Results
2023-21-08: The FAA is superseding Airworthiness Directive (AD) 2021-21-13 for certain Rolls-Royce Deutschland Ltd & Co KG (RRD) Model Trent 1000 engines. AD 2021-21-13 required the operator to revise the airworthiness limitation section (ALS) of their existing approved aircraft maintenance program (AMP) by incorporating the revised tasks of the applicable time limits manual (TLM) for each affected model engine. Since the FAA issued AD 2021-21-13, the manufacturer has revised the TLM, introducing new and more restrictive instructions. This AD is prompted by the manufacturer revising the engine TLM life limits of certain critical rotating parts. This AD requires revisions to the ALS of the operator's existing approved AMP, 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.
2023-22-11: The FAA is adopting a new airworthiness directive (AD) for certain Embraer S.A. (Embraer) Model EMB-505 airplanes. This AD was prompted by an occurrence of corrosion on the clutch retaining bolt of the aileron autopilot servo mount. This AD requires repetitively replacing the clutch retaining bolt and washer of the aileron autopilot servo mount, as specified in an Ag[ecirc]ncia Nacional de Avia[ccedil][atilde]o Civil (ANAC) AD, which is incorporated by reference. The FAA is issuing this AD to address the unsafe condition on these products.
97-07-03: This amendment supersedes Airworthiness Directive (AD) 81-11-04 that applies to The New Piper Aircraft, Inc. (Piper) Models PA31, PA31-300, PA31-325, and PA31-350 airplanes that have Cleveland nose wheel assembly part number (P/N) 40-76B installed. AD 81-11-04 currently requires inspecting the nose wheel flange for cracks. The repetitive inspections terminate by replacing the nose wheel assembly with Cleveland P/N 40-140, which is an improved design. This action is prompted by the lack of designation of Piper Model PA31P in the Applicability section of AD 81-11-04, and the subsequent failure of a nose wheel assembly on a Piper Model PA31P airplane during taxiing operations. The actions specified by this AD are intended to prevent the failure of the nose wheel, which if not corrected, could result in loss of control of the airplane during taxiing, take-off, or landing operations.
76-20-08: 76-20-08 LOCKHEED-CALIFORNIA COMPANY: Amendment 39-2742 as amended by Amendment 39-2916. Applies to Model L-1011-385 series airplanes, certificated in all categories. Compliance required as indicated. To prevent possible collapse of a main landing gear assembly due to failure of one or both of the two main landing gear upper side brace spherical bearing trunnion retaining bolts, accomplish the following: (a) Within the next 75 hours' time in service after the effective date of this AD accomplish the following checks, inspections, repairs or replacements as necessary, in accordance with accomplishment instructions of the Lockheed-California Company Alert Service Bulletin 093- 32-A115, dated September 1, 1976, or later FAA-approved revisions. (1) Prior to each flight, perform a visual check of each main landing gear upper side brace trunnion joint and verify that the two trunnion bearing cap retaining bolts P/Ns 76754-18-71 or 69680v18-71 or 69680-18-71 are in place and that no obvious structural deformation of the trunnion bearing caps P/Ns 1504393-109 or -110 has occurred. (2) If one or both retaining bolts P/Ns 76754-18-71 or 69680v18-71 or 69680-18-71 are missing or if a structural deformation of the trunnion bearing caps P/Ns 1504393-109 or -110 appears to have occurred, before further flight replace both retaining bolts and inspect the side brace support fitting P/Ns 1504393-107 or -108 and the trunnion bearing caps P/Ns 1504393-109 or -110 for structural damage and replace or repair as necessary the parts found to be damaged. (3) The checks required by this AD may be performed by a flight crew member. (b) Equivalent checks, inspections, repairs and replacements may be used when approved by the Chief, Aircraft Engineering Division, FAA, Western Region. (c) Compliance is required on or before March 31, 1978, unless already accomplished: Accomplish the modification of the main landing gear upper side brace trunnion jointsin accordance with Paragraph 2, Accomplishment Instructions, of the FAA approved Lockheed-California Company Service Bulletin 093-32-115, Revision I, dated March 18, 1977 or later FAA approved revisions. (d) Accomplishment of the modification of the upper side brace trunnion joints in accordance with paragraph (c) will remove the need for accomplishment of the requirements of paragraph (a). Amendment 39-2742 became effective October 18, 1976. This amendment 39-2916 becomes effective June 17, 1977.
