Results
2024-15-08: The FAA is adopting a new airworthiness directive (AD) for all Airbus Helicopters Model AS350B, AS350BA, AS350B1, AS350B2, AS350D, AS355E, AS355F, AS355F1, AS355F2, and AS355N helicopters. This AD was prompted by reports of debonding on the leading edge protection of certain part-numbered main rotor blades (MRBs). This AD requires repetitively tap inspecting the MRB and, depending on the results, taking corrective action. This AD also prohibits installing an affected MRB on any helicopter unless its requirements are met. These actions are 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.
2017-04-11: We are adopting a new airworthiness directive (AD) all The Boeing Company Model 737-600, -700, -700C, -800, and -900 series airplanes. This AD was prompted by reports of paint deterioration on the surface of the main landing gear (MLG) and the early onset of corrosion in the trunnion bore of the MLG outer cylinder. This AD requires identifying affected parts, repetitive external surface detailed inspections for damage of affected parts, and related investigative and corrective actions if necessary. For certain airplanes, this AD also requires a detailed inspection and bushing replacement of the trunnion bore, and related investigative and corrective actions if necessary. We are issuing this AD to address the unsafe condition on these products.
75-15-05: 75-15-05 MCDONNELL DOUGLAS, LOCKHEED, BOEING, AND AIRBUS INDUSTRIE: Amendment 39-2262 as amended by Amendment 39-2739. Applies to McDonnell Douglas Model DC-10 Series, Lockheed Model L-1011 Series, Boeing Model B-747 Series, and Airbus Industrie Model A-300 Series airplanes certificated in all categories. \n\n\tUnless already accomplished, compliance is required on or before December 31, 1977, or in accordance with a schedule of accomplishment approved by the Chief, Aircraft Engineering Division, FAA Western Region, for McDonnell Douglas Model DC-10 Series and Lockheed Model L-1011 Series airplanes; the Chief, Engineering and Manufacturing Branch, FAA Northwest Region, for Boeing Model B-747 Series airplanes, or the Chief, Aircraft Certification Staff, FAA Europe, Africa, and Middle East Region, for Airbus Industrie Model A-300 Series airplanes, but not later than December 31, 1978. \n\n\tTo improve the capability of the passenger and crew compartment floors to withstand, without collapse, an in-flight depressurization caused by the sudden opening of a large hole in the lower deck cargo compartment, comply with paragraphs (a) or (b) as appropriate: \n\n\t(a)\tIncorporate the modification specified in paragraph (a)(1), taking into consideration the factors specified in paragraphs (a)(2) and (a)(3): \n\n\t\t(1)\tProvide additional venting capability or an increase in floor strength, or both, as necessary, to prevent floor collapse caused by the decompression effects resulting from a sudden large in-flight opening in any portion of any lower deck cargo compartment. \n\n\t\t(2)\tThe size of openings to be considered must include the maximum size opening expected in service, but the maximum size opening considered may not have an area of less than 20 square feet. \n\n\t\t(3)\tEach compartment and ambient condition pressure differential expected in service must be considered. \n\n\t\t(4)\tIn showing compliance with paragraphs (a)(1), (a)(2), and (a)(3), damage to the floor is permitted if the degree of damage will not preclude continued safe flight and landing, or result in injury to occupants. \n\n\t(b)\tFor the all-cargo version of each of the above airplanes, it is satisfactory to comply with paragraph (a)(2) by showing that continued safe flight and landing is assured and that no injury to any occupant results in lieu of showing no floor collapse. Appropriate limitations must be added to the flight manual for the particular airplane approved under the all-cargo provisions. \n\n\t(c)\tThe modification and determinations required under paragraphs (a) and (b) of this AD must be approved by the Chief, Aircraft Engineering Division, FAA Western Region, for McDonnell Douglas Model DC-10 Series and Lockheed Model L-1011 Series airplanes; the Chief, Engineering and Manufacturing Branch, FAA Northwest Region, for Boeing Model B-747 Series airplanes; or the Chief, Aircraft Certification Staff, FAA Europe, Africa, and Middle East Region, for Airbus Industrie Model A-300 Series airplanes. \n\n\tAmendment 39-2262 became effective August 11, 1975. \n\n\tThis amendment 39-2739 becomes effective November 3, 1976.
