Results
2000-02-21: This amendment adopts a new airworthiness directive (AD), applicable to all British Aerospace (Jetstream) Model 4101 airplanes, that requires manufacture and installation of a placard on the left-hand instrument panel in the cockpit to prohibit push-backs of the airplane while the engines are running. In lieu of accomplishing the placard installation, this amendment requires repetitive installation of a new tow bracket sub-assembly that has the serial number and date of installation vibro etched on it. 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 fatigue failure of the towing bracket. Failure of the towing bracket could cause a towing vehicle to collide into the propeller while the airplane engines are running, and consequently, cause damage to the airplane, and injure ground personnel, flight crew, or passengers.
2005-20-34: The FAA is adopting a new airworthiness directive (AD) for certain British Aerospace Model HS 748 airplanes. This AD requires relocating the battery earth posts located on the nose landing gear (NLG) pintle webs. This AD results from an accident in which the nose landing leg, together with the pintle webs, detached from the airplane. As a result, the battery earth return cables were severed from their earth posts. We are issuing this AD to prevent loss of safety critical services including fuel shut-off and nacelle fire extinguishing services.
2000-02-18: This amendment supersedes an existing airworthiness directive (AD), applicable to certain Boeing Model 737-100, -200, -300, -400, and -500 series airplanes; that currently requires an inspection of reworked aileron/elevator power control units (PCU's) and rudder PCU's to determine if reworked PCU manifold cylinder bores containing chrome plating are installed, and replacement of the cylinder bores with cylinder bores that have been reworked using the oversize method or the steel sleeve method, if necessary. This amendment, among other items, expands the applicability of the existing AD to include airplanes equipped with certain rudder PCU's. This amendment is prompted by a review of the design of the flight control systems on Model 737 series airplanes. The actions specified by this AD are intended to prevent a reduced rate of movement of the elevator, aileron, or rudder due to contamination of hydraulic fluid from chrome plating chips; such reduced rate of movement, ifnot corrected, could result in reduced controllability of the airplane.
2022-27-07: The FAA is adopting a new airworthiness directive (AD) for certain The Boeing Company Model 747-400 and 747-8 series airplanes. This AD was prompted by reports of wear-through of the motor impeller inlet adapter of a transfer pump for the horizontal stabilizer fuel tank caused by contact between the pump inlet check valve and the inlet adapter. This AD requires inspecting for wear of the motor impeller inlet check valves and inlet adapters of the transfer pumps for the horizontal stabilizer fuel tank and doing corrective actions, if necessary. This AD also limits the installation of affected parts. The FAA is issuing this AD to address the unsafe condition on these products.
2000-02-19: This amendment supersedes an existing airworthiness directive (AD), applicable to certain Boeing Model 727 series airplanes, that currently requires repetitive inspections of the front spar web between the upper and lower seals of the center section of the wings, and repair, if necessary. That amendment also provides for an optional terminating modification for the repetitive inspections. This amendment requires a new terminating modification for the repetitive inspections. For certain airplanes, this amendment also requires new repetitive inspections to detect discrepancies of the front spar web. This amendment is prompted by a report indicating that the optional terminating modification in the existing AD does not adequately address the identified unsafe condition. The actions specified by this AD are intended to prevent fatigue cracks in the front spar web, which could lead to fuel leakage into the air-conditioning distribution bay and/or depressurization of the cabin, and to prevent fuel fumes in the cabin of the airplane.
2000-02-24: This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A300, A310, and A300-600 series airplanes, that requires either replacement of the spring rod assemblies of the rudder servo controls with improved spring rod assemblies; or modification of the existing spring rod assemblies. For certain airplanes, this amendment requires a one-time visual inspection to determine whether certain parts of the spring rod assemblies of the rudder servo controls are installed; and corrective actions, if necessary. 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 corrosion of the spring rod assemblies of the rudder servo controls, which could result in the jamming of the rudder servo controls and consequent reduced controllability of the airplane.
96-24-15: This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model DC-10 series airplanes, and KC-10A (military) series airplanes, that requires high frequency eddy current inspections to detect cracks in the secondary pivot support of the horizontal stabilizer, and various follow-on actions, if necessary. This amendment is prompted by reports of crack development in the secondary pivot support of the horizontal stabilizer due to fatigue. The actions specified by this AD are intended to prevent such fatigue cracking, which could result in reduced structural integrity of the horizontal stabilizer and, consequently, lead to reduced controllability of the airplane.
2022-27-08: The FAA is adopting a new airworthiness directive (AD) for certain Bell Textron Canada Limited Model 407 helicopters. This AD was prompted by an accident. This AD requires inspecting the tailboom attachment structure, as specified in a Transport Canada AD, which is incorporated by reference. The FAA is issuing this AD to address the unsafe condition on these products.
85-15-02: 85-15-02 BRITISH AEROSPACE: Amendment 39-5100. Applies to all Model BAe 146 airplanes certificated in any category on which Modification HCM00301A or B has been accomplished, and on which Modification HCM00432A or B has not been accomplished. Compliance is required within the next 100 landings after the effective date of this airworthiness directive (AD). To detect and prevent chafing of the fuselage skin, accomplish the following, unless previously accomplished: 1. Inspect the fuselage skin beneath the wing to-fuselage fairings for chafing, repair if necessary, and apply anti-chafe tape in accordance with British Aerospace Service Bulletin 53-5 dated August 15, 1984, or Service Bulletin 53-5, Revision 1, dated April 19, 1985. 2. Repeat the inspection required by paragraph 1., above, at intervals not to exceed 1000 landings until Modification HCM00432A or B is incorporated. 3. Alternate means of compliance which provide an acceptable level of safety may be used when approved by the Manager, Seattle Aircraft Certification Office, FAA, Northwest Mountain Region. 4. 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 inspections and/or modifications required by this AD. This amendment becomes effective August 22, 1985.
2000-02-15: This amendment adopts a new airworthiness directive (AD) that applies to Raytheon Aircraft Company (Raytheon) Beech Models 65-90, 65-A90, B90, and C90 airplanes that incorporate a certain engine and propeller configuration. This AD prohibits you from operating any affected airplane with this engine and propeller configuration and prohibits its future installation. Results of an accident investigation involving one of the affected airplanes reveals installation discrepancies with the engine and propeller configuration. These discrepancies, if not corrected, could lead to engine failure and the inability to feather the propeller. The actions specified by this AD are intended to prevent an uncontained engine failure due to suspect engine and propeller installation, which could result in loss of control of the airplane. The FAA must receive any comments on this rule on or before March 17, 2000.