Results
2020-18-06: The FAA is adopting a new airworthiness directive (AD) for 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, and -233 airplanes; and Model A321-111, -112, - 131, -211, -212, -213, -231, and -232 airplanes. This AD was prompted by a report that cracks were detected on the left-hand (LH) and right- hand (RH) sides of the first rivet hole of the frame (FR) 43 foot coupling during scheduled maintenance. This AD requires a rotating probe test of the fastener holes at FR43 on the LH and RH sides for any cracking, and on-condition actions if necessary, 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.
2009-04-10: The FAA is superseding an existing airworthiness directive (AD) for General Electric Company (GE) CF6-80A, CF6-80C2, and CF6-80E1 series turbofan engines. That AD required revisions to the Airworthiness Limitations Section (ALS) of the manufacturer's Instructions for Continued Airworthiness (ICA) to include required inspection of selected critical life-limited parts at each piece-part exposure. This AD requires revisions to the CF6-80A, CF6-80C2, and CF6- 80E1 series engines ALS sections of the manufacturer's manuals and an air carrier's approved continuous airworthiness maintenance program to incorporate additional inspection requirements, and to update certain Engine Manual Inspection Task and Sub Task Number references. This AD results from the need to require enhanced inspection of selected critical life-limited parts of CF6-80A, CF6-80C2, and CF6-80E1 series engines. We are issuing this AD to prevent critical life-limited rotating engine part failure, which could result in an uncontained engine failure and damage to the airplane.
83-21-05: 83-21-05 AIRBUS INDUSTRIE: Amendment 39-4749. Applies to all model A300 series airplanes listed in Airbus Industrie Service Bulletin A300-30-026, certificated in all categories. To prevent loss of all airspeed indications, accomplish the following within the next 1800 flight hours after the effective date of this AD, unless already accomplished: A. Modify the pitot probe heater in accordance with Airbus Industrie Service Bulletin A300-30-026, Revision 6, dated April 9, 1982. B. Alternate means of compliance which provide an equivalent level of safety may be used if approved by the Manager, Seattle Aircraft Certification Office, FAA, Northwest Mountain Region. C. 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 and/or modifications required by this AD. This amendment becomes effective November 28, 1983.
63-19-04: 63-19-04 SENSENICH: Amdt. 618 Part 507 Federal Register September 14, 1963. Applies to All Controllable and Constant Speed Propeller Models C-2FM, CS-2FM, C-3FR4, CS-3FR5, and CS-3FM4. (Aircraft on which these propeller models are installed include but are not necessarily confined to the Piper PA-12, -14, -16, -20, -22, Monocoupe 90AL-115, Stinson 108-2 and -3, Bellanca 14-13 and Goodyear GA-2B.) Compliance required as indicated. (a) On aircraft with Lycoming 0-235C or 0-290-D Series engines or Franklin 6A4- 165-B3 engines, inspect propellers with 90 hours or more propeller time in service on the effective date of this AD in accordance with (e) within 10 hours propeller time in service after the effective date of this AD, and thereafter each 100 hours propeller time in service from the last inspection. (b) On aircraft with Lycoming 0-325C or 0-290-D Series engines or Franklin 6A4- 165-B3 engines, inspect propellers with less than 90 hours propeller time in service on the effective date of this AD in accordance with (e) prior to the accumulation of 100 hours propeller time in service, and thereafter within each 100 hours propeller time in service from the last inspection. (c) On aircraft with engines not listed in (a) and (b), inspect propellers with 290 hours or more propeller time in service on the effective date of this AD in accordance with (e) within 10 hours propeller time in service after the effective date of this AD, and thereafter within each 300 hours propeller time in service from the last inspection. (d) On aircraft with engines not listed in (a) and (b), inspect propellers with less than 290 hours propeller time in service on the effective date of this AD in accordance with (e) prior to the accumulation of 300 hours propeller time in service, and thereafter within each 300 hours propeller time in service from the last inspection. (e) Remove the propeller blades from the hub and carefully inspect the wood blade shankand split retaining groove in the blade ferrule for cracks. Check and tighten the lag screws to 160 inch-pounds of torque. Magnetically inspect the ferrule and all ferrous metallic parts of the hub. Special care should be given to the inspection for cracks originating in the hub lock ring groove. Replace blades with broken lag screws, cracked wood shanks or ferrule before further flight. (Sensenich Service Bulletins Nos. 133, Revision 1, dated January 29, 1960, and R-9 dated December 7, 1962, cover this same subject.) This supersedes AD 50-47-01. This directive effective October 15, 1963.
2009-04-08: 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: The Luftfahrt-Bundesamt received a report from the Grob Company that a bolt in the airbrake control was found failed during a pre- flight inspection on a G 103C TWIN III ACRO. During an extensive investigation (metallurgical investigation) a double sided fatigue crack was found as root cause. As the bolt is insignificantly stressed by cyclic bending the crack was probably caused by mean stress supported by a bolt torque exceeding the limit. The actions specified by this airworthiness directive are intended to prevent further bolt cracking which can result in airbrake as well as elevator failure (elevator control is on the same pedestal) and reduced controllability of the power glider. We are issuing this AD to require actions to correct the unsafe condition on these products.
