Results
2022-19-03: The FAA is superseding Airworthiness Directive (AD) 2016-26- 08, which applied to all Pilatus Aircraft Ltd. Model PC-12, PC-12/45, PC-12/47, and PC-12/47E airplanes. AD 2016-26-08 required incorporating revisions into the airworthiness limitations section (ALS) of the maintenance program and inspecting the main landing gear (MLG) attachment bolts for cracks and corrosion. Since the FAA issued AD 2016-26-08, the European Union Aviation Safety Agency (EASA) superseded its mandatory continuing airworthiness information (MCAI) to add a new life limit for certain MLG actuator bottom attachment bolts and then superseded it again to add new life limits for the rudder bellcrank. This AD requires incorporating new revisions to the ALS of the existing airplane maintenance manual (AMM) or Instructions for Continued Airworthiness (ICA) to establish a 5-year life limit for certain MLG actuator bottom attachment bolts and new life limits for the rudder bellcrank. The FAA is issuing this AD to address the unsafe condition on these products.
2007-19-09: We are superseding an existing airworthiness directive (AD) by adopting a new AD for the products listed above. This AD results from mandatory continuing airworthiness information (MCAI) provided by the aviation authority of France to identify and correct an unsafe condition on Turbomeca Arriel 2B1 turboshaft engines. The MCAI states the following: This AD is prompted by several reported cases of rupture of the constant delta pressure valve diaphragm on Arriel 2B1 engines, due to the wear of the delta P diaphragm fabric. Rupture can result in the loss of the automatic control mode of the helicopter, accompanied with a deterioration of the behavior of the auxiliary back-up mode (emergency mode). On a single-engine helicopter, the result may be an emergency landing or, at worst, an accident. This AD supersedes European Aviation Safety Agency (EASA) AD 2007-0006 which required the removal from service of all the delta pressure valve diaphragms logging more than 2,000 hours-since-new. Since issuance of EASA AD 2007-0006, no further case of rupture of the constant delta pressure valve diaphragm has been reported on Arriel 2 engines. However, about 40 additional diaphragms returning from service have been inspected by Turbomeca, and some signs of wear have been detected on diaphragms having logged less than 2,000 hours. Based on the inspection results, it has been decided to decrease this limit from 2,000 hours to 1,500 hours in order to further reduce the probability of delta P diaphragm rupture. We are issuing this AD to prevent forced autorotation landing, or an accident.
2007-17-03: We are adopting a new airworthiness directive (AD) for the products listed above. This AD results from mandatory continuing airworthiness information (MCAI) issued by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as: To prevent damage to the rear spar due to working and failing rivets between the rear spar and the inboard rib * * * We are issuing this AD to require actions to correct the unsafe condition on these products.
2022-18-09: The FAA is superseding Airworthiness Directive (AD) 2019-26- 11, which applied to certain Airbus SAS Model A319-112, -115, and -132; A320-214, -216, -232, -233, -251N, and -271N; and A321-211, -231, -232, -251N, and -253N airplanes; and AD 2021-23-15, which applied to certain Airbus SAS Model A319-111, -112, -113, -114, -115, -131, -132, and - 133; A320-211, -212, -214, -216, -231, -232, and -233; and A321-111, - 112, -131, -211, -212, -213, -231, and -232 airplanes. AD 2019-26-11 required replacing the affected bumpers with serviceable bumpers. AD 2021-23-15 required modifying the waste compartment door of each affected galley. This AD was prompted by reports that the waste compartment door opened prematurely during a test, that container/ galley end stop bumpers were damaged in service, and that additional airplanes are subject to the unsafe conditions described in those ADs. This AD continues to require the actions in AD 2019-26-11 and AD 2021- 23-15, and adds airplanes to the applicability; 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.
2007-18-10: The FAA is adopting a new airworthiness directive (AD) for General Electric Company (GE) CF6-80E1 series turbofan engines with certain part number (P/N) compressor rear frames (CRFs) installed. This AD requires revisions to the Airworthiness Limitations Section (ALS) of the manufacturer's Instructions for Continued Airworthiness (ICA) and air carrier's approved Continued Airworthiness Maintenance Programs (CAMP) to include initial and repetitive eddy current inspections (ECIs) or fluorescent penetrant inspections (FPIs) of the affected CRFs. This AD results from the need to require enhanced inspections of the CF6-80E1 series engine CRFs for cracks. We are issuing this AD to prevent rupture of the CRF, which could result in an under-cowl engine fire.