2005-05-04: The FAA is adopting a new airworthiness directive (AD) for all Aerospatiale Model ATR 42-200, -300, and -320 series airplanes. This AD requires inspecting to determine the part and serial number of the swinging lever of the main landing gears (MLG) and replacing the swinging lever if necessary. This AD is prompted by a report that, on an airplane lined up for takeoff, the swinging lever of the left MLG collapsed when engine power was applied. We are issuing this AD to prevent fracture of the MLG swinging lever, which could result in collapse of the swinging lever and reduced structural integrity and possible collapse of the MLG during operations on the ground.
2023-21-09: The FAA is adopting a new airworthiness directive (AD) for all The Boeing Company Model 777-200, 777-200LR, 777-300, 777-300ER, and 777F series airplanes. This AD was prompted by a report of a ''FLAPS DRIVE'' caution message in flight due to the torque trip indicator of the No. 2 trailing edge (TE) flap transmission assembly being in the set position, which resulted in an air turn-back. This AD requires an inspection or records review to determine the serial numbers of the TE flap transmission and gearbox assemblies, and applicable on-condition corrective actions. This AD also limits the installation of affected parts. The FAA is issuing this AD to address the unsafe condition on these products.
95-19-02: This amendment adopts a new airworthiness directive (AD), applicable to certain Fokker Model F28 Mark 0100 series airplanes, that requires replacement of the flight control lock (FCL) handle and switch with a modified unit. This amendment is prompted by a report of sudden engagement of the FCL system during approach for landing. The actions specified by this AD are intended to prevent inadvertent engagement of the FCL system during flight and subsequent reduced controllability of the airplane.
2005-05-01: The FAA is adopting a new airworthiness directive (AD) for certain Boeing Model 757 series airplanes. This AD requires identification of the part number for the cable assembly for the lower anti-collision light, and related \ninvestigative and corrective actions if necessary. This AD is prompted by a report of damage caused by an electrical arc in a connector on the cable assembly for the lower anti-collision light. We are issuing this AD to prevent an electrical arc in the cable assembly for the lower anti-collision light, which could result in a fire in a flammable leakage zone of the airplane.
2015-02-25: We are adopting a new airworthiness directive (AD) for certain Bombardier, Inc. Model DHC-8-400 series airplanes. This AD was prompted by fuel system reviews conducted by the manufacturer. This AD requires replacing a fitting that is part of the refuel control solenoid valve assembly. We are issuing 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.
2000-22-01: This amendment adopts a new airworthiness directive (AD) that is applicable to certain Pratt & Whitney (PW) PW4000 series turbofan engines that are equipped with the high pressure compressor (HPC) cutback stator (CBS) configuration and that are used on Boeing 747, Boeing 767, and McDonnell Douglas MD-11 series airplanes. This action requires Operators to limit the number of engines with the HPC CBS configuration to one per airplane, and prohibits installation of engines with HPC modules modified after the effective date of this AD to incorporate the HPC CBS configuration. This amendment is prompted by reports of HPC surges in engines that have the HPC CBS configuration. The actions specified in this AD are intended to prevent a multiple-engine power loss due to HPC surges, which could result in engine power loss at a critical phase of flight such as takeoff or climb.
94-04-11: This amendment adopts a new airworthiness directive (AD) that applies to certain Twin Commander Aircraft Corporation (Twin Commander) Models 500S and 690B airplanes. This action requires removing a sample of the wing front spar lower cap (spar cap) material for examination, and, depending upon the results of that examination, inspecting or replacing the Airworthiness Directives: Twin Commander Aircraft Corporation Models 500S and 690B Airplanes . Reports of cracks caused by stress corrosion in the spar cap on several of the affected airplanes prompted this action. The actions specified by this AD are intended to prevent failure of the wing structure caused by cracks in the spar cap.
