Results
2012-17-10: We are adopting a new airworthiness directive (AD) for various restricted category Model HH-1K, TH-1F, TH-1L, UH-1A, UH-1B, UH-1E, UH- 1F, UH-1H, UH-1L, and UH-1P helicopters with certain main rotor (M/R) blade assemblies installed, to require inspecting the grip plates, doublers, and upper and lower surfaces of the M/R blades in the area between blade stations 24.5 and 40 for an edge void, corrosion, or a crack. This AD is prompted by several reports of fatigue cracks on M/R blades installed on Bell Helicopter Textron, Inc. (Bell) Model 212 helicopters. These same part-numbered M/R blades may also be installed on certain FAA-approved modified restricted category helicopters. These actions are intended to detect an edge void, corrosion, or a crack on an M/R blade, which could lead to loss of the M/R blade and subsequent loss of control of the helicopter.
98-07-07: This amendment supersedes existing airworthiness directive (AD) 96-13-04, applicable to Rolls-Royce, plc RB211 series turbofan engines, that currently requires removing and replacing a rigid low pressure (LP) fuel system tube assembly with a tube assembly incorporating flexible sections and revised clip points in order to preclude cracking and subsequent fuel leakage. This amendment requires replacing one of the flexible fuel tube assemblies installed in accordance with AD 96-13-04 with an alternate flexible fuel tube assembly that is not prone to rupture. This AD also requires immediate replacement of any rigid fuel tubes not previously removed from service as required by AD 96-13-04. The amendment is prompted by reports of fuel line rupture on one of the flexible fuel tube assemblies installed in accordance with AD 96-13-04. The actions specified by this AD are intended to prevent high volume fuel leaks and reported fuel collection inside the engine nacelle, which couldresult in an uncontrolled engine fire. The incorporation by reference of certain publications listed in the regulations is approved by the Director of the Federal Register as of April 29, 1998. Comments for inclusion in the Rules Docket must be received on or before June 15, 1998.
98-08-16: This amendment adopts a new airworthiness directive (AD), applicable to certain Saab Model SAAB SF340A and 340B series airplanes, that requires a one-time inspection to detect discrepancies of the flight idle stop override mechanism, and corrective action, if necessary. This amendment is prompted by the issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified by this AD are intended to prevent increased braking distance for landings that require the flight idle stop override, resulting from the combination of failure of the override mechanism and inability of the power levers to be moved below the flight idle position after touchdown.
2012-15-07 R1: We are revising an existing airworthiness directive (AD) for Glasflugel Models Standard Libelle-201B, Club Libelle 205, Mosquito, and Kestrel gliders. That AD currently requires actions to address the unsafe condition on these products. This new AD includes clarification that the replacement control rod has an additional drain hole at the rod bottom between the forks and is the acceptable configuration for compliance. 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 corrosion damage to the elevator control rod that could lead to failure of the elevator control rod, possibly resulting in loss of control of the glider. We are issuing this AD to require actions to address the unsafe condition on these products.
98-08-17: This amendment adopts a new airworthiness directive (AD), applicable to various turbo-propeller powered General Dynamics (Convair) Model 240, 340, and 440 series airplanes, that requires revising the Airplane Flight Manual (AFM) to modify the limitation that prohibits positioning the power levers below the flight idle stop during flight, and to provide a statement of the consequences of positioning the power levers below the flight idle stop during flight. This amendment is prompted by incidents and accidents involving airplanes equipped with turboprop engines in which the ground propeller beta range was used improperly during flight. The actions specified by this AD are intended to prevent loss of airplane controllability, or engine overspeed and consequent loss of engine power caused by the power levers being positioned below the flight idle stop while the airplane is in flight.
98-08-14: This amendment adopts a new airworthiness directive (AD) applicable to Eurocopter France (Eurocopter) Model SA-365N, N1 and AS-365N2 helicopters that requires inspections of the main gearbox suspension diagonal cross-member (diagonal cross-member) for cracks, and removal of the diagonal cross-member and replacement with an airworthy diagonal cross-member if any crack is found. This amendment is prompted by several reports of the discovery of cracks in diagonal cross-members. The actions specified by this AD are intended to prevent failure of the diagonal cross-member which could cause the main gearbox to pivot, resulting in severe vibrations and a subsequent forced landing.
2012-17-12: We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 747-400 series airplanes. This AD was prompted by reports of water leaking into electrical and electronic equipment in the main equipment center (MEC). This AD requires modifying the floor panels; removing drains; installing floor supports, floor drain trough doublers, drain troughs, and drains; and sealing and taping the floor panels. We are issuing this AD to prevent water from entering the MEC, which could result in an electrical short and potential loss of several functions essential for safe flight.
