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95-17-12: 95-17-12 AIRBUS INDUSTRIE: Amendment 39-9342. Docket 94-NM-143-AD. Applicability: Model A320 series airplanes on which Airbus Modification 22621 (reference Airbus Service Bulletin A320-27-1041) and Airbus Modification 23556 (reference Airbus Service Bulletin A320-29-1058) have not been installed, certificated in any category. NOTE 1: This AD applies to each airplane identified in the preceding applicability provision, regardless of whether it has been modified, altered, or repaired in the area subject to the requirements of this AD. For airplanes that have been modified, altered, or repaired so that the performance of the requirements of this AD is affected, the owner/operator must use the authority provided in paragraph (b) of this AD to request approval from the FAA. This approval may address either no action, if the current configuration eliminates the unsafe condition; or different actions necessary to address the unsafe condition described in this AD. Such a request should include an assessment of the effect of the changed configuration on the unsafe condition addressed by this AD. In no case does the presence of any modification, alteration, or repair remove any airplane from the applicability of this AD. Compliance: Required as indicated, unless accomplished previously. To prevent loss of the pilot's ability to control the moveable surfaces of the trimmable horizontal stabilizer (THS), accomplish the following: (a) Within 3,500 flight hours after the effective date of this AD, modify the THS in accordance with Airbus Service Bulletin A320-29-1058, July 16, 1993, and Airbus Service Bulletin A320-27-1041, Revision 2, dated April 20, 1994. (b) An alternative method of compliance or adjustment of the compliance time that provides an acceptable level of safety may be used if approved by the Manager, Standardization Branch, ANM-113, FAA, Transport Airplane Directorate. Operators shall submit their requests through an appropriate FAA Principal Maintenance Inspector, who may add comments and then send it to the Manager, Standardization Branch, ANM-113. NOTE 2: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Standardization Branch, ANM-113. (c) Special flight permits may be issued in accordance with sections 21.197 and 21.199 of the Federal Aviation Regulations (14 CFR 21.197 and 21.199) to operate the airplane to a location where the requirements of this AD can be accomplished. (d) The modification shall be done in accordance with Airbus Service Bulletin A320-29-1058, July 16, 1993, and Airbus Service Bulletin A320-27-1041, Revision 2, dated April 20, 1994. 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 Airbus Industrie, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France. Copies may be inspected at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC. (e) This amendment becomes effective on September 21, 1995.
98-18-21: This amendment adopts a new airworthiness directive (AD), applicable to all CASA Model C-212 series airplanes, that requires implementation of a corrosion prevention and control program either by accomplishing specific inspections or by revising the maintenance inspection program to include such a program. This amendment is prompted by reports of incidents involving corrosion and fatigue cracking in transport category airplanes that are approaching or have exceeded their economic design goal; these incidents have jeopardized the airworthiness of the affected airplanes. The actions specified by this AD are intended to prevent degradation of the structural capabilities of the airplane due to the problems associated with corrosion.
2019-18-08: The FAA is superseding Airworthiness Directive (AD) 2019-16-04 for all Engine Alliance (EA) GP7270 and GP7277 model turbofan engines. AD 2019-16-04 required a visual inspection of the 1st-stage low- pressure compressor (LPC) rotor assembly, referred to after this as the ``engine fan hub assembly,'' for damage, a one-time eddy current inspection (ECI) of the engine fan hub blade slot bottom and blade slot front edge for cracks; and removal of parts if damage or defects are found. AD 2019-16-04 also required replacement of the engine fan hub blade lock assembly for certain GP7270 and GP7277 model turbofan engines. This AD, for certain GP7270 and GP7277 model turbofan engines, reduces the compliance time for the initial ECI and requires repetitive ECIs of the engine fan hub blade slot bottom and blade slot front edge for cracks. This AD also retains the visual inspection requirements of the engine fan hub assembly for all GP7270 and GP7277 model turbofan engines. This AD was prompted by an uncontained failure of the engine fan hub. The FAA is issuing this AD to address the unsafe condition on these products.
