14 CFR Part 39 - AIRWORTHINESS DIRECTIVES

We are adopting a new airworthiness directive (AD) for SOCATA Model TB 9, TB 10, TB 20, TB 21, and TB 200 airplanes. 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 corrosion of the horizontal stabilizer. We are issuing this AD to require actions to address the unsafe condition on these products.

We are adopting a new airworthiness directive (AD) for Viking Air Limited Model DHC-3 Airplanes. 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 corrugation cracking found at various wing stations and on the main spar lower cap. We are issuing this AD to require actions to address the unsafe condition on these products.

We are adopting a new airworthiness directive (AD) for all Airbus Model A330-200 Freighter, A330-200, A330-300, A340-200, A340-300, A340-500, and A340-600 series airplanes. This AD was prompted by a report of skin disbonding on a composite side panel of a rudder installed on an A310 airplane. This AD requires a review of the maintenance records of the rudder to determine if any composite side shell panel repair has been done; a thermography inspection limited to the repair areas or complete side shells, as applicable, to identify possible in-service rudder repairs, damages, or fluid ingress; and applicable related investigative and corrective actions. We are issuing this AD to detect and correct the rudder skin disbonding, which could affect the structural integrity of the rudder, and could result in reduced controllability of the airplane.

We are adopting a new airworthiness directive (AD) for all Airbus Model A318, A319, A320, and A321 series airplanes. This AD was prompted by a determination that, in specific flight conditions, the allowable load limits on the vertical tail plane could be reached and possibly exceeded. Exceeding allowable load could result in detachment of the vertical tail plane. This AD requires modification of the pin programming flight warning computer (FWC) to activate the stop rudder input warning (SRIW) logic; and an inspection to determine the part numbers of the FWC and the flight augmentation computer (FAC), and replacement of the FWC and FAC if necessary. We are issuing this AD to prevent detachment of the vertical tail plane and consequent loss of control of the airplane.

We are superseding Airworthiness Directive (AD) 2011-09-04 for all Lockheed Martin Corporation/Lockheed Martin Aeronautics Company Model 382, 382B, 382E, 382F, and 382G airplanes. AD 2011-09-04 required repetitive inspections for damage to the lower surface of the center wing box (CWB), and corrective actions if necessary. This new AD adds related investigative actions, and corrective actions if necessary. This AD was prompted by an evaluation by the design approval holder (DAH) that indicated that the CWB is subject to widespread fatigue damage (WFD). We are issuing this AD to detect and correct fatigue cracking of the lower surface of the CWB, which could result in structural failure of the wings.

We are adopting a new airworthiness directive (AD) for all Airbus Model A330-200, A330-200 Freighter, and A330-300 series airplanes; and Model A340-200 and A340-300 series airplanes. This AD was prompted by reports of cracked support strut body ends at a certain frame location of the trimmable horizontal stabilizer (THS). This AD requires repetitive inspections for cracking of the strut ends of the THS support located at a certain frame in the tail cone, and replacement if necessary; and reinstallation or installation of reinforcing clamps on certain strut ends. We are issuing this AD to detect and correct cracked support strut body ends of the THS, which could lead to the loss of all four THS support struts, making the remaining structure unable to carry limit loads, resulting in the loss of the horizontal tail plane.

We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 747-100, 747-100B, 747-100B SUD, 747-200B, 747-300, 747SR, and 747SP series airplanes. This AD was prompted by an evaluation by the design approval holder (DAH) indicating that certain fuselage skin lap joints are subject to widespread fatigue damage (WFD). This AD requires repetitive post-modification inspections for cracking of the skin or internal doubler along the edge fastener rows of the modification, and repair if necessary. We are issuing this AD to detect and correct fatigue cracking in certain fuselage skin lap joints, which could result in rapid depressurization of the airplane.

