Results
2022-22-07: The FAA is adopting a new airworthiness directive (AD) for certain Piaggio Aviation S.p.A. (type certificate previously held by Piaggio Aero Industries S.p.A.) (Piaggio) Model P-180 airplanes. This AD was prompted by 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 identifies the unsafe condition as corrosion in the bottom fuselage area of the cabin compartment due to inner and outer sides of fuselage skin panels of certain airplanes treated with the less effective primer. This AD requires repetitively inspecting the fuselage skin panels, visually inspecting the entire fuselage inner side skin if necessary, and taking any necessary corrective actions. The FAA is issuing this AD to address the unsafe condition on these products.
90-10-06: 90-10-06 SAAB-SCANIA: Amendment 39-6595. Docket No. 90-NM-64-AD. Applicability: Model SAAB 340B series airplanes, Serial Numbers 161 through 197, certificated in any category. Compliance: Required as indicated, unless previously accomplished. To prevent oscillations (flutter) of the rudder, accomplish the following: A. Within 10 flight hours time-in-service, accomplish the following: 1. Install a placard in the cockpit stating: "Air Speed Restricted to 220 KIAS", and 2. Incorporate the following into the Limitations Section of the FAA-approved Airplane Flight Manual (AFM): Restrict the maximum operating speed to 220 KIAS in accordance with Section 2. under "Short Term Actions" of SAAB 340 Service Newsletter, SN-9002, Revision 1, dated February 19, 1990. This may be accomplished by inserting a copy of this AD in the AFM. B. Within 90 days after the effective date of this AD, install new rudder and rudder trim tab balance weights in accordance with SAAB-Scania Service Bulletin SAAB 340-55-026, dated March 16, 1990. Upon installation of these balance weights, the placard and flight manual limitation required by paragraph A., above, may be removed. C. 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. D. 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 obtaincopies upon request to SAAB-Scania AB, SAAB Aircraft Product Support, S-581.88, Linkoping, Sweden. This information may be examined at the FAA, Northwest Mountain Region, Transport Airplane Directorate, 17900 Pacific Highway South, Seattle, Washington, or at the Standardization Branch, 9010 East Marginal Way South, Seattle, Washington. This amendment (39-6595, AD 90-10-06) becomes effective on May 24, 1990.
96-12-02: This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A300 B2 and B4 series airplanes, that requires measurements of the thickness of the inner skin of the longitudinal lap joint from the inside of the fuselage at certain stringers. This amendment also requires inspections to detect stress corrosion cracking in the subject area, and repair, if necessary. This amendment is prompted by reports of stress corrosion cracking found in the skin at the longitudinal lap joint at certain stringers of the fuselage, which was caused by the increased stress level in the subject area when it was reworked beyond certain limits. The actions specified by this AD are intended to prevent such stress corrosion cracking which, if not detected and corrected in a timely manner, could result in rapid depressurization of the airplane.
2004-22-03: The FAA is adopting a new airworthiness directive (AD) for certain EMBRAER Model EMB-135 and -145 series airplanes. This AD requires measuring the fillet radius dimension of the trunnion fitting webs of the wings; and reworking the fillet radius of the trunnion fitting web in order to increase the radius, doing related investigative actions, and doing applicable corrective action, if necessary. This AD is prompted by a report indicating that trunnion fittings of the wings have been manufactured with a web fillet radius smaller than the minimum required by the design data, which may induce the occurrence of fatigue cracks at the root of the trunnion fillet radius and adjacent structures (e.g., spar and ribs). We are issuing this AD to detect and correct fatigue cracking of the wing trunnion fittings or adjacent structure, which could result in failure of the main landing gear, consequent damage to surrounding structure, and possible loss of control of the airplane during landing.
99-27-03: This amendment adopts a new airworthiness directive (AD), applicable to certain Fokker Model F27 Mark 050 series airplanes. This action requires repetitive inspections of the connections between certain ribs and stringers of the wing skins to detect loose or missing rivets or gaps, and corrective actions, if necessary. This action also requires eventual modification of the rib-stringer connection, which terminates the repetitive inspections. This amendment is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified in this AD are intended to prevent fatigue cracking in the skin and stringers, which could result in reduced structural integrity of the wings.
