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2010-23-14: We are adopting a new 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: Several cases of corrosion in lower structural members of the passenger door have been reported. It was subsequently determined that a drainage ramp (constructed from resin) had deteriorated with time and was retaining moisture. * * * Corrosion left undetected could eventually affect the structural integrity of the door and surrounding structure. We are issuing this AD to require actions to correct the unsafe condition on these products.
79-10-02: 79-10-02 SHORT BROTHERS LIMITED: Amendment 39-3457. Applies to Model SD3-30 airplanes, S/N SH3002 through SH3019, certificated in all categories, which have low blade angle pitch mechanism support bracket, P/N SD3-49-0784, or P/N SD3-49-0784xB installed. Compliance is required as indicated, unless already accomplished. To prevent propeller blade angle from increasing beyond the flight setting, accomplish the following: (a) Within the next 30 hours time in service after the effective date of this AD, remove each low blade angle pitch mechanism support bracket, P/N SD3-49-0784 or P/N SD3- 49-0784xB, and inspect it for cracks using the dye penetrant procedure or an equivalent FAA- approved procedure, in accordance with paragraph 2.A., "Accomplishment Instructions", of Short Brothers Service Bulletin No. SD3-61-A05, dated August 2, 1978, or an FAA-approved equivalent. (b) Within the next 300 hours time in service after bracket reinstallation in accordance with paragraph (c)(1) of this AD or bracket replacement in accordance with paragraph (d)(1) of this AD, and thereafter at intervals not to exceed 300 hours from the last inspection, visually inspect support bracket, P/N SD3-49-0784 or P/N SD3-49-0784xB, for cracks in accordance with paragraph 2.A.10 of the Short Brothers Service Bulletin No. SD3-61- A05 dated August 2, 1978, or an FAA-approved equivalent. (c) If, during any inspection required by paragraph (a) of this AD, no cracks are found (1) Reinstall support bracket, P/N SD3-49-0784 or P/N SD3-49-0784xB in accordance with Short Brothers Service Bulletin No. SD3-61-A05 dated August 2, 1978, or an FAA-approved equivalent and accomplish the repetitive inspections required by paragraph (b) of this AD; or (2) Install a modified support bracket, P/N SD3-49-0902 or P/N SD3-49- 0902xA in accordance with Short Brothers Service Bulletin No. SD3-61-05 dated September 27, 1978, or an equivalent approved by the Chief, Aircraft Certification Staff, FAA, Europe, Africa and Middle East Region. (d) If, during any inspection required by this AD, any cracks are found, remove the cracked bracket from service and - (1) Replace the cracked support bracket with a crack-free, new or used support bracket of the same part number, and accomplish the repetitive inspections required by paragraph (b) of this AD. (Before installation of a used support bracket, inspect it in accordance with the method specified in paragraph (a) of this AD to ensure that it is crack-free); or (2) Replace the cracked bracket with a modified support bracket, P/N SD3- 49-0902 or P/N SD3-49-0902xA, in accordance with Short Brothers Service Bulletin No. SD3- 61-05 dated September 27, 1978, or an equivalent approved by the Chief, Aircraft Certification Staff, FAA, Europe, Africa and Middle East Region. (e) Upon installation of a modified support bracket, P/N SD3-49-0902 or P/N SD3- 49-0902xA, in accordance with Short Brothers Service Bulletin No. SD3-61-05 dated September 27, 1978, or an equivalent approved by the Chief, Aircraft Certification Staff, FAA, Europe, Africa, and Middle East Region, inspections required by paragraph (b) of this AD may be discontinued. (f) Upon request of an operator, the Chief, Aircraft Certification Staff, FAA, Europe, Africa and Middle East Region, c/o American Embassy, Brussels, Belgium, may adjust the repetitive inspection interval specified in paragraph (b) of this AD or approve modifications equivalent to that specified in paragraphs (c), (d), and (e) of this AD provided that such requests are made through an FAA maintenance inspector and the request contains substantiating data to justify the request for that operator. This amendment becomes effective May 14, 1979.
94-21-03: This amendment adopts a new airworthiness directive (AD), applicable to certain Jetstream Model 4101 airplanes, that requires installation of a placard near the decouple control handle for the elevator control system to ensure that the pilots are made aware that maintenance action is required to reset the disconnect unit once the decouple control handle has been pulled. This amendment is prompted by a report that, if the decouple control handle for the elevator control system is pulled, the lock linkage will remain unlocked until it is reset during maintenance. The actions specified by this AD are intended to prevent reduced controllability of the airplane due to loss of the mechanical linkage between the pilots' elevator controls, and each pilot having control authority over only one-half of the elevator control system.
