Results
2006-17-12: This amendment supersedes an existing airworthiness directive (AD), that is applicable to Rolls-Royce plc (RR) models RB211-535E4-37, RB211-535E4--37, RB211-535C-37, RB211-535E4-B-75, RB211-535E4-C, and RB211-22B-02 turbofan engines. That AD currently requires inspecting certain high pressure (HP) turbine discs, manufactured between 1989 and 1999, for cracks in the rim cooling air holes, and, if necessary, replacing the discs with serviceable parts. The manufacturer identified reaming-induced machining anomalies (RIMA) as the cause for the cracking. This amendment requires the same inspections, and reduces the compliance times for eddy current inspection (ECI) for the RR RB211- 22B-02 engines. This amendment results from the manufacturer reducing their recommended compliance times for inspections on RB211-22B-02 engines. We are issuing this AD to prevent possible disc failure, which could result in an uncontained engine failure and damage to the airplane.
2021-03-05: The FAA is adopting a new airworthiness directive (AD) for all Airbus SAS Model A318, A319, A320, and A321 series airplanes. This AD was prompted by a report that following accomplishment of tap tests on certain modified rudders, disbonding of the rudder was found close to the lightning protection plate. This AD requires inspections of the left- and right-hand rudder side shells for defects, and applicable corrective actions, 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.
2007-01-07: The FAA is superseding an existing airworthiness directive (AD), that applies to certain Bombardier Model CL-600-2B19 (Regional Jet Series 100 & 440) airplanes. That AD currently requires repetitive inspections for cracks, sealant damage, and corrosion of the main fittings of the main landing gear (MLG), and corrective actions if necessary. This new AD reduces the compliance times for inspecting certain low-utilization airplanes, and provides a terminating action for the repetitive inspections. This AD results from a report of a cracked main fitting of the MLG. We are issuing this AD to detect and correct fatigue cracking of the main fitting of the MLG and consequent failure of the main fitting, which could result in the collapse of the MLG.
2007-01-04: 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: 3 cases of cracking due to exfoliation corrosion on the unions of fuel pipes P/N 0 202 12 800 0, connecting the Fuel Control Unit to the start electrovalve, were reported. These cases of cracking, if they had not previously been detected, could have caused a loss of integrity of the union conveying fuel under pressure. A fuel leakage could then have happened and would have led to an uncommanded loss of power and to a fire hazard. This AD requires the fuel pipe to be inspected for cracking. This AD requires actions that are intended to address the unsafe condition described in the MCAI.
2020-26-11: The FAA is adopting a new airworthiness directive (AD) for certain Airbus SAS Model A300 F4-605R airplanes and Model A310-324 airplanes. This AD was prompted by a report that certain emergency locator transmitter (ELT) lithium batteries lack protection against current injection. This AD requires modification of the airplane circuit connecting the ELT battery, 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.
2006-26-13: The FAA is superseding two existing airworthiness directives (AD), which apply to certain Boeing airplanes as specified above. Those ADs currently require inspection of the attachment of the shoulder restraint harness to the mounting bracket on certain observer and attendant seats to determine if a C-clip is used in the attachment, and corrective action if necessary. This new AD removes certain airplanes from the applicability of one existing AD and adds other airplanes. We also determined that this new AD refers to identical revisions of certain service information cited by another existing AD. This AD results from the determination that some airplanes had been inadvertently included in or excluded from the applicability of one existing AD and that certain additional new airplanes are now subject to the identified unsafe condition. We are issuing this AD to prevent detachment of the shoulder restraint harness of the attendant or observer seat from its mounting bracket duringservice, which could result in injury to the occupant of the seat. \n\nDATES: This AD becomes effective February 12, 2007. \n\n\tThe Director of the Federal Register approved the incorporation by reference of certain publications listed in the AD as of February 12, 2007. \n\n\tOn October 21, 2003 (68 FR 57609, October 6, 2003), the Director of the Federal Register approved the incorporation by reference of certain other publications listed in the AD. \n\n\tOn January 4, 2002 (66 FR 59681, November 30, 2001), the Director of the Federal Register approved the incorporation by reference of certain other publications listed in the AD.
2020-26-02: The FAA is adopting a new airworthiness directive (AD) for certain Yabora Industria Aeronautica S.A. (type certificate previously held by Embraer S.A.) Model ERJ 190-400 airplanes. This AD was prompted by a report of an in-flight shutdown (IFSD) due in part to failure in the low-pressure compressor (LPC) rotor 1 during operation in high altitude at high thrust settings. This AD requires amending the airplane flight manual (AFM) to incorporate a new limitation and revise certain normal procedures, as specified in an Agencia Nacional de Aviacao Civil (ANAC) AD, which is incorporated by reference. The FAA is issuing this AD to address the unsafe condition on these products.
