Results
2021-18-13: The FAA is adopting a new airworthiness directive (AD) for all General Electric Company (GE) CF34-8 model turbofan engines with a certain outer shell combustion liner (combustion outer liner shell) installed. This AD was prompted by two in-flight engine shutdowns (IFSDs) that occurred as a result of failures of the combustion outer liner shell. This AD requires a borescope inspection (BSI) or visual inspection of the combustion outer liner shell and, depending on the results of the inspection, possible replacement of the combustion outer liner shell. The FAA is issuing this AD to address the unsafe condition on these products.
2012-11-07: We are adopting a new airworthiness directive (AD) for all Honeywell International, Inc. ALF502L-2C; ALF502R-3; ALF502R-3A; ALF502R-5; LF507-1F; and LF507-1H turbofan engines. This AD was prompted by two reports of engines experiencing uncontained release of low-pressure (LP) turbine blades. This AD requires operational checks of the engine overspeed trip system. We are issuing this AD to prevent LP turbine overspeed leading to uncontained release of the LP turbine blades and damage to the airplane.
98-24-28: This amendment adopts a new airworthiness directive (AD), applicable to certain Allison Engine Company 250-B and 250-C series turboshaft and turboprop engines, that requires replacing existing beryllium copper main fuel control (MFC) bellows assemblies with Inconel 718 stainless steel welded MFC bellows assemblies. This amendment is prompted by reports of leaking MFC bellows assemblies resulting in an uncommanded minimum fuel flow condition, loss of engine fuel flow control and subsequent forced landing. The actions specified by this AD are intended to prevent MFC bellows assembly leakage, which can result in an uncommanded minimum fuel flow condition and subsequent loss of engine fuel flow control.
75-14-03: 75-14-03 BEECH: Amendment 39-2248. Applies to Model 200 series (Serial Numbers BB-2 through BB-66) airplanes in which the Collins AP105 autopilot is installed. Compliance: Required as indicated, unless already accomplished. To prevent the aircraft from exceeding 60 degrees bank angle as a result of an autopilot hard over, accomplish the following: A) Within the next 10 hours' time in service after receipt of the air mail letter dated June 11, 1975, or after the effective date of this AD, whichever occurs first, install the following placard adjacent to the autopilot controller: UNCOUPLE AUTOPILOT ABOVE 10,000 FEET MSL" and operate the aircraft in accordance with this limitation. B) Modify the Collins AP105 autopilot in accordance with Beechcraft Service Instructions No. 0744-180 or later revisions, or by the accomplishment of any equivalent modification approved by the Chief, Engineering and Manufacturing Branch, FAA, Central Region. C) Upon accomplishment of the modification provided in Paragraph B, compliance with the provisions of Paragraph A is no longer required. This amendment becomes effective July 3, 1975, to all persons except those to whom it was made effective earlier by air mail letter issued June 11, 1975.
98-25-01: This amendment supersedes Airworthiness Directive (AD) 96-23-19, which currently requires installing a new flap actuator overtravel stop and a roll pin through the overtravel stop and jack screw on certain Air Tractor, Inc. (Air Tractor) Models AT-300, AT-400, and AT-500 series airplanes. This AD requires replacing the existing flap actuator overtravel stop with a new one of improved design. This AD is the result of reports of the jack screw breaking through the roll pin hole on three of the affected airplanes that were already in compliance with AD 96-23-19. The actions specified by this AD are intended to prevent interference between the flap pushrod and the aileron pushrod caused by the flap actuator overtravel nut disengaging, which could result in loss of aileron control.