92-10-14: 92-10-14 LOCKHEED AERONAUTICAL SYSTEMS COMPANY-GEORGIA: Amendment 39-8249. Docket No. 91-NM-69-AD. Supersedes AD 89-15-03, Amendment 39- 6265. Applicability: Model 382 series airplanes, serial numbers 3946 through 5305, inclusive, certificated in any category. Compliance: Required as indicated, unless accomplished previously. To prevent fatigue cracking and subsequent decompression of the airplane, accomplish the following: (a) For airplanes that had accumulated 6,300 hours time-in-service prior to July 31, 1989 (the effective date of AD 89-15-03, Amendment 39-6265), within the next 10 hours time-in-service after July 31, 1989, accomplish the following: (1) Incorporate the following statement into the Limitations Section of the FAA-approved Airplane Flight Manual (AFM). This may be accomplished by including a copy of this AD in the AFM. "Aircraft cabin operating pressure is limited to 10 inches of mercury." (2) Temporarily reduce cabin operating pressure in accordance with paragraph (a)(1) of this AD. (b) For all other airplanes not subject to paragraph (a) of this AD: Within 10 hours time-in-service after the effective date of this AD, or prior to the accumulation of 6,300 hours time- in-service, whichever occurs later, accomplish the following: (1) Incorporate the following into the Limitations Section of the FAA-approved Airplane Flight Manual (AFM). This may be accomplished by including a copy of this AD in the AFM. "Aircraft cabin operating pressure is limited to 10 inches of mercury." (2) Temporarily reduce cabin operating pressure in accordance with paragraph (b)(1) of this AD. (c) For airplanes that had accumulated 6,300 hours time-in-service prior to July 31, 1989 (the effective date of AD 89-15-03, Amendment 39-6265), and have not been inspected in accordance with AD 89-15-03: Within 45 days after the effective date of this AD, perform an inspection of the following areas of the pressurized fuselage fairing support (FS) structure according to the specified Work Card procedures of Standard Maintenance Publication (SMP) 515-A/C, as specified in Lockheed Aeronautical Systems Company (LASC)-Georgia Service Bulletin 382-53-50, Revision 1, dated December 13, 1991: FS477 to FS517 General Area Work Card SP-126 FS477 Upper Web Flange Work Card SP-224 FS497 Overhead Bulkhead Web and Tee-Outboard S/N 3946 through S/N 4932 Work Card SP-224 S/N 4933 through S/N 5305 Work Card SP-126 FS497 Overhead Bulkhead Upper Attach Angle Work Card SP-224 (d) For airplanes that have been inspected in accordance with AD 89-15-03: Within 3,000 hours time-in-service since the last inspection, perform an inspection of the following areas of the pressurized fuselage FS structure according to the specified Work Card procedures of Hercules Maintenance Program Plan SMP 515-A/C, as shown in LASC-Georgia Service Bulletin 382-53-50, Revision 1, dated December 13, 1991: FS477 to FS517 General Area Work Card SP-126 FS477 Upper Web Flange Work Card SP-224 FS497 Overhead Bulkhead Web and Tee Outboard S/N 3946 through S/N 4932 Work Card SP-224 S/N 4933 through S/N 5305 Work Card SP-126 FS497 Overhead Bulkhead Upper Attach Angle Work Card SP-224 (e) For all other airplanes, not subject to paragraph (c) or (d) of this AD: Prior to the accumulation of 6,300 hours time-in-service, or within 45 days after the effective date of this AD, whichever occurs later, perform an inspection of the following areas of the pressurized fuselage FS structure according to the specified Work Card procedures of Hercules Maintenance Program Plan SMP 515-A/C, as shown in LASC-Georgia Service Bulletin 382-53-50, Revision 1, dated December 13, 1991: FS477 to FS517 General Area Work Card SP-126 FS477 Upper Web Flange Work Card SP-224 FS497 Overhead BulkheadWeb and Tee Outboard S/N 3946 through S/N 4932 Work Card SP-224 S/N 4933 through S/N 5305 Work Card SP-126 FS497 Overhead Bulkhead Upper Attach Angle Work Card SP-224 (f) For all airplanes: At intervals not to exceed 3,600 hours