Results
52-28-02: 52-28-02 BELLANCA: Applies to Models 14-13, 14-13-2, 14-13-3 Aircraft, Serial Numbers Up to Number 1584. Compliance required as soon as practicable, but not later than next engine overhaul after January 1, 1953. In order to eliminate possible hazard due to excessive pressure from the engine-driven fuel pump, install a high-pressure relief valve between the fuel pump outlet and the inlet side of the hand wobble pump. (Bellanca Service Bulletin No. 23 covers this same subject.)
2003-12-09: This amendment adopts a new airworthiness directive (AD), applicable to certain BAE Systems (Operations) Limited Model BAe 146 series airplanes, that requires modification of the flight annunciator box. This action is necessary to prevent traffic collision avoidance system (TCAS) aural messages and resolution advisories of the TCAS from being inhibited following a ground proximity warning system alert or test message, which could prevent the TCAS from providing attention- getting alerts, and could result in the consequent possibility of a mid-air collision or near mid-air collision. This action is intended to address the identified unsafe condition.
2003-12-08: This amendment adopts a new airworthiness directive (AD), that is applicable to General Electric Company (GE) CF6-80A1/A3 and CF6- 80C2A PMC series turbofan engines. This amendment requires performing either a directional pilot valve (DPV) pressure switch moisture purge procedure and an operational check of the fan reverser or replacing the DPV assembly with a serviceable assembly and performing an operational check of the fan reverser. Thereafter, this AD requires one of these actions on a repetitive basis. This amendment is prompted by a review of fan reverser safety analyses resulting from the discovery of an undetectable failure mode of the DPV pressure switch on certain GE CF6- 80C2A and CF6-80A1/A3 engine models. The actions specified by this AD are intended to prevent inadvertent fan reverser deployment, which, if it occurred in-flight, could result in loss of control of the airplane.
2020-15-13: The FAA is superseding Airworthiness Directive (AD) 2017-02-07 for Airbus Helicopters Deutschland GmbH (Airbus Helicopters) Model MBB- BK 117 C-2 and Model MBB-BK 117 D-2 helicopters. AD 2017-02-07 required a repetitive inspection and a one-time torque of each hydraulic module plate assembly attachment point (attachment point). This new AD retains the initial inspection and torque requirements of AD 2017-02-07 and requires replacing the attachment point hardware. This AD was prompted by a terminating action has been developed to address the unsafe condition. The actions of this AD are intended to address an unsafe condition on these products.
2008-22-20: We are adopting a new airworthiness directive (AD) for the products listed above. This AD results from mandatory continuing airworthiness information (MCAI) originated by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as: During fatigue tests (EF3) on the A340-600, damages were found in longitudinal doubler at VTP [vertical tail plane] attachment cutout between Frame (FR) 80 and FR86. This damage occurred between 58341 and 72891 simulated Flight Cycles (FC). Due to the higher Design Service Goal and different design (e.g., doubler thickness) [of the] A330-200/-300 and A340-300 aircraft series, the damage assessment concluded [there was] potential impact on [the airplanes specified in the] applicability. * * * * * The unsafe condition is crack propagation in the VTP attachment cutout, which could reduce airplane structural integrity in the tail section. We are issuing this AD to require actions to correct the unsafe condition on these products.
99-23-25: This amendment adopts a new airworthiness directive (AD), applicable to certain Fokker Model F27 Mark 050 series airplanes. This action requires replacement of the lighting plates of the fuel control panel and the electrical power control panel with new, improved lighting plates. 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 internal short circuits in the fuel control and electrical power control panels, which could result in burning of the panels and consequent smoke in the flight deck area.
95-21-18: This amendment adopts a new airworthiness directive (AD), applicable to certain Jetstream Model ATP airplanes, that requires an inspection to ensure that various components of the retraction actuator of the nose landing gear (NLG) are secure, and an inspection of the bearing cap mounting holes for correct hole and thread length. This AD also requires a later inspection for certain discrepancies of the retraction actuator; installation of revised tolerance bushings; and correction of any discrepancy found. This amendment is prompted by reports of failure of the attachment bolts of the bearing cap of the retraction actuator of the NLG. The actions specified by this AD are intended to prevent the inability to raise or lower the NLG, or possible collapse of the NLG, due to failure of the attachment bolts of the bearing cap.
85-16-05: 85-16-05 BOEING: Amendment 39-5111. Applies to Model 727 and Model 737 series airplanes as specified in Boeing Service Bulletins 727-25-277 dated February 23, 1984, and 737- 25-1171 dated August 10, 1984, respectively, certificated in any category. To assure adequate lavatory fire protection, accomplish the following within one year after the effective date of this amendment, unless previously accomplished: \n\n\tA.\tFor Boeing Model 727 airplanes, modify lavatories in accordance with Boeing Service Bulletin 727-25-277 dated February 23, 1984, or later FAA approved revisions. \n\n\tB.\tFor Boeing Model 737 airplanes, install lavatory placards in accordance with Boeing Service Bulletin 737-25-1171 dated August 10, 1984, or later FAA approved revisions. \n\n\tC.\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\tD.\tSpecial flight permits may beissued 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 Boeing Service Bulletins 727-25-277 and 737-25-1171 may obtain copies upon request to Boeing Commercial Airplane Company, 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 9010 East Marginal Way South, Seattle, Washington. \n\n\tThis amendment becomes effective September 6, 1985.
2006-09-04: The FAA is adopting a new airworthiness directive (AD) for certain Dassault Model Falcon 900EX airplanes. This AD requires inspecting the number 2 engine left- and right-hand forward mounts for missing rivets, and installing rivets if necessary. This AD results from reports of two missing rivets in the front section of the central engine mast discovered on airplanes in service and in production. We are issuing this AD to detect and correct missing rivets in the front section of the central engine mast, which could result in reduced structural integrity of the central engine mast, possible separation of the engine from the airplane during flight, and consequent loss of control of the airplane.
2003-12-04: This amendment adopts a new airworthiness directive (AD), applicable to certain EMBRAER Model EMB-135 and -145 series airplanes, that requires replacing the four Gamah clamp/sleeve joints on an engine bleed air duct with new threaded coupling assemblies. For certain airplanes, this AD also requires replacing the two supports for the engine bleed air duct with two new supports. The actions specified by this AD are intended to prevent hot air leaks from the bleed air duct due to disconnection of the duct joint, which could result in heat damage to components near the duct, and consequent increased risk of fire in the rear baggage compartment. This action is intended to address the identified unsafe condition.