Results
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.
98-24-25: This amendment adopts a new airworthiness directive (AD), applicable to all Lockheed Model L-188A and L-188C series airplanes, that requires revising the Airplane Flight Manual to provide the flightcrew with modified procedures and limitations for operating in icing conditions. This amendment is prompted by incidents and accidents involving airplanes equipped with turboprop engines that experienced tailplane stall due to ice accretion on the horizontal stabilizer of the airplane. The actions specified by this AD are intended to prevent undetected accretion of ice on the horizontal stabilizer, which could result in ice contaminated tailplane stall and consequent loss of pitch control.
98-22-07: This amendment adopts a new airworthiness directive (AD) that is applicable to all Dornier Model 328-100 series airplanes. This action requires revising the Airplane Flight Manual to provide the flightcrew with additional information regarding procedures to ensure complete pressurization of the hydraulic lines for the flaps. This amendment is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified in this AD are intended to prevent an uncommanded retraction of the flaps during takeoff, which could result in an aborted takeoff and consequent potential for runway overrun.
2012-10-09: We are superseding an existing airworthiness directive (AD) for certain Piper Aircraft, Inc. (type certificate previously held by The New Piper Aircraft Inc.) Models PA-31T and PA-31T1 airplanes. That AD currently requires correcting a model identification error on the aircraft data plate. Since we issued that AD, we have become aware that some owner/operators of the affected airplanes modified the aircraft data plate in error because of confusion in the serial number applicability. Because of the confusion, the manufacturer has issued new service information to clarify affected airplane serial numbers. This new AD requires determining the airplane model based on the serial number and modifying the aircraft data plate to properly identify the airplane model. This new AD also requires doing a detailed search for all applicable airworthiness related documents that apply to any airplane that has an incorrectly marked data plate and take necessary corrective actions based on the search findings. We are issuing this AD to correct the unsafe condition on these products.
2012-10-07: We are adopting a new airworthiness directive (AD) for certain Bombardier, Inc. Model CL-600-2C10 (Regional Jet Series 700, 701, & 702); CL-600-2D15 (Regional Jet Series 705); CL-600-2D24 (Regional Jet Series 900); and CL-600-2E25 (Regional Jet Series 1000) airplanes. This AD was prompted by reports of deformation of the pressure regulator on the oxygen cylinder, which was attributed to batches of raw material that did not meet required tensile strength. This AD requires an inspection to determine if certain oxygen pressure regulators are installed, and replacement of oxygen cylinder and regulator assemblies (CRAs) containing pressure regulators that do not meet required material properties. We are issuing this AD to prevent elongation of the pressure regulator neck, which could result in rupture of the oxygen cylinder, and in the case of cabin depressurization, oxygen would not be available when required.
59-10-06: 59-10-06 KAMAN: Applies to All K-240 Helicopters (Military HTK-1). Due to associated adverse service experience, the wood type cheek plate rotor blades, P/N K411042-1, -2, -7, and -8 are ineligible for use. These blades modified to conform to, or replaced by, fiberglass type cheek plate rotor blades, P/N K411042-77 and -78, are acceptable with a 2,500-hour retirement life.
75-22-09: 75-22-09 ROCKWELL: Amendment 39-2396. Applies to Model 112, S/N 3 through 380, certificated in all categories. Compliance required as indicated: (a) Before further flight and prior to each flight thereafter until complete inspection and modifications are accomplished, visually inspect the airplane structure at all aileron hinge positions. If visual inspection reveals distortion of the aileron skin or readily visible cracks in hinge doublers, comply with subparagraph (b)(3) below: (b) Within 10 hours' time in service, after the effective date of this AD, accomplish the following: (1) Replace all outboard aileron doublers in accordance with Rockwell International Service Bulletin No. SB-112-35 dated October 1, 1975, or later approved revision or by an equivalent method approved by the Chief, Engineering and Manufacturing Branch, Flight Standards Division, Southwest Region, Federal Aviation Administration, Fort Worth, Texas. (2) Inspect all inboard aileron doublers for cracks, proper doubler thickness (.040 inches), and preloading of hinge doublers in accordance with Rockwell International Service Bulletin No. SB-112-35 dated October 1, 1975, or later approved revision, or by an equivalent method approved by the Chief, Engineering and Manufacturing Branch, Flight Standards Division, Southwest Region, Federal Aviation Administration, Fort Worth, Texas. (3) If cracks, improper thickness, or preloading are found, replace doublers in accordance with Rockwell International Service Bulletin No. SB-112-35 dated October 1, 1975, or by an equivalent method approved by the Chief, Engineering and Manufacturing Branch, Flight Standards Division, Southwest Region, Federal Aviation Administration, Fort Worth, Texas, before further flight. This amendment becomes effective November 4, 1975.