Results
2025-09-04: The FAA is adopting a new airworthiness directive (AD) for certain Bombardier Inc. Model BD-700-1A10 and BD-700-1A11 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. The FAA is issuing this AD to address the unsafe condition on these products.
96-23-04: This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 737-100 and -200 series airplanes, that requires replacement of the 250 volt-ampere (VA) rated static inverters with 410 VA or 500 VA rated static inverters, and an operational test of the standby electrical power system. This amendment is prompted by a report that accomplishment of a certain modification could result in overload of the static inverter on these airplanes. The actions specified by this AD are intended to prevent overload of the static inverter, which could result in the loss of the 115 volt alternating current (VAC) standby bus and the associated flight instruments when the airplane is operating on standby electrical power.
99-25-06: This amendment adopts a new airworthiness directive (AD), applicable to certain British Aerospace (Jetstream) Model 4101 airplanes, that requires a one-time inspection of the bottom aft roller of the main baggage-bay door structure for cracking or damage to the sub-frame; repetitive operational tests to determine if the counter-balance motor functions properly; and corrective actions, if necessary. This amendment is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified by this AD are intended to prevent sub-frame damage, which, if left undetected, could cause rapid decompression of the airplane and consequent injury to passengers and crew.
2011-09-15: We are adopting a new airworthiness directive (AD) for the products listed above. This AD requires, for certain airplanes, replacing certain boost pump relays with ground fault interrupter (GFI) relays. For certain other airplanes, this AD requires installing new panels in the main equipment center, making certain wiring changes, installing new GFI relays in the new panels, and installing \n\n((Page 24346)) \n\nnew electrical load management system (ELMS) software. For certain other airplanes, this AD requires doing certain bond resistance measurements, and corrective actions if necessary. This AD was prompted by fuel system reviews conducted by the manufacturer. We are issuing this AD to prevent potential ignition sources inside fuel tanks, which, in combination with flammable fuel vapors, could result in a fuel tank explosion and consequent loss of the airplane.
2011-09-14: We are adopting a new airworthiness directive (AD) for the products listed above. This AD requires an inspection to determine the part number of the mid-pivot access door and to determine if the correct door is installed, and the installation of a marker on the mid- pivot access door, and if necessary, repetitive ultrasonic inspections for cracking of the mid-pivot bolt assembly and eventual replacement of the mid-pivot bolt assembly. This AD was prompted by a report that the left and right access doors of the spring beam mid-pivot bolt assembly for the No. 1 strut were inadvertently installed in the incorrect position during strut modification. We are issuing this AD to detect and correct incorrectly installed mid-pivot bolt assemblies on the spring beam on the outboard struts. Incorrectly installed bolt assemblies could lead to fatigue cracking and consequent fracturing of the mid-pivot bolt assembly, which could lead to loss of the spring beam load path and the possible separation of a strut and engine from the airplane during flight.
2005-18-07: The FAA is superseding an existing airworthiness directive (AD), which applies to certain McDonnell Douglas transport category airplanes. That AD currently requires repetitive inspections for cracking of the lower cargo doorjamb corners, and corrective action if necessary. That AD provides for optional terminating action for certain repetitive inspections for certain airplanes. For certain other airplanes, that AD requires modification of the lower cargo doorjamb corners. This new AD adds airplanes to the applicability. The existing AD was prompted by reports of fatigue cracks in the fuselage skin in the lower cargo doorjamb corners; this AD is prompted by the inadvertent omission of certain airplanes from the existing applicability. We are issuing this AD to ensure that the unsafe condition will be addressed on all affected airplanes so that cracking in the lower cargo doorjamb corners is detected and corrected before it can result in rapid decompression of the fuselage and consequent reduced structural integrity of the airplane. \n\nDATES: Effective October 7, 2005. \n\n\tOn April 29, 2004 (69 FR 15234, March 25, 2004), the Director of the Federal Register approved the incorporation by reference of McDonnell Douglas Service Bulletin DC8-53-078, Revision 01, dated January 25, 2001.
97-16-05: This amendment supersedes an existing airworthiness directive (AD), applicable to all Gulfstream Model G-159 (G-I) airplanes, that currently requires repetitive inspections to detect corrosion in the wing planks under the bottom wing center fairings, and repair, if necessary. This amendment requires the installation of a protective paint system which, when accomplished, will allow the inspections to be conducted at longer intervals. This amendment is prompted by the development of a modification that will improve the corrosion resistance of the subject area. The actions specified by this AD are intended to detect and prevent corrosion in the lower skins of the wing center section. If corrosion in this area remains unchecked, it could reduce the integrity of the wing-to-fuselage fitting, and consequently could lead to separation of the wing from the airplane.
96-22-11: This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 737 and 747 series airplanes, that requires replacement of Waterman hydraulic fuse assemblies with modified assemblies. This amendment is prompted by reports of failure of hydraulic system A and the standby system, due to corrosion on the magnesium piston of the hydraulic fuse and consequent failure of the fuse to close sufficiently to prevent the loss of hydraulic fluid from the system. The actions specified by this AD are intended to prevent such failure of the fuse, which could result in the failure of one or more hydraulic systems and resultant reduced controllability of the airplane.
98-09-04: This amendment adopts a new airworthiness directive (AD), applicable to certain Aerospatiale Model ATR72 series airplanes, that requires a one-time high frequency eddy current inspection to detect cracking of the lower fuselage structure, and repair, if necessary. This amendment also requires modification of certain fastener holes in the lower fuselage structure. This amendment is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified by this AD are intended to prevent reduced structural integrity of the airplane due to fatigue cracking in the lower fuselage structure.
2011-09-01: We are adopting a new airworthiness directive (AD) for the products listed above. This AD results from mandatory continuing airworthiness information (MCAI) originated 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: * * * * * * * * [S]ome Allowable Damage Limits and Repairs published in SRM Chapters 57-61-12 PB101 and 57-61-12 PB201 were de-validated starting from the SRM revision issued on January 2009. The terminology ``De-validated SRM'' used in this AD text refers to the SRM chapters mentioned above. In order to prevent complete inner aileron split due to possible failure or disbonding of the repairs on the inner aileron panels performed as per ``devalidated SRM'', which may result in flutter coupling of the free aileron part, this AD requires a one time inspection of the inner aileron panels to identify the presence of ``de-validated SRM'' repairs and, if necessary, to apply the associated corrective actions [repair]. The flutter coupling of the free aileron part might result in separation of the aileron from the airplane, degradation of airplane control, and increased workload for the flight crew. This AD requires actions that are intended to address the unsafe condition described in the MCAI.