Results
96-14-05: This amendment supersedes an existing airworthiness directive (AD), applicable to certain Boeing Model 767 series airplanes, that currently requires an inspection of the control rods of the outboard leading edge slat, and follow-on actions (including repetitive ultrasonic inspections), if necessary. For certain airplanes, that AD also requires replacement of the control rod ends and attach bolts. It also provides for an optional terminating action for follow-on repetitive inspections. That AD was prompted by reports of cracks and worn attach bolts of the control rods of the leading edge outboards slats of the wings due to the high breakout torque in the joint of the control rod end. This amendment requires the installation of the previously optional terminating action. The actions specified by this AD are intended to prevent reduced controllability of the airplane and damage in the slat structure or fixed leading edge of the wing, as a result of cracks and worn attach bolts.
2021-06-02: The FAA is adopting a new airworthiness directive (AD) for all Airbus Helicopters Model AS332L, AS332L1, AS332C, and AS332C1 helicopters. This AD was prompted by the failure of a second stage planet gear installed in the main gearbox (MGB). This AD requires identifying the part number of each second stage planet gear assembly installed in the MGB, replacing an MGB having certain second stage planet gear assembly part numbers with a serviceable MGB, modifying the helicopter by installing a full flow magnetic plug (FFMP), repetitively inspecting the FFMP and the MGB bottom housing and conical housing for metal particles, analyzing any metal particles that are found, and applying corrective actions if necessary, as specified in European Union Aviation Safety Agency (EASA) ADs, which are incorporated by reference. The FAA is issuing this AD to address the unsafe condition on these products.
92-13-08: 92-13-08 BOEING: Amendment 39-8278. Docket No. 92-NM-13-AD.\n\n\tApplicability: Model 747-400 series airplanes; as listed in Boeing Alert Service Bulletin 747-38A2090, dated November 21, 1991; certificated in any category.\n\n\tCompliance: Required within 12 months after the effective date of this AD, unless accomplished previously.\n\n\tTo prevent fires in the drain mast internal space, accomplish the following:\n\n\t(a)\tInstall shields with sealant over the mid and aft drain masts in accordance with Boeing Alert Service Bulletin 747-38A2090, dated November 21, 1991.\n\n\t(b)\tInstall moisture resistant and thermal insulation tape around the forward drain tube and heater elements on the mid and aft drain masts in accordance with Boeing Alert Service Bulletin 747-38A2090, dated November 21, 1991.\n\n\t(c)\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, Seattle Aircraft Certification Office (ACO), FAA, Transport Airplane Directorate. Operators shall submit their requests through an FAA Principal Maintenance Inspector, who may concur or comment and then send it to the Manager, Seattle ACO.\n\n\tNOTE: Information concerning the existence of approved alternative methods of compliance with this airworthiness directive, if any, may be obtained from the Manager, Seattle ACO.\n\n\t(d)\tSpecial flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate the airplane to a location where the requirements of this AD can be accomplished.\n\n\t(e)\tThe installations shall be done in accordance with Boeing Alert Service Bulletin 747-38A2090, dated November 21, 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 Boeing Commercial Airplane Group, P. O. Box 3707, Seattle, Washington 98124. Copies may be inspected at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, Washington; or at the Office of the Federal Register, 1100 L Street NW., Room 8401, Washington, DC.\n\n\t(f)\tThis amendment becomes effective on August 5, 1992.
2021-05-18: The FAA is superseding Airworthiness Directive (AD) 2019-06-06 for all International Aero Engines AG (IAE) V2500-A1, V2522-A5, V2524- A5, V2525-D5, V2527-A5, V2527E-A5, V2527M-A5, V2528-D5, V2530-A5, and V2533-A5 model turbofan engines. AD 2019-06-06 required initial and repetitive borescope inspections (BSIs) of the M-flange and, if it fails the inspection, replacement of the diffuser case with a part eligible for installation. This AD requires an initial BSI of the M- flange and, if it fails the inspection, repetitive BSIs of the M-flange until replacement of the diffuser case M-flange. The FAA is issuing this AD to address the unsafe condition on these products.
96-13-01: This amendment adopts a new airworthiness directive (AD) that applies to MDB Flugtechnik AG Model MD3-160 airplanes. This action requires inserting a supplement Aircraft Flight Manual (AFM), installing a placard prohibiting aerobatics and spinning, inspecting the nosewheel steering system for damaged parts and improper rigging, and if necessary, replacing the parts and re-rigging the nosewheel steering system (NWS). Two incidents on certain MD3-160 airplanes while in flight causing the airplanes to go into a left spin and loose rudder control prior to landing prompted this AD action. The actions specified by this AD are intended to prevent the rudder pedals from locking up and the nosewheel steering from disengaging, which if not detected and corrected, could cause loss of control of the airplane.