2006-26-05: The FAA is adopting a new airworthiness directive (AD) for all Fokker Model F27 Mark 100, 200, 300, 400, 500, 600, and 700 airplanes. This AD requires revising the Limitations section of the airplane flight manual regarding the use of continuous ignition, fuel filter heating, and resetting circuit breakers during flight in certain conditions such as icing. This AD results from reports of power loss on one or both engines in icing conditions. We are issuing this AD to advise the flightcrew that continuous ignition will not reduce the probability of power loss, and what action they must take to avoid this hazard. Loss of power in one or more engines during flight, if not prevented, could result in loss of control of the airplane.
2006-26-03: The FAA is adopting a new airworthiness directive (AD) for certain Alpha Aviation Model R2160 airplanes. This AD requires you to inspect the fuel pressure indication system for leakage at the end of the adapter in the fuel pressure indication system. This AD results from the possibility of fuel leakage at the end of the adapter in the fuel pressure indication system. We are issuing this AD to detect, correct, and prevent fuel leaks in the fuel pressure indicating system. This failure could allow fuel to leak near the exhaust manifold and lead to a fire.
2005-24-08: The FAA is adopting a new airworthiness directive (AD) for certain McCauley Propeller Systems propeller assemblies installed on BAE Systems (Operations) Limited Jetstream model 4100 series airplanes. This AD requires removing certain propeller hubs from service at new reduced life limits and eddy current inspections (ECIs) of the propeller hub. This AD results from three reports of cracked propeller hubs. We are issuing this AD to prevent cracked propeller hubs, which could cause failure of the propeller hub, blade separation, and loss of control of the airplane.
2006-23-02: The FAA adopts a new airworthiness directive (AD) for certain Raytheon Aircraft Company (RAC) (formerly Beech) Models C90A, B200, B200C, B300, and B300C airplanes. This AD requires you to inspect the flight controls for improper assembly or damage, and if any improperly assembled or damaged flight controls are found, take corrective action. This AD results from a report of inspections of several affected airplanes with improperly assembled or damaged flight controls. We are issuing this AD to detect and correct improperly assembled or damaged flight controls, which could result in an unsafe condition by reducing capabilities of the flight controls and lead to loss of control of the airplane.
2020-23-11: The FAA is adopting a new airworthiness directive (AD) for all Airbus SAS Model A300 series airplanes; and Airbus SAS Model A300 B4- 600, B4-600R, and F4-600R series airplanes, and Airbus SAS Model A300 C4-605R Variant F airplanes (collectively called Model A300-600 series airplanes). This AD was prompted by reports of cracking at a certain hole location on the left-hand (LH) side of a certain frame (FR). This AD requires repetitive inspections for discrepancies of certain areas in and around the fuselage, as specified in two European Union Aviation Safety Agency (EASA) ADs, which are incorporated by reference. The FAA is issuing this AD to address the unsafe condition on these products.
2006-25-16: The FAA is adopting a new airworthiness directive (AD) for all Bombardier Model CL-600-1A11 (CL-600), CL-600-2A12 (CL-601), and CL- 600-2B16 (CL-601-3A and CL-601-3R) airplanes. This AD requires implementing a corrosion prevention and control program (CPCP) either by accomplishing specific tasks or by revising the maintenance inspection program to include a CPCP. This AD results from the determination that, as airplanes age, they are more likely to exhibit indications of corrosion. We are issuing this AD to prevent structural failure of the airplane due to corrosion.
2020-23-06: The FAA is adopting a new airworthiness directive (AD) for Airbus Helicopters Model AS332C, AS332C1, AS332L, and AS332L1 helicopters. This AD requires inspecting the main rotor (M/R) hub assembly (hub) phonic wheel lock washer (lock washer) for correct installation and depending on the outcome, repairing or replacing the M/R hub. This AD was prompted by reported occurrences of M/R revolutions per minute (''NR'') sensor fluctuations. The actions of this AD are intended to address an unsafe condition on these products.
2020-23-13: The FAA is adopting a new airworthiness directive (AD) for all ATR--GIE Avions de Transport Regional Airplanes Model ATR42-200, -300, and -320 airplanes. This AD was prompted by false activation of the stall warning system due to wiring damage on the wire bundle between an angle of attack (AOA) probe and the crew alerting computer. This AD requires a one-time inspection for discrepancies of the wire bundles between the left- and right-hand AOA probes and the crew alerting computer, and, depending on findings, applicable corrective actions, 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.
