Results
2006-23-04: We are adopting a new airworthiness directive (AD) for the products listed above. This AD results from mandatory continuing airworthiness information (MCAI) issued by the aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as during production installation of the Garmin G1000 supplemental type certificate (STC) some parts of the installed fuel system indicating system were contaminated with particles from the manufacturing process. This AD requires actions that are intended to address the unsafe condition described in the MCAI. DATES: This AD becomes effective November 28, 2006. The Director of the Federal Register approved the incorporation by reference of Diamond Aircraft Industries GmbH Mandatory Service Bulletin No. MSB-40-048/2, Revision 2, dated September 26, 2006; and Work Instruction WI-MSB-40.048/2, Revision 2, dated September 26, 2006, listed in this AD as of November 28, 2006. We must receive comments on this AD by December 8, 2006.
2006-23-06: The FAA is adopting a new airworthiness directive (AD) for certain Airbus Model A300 airplanes. This AD requires modifying the airplane and the engine/nacelle to install a third line of defense against inadvertent deployment of the thrust reverser in flight. This AD also requires two other actions that must be accomplished before or concurrently with the modification: installing a structural change in the fan cowl to avoid interference; and installing a dedicated, shielded electrical circuit. This AD results from a report that the manufacturer has developed a third line of defense against the inadvertent deployment of the thrust reverser of Model A300 airplanes that are equipped with General Electric CF6-50 series engines (in accordance with FAA guidelines). We are issuing this AD to prevent inadvertent deployment of the thrust reverser in flight, which could result in reduced controllability of the airplane.
86-17-04: 86-17-04 BOEING: Amendment 39-5369. Applies to all Model 757-200 series airplanes listed in Boeing Service Letter 757-SL-27-24-B, dated June 2, 1986, certificated in any category. \n\n\tTo detect nuts that have insufficient self-locking torque characteristics, installed on the nose gear door actuator attachment, main landing gear jury brace support attachment, main landing gear forward trunnion drag fitting aft attachment, and the P&W 2037 engine front evener bar attachment, accomplish the following, unless already accomplished: \n\n\tA.\tWithin the next 90 days after the effective date of this AD, check the Category II self-locking nuts, P/N BACN10JC12CM or BACN10JC12CD, except the rudder pedal adjustment cable retainer self-locking nut, for proper self-locking torque in accordance with Paragraph II of Boeing Service Letter 757-SL-27-24-B, dated June 2, 1986, or later FAA- approved revision. If any self-locking nut is found not to meet the self-locking torque criteria of Boeing Service Letter 757-SL-27-24-B, dated June 2, 1986, or later FAA-approved revision, it must be replaced prior to further flight with a nut which meets the self-locking torque criteria. