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89-02-04: 89-02-04 BOEING: Amendment 39-6101. Applicability: Model 737 series airplanes, line numbers 1 through 446, certificated in any category. \n\n\tCompliance: Required within 18 months after the effective date of this AD, unless previously accomplished. \n\n\tTo prevent collapse of the nose landing gear, accomplish the following: \n\n\tA.\tReplace the aluminum nose landing gear actuator support fitting with a steel fitting, in accordance with Boeing Service Bulletin 737-53-1119, dated September 22, 1988. \n\n\tB.\tAn 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, Seattle Aircraft Certification Office, FAA, Northwest Mountain Region. \n\n\t\tNOTE: The request should be forwarded through an FAA Principal Maintenance Inspector (PMI), who may add any comments and then send it to the Manager, Seattle Aircraft Certification Office. \n\n\tC.\tSpecial 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. \n\n\tAll persons affected by this directive who have not already received the appropriate service documents from the manufacturer may obtain copies upon request to Boeing Commercial Airplanes, P. O. Box 3707, Seattle, Washington 98124. These documents may be examined at the FAA, Northwest Mountain Region, 17900 Pacific Highway South, Seattle, Washington, or Seattle Aircraft Certification Office, FAA, Northwest Mountain Region, 9010 East Marginal Way South, Seattle, Washington. \n\n\tThis amendment (39-6101, AD 89-02-04) becomes effective February 8, 1989.
2004-03-31: This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 727, 727-100C, 727-200F, and 727C series airplanes, that requires repetitive open-hole high frequency eddy current inspections for cracks in the fuselage skin, strap (bearstrap), and doubler at the forward and aft hinge fittings for the main deck cargo door, and repair of any cracks found. This action is necessary to detect and correct such cracks, which could reach critical crack length and result in rapid decompression of the airplane. This action is intended to address the identified unsafe condition.
58-07-06: 58-07-06 VICKERS: Applies to All Viscount 700 Series Aircraft Fitted With Heavy- Duty Wing Root Terminals and Aluminum Cables, Incorporating Modification D.1255. Compliance required as indicated. Cases have occurred of heavy-duty wing root terminals with their associated aluminum cables overheating as a result of poor electrical contact between the aluminum cable lug and the wing root terminal assembly. The poor electrical contact is attributed to the relaxation of the connection and the spreading and indentation of the aluminum cable lug by repetitive torque loading. To prevent the possibility of damage to the cable lug, a special washer, 80236 Part 3043, has been introduced by Mod. D.2628 to replace the existing washer 72436 Part 2069. The new washer is of increased thickness with an electro-tinned finish and has an outside diameter equal to the width of the cable lug. Vickers-Armstrong has issued the following corrective measures which the British Air registration Board considers mandatory. The FAA concurs and considers compliance therewith mandatory. Inspect all wing root connections for signs of looseness and overheated condition within the next 135 flying hours and take the following action: 1. Where signs of overheat are apparent the wing root terminal and cable lug assembly should be dismantled, and the overheated cable and components renewed. 2. Where loose connections are found these should be retightened after first inspecting the cable lug to ensure that the faces of the lug are clean, flat and free from signs of burning. 3. If signs of burning or damage are found on either face of the lug when complying with the recommendations in paragraphs 1 and 2, the lug and its associated cable should be replaced. 4. Where no signs of overheated or loose connections are found, existing terminal connections may be considered serviceable. All wing root connections should, however, be further inspected within every subsequent 135 flying hours until the new washer 80236 Part 3043 is fitted in place of washer 72436 Part 2069. 5. All wing root connections must have washer 80236 Part 3043 installed within 800 flying hours. (Vickers-Armstrong PTL No. 186, Issue 1, dated February 11, 1958, and Modification Bulletin No. D.2628 covers the same subject.)
2018-19-15: We are adopting a new airworthiness directive (AD) for certain GEVEN S.p.A. (Geven) Type D1-02 and D1-03 seat assemblies. This AD was prompted by a report that seat belt attachment bolts were found detached or partially detached from the seat. This AD requires inspection, torque verification, and modification of certain model seats. We are issuing this AD to address the unsafe condition on these products.
