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87-04-02: 87-04-02 CONSTRUCCIONES AERONAUTICAS S.A. (CASA): Amendment 39- 5556. Applies to Model C-212 airplanes identified in CASA Service Bulletin 212-32-21, Revision 1, dated June 4, 1986, certificated in any category. Compliance is required within 45 days after the effective date of this AD. To prevent loss of aircraft control on the runway caused by fractured nose landing gear components, accomplish the following, unless already accomplished: A. Modify the nose landing gear in accordance with the accomplishment instructions of CASA Service Bulletin 212-32-21, Revision 1, dated June 4, 1986. 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, Northwest Mountain Region. C. Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes to a base for the accomplishment of the modification required by this AD. All persons affected by this directive who have not already received the appropriate service information from the manufacturer, may obtain copies upon request to Construcciones Aeronauticas S.A., Getafe, Madrid, Spain. This information may be examined at FAA, Northwest Mountain Region, 17900 Pacific Highway South, Seattle, Washington, or the Seattle Aircraft Certification Office, 9010 East Marginal Way South, Seattle, Washington. This amendment becomes effective March 2, 1987.
2019-01-03: We are superseding Airworthiness Directive (AD) 2016-18-01, which applied to certain The Boeing Company Model 737-600, -700, -700C, -800, -900, and -900ER series airplanes. AD 2016-18-01 required repetitive lubrication of the forward and aft trunnion pin assemblies of the right and left main landing gears (MLGs); repetitive inspection of these assemblies for corrosion and chrome damage, and related investigative and corrective actions if necessary; and installation of \n\n((Page 3291)) \n\nnew or modified trunnion pin assembly components, which terminated the repetitive lubrication and repetitive inspections. Since we issued AD 2016-18-01, we have determined that rotable parts were not addressed in that AD, and it is therefore necessary to include all airplanes of the affected models in the applicability. This AD retains the requirements of AD 2016-18-01, adds airplanes to the applicability, and prohibits the installation of a MLG or MLG trunnion pin assembly under certain conditions. We are issuing this AD to address the unsafe condition on these products.
2000-10-08: This amendment adopts a new airworthiness directive (AD) that applies to Eurocopter France Model SA-365N1, AS-365N2, and SA-366G1 helicopters and requires conducting inspections of each tail rotor blade for bonding separation, measuring the clearance between the tip of each tail rotor blade and the circumference of the air duct, and replacing the blade if necessary. This amendment is prompted by an inflight incident in which the tail rotor blades were significantly damaged due to bonding separation. The actions specified by this AD are intended to prevent damage to a tail rotor blade, loss of tail rotor control, and subsequent loss of control of the helicopter.
99-20-11: This amendment adopts a new airworthiness directive (AD) that applies to certain Burkhart Grob Luft - Und Raumfahrt GmbH & CO KG (Grob) Models G103 TWIN II and G103A TWIN II ACRO sailplanes. This AD requires accomplishing preflight checks of the fastening (knurled) nut at the rear control stick for cracks, and replacing the nut with one made of stainless steel either immediately or at a certain time period depending on whether a crack(s) is found. The checks are no longer required after the knurled nut is replaced. This AD is the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for Germany. The actions specified by this AD are intended to prevent the inability to use the rear control stick because of a cracked knurled nut, which could result in loss of control of the sailplane during flight instruction operations.
86-05-04: 86-05-04 BOEING: Amendment 39-5249. Applies to Model 737-100, -200, and -300 airplanes, as specified in Boeing Service Bulletin 737-25A1182, Revision 2, dated November 12, 1985, certificated in any category. To correct aft door emergency opening characteristics, accomplish the following within 6 months after the effective date of this amendment, unless previously accomplished: \n\n\tA.\tInstall escape slide cover restraining straps in accordance with Boeing Service Bulletin 737-25A1182, Revision 2, Part II, dated November 12, 1985, or later FAA-approved revisions. \n\n\tNOTE: Installation of escape slide cover restraining straps in accordance with Boeing Service Bulletin 737-25A1182, Revision 1, dated September 24, 1985, is equivalent to such installation in accordance with Revision 2 of that service bulletin, and constitutes compliance with this paragraph. \n\n\tB.\tAn alternate means of compliance 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\tC.\tSpecial flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes to a base for the accomplishment of inspections and/or modifications required by this AD. \n\n\tAll persons affected by this amendment who have not already received the appropriate service bulletin from the manufacturer may obtain copies upon request to the Boeing Commercial Airplane Company, P.O. Box 3707, Seattle, Washington 98124-2207. This service bulletin may be examined at the FAA, Northwest Mountain Region, 17900 Pacific Highway South, Seattle, Washington, or the Seattle Aircraft Certification Office, 9010 East Marginal Way South, Seattle, Washington. \n\n\tThis amendment becomes effective April 11, 1986.
