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2006-17-51: This document publishes in the Federal Register an amendment adopting Airworthiness Directive (AD) 2006-17-51, sent previously to all known U.S. owners and operators of Agusta S.p.A. (Agusta) Model AB139 helicopters by individual letters. This AD requires, before further flight and at specified intervals, certain visual inspections of each tailpipe assembly for a crack and for overheating. If you find areas of overheating, this AD also requires, before further flight, certain inspections for damage to the surrounding structure, outside of the cowling, and inside of each tailpipe assembly in certain areas. This AD also requires, before further flight, if you find a crack, replacing the tailpipe assembly with an airworthy tailpipe assembly. This AD is prompted by several reports of tailpipe assembly cracks. The actions specified by this AD are intended to prevent a fire due to the structure in the cowling area overheating, separation of a part of a tailpipe assembly, and subsequent loss of control of the helicopter.
2018-17-19: We are adopting a new airworthiness directive (AD) for certain Airbus SAS Model A318, A319, and A320 series airplanes, and Model A321- 111, -112, -131, -211, -212, -213, -231, -232, -251N, -253N, and -271N airplanes. This AD was prompted by a determination that more restrictive maintenance requirements and airworthiness limitations are necessary. This AD requires revising the maintenance or inspection program, as applicable, to incorporate the specified maintenance requirements and airworthiness limitations. We are issuing this AD to address the unsafe condition on these products. \n\n((Page 44461))
2018-17-18: We are superseding Airworthiness Directive (AD) 2015-02-17, which applied to all Airbus Model A330-200, A330-200 Freighter, and A330-300 series airplanes. AD 2015-02-17 required revising the electrical emergency configuration procedure in the Emergency Procedures section of the airplane flight manual (AFM) to include procedures for deploying the ram air turbine manually to provide sufficient hydraulic power and avoid constant speed motor/generator (CSM/G) shedding. Since we issued AD 2015-02-17, we have determined that replacement or modification of the two flight warning computers (FWCs) is necessary to address the identified unsafe condition. This AD requires the replacement or modifications of the two FWCs. This AD also removes airplanes from the applicability. We are issuing this AD to address the unsafe condition on these products.
2020-24-12: The FAA is adopting a new airworthiness directive (AD) for certain Airbus SAS Model A350-941 airplanes. This AD was prompted by reports that certain central wing box (CWB) fasteners had rotated inside the fastener holes due to insufficient friction for the application. This AD requires replacement of the affected fasteners, 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.
87-04-10: 87-04-10 CASA: Amendment 39-5538. Applies to all CASA Model C-212 series airplanes when converted to a cargo configuration in accordance with CASA Service Bulletin 212- 25-35, dated October 23, 1985, or other modifications, certificated in any category. Compliance is required within 9 months after the effective date of this AD, or prior to conversion to a cargo configuration, whichever occurs later. In the cargo configuration, to preclude an undetected fire in the main cabin, accomplish the following, unless previously accomplished: A. Install a smoke detector system in accordance with CASA Service Bulletin 212- 26-06, dated October 23, 1985. 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, Standardization Branch, ANM-113, 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 the modification required by this AD. All persons affected by this directive who have not already received the appropriate service document from the manufacturer may obtain copies upon request to Construcciones Aeronauticas S.A., Getafe, Madrid, Spain. This document may be examined at the FAA, Northwest Mountain Region, 17900 Pacific Highway South, Seattle, Washington, or the Seattle Aircraft Certification Office, 9010 East Marginal Way South, Seattle, Washington. This amendment becomes effective March 9, 1987.
2006-18-03: The FAA is adopting a new airworthiness directive (AD) for certain EMBRAER Model EMB-145XR airplanes. This AD requires modification of the flap system interface wiring. This AD results from a finding that the aural and visual warnings, which should be activated when the flaps are set to 22 degrees during takeoff, were not enabled during the manufacture of certain Model EMB-145XR airplanes. We are issuing this AD to prevent overrunning the runway during takeoff.
2018-15-04: We are adopting a new airworthiness directive (AD) for certain General Electric Company (GE) CF6-80A, CF6-80A1, CF6-80A2, CF6-80A3, CF6-80C2A1, CF6-80C2A2, CF6-80C2A3, CF6-80C2A5, CF6-80C2A5F, CF6- 80C2A8, CF6-80C2B1, CF6-80C2B1F, CF6-80C2B2, CF6-80C2B2F, CF6-80C2B4, CF6-80C2B4F, CF6-80C2B5F, CF6-80C2B6, CF6-80C2B6F, CF6-80C2B6FA, CF6- 80C2B7F, CF6-80C2D1F, CF6-80C2L1F, and CF6-80C2K1F turbofan engines. This AD was prompted by an uncontained failure of a high-pressure turbine (HPT) stage 2 disk that resulted in a fire. This AD requires ultrasonic inspection (UI) of HPT stage 1 and 2 disks. We are issuing this AD to address the unsafe condition on these products.
