Results
2022-25-02: The FAA is superseding Airworthiness Directive (AD) 2020-18- 04, which applied to Airbus SAS Model A350-941 and -1041 airplanes. AD 2020-18-04 required a one-time health check of the slat power control unit (PCU) torque sensing unit (TSU) for discrepancies, and corrective actions if necessary; a detailed inspection of the left-hand (LH) and right-hand (RH) slat transmission systems for discrepancies, and corrective actions if necessary; and LH and RH track 12 slat gear rotary actuator (SGRA) water drainage and vent plug cleaning (which includes an inspection for moisture). This AD was prompted by a determination that requiring modification of the PCU by replacing each affected slat PCU with a serviceable PCU (one having a different part number) is necessary. This AD continues to require the actions required by AD 2020-18-04, and also requires modification (replacement of each affected slat PCU with a slat PCU having a different part number), and revising the limitations on the installation of affected parts; 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.
77-09-05: 77-09-05 CANADAIR: Amendment 39-2886. Applies to Canadair CL-215-1A10 airplanes, Serial Numbers 1001 to 1040 inclusive, in all categories. Compliance is required as indicated unless already accomplished. To assure the structural integrity of the nose landing gear door closing rods, P/N 215- 85009, and the sequencing redundancy mechanism rod, P/N 215-85026, accomplish the following: (a) On aircraft that have been in service for 12 months or more, compliance with paragraph (c) is required and flight operations are restricted to land operations until compliance is shown. (b) On aircraft that have been in service less than 12 months, compliance with paragraph (c) is required before achieving 12 months in service. (c) Inspect and rework in accordance with Canadair Service Information Circular No. 101-CL-215 dated May 6, 1975, or an equivalent method of compliance. A later revision and an equivalent method of compliance must be approved by the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region. (d) Upon request, with substantiating data submitted through an FAA Maintenance Inspector, the compliance time specified in this AD may be increased by the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region. This amendment becomes effective May 9, 1977.
2013-14-04: We are adopting a new airworthiness directive (AD) for all Airbus Model A330-223F, -223, -321, -322, and -323 airplanes. This AD was prompted by fatigue load analysis that determined that the inspection interval for certain pylon bolts must be reduced. This AD requires a torque check of forward engine mount bolts, and replacement if necessary. We are issuing this AD to detect and correct loose or broken bolts, which could lead to engine detachment in-flight, and damage to the airplane.
2013-21-03: We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 747-8F and 747-8 series airplanes. This AD requires a detailed inspection of the power control actuator (PCA) installation to determine if a bushing is installed, a general visual inspection between the horizontal stabilizer rear spar and the elevator front spar and between certain stabilizer stations for defects and damage, and corrective actions if necessary. This AD was prompted by a report of unusual noise coming from the left inboard elevator during a functional check of the ram air turbine system, and a determination that a bushing was not installed. We are issuing this AD to detect and correct non-installation of bushings. If the \n\n((Page 63856)) \n\nbushings are not present, the stiffness of the load path will be decreased, which will cause wear of adjacent parts and increased freeplay of the elevator surfaces. Freeplay that exceeds acceptable limits could result in divergent flutter for certain maneuvers, which could lead to loss of controllability of the airplane.
2004-23-03: The FAA is adopting a new airworthiness directive (AD) for Rolls-Royce plc (RR) RB211 Trent 700 series turbofan engines. This AD requires initial and repetitive borescope inspections of the high pressure-and-intermediate pressure (HP-IP) turbine internal and external oil vent tubes for coking and carbon buildup, and cleaning or replacing the vent tubes if necessary. This AD results from a report of a RB211 Trent 700 series engine experiencing a disk shaft separation, overspeed of the IP turbine rotor, and multiple blade release of IP turbine blades. Preliminary findings suggest these events resulted from an internal oil fire in the HP-IP turbine oil vent tubes due to coking and carbon buildup. This fire led to a second fire in the internal air cavity below the IP turbine disk drive shaft. We are issuing this AD to prevent internal oil fires due to coking and carbon buildup, that could cause uncontained engine failure and damage to the airplane.