time-in-service, repeat the inspections specified in, and in accordance with, the specified Work Card procedures of Hercules Maintenance Program Plan SMP 515-A/C, as shown in LASC-Georgia Service Bulletin 382-53-50, Revision 1, dated December 13, 1991: FS477 to FS517 General Area Work Card SP-126 FS477 Upper Web Flange Work Card SP-224 FS497 Overhead Bulkhead Web and Tee Outboard S/N 3946 through S/N 4932 Work Card SP-224 S/N 4933 through S/N 5305 Work Card SP-126 FS497 Overhead Bulkhead Upper Attach Angle Work Card SP-224 (g) If cracks are found, prior to further flight, repair in accordance with the procedures contained in Appendix A of LASC-Georgia Service Bulletin 382-53-50, Revision 1, dated December 13, 1991; or in a manner approved by the Manager, Atlanta Aircraft Certification Office, ACE-115A, FAA, Small Airplane Directorate. After repair, continue to perform the repetitive inspections required by paragraph (f) of this AD. (h) The limitations required by paragraphs (a) and (b) of this AD may be removed if one of the conditions specified in either paragraph (h)(1), (h)(2), (h)(3), or (h)(4) of this AD, is applicable: (1) If no cracks were found as a result of the inspections performed in accordance with AD 89-15-03, Amendment 39-6265; or (2) If any cracks were found as a result of the inspections performed in accordance with AD 89-15-03, Amendment 39-6265 were repaired in accordance with paragraph C. of that AD; or (3) If no cracks are found as a result of the inspections required by paragraphs (c), (d), (e), or (f) of this AD; or (4) If cracks are found as a result of the inspections required by paragraphs (c), (d), (e), or (f) of this AD, and they are repaired in accordance with paragraph (g) of this AD. (i) An alternative method of compliance or adjustment of the compliance time, which provides an acceptable level of safety, may be used when approved by the Manager, Atlanta Aircraft Certification Office (ACO), ACE-115A, FAA, Small Airplane Directorate. The request shall be forwarded through an FAA Principal Maintenance Inspector, who may concur or comment and then send it to the Manager, Atlanta ACO. (j) Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate the airplane to a location where the requirements of this AD can be accomplished. (k) The inspections and repairs shall be done in accordance with Lockheed Aeronautical Systems Company (LASC)-Georgia Service Bulletin 382-53-50, Revision 1, dated December 13, 1991, which includes the following list of effective pages: Page Number Revision Level Date 1 - 11, A7, A8 1 December 13,1991 A-1 Original February 14, 1990 A2 - A6, A9 - A33 Original Undated This incorporation by reference was approved by the Director of the Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR Part 51. Copies may be obtained from Lockheed Aeronautical Systems Company-Georgia, Attn: Commercial and Customer Support, Dept. 73-05, Zone 0199, 86 South Cobb Drive, Marietta, Georgia 30063. Copies may be inspected at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, Washington; or at the FAA, Small Airplane Directorate, Atlanta Aircraft Certification Office, 1669 Phoenix Parkway, Suite 210C, Atlanta, Georgia; or at the Office of the Federal Register, 1100 L Street NW., Room 8401, Washington, DC. (l) This amendment becomes effective on June 29, 1992.
2005-04-16: The FAA is adopting a new airworthiness directive (AD) for certain Pilatus Aircraft Ltd. Models PC-12 and PC-12/45 airplanes. This AD requires you to do a one-time inspection of the windshield de-ice wiring system for heat damage and incorrect wire sizes and to replace any wires that are damaged or the incorrect size. This AD results from mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for Switzerland. We are issuing this AD to detect and replace windshield de-ice wiring of the incorrect size, which could result in heat damage of the windshield de-ice wiring. This failure could lead to possible fire in the overhead panel of the flight compartment.