2017-04-07: We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 757 airplanes. This AD was prompted by reports of single and multiple uncommanded spoiler panel extensions during flight when there was a hydraulic system failure. This AD requires replacing certain spoiler power control units (PCUs) with new or changed PCUs. We are issuing this AD to address the unsafe condition on these products.
2024-14-10: The FAA is adopting a new airworthiness directive (AD) for certain Airbus SAS Model A350-1041 airplanes. This AD was prompted by a report of a production quality escape that could lead to deficiencies in surface protection on several left-hand and right-hand flap support structures. This AD requires a one-time detailed inspection of the affected parts at certain locations for evidence of corrosion or damage to the surface protection, repetitive detailed inspections of the affected parts at certain other locations for evidence of corrosion, and the accomplishment of applicable corrective actions, 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.
2017-02-12: We are adopting a new airworthiness directive (AD) for all The Boeing Company Model 737-300, -400, and -500 series airplanes. This AD was prompted by reports of intergranular cracks on the front spar chord lugs of the outboard horizontal stabilizer. This AD requires repetitive inspections of the front spar chord lugs and lug bores of the horizontal stabilizer, and repair if necessary. We are issuing this AD to address the unsafe condition on these products.
75-16-18: 75-16-18 DOWTY ROTOL: Amendment 39-2292. Applies to Dowty Rotol Propellers R245/4-40-4.5/13, R259/4-40-4.5/17 and R209/4-40-4.5/2 used on Convair 600 series and YS-11 series airplanes. Compliance required as indicated within the next 300 hours propeller time in service after the effective date of this AD or before the accumulation of 5300 hours propeller time in service, whichever occurs later, unless already accomplished. To prevent propeller blade failures from occurring in flight: (a) Inspect and test the following serial number blades for cracks or forging defects in accordance with Appendix B of Dowty Rotol Alert Service Bulletin 61-A862, Revision 1, dated May 22, 1975, (hereafter Dowty Rotol Bulletin 61-A862) or later FAA-approved revision, or an equivalent approved by the Chief, Aircraft Certification Staff, FAA, Europe, Africa and Middle East Region, c/o American Embassy, APO New York, N.Y. 09667. YS11 & 11A propeller blades with blade serial numbers:A124879 A125027 A125113 A125242 A125292 A12556 A125720 A124882 A125028 A125115 A125243 A125293 A125570 A125762 A124884 A125035 A125116 A125244 A125294 A125583 A125780 A124890 A125036 A125121 A125245 A125296 A125585 A125822 A124892 A125037 A125122 A125246 A125298 A125587 A125824 A124893 A125038 A125123 A125299 A125247 A125589 A125833 A124894 A125039 A125141 A125248 A125302 A125590 A125834 A124906 A125040 A125142 A125249 A125304 A125611 A125835 A124907 A125047 A125143 A125251 A125316 A125612 A125842 A124908 A125048 A125149 A125252 A125317 A125613 A125843 A124909 A125049 A125151 A125262 A125318 A125614 A125900 A124910 A125050 A125152 A125263 A125527 A125628 A125908 A124928 A125051 A125159 A125264 A125528 A125629 A125911 A124929 A125057 A125160 A125272 A125538 A125642 A125930 A125008 A125058 A125275 A125540 A125654 A125654 A125956 A125009 A125059 A125165 A125276 A125547 A12565 A125982 A125010 A125061 A125166 A125283 A125549 A125674 A125984 A125016 A125062 A125167 A125285 A125556 A125676 A125985 A125017 A125090 A125169 A125287 A125557 A125677 A125989 A125018 A125091 A125171 A125288 A125565 A125708 A126089 A125019 A125093 A125290 A125290 A125566 A125709 A126090 A125025 A125112 A125239 A125291 A125567 A125718 A126122 Convair propeller blades with blade serial numbers: A125447 A125661 A125448 A125662 A125458 A125699 A125462 A125844 (b) If cracks or forging defects are found, comply with (1) or (2) as appropriate: (1) Repair the blade in accordance with Appendix B of Dowty Rotol Bulletin 61-A862 or later FAA-approved revision or an FAA equivalent approved by the Chief, Aircraft Certification Staff, FAA, Europe, Africa and Middle East Region, c/o American Embassy, APO New York, N.Y. 09667. (2) Remove the blade from service if repair cannot be made in accordance with paragraph (b)(1). (c) Blades may be returned to service following inspection and test if found free of cracks or forging defects or have been repaired in accordance with paragraph (b)(1) of this AD. This amendment becomes effective July 29, 1975.