2020-23-10:
2006-25-15: The FAA is adopting a new airworthiness directive (AD) for Sicma Aero Seat third occupant seat assemblies, 133 series. This AD requires visually inspecting the installation of the two headrest bushings and installing Mecanindus pins to secure the bushings. This AD results from Sicma's determination that missing or incorrectly secured bushings could loosen and cause disengagement of the headrest from the seat during a high-energy stop of the airplane, possibly injuring the seat occupant. We are issuing this AD to prevent disengagement of the headrest from the seat during a high-energy stop of the airplane that could injure the seat occupant.
2020-22-16: The FAA is superseding Airworthiness Directive (AD) 2017-25- 04, which applied to certain Airbus SAS Model A318 series airplanes; Model A319-111, -112, -113, -114, -115, -131, -132, and -133 airplanes; Model A320-211, -212, -214, -231, -232, and -233 airplanes; and Model A321-111, -112, -131, -211, -212, -213, -231, and -232 airplanes. The FAA is also superseding AD 2019-03-17, which applies to certain Airbus SAS Model A318 series airplanes; Model A319-111, -112, -113, -114, - 115, -131, -132, and -133 airplanes; Model A320-211, -212, -214, -216, -231, -232, -233, -251N, and -271N airplanes; and Model A321 series airplanes. AD 2019-03-17 required revising the existing maintenance or inspection program, as applicable, to incorporate new maintenance requirements and airworthiness limitations. This AD retains the requirements of AD 2019-03-17 and also requires new or more restrictive airworthiness limitations, as specified in a European Union Aviation Safety Agency (EASA) AD, which is incorporated by reference. This AD was prompted by a determination that new or more restrictive airworthiness limitations are necessary. The FAA is issuing this AD to address the unsafe condition on these products.
2006-25-09: The FAA is adopting a new airworthiness directive (AD) for certain McDonnell Douglas Model MD-11F airplanes. This AD requires a general visual inspection for installation of conduit and chafing damage on the auxiliary power unit (APU) power feeder wires and the upper surface of the auxiliary fuel tank and repair if necessary. This AD results from fuel system reviews conducted by the manufacturer. We are issuing this AD to detect and correct unprotected APU power feeder wires that come into close proximity to the upper surface of the auxiliary "piggy back'' fuel tank, which could result in a potential ignition source, and in combination with flammable fuel vapors, could cause a fuel tank explosion and consequent loss of the airplane.
2020-22-01: The FAA is adopting a new airworthiness directive (AD) for all Airbus Helicopters Model AS332C, AS332C1, AS332L, and AS332L1 helicopters. This AD requires inspecting the affected parts and associated frame bores for discrepancies, applicable corrective actions, and reporting certain information if necessary. This AD was prompted by reports of corrosion on attachment screws and fittings fastening the main gearbox (MGB) suspension bars to the fuselage. The actions of this AD are intended to address an unsafe condition on these products.
2006-25-08: The FAA is adopting a new Airworthiness Directive (AD) for all Columbia Aircraft Manufacturing (previously The Lancair Company) Models LC41-550FG and LC42-550FG airplanes equipped with Kelly Aerospace Thermal Systems Supplemental Type Certificate (STC) SA02260CH, Thermawing Deice System (also known as E-Vade). This AD requires you to deactivate the deice system and install a placard in clear view of the pilot. This AD results from problems with the installation of the Kelly Aerospace Thermal Systems Thermawing Deice System following STC SA02260CH. We are issuing this AD to prevent a short circuit condition at the deice heater connector, which could result in damage to the wings and horizontal stabilizer. This damage could lead to reduced structural integrity of the airplane.
2020-21-10: The FAA is superseding Airworthiness Directive (AD) 2017-19- 24, which applies to Model A319-111, -112, -113, -114, -115, -131, - 132, and -133 airplanes; Model A320-211, -212, -214, -231, -232, and - 233 airplanes; and Model A321-111, -112, -131, -211, -212, -213, -231, and -232 airplanes. The FAA is also superseding AD 2018-16-04, which applies to Airbus SAS Model A320-216, -251N, and -271N airplanes; and Model A321-251N, -253N, and -271N airplanes; as well as the models in AD 2017-19-24. Those ADs required revising the existing maintenance or inspection program, as applicable, to incorporate new or more \n\n((Page 65191)) \n\nrestrictive maintenance requirements and airworthiness limitations. Since AD 2018-16-04 was issued, the FAA has determined that new or more restrictive airworthiness limitations are necessary. This AD requires revising the existing maintenance or inspection program, as applicable, to incorporate new or more restrictive airworthiness limitations; as specified in a European Union Aviation Safety Agency (EASA) AD, which is incorporated by reference. This AD was prompted by a determination that new or more restrictive airworthiness limitations are necessary. The FAA is issuing this AD to address the unsafe condition on these products.