2018-04-07: We are adopting a new airworthiness directive (AD) for all The Boeing Company Model 747-100, 747-100B, 747-100B SUD, 747-200B, 747- 200C, 747-200F, 747-300, 747-400, 747-400D, 747-400F, 747SR, and 747SP series airplanes. This AD was prompted by a report of incidents involving fatigue cracking in transport category airplanes that are approaching or have exceeded their design service objective and a structural reevaluation by the manufacturer that identified additional structural elements that qualify as structural significant items (SSIs). This AD requires revising the maintenance or inspection program, as applicable, to include inspections that will give no less than the required damage tolerance rating (DTR) for certain SSI, performing repetitive inspections to detect cracks of all SSIs, and repairing cracked structures if necessary. Additionally, this AD requires all cracks involving an SSI or related structure in close vicinity to the SSI to be reported to Boeing. We are issuing this AD to address the unsafe condition on these products.
98-24-23: This amendment adopts a new airworthiness directive (AD) that is applicable to Eurocopter France Model SE.3160, SA.316B, SA.316C, and SA.319B helicopters. This action requires inspecting certain horizontal stabilizer spar tubes and replacing them if cracks are found or repairing them if crazing, corrosion, fretting marks, or scratches are found and are repairable. This amendment is prompted by several service reports of spar tube corrosion and fatigue cracks discovered during normal maintenance inspections, which could cause loss of the horizontal stabilizer and subsequent loss of control of the helicopter.
2003-08-03: This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas airplane models. This amendment requires repetitive inspections for chafing or potential chafing of the wiring for the throttle control module (TCM) on the center pedestal in the flight deck compartment, corrective actions if necessary, an inspection of the TCM to determine its part number and configuration, and modification of the TCM. Doing this modification terminates the repetitive inspections. The actions specified by this AD are intended to prevent chafing \nof wiring inside the TCM, fuel shutoff lever lights, and/or aft pedestal lightplates due to degradation of protective sleeving, which could result in electrical arcing and failure of the auto throttle/ speed control system and consequent smoke and/or fire in the cockpit.
2012-10-01: We are adopting a new airworthiness directive (AD) for Bell Helicopter Textron Canada Limited (BHTC) Model 427 helicopters which requires replacing certain tailboom attachment hardware and at certain intervals thereafter, determining the torque of that tailboom attachment hardware. This AD was prompted by a review of the tailboom attachment installation, which revealed that the torque value of the bolts specified in the BHTC Model 427 Maintenance Manual and applied during manufacturing was incorrect and exceeded the torque range recommended for the bolts. The actions are intended to prevent an over- torque of the tailboom attachment bolt (bolt), bolt failure, loss of the tailboom, and subsequent loss of control of the helicopter.
75-06-10: 75-06-10 BELL: Amendment 39-2128. Applies to Bell Models 206A and 206B helicopters, serial numbers 1 through 1163, certificated in all categories. Compliance required within the next 1200 hours' time in service after the effective date of this AD, unless already accomplished. To prevent possible failure of the cabin roof straps, P/N 206-031-200-23 and -24, accomplish the following: a. Remove the cabin roof straps, P/N 206-031-200-23 and -24, in accordance with items 1 through 4 of Bell Helicopter Company Service Bulletin No. 206-01-74-2, dated November 12, 1974, or later approved revision. b. Install the cabin roof straps, P/N 206-032-200-37 and -38, in accordance with items 5 through 9 of Bell Helicopter Company Service Bulletin No. 206-01-74-2, dated November 12, 1974, or later approved revision. 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 these documents from the manufacturer, may obtain copies upon request to the Service Manager, Bell Helicopter Company, P. O. Box 482, Fort Worth, Texas 76101. These documents may also be examined at the office of the Regional Counsel, Southwest Region, FAA, 4400 Blue Mound Road, Fort Worth, Texas, and at FAA Headquarters, 800 Independence Avenue S.W., Washington, D.C. A historical file on this AD, which includes the incorporated material in full, is maintained by the FAA at its headquarters in Washington, D.C., and at the Southwest Regional Office in Fort Worth, Texas. This supersedes Amendment 39-1437 (37 F.R. 8438), AD 72-09-02. This amendment becomes effective April 15, 1975.