Results
2024-17-09: The FAA is adopting a new airworthiness directive (AD) for certain Embraer S.A. (Embraer) Model EMB-505 airplanes. This AD was prompted by analysis of the left-hand (LH) refreshment center and LH forward cabinet that identified the need for installing structural reinforcements. This AD requires installing structural reinforcements as specified in an Ag[ecirc]ncia Nacional de Avia[ccedil][atilde]o Civil (ANAC) AD, which is incorporated by reference. The FAA is issuing this AD to address the unsafe condition on these products.
2016-18-01: We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 737-600, -700, -700C, -800, -900, and -900ER series airplanes. This AD was prompted by reports of heavy corrosion and chrome damage on the forward and aft trunnion pin assemblies of the right and left main landing gears (MLGs). This AD requires repetitive lubrication of the forward and aft trunnion pin assemblies of the right and left MLGs; repetitive inspections of these assemblies for corrosion and chrome damage, and related investigative and corrective actions if necessary; and installation of new or modified trunnion pin assembly components, which will terminate the repetitive lubrication and repetitive inspections. We are issuing this AD to detect and correct heavy corrosion and chrome damage on the forward and aft trunnion pin assemblies of the right and left MLGs, which could result in cracking of these assemblies and collapse of the MLGs.
71-01-05: 71-01-05 MCDONNELL DOUGLAS: Amdt. 39-1140. Applies to DC-9 series airplanes certificated in all categories. \n\n\tCompliance required within the next 500 hours time in service after the effective date of this AD, unless already accomplished. \n\n\tTo prevent failures in the deployment of the emergency evacuation slide, accomplish the following: \n\n\t(a)\tModify the Douglas Aircraft Company P/N 3753213-39 latch clip in accordance with Douglas Aircraft Company All Operators Letter (AOL) 9-370, dated November 17, 1969, or Revision A thereto, dated November 19, 1970, or later FAA approved revisions, to provide a notch in the latch clip at the point of interference with the clevis pin in the swaged head of the emergency evacuation slide deployment cable assembly, or \n\n\t(b)\tReplace Douglas P/N 3753213-39 latch clip with Douglas P/N 3753213-99 latch clip, or \n\n\t(c)\tAn equivalent modification approved by the Chief, Aircraft Engineering Division, FAA Western Region. \n\n\tThis amendment becomes effective February 17, 1971.
84-25-06: 84-25-06 HAMILTON STANDARD: Amendment 39-4970. Applies to Hamilton Standard Model 23LF-335 and -371 variable pitch propellers installed on, but not limited, to British Aerospace HP137 aircraft certificated in any category. Compliance is required within the next 20 hours time in service or before the next propeller landing reversal, whichever occurs first, following the effective date of this AD, unless already accomplished, and at every 50 propeller landing reversals thereafter. To detect cracks in the blades/counterweights which could cause possible propeller failure, accomplish the following: (a) Clean and inspect for cracks in the propeller blades and counterweights in accordance with section 2, paragraphs A and B of Hamilton Standard ASB No. A27, Revision 1, November 1, 1984, or FAA approved equivalent. (b) Blades and counterweights found to have evidence of cracks must be removed from service and replaced with a serviceable assembly prior to further flight.Aircraft may be ferried in accordance with the provisions of Federal Aviation Regulations (FARs) 21.197 and 21.199 to a base where the AD can be accomplished. Upon request, an equivalent means of compliance with the requirements of this AD may be approved by the Manager, Engine and Propeller Standards Staff, ANE-110, FAA, 12 New England Executive Park, Burlington, Massachusetts 01803. The manufacturer's specifications and procedures identified and described in this directive are incorporated herein and made a part hereof pursuant to 5 U.S.C. 552(a)(1). All persons affected by this directive who have not already received this document from the manufacturer may obtain copies upon request to Hamilton Standard, Division of United Technologies Corporation, Windsor Locks, Connecticut 06096. These documents also may be examined at the Office of the Regional Counsel, FAA, Attn: Rule Docket No. 84-ANE-22, 12 New England Executive Park, Burlington, Massachusetts 01803. This amendment becomes effective on January 3, 1985.
