Results
2007-02-16: The FAA is superseding an existing airworthiness directive (AD), which applies to certain Saab Model SAAB-Fairchild SF340A and SAAB 340B airplanes. That AD currently requires repetitive inspections for wear of the brushes and leads and for loose rivets of the direct current (DC) starter generator, and related investigative/corrective actions if necessary. This new AD requires installing new, improved generator control units (GCUs). Installing the GCUs ends the repetitive inspection requirements of the existing AD. This AD results from reports of premature failures of the DC starter generator prior to scheduled overhaul. We are issuing this AD to prevent failure of the starter generator, which could cause a low voltage situation in flight and result in increased pilot workload and reduced redundancy of the electrical powered systems. DATES: This AD becomes effective March 1, 2007. The Director of the Federal Register approved the incorporation by reference of a certainpublication listed in the AD as of March 1, 2007. On April 1, 2005 (70 FR 9215, February 25, 2005), the Director of the Federal Register approved the incorporation by reference of Saab Service Bulletin 340-24-035, dated July 5, 2004, including Attachment 1 (Goodrich Service Information Letter 23080-03X-24-01), dated July 1, 2004.
2007-02-14: The FAA is adopting a new airworthiness directive (AD) for certain Boeing Model 737-600, -700, -700C, -800, and -900 series airplanes. This AD requires testing the electrical resistance of the bond between the bulkhead fitting for the fuel feed line and the front spar of the left and right wings, inspecting an adjacent bonding jumper to make sure it is installed correctly, and performing corrective and other specified actions as applicable. This AD results from fuel system reviews conducted by the manufacturer. We are issuing this AD to prevent arcing or sparking in the fuel tank in the event of a lightning strike, which could result in an uncontrolled fire or explosion.
2018-23-10: We are adopting a new airworthiness directive (AD) for certain Airbus SAS Model A350-941 airplanes. This AD was prompted by leakage of shrouded pipe T-boxes in the potable water system. This AD requires replacement of the affected potable water T-boxes and clamps with new parts. We are issuing this AD to address the unsafe condition on these products.
2000-16-15: This amendment adopts a new airworthiness directive (AD), applicable to certain Saab Model SAAB 340B series airplanes. This action requires adjustment of the cargo baggage net, replacement of baggage net placards with new placards, and installation of certain new baggage net placards. This action is necessary to prevent failure of the cargo bulkhead floor attachments, which could result in damage to the airplane structure and possible injury to passengers and crewmembers. This action is intended to address the identified unsafe condition.
81-09-09: 81-09-09 STEWART-WARNER (SOUTH WIND DIVISION): Amendment 39-4102. Applies to Model Series 8240, 8253, 8259, and 8472 marked as meeting the standards of FAA TSO-C20, installed in aircraft certificated in all categories. Compliance required as indicated. To prevent a hazardous condition caused by deterioration of the combustion heater, accomplish the following: A. For combustion heaters having 250 hours or more time in service after the effective date of this AD, conduct the 250 hour inspection in accordance with the manufacturer's service manual (see Note 2) within the next 50 hours of combustion heater operation, unless already accomplished within the last 200 hours of heater time, and thereafter at intervals not to exceed 250 hours of combustion heater operation. Also, along with the above inspection, a general inspection of the combustion heater installation must also be accomplished including at least the following: 1. Inspect ventilating air and combustion airinlets and exhaust outlet correcting restrictions and insuring attachment security. 2. Inspect drain line and insure it is free of obstruction. 3. Check all fuel lines for security at joints and shrouds, correcting those showing evidence of looseness or leakage. 4. Check all electrical wiring for security at attachment points, correcting conditions leading to arcing, chafing or looseness. B. For combustion heaters having 1000 hours or more time in service after the effective date of this AD, overhaul the combustion heater in accordance with the manufacturer's service manual (See Note 2) within the next 50 hours of combustion heater operation, unless already accomplished within the last 950 hours of heater time, and thereafter at intervals not to exceed 1000 hours of combustion heater operation. An overhaul consists of complete disassembly, cleaning, repair, reassembly and test as outlined in the appropriate service manual. Note 1 - In complying with this AD, if the owner or operator cannot document combustion heater operative time, the aircraft time must be used. Note 2 - The following is a list of combustion heaters covered by this AD and the appropriate service manual. Methods of inspection or overhaul other than those contained in the manufacturer's service manuals must be approved by the Chief, Engineering and Manufacturing Branch, FAA Great Lakes Region. Models Service Manual Number 8240 Series 09-998 or P.M. 35710 8259 Series (Appropriate usage is shown in Manual or Manual Supplements) 8253 Series P.M. 20688 8472 Series 09-1015 This amendment becomes effective May 8, 1981.
2007-02-02: This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model DC-8 airplanes. This AD requires a one-time inspection for previous repairs of the aft fuselage skin panel at the longeron 28 skin splice; repetitive inspections for cracks of the same area; and related investigative and corrective actions. This AD also provides optional actions for extending the repetitive inspection intervals. The actions specified by this AD are intended to detect and correct cracks in the aft fuselage skin at the longeron 28 skin splice, which could lead to loss of structural integrity of the aft fuselage, resulting in rapid decompression of the airplane. This action is intended to address the identified unsafe condition.
