Results
2010-14-10: The FAA is superseding an existing airworthiness directive (AD), which applies to certain Model 747-100, 747-200B, and -200F series airplanes. That AD currently requires inspections to detect cracking in the upper row of fasteners holes of the skin lap joints in the fuselage lower lobe, and repair if necessary. This new AD reduces the maximum interval of the post-modification inspections. This AD results from reports of fatigue cracking on modified airplanes. We are issuing this AD to detect and correct fatigue cracking in the longitudinal lap joints of the fuselage lower lobe, which could lead to the rapid decompression of the airplane and the inability of the structure to carry fail-safe loads.
99-07-02: This amendment adopts a new airworthiness directive (AD) that is applicable to Eurocopter France Model AS 332C, L, L1, and L2 helicopters and Model SA 330F, G, and J helicopters. This action requires inspecting the position and bonding of the main rotor blade (blade) leading edge stainless steel protective strips (strips) that were replaced by C.T.I. Dallas. This amendment is prompted by the discovery of a strip that was both mislocated and improperly bonded. The strip had been replaced by C.T.I. Dallas. This condition, if not corrected, could result in failure of the blade and subsequent loss of control of the helicopter.
2022-13-01: The FAA is adopting a new airworthiness directive (AD) for certain Leonardo S.p.a. Model AW169 helicopters. This AD was prompted by a report of a blockage in a fuel tank vent line. This AD requires inspecting the fuel tank vent lines, 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.
2006-13-18: The FAA is adopting a new airworthiness directive (AD) for certain transport category airplanes, identified above. This AD requires installing a bonding jumper from the boost pump volute to the fuel tank structure, and related investigative/corrective actions. This AD results from fuel system reviews conducted by the manufacturer. We are issuing this AD to prevent point-contact arcing or filament heating in the fuel tank, which, in the event of a short or ground fault inside the fuel tank, could result in a fuel tank explosion and consequent loss of the airplane.
47-32-17: 47-32-17 BELLANCA: (Was Mandatory Note 7 of AD-773-5.) Applies to Models 14- 13, 14-13-2 Serial Numbers 1060, and Up. Compliance required prior to October 15, 1947. Improper positioning of the inspection covers on the top surface of each wing at the landing gear retracting sprocket can cause malfunctioning of the gear retracting mechanism. This cover is held in place by two spring clips, and if the cover is installed with the clips running in a chordwise direction, it is possible that the ends of the clips will bear against the chain and force it off the sprocket, jamming the system. Inspect the covers on your airplane for proper installation, and paint arrows on the cover and wing surface so that the arrows point toward each other when the spring clips run spanwise. (Bellanca Service Bulletin No. 10 covers this same subject.)
91-12-07: 91-12-07 WYTWORNIA SPRZETU KOMUNEKACYJNEGO PZL-MIELEC: Amendment No. 39-7018. Docket No. 91-CE-07-AD. Applicability: Model M18 airplanes (serial numbers (S/N) 1Z013-21 through 1Z023-30), equipped with an agriculture equipment electro-hydraulic control system (Modification D73.701.00.1), certificated in any category. Compliance: Required as indicated, unless already accomplished. To prevent failure of the electro-hydraulic control system that results in loss of flap and brake control, accomplish the following: (a) For S/N 1Z013-21 through 1Z023-30 airplanes, upon the accumulation of 200 hours time-in- service (TIS) or within the next 25 hours TIS after the effective date of this AD, whichever occurs later, replace each flexible hose having part number (P/N) D73.7/21.00.0 or D73.7/24.00.0. with a new hose in accordance with the instructions in PZL-Mielec Mandatory Engineering Bulletin (MEB) No. K/02.141/90, dated April 1990. (1) If hoses are replaced with either P/N D73.7/21.00.0 or D73.7/24.00.0, replace these hoses at intervals not to exceed 200 hours TIS. (2) If hoses are replaced with P/N D73.7/26.00.0 or D73.7.25.00.0 hose, no further action is required. (b) For S/N 1Z013-21 through 1Z022-05 airplanes, upon the accumulation of 500 hours TIS or within the next 100 hours TIS after the effective date of this AD, whichever occurs later, modify the electro- hydraulic control system in accordance with the instructions in Paragraph III, 2. of PZL-Mielec MEB No. K/02.141/90, dated April 1990. (c) Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes to a location where the requirements of this AD can be accomplished. (d) An alternative method of compliance or adjustment of the initial or repetitive compliance times that provides an equivalent level of safety may be approved by the Manager, Brussels Aircraft Certification Staff, FAA, Europe, Africa, and Middle East Office, c/oAmerican Embassy, B-1000, Brussels, Belgium. The request should be forwarded through an appropriate FAA Maintenance Inspector, who may add comments and then send it to the Manager, Brussels Aircraft Certification Staff. (e) The modifications and replacements required by this AD shall be done in accordance with PZL-Mielec Mandatory Engineering Bulletin No. K/02.141/90, dated April 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 PZL-Mielec, Ludowego Wojska Polkiego 3, 39-300 Mielec, Poland. 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, 1100 L Street, NW; Room 8401, Washington, DC. This amendment (39-7018, AD 91-12-07) becomes effective on July 5, 1991.