52-23-01: 52-23-01 EDISON FIRE DETECTORS: Applies to All Aircraft Equipped With Edison P/N 35534, Fire Detectors Installed in Junction Boxes. To be accomplished not later than next engine change after January 1, 1953. In order to prevent grounding of either or both terminals of Edison P/N 35534 fire detectors due to inadequate clearance between the detector terminals and the structure to which the junction box and detector assembly are mounted, or the junction box cover in some instances, the following corrective action must be accomplished. The dimensions of the P/N 35534 Edison fire detector should be compared with the dimensions of the junction box employed by each operator to assure that there is sufficient clearance between the detector terminals and the structure to which it is mounted, or the cover. Sufficient clearance will depend on the construction of the junction box, but 3/16 of an inch may be used as a general guide. If such clearance does not exist an appropriate modification should be made, or appropriate insulation provided between the terminals and the structure or the junction box cover, as the case may be. (Douglas General Service Letter DC-6 No. 115, dated January 29, 1952, covers this same subject.)
2024-20-05: The FAA is adopting a new airworthiness directive (AD) for Columbia Helicopters, Inc., Model 234 helicopters and restricted category Model CH-47D helicopters. This AD was prompted by two reports of a flight control rigid connecting link (link) failure, due to a manufacturing defect. This AD requires removing certain links from service and prohibits installing those links. The FAA is issuing this AD to address the unsafe condition on these products.
2016-17-15: We are adopting a new airworthiness directive (AD) for certain Bombardier, Inc. Model CL-600-2B19 (Regional Jet Series 100 & 440) airplanes. This AD was prompted by the need for more stringent inspection requirements for certain affected components. This AD requires revising the maintenance or inspection program to incorporate certain revised airworthiness limitations (AWL) and require repairs of affected components. We are issuing this AD to detect and correct fatigue cracking in the affected components; such cracking could result in loss of structural integrity.
69-25-03: 69-25-03\tBOEING: Amdt. 39-884. Applies to Model 727 series airplanes listed in Boeing Service Bulletin 71-43 dated 10 November 1969, or later FAA approved revisions. \n\n\tCompliance required within the next 500 hours time in service after the effective date of this AD, unless already accomplished. \n\n\tTo prevent engine cone bolt failures, accomplish the inspections and bolt replacement in accordance with the instructions in Boeing Service Bulletin 71-43, dated 10 November 1969, Section II, Pages 4, 5, and 6, Steps A through F, or later FAA approved revisions, or an equivalent inspection and replacement procedure approved by the Chief, Aircraft Engineering Division, FAA Western Region. \n\n\tThis amendment becomes effective December 5, 1969.
2016-17-06: We are adopting a new airworthiness directive (AD) for all The Boeing Company Model 767-200 and -300 series airplanes. This AD was prompted by an evaluation by the design approval holder (DAH) indicating that the aft pressure bulkhead web to pressure chord joint is subject to widespread fatigue damage (WFD). This AD requires repetitive high frequency eddy current (HFEC) inspections of the aft pressure bulkhead web at fasteners common to the bulkhead web and pressure chord, around the entire circumference of the pressure chord, for any crack, and repair of cracks. We are issuing this AD to detect and correct cracks in the aft pressure bulkhead web. Such cracking could result in the loss of structural integrity of the airplane.
70-14-02: 70-14-02 BELL: Amendment 39-1023. Applies to all Bell Model 47D, 47D-1, 47G, 47G-2 and 47H-1 helicopters certificated in all categories, and to any other helicopters equipped with tail rotor hub assembly bolt (also called a blade grip retaining bolt or a bearing retaining bolt), P/N 47-641-052-3. Compliance required as indicated. To detect and prevent possible failure of the tail rotor hub assembly bolt due to a fatigue crack and to correct any improper installation of the hub bolt, accomplish the following: (a) Within the next 50 hours time in service, remove and replace bolts with 550 hours or more total time in service on the effective date of this AD. (b) Within the next 50 hours time in service, inspect, one time, bolts with less than 550 hours total time in service on the effective date of this AD as follows: (1) Remove and disassemble the tail rotor assembly and remove the hub assembly bolts. (2) Inspect the bolt head to shank radius for cracks using a magnetic particle or equivalent inspection method. (3) Replace cracked bolts before further flight as specified in paragraph (e). (c) Remove and replace bolts with less than 550 hours total time in service on the effective date of this AD at or prior to accumulating 600 hours total time in service. (d) Remove and replace all replacement bolts at or prior to accumulating 600 hours total time in service. (e) Install bolts in accordance with paragraph 6-16.e., Section VI, Model 47D-1, 47G and 47G-2 Maintenance and Overhaul Instruction Manual, as revised August 15, 1961, or in accordance with equivalent FAA approved procedures. This amendment becomes effective August 10, 1970.