2021-16-17: The FAA is adopting a new airworthiness directive (AD) for Airbus Helicopters Deutschland GmbH (AHD) Model MBB-BK 117 D-2 helicopters. This AD was prompted by the discovery that certain parts that are approved for installation on multiple helicopter models are life limited parts when installed on Model MBB-BK 117 D-2 helicopters and some helicopter delivery documents excluded the life limit information. This AD requires determining the total hours time-in- service (TIS) of a certain part-numbered rotor mast nut and re- identifying a certain part-numbered rotor mast nut. This AD also requires establishing a life limit for a certain part-numbered rotor mast nut and helical gear support, and removing each part from service before reaching its life limit. Additionally, this AD requires replacing a certain part-numbered main gearbox (MGB) with a not affected MGB as specified in a European Aviation Safety Agency (now European Union Aviation Safety Agency) (EASA) AD, which is incorporated by reference (IBR). The FAA is issuing this AD to address the unsafe condition on these products.
2018-23-07: We are adopting a new airworthiness directive (AD) for certain Airbus SAS Model A350-941 airplanes. This AD was prompted by a review of the Airbus A350 structure design principles database for type definition that revealed that the balancer fitting part, installed on the tail cone, on a certain frame (FR) has several corrosion-resistant stainless steel nuts that do not meet the requirements for protection against corrosion. This AD requires application of a new additional overcoat sealant and elastic varnish on the affected nuts and fasteners. We are issuing this AD to address the unsafe condition on these products.
93-14-21: 93-14-21 BOEING: Amendment 39-8646. Docket 93-NM-109-AD. \n\n\tApplicability: All Model 747-400 series airplanes, certificated in any category. \n\n\tCompliance: Required as indicated, unless accomplished previously. \n\n\tTo reduce the effect on airplane systems should they enter ground operating mode while the airplane is in flight due to depressurization of hydraulic system number one or four, accomplish the following: \n\n\t(a)\tWithin 15 days after the effective date of this AD, revise the Limitations Section of the FAA-approved Airplane Flight Manual (AFM) by accomplishing paragraphs (a)(1) and (a)(2) of this AD. \n\n\t\t(1)\tInsert a copy of 747-400 Operations Manual Bulletin 93-5, dated July 26, 1993, into the AFM. \n\n\t\t(2)\tInclude the requirements of paragraphs (a)(2)(i), (a)(2)(ii), and (a)(2)(iii) of this AD in the AFM. This may be accomplished by inserting a copy of this AD in the AFM. \n\n\t\t\t(i)\tDo not operate the airplane unless both the number 4 hydraulic engine drivenpump and the number 4 hydraulic demand pump are operative. \n\n\t\t\t(ii)\tIf hydraulic system number 1 or 4 becomes inoperative while the airplane is in flight, the flight crew shall accomplish the procedures contained in 747-400 Operations Manual Bulletin 93-5, dated July 26, 1993. \n\n\t\t\t(iii)\tIf hydraulic system number 4 becomes inoperative while the airplane is in flight, the flight crew shall consider the ramifications of changes in system operation should the airplane enter the "ground mode." Specifically, consideration shall be given to trip and reserve fuel requirements, and enroute and destination forecasts for potential icing conditions. If these or other conditions present a significant adverse effect on safety if the flight is continued, the crew shall consider, as an alternative, diverting to a suitable airport. It is the responsibility of the captain to assess the situation and execute sound judgement to determine a safe course of action. A landing shall be made at the most suitable airport. \n\n\t(b)\tWithin 60 days after the effective date of this AD, install a system that provides full pitot and total air temperature heat in the event an airplane enters "ground mode" while the airplane is in flight, in accordance with Boeing Alert Service Bulletin 747-30A2069, dated July 15, 1993. \n\n\t(c)\tAn 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, Seattle Aircraft Certification Office (ACO), FAA, Transport Airplane Directorate. Operators shall submit their requests through an appropriate FAA Principal Maintenance Inspector, who may add comments and then send it to the Manager, Seattle ACO. \n\n\tNOTE: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Seattle ACO. \n\n\t(d)\tSpecial flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate the airplane toa location where the requirements of this AD can be accomplished. \n\n\t(e)\tThe AFM revision shall be accomplished in accordance with 747-400 Operations Manual Bulletin 93-5, dated July 26, 1993. The installation shall be done in accordance with Boeing Alert Service Bulletin 747-30A2069, dated July 15, 1993. 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 Boeing Commercial Airplane Group, P.O. Box 3707, Seattle, Washington 98124-2207. 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. \n\n\t(f)\tThis amendment becomes effective on August 9, 1993.
2004-07-10: This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 737-600, -700, -700C, -800, and -900 series airplanes, that requires replacement of the proximity switch electronics unit with a new, improved unit. This action is necessary to prevent a malfunction of the aural warning for the landing gear, leading the crew to open the circuit breaker for the aural warning horn which stops the operation of other aural warnings of malfunctions in other systems and, thus, could jeopardize a safe flight and landing. This action is intended to address the identified unsafe condition.