98-07-03: This document corrects a technical bulletin date in airworthiness directive (AD) 98-07-03 that was incorrectly published in the Federal Register on March 24, 1998 (63 FR 14026). This AD is applicable to Bell Helicopter Textron, Inc. Model 412 helicopters and Agusta S.p.A Model AB 412 helicopters and requires a temporary reduction of the never-exceed velocity (Vne) limitation until an inspection of the tail rotor yoke (yoke) assembly for fatigue damage and installation of a redesigned yoke flapping stop are accomplished. Recurring periodic and special inspections to detect occurrences of yoke overload are also required.
2007-07-04: The FAA is adopting a new airworthiness directive (AD) for all McDonnell Douglas Model MD-11 and -11F airplanes. This AD requires revising the maintenance inspection program that provides for inspection of principal structural elements (PSEs) and replacement of safe-life parts, to incorporate a new revision to the MD-11 Airworthiness Limitations Instructions. The revision reduces inspection intervals for fatigue cracking of certain PSEs, and expands the inspection area for a certain other PSE. This AD results from a revised damage tolerance analysis. We are issuing this AD to detect and correct fatigue cracking of certain PSEs, which could adversely affect the structural integrity of the airplane.
2007-07-01: The FAA is adopting a new airworthiness directive (AD) for certain Airbus Model A300-600 airplanes. This AD requires an inspection to determine if certain spoiler actuators having certain part numbers are installed, and eventual replacement of all affected actuators. This AD results from failure of a distribution block, which was detected during fatigue qualification tests of certain spoiler actuators. We are issuing this AD to prevent failure of the distribution block, which could result in leakage of the hydraulic fluid that supplies those actuators. This failure could cause failure of one of the three spoiler actuators and the associated hydraulic circuits, which could result in loss of those hydraulic circuits and consequent reduced controllability of the airplane.
99-14-07: This amendment adopts a new airworthiness directive (AD), applicable to all Dassault Model Falcon 2000 series airplanes; and certain Dassault Model 900EX, and Mystere Falcon 900 series airplanes, that requires repetitive operational tests of the flap asymmetry detection system to verify proper functioning, and repair, if necessary; repetitive replacement of the inboard flap jackscrews with new jackscrews; repetitive measurement of the screw/nut play to detect discrepancies; and corrective action, 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 jamming of the flap jackscrews, which could result in the inability to move the flaps or an asymmetric flap condition, and consequent reduced controllability of the airplane.
2019-17-07: The FAA is adopting a new airworthiness directive (AD) for certain Bombardier, Inc., Model CL-600-2B19 (Regional Jet Series 100 & 440); CL-600-2C10 (Regional Jet Series 700, 701 & 702); CL-600-2D15 (Regional Jet Series 705); CL-600-2D24 (Regional Jet Series 900); and CL-600-2E25 (Regional Jet Series 1000) airplanes. This AD was prompted by reports of incorrect deployment of forward and aft flight attendant oxygen masks. This AD requires repacking the flight attendant and lavatory oxygen box assemblies as applicable, replacing the placards, and re-identifying the assemblies. The FAA is issuing this AD to address the unsafe condition on these products.