2023-21-01: The FAA is superseding Airworthiness Directive (AD) 2020-01- 13, which applied to all Dassault Aviation Model MYSTERE-FALCON 200 airplanes. AD 2020-01-13 required revising the existing maintenance or inspection program, as applicable, to incorporate new or more restrictive airworthiness limitations. This AD was prompted by a determination that new or more restrictive airworthiness limitations are necessary. This AD continues to require the actions in AD 2020-01- 13 and require revising the existing maintenance or inspection program, as applicable, to incorporate new or more restrictive airworthiness limitations; 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.
92-01-10: 92-01-10 DASSAULT AVIATION (formerly Avions Marcel Dassault-Breguet Aviation): Amendment 39-8134. Docket 91-NM-256-AD. Applicability: Model Fan Jet Falcon Series G and Mystere Falcon 200 series airplanes, certificated in any category. Compliance: Required as indicated, unless accomplished previously. To prevent in-flight separation of the engine cowls, accomplish the following: (a) Within 14 days after the effective date of this AD, and thereafter at intervals not to exceed 7 days, perform an inspection of the hinges and fasteners (latches and aprons) on the engine cowls to verify their integrity, in accordance with the airplane maintenance manual (refer to Work Card 741-0, Revision A-1-b, dated December 1990). Replace discrepant hinges or fasteners (latches or aprons) prior to further flight, in accordance with the airplane maintenance manual. (b) Accomplishment of subparagraphs (b)(1), (b)(2), and (b)(3) of this AD constitutes terminating action for therepetitive inspections required by paragraph (a) of this AD. (1) Reinforce the latches in accordance with Dassault Aviation Service Bulletin F200- 59 (ATA Number F200-54-4), Revision 1, dated September 18, 1991. (2) Install new hinge pin latching systems in accordance with Dassault Aviation Service Bulletin F200-78 (ATA Number F200-54-7), Revision 1, dated September 18, 1991. (3) Reinforce the small aprons and modify the hinged cowl attachments in accordance with Dassault Aviation Service Bulletin F200-87 (ATA Number F200-54-10), dated September 18, 1991. (c) An alternative method of compliance or adjustment of the compliance time, which provides an acceptable level of safety, may be used when approved by the Manager, Standardization Branch, ANM- 113, FAA, Transport Airplane Directorate. The request shall be forwarded through an FAA Principal Maintenance Inspector, who may concur or comment and then send it to the Manager, Standardization Branch, ANM-113.(d) Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate the airplane to a location where the requirements of this AD can be accomplished. (e) The modifications required by this AD shall be done in accordance with Dassault Aviation Service Bulletin F200-59 (ATA Number F200-54-4), Revision 1, dated September 18, 1991; Dassault Aviation Service Bulletin F200-78 (ATA Number F200-54-7), Revision 1, dated September 18, 1991; and Dassault Aviation Service Bulletin F200-87 (ATA Number F200-54-10), dated September 18, 1991. This incorporation by reference was approved by the Director of the Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR Part 51. Copies may be obtained from Falcon Jet Corporation, Customer Support Department, Teterboro Airport, Teterboro, New Jersey 07608. Copies may be inspected at the FAA, Transport Airplane Directorate, 1601 Lind Avenue S.W., Renton, Washington; or at the Office of the Federal Register, 1100 L StreetN.W., Room 8401, Washington, D.C. (g) This amendment (39-8134, AD 92-01-10) becomes effective on January 24, 1992.
2000-20-18: This amendment adopts a new airworthiness directive (AD) for Bell Helicopter Textron Canada (BHTC) Model 407 helicopters. This AD requires inspecting the brackets that attach each horizontal stabilizer slat (slat) to the stabilizer for a crack and replacing the slat assembly if a crack is found. Installing airworthy segmented slat assemblies would be required prior to flight after December 31, 2000 and would constitute terminating action for the requirements of this AD. This amendment is prompted by an incident in which a slat separated from a helicopter. The actions specified by this AD are intended to prevent a slat from separating, impact with a main or tail rotor blade, and subsequent loss of control of the helicopter.