2016-21-06: We are superseding Airworthiness Directive (AD) 2015-02-23, for certain Bombardier, Inc. Model CL-600-1A11 (CL-600), CL-600-2A12 (CL-601), and CL-600-2B16 (CL-601-3A and CL-601-3R Variants) airplanes. AD 2015-02-23 required repetitive inspections for fractured or incorrectly oriented fasteners on the inboard flap hinge-box forward fittings on both wings, and replacement of all fasteners if necessary. This new AD also requires replacement of the fasteners, which terminates the requirements of this AD. This AD was prompted by reports of incorrectly oriented fasteners. We are issuing this AD to prevent incorrectly oriented or fractured fasteners, which could result in detachment of the flap hinge-box and the flap surface, and consequent reduced controllability of the airplane.
2001-15-05: This amendment adopts a new airworthiness directive (AD), applicable to all Aerospatiale Model ATR42-200, -300, -320, -500, and ATR72 series airplanes, that requires a revision of the Airplane Flight Manual to add instructions that prohibit the flightcrew from selecting the reverse position on the engines in the event of propeller thrust dissymmetry. The actions specified by this AD are intended to ensure that the flightcrew is advised of the hazard associated with selecting reverse thrust during propeller thrust dissymmetry, which could result in reduced controllability of the airplane during landing. This action is intended to address the identified unsafe condition.
2022-26-01: The FAA is adopting a new airworthiness directive (AD) for certain GE Aviation Czech s.r.o. (GEAC) M601D-11, M601E-11, M601E-11A, M601E-11AS, M601E-11S, M601F, H75-100, H75-200, H80, H80-100, H80-200, H85-100, and H85-200 model turboprop engines. This AD was prompted by reports of cracks in dilution tube weld areas of the combustion chamber outer liner. This AD requires initial and repetitive borescope inspections (BSIs) of the dilution tube weld areas of the combustion chamber outer liner and, depending on the results of the inspections, replacement of the combustion chamber outer liner with a part eligible for installation. The FAA is issuing this AD to address the unsafe condition on these products.
2001-13-26: This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model DC-10-10, -15, -30, and -40 series airplanes, and Model MD-10-10F and -30F series airplanes, that requires a general visual inspection to detect chafing or damage of the feeder cables of the external ground power in the forward cargo compartment between certain fuselage stations; and repair, if necessary. This amendment also requires installation of spiral wrap on the feeder cables of the external ground power. This action is necessary to prevent chafing of the feeder cables during removal of the sump panels of the cargo floor, which could result in electrical arcing and damage to adjacent structure, and consequent smoke and/or fire in the forward cargo compartment. This action is intended to address the identified unsafe condition.
2001-15-06: This amendment supersedes an existing airworthiness directive (AD), applicable to certain Airbus Model A319, A320, and A321 series airplanes, that currently requires modification of the forward and aft evacuation slide systems by replacing the Velcro restraints for the support logs with frangible link restraints. This amendment reduces the time to accomplish the modification from 3 years to 9 months. 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 prevent the ingestion of sill support-log material into the aspirator of the evacuation slide, which could result in failure of the slide to inflate. The incorporation by reference of Airbus Service bulletin A320-25-1215, dated April 29, 1999, as listed in the regulations was approved previously by the Director of the Federal Register as of March 30, 2000 (65 FR 9212, February 24, 2000).
2016-22-15: We are superseding Airworthiness Directive (AD) 2012-24-06 for certain Saab AB, Saab Aeronautics Model 340A (SAAB/SF340A) and SAAB 340B airplanes. AD 2012-24-06 required replacing the stall warning computer (SWC) with a new SWC that provides an artificial stall warning in icing conditions, and modifying the airplane for the replacement of the SWC. This new AD adds airplanes to the applicability, and adds requirements to replace the existing SWCs with new, improved SWCs, and to modify the airplane for the new replacement of the SWC. This new AD also reduces the compliance time for replacing the SWCs. This AD was prompted by a determination that airplanes with certain modifications were excluded from the applicability in AD 2012-24-06, and are affected by the identified unsafe condition; and that the SWC required by AD 2012-24-06 contained erroneous logic. We are issuing this AD to prevent natural stall events during operation in icing conditions, which could result in loss of control of the airplane.
2016-22-12: We are adopting a new airworthiness directive (AD) for all Pilatus Aircraft Ltd. Models PC-6, PC-6-H1, PC-6-H2, PC-6/350, PC-6/ 350-H1, PC-6/350-H2, PC-6/A, PC-6/A-H1, PC-6/A-H2, PC-6/B-H2, PC-6/B1- H2, PC-6/B2-H2, PC-6/B2-H4, PC-6/C-H2, and PC-6/C1-H2 airplanes. This AD results from mandatory continuing airworthiness information (MCAI) issued by the aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as wear and cracks on the stabilizer-trim attachment and structural components. We are issuing this AD to require actions to address the unsafe condition on these products. [[Page 76846]]