We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 747-8 series airplanes. This AD was prompted by a report of improperly installed outboard stowage bin modules in the passenger compartment found during maintenance. Further investigation revealed that certain attachment bracket bushings were missing or had moved out of the holes. This AD requires installing a spacer on the end of each quick-release pin that attaches the outboard stowage bin module to the lateral support tie rods of the main deck passenger compartment. We are issuing this AD to prevent detachment of the quick-release pin, which could result in separation of the lateral support tie rod and subsequent detachment of the module and consequent injuries to passengers or flightcrew.

We are superseding Airworthiness Directive (AD) 2002-07-08 for certain The Boeing Company Model 737 airplanes. AD 2002-07-08 required repetitive inspections for cracking of the lower skin at the lower row of fasteners in the lap joints of the fuselage; repair of any cracking found; modification of the fuselage lap joints at certain locations, which terminated the repetitive inspections of the modified areas; and replacement of a certain preventive modification with an improved modification. This new AD adds repetitive inspections for cracking at certain window corner fastener holes, a preventive modification, and repair if necessary. This AD was prompted by the FAA's determination that certain modifications of the fuselage lap joints do not provide an adequate level of safety, and the subsequent discovery of cracks in additional fastener locations in the window belt skin panels, adjacent stringers, and window frames in locations outside the previous inspection area. We are issuing this AD to detect and correct fatigue cracking of the fuselage lap joints and window belt skin panels, which could result in reduced structural integrity and sudden decompression of the airplane.

We are adopting a new airworthiness directive (AD) for Sikorsky Aircraft Corporation (Sikorsky) Model 269A, 269A-1, 269B, 269C, 269C-1, 269D, and TH-55A helicopters. This AD requires repetitively inspecting and lubricating the tail rotor (T/R) driveshaft splined fittings. This AD was prompted by a report that the T/R driveshaft can disconnect due to deterioration of the splined coupling. The actions are intended to detect and prevent excessive wear of the splined coupling, which could lead to failure of the T/R driveshaft and subsequent loss of control of the helicopter.

We are adopting a new airworthiness directive (AD) for all Airbus Model A318, A319, and A320 series airplanes. This AD was prompted by a cracked upper cardan in the main landing gear (MLG). This AD requires revising the maintenance or inspection program, as applicable, to reduce the life limits for the MLG upper cardan for certain installations. We are issuing this AD to prevent failure of the upper cardan in the MLG, which could result in MLG collapse and subsequent damage to the airplane and injury to occupants.

We are adopting a new airworthiness directive (AD) for certain Lockheed Martin Corporation/Lockheed Martin Aeronautics Company Model 188 series airplanes. This AD was prompted by an evaluation by the design approval holder (DAH) indicating that the circumferential fuselage splice at fuselage-station (FS) 695 is subject to widespread fatigue damage (WFD). This AD requires an inspection for corrosion and previous repairs, severed stringers, cracking, and loose or distressed fasteners of the forward and aft ends of the stringer splices of certain stringers, inspection for cracking and modification of certain fastener holes common to the stringer and splice member at the forward and aft ends of the splice, and related investigative and corrective actions if necessary. We are issuing this AD to prevent loss of residual strength of the circumferential fuselage splice at FS 695, which could lead to rapid decompression of the cabin and potential loss of the airplane.

We are superseding Airworthiness Directive (AD) 2015-16-01 for certain The Boeing Company Model airplanes. AD 2015-16-01 required incorporating design changes to improve the reliability of the cabin altitude warning system by installing a redundant cabin altitude pressure switch, replacing the aural warning module (AWM) with a new or reworked AWM, and changing certain wire bundles or connecting certain previously capped and stowed wires as necessary. For certain airplanes, AD 2015-16-01 also required prior or concurrent incorporation of related design changes by modifying the instrument panels, installing light assemblies, modifying the wire bundles, and installing a new circuit breaker, as necessary. This AD retains all actions required by AD 2015-16-01. This AD was prompted by the discovery of a typographical error in AD 2015-16-01 that referred to a nonexistent paragraph. We are issuing this AD to prevent the loss of cabin altitude warning, which could delay flightcrew recognition of a lack of cabin pressurization, and could result in incapacitation of the flightcrew due to hypoxia (a lack of oxygen in the body), and consequent loss of control of the airplane.