87-23-07 R1: 87-23-07 R1 SIKORSKY AIRCRAFT DIVISION: Amendment 39-5754 as amended by Amendment 39-6091. Applies to all Sikorsky Model S-76A/B helicopters, certificated in all categories, equipped with electrical door locking actuators installed in accordance with Sikorsky Drawing 76088-20016 using actuator P/N 22020256 in left and right passenger doors, except those helicopters which have installed a manual override kit, P/N 76070-20097. (Docket 87-ASW-30) Compliance is required within the next 25 hours' time in service after the effective date of this AD unless already accomplished. To prevent the passenger door locks from jamming in the locked position due to a malfunctioning electrical door locking actuator, accomplish the following: (a) Remove electrical door locking actuators, P/N 22020256, in accordance with Sikorsky Alert Service Bulletin (ASB) No. 76-52-10A, dated August 27, 1987. NOTE: Some of the actuators may not be identified with this P/N 22020256; however, as an alternate means of identifying these actuators, a housing/casting, P/N 20220307, appears on these units identifying them as GM actuators P/N 22020256. (b) Upon request, with substantiating data, an alternate means of compliance which provides an equivalent level of safety or adjustment in the compliance time may be used when approved by the Manager, Boston Aircraft Certification Office, Aircraft Certification Division, Federal Aviation Administration, New England Region, 12 New England Executive Park, Burlington, Massachusetts 01803. These procedures shall be accomplished in accordance with Sikorsky ASB No. 76-52-10A, dated August 27, 1987. This incorporation by reference was approved by the Director of the Federal Register in accordance with 5 U.S.C. 552(a)(1) and 1 CFR Part 51. Copies may be obtained from Sikorsky Aircraft, 6900 Main Street, Stratford, Connecticut 06601-1381. Copies may be inspected at the Office of the Regional Counsel, Federal Aviation Administration, 4400 Blue Mound Road, Fort Worth, Texas, or at the Office of the Federal Register, 1100 L Street, NW., Room 8401, Washington, D.C. This amendment revises Amendment 39-5754 (52 FR 43054; November 9, 1987), AD 87-23-07 which was effective on January 11, 1989. This amendment (39-6091, AD 87-23-07 R1) becomes effective on January 11, 1989.
89-12-03: 89-12-03 BRITISH AEROSPACE: Amendment 39-6228. Applicability: Model BAe 125-800A series airplanes, up to and including serial number 258147, certificated in any category. Compliance: Required as indicated, unless previously accomplished. To prevent damage to the engine fan blades, accomplish the following: A. Within 14 days after the effective date of this AD, inspect the left and right airflow angle sensor vanes for the trailing edge balance weight installation feature, in accordance with British Aerospace Service Bulletin 27-149, dated March 17, 1989. 1. If the inspection reveals an airflow angle sensor vane that does not have the balance weight feature installed, no further action is required. 2. If the inspection reveals an airflow angle sensor vane that has the balance weight feature installed, visually inspect the balance weight for security of its attachment in the trailing edge of the airflow angle sensor vane, in accordance with the service bulletin. a. If the balance weight is loose, damaged, or missing, replace it with a new airflow angle sensor vane prior to further flight, in accordance with the service bulletin. b. If the balance weight is secure and is not damaged, reinspect the balance weight for security, prior to each flight, until it is replaced with a new airflow angle sensor vane that does not have the trailing edge balance weight installation feature. 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, Standardization Branch, ANM-113, 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, Standardization Branch, ANM-113. 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 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 British Aerospace, PLC, Librarian for Service Bulletins, P.O. Box 17414, Dulles International Airport, Washington, D.C. 20041. This information may be examined at the FAA, Transport Airplane Directorate, Northwest Mountain Region, 17900 Pacific Highway South, Seattle, Washington, or Seattle Aircraft Certification Office, 9010 East Marginal Way South, Seattle, Washington. This amendment (39-6228, AD 89-12-03) becomes effective on June 12, 1989.
89-18-04: 89-18-04 MCDONNELL DOUGLAS: Amendment 39-6295. (Docket No. 89-NM-16-AD) \n\n\tApplicability: McDonnell Douglas Model DC-9-80 (MD-80) series airplanes and Model MD-88 airplanes, as listed in McDonnell Douglas Service Bulletin 80-8, dated November 3, 1988, certificated in any category. \n\n\tCompliance: Required as indicated, unless previously accomplished. \n\n\tTo prevent fire in the number 2 engine nacelle, accomplish the following: \n\n\tA.\tWithin 18 months after the effective date of this AD, relocate the number 2 engine starter shutoff valve pneumatic tube, in accordance with the accomplishment instructions in McDonnell Douglas MD-80 Service Bulletin 80-8, dated November 3, 1988. \n\n\tB.\tAn 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. \n\n\tNOTE: 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. \n\n\tC.\tSpecial 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. \n\n\tAll persons affected by this directive who have not already received the appropriate service documents from the manufacturer may obtain copies upon request to McDonnell Douglas Corporation, 3855 Lakewood Boulevard, Long Beach, California 90846, Attention: Director of Publications, C1-LOO (54-60). These documents may be examined at the FAA, Northwest Mountain Region, 17900 Pacific Highway South, Seattle, Washington, or at 3229 East Spring Street, Long Beach, California. \n\n\tThis amendment (39-6295, AD 89-18-04) becomes effective on September 18, 1989.