Results
2001-13-05: This amendment adopts a new airworthiness directive (AD), applicable to certain Raytheon Model BAe.125 series 800A (C-29A and U-125 military), 1000A, and 1000B airplanes; Hawker 800 (U-125A military) airplanes; and Hawker 800XP and 1000 series airplanes, that requires removal of existing clamps, bedding tapes, and rubber connecting sleeves at the ends of the turbine air discharge duct and the water separator, and replacement of the clamps and rubber connecting sleeves with new, improved components. This AD also requires, for certain airplanes, removal of aluminum bedding strips that are installed under the existing clamps. The actions specified by this AD are intended to prevent the turbine air discharge duct or water separator outlet duct from disconnecting from the cold air unit turbine or from the water separator, resulting in the loss of air supply to maintain adequate cabin pressure. Loss of adequate cabin pressure at high altitude would require emergency procedures, suchas use of oxygen, auxiliary pressurization, or emergency descent.
2001-08-13: This amendment adopts a new airworthiness directive (AD) that is applicable to certain Gulfstream Model G-1159, G-1159A, G-1159B, G-IV, and G-V series airplanes. This action requires an inspection to determine if certain door control valves of the landing gear are installed, and modification of the valve, if necessary. This action is necessary to prevent loss of hydraulic system fluid due to failure of the door control valve of the landing gear, which could require the flight crew to use alternate gear extension procedures (landing gear blow down) for landing of all models. This action is intended to address the identified unsafe condition.
94-15-12: This amendment supersedes an existing airworthiness directive (AD), applicable to certain Boeing Model 747-100SR series airplanes, that currently requires that the FAA-approved maintenance inspection program include inspections which will give no less than the required damage tolerance rating (DTR) for each Structural Significant Item (SSI). That AD was prompted by a structural re-evaluation of this airplane model by the FAA. The actions specified in that AD are intended to ensure the continued structural integrity of the total Boeing Model 747-100SR fleet. This amendment revises the applicability of the rule by removing airplanes and adding others.
2008-02-07: 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: Bombardier Aerospace has completed a system safety review of the CL-600-2B19 aircraft fuel system * * *. The assessment showed that if the fuel boost pump reducer coupling is anodized, insufficient electrical bonding between the boost pump canister and the pressure pick-up line could occur. Insufficient electrical bonding between the boost pump canister and the pressure pick-up line, if not corrected, could result in arcing and potential ignition source inside the fuel tank during lightning strikes and consequent fuel tank explosion. * * * We are issuing this AD to require actions to correct the unsafe condition on these products.
2020-05-12: The FAA is adopting a new airworthiness directive (AD) for all Gulfstream Aerospace Corporation Model GVII-G500 and GVII-G600 airplanes. This AD requires revising the airplane flight manual (AFM) for your airplane to incorporate revised limitations and procedures. This AD was prompted by a report of a landing incident where the alpha limiter engaged in the landing flare in unstable air while on the approach, resulting in a high rate of descent landing and damage to the airplane. The FAA is issuing this AD to address the unsafe condition on these products.
2001-12-20: This amendment adopts a new airworthiness directive (AD) that is applicable to General Electric Company (GE) CF6-50 turbofan engines. This amendment requires removal of old high pressure compressor (HPC) air ducts and mating hardware and replacement with newly designed air ducts and reworked mating hardware. This amendment also requires the repetitive inspection of certain reworked mating hardware. This amendment is prompted by reports of an uncontained low pressure turbine (LPT) disk failure that resulted from an air duct failure that caused a fan mid shaft (FMS) separation. The actions specified by this AD are intended to prevent HPC air duct failures that could result in FMS failures, that in turn could result in rejected takeoffs or uncontained LPT events, and to prevent HPC rear shaft failures that could result in uncontained engine failures.