We are superseding Airworthiness Directive (AD) 2007-16-08, which applied to all The Boeing Company Model 747-100, 747-100B, 747-100B SUD, 747-200B, 747-200C, 747-300, 747-400, 747-400D, and 747SR series airplanes. AD 2007-16-08 required repetitive inspections for cracking of the station 800 frame assembly, and repair if necessary. This new AD continues to require repetitive inspections for cracking of the station 800 frame assembly, and repair if necessary, and expands the inspection area. This AD was prompted by reports of cracks found at the forward and aft inner chord strap and angles on the station 800 frame on the left-side and right-side main entry doors. We are issuing this AD to detect and correct fatigue cracks that could extend and fully sever the frame, which could result in development of skin cracks that could lead to rapid depressurization of the airplane.

We are superseding Airworthiness Directive (AD) 2015-19-03 for all The Boeing Company Model 737-600, -700, -700C, -800, -900, and -900ER series airplanes. AD 2015-19-03 required revising the maintenance or inspection program to include new airworthiness limitations. This AD continues to require a maintenance or inspection program revision, but with revised language. This AD was prompted by a determination that certain language in the airworthiness limitation was not accurate in AD 2015-19-03. We are issuing this AD to detect and correct latent failures of the fuel shutoff valve to the engine, which could result in the inability to shut off fuel to the engine and, in case of certain engine fires, an uncontrollable fire that could lead to wing failure.

We are adopting a new airworthiness directive (AD) for all Fokker Services B.V. Model F.27 Mark 200, 300, 400, 500, 600, and 700 airplanes. This AD was prompted by a design review, which revealed that no controlled bonding provisions are present on a number of critical locations inside the fuel tank or connected to the fuel tank wall; and no anti-spray cover is installed on the fuel shut-off valve (FSOV) in both wings. This AD requires installing additional bonding provisions in the fuel tank, installing an anti-spray cover on the FSOV, and revising the airplane maintenance program by incorporating fuel airworthiness limitation items and critical design configuration control limitations. We are issuing this AD to prevent an ignition source in the fuel tank vapor space, which could result in a fuel tank explosion and consequent loss of the airplane.

We are adopting a new airworthiness directive (AD) for certain Pratt & Whitney (PW) PW4164, PW4168, PW4168A, PW4164-1D, PW4168-1D, PW4168A-1D, and PW4170 turbofan engines. This AD was prompted by crack finds in the 6th stage low-pressure turbine (LPT) disk. This AD requires removal of the affected 6th stage LPT disks. We are issuing this AD to prevent failure of the 6th stage LPT disk, which could lead to an uncontained disk release, damage to the engine, and damage to the airplane.

We propose to adopt a new airworthiness directive (AD) for all Embraer S.A. Model ERJ 170 airplanes; and all Embraer S.A. Model ERJ 190-100 STD, -100 LR, -100 IGW, -200 STD, -200 LR, and -200 IGW airplanes. This proposed AD was prompted by reports of cracks in certain engine low-stage bleed check valves. This proposed AD would require replacing the air management system (AMS) controller operation program of the AMS controller processor boards, and replacement of the current low-stage bleed check valve and associated seals. We are proposing this AD to prevent failure of the low-stage bleed check valve, which could result in dual engine in-flight shutdown.

The FAA is withdrawing a notice of proposed rulemaking (NPRM). The NPRM proposed a new airworthiness directive (AD) that had applied to all Rolls-Royce Deutschland Ltd & Co KG (RRD) Tay 650-15 and Tay 651-54 turbofan engines. The proposed action would have required reducing the cyclic life limits for certain high-pressure turbine (HPT) disks. Accordingly, we withdraw the proposed rule.