2021-05-17: The FAA is superseding Airworthiness Directive (AD) AD 2019- 12-09 for certain Rockwell Collins, Inc. (Rockwell Collins) FDSA-6500 flight display system applications installed on airplanes. AD 2019-12- 09 imposed operating limitations on the traffic collision avoidance system (TCAS). AD 2019-12-09 was prompted by conflict between the TCAS display indications and aural alerts that may occur during a resolution advisory (RA) scenario. This AD retains the requirements of AD 2019-12- 09 until a software upgrade is completed. The FAA is issuing this AD to address the unsafe condition on these products.
78-12-02: 78-12-02 SCOTTISH AVIATION LIMITED: Amendment 39-3230. Applies to "Beagle" Model B206 Series II airplanes, certificated in all categories, which have exhaust system bellows assembly, P/N CE20901 or P/N CE 20806, installed. Compliance required as indicated, unless already accomplished. To minimize the possibility of hot exhaust gases escaping from a fractured exhaust bellows assembly and impinging on the tachometer electrical leads and other engine compartment components, accomplish the following: (a) Within the next 25 hours time in service after the effective date of this AD, inspect the exhaust system bellows assemblies, Part Number CE 20901 and Part Number CE 20806, for cracks, corrosion, and deterioration in accordance with paragraph 3(a) of Scottish Aviation Limited Service Bulletin No. B206/55 Issue 2, dated January 5, 1976, or an FAA approved equivalent, (hereinafter referred to as the Service Bulletin). (b) If a crack, corrosion, or deterioration is not found during the inspection required by paragraph (a) of this AD - (1) Within 50 hours time in service after the inspection required by paragraph (a) of this AD and, thereafter, at intervals not to exceed 50 hours time in service, inspect the bellows assemblies in accordance with paragraph 3(b) of the Service Bulletin; and (2) Within 100 hours time in service, or 3 months after the inspection required by paragraph (a), whichever occurs sooner, and, thereafter, at intervals not to exceed 100 hours time in service or 3 months, whichever occurs sooner, inspect the bellows assemblies in accordance with paragraph 3(a) of the Service Bulletin. (c) If a crack, corrosion, or deterioration is found during any inspection required by this AD, replace the affected bellows assembly with a serviceable part of the same part number. (d) For bellows assemblies installed as replacements - (1) Within 50 hours time in service after installation and, thereafter, at intervals not to exceed 50 hours time in service, inspect the bellows assemblies in accordance with paragraph 3(b) of the Service Bulletin; (2) Within 200 hours time in service, or 6 months, after installation, whichever occurs sooner, and, thereafter, at intervals not to exceed 100 hours time in service or 3 months, whichever occurs sooner, inspect the bellows assemblies in accordance with paragraph 3(a) of the Service Bulletin. This amendment becomes effective June 22, 1978.
2021-07-05: The FAA is superseding Airworthiness Directive (AD) 2007-26-52 which applied to certain Agusta S.p.A. (now Leonardo) Model A109C, A109E, and A109K2 helicopters. AD 2007-26-52 required inspecting for swelling, deformation, bonding separation, and for a crack on each main rotor blade (MRB) with a certain part-numbered tip cap installed, and removing the MRB from service before further flight if any of these conditions exist and exceed the prescribed limits. This AD retains all inspections for certain serial-numbered MRBs, but for MRBs with a certain tip cap installed, this AD requires dye-penetrant inspections rather than visual inspections. This AD was prompted by additional reports of in-flight loss of part of a tip cap. The FAA is issuing this AD to address the unsafe condition on these products.
96-12-20: This amendment supersedes an existing airworthiness directive (AD), applicable to certain Lockheed Model 382, 382B, 382E, 382F, and 382G series airplanes, that currently requires visual inspections to detect loose, missing, or deformed fasteners in the upper truss mounts of certain engines, inspections to detect cracking in the associated tangs, and replacement of damaged parts. This amendment adds a requirement for repetitive ultrasonic inspections to detect cracking of the upper tangs and replacement of cracked parts. This amendment also provides for an optional terminating action for the repetitive inspections, and revises the applicability of the rule to specify groupings of airplanes. This amendment is prompted by reports indicating that fatigue cracking of the tangs of the upper truss mount has been detected. The actions specified by this AD are intended to prevent multiple failures of the upper truss mounts due to problems associated with fatigue cracking, which could adversely affect the integrity of the engine mount structure. The incorporation by reference of Hercules Service Bulletin 382-71-20, dated March 18, 1994, as listed in the regulations, is approved by the Director of the Federal Register as of July 15, 1996. The incorporation by reference of Lockheed Alert Service Bulletin A382-71-19/A82-687, dated December 23, 1993, as listed in the regulations, was approved previously by the Director of the Federal Register as of February 18, 1994 (59 FR 5078, February 3, 1994).
2021-05-12: The FAA is adopting a new airworthiness directive (AD) for certain Airbus SAS Model A330-200 Freighter series airplanes. This AD was prompted by a determination that new or more restrictive airworthiness limitations are necessary. This AD requires revising the existing maintenance or inspection program, as applicable, to incorporate new or more restrictive airworthiness limitations, as specified in a European Union Aviation Safety Agency (EASA) AD, which is incorporated by reference. The FAA is issuing this AD to address the unsafe condition on these products.