2005-04-14: The FAA is superseding an existing airworthiness directive (AD) that applies to certain Boeing Model 757-200, 757-200CB, and 757- 200PF series airplanes. The existing AD currently requires repetitive detailed inspections to detect horizontal or vertical movement of the shims at the joint of the mid-bulkhead and the upper link fittings, and corrective action if necessary; or certain alternative actions that terminate the requirement for the repetitive inspections. This new AD continues to require those repetitive inspections; decreases the allowable tolerance for shim migration; and adds new repetitive detailed inspections for cracking of the entire mid-bulkhead, and repair if necessary. This new AD also adds additional airplanes to the applicability of the AD. This AD is prompted by reports of cracks in the mid-bulkhead lower vertical flange common to the lower chord and stiffener and reports of cracking at other locations on the mid- bulkhead. We are issuing this AD to detectand correct migration of shims at the joint of the mid-bulkhead and the upper link fittings and cracking of the mid-bulkhead, which could result in cracking of the strut and consequent loss of the strut and engine. \n\nDATES: Effective March 15, 2005. \n\n\tThe incorporation by reference of Boeing Service Bulletin 757- 54A0039, Revision 2, dated December 2, 2004; and Boeing Service Bulletin 757-54A0039, Revision 3, dated January 13, 2005; as listed in the AD are approved by the Director of the Federal Register as of March 15, 2005. \n\n\tOn April 18, 2003 (68 FR 16200, April 3, 2003), the Director of the Federal Register approved the incorporation by reference of Boeing Alert Service Bulletin 757-54A0039, Revision 1, dated June 20, 2002. \n\n\tWe must receive any comments on this AD by April 29, 2005.
2023-21-04: The FAA is adopting a new airworthiness directive (AD) for certain Embraer S.A. (Embraer) Model EMB-505 airplanes. This AD was prompted by occurrences of an uncommanded change in the setting of the barometric pressure in both primary flight displays (PFDs). This AD requires installing a new version of the airplane avionics system software, as specified in an Ag[ecirc]ncia Nacional de Avia[ccedil][atilde]o Civil (ANAC) AD, which is incorporated by reference. The FAA is issuing this AD to address the unsafe condition on these products.
2023-20-10: The FAA is adopting a new airworthiness directive (AD) for certain Bombardier, Inc., Model BD-700-2A12 airplanes. This AD was prompted by a report that some of the multi-function spoiler (MFS) anti-rotation plates failed in-service due to a thin wall design. This AD requires replacing the MFS anti-rotation plates, inspecting the MFS anti-rotation plates for cracking and hinge bolts for evidence of rotation, accomplishing applicable corrective actions, and performing a functional test of the MFS control surfaces. The FAA is issuing this AD to address the unsafe condition on these products.
2000-20-19: This amendment supersedes an existing airworthiness directive (AD) for Eurocopter France Model AS-350B, BA, B1, B2, C, D, and D1, and AS-355E, F, F1, and F2 helicopters. That AD currently requires inspections of the main rotor head components, the main gearbox (MGB) suspension bars, and the ground resonance prevention system components. This amendment requires those same inspections, but would also apply to Model AS-350B3 and AS-355N helicopters. This amendment is prompted by the inadvertent omission of those model helicopters from the previous AD. The actions specified by this AD are intended to prevent ground resonance due to reduced structural stiffness, which could lead to failure of a main rotor head or MGB suspension component and subsequent loss of control of the helicopter.
90-21-14: 90-21-14 AIRBUS INDUSTRIE: Amendment 39-6771. Docket No. 90-NM-94-AD. Applicability: Model A320 series airplanes, which have not incorporated Modification 21892, certificated in any category. Compliance: Required within 30 days after the effective date of this AD, unless previously accomplished. To prevent failure of the ram air turbine (RAT) to deploy on command due to a malfunction of the extension jack, accomplish the following: A. Remove ejection jack, Part Number (P/N) 114160003, and replace it with a new or modified ejection jack, P/N 114160004 or 114160005, in accordance with Airbus Industrie Service Bulletin A320-29-1030, dated February 15, 1990. B. An alternate means of compliance or adjustment of the compliance time, which provides an acceptable level of safety, may be used when approved by the Manager, Standardization Branch, ANM-113, FAA, Transport Airplane Directorate. NOTE: The request should be submitted directly to the Manager, Standardization Branch, ANM-113, and a copy sent to the cognizant FAA Principal Inspector (PI). The PI will then forward comments or concurrence to the Manager, Standardization Branch, ANM-113. C. Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes to a base in order to comply with the requirements of this AD. All persons affected by this directive who have not already received the appropriate service documents from the manufacturer may obtain copies upon request to Airbus Industrie, Airbus Support Division, Avenue Didier Daurat, 31700 Blagnac, France. These documents may be examined at the FAA, Northwest Mountain Region, Transport Airplane Directorate, 1601 Lind Avenue S.W., Renton, Washington. This amendment (39-6771, AD 90-21-14) becomes effective on November 19, 1990.