2022-17-02: The FAA is adopting a new airworthiness directive (AD) for certain CFM International, S.A. (CFM) LEAP-1B model turbofan engines. This AD was prompted by multiple commanded in-flight shutdowns (IFSDs) due to inner radial drive shaft (RDS) failure. This AD requires initial and repetitive inspections of the transfer gearbox (TGB) scavenge screens and, depending on the results of the inspections, replacement or rework of the affected inner RDS. As a mandatory terminating action to the initial and repetitive inspections of the TGB scavenge screens, this AD requires replacement or rework of the affected inner RDS. This AD also prohibits the installation of an engine with an affected inner RDS onto an airplane that already has one engine with an affected inner RDS installed. The FAA is issuing this AD to address the unsafe condition on these products.
2007-18-06: The FAA is superseding an existing airworthiness directive (AD) for Pratt & Whitney (PW) JT9D-7R4 turbofan engines. That AD currently requires inspection of the blade root thickness of 1st stage fan blades identified by part number (P/N) and serial number (SN) in the AD. This AD requires the same actions but corrects 12 P/Ns, adds 10 part SNs, and adds the definition of next fan blade exposure to the compliance section. This AD results from the discovery of inaccurate part quantity, part numbers, and serial numbers used in AD 2005-26-09. We are issuing this AD to prevent 1st stage fan blade fracture and uncontained engine failure, resulting in possible damage to the airplane.
2007-18-04: We are superseding an existing airworthiness directive (AD) for the products listed above. This AD results from mandatory continuing airworthiness information (MCAI) originated by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as: Two A330 operators have reported uncontained APU (auxiliary power unit) generator failures on ground. Preliminary investigations confirmed an uncontained APU Generator failure with subsequent aircraft structural damages to the APU compartment and, in one case, to the stabiliser compartment. Loose APU generator parts can lead to damage to the APU fire wall which might reduce its fire extinguishing capability, possibly leading to a temporary uncontrolled fire which constitutes an unsafe condition. * * * * * This AD requires actions that are intended to address the unsafe condition described in the MCAI. DATES: This AD becomes effective September 14, 2007. The Director of the Federal Register approved the incorporation by reference of certain publications listed in the AD as of September 14, 2007. On June 26, 2007 (72 FR 31973, June 11, 2007), the Director of the Federal Register approved the incorporation by reference of certain other publications. We must receive comments on this AD by October 1, 2007.
2022-17-08: The FAA is superseding Airworthiness Directive (AD) 2020-22- 03, which applied to all Airbus SAS Model A330-200, -200 Freighter, and -300 series airplanes. AD 2020-22-03 required revising the existing airplane flight manual (AFM) to incorporate procedures to be applied if an engine bleed over-temperature occurs when the associated engine bleed valve is jammed open, and provided for the optional embodiment of updated flight warning computer (FWC) software, which terminated the AFM revision. This AD was prompted by the development of new maintenance actions and software related to over-temperature failure conditions. This AD continues to require the actions specified in AD 2020-22-03, requires accomplishing the new maintenance tasks and corrective actions, and mandates embodiment of the updated FWC software for certain airplanes, as specified in a European Union Aviation Safety Agency (EASA) AD, which is incorporated by reference. This AD also prohibits the installation of affected FWC software. The FAA is issuing this AD to address the unsafe condition on these products.
2007-17-13: The FAA is adopting a new airworthiness directive (AD) for certain Boeing Model 747-100, -200B, -200C, and -200F series airplanes. This AD requires performing repetitive inspections for cracks in the fuselage skin at the cutout of the bulk cargo door light, and corrective actions if necessary. This AD also provides terminating action for airplanes with a certain type of damage. This AD results from a report of a 2-inch crack through the fuselage skin and internal bonded doubler at the cutout of the bulk cargo door light. We are issuing this AD to detect and correct cracks in the fuselage skin at the cutout of the bulk cargo door light, which could result in reduced structural integrity of the fuselage at the bulk cargo door and consequent rapid decompression of the fuselage.