2022-11-05: The FAA is adopting a new airworthiness directive (AD) for certain The Boeing Company Model 777 airplanes. This AD was prompted by a report of the loss of the nuts at all four fastener locations common to the outboard flap inboard support rear spar attachment fittings, which affects the retention feature of the fasteners and leaves the fasteners susceptible to migrating out of the joint. This AD requires repetitive detailed inspections for discrepancies of the fasteners and shim of the wing rear spar at certain outboard flap supports; a detailed inspection for damage of the shim, flap support mechanism, and wing lower skin; installation of new fasteners and shims; and repair or replacement of damaged parts. The FAA is issuing this AD to address the unsafe condition on these products.
92-27-21: 92-27-21 BELL HELICOPTER TEXTRON, INC. (BHTI): Amendment 39-8575. Docket Number 92-ASW-45. Applicability: Model 205A-1 and 205B series helicopters, with increased diameter tail rotor drive shaft (drive shaft), P/N 204-040-620-011, installed, certificated in any category. Compliance: Required as indicated, unless accomplished previously. To prevent failure of the drive shaft, loss of tail rotor control, and subsequent loss of control of the helicopter, accomplish the following: (a) Within 25 hours' time-in-service after the effective date of this AD: (1) Conduct a one-time inspection of the helicopter and the drive shaft in accordance with paragraphs 1 through 4 of the Accomplishment Instructions of BHTI Alert Service Bulletin (ASB) 205-92-49, dated October 5, 1992, for BHTI Model 205A-1 helicopters, and ASB 205B-92-13, dated October 5, 1992, for BHTI Model 205B helicopters. (2) Reassemble the tail rotor drive shaft assembly in accordance with paragraph 5 of the pertinent ASB to ensure a minimum of 0.50 inch clearance is obtained between the tail rotor drive shaft tunnel (drive shaft tunnel) and the drive shaft. (b) Each time the starter generator is installed after maintenance, ensure a minimum of 0.50 inch clearance is maintained between the drive shaft tunnel and the drive shaft. Adjust the position of the drive shaft tunnel in accordance with paragraph 5 of the pertinent ASB to obtain proper clearance. (c) Remove unairworthy parts found during the inspection required in paragraph (a) and replace with airworthy parts before further flight. (d) 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, Rotorcraft Certification Office, FAA, Rotorcraft Directorate, Fort Worth, Texas 76193-0170. Operators shall submit their requests through an FAA Principal Maintenance Inspector, who may concur or comment and then send it to the Manager, Rotorcraft Certification Office. NOTE: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Rotorcraft Certification Office. (e) Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate the helicopter to a location where the requirements of this AD can be accomplished. (f) The inspection, removal, and replacement, if necessary, and reassembly shall be done in accordance with the applicable BHTI ASB 205-92-49 or 205B-92-13, both dated October 5, 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 Bell Helicopter Textron, Inc., P.O. Box 482, Fort Worth, Texas 76101. Copies may be inspected at the FAA, Office of the Assistant Chief Counsel, 4400 Blue Mound Road, bldg. 3B, room 158, Fort Worth, Texas; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC. (g) This amendment becomes effective on July 7, 1993, to all persons except those persons to whom it was made immediately effective by Priority Letter AD 92-27-21, issued January 7, 1993, which contained the requirements of this amendment.
2022-12-01: The FAA is adopting a new airworthiness directive (AD) for certain Bombardier, Inc., Model BD-700-1A10 and BD-700-1A11 airplanes. This AD was prompted by reports of oxygen leaks caused by cracked, brittle, or broken oxygen hoses that were found during scheduled maintenance tests of the airplane oxygen system. This AD requires an inspection of the oxygen hose assembly to determine if an affected part number is installed, and replacement of affected oxygen hoses. For certain airplanes, this AD allows repetitive testing of the oxygen system until affected hoses are replaced. This AD also prohibits installation of an affected oxygen hose. The FAA is issuing this AD to address the unsafe condition on these products.
99-06-16: This amendment adopts a new airworthiness directive (AD), applicable to CFM International CFM56-5 series turbofan engines, that reduces the low cycle fatigue (LCF) retirement lives for certain high pressure turbine rotor (HPTR) front air seals, and provides a drawdown schedule for those affected parts with reduced LCF retirement lives. This amendment is prompted by results of a refined life analysis performed by the manufacturer that revealed minimum calculated LCF lives significantly lower than the published LCF retirement lives. The actions specified by this AD are intended to prevent a LCF failure of the HPTR front air seal, which could result in an uncontained engine failure and damage to the aircraft.