80-08-07: 80-08-07 ROCKWELL INTERNATIONAL: Amendment 39-3750. Model NA265-40 (all), -60 (all) and -70 S/N 370-2 through -6 and 370-8 and -9 series airplanes except those modified by Supplemental Type Certificate SA687NW, certificated in all categories. Compliance required as indicated, unless already accomplished. To prevent adverse flight characteristics resulting from elevator delamination accomplish the following: (a) On aircraft with honeycomb elevator trailing edge surfaces in service for one calendar year or more, or with 1,000 hours' time in service, whichever occurs earlier; (1) Within 100 hours' additional time in service, or within 30 days from the effective date of this AD, whichever occurs earlier, inspect left and right elevator trailing edges for delamination as specified in paragraphs 1(a) and 1(b) of "Modification Instructions" of Rockwell International Service Bulletin No. 48 dated January 9, 1980, and; (2) At intervals not to exceed 500 hours' timein service or 6 months from the last such inspection, whichever occurs sooner, repeat the inspection of paragraph (a)(1) of this AD. (b) Repair delaminated elevator trailing edges prior to further flight per paragraph 3 of "Modification Instructions" of Rockwell International Service Bulletin No. 48 dated January 9, 1980 and prior to the accumulation of 1,000 hours' additional time in service on new trailing edges, inspect per paragraph (a)(1) of this AD and reinspect at repetitive intervals specified per paragraph (a)(2) of this AD. (c) Installation of non-honeycomb trailing edges constitutes terminating action for the inspections required by this AD. (d) Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes to a base for the accomplishment of inspections required by this AD. (e) Alternative inspections, modifications or other actions which provide an equivalent level of safety may be used when approved by the Chief, Aircraft Engineering Division, FAA Western Region. This amendment becomes effective April 21, 1980.
2020-21-11: The FAA is superseding Airworthiness Directive (AD) 2015-22- 08, which applied to all Airbus SAS Model A318 series airplanes; Model A319-111, -112, -113, -114, -115, -131, -132, and -133 airplanes; and Model A320-211, -212, -214, -231, -232, and -233 airplanes. The FAA is also superseding AD 2018-17-19, which applied to certain Airbus SAS Model A318 series airplanes; Model A319-111, -112, -113, -114, -115, - 131, -132, and -133 airplanes; Model A320-211, -212, -214, -216, -231, -232, -233, -251N, and -271N airplanes; and Model A321-111, -112, -131, -211, -212, -213, -231, -232, -251N, -253N, and -271N airplanes. The FAA is also superseding AD 2019-19-15, which applied to certain Airbus SAS Model A318 series airplanes; Model A319-111, -112, -113, -114, - 115, -131, -132, and -133 airplanes; Model A320-211, -212, -214, -216, -231, -232, -233, -251N, and -271N airplanes; and Model A321 series airplanes. AD 2019-19-15 required revising the existing maintenance or inspection program, as applicable, to incorporate new or more restrictive airworthiness limitations. This AD requires revising the existing maintenance or inspection program, as applicable, to incorporate new or more restrictive airworthiness limitations, as specified in a European Union Aviation Safety Agency (EASA) AD, which is incorporated by reference. This AD was prompted by a determination that new or more restrictive airworthiness limitations are necessary. The FAA is issuing this AD to address the unsafe condition on these products.
65-08-02: 65-08-02 SIKORSKY: Amdt. 39-54 Part 39 Federal Register April 9, 1965. Applies to Models S-55, S-62, and S-61 Series Helicopters. Compliance required as indicated. Pitting in main rotor blade spars has resulted in fatigue cracks. To detect possible pitting and cracking, accomplish the following: (a) Within 10 hours' time in service after the effective date of this AD and at intervals thereafter within 10 hours' time in service from the last inspection, until (b) has been accomplished, conduct a visual inspection for cracks of the spars of S14-10-2100 Series main rotor blades, Serial Numbers 55MH15340 through 55MH19858, in accordance with the inspection procedures specified in Sikorsky Service Bulletin 55B10-4 or 62B10-3. Replace all main rotor blades found with cracks in the spar before further flight. (b) Unless already accomplished, within 25 hours' time in service after the effective date of this AD accomplish the following: (1) On S-55 and S-62 helicopters, conduct an X-ray inspection of the spar of S14-10-2100 Series and S14-10-2201 Series main rotor blades, Serial Numbers 55MH15340 through 55MH19858, for pitting in accordance with the inspection procedures specified in Sikorsky Service Bulletin 55B10-4 or 62B10-3. (2) On S-61 helicopters, conduct an X-ray inspection of the spar of S6115- 20501 Series main rotor blades, Serial Numbers 61M101 through 61M1429, for pitting in accordance with the inspection procedures specified in Sikorsky Service Bulletin 61B15-3. (3) Replace all blades with pitting in the spar, before further flight. This directive effective April 9, 1965.