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2011-13-02: 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: During Landing Gear retraction/extension ground checks performed on the P2006T, a loose Seeger ring was found on the nose landing gear hydraulic actuator cap. The manufacturer has identified the root cause of this discrepancy in a design deficiency of the hydraulic actuator caps. This condition, if not corrected, could determine uncommanded and improper extension of the nose or main landing gear. We are issuing this AD to require actions to correct the unsafe condition on these products.
2021-13-08: The FAA is adopting a new airworthiness directive (AD) for all Safran Helicopter Engines, S.A. Arriel 2C and Arriel 2S1 model turboshaft engines. This AD was prompted by reports of error messages on the full authority digital engine control (FADEC) B digital engine control unit (DECU), caused by blistering of the varnish on the DECU circuit board. This AD requires the replacement of certain FADEC B DECUs. The FAA is issuing this AD to address the unsafe condition on these products.
98-04-24: This amendment adopts a new airworthiness directive (AD) that applies to Raytheon Aircraft Company Models E55, E55A, 58, 58A, 58P, 58PA, 58TC, 58TCA airplanes, and 60, 65-B80, 65-B90, 90, F90, 100, 300, and B300 series airplanes. This action requires revising the FAA-approved Airplane Flight Manual (AFM) to specify procedures that would prohibit flight in severe icing conditions (as determined by certain visual cues), limit or prohibit the use of various flight control devices while in severe icing conditions, and provide the flight crew with recognition cues for, and procedures for exiting from, severe icing conditions. This AD is prompted by the results of a review of the requirements for certification of these airplanes in icing conditions, new information on the icing environment, and icing data provided currently to the flight crew. The actions specified by this AD are intended to minimize the potential hazards associated with operating these airplanes in severe icingconditions by providing more clearly defined procedures and limitations associated with such conditions
98-04-22: This amendment adopts a new airworthiness directive (AD) that applies to SOCATA - Groupe AEROSPATIALE, Model TBM 700 airplanes. This action requires revising the FAA-approved Airplane Flight Manual (AFM) to specify procedures that would prohibit flight in severe icing conditions (as determined by certain visual cues), limit or prohibit the use of various flight control devices while in severe icing conditions, and provide the flight crew with recognition cues for, and procedures for exiting from, severe icing conditions. This AD is prompted by the results of a review of the requirements for certification of these airplanes in icing conditions, new information on the icing environment, and icing data provided currently to the flight crew. The actions specified by this AD are intended to minimize the potential hazards associated with operating these airplanes in severe icing conditions by providing more clearly defined procedures and limitations associated with such conditions.
98-04-05: This amendment adopts a new airworthiness directive (AD) that applies to certain Fairchild Aircraft Incorporated (Fairchild) Models SA226-TC, SA226-T, SA226-T(B), and SA226-AT airplanes. This action requires inspecting the center flap hinge and wing trailing edge ribs at the flap actuator attach brackets for cracks and if no cracks are found, installing a doubler on the rib, or replacing a cracked rib with a new rib assembly that is reinforced with a doubler. This action is the result of high local stress concentration, which led to fatigue cracking of the wing trailing edge ribs. The actions specified by this AD are intended to prevent asymmetrical flap deflection, which could force the airplane into an uncommanded roll with possible loss of control of the airplane.
93-01-16: 93-01-16 BEECH AIRCRAFT CORPORATION: Amendment 39-8470. Docket No. 92-CE-39-AD. Applicability: Model 1900C airplanes, serial numbers UC-1 through UC-174 and UD-1 through UD-6 (also referred to as Model C-12J), certificated in any category. Compliance: Required within the next 200 hours time-in-service after the effective date of this AD, unless already accomplished. To prevent an airplane fire caused by fuel entering the electrically-heated stall warning vane housing, accomplish the following: (a) Inspect the pneumatic deice lines and the deice distributor valve for fuel leakage in accordance with Parts I and II of the ACCOMPLISHMENT INSTRUCTIONS section of Beech Service Bulletin (SB) No. 2430, dated March 1992. Prior to further flight, replace any fuel contaminated parts in accordance with Part II of the ACCOMPLISHMENT INSTRUCTIONS section of the referenced service information. (b) Modify the wet wing fuel barriers in accordance with Parts III and IV of the ACCOMPLISHMENT INSTRUCTIONS section of Beech SB No. 2430, dated March 1992. (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) An alternative method of compliance or adjustment of the compliance time that provides an equivalent level of safety may be approved by the Manager, Wichita Aircraft Certification Office, FAA, 1801 Airport Road, Room 100, Wichita, Kansas 67209. The request shall be forwarded through an appropriate FAA Maintenance Inspector, who may add comments and send it to the Manager, Wichita Aircraft Certification Office. NOTE: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Wichita Aircraft Certification Office. (e) The inspection and modification required by this AD shall be done in accordance with Beech Service Bulletin No. 2430, datedMarch 1992. 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 the Beech Aircraft Corporation, P.O. Box 85, Wichita, Kansas 67201-0085. Copies may be inspected at the FAA, Central Region, Office of the Assistant Chief Counsel, Room 1558, 601 E. 12th Street, Kansas City, Missouri, or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC. (f) This amendment becomes effective on March 8, 1993.