2013-19-17: We are adopting a new airworthiness directive (AD) for all Rolls-Royce plc (RR) RB211-535E4-B-37 series turbofan engines. This AD requires removal of affected parts using a drawdown plan. This AD was prompted by recalculating the lives of certain rotating life limited parts (LLPs) operated to certain flight profiles. We are issuing this AD to prevent the failure of rotating LLPs, which could result in uncontained failure of the engine and damage to the airplane.
90-12-11 R1: 90-12-11 R1 BOEING: Amendment 39-6626 as revised by Amendment 39-6683. Docket No. 90-NM-86-AD. \n\n\tApplicability: Model 727, 737, and 757 series airplanes, equipped with escape slide release cables, certificated in any category. \n\n\tCompliance: Required as indicated, unless previously accomplished. \n\n\tTo ensure proper escape slide release from the escape slide compartment, accomplish the following: \n\n\tA.\tWithin 45 days after the effective date of this AD, unless previously inspected within the last three months, perform a visual inspection of each escape slide release cable, if installed. Replace frayed (one or more broken strands) or broken cables prior to further flight.\n \n\tB.\tRepeat the inspection for frayed or broken release cables required by paragraph A. of this AD, at intervals not to exceed 12 months. \n\n\tC.\tAn 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, Seattle Aircraft Certification Office, FAA, Northwest Mountain Region. \n\n\tNOTE: 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, Seattle Aircraft Certification Office. \n\n\tD.\tSpecial 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. \n\n\tThis AD revises AD 90-12-11, Amendment 39-6626. \n\n\tThe effective date for the requirements of this amendment remains June 25, 1990, as specified in Amendment 39-6626, AD 90-12-11. \n\tThis amendment (39-6683, AD 90-12-11 R1) is effective on July 31, 1990.
2004-22-14: The FAA is adopting a new airworthiness directive (AD) for certain Saab Model SAAB SF340A and SAAB 340B series airplanes. This AD requires an inspection of the elevator and aileron trim-tab fittings, and related investigative/corrective actions if necessary. This AD is prompted by reports of improperly installed rivets in the retainers that hold the elevator trim-tab bearings. We are issuing this AD to prevent the elevator and aileron trim-tab bearings from coming loose, which could result in excessive play in the elevator and aileron trim systems, and reduced controllability of the airplane.
2022-25-22: The FAA is adopting a new airworthiness directive (AD) for certain Airbus SAS Model A350-941 and -1041 airplanes. This AD was prompted by reports indicating that protective caps were found on engine fire extinguishing pipes in the engine core zone (Zone 2) after airplane delivery. This AD requires a one-time inspection of the engine fire extinguishing pipes for the presence of protective caps and removal of any protective caps found, 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.
77-15-14: 77-15-14 MORANE SAULNIER (SOCATA): Amendment 39-2985. Applies to Model MS 760 (Paris 1) and MS 760A (Paris 1A) airplanes, all serial numbers, certificated in all categories, that are equipped with ERAM wheels, P/N 3760-A. Compliance is required within the next 50 hours time in service after the effective date of this AD, unless already accomplished within the preceding 50 hours time in service, and thereafter, at intervals not to exceed 100 hours time in service from the last inspection. To detect cracks in the landing gear wheels and prevent possible wheel failure, accomplish the following: (a) Visually inspect, using a dye penetrant procedure, each ERAM wheel, P/N 3760-A, in accordance with paragraph 2 of ERAM Service Bulletin No. 32-01, dated December 1970, as revised October 1973, or an FAA-approved equivalent. (b) If, during an inspection required by this AD, a wheel is found to have more than one crack per stud or any crack exceeding 14 mm in length, replacethat wheel with a serviceable wheel of the same part number or an FAA-approved equivalent. This amendment becomes effective August 29, 1977.