Results
2001-12-15: This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model MD-90-30 series airplanes, that requires revising the wiring of the selective calling (SELCAL) system. The actions specified by this AD are intended to prevent inadvertent very high frequency transmissions and subsequent loss of radio communications for airplane and/or airport operations; and to prevent inadvertent high frequency transmissions and subsequent electrical shock to ground service personnel and/or damage to the airplane during fueling operations or fuel tank maintenance. This action is intended to address the identified unsafe condition.
91-05-12: 91-05-12 AIRBUS INDUSTRIE: Amendment 39-6914. Docket No. 90-NM-158-AD. Applicability: All Model A300 series airplanes, equipped with one or more trimmable horizontal stabilizer (THS) attachment lugs made from 2014 material, certificated in any category. Compliance: Required as indicated, unless previously accomplished. To detect cracks and corrosion in the THS attachment lugs at Frame 91 and to prevent reduced structural integrity of the horizontal stabilizer attachment, accomplish the following: A. Prior to the accumulation of 1,200 landings, or within 90 days after the effective date of this AD, whichever occurs later, unless previously accomplished within the last 1,200 landings, perform a visual and eddy current inspection of all attachment lugs made from 2014 material, in accordance with Airbus Industrie Service Bulletin A300-53-269, dated December 18, 1989. Repeat these inspections thereafter at intervals not to exceed 1,200 landings. NOTE: Attachment lugs made from 7075 material are not affected by this AD. B. If cracks or corrosion are detected, prior to further flight, repair or replace the affected lugs in accordance with Airbus Industrie Service Bulletin A300-53-269, dated December 18, 1989. C. Installation of Modification No. 7715/D7222, in accordance with Airbus Industrie Service Bulletin A300-53-270, Revision 1, dated February 22, 1990, or Revision 2, dated August 27, 1990, constitutes terminating action for the repetitive inspections required by paragraph A. of this AD. D. 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. E. 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 (39-6914, AD 91-05-12) becomes effective on April 1, 1991.
97-05-05: 97-05-05 DORNIER: Amendment 39-9949. Docket 96-NM-116-AD. Applicability: Model 328-100 series airplanes having serial numbers 3005 through 3014 inclusive; certificated in any category. NOTE 1: This AD applies to each airplane identified in the preceding applicability provision, regardless of whether it has been otherwise 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 (b) 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 prevent failure of the diagonal braces that connect the left and right wings to the fuselage, which could result in unstable movement of the wings and adversely affect the aerodynamic characteristics of the wings, accomplish the following: (a) Within 90 days after the effective date of this AD, perform the actions required by paragraphs (a)(1) and (a)(2) of this AD. (1) Check the clearance between the diagonal braces that connect the left and right wings to the fuselage and the Z-profile of the frame to which the top fairing is attached, in accordance with Dornier Service Bulletin SB-328-53-051, dated August 16, 1994. (i) If the clearance meets or exceeds the minimum limits specified in the service bulletin, no further action is required by paragraph (a)(1) of this AD. (ii) If the clearance is less than the minimum limits specified in the service bulletin, prior to further flight, modify the Z-profile of the frame to which the top fairing is attached, in accordance with the service bulletin. (2) Check each diagonal brace for damage or wear, in accordance with the service bulletin. (i) If no damage or wear is detected, no further action is required by paragraph (a)(2) of this AD. (ii) If any damage or wear is detected, prior to further flight, repair the diagonal brace in accordance with a method approved by the Manager Standardization Branch, ANM-113, FAA, Transport Airplane Directorate. (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 actions shall be done in accordance with Dornier Service Bulletin SB-328-53-051, dated August 16, 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 Dornier Luftfahrt GmbH, P.O. Box 1103, D-82230 Wessling, Germany. 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 April 3, 1997.
2016-19-08: We are adopting a new airworthiness directive (AD) for Viking Air Limited Models DHC-2 Mk. I, DHC-2 Mk. II, and DHC-2 Mk. III airplanes. This AD results from mandatory continuing airworthiness information (MCAI) issued by an aviation authority of another country to identify and [[Page 64054]] correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as corrosion of the elevator control rod and of the elevator actuating lever on the control column. We are issuing this AD to detect and correct corrosion and/or cracking of the elevator control rod assemblies and the elevator actuating lever, which if not detected and corrected, could cause these components to fail. This failure could result in loss of control.
