We are superseding airworthiness directive (AD) 2013-02-06 for all Engine Alliance (EA) GP7270 and GP7277 turbofan engines with certain part number (P/N) high-pressure turbine (HPT) stage 2 nozzle segments installed. AD 2013-02-06 required initial and repetitive borescope inspections (BSI) and removal from service of these nozzles before further flight if one or more burn holes were detected in any HPT stage 2 nozzle segment. AD 2013-02-06 also required removal from service of these HPT stage 2 nozzle segments at the next engine shop visit. This AD requires the same inspections as AD-2013-02-06, requires removal of affected HPT stage 2 nozzles at next piece-part exposure, and adds certain P/Ns to the applicability. This AD was prompted by another report of inadequate cooling of the HPT stage 1 shroud and stage 2 nozzle, leading to damage to the HPT stage 2 nozzle, burn- through of the turbine case, and in-flight shutdown. We are issuing this AD to prevent HPT stage 2 nozzle failure, uncontrolled fire, in- flight shutdown, and damage to the airplane.
AD 2016-23-04 · published Nov 22, 2016, effective Dec 7, 2016
BRP-Powertrain GmbH & Co KG Reciprocating Engines
We are adopting a new airworthiness directive (AD) for certain BRP-Powertrain GmbH & Co KG Rotax 912 F2, 912 F3, 912 F4, 912 S2, 912 S3, 912 S4, 914 F2, 914 F3, and 914 F4 reciprocating engines. This AD requires replacement of any affected carburetor float with a float that is eligible for installation. This AD was prompted by a report of a quality escape in the manufacturing of the affected floats. We are issuing this AD to prevent failure of the carburetor float, failure of the engine, in-flight shutdown, and loss of the airplane.
AD 2016-23-06 · published Nov 18, 2016, effective Dec 23, 2016
Various Aircraft Equipped With BRP-Powertrain GmbH & Co KG 912 A Series Engine
We are adopting a new airworthiness directive (AD) for various aircraft equipped with a BRP-Powertrain GmbH & Co KG (formerly Rotax Aircraft Engines) 912 A series engine. This AD results from mandatory continuing airworthiness information (MCAI) issued by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as a manufacturing defect found in certain carburetor floats where an in-flight engine shutdown and forced landing could occur when the affected cylinder had reduced or blocked fuel supply. We are issuing this AD to require actions to address the unsafe condition on these products.
AD 2016-23-09 · published Nov 22, 2016, effective Dec 27, 2016
Various Restricted Category Helicopters
We are adopting a new airworthiness directive (AD) for various restricted category helicopters. This AD requires cleaning and visually inspecting certain main rotor (M/R) blades and, depending on the outcome of the inspections, repairing or replacing the M/R blades. This AD was prompted by a report of an M/R blade with multiple fatigue cracks around the blade retention bolt hole. The actions are intended to detect a crack in the M/R blade, and prevent failure of the M/R blade and subsequent loss of helicopter control.