67-29-01: 67-29-01 BEECHCRAFT: Amendment 39-574. Applies to Model 95-55 (Serial Numbers TC-1 through TC-190), 95-A55 (Serial Numbers TC-191 through TC-501 except TC- 350 and TC-371), 95-B55 (Serial Numbers TC-371, TC-502 through TC-1042), 95-C55 (Serial Numbers TC-350, TE-1 through TE-451), and 56TC (Serial Numbers TG-1 through TG-51) airplanes with 250 hours' or more time in service. Compliance required as indicated. To detect cracks in the rudder spar web, within the next 25 hours' time in service after the effective date of this AD, unless already accomplished, and thereafter at intervals of not to exceed 250 hours' time in service from the date of the last inspection, accomplish the following: (a) Inspect visually the rudder spar web, in the area under and adjacent to the upper and the center hinge attach points. (b) If a crack is found during an inspection required by Paragraph (a), before further flight, accomplish one of the following - (1) Modify the rudderspar web in accordance with the method contained in Beechcraft Service Bulletin 67-34, Rev. 1, or any other method approved as an equivalent by the Chief, Engineering and Manufacturing Branch, Federal Aviation Administration, Central Region; or (2) Replace the rudder spar web with one that has been modified in accordance with Paragraph (b)(1) of this airworthiness directive. (c) When either the modification or replacement prescribed in Paragraph (b) of this AD have been accomplished, the inspections required by this airworthiness directive are no longer required. Effective October 27, 1967. Revised April 5, 1968.
2017-02-02: We are superseding Airworthiness Directive (AD) 2005-13-30, for all The Boeing Company Model 737-100, -200, and -200C series airplanes. AD 2005-13-30 required repetitive inspections to detect discrepancies of certain fuselage skin panels located just aft of the wheel well, and repair if necessary. This new AD adds new fuselage skin inspections for cracking, inspections to detect missing or loose fasteners and any disbonding or cracking of bonded doublers, permanent repairs of time-limited repairs, related investigative and corrective actions if necessary, and skin panel replacement. This AD was prompted by an evaluation by the design approval holder (DAH) indicating that the fuselage skin is subject to widespread fatigue damage (WFD), and reports of cracks at the chem-milled steps in the fuselage skin. We are issuing this AD to address the unsafe condition on these products.
2024-15-03: The FAA is superseding Airworthiness Directive (AD) 2019-16- 05, which applied to all The Boeing Company Model 777 airplanes. AD 2019-16-05 required identifying the part number, and the serial number if applicable, of the Captain's and First Officer's seats, and applicable on-condition actions for affected seats. This AD was prompted by reports of uncommanded fore/aft movement of the Captain's and First Officer's seats. This AD retains the requirements of AD 2019- 16-05 and adds an inspection of previously omitted part numbers. The FAA is issuing this AD to address the unsafe condition on these products.