Results
2005-12-02: The FAA is adopting a new airworthiness directive (AD) to supersede Airworthiness Directive (AD) 98-10-12, which applies to all Revo, Incorporated (REVO) (Type Certificate 1A13 formerly held by Colonial Aircraft Company, Lake Aircraft Corporation, Consolidated Aeronautics, Inc., and Global Amphibians LLC) Models Colonial C-2, Lake LA-4, Lake LA-4A, Lake LA-4P, and Lake LA-4-200 airplanes. AD 98-10-12 currently requires you to ensure adequate clearance between the attachment fitting and the horizontal stabilizer rear beam and between the attachment fitting and the stabilizer skin with inspections, possible replacement, and adjustments as necessary. This new AD is the result of several reports of fatigue cracks found in the horizontal stabilizer attachment fitting (part number 2-2200-21) of Model LA-4-200 airplanes that were in compliance with AD 98-10-12. This includes an airplane accident with a fatality attributed to a fatigue crack in the horizontal stabilizer attachment fitting. Consequently, this AD requires either a dye penetrant inspection of the horizontal stabilizer attachment fitting for any evidence of fretting, cracking, or corrosion (with necessary replacement and modification) or replacement of the fittings depending on the number of operational hours on the fitting. The AD also requires you to repetitively replace the fitting every 850 hours time-in-service (TIS), repetitively inspect (visually) the fittings between replacement times, and report to FAA the results of the initial inspection and any cracks found on repetitive inspections. We are issuing this AD to detect, correct, and prevent future cracks in the horizontal stabilizer attachment fitting, which could result in failure of the horizontal stabilizer attachment fitting. This failure could result in loss of control of the airplane.
2018-07-08: We are adopting a new airworthiness directive (AD) for Agusta S.p.A. (Agusta) Model A109E, A109K2, A109S, AW109SP, A119, and AW119 MKII helicopters. This AD reduces the life limit of and requires inspecting a tail rotor blade retention bolt (bolt). This AD is prompted by the discovery of a cracked bolt. The actions of this AD are intended to address an unsafe condition on these products.
89-11-03: 89-11-03 BOEING: Amendment 39-6223. \n\tApplicability: Model 737-300 and -400 series airplanes, certificated in any category. \n\n\tCompliance: Required as indicated, unless previously accomplished. \n\n\tTo prevent the ingestion of "blue ice" into the engine and the potential loss of an engine, accomplish the following: \n\n\tA.\tWithin 200 hours time-in-service after the effective date of this AD: \n\n\t\t1.\tConduct a leak check of the forward lavatory service system, in accordance with Boeing Telex M-7272-89-2127 dated April 25, 1989, and repeat the check at intervals thereafter not to exceed 200 hours time-in-service; or \n\n\t\t2.\tDrain the forward lavatory system, lock the lavatory(s), and placard the lavatory(s) inoperative. \n\n\tB.\tLeaks discovered at any time must be repaired prior to further flight, or the forward lavatory system must be drained, and the lavatory(s) locked and placarded inoperative, prior to further flight. \n\n\tC.\tAn alternate means of compliance or adjustmentof the compliance time, 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\tNOTE: The request should be forwarded through an FAA Principal Maintenance Inspector (PMI), who will either concur or comment and then send it to the Manager, Seattle Aircraft Certification Office. \n\n\tD.\tSpecial flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes to a base for the accomplishment of the inspections and/or modifications required by this AD. \n\n\tAll persons affected by this directive who have not already received the appropriate service information from the manufacturer may obtain copies upon request to Boeing Commercial Airplanes, P.O. Box 3707, Seattle, Washington, 98124. This information may be examined at the FAA, Northwest Mountain Region, Transport Airplane Directorate, 17900 Pacific Highway South, Seattle, Washington, or at the Seattle Aircraft Certification Office, FAA, Northwest Mountain Region, 9010 East Marginal Way South, Seattle, Washington. \n\n\tThis amendment (39-6223, AD 89-11-03) becomes effective on June 5, 1989.
2018-07-06: We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 747-8 series airplanes. This AD was prompted by a report of restricted movement of the right brake pedals after landing rollout. This AD requires revising the airplane flight manual (AFM) by adding an autobrake system limitation. This AD also requires modifying intercostal webs near a main entry door, which terminates the AFM limitation. We are issuing this AD to address the unsafe condition on these products.
2005-13-15: The FAA is adopting a new airworthiness directive (AD) for certain Boeing Model 737-200, -200C, -300, -400, -500, -600, -700, - 700C, -800, and -900 series airplanes. This AD requires a one-time detailed inspection for discrepancies of the secondary fuel vapor barrier of the wing center section, and related investigative/ corrective actions if necessary. This AD is prompted by reports that the secondary fuel vapor barrier was not applied correctly to, or was missing from, certain areas of the wing center section. We are issuing this AD to prevent fuel or fuel vapors from leaking into the cargo or passenger compartments and coming into contact with a possible ignition source, which could result in fire or explosion.
