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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]]
2001-13-27: This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model DC-9-10 and -30 series airplanes. This action requires replacement of a certain circuit breaker in the navigation transfer circuit located on the overhead circuit breaker panel with a certain new circuit breaker; and installation of a new nameplate. This action is necessary to prevent damage to wires or equipment and consequent smoke/fire in the cockpit from heat generated in the wires during an overload condition. This action is intended to address the identified unsafe condition.
89-26-07: 89-26-07 BOEING OF CANADA, LTD., DE HAVILLAND DIVISION: Amendment 39-6422. Docket No. 89-NM-161-AD. Applicability: All Model DHC-7 series airplanes, certificated in any category. Compliance: Required as indicated, unless previously accomplished. To prevent reduced structural capability of the fuselage and subsequent decompression of the airplane, accomplish the following: A. Within 60 days after the effective date of this AD, perform the following inspections and repair, in accordance with de Havilland Service Bulletin 7-53-33, Revision A, dated June 9, 1989: 1. Perform a low frequency ultrasonic inspection for disbonding of the fuselage belly skin doublers, between fuselage stations X248.00 and X535.25 below stringer 20 left and right, in accordance with Inspection Part A of the service bulletin. 2. Visually inspect for looseness or working of the rivets in the vertical skin joints, at fuselage stations X535.25 and X576.25 below stringer 20, leftand right. 3. Visually inspect for looseness or working of the rivets in the fuselage skin joints at station X630.00 around the complete periphery of the fuselage, above and below the passenger and emergency exit doors. 4. Visually inspect for looseness or working of the rivets in the skin longitudinal joint between fuselage stations X424.00 to X484.00 along stringer 20, left and right. Pay particular attention to the lower line of rivets. 5. Repair all loose rivets prior to further flight, in a manner approved by the Manager, New York Aircraft Certification Office, ANE-170, FAA, New England Region. 6. Repair all disbonding prior to further flight, in accordance with the service bulletin. B. Within 90 days after the effective date of this AD: 1. Perform a low frequency ultrasonic inspection for disbonding of the fuselage left and right sidewall skin doublers, between fuselage stations X248.00 and X596.75, between stringer 20 and 10, in accordance withde Havilland Service Bulletin 7-53-33, Revision A, dated June 9, 1989. 2. Repair any disbonding prior to further flight, in accordance with the service bulletin. C. Within 150 days after the effective date of this AD: 1. Perform a low frequency ultrasonic inspection for disbonding of the fuselage roof skin doublers between fuselage stations X248.00 and X630.00, between stringer 10, left and right, in accordance with de Havilland Service Bulletin 7-53-33, Revision A, dated June 9, 1989. 2. Repair any disbonding prior to further flight, in accordance with the service bulletin. D. Within 3 days after accomplishing each of the inspections required by paragraphs A., B., and C., above, report all findings, positive or negative, to the Director, Airworthiness Branch, Transport Canada, Ottawa, Canada; to the manufacturer, Boeing of Canada, Ltd., de Havilland Division, in accordance with de Havilland Service Bulletin 7-53-33, Revision A, dated June 9, 1989; and to the FAA, Manager, New York Aircraft Certification Office, ANE-170, New England Region. E. 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, New York Aircraft Certification Office, ANE-170, FAA, New England 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, New York Aircraft Certification Office, ANE-170. F. 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 persons affected by this directive who have not already received the appropriate service documents from the manufacturer may obtain copies upon request to Boeing of Canada, Ltd., de Havilland Division, Garratt Boulevard, Downsview, Ontario M3K 1Y5, Canada. These documents may beexamined at the FAA, Northwest Mountain Region, Transport Airplane Directorate, 17900 Pacific Highway South, Seattle, Washington, or New York Aircraft Certification Office, FAA, New England Region, 181 South Franklin Avenue, Valley Stream, New York. This amendment (39-6422, AD 89-26-07) becomes effective on January 14, 1990.
2016-22-18: We are adopting a new airworthiness directive (AD) for all The Boeing Company Model MD-90-30 airplanes. This AD requires a detailed inspection of the forward and aft surfaces on the left and right sides at the cant station 1520 bulkhead for any crack in the upper cap and (cap) doubler, webs and doublers, stiffeners, and the lower tee cap between longerons 3 through 11, and repairs if necessary. This AD was prompted by a report of cracking in various structures in the fuselage cant station 1520 bulkhead. We are issuing this AD to detect and correct cracking in the bulkhead, which could result in reduced structural integrity of the airplane.