91-13-04: 91-13-04 MCDONNELL DOUGLAS: Amendment 39-7035. Docket No. 91 NM-108-AD. \n\n\tApplicability: Model DC-9-87 (MD-87) series airplanes, certificated in any category. \n\n\tCompliance: Required as indicated, unless previously accomplished. \n\n\tTo prevent chafing and subsequent arcing of wires which could cause a fire resulting in the loss of engine controls and/or passengers becoming asphyxiated due to smoke inhalation, accomplish the following: \n\n\t(a)\tWithin 30 days after the effective date of this AD, modify the airplane by rerouting the wire assembly located on the right side of the airplane between stations Y=1022.000 and Y=1062.000 at longeron 3 in accordance with McDonnell Douglas Alert Service Bulletin A24-123, dated March 19, 1991. \n\n\t(b)\tAn alternative method of compliance or adjustment of the compliance time, which provides an acceptable level of safety, may be used when approved by the Manager, Los Angeles Aircraft Certification Office (ACO), FAA, Transport Airplane Directorate. \n\n\tNOTE: The request should be forwarded through an FAA Principal Maintenance Inspector, who may concur or comment and then send it to the Manager, Los Angeles ACO. \n\n\t(c)\tSpecial 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. \n\n\t(d)\tThe modification requirements shall be done in accordance with McDonnell Douglas Alert Service Bulletin A24-123, dated March 19, 1991. 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 McDonnell Douglas Corporation, Douglas Aircraft Company, P.O. Box 1771, Long Beach, California 90801, Attention: Business Unit Manager, Service Bulletins, Service Change and Modification Kits, Product Support, Mail Code 73-30. This information may be examined at the FAA, Northwest Mountain Region, Transport Airplane Directorate, 1601Lind Avenue S.W., Renton, Washington, or the Los Angeles Aircraft Certification Office, 3229 East Spring Street, Long Beach, California, or at the Office of the Federal Register, 1100 L Street N.W., Room 8401, Washington, D.C. \n\n\tThis amendment (39-7035, AD 91-13-04) becomes effective on June 27, 1991.
2007-26-14: The FAA is superseding an existing airworthiness directive (AD), which applies to all Airbus Model A300 B2 and B4 series airplanes; and all Model A300 B4-600, B4-600R, and F4-600R (collectively called A300-600) series airplanes. That AD currently requires repetitive inspections to detect cracking of the upper radius of the forward fitting of frame 47, and repair if necessary. This new AD retains those requirements, but reduces inspection thresholds and repetitive intervals, and adds related investigative and corrective actions. This AD also provides an optional terminating action for the repetitive inspections only for airplanes with cracking that is within certain limits, and a post-repair inspection program following the optional terminating action. This AD results from reports of additional cracking in airplanes that were inspected in accordance with the existing AD. We are issuing this AD to detect and correct fatigue cracking of the left and right upper radius at frame 47, which could propagate and result in reduced structural integrity of the airplane.
2001-12-21: This amendment supersedes an existing airworthiness directive (AD), applicable to all Boeing Model 747 series airplanes, that currently requires revising the Airplane Flight Manual to include procedures to prevent dry operation of the center wing fuel tank override/jettison pumps and, for certain airplanes, to prohibit operation of the horizontal stabilizer tank transfer pumps in-flight. For certain airplanes, this amendment requires installation of improved fuel pumps, which terminates the requirements of the existing AD. This amendment is prompted by new information received from the fuel pump manufacturer. The actions specified by this AD are intended to prevent contact between the rotating paddle wheel and the stationary end plates within the center wing tank override/jettison fuel pumps or horizontal stabilizer tank transfer pumps, which could cause sparks and/or a hot surface condition and consequent ignition of fuel vapor in the center wing tank or horizontal stabilizertank during dry pump operation (no fuel flowing).
94-15-05: This amendment adopts a new airworthiness directive (AD), applicable to all Boeing Model 747-400 series airplanes, that requires various inspections and functional tests of the thrust reverser control and indication system, and correction of any discrepancy found. This amendment is prompted by an investigation to determine the controllability of Model 747 series airplanes following an in-flight thrust reverser deployment, which has revealed that, in the event of thrust reverser deployment during high-speed climb or during cruise, these airplanes could experience control problems. The actions specified by this AD are intended to ensure the integrity of the fail safe features of the thrust reverser system by preventing possible failure modes in the thrust reverser control system that can result in inadvertent deployment of a thrust reverser during flight.