2023-20-12: The FAA is superseding Airworthiness Directive (AD) 2022-18- 09, which applied to certain Airbus SAS Model A319-111, -112, -113, - 114, -115, -131, -132, and -133; A320-211, -212, -214, -216, -231, - 232, -233, -251N, and -271N; and A321-111, -112, -131, -211, -212, - 213, -231, -232, -251N, and -253N airplanes. AD 2022-18-09 continued to require the actions in AD 2019-26-01 and AD 2021-23-15, and added airplanes to the applicability. Since the FAA issued AD 2022-18-09, it was determined that additional airplanes and galleys are subject to the unsafe condition, and a compliance time for certain airplanes should be extended. This AD continues to require the actions in AD 2022-18-09 and requires expanding the applicability, obtaining and following additional instructions for certain modified airplanes, and extending the compliance time for certain airplanes, 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.
2000-20-09: This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 757 series airplanes, that requires modification of the nacelle strut and wing structure. This amendment is prompted by reports indicating that the actual operational loads applied to the nacelle are higher than the analytical loads that were used during the initial design. Such an increase in loading can lead to fatigue cracking in primary strut structure prior to an airplane reaching its design service objective. The actions specified by this AD are intended to prevent fatigue cracking in primary strut structure and consequent reduced structural integrity of the strut.
2000-20-16: This amendment adopts a new airworthiness directive (AD) that is applicable to certain Boeing Model 757-200 series airplanes. This action requires repetitive inspections of the cargo loader system in the forward and aft cargo compartments to detect discrepancies, and corrective actions, if necessary. This action is necessary to detect and correct such discrepancies, which could result in reduced structural integrity of the fuselage and consequent cabin depressurization.
81-12-02: 81-12-02 LOCKHEED: Amendment 39-4127. Applies to Model 382 series airplanes, Serial Numbers 3946 and 4101 through 4871 except 4834, 4839, 4850, and 4853, certificated in all categories. Compliance required during the next "B" or "C" inspection/check, whichever occurs first after the effective date of this AD, unless already accomplished. To prevent possible failure of the longerons, accomplish the following: a. Inspect the center fuselage upper longeron splice bolts, immediately aft of fuselage station 597.00, along buttock line 20.00, on each side of the airplane, for correct installation, and determine the condition category of the airplane in accordance with Lockheed-Georgia Company Service Bulletin No. A382-53-29, Revision 1, dated April 24, 1981, or later FAA approved revision. b. If an out-of-tolerance condition is found to exist, accomplish one of the following: 1. Based on the condition category, placard the airplane in accordance with Lockheed-GeorgiaCompany Service Bulletin No. A382-53-29, Revision 1, dated April 24, 1981, or later FAA approved revision, and incorporate Airplane Flight Manual (AFM) Supplement No. 382-11, dated February 18, 1981. The AFM Supplement may be obtained from the Lockheed- Georgia Company, Marietta, Georgia 30063. If repairs are accomplished in accordance with b.2., placards and AFM Supplement may be discarded. 2. Repair the airplane in accordance with Lockheed-Georgia Company Service Bulletin No. A382-53-29, Revision 1, dated April 24, 1981, or later FAA approved revision, or an alternate method of compliance, approved by the Chief, Engineering and Manufacturing Branch, Southern Region. c. An alternate method of compliance may be approved by the Chief, Engineering and Manufacturing Branch, Southern Region. d. Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes to a base in order to comply with the requirements of this AD. This amendment becomes effective June 5, 1981.