We propose to adopt a new airworthiness directive (AD) for all Airbus Model A318-111 and -112 airplanes; Model A319-111, -112, -113, -114, and -115 airplanes; Model A320-211, -212, and -214 airplanes; and Model A321-111, -112, -211, -212, and -213 airplanes. This proposed AD was prompted by an evaluation by the design approval holder (DAH) indicating that the forward engine mounts are subject to widespread fatigue damage (WFD). This proposed AD would require repetitive detailed inspections of the right and left forward engine mounts, and corrective action if necessary. These inspections are required by AD 2015-05-02. This proposed AD would reduce the compliance times for those inspections. We are proposing this AD to detect and correct fatigue cracking in the forward engine mounts, which could result in reduced structural integrity of the airplane and could lead to in-flight loss of an engine, possibly resulting in reduced controllability of the airplane.

We propose to adopt a new airworthiness directive (AD) for certain Airbus Model A318, A319, A320, and A321 series airplanes. This proposed AD was prompted by reports of cracking of the aft fixed fairing (AFF) of the pylons due to fatigue damage of the structure. This proposed AD would require repetitive inspections for damage and cracking of the AFF of the pylons, and repair if necessary. We are proposing this AD to detect and correct damage and cracking of the AFF of the pylons, which could result in detachment of a pylon and consequent reduced structural integrity of the airplane.

We propose to adopt a new airworthiness directive (AD) for certain The Boeing Company Model 737-100, -200, -200C, -300, -400, and -500 series airplanes. This proposed AD was prompted by an evaluation by the design approval holder (DAH) indicating that the bulkhead is subject to widespread fatigue damage (WFD). This proposed AD would require repetitive inspections of the aft pressure bulkhead web for any cracking, incorrectly drilled fastener holes, and elongated fastener holes, and related investigative and corrective actions if necessary. We are proposing this AD to detect and correct fatigue cracking of the aft pressure bulkhead web at the “Y”-chord, which could result in reduced structural integrity of the airplane and rapid decompression of the fuselage.

We are adopting a new airworthiness directive (AD) for SOCATA Model TB 9, TB 10, TB 20, TB 21, and TB 200 airplanes. 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 corrosion of the horizontal stabilizer. We are issuing this AD to require actions to address the unsafe condition on these products.

We are adopting a new airworthiness directive (AD) for Viking Air Limited Model DHC-3 Airplanes. 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 corrugation cracking found at various wing stations and on the main spar lower cap. We are issuing this AD to require actions to address the unsafe condition on these products.

We are adopting a new airworthiness directive (AD) for all Airbus Model A330-200 Freighter, A330-200, A330-300, A340-200, A340-300, A340-500, and A340-600 series airplanes. This AD was prompted by a report of skin disbonding on a composite side panel of a rudder installed on an A310 airplane. This AD requires a review of the maintenance records of the rudder to determine if any composite side shell panel repair has been done; a thermography inspection limited to the repair areas or complete side shells, as applicable, to identify possible in-service rudder repairs, damages, or fluid ingress; and applicable related investigative and corrective actions. We are issuing this AD to detect and correct the rudder skin disbonding, which could affect the structural integrity of the rudder, and could result in reduced controllability of the airplane.

We are adopting a new airworthiness directive (AD) for all Fokker Services B.V. Model F.28 Mark 0070 and 0100 airplanes. This AD was prompted by reports that cracks can occur in a frame of the tail section on certain airplanes. This AD requires a one-time detailed inspection of the oblique frame 67-2 for any cracking, and repair if necessary. We are issuing this AD to detect and correct such cracking, which could lead to failure of the oblique frame 67-2, and consequent loss of the structural integrity of the tail section.