98-03-06: 98-03-06 AIRBUS INDUSTRIE: Amendment 39-10298. Docket 97-NM-178-AD. Applicability: Model A300-600 series airplanes, as listed in Airbus Service Bulletin A300-57A6087, dated August 5, 1997; and Model A300 series airplanes, as listed in Airbus Service Bulletin A300-57A0234, dated August 5, 1997; certificated in any category. NOTE 1: This AD applies to each airplane identified in the preceding applicability provision, regardless of whether it has been modified, altered, or repaired in the area subject to the requirements of this AD. For airplanes that have been modified, altered, or repaired so that the performance of the requirements of this AD is affected, the owner/operator must request approval for an alternative method of compliance in accordance with paragraph (d) of this AD. The request should include an assessment of the effect of the modification, alteration, or repair on the unsafe condition addressed by this AD; and, if the unsafe condition has not been eliminated, the request should include specific proposed actions to address it. Compliance: Required as indicated, unless accomplished previously. To detect and correct cracks in Gear Rib 5 of the main landing gear attachment fittings at the lower flange, which could result in reduced structural integrity of the airplane, accomplish the following: (a) For Model A300 series airplanes that have accumulated more than 27,000 flight cycles as of the effective date of this AD: Except as provided by paragraph (b) of this AD, within 40 flight cycles after the effective date of this AD, perform a detailed visual inspection to detect cracks in Gear Rib 5 of the main landing gear attachment fittings at the lower flange, in accordance with Airbus Service Bulletin A300-57A0234, dated August 5, 1997. Thereafter, repeat the inspection at intervals not to exceed 40 flight cycles, until the actions required by paragraph (b) are accomplished. (b) For all airplanes: Perform a detailed visual and a high frequency eddy current inspection to detect cracks in Gear Rib 5 of the main landing gear attachment fittings at the lower flange, in accordance with Airbus Service Bulletin A300-57A6087 (for Model A300-600 series airplanes) or A300-57A0234 (for Model A300 series airplanes), both dated August 5, 1997; as applicable; at the time specified in paragraph (b)(1) or (b)(2) of this AD, as applicable. Accomplishment of the inspection required by this paragraph terminates the inspections required by paragraph (a) of this AD. (1) For airplanes that have accumulated 20,000 or more total flight cycles as of the effective date of this AD: Inspect within 500 flight cycles after the effective date of this AD. (2) For airplanes that have accumulated less than 20,000 total flight cycles as of the effective date of this AD: Inspect prior to the accumulation of 18,000 total flight cycles, or within 1,500 flight cycles after the effective date of this AD, whichever occurs later. (c) If any crack is detected during any inspection required by this AD, prior to further flight, repair in accordance with a method approved by the Manager, International Branch, ANM-116, FAA, Transport Airplane Directorate. (d) An alternative method of compliance or adjustment of the compliance time that provides an acceptable level of safety may be used if approved by the Manager, International Branch, ANM-116. Operators shall submit their requests through an appropriate FAA Principal Maintenance Inspector, who may add comments and then send it to the Manager, International Branch, ANM-116. NOTE 2: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the International Branch, ANM-116. (e) Special flight permits may be issued in accordance with sections 21.197 and 21.199 of the Federal Aviation Regulations (14 CFR 21.197 and 21.199) to operate the airplane to a location where the requirements of this AD can be accomplished. (f) The actions shall be done in accordance with Airbus Service Bulletin A300-57A6087, dated August 5, 1997; or Airbus Service Bulletin A300-57A0234, dated August 5, 1997; as applicable. 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 Airbus Industrie, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France. Copies may be inspected at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC. NOTE 3: The subject of this AD is addressed in French airworthiness directive (CN) 97- 274-230(B), dated September 24, 1997. (g) This amendment becomes effective on March 9, 1998.
78-26-07: 78-26-07 BOEING: Amendment 39-3375. Applies to all Model 727 airplanes equipped with operative thrust reverser assemblies P/N 65-27800-29 through 65-27800-59 which have any of the following actuator and track assemblies: P/N 65-37920-28, -30, -32, or -34. \n\tA.\tWithin ten (10) days from the effective date of this AD, install a placard stating, "Idle Reverse Only" above the EPR indicator for each engine position equipped with one of the above operative thrust reverser assemblies, except those equipped with any of the above reverser assemblies and track and actuator assemblies that have been inspected and reworked in accordance with Boeing Service Bulletin 727-78-A86, dated December 8, 1978, or later FAA approved revisions, or an equivalent procedure approved by the Chief, Engineering and Manufacturing Branch, FAA Northwest Region. \n\tThe manufacturer's specifications and procedures identified and described in this directive are incorporated herein and made a part hereof pursuant to 5 U.S.C. 552(a)(1). \n\tAll persons affected by this directive who have not already received these documents from the manufacturer, may obtain copies upon request to Boeing Commercial Airplane Company, P.O. Box 3707, Seattle, Washington 98124. These documents may also be examined at FAA Northwest Region, 9010 East Marginal Way South, Seattle, Washington 98108. \n\n\tThis amendment becomes effective January 3, 1979.