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.
|