We propose to adopt a new airworthiness directive (AD) for certain Fokker Services B.V. Model F.28 Mark 0070 and 0100 airplanes. This proposed AD was prompted by a design review that revealed that a wiring failure, external to the center wing fuel tank, could cause a hot short circuit to a maximum level sensor wire, and result in excessive heating of the maximum level sensor element. This proposed AD would require modifying the wiring of the maximum level sensors in the center wing fuel tank, performing after-installation tests, and corrective action if necessary. This proposed AD would also require revising the airplane maintenance or inspection program to incorporate fuel airworthiness limitation items and critical design configuration control limitations. We are proposing this AD to prevent the potential of ignition sources inside fuel tanks, which, in combination with flammable fuel vapors, could result in fuel tank explosions and consequent loss of the airplane.

We propose to supersede Airworthiness Directive (AD) 2004-19-11 for certain Airbus Model 320 series airplanes. AD 2004-19-11 currently requires modification of the inner rear spar web of the wing, cold expansion of the attachment holes of the forward pintle fitting and the actuating cylinder anchorage of the main landing gear (MLG), repetitive ultrasonic inspections for cracking of the rear spar of the wing, and corrective action if necessary. AD 2004-19-11 also provides optional terminating action for the repetitive inspections. Since we issued AD 2004-19-11, we have determined that the terminating action is necessary to address the unsafe condition. This proposed AD is intended to complete certain mandated programs intended to support the airplane reaching its limit of validity (LOV) of the engineering data that support the established structural maintenance program. This proposed AD would retain the requirements of AD 2004-19-11 and would require the previously optional terminating action. We are proposing this AD to prevent fatigue cracking of the inner rear spar, which may lead to reduced structural integrity of the wing and the MLG.

We propose to adopt a new airworthiness directive (AD) for certain Airbus Model A318, A319, and A320 series airplanes. This proposed AD was prompted by reports of an operator finding chafing damage on the fuselage skin at the bottom of certain frames, underneath the fairing structure. This proposed AD would require a repetitive detailed inspection for damage on the fuselage skin at certain frames, and applicable related investigative and corrective actions. We are proposing this AD to detect and correct damage to the fuselage skin, which could lead to crack initiation and propagation, possibly resulting in reduced structural integrity of the fuselage.

We propose to adopt a new airworthiness directive (AD) for certain Airbus Model A330-200 and -300 series airplanes; and all Model A340-200, -300, -500, and -600 series airplanes. This proposed AD was prompted by reports that the potable water service panel access door was lost during flight. This proposed AD would require modifying affected potable water service panel access doors. We are proposing this AD to prevent failure of the latching mechanism of the potable water service panel access door, which could result in the loss of the potable water service panel access door during flight, and resultant damage to the airplane ( e.g., damage to the trimmable horizontal stabilizer) that could cause loss of control of the airplane.

We propose to supersede Airworthiness Directive (AD) 2011-23-05, which applies to certain The Boeing Company Model 737-300, -400, and -500 series airplanes. AD 2011-23-05 currently requires repetitive inspections for cracking of the 1.04-inch nominal diameter wire penetration hole, and applicable related investigative and corrective actions. Since we issued AD 2011-23-05, an evaluation by the design approval holder (DAH) indicates that the fuselage frames and frame reinforcements are subject to widespread fatigue damage (WFD). This proposed AD would add new inspection areas, a modification that terminates certain inspections, post-modification inspections, and repair if necessary. We are proposing this AD to detect and correct fatigue cracking of the fuselage frames and frame reinforcements, which could result in reduced structural integrity of the airplane.

