Results
97-06-16: This amendment adopts a new airworthiness directive (AD) that is applicable to McCauley Propeller Systems 1A103/TCM series propellers. This action supersedes priority letter AD 95-21-01 that currently requires visual inspections for cracks in the propeller hub of certain propellers using a 10X power magnifying-glass. This action requires an initial inspection for cracks in the propeller hub in accordance with a dye penetrant inspection procedure, replacement of propellers with cracks that do not meet acceptable limits, rework of propellers with cracks that meet acceptable limits, and repetitive inspections of all affected propellers. This amendment is prompted by development of a dye penetrant inspection and rework procedures. The actions specified by this AD are intended to prevent propeller separation due to hub fatigue cracking, which can result in loss of control of the aircraft.
99-26-15: This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A300 B2 and B4 series airplanes, that requires repetitive inspections to detect cracking of the inner skin panel of the longitudinal lap joint; and repair, or modification and new repetitive inspections, if necessary. This amendment is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified by this AD are intended to detect and correct stress corrosion cracking of the inner skin panel of the longitudinal lap joint, which could result in rapid depressurization of the airplane.
2011-14-03: We are adopting a new airworthiness directive (AD) for the products listed above. This AD requires repetitive inspections for cracking of the left and right upper center skin panels of the horizontal stabilizer, and corrective action if necessary. This AD was prompted by a report of a crack found in the upper center skin panel at the aft inboard corner of a right horizontal stabilizer. We are issuing this AD to detect and correct cracks in the horizontal stabilizer upper center skin panel. Uncorrected cracks might ultimately lead to the loss of overall structural integrity of the horizontal stabilizer.
97-06-15: 97-06-15 General Electric Company: Amendment 39-9972. Docket 95-ANE-41. Applicability: General Electric Company (GE) Models CF34-1A, -3A, and -3A2 turbofan engines, with high pressure compressor (HPC) stage 1 rotor disks, part number 6040T79G01, installed. These engines are installed on but not limited to Canadair Limited Model CL-600-2A12 and CL-600-2B16 aircraft. Note 1: This airworthiness directive (AD) applies to each engine identified in the preceding applicability provision, regardless of whether it has been modified, altered, or repaired in the area subject to the requirements of this AD. For engines that have been modified, altered, or repaired so that the performance of the requirements of this AD is affected, the owner/operator must request approval for an alternative method of compliance in accordance with paragraph (b) of this AD. The request should include an assessment of the effect of the modification, alteration, or repair on the unsafe condition addressed by this AD; and, if the unsafe condition has not been eliminated, the request should include specific proposed actions to address it. Compliance: Required as indicated, unless accomplished previously. To prevent HPC stage 1 rotor disk rupture, engine failure, and damage to the aircraft, accomplish the following: (a) Remove from service HPC stage 1 rotor disks prior to accumulating 6,000 cycles in service since new, and replace with a serviceable part. (b) An alternative method of compliance or adjustment of the compliance time that provides an acceptable level of safety may be used if approved by the Manager, Engine Certification Office. The request should be forwarded through an appropriate FAA Principal Maintenance Inspector, who may add comments and then send it to the Manager, Engine Certification Office. Note 2: Information concerning the existence of approved alternative methods of compliance with this airworthiness directive, if any, may be obtained from the Engine Certification Office. (c) This amendment becomes effective on May 27, 1997.
2002-26-14: This amendment adopts a new airworthiness directive (AD) that is applicable to all Boeing Model 767-300 series airplanes modified by supplemental type certificate ST01869AT-D. This action requires modifying the passenger entertainment system (PES) and revising the airplane flight manual. This action is necessary to ensure that the airplane crew is able to remove electrical power from the PES when necessary and is advised of appropriate procedures for such action. Inability to remove power from the PES during a non-normal or emergency situation could result in inability to control smoke or fumes in the airplane flight deck or cabin. This action is intended to address the identified unsafe condition.
2018-03-02: We are adopting a new airworthiness directive (AD) for certain 328 Support Services GmbH Model 328-300 airplanes. This AD requires contacting the FAA to obtain instructions for addressing the unsafe condition on these products, and doing the actions specified in those instructions. This AD was prompted by a determination that incomplete inspection instructions exist for the skin under outer and inner doublers left installed after the removal of a certain data link system. We are issuing this AD to address the unsafe condition on these products.
47-07-05: 47-07-05 FAIRCHILD: (Was Mandatory Note 7 of AD-724-2.) Applies to M-62 Series Aircraft. Compliance required at next periodic inspection. In order to eliminate the possibility of foreign objects entering the torque tube, install a boot at the point where the elevator control enters the torque tube in the front cockpit, and where the control stick enters the torque tube bracket in the rear cockpit. Also install cover plates on the sides of the torque tube bracket in the rear cockpit. (Fairchild Service Bulletin 44-62-5 dated October 10, 1944, covers this same subject.)
2002-26-20: This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model DC-9-81 (MD-81), DC-9-82 (MD-82), and DC-9-83 (MD-83) airplanes, and Model MD-88 airplanes, that requires an inspection of the disconnect panel area above the aft left lavatory for chafed or damaged wires or unacceptable clearance between the wires and adjacent structure, and corrective actions, if necessary. The actions specified by this AD are intended to prevent chafing of wires at the disconnect panel above the aft left lavatory, which could result in electrical arcing, and consequent fire in the cabin. This action is intended to address the identified unsafe condition.
2002-26-21: This amendment adopts a new airworthiness directive (AD), applicable to certain Dornier Model 328-100 and -300 series airplanes, that requires inspecting the electrical wire harness next to the fuel line at the left electric fuel pump for signs of chafing; securing the electrical wire harness to the fuel line using ty-rap; and taking corrective actions, if necessary. This action is necessary to prevent damage to the electrical wire harness, which could result in electrical arcing and an increased potential for fire or explosion. This action is intended to address the identified unsafe condition.
2011-13-03: We are adopting a new airworthiness directive (AD) for the products listed above. This AD requires inspecting certain Lycoming and TCM reciprocating engines with certain Hartzell Engine Technologies, LLC (HET) turbochargers installed, and disassembly and cleaning of the turbocharger center housing and rotating assembly (CHRA) cavities of affected turbochargers. This AD was prompted by a turbocharger failure due to machining debris left in the cavities of the CHRA during manufacture. We are issuing this AD to prevent seizure of the turbocharger turbine, which could result in damage to the engine, and smoke in the airplane cabin.