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2017-17-19: We are adopting a new airworthiness directive (AD) for all The Boeing Company Model DC-9-81 (MD- \n\n((Page 41161)) \n\n81), DC-9-82 (MD-82), DC-9-83 (MD-83), and DC-9-87 (MD-87) airplanes, and Model MD-88 airplanes. This AD was prompted by reports of cracking of various structures in the bulkhead. This AD requires an inspection for cracking in these structures, and corrective actions if necessary. We are issuing this AD to address the unsafe condition on these products.
2002-01-05: This amendment adopts a new airworthiness directive (AD) that applies to all British Aerospace Model HP.137 Jetstream Mk.1, Jetstream Series 200, Jetstream Series 3101, and Jetstream Model 3201 airplanes that are equipped with certain main landing gear (MLG) radius rods. This AD requires you to inspect the MLG radius rod cylinders for the required conductivity or hardness standard. This AD also requires you to replace any MLG radius rod cylinder that does not meet this standard. This AD is the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for the United Kingdom. The actions specified by this AD are intended to prevent failure of the MLG due to incorrectly heat treated MLG radius rod cylinders. Such failure during takeoff, landing, or taxi operations, could lead to loss of airplane control.
78-05-01: 78-05-01 SIKORSKY AIRCRAFT: Amendment 39-3146. Applies to all Model S-58T series helicopters. Compliance required prior to May 25, 1978. To preclude possible fuel starvation of the PT6T-3 and PT6T-6 engines resulting from oil-to-fuel heater contamination, relocate the impending fuel bypass sensor lines on both engine power sections in accordance with the instructions set forth in Part II, Paragraph A, of Sikorsky Service Bulletin No. 58B30-12C, dated January 12, 1976. This amendment becomes effective March 31, 1978.
2002-01-07: This amendment adopts a new airworthiness directive (AD) for Bell Helicopter Textron Canada (BHTC) Model 430 helicopters that requires changes to the electrical power distribution system. This amendment is prompted by design deficiencies in the electrical systems. The actions specified by this AD are intended to prevent failure of both generators, loss of primary electrical power, and subsequent loss of control of the helicopter.
74-12-06: 74-12-06 LOCKHEED: Amendment 39-1867 as amended by Amendment 39-2512 is further amended by Amendment 39-3361. Applies to all Model 382 series airplanes, Serial Numbers 3946 and 4101 through 4541 certificated in all categories. Compliance as indicated. a) For airplanes with 5000 or more hours total time in service on the effective date of this AD comply with paragraph (c) within the next 50 hours time in service, and thereafter at intervals not to exceed 1000 hours time in service from the last inspection. b) For airplanes with less than 5000 hours total time in service on the effective date of the AD comply with paragraph (c) before the accumulation of 5050 hours total time in service, and thereafter at intervals not to exceed 1000 hours time in service from the last inspection. c) Inspect outer wing lower forward beam cap, web, and skin for cracks in the area extending from outer wing stations 144 to 165 and 195 to 214, both left and right in accordance with Lockheed Hercules Airfreighter Inspection Procedures, SMP 515-A, Card SP-75, revised October 15, 1978, or in an equivalent manner approved by the Chief, Engineering and Manufacturing Branch, FAA, Southern Region. d) Repair of the beam cap shall be in accordance with Lockheed Service Bulletin A382-169, Revision 7, and repair of the beam web in accordance with SMP 583, Lockheed Hercules Structural Repair Manual, or in an equivalent manner approved by the Chief, Engineering and Manufacturing Branch, FAA, Southern Region. e) Before the accumulation of 30,000 flight hours, preventive modification shall be installed in accordance with Lockheed Service Bulletin 382-152, Revision 2, and Alert Service Bulletin A382-169, Revision 7, or in an equivalent manner approved by the Chief, Engineering and Manufacturing Branch, FAA, Southern Region. f) Recurring inspections shall be performed in accordance with the following: 1) Recurring inspections for unmodified airplanes will be in accordance with paragraphs (a), (b), and (c) of this amendment. 2) Recurring inspections for airplanes with preventive modifications shall be in accordance with Lockheed Airfreighter Inspection Procedures, SMP 515-A, Card SP-75, revised October 15, 1978, or in an equivalent manner approved by the Chief, Engineering and Manufacturing Branch, FAA, Southern Region, and a detailed visual inspection of the front beam lower cap and adjacent structure including modifications across the entire length of the outer wing dry bays from outer wing stations 144 to 214 at each "C" check. 3) In addition to the recurring inspections of paragraphs (f)(1) and (f)(2), recurring inspections for airplanes with repairs shall be a detailed visual inspection of the front beam lower cap and adjacent structure, including repairs, across the entire length of the outer wing dry bays from outer wing stations 144 to 214 at each "C" check. g) Upon request of the operator, an FAA Maintenance Inspector, subjectto prior approval of the Chief, Engineering and Manufacturing Branch, FAA, Southern Region, may adjust the repetitive inspection intervals specified in this amendment to permit compliance at an established inspection period of the operator if the request contains substantiating data to justify the increase for such operator. h) Airplanes may be flown to a base for performance of the inspections required by this amendment in accordance with Federal Aviation Regulations 21.197 and 21.199. i) Report inspection findings to Chief, Engineering and Manufacturing Branch, FAA, Southern Region, P.O. Box 20636, Atlanta, Georgia 30320. Lockheed-Georgia Alert Service Bulletin A382-169, dated May 30, 1974, covers this same subject. Amendment 39-1867 became effective May 30, 1974. Amendment 39-2512 became effective February 13, 1976. This amendment 39-3361 becomes effective December 8, 1978.
2023-03-03: The FAA is adopting a new airworthiness directive (AD) for all Leonardo S.p.a. Model AB139 and AW139 helicopters. This AD was prompted by a report of a damaged tail rotor duplex bearing (TRDB). This AD requires repetitively inspecting certain TRDBs and depending on the results, replacing the TRDB or tail rotor actuator (TRA), or as an option, replacing the sliding control assembly. This AD also requires replacing an affected TRDB with a serviceable TRDB at a specified threshold and prohibits the installation of certain TRDBs or sliding control assemblies on any helicopter, 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.
2017-17-13: We are adopting a new airworthiness directive (AD) for certain Bombardier, Inc., Model BD-100-1A10 airplanes. This AD was prompted by reports of low clearance in the aft equipment bay between auxiliary power unit (APU) generator power cables and a hydraulic line, which can cause damage to wire insulation. This AD requires an inspection of the APU generator power cables and the adjacent hydraulic line for damage, and repair, if necessary; and modification of the APU generator power cable installation. We are issuing this AD to address the unsafe condition on these products.
2002-01-08: This amendment adopts a new airworthiness directive (AD) that is applicable to certain Israel Aircraft Industries, Ltd., Model Galaxy airplanes. This action requires disabling the baggage compartment heating blanket system. This action is necessary to prevent a short circuit between the baggage compartment heating blankets and the electrical connectors, which could result in fire and smoke in the baggage compartment. This action is intended to address the identified unsafe condition.
2004-08-01: This amendment adopts a new airworthiness directive (AD), applicable to certain Fokker Model F.28 Mark 0070 and 0100 series airplanes, that requires a magnetic inspection of the sliding members of the main landing gear (MLG) for cracking, and replacement of the sliding members with serviceable parts, if necessary. This action is necessary to prevent fatigue cracking of the sliding member, which could result in possible separation of the MLG from the airplane and consequent reduced controllability of the airplane upon landing and possible injury to passengers. This action is intended to address the identified unsafe condition.
2017-16-12: We are superseding Airworthiness Directive (AD) 2013-19-09 and AD 2014-25-51, which applied to all Airbus Model A318, A319, A320, and A321 series airplanes. AD 2013-19-09 required replacing Angle of Attack (AOA) sensor conic plates with AOA sensor flat plates. AD 2014-25-51 required revising the airplane flight manual (AFM) to advise the flightcrew of emergency procedures for abnormal Alpha Protection (Alpha Prot). This new AD requires replacing certain AOA sensors; and doing a detailed inspection and a functional heating test for discrepancies on certain AOA sensors, and replacing the affected AOA sensors. This AD was prompted by a report indicating that a Model A321 airplane encountered a blockage of two AOA probes during climb, leading to activation of the Alpha Prot while the Mach number increased. We are issuing this AD to address the unsafe condition on these products.