92-26-06: 92-26-06 BRITISH AEROSPACE: Amendment 39-8433. Docket No. 92-NM-143-AD. Applicability: All Model BAe 125-800A series airplanes on which Modification No. 253284A has not been installed; certificated in any category. Compliance: Required as indicated, unless accomplished previously. To prevent the crew from failing to disable all appropriate circuit breakers in an emergency, accomplish the following: (a) Within 3 months after the effective date of this AD, install Modification No. 253284A by painting the perimeters of the "A SCRN" and "B SCRN" heat control circuit breakers with matte white (non-cellulose) paint, in accordance with British Aerospace Service Bulletin SB.24-288-3284A, dated February 7, 1992. (b) An alternative method of compliance or adjustment of the compliance time that provides an acceptable level of safety may be used if approved by the Manager, Standardization Branch, ANM-113, FAA, Transport Airplane Directorate. Operators shall submittheir requests through an appropriate FAA Principal Maintenance Inspector, who may add comments and then send it to the Manager, Standardization Branch. NOTE: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Standardization Branch, ANM-113. (c) Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate the airplane to a location where the requirements of this AD can be accomplished. (d) The installation shall be done in accordance with British Aerospace Service Bulletin SB.24-288-3284A, dated February 7, 1992. (NOTE: The issue date of that service bulletin is indicated only on "page 1 of 7"; no other page of the document is dated.) This incorporation by reference was approved by the Director of the Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR Part 51. Copies may be obtained from British Aerospace, PLC, Librarian for Service Bulletins, P.O. Box 17414, Dulles International Airport, Washington, DC 20041-0414. Copies may be inspected at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC. (e) This amendment becomes effective on February 1, 1993.
98-08-13: This amendment adopts a new airworthiness directive (AD) that is applicable to Eurocopter France Model SA 330F, G, and J, and AS 332C, L, L1, and L2 helicopters. This action requires daily inspections of the root of each tail rotor head pitch change spider arm (spider arm) for cracks, and an inspection of the tail rotor head pitch change spider (spider) for cracks and fretting corrosion. A terminating action for the requirements of this AD is the installation of an airworthy modified spider, an airworthy replacement spider, or an airworthy repaired spider. This amendment is prompted by one in-service report of fatigue cracking on a Model AS 332 helicopter. This condition, if not corrected, could result in failure of the spider arm, loss of control of the tail rotor blade, and subsequent loss of control of the helicopter.
91-04-09: 91-04-09 BRITISH AEROSPACE: Amendment 39-6896. Docket No. 90-NM-232-AD. Applicability: All Model ATP series airplanes, certificated in any category. Compliance: Required as indicated, unless previously accomplished. To detect damaged wires in the primary flight control cables, accomplish the following: A. For airplanes in Pre-Modification 10060A configuration: 1. Within 250 hours time-in-service after the effective date of this AD, and thereafter at intervals not to exceed 125 hours time-in-service, perform a visual inspection of the aileron primary control cables in the wings for wear and broken wires, in accordance with the Accomplishment Instructions in British Aerospace Service Bulletin ATP-27-26, dated April 5, 1990. 2. Prior to the accumulation of 2,500 hours time-in-service or within 200 hours time-in-service after the effective date of this AD, whichever occurs later, and thereafter at intervals not to exceed 2,500 hours time-in-service,perform a visual inspection of the fuselage primary control cables for wear and broken wires, in accordance with the Accomplishment Instructions in British Aerospace Service Bulletin ATP-27-26, dated April 5, 1990. NOTE: The repetitive inspection intervals shown herein should not be interpreted as extending the published life limits of any control cables being inspected. B. For airplanes in Post-Modification 10060A configuration: Within 125 hours time-in-service after the effective date of this AD, or within 750 hours time-in-service following accomplishment of Modification 10060A, whichever occurs later, and thereafter at intervals not to exceed 250 hours time-in-service, perform a visual inspection of the aileron primary control cables in the wings for wear and broken wires, in accordance with the Accomplishment Instructions in British Aerospace Service Bulletin ATP-27-26, dated April 5, 1990. C. If defective wires are found as a result of the inspections required by this AD, prior to further flight, accomplish the following in accordance with the Accomplishment Instructions in British Aerospace Service Bulletin ATP-27-26, dated April 5, 1990. 1. In the event of a single wire break, the ends must be trimmed to lie flush with the cable assembly and a full and free check of control travel must be carried out to ensure that the wire ends do not "snag". If cables do "snag", the cable must be replaced prior to further flight, in accordance with the service bulletin. 2. If two or more wires are found to be broken, prior to further flight, replace the damaged cable and replace any associated damaged fairlead rollers, in accordance with the service bulletin. D. 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, Transport Airplane Directorate. NOTE: Manager, Standardization Branch, ANM-113, and a copy sent to the cognizant FAA Principal Inspector (PI). The PI will then forward comments or concurrence to the Manager, Standardization Branch, ANM-113. E. 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 British Aerospace, PLC, Librarian for Service Bulletins, P.O. Box 20041-0414. These documents may be examined at the FAA, Northwest Mountain Region, Transport Airplane Directorate, 1601 Lind Avenue S.W., Renton, Washington. This amendment (39-6896, AD 91-04-09) becomes effective on March 22, 1991.