2018-19-27: We are adopting a new airworthiness directive (AD) for certain Dassault Aviation Model FALCON 2000EX airplanes. This AD was \n\n((Page 50480)) \n\nprompted by the manufacturer revising the airplane maintenance manual (AMM) maintenance requirements and airworthiness limitations. This AD requires revising the maintenance or inspection program, as applicable, to incorporate new maintenance requirements and airworthiness limitations. We are issuing this AD to address the unsafe condition on these products.
2021-11-24: The FAA is adopting a new airworthiness directive (AD) for certain The Boeing Company Model 737-600, -700, -700C, -800, -900, and -900ER series airplanes. This AD was prompted by significant changes made to the airworthiness limitations (AWLs) related to fuel tank ignition prevention and the nitrogen generation system (NGS). This AD requires revising the existing maintenance or inspection program, as applicable, to incorporate the April 2019 or November 2020 revision of the airworthiness limitations document. The FAA is issuing this AD to address the unsafe condition on these products.
2006-23-03: The FAA adopts a new airworthiness directive (AD) for all B-N Group Ltd. BN-2, BN-2A, BN-2B, BN-2T, and BN-2T-4R series (all individual models included in Type Certificate Data Sheet (TCDS) A17EU, Revision 16, dated December 9, 2002) airplanes. This AD requires you to inspect the horizontal stabilizer attachment bolts and anchor nuts for damage and wear and replace damaged and/or worn parts with new, modified parts. If no damaged or worn parts are found during the inspection, this AD requires you to replace the horizontal stabilizer attachment bolts and anchor nuts at a specified time with new, modified parts. This AD results from mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for the United Kingdom. We are issuing this AD to detect and correct damaged and/or worn horizontal stabilizer attachment bolts and anchor nuts, which could result in failure of the horizontal stabilizer. This failure could result in loss of control.
2006-23-01: The FAA adopts a new airworthiness directive (AD) for certain Pilatus Aircraft Ltd. (Pilatus) Model PC-7 airplanes. This AD requires you to do repetitive eddy-current, non-destructive inspections of the nose skin and adjacent structure above the left and right main landing gear bay and repetitive visual inspections of the forward support structure of the floor panel for crack damage. If you find any crack damage, this AD requires you to contact Pilatus to obtain a repair solution and incorporate the repair. This AD results from mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for Switzerland. We are issuing this AD to detect and correct cracks in the nose skin and adjacent structure above the left and right main landing gear bay and in the forward support structure of the floor panel. Crack propagation in certain areas could lead to failure of the main wing torsion box, which could result in loss of control.
2018-19-07: We are adopting a new airworthiness directive (AD) for all Airbus SAS Model A300 series airplanes; Model A300 B4-600, B4-600R, and F4-600R series airplanes, and Model A300 C4-605R Variant F airplanes (collectively called Model A300-600 series airplanes); and Model A310 series airplanes. This AD was prompted by a report of yellow hydraulic system failure, including both braking accumulators, due to failure of the parking brake operated valve (PBOV). This AD requires replacement of a certain PBOV with a different PBOV. We are issuing this AD to address the unsafe condition on these products.
2006-23-04: We are adopting a new airworthiness directive (AD) for the products listed above. This AD results from mandatory continuing airworthiness information (MCAI) issued by the aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as during production installation of the Garmin G1000 supplemental type certificate (STC) some parts of the installed fuel system indicating system were contaminated with particles from the manufacturing process. This AD requires actions that are intended to address the unsafe condition described in the MCAI. DATES: This AD becomes effective November 28, 2006. The Director of the Federal Register approved the incorporation by reference of Diamond Aircraft Industries GmbH Mandatory Service Bulletin No. MSB-40-048/2, Revision 2, dated September 26, 2006; and Work Instruction WI-MSB-40.048/2, Revision 2, dated September 26, 2006, listed in this AD as of November 28, 2006. We must receive comments on this AD by December 8, 2006.