2018-23-04: We are adopting a new airworthiness directive (AD) for certain Bombardier, Inc., Model DHC-8-102, -103, and -106 airplanes; Model DHC- 8-200 series airplanes; and Model DHC-8-300 series airplanes. This AD was prompted by a report that a certain modification to the auto relight system is incompatible with a certain beta lockout system modification and could result in de-activation of the auto ignition feature of the No. 2 engine. This AD requires an inspection of the auto ignition system and applicable rectification. We are issuing this AD to address the unsafe condition on these products.
97-06-10: This amendment supersedes Airworthiness Directive (AD) 91-14-14, which currently requires repetitively inspecting the main landing gear (MLG) "A" frame assemblies for cracks on Raytheon Aircraft Company (Raytheon) Model 76 airplanes (formerly referred to as Beech Model 76 airplanes), and replacing any assembly found cracked. AD 91-14-14 resulted from reports of fatigue cracks developing on the MLG "A" frame assemblies of the affected airplanes. Raytheon has developed improved design MLG "A" frame assemblies, and the Federal Aviation Administration (FAA) has determined that Model 76 airplanes with an improved design "A" frame assembly installed on both the left and right MLG should be exempt from AD 91-14-14. This action retains the requirement of repetitively inspecting the MLG "A" frame assemblies for cracks and replacing any cracked "A" frame assembly only for those Model 76 airplanes that do not have the improved design parts installed. The actions specified by this ADare intended to prevent MLG failure because of a cracked "A" frame assembly, which could result in loss of control of the airplane during landing operations.
2019-02-04: We are superseding Airworthiness Directive (AD) 2018-22-05, which applied to Engine Alliance (EA) GP7270, GP7272, and GP7277 turbofan engines with a certain high-pressure turbine (HPT) case installed. AD 2018-22-05 required removal of affected HPT stator cases (HPT cases) from service and their replacement with a part eligible for installation. This AD retains these requirements, reduces the compliance times for the removal and replacement of certain HPT cases, and identifies additional affected parts that must be removed and replaced. This AD was prompted by the discovery of a quality escape at a manufacturing facility involving unapproved welds on HPT cases. Subsequent additional findings suggested the need for an updated risk analysis, resulting in reduced compliance times for those parts and the identification of additional affected parts. We are issuing this AD to address the unsafe condition on these products.
98-21-02: This amendment supersedes an existing airworthiness directive (AD), applicable to certain Fokker Model F27 Mark 100, 200, 300, 400, 500, 600, and 700 Rough Field Version (RFV) series airplanes, that currently requires inspection of the main landing gear (MLG) legs to determine if parts are missing or damaged, and modification, if necessary; and periodic measurements of the extension of each MLG shock absorber sliding member. That AD also provides for the accomplishment of a certain modification as optional terminating action for the periodic measurements. This amendment requires accomplishment of the previously optional terminating action, and revises the applicability of the existing AD to add an airplane model. 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 loss of the MLG sliding member, which could result in reduced structural integrity of the MLG.
2019-02-01: We are superseding Airworthiness Directive (AD) 2018-16-07, which applied to certain General Electric Company (GE) GEnx turbofan engines. AD 2018-16-07 required removal and replacement of affected high-pressure turbine (HPT) stator cases (HPT cases). This AD retains those requirements, but reduces certain compliance times. This AD was prompted by the discovery of a quality escape at a manufacturing facility and a determination that the compliance time for the removal and replacement of certain HPT cases must be reduced. We are issuing this AD to address the unsafe condition on these products.