62-23-02: 62-23-02 BELL: Amdt. 498 Part 507 Federal Register October 23, 1962. Applies to Model 47 Series Helicopters Equipped with Main Rotor Mast Thrust Bearing, P/N 47-130-110-1. Compliance required as indicated. Excessive wear and evidence of impending failure of the main rotor mast thrust bearing have occurred. To preclude progression of bearing deterioration to a hazardous degree, accomplish the following: (a) Within the next 25 hours' time in service following the effective date of this AD and thereafter at periods not to exceed 25 hours, conduct a close visual inspection of the engine oil filter. (b) If metal particles are found during any inspection of the engine oil filter, the following shall be accomplished prior to further flight: (1) The source of the contaminant shall be located and eliminated and other components of the engine and transmission which may be jeopardized by metal particles shall be inspected and overhauled as prescribed by the appropriate Bell maintenance manual; and (2) The main rotor mast thrust bearing, P/N 47-130-110-1, shall be thoroughly inspected and replaced with a like component if found not to be in a serviceable condition. (c) Clean engine oil filter carefully before reinstalling. NOTE: For the purpose of this AD, the operations outlined under (a) and (c) are considered to be preventive maintenance and may, therefore, be accomplished by persons specified in Section 18.10(c) of the Civil Air Regulations. This directive effective October 29, 1962. Revised September 16, 1966.
2018-07-12: We are adopting a new airworthiness directive (AD) for all Airbus Model A350-941 airplanes. This AD requires performing repetitive station position pick-off unit (SPPU) calibration tests, and applying the corresponding airplane fault isolation if necessary. This AD was prompted by a report indicating malfunctions of the SPPU and failures of the internal wiring due to water ingress via certain electrical connectors, inducing subsequent icing during flight. We are issuing this AD to address the unsafe condition on these products.
85-12-07: 85-12-07 FOKKER: Amendment 39-5080. Applies to Model F27 series airplanes, serial numbers 10105 through 10648, 10654, 10658 through 10660, 10662 through 10667 and 10669 through 10672, certificated in all categories. To ensure structural integrity of the rudder tab, accomplish the following, unless already accomplished: A. Conduct a one-time visual inspection of the rudder tab in accordance with Fokker Service Bulletin F27/55-58, dated March 28, 1985, within twenty days after the effective date of this AD. B. If incorrect rivets are found, repair the tab before further flight in accordance with the above service bulletin or in a manner approved by the Manager, Seattle Aircraft Certification Office. C. 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. D. 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. All persons affected by this directive who have not already received these documents from the manufacturer may obtain copies upon request to Fokker B.V., Product Support, P.O. Box 7600, 11172J Schiphol Oost, The Netherlands. These documents also may be examined at FAA Northwest Mountain Region, 17900 Pacific Highway South, Seattle, Washington, or Seattle Aircraft Certification Office, 9010 East Marginal Way South, Seattle, Washington. This amendment becomes effective June 28, 1985.
2005-13-10: The FAA adopts a new airworthiness directive (AD) for certain Cessna Aircraft Company (Cessna) Models 172R, 172S, 182T, T182T, 206H, and T206H airplanes. This AD requires you to inspect any MC01-3A I.C. 9 or MC01-3A I.C. 10 main electrical power junction box circuit breakers for correct amperage (amp) (a correct 40-amp circuit breaker) and replace any incorrect amp circuit breaker with the correct 40-amp circuit breaker. This AD results from several reports of circuit breakers that are not the correct 40-amp circuit breaker installed in the MC01-3A main electrical power junction box. We are issuing this AD to replace any incorrect circuit breaker installed in the MC01-3A I.C. 9 or MC01-3A I.C. 10 main electrical power junction box, which could result in premature tripping of the power junction box main feeder circuit breakers and could lead to partial or complete loss of all electrical power on the airplane. This condition could lead to the loss of all navigation and communication equipment and lighting in the cockpit.
2005-13-09: The FAA adopts a new airworthiness directive (AD) for certain GROB-WERKE Model G120A airplanes. This AD requires you to replace the main landing gear (MLG) up-lock hook assembly. This AD results from mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for Germany. We are issuing this AD to prevent the MLG from becoming jammed and not extending, which could result in loss of control of the airplane during landing. During the comment period for the notice of proposed rulemaking (NPRM) regarding this action, we received a comment recommending the incorporation of service information to install connecting bolts secured with cotter pins instead of connecting bolts secured with snap rings. All U.S.- registered airplanes currently have these actions incorporated so these actions do not impose an additional burden over that proposed in the NPRM and prior public comment is not necessary. However, we are reopening the comment period to allow the public the chance to comment on these additional actions.