2022-20-04: The FAA is superseding airworthiness directive (AD) 2021-26- 08, which applied to certain Bell Textron Canada Limited Model 206, 206A, 206A-1, 206B, 206B-1, 206L, 206L-1, 206L-3, and 206L-4 helicopters. AD 2021-26-08 required removing certain nuts from service; installing newly designed nuts; applying a specific torque, and a torque stripe to each newly installed nut; after the installation of each newly designed nut, inspecting the torque; and depending on the inspection results, either applying a torque stripe, or performing further inspections and removing certain parts from service. AD 2021- 26-08 also prohibited installing any affected nut on any tail rotor drive shaft (TRDS) disc pack (Thomas) coupling. Since the FAA issued AD 2021-26-08, the FAA determined certain torque values and part numbers (P/Ns) need to be revised. This AD was prompted by reports of cracked or missing nuts installed on the TRDS Thomas couplings and the need to revise certain torque values and P/Ns in AD 2021-26-08. This AD requires removing certain nuts from service; installing newly designed nuts; applying torque and a torque stripe; and additional corrective actions if necessary. This AD also prohibits installing any affected nut on any TRDS Thomas coupling, as specified in a Transport Canada AD, which is incorporated by reference. The FAA is issuing this AD to address the unsafe condition on these products.
95-25-06: This amendment adopts a new airworthiness directive (AD), applicable to certain Beech Model 400, 400A, and 400T (military T-1A) airplanes, that requires modification of the standby instrument lighting system. This amendment is prompted by a report that, due to the design of the standby instrument lighting system, the lighting for the standby instruments dimmed to an unacceptable level when the main electrical power was turned off. The actions specified by this AD are intended to ensure that the standby instrument lighting system adequately illuminates the standby instrument, if normal electrical power is lost or is turned off as a result of fire or smoke in the cockpit.
99-27-02: This amendment adopts a new airworthiness directive (AD) that applies to all Cessna Aircraft Company (Cessna) 170, 172, 175, and 177 series airplanes. This AD requires replacing certain fuel selector valve cams or fuel selector valves that Cessna shipped from December 6, 1998, through May 10, 1999, and prevents the future installation of these fuel selector valve cams or fuel selector valves. This AD allows the pilot to check the logbooks to determine whether one of these fuel selector valve cams or fuel selector valves is installed. This AD results from reports from Cessna that fuel selector valve cams and fuel selector valves were manufactured with control shafts that will not allow both tanks to supply fuel to the engine in certain situations. The actions specified by this AD are intended to prevent an inadequate supply of fuel from reaching the engine because of a fuel selector valve cam or fuel selector valve. This could result in an emergency landing or loss of control of the airplane.
90-17-11: 90-17-11 BRITISH AEROSPACE: Amendment 39-6699. Docket No. 90-NM-78-AD. Applicability: Model HS. 125-700A and BAe 125-800A series airplanes, as listed in British Aerospace Service Bulletin 24-263-9486A, Revision 1, dated January 27, 1988, certificated in any category. Compliance: Required within 30 days after the effective date of this AD, unless previously accomplished. To ensure crewmembers will pull the correct circuit breakers to electrical/electronic equipment that may be the source of fire or smoke in the cockpit, accomplish the following. A. Install circuit breaker identification labels in panel DA-A, in accordance with British Aerospace Service Bulletin 24-263-9486A, Revision 1, dated January 27, 1988. 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, Transport Airplane Directorate. NOTE: The request should be submitted directly to the 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. 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 documents 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. These documents may be examined at the FAA, Northwest Mountain Region, Transport Airplane Directorate, 1601 Lind Avenue, S.W., Renton, Washington. This amendment (39-6699, AD 90-17-11) becomes effective on September 17, 1990.
2022-22-08: The FAA is adopting a new airworthiness directive (AD) for Bell Textron Canada Limited (type certificate previously held by Bell Helicopter Textron Canada Limited) Model 206L, 206L-1, 206L-3, and 206L-4 helicopters with a certain part-numbered main rotor (M/R) blade installed under Supplemental Type Certificate (STC) SR02684LA. This AD was prompted by delamination of M/R blades. This AD requires a repetitive inspection for delamination, and depending on the results, removing the M/R blade from service and reporting certain information. The FAA is issuing this AD to address the unsafe condition on these products.