2010-23-22: We are adopting a new airworthiness directive (AD) for the Eurocopter Model AS332L2 helicopters. This AD results from a mandatory continuing airworthiness information (MCAI) AD issued by the European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Community. The MCAI AD states that a hard landing occurred during in-flight engine failure (one engine inoperative (OEI)) training. An examination revealed the failure of the right-hand main reduction gear module (module) freewheel unit due to excessive wear on some of its components. The MCAI AD prohibits engine failure OEI training with helicopters on which certain main gearbox (MGB) modules with certain freewheel shafts are installed and mandates the replacement of those modules. The actions are intended to prevent failure of certain freewheel units, loss of power to the main rotor system, and subsequent loss of control of the helicopter.
2001-01-52 R1: This amendment rescinds an existing airworthiness directive (AD) that applies to Bell Helicopter Textron Canada (BHTC) Model 407 helicopters and currently requires, before further flight, imposing never exceed velocity (Vne) restrictions on the helicopter. The requirements of that AD were intended to prevent tail rotor blades from striking the tailboom, separation of the aft section of the tailboom with the tail rotor gearbox and vertical fin, and subsequent loss of control of the helicopter. That AD was prompted by an accident suspected of being the result of a tail rotor strike caused by high airspeed. Since the issuance of that AD, accident investigation findings have not substantiated that a tail rotor strike caused by high airspeed was the cause of the accident. This amendment rescinds that AD. This amendment is prompted by the FAA's determination that the Vne restrictions and accompanying actions imposed by that AD do not correct an unsafe condition.
2016-19-07: We are superseding Airworthiness Directive (AD) 2008-19-08, for all Dassault Aviation Model Falcon 10 airplanes. AD 2008-19-08 required repetitive replacement of the flexible hoses installed in the wing (slat) anti-icing system with new hoses. This new AD requires reducing the life limit of these flexible hoses, which reduces the repetitive replacement intervals. This AD was prompted by additional reports of collapse of the flexible hoses installed in the slat anti- icing systems on airplanes equipped with new, improved hoses. We are issuing this AD to prevent collapse of the flexible hoses in the slat anti-icing system, which could lead to insufficient anti-icing capability and, if icing is encountered in this situation, could result in reduced controllability of the airplane.
2016-18-18: We are adopting a new airworthiness directive (AD) for Agusta S.p.A. (Agusta) Model A109A, A109A II, A109C, A109E, A109K2, A109S, and AW109SP helicopters. This AD requires visually inspecting the tail rotor drive shaft assembly (drive shaft) for a crack. This AD was prompted by the discovery of three cracks on the drive shaft of a Model A109S helicopter. The actions of this AD are intended to detect a crack on the drive shaft to prevent failure of the driveshaft, failure of the tail rotor, and subsequent loss of helicopter control.
2005-14-09: The FAA is adopting a new airworthiness directive (AD) for Rolls-Royce plc (RR) models RB211 Trent 768-60, Trent 772-60, and Trent 772B-60 turbofan engines. This AD requires removal of certain Engine Electronic Controller (EEC) part numbers from service. This AD results from nine reports of loss of engine parameters displayed in the airplane cockpit, with the simultaneous loss of capability to change thrust of the affected engine. We are issuing this AD to prevent loss of airplane control after an aborted takeoff due to asymmetric thrust.
98-09-26: This amendment adopts a new airworthiness directive (AD) that is applicable to certain Dassault Model Falcon 2000 series airplanes. This action requires revising the Airplane Flight Manual (AFM) to provide the flightcrew with procedures for monitoring and properly setting the fuel booster pump pressure; and repetitive visual inspections of the fuel lines to detect fatigue cracking and fuel leakage. This action also requires a one-time inspection of the fuel lines to detect cracking, replacement of any discrepant part with a new part, and installation of new brackets between the pressure switch and the fuel pump of the numbers 1 and 2 engines, which constitutes terminating action for the repetitive inspections and the AFM revision. This amendment is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified in this AD are intended to prevent fatigue cracking of the fuel line at the pressure switch pickoff point, which could result in fuel leakage and potential engine fire.