We propose to supersede Airworthiness Directive (AD) 2006-10-16, which applies to all 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 2006-10-16 requires, for certain airplanes, repetitive inspections for cracking of the outboard and center sections of the horizontal stabilizer, and repair if necessary. For certain other airplanes, AD 2006-10-16 requires a detailed inspection to determine the type of fasteners, and related investigative actions and repair if necessary. Since we issued AD 2006-10-16, additional cracking was found in the splice plates, hinge fittings, terminal fittings, the upper skin of the outboard and center sections, and the rear spar webs before reaching the inspection interval specified in AD 2006-10-16. Cracked and fractured Maraging steel fasteners were also found. This proposed AD would reduce the compliance time for certain inspections and would add repetitive inspections for cracking of the splice plates, hinge fittings, terminal fittings, the upper skin of the outboard and center sections, and the rear spar webs in Zone B. This proposed AD would also add an inspection to determine whether fasteners are magnetic in Zone C, repetitive ultrasonic inspections for cracking and fractures of affected fasteners, and related investigative and corrective actions if necessary. This proposed AD would also add an optional modification, which would terminate certain repetitive inspections, and would add post-modification inspections and corrective action if necessary. We are proposing this AD to detect and correct this cracking, which could lead to reduced structural capability of the outboard and center sections of the horizontal stabilizer and could result in loss of control of the airplane.

We are adopting a new airworthiness directive (AD) for all Airbus Model A318, A319, A320, and A321 series airplanes. This AD was prompted by a determination that, in specific flight conditions, the allowable load limits on the vertical tail plane could be reached and possibly exceeded. Exceeding allowable load could result in detachment of the vertical tail plane. This AD requires modification of the pin programming flight warning computer (FWC) to activate the stop rudder input warning (SRIW) logic; and an inspection to determine the part numbers of the FWC and the flight augmentation computer (FAC), and replacement of the FWC and FAC if necessary. We are issuing this AD to prevent detachment of the vertical tail plane and consequent loss of control of the airplane.

We are adopting a new airworthiness directive (AD) for all ATR—GIE Avions de Transport Régional Model ATR42 and ATR72 airplanes. This AD was prompted by new occurrences of certain cracked main landing gear (MLG) rear hinge pins. This AD requires identifying the serial number and part number of the MLG rear hinge pins, and replacing pins or the MLG if necessary. We are issuing this AD to detect and correct cracked rear hinge pins, which could lead to MLG structural failure, possibly resulting in collapse of the MLG and consequent injury to the occupants of the airplane.

We propose to adopt a new airworthiness directive (AD) for certain Turbomeca S.A. Arriel 2B, 2B1, 2C, 2C1, 2C2, 2D, 2E, 2S1, and 2S2 turboshaft engines. This proposed AD was prompted by a report of an uncommanded in-flight shutdown of an Arriel 2 engine caused by rupture of the 41-tooth gear, which forms part of the bevel gear in the engine accessory gearbox (AGB). This proposed AD would require inspection, and, depending on the results, removal of the engine AGB. We are proposing this AD to prevent failure of the engine AGB, which could lead to in-flight shutdown, damage to the engine, and damage to the aircraft.

We are superseding Airworthiness Directive (AD) 2011-09-04 for all Lockheed Martin Corporation/Lockheed Martin Aeronautics Company Model 382, 382B, 382E, 382F, and 382G airplanes. AD 2011-09-04 required repetitive inspections for damage to the lower surface of the center wing box (CWB), and corrective actions if necessary. This new AD adds related investigative actions, and corrective actions if necessary. This AD was prompted by an evaluation by the design approval holder (DAH) that indicated that the CWB is subject to widespread fatigue damage (WFD). We are issuing this AD to detect and correct fatigue cracking of the lower surface of the CWB, which could result in structural failure of the wings.

We are adopting a new airworthiness directive (AD) for all Airbus Model A330-200, A330-200 Freighter, and A330-300 series airplanes; and Model A340-200 and A340-300 series airplanes. This AD was prompted by reports of cracked support strut body ends at a certain frame location of the trimmable horizontal stabilizer (THS). This AD requires repetitive inspections for cracking of the strut ends of the THS support located at a certain frame in the tail cone, and replacement if necessary; and reinstallation or installation of reinforcing clamps on certain strut ends. We are issuing this AD to detect and correct cracked support strut body ends of the THS, which could lead to the loss of all four THS support struts, making the remaining structure unable to carry limit loads, resulting in the loss of the horizontal tail plane.

