Results
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.
98-24-03 R1: This amendment revises an existing airworthiness directive (AD), applicable to BMW Rolls-Royce GmbH (BRR) Models BR700-710A1-10 and BR700-710A2-20 turbofan engines. The existing AD requires initial and repetitive visual inspections of the engine compressor and combustion core fairings (also referred to as the engine core fairings) and fasteners for correct installation and damage, and verification that the engine core fairing fasteners are torqued to a higher torque value. This amendment increases the repetitive inspection interval to 150 hours time-in-service (TIS) following an initial inspection and follow-on inspection at the current 50 hours TIS interval. This amendment also requires an initial inspection and follow-on inspection at a 50 hours TIS interval following any engine core fairing or fastener removal, repair, or replacement. Repair of engine core fairings has been added as an alternate to engine core fairing replacement, and an inspection for loose engine core fairing(s) has been included to verify correct installation on the engine. Finally, this amendment adds a new paragraph in the compliance section allowing the option to incorporate redesigned core engine fairings as the terminating action to the required repetitive inspections. This amendment is prompted by results of repetitive inspections that indicate that the inspection interval can be increased safely, and by introduction of redesigned engine core fairings. The actions specified by this AD are intended to prevent engine compressor or combustion core fairing detachment and damage to the engine bypass duct, resulting in engine failure and damage to the airplane.
2006-09-02: The FAA is adopting a new airworthiness directive (AD) for certain Boeing Model 757-200 and -200PF series airplanes equipped with Pratt & Whitney engines. This AD requires repetitive detailed inspections to detect and correct any gap between the strut fitting and the forward engine mount assembly and applicable related investigative actions, corrective actions, and other specified actions. This AD results from a report indicating that gaps had been found between the strut fitting and the forward engine mount assembly. We are issuing this AD to detect and correct any gaps between the strut fitting and the forward engine mount assembly of both engines, which could result in separation of the engine from the wing and subsequent loss of control of the airplane.
2003-12-01: This amendment adopts a new airworthiness directive (AD), applicable to all Boeing Model 777 series airplanes, that requires either a one-time inspection or a review of the airplane maintenance records for both stabilizer trim control modules (STCM) of the trim system of the horizontal stabilizer to determine if STCMs having certain serial numbers are installed; and follow-on corrective actions, if necessary. This amendment also requires eventual replacement of affected STCMs with new or reworked STCMs, which would terminate the follow-on actions. The actions specified by this AD are intended to prevent an uncommanded stabilizer trim due to simultaneous failure of two static seals on one STCM, combined with failure of the automatic shutdown function of the stabilizer trim system. Such failures could result in loss of pitch control and consequent loss of control of the airplane. This action is intended to address the identified unsafe condition.
2002-07-06: This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model DC-9-10, -20, -30, -40, and -50 series airplanes; and C-9 airplanes; that requires repetitive visual and x-ray inspections to detect cracks of the upper and lower corners and upper center of the door cutout of the aft pressure bulkhead; corrective actions, if necessary; and follow-on actions. For certain airplanes, the amendment also requires modification of the ventral aft pressure bulkhead. The actions specified by this AD are intended to detect and correct fatigue cracks in the corners and upper center of the door cutout of the aft pressure bulkhead, which could result in rapid decompression of the fuselage and consequent reduced structural integrity of the airplane. This action is intended to address the identified unsafe condition.
99-17-06: This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A310 series airplanes, that requires repetitive inspections and tests to detect missing or damaged vespel bushes on the slat system universal joint assemblies of the left- and right-hand wings; and replacement of the universal joints with new joints, if necessary. This amendment also provides for an optional terminating modification for the repetitive inspection and test requirements. This amendment is prompted by a report of loose and migrated vespel bushes and partial cracking within unsupported bush areas found on the slat system universal joint assemblies. The actions specified by this AD are intended to prevent rupture of the universal joints, which could result in inadvertent movement of the slats, and consequent reduced controllability of the airplane.
2008-12-12: We are superseding an existing airworthiness directive (AD) for the products listed above. This AD results from mandatory continuing airworthiness information (MCAI) issued 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: A complete loss of both ignition systems occurred on a DHC-3 Otter when the lock wire hole in the ignition connector plug on the firewall broke out, allowing the plug to vibrate loose. A maintenance safety feature grounds out both magneto systems through a spring-loaded safety pin incorporated into the Cannon plug. The DHC-2 system is similar in design. Subsequent to the issuance of AD CF-2001-36 a complete loss of both ignition systems occurred on a DHC-2 Beaver resulting in engine failure and subsequent forced approach and landing. Investigation by the Transportation Safety Board determined the internal failure of the magneto firewall connectorresulted in both magneto "P'' leads shorting to ground. A maintenance "safety'' feature through a spring-loaded safety pin incorporated in the firewall connector on many DHC-2 aircraft grounds out both magneto systems when the connector is disconnected. This connector type is readily identified when disconnected by the existence of three internal pins on the firewall and magneto harness side, one of which is shorted directly to ground. We are issuing this AD to require actions to correct the unsafe condition on these products. DATES: This AD becomes effective July 23, 2008. On July 23, 2008, the Director of the Federal Register approved the incorporation by reference of Viking DHC-2 Beaver Service Bulletin Number V2/0001, dated June 27, 2007; and Viking DHC-3 Otter Service Bulletin Number V3/0001, dated June 27, 2007, listed in this AD. As of December 6, 2004 (69 FR 61758, October 21, 2004), the Director of the Federal Register approved the incorporation by reference ofdeHavilland Beaver Alert Service Bulletin Number A2/53, Revision B, dated May 28, 2004; and deHavilland Otter Alert Service Bulletin Number A3/53, Revision B, dated May 28, 2004, listed in this AD.