87-17-06: 87-17-06 AM-SAFE, INCORPORATED: Amendment 39-5710. Applies to Am-Safe, Inc., occupant restraint system assemblies, Part Numbers 501825-403, 501907-401, 501907-403, 501907-405, 502061-401, 502147-401, and 502147-403, which may be installed in large or small aircraft. (Seat belt portion approved under Technical Standard Order C22f.) Compliance required within 90 days after the effective date of this AD, unless previously accomplished. To eliminate restraint system connectors with the incorrect dimensions, which could allow inadvertent opening of occupant restraint system assemblies, accomplish the following: A. Inspect the affected restraint system assemblies in accordance with Am-Safe, Inc., Service Bulletin No. AS001, dated November 5, 1986, or later FAA-approved revisions, to determine the Lot Number of the connector. If the connector is not of Lot 04, no further action is required. If the connector is found to be of Lot 04, the connector must be removed and replacedwith a connector of a different lot number before further flight. B. Alternate means of compliance which provide an acceptable level of safety may be used when approved by the Manager, Western Aircraft Certification Office, FAA, Northwest Mountain Region. C. 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 information from the manufacturer may obtain copies upon request to Am-Safe, Incorporated, 240 North 48th Avenue, Phoenix, Arizona 85043. These documents may be examined at the FAA, Northwest Mountain Region, 17900 Pacific Highway South, Seattle, Washington, or at 15000 Aviation Boulevard, Hawthorne, California. This amendment becomes effective September 22, 1987.
2003-19-13: The FAA adopts a new airworthiness directive (AD) for all GROB-WERKE (GROB) Model G120A airplanes. This AD requires you to modify the flight control system operating levers. This AD is the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for Germany. We are issuing this AD to prevent failure of a ball bearing in the flight control system operating levers. Such failure could lead to reduced control or loss of control of the airplane.
89-18-11: 89-18-11 LOCKHEED AERONAUTICAL SYSTEMS COMPANY: Amendment 39-6303. (Docket No. 89-NM-33-AD) Applicability: Lockheed Model L-1011-385-1, L-1011-385-1-14, L-1011-385-1-15, and L-1011-385-3 series airplanes, as listed in Lockheed TriStar L-1011 Service Bulletin 093-49-062, dated September 19, 1988, certificated in any category. Compliance: Required as indicated, unless previously accomplished. To prevent a fire from arcing due to loose APU starter ground cables falling off the ground studs and onto the APU fuel shutoff valves, accomplish the following: A. Within 6 months after the effective date of this airworthiness directive (AD), inspect the APU starter ground stud/bracket for proper installation and proper ground stud torque, in accordance with the Accomplishment Instructions of Lockheed TriStar Service Bulletin 093-49- 062, dated September 19, 1988. Any discrepancies identified must be corrected prior to further flight, in accordance with the service bulletin. B. 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, Los Angeles Aircraft Certification Office, FAA, Northwest Mountain 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, Los Angeles Aircraft Certification Office, FAA, Northwest Mountain Region. C. Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate the airplane 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 Lockheed Aeronautical Systems Company, P.O. Box 551, Burbank, California 91520, Attention: Commercial Order Administration, Dept. 65-33, Unit 20, Plant A-1. These documents may be examined at the FAA, Northwest Mountain Region, Transport Airplane Directorate, 17900 Pacific Highway South, Seattle, Washington, or the Los Angeles Aircraft Certification Office, 3229 East Spring Street, Long Beach, California. This amendment (39-6303, AD 89-18-11) becomes effective on September 25, 1989.
2020-15-21: The FAA is adopting a new airworthiness directive (AD) for all Airbus SAS Model A330-200, -200 Freighter, and -300 series airplanes. This AD was prompted by a determination that certain inspection procedures specified an incorrect inspection area. This AD requires repetitive detailed inspections of a certain stringer location, and applicable corrective actions if necessary, as specified in European Union Aviation Safety Agency (EASA) AD 2019-0315, dated December 23, 2019, which is incorporated by reference. The FAA is issuing this AD to address the unsafe condition on these products.
2020-15-18: The FAA is adopting a new airworthiness directive (AD) for certain Leonardo S.p.A. (Leonardo) Model AB139, AW139, AW169, and AW189 helicopters. This AD was prompted by reports of uncommanded deployment of the emergency flotation system (EFS) due to improper accomplishment of the reset procedure of the shape memory alloy (SMA) inflation system actuation device. This AD requires removal of affected SMA inflation systems and installation of serviceable SMA inflation systems. The FAA is issuing this AD to address the unsafe condition on these products.