We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 747-100, 747-100B, 747-100B SUD, 747-200B, 747-300, 747SR, and 747SP series airplanes. This AD was prompted by an evaluation by the design approval holder (DAH) indicating that certain fuselage skin lap joints are subject to widespread fatigue damage (WFD). This AD requires repetitive post-modification inspections for cracking of the skin or internal doubler along the edge fastener rows of the modification, and repair if necessary. We are issuing this AD to detect and correct fatigue cracking in certain fuselage skin lap joints, which could result in rapid depressurization of the airplane.

We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 747-8 series airplanes. This AD was prompted by a report of improperly installed outboard stowage bin modules in the passenger compartment found during maintenance. Further investigation revealed that certain attachment bracket bushings were missing or had moved out of the holes. This AD requires installing a spacer on the end of each quick-release pin that attaches the outboard stowage bin module to the lateral support tie rods of the main deck passenger compartment. We are issuing this AD to prevent detachment of the quick-release pin, which could result in separation of the lateral support tie rod and subsequent detachment of the module and consequent injuries to passengers or flightcrew.

We are adopting a new airworthiness directive (AD) for certain Zodiac Aerotechnics (formerly Intertechnique Aircraft Systems) flightcrew oxygen mask regulators as installed on, but not limited to, various transport and small airplanes. This AD was prompted by a report that improper maintenance on oxygen mask regulators was found. This AD requires the identification and replacement of all potentially affected units. This AD also requires installation of a placard and revision of the airplane flight manual to include an operational procedure for use in case of depressurization. We are issuing this AD to detect and correct affected oxygen mask regulators, which could lead to inadequate protection to the affected flightcrew against hypoxia. Hypoxia can start from a headache and drowsiness and lead eventually to unconsciousness with severe consequence in terms of airplane controllability.

We propose to adopt a new airworthiness directive (AD) for certain The Boeing Company Model 787-8 airplanes. This proposed AD was prompted by reports of water leakage from the potable water system due to improperly installed waterline couplings, and water leaking into the electronics equipment (EE) bays from above the floor in the main cabin, resulting in water on the equipment in the EE bays. This proposed AD would require replacing the potable waterline couplings above the forward and aft EE bays with new, improved couplings. This proposed AD would also require sealing the main cabin floor areas above the aft EE bay, installing drip shields and foam blocks, and rerouting the wire bundles near the drip shields above the equipment in the aft EE bay. We are proposing this AD to prevent a water leak from an improperly installed potable water system coupling, or main cabin water source, which could cause the equipment in the EE bays to become wet, resulting in an electrical short and potential loss of system functions essential for safe flight.

We propose to supersede Airworthiness Directive (AD) 2015-03-06, for all Airbus Model A330-200, A330-200 Freighter, A330-300, A340-200, A340-300, A340-500, and A340-600 series airplanes. AD 2015-03-06 currently requires repetitive inspections of the left-hand and right-hand wing main landing gear (MLG) rib 6 aft bearing lugs (forward and aft) to detect any cracks on the two lugs, and replacement if necessary. Since we issued AD 2015-03-06, we have received reports of additional cracking of the MLG rib 6 aft bearing lugs. This proposed AD would reduce certain compliance times. We are proposing this AD to detect and correct cracking of the MLG rib 6 aft bearing lugs, which could result in collapse of the MLG upon landing.

We propose to supersede Airworthiness Directive (AD) 95-18-08, for all Airbus Model A300-600 series airplanes. AD 95-18-08 currently requires repetitive inspections to detect cracks in the bottom skin of the wing in the area of the cut out for the pylon rear attachment fitting, and repair if necessary. Since we issued AD 95-18-08, we received a report that updated fatigue and damage tolerance analyses and a fleet survey found that certain inspection thresholds and intervals must be reduced to allow more timely findings of cracking. This proposed AD would, for certain airplanes, reduce the compliance times for the inspections. We are proposing this AD to detect and correct such fatigue-related cracking, which could result in reduced structural integrity of the wing.