91-21-04: 91-21-04 BRITISH AEROSPACE: Amendment 39-8051. Docket No. 91-NM-26-AD. Applicability: Model BAC 1-11 200 and 400 series airplanes, certificated in any category. Compliance: Required as indicated, unless previously accomplished. To prevent degradation in the structural capabilities of the pressure cabin on affected airplanes, accomplish the following: A. For airplanes operating at a maximum cabin differential pressure of 7.5 pounds per square inch (psi), as specified in British Aerospace Alert Service Bulletin 53-A-PM5991, Issue 1, dated September 5, 1990: At or prior to the accumulation of 33,000 landings or within 4,000 landings after the effective date of this AD, whichever occurs later, and thereafter at intervals not to exceed 8,000 landings, accomplish the following: 1. Perform a dye penetrant inspection to detect cracks in the left and right machined attachment angles, Part Number AB27-7761/2, in accordance with paragraph 2.1.3 of the service bulletin. 2. Perform a visual inspection to detect cracks in the top flange of the longitudinal boom of the left and right outboard auxiliary beam, in accordance with paragraph 2.1.4 of the service bulletin. B. For airplanes operating at a cabin pressure in excess of 7.5 psi up to a maximum of 8.2 psi, as specified in British Aerospace Alert Service Bulletin 53-A-PM5991, Issue 1, dated September 5, 1990: At or prior to the accumulation of 22,000 landings or within 3,000 landings after the effective date of this AD, whichever occurs later, and thereafter at intervals not to exceed 5,000 landings, accomplish the following: 1. Perform a dye penetrant inspection to detect cracks in the left and right machined attachment angles, Part Number AB27-7761/2, in accordance with paragraph 2.2.3 of the service bulletin. 2. Perform a visual inspection to detect cracks in the top flange of the longitudinal boom of the left and right outboard auxiliary beam, in accordance with paragraph 2.2.4 of the service bulletin. C. If defects are found during the inspections required by this AD, prior to further flight, either replace the cracked structure with serviceable parts of the same part number; or repair in accordance with a method approved by the Manager, Standardization Branch, ANM-113, FAA, Northwest Mountain Region. Following repair or replacement, repeat the inspections required by paragraphs A. and B. of this AD at the specified intervals. D. All machined attachment angles having Part Number AB27-7761/2 must be replaced with a new part of the same part number prior to the accumulation of 85,000 landings since new and thereafter at intervals not to exceed 85,000 landings. E. An alternative method 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 forwarded through an FAA Principal Maintenance Inspector, who may concur or comment and then send it to the Manager, Standardization Branch, ANM-113. 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. G. The inspection, repair, and replacement requirements shall be done in accordance with British Aerospace Alert Service Bulletin 53-A-PM5991, Issue 1, dated September 5, 1990. 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, D.C. 20041-0414. Copies may be inspected at the FAA, Transport Airplane Directorate, 1601 Lind Avenue S.W., Renton, Washington; or at the Office of the Federal Register, 1100 L Street N.W., Room 8401, Washington, D.C.This amendment (39-8051, AD 91-21-04) becomes effective on November 19, 1991.
2021-13-02: The FAA is adopting a new airworthiness directive (AD) for certain The Boeing Company Model 777-300ER series airplanes. This AD was prompted by a report that a production design change to certain insulation blankets inadvertently opened up leakage paths for halon and smoke to escape from the aft cargo compartment in the event of a fire. This AD requires installation of an insulation blanket assembly on top of existing insulation blankets in certain areas of the forward endwall in the aft cargo compartment. The FAA is issuing this AD to address the unsafe condition on these products.
2021-14-10: The FAA is adopting a new airworthiness directive (AD) for certain The Boeing Company Model 747-400, 747-400D, and 747-400F series airplanes. This AD was prompted by reports of burned Boeing Material Specification (BMS) 8-39 urethane foam found in certain locations on the airplane; investigation revealed that the fire-retardant properties degrade with age. This AD requires inspecting the insulation blankets in certain areas of the forward cargo compartment for exposed BMS 8-39 urethane foam, not encapsulated by a protective fire resistant barrier, and for seal integrity, and replacing the BMS 8-39 urethane foam and seal if necessary. The FAA is issuing this AD to address the unsafe condition on these products.
48-08-01: 48-08-01 BEECH: Applies to Model 35 Airplanes Having Serial Numbers Below D-1095 Except D-923, D-925, D-940, D-954, D975, D-983, D-1003, D-1006, D-1013, D-1025, D-1031, D-1038, D-1042, D-1048 Through D-1050, D-1052, D-1053, D-1056 Through D-1062, D-1064, D-1066 Through D-1068, D-1071, D-1072, D-1074, D-1075, D-1077 Through D-1081, D-1083, and D-1085 Through D-1093. Compliance required by November 1, 1948. To preclude possible engine malfunctioning as a result of starter gear chipping caused by improper engagement of the starter mechanism, accomplish the following: (1) Remove the starter assembly from the engine and replace the original starter pinion and clutch assembly with the new assembly, P/N DR1885537. Check the solenoid linkage adjustment to ascertain that the pinion and clutch assembly can move rearward to contact the starter adapter. If the linkage prevents full disengagement of the pinion, remove the toggle link pin and turn the plunger shaft outward untilfull retraction is obtained. Check to make sure that at least two threads are still engaged. Reinstall the starter assembly. (2) Install the new resistor coil, P/N DR 1885541, on the starter battery and ground power terminals. The coil must hang downward from the terminals. (3) Make all electrical connections as covered in Beech Starter Latching Relay Installation Instructions. (Continental Service Bulletin No. M47-19 dated August 31, 1947, and Beech Service Letter No. 10, Model 35, cover this same subject.)