Results
2010-16-12: We are adopting a new airworthiness directive (AD) for certain Model 777-200LR and -300ER series airplanes equipped with GE90-100 series engines. This AD requires replacing the insulation blanket fasteners of the lower aft cowl of the thrust reverser. This AD also requires inspecting the oil scavenge tube on the turbine rear frame of the engine for damage, and replacement if necessary. This AD results from a determination of insufficient clearance and subsequent interference between the oil scavenge tube on the turbine rear frame of the engine and the bolt on the aft cowl insulation blanket of the thrust reverser. We are issuing this AD to prevent damage and possible puncture of the oil scavenge tube and consequent oil loss, which could result in an in-flight shutdown of the engine.
99-23-20: This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 737-100, -200, -300, -400, and -500 series airplanes. For certain airplanes, this AD requires installation of a transient suppression diode in the wiring circuit of the refueling valve-to-float switch of each fuel tank. For certain other airplanes, this AD requires replacement of the existing transient suppression diode with an improved diode. This AD also requires a functional test to verify proper installation of each diode, and corrective action, if necessary. This amendment is prompted by incidents of electrical fire during fueling of the airplane, due to a short circuit and overheating of a transient suppression diode. The actions specified by this AD are intended to prevent such conditions, which could result in electrical arcing and ignition of fuel vapors at the refueling receptacle for the fuel tanks, and consequent fire during airplane fueling.
58-24-01: 58-24-01 HAMILTON STANDARD: Applies to All 2H17K3, 2H17U3, 2H17AA3 and 2H17AC3 Hollow Steel Propeller Blades. Compliance required as indicated. It has been determined that 2H17K3, 2H17U3, and 2H17AA3 blades have a substantial reduction in fatigue resistance after 5,000 hours' operational time. The 2H17AC3 blades have shown no reduction in fatigue resistance at 5,400 hours' operational time, but the limited number of blades in service does not warrant continued sampling inspection. Therefore, these blades must be removed from service, as follows: 1. 2H17K3, 2H17U3, and 2H17AA3 blades when they have accumulated 5,000 operational hours. 2. 2H17AC3 blades when they have accumulated 5,400 operational hours. (Hamilton Standard Service Bulletins Nos. 305 and 559 cover this same subject.) This supersedes AD 54-23-03.
90-01-10: 90-01-10 AIRBUS INDUSTRIE: Amendment 39-6448. Docket No. 89-NM-162-AD. Applicability: All Model A300 series airplanes, Serial Number 001 through 156, certificated in any category. Compliance: Required as indicated, unless previously accomplished. To ensure structural integrity of the airplane, accomplish the following: A. Inspect longitudinal lap joints for cracks as follows: 1. Inspection of "special" areas, as defined in paragraph 1.C(1) of Airbus Industrie Service Bulletin A300-53-211, Revision 1, dated April 10, 1989. a. Prior to the accumulation of 24,000 landings, or within 10 days after the effective date of this AD, whichever occurs later, perform an eddy current inspection in special areas of the longitudinal lap joints, in accordance with paragraph 2.B. of the service bulletin. b. If no cracks are found, repeat this inspection at intervals not to exceed 6,000 landings. c. If a crack is detected, repair prior to further flight, in accordance with the service bulletin. 2. Inspection of "standard" areas, as defined in paragraph 1.C(2) of Airbus Industrie Service Bulletin A300-53-211, Revision 1, dated April 10, 1989. a. Prior to the accumulation of 32,000 landings, or within 10 days after the effective date of this AD, whichever occurs later, perform an eddy current inspection of the standard areas of the longitudinal lap joints, in accordance with paragraph 2.B. of the service bulletin. b. If no crack is found, repeat the inspection at intervals not to exceed: (1) 6,000 landings for longitudinal lap joints with bonded doublers; (2) 8,000 landings for longitudinal lap joints without bonded doublers. c. If a crack is found, repair prior to further flight, in accordance with the service bulletin. 3. Inspection of modified or repaired areas, as defined in Tables 1 and 2 of Airbus Industrie Service Bulletin A300-53-211, Revision 1, dated April 10, 1989. a. Prior to the accumulation of the threshold values (landings since first flight) identified in Tables 1 or 2 of the service bulletin, or within 60 days after the effective date of this AD, whichever occurs later, perform an eddy current inspection of the longitudinal lap joints in modified or repaired areas in accordance with paragraph 2.B. of the service bulletin. b. If no crack is found, repeat the inspections at intervals not to exceed 6,000 landings for each repair solution identified in Tables 1 and 2 of the service bulletin. c. If a crack is found, repair prior to further flight, in accordance with the service bulletin. B. Prior to the accumulation of 24,000 landings or 15 years since new, whichever occurs first, or within 60 days after the effective date of this AD, whichever occurs later, inspect fuselage bonded inner doublers of longitudinal lap joints in Sections 13 through 18 (except Sections 16 and 17 at Stringer 31 left-hand and right-hand) for disbonding and corrosion, in accordance with Airbus Industrie Service Bulletin A300-53-229, dated August 29, 1988, or Revision 1, dated April 10, 1989, or Revision 2, dated July 28, 1989. 1. If no disbonding or corrosion is found in areas other than Sections 13 and 14, no further action is required in those areas. 2. If disbonding or corrosion is found in Sections 13 and 14, repeat the inspections of these areas at intervals not to exceed 12,000 landings or 8 years since last inspection, whichever occurs first, in accordance with paragraph 1.B. of the service bulletin. 3. If disbonding is detected, repair prior to further flight, in accordance with the service bulletin. C. Prior to the accumulation of 24,000 landings or 12 years since new, whichever occurs first, or within 60 days after the effective date of this AD, whichever occurs later, inspect fuselage bonded inner doublers of longitudinal lap joints in Sections 16 and 17 at Stringer 31 left- hand and right-hand for disbonding and corrosion, in accordance with Airbus Industrie Service Bulletin A300-53-229, Revision 2, dated July 28, 1989. Airplanes older than 12 years must be inspected within 12 months after the effective date of this AD. 1. If no disbonding or corrosion is found, no further action is required. 2. If disbonding is detected, repair prior to further flight, in accordance with the service bulletin. D. An alternate means of compliance or adjustment of the compliance time, which provides an acceptable level of safety, may be used when approved by the Manager, Standardization Branch, ANM-113, FAA, Northwest Mountain Region. NOTE: The request should be forwarded through an FAA Principal Maintenance Inspector (PMI), who will either concur or comment, and then send it to the Manager, Standardization Branch, ANM-113. E. Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes to a base in order to comply with the requirements of this AD. All personsaffected by this directive who have not already received the appropriate service documents from the manufacturer may obtain copies upon request to Airbus Industrie, Airbus Support Division, Avenue Didier Daurat, 31700 Blagnac, France. These documents may be examined at the FAA, Northwest Mountain Region, Transport Airplane Directorate, 17900 Pacific Highway South, Seattle, Washington, or the Standardization Branch, 9010 East Marginal Way South, Seattle, Washington. This amendment (39-6448, AD 90-01-10) becomes effective on February 5, 1990.
2021-02-08: The FAA is superseding Airworthiness Directive (AD) 2018-19- 01, which applied to all Airbus Helicopters Model AS-365N2, AS 365 N3, EC 155B, EC155B1, SA-365N1, and SA-366G1 helicopters. AD 2018-19-01 required repetitive inspections of the aft fuselage outer skin. This AD continues to require repetitive inspections and adds Model SA-365N helicopters, as specified in a European Union Aviation Safety Agency (EASA) AD, which is incorporated by reference. This AD was prompted by aft fuselage (baggage compartment area) outer skin disbonding and a determination that Model SA-365N helicopters are also affected by the unsafe condition identified in AD 2018-19-01. The FAA is issuing this AD to address the unsafe condition on these products.
99-24-01: Emergency Fuel Shutoff Cable
2014-08-03: We are adopting a new airworthiness directive (AD) for certain Bombardier, Inc. Model CL-600-2C10 (Regional Jet Series 700, 701, & 702) airplanes, Model CL-600-2D15 (Regional Jet Series 705) airplanes, Model CL-600-2D24 (Regional Jet Series 900) airplanes, and Model CL- 600-2E25 (Regional Jet Series 1000) airplanes. This AD was prompted by a determination that for certain slat system failure cases, the resulting slat skew could lead to failure of the slat system. This AD requires replacing certain locking plates with certain anti-migration assemblies on certain left and right wing slats. We are issuing this AD to prevent failure of the eccentric pins at the slat track attachment, and slat panels consequently disconnecting from the wing, leading to the loss of the airplane.
2014-07-06: We are superseding airworthiness directive (AD) 2007-19-09R1 for all Turbomeca S.A. Arriel 2B1 turboshaft engines that do not have modification TU157 incorporated. AD 2007-19-09R1 required replacement of the hydromechanical metering unit (HMU) with a serviceable HMU. This AD requires HMU replacement; reduction of the compliance interval; and inclusion of the power turbine C2 cycle consumption rate when determining compliance times. This AD was prompted by reports of ruptures on HMU constant delta pressure valves that have less than 2,000 hours in service. We are issuing this AD to prevent failure of the HMU, which could lead to damage to the engine, and damage to the aircraft.
99-23-21: This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 757 series airplanes, that requires a modification of the reverse thrust lever assemblies and replacement of the spring bumper assemblies of the thrust reverser sleeves with new assemblies. This amendment is prompted by an FAA review of the thrust reverser system on all transport category airplanes including the Boeing Model 757 series airplane. The actions specified by this AD are intended to prevent operation with an energized sync lock or malfunctioning sleeve locking devices, which could result in the deployment of a thrust reverser in flight and subsequent reduced controllability of the airplane.
99-23-05: This amendment adopts a new airworthiness directive (AD), applicable to all Bombardier Model DHC-8-101, -102, -103, -106, -201, -202, -301, -311, and -315 series airplanes, that requires repetitive detailed visual inspections and high frequency eddy current inspections to detect cracking of the wing upper skin and ladder plates at over wing access panels between certain stations; and repair, 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 fatigue cracking of the wing ladder plates, which, if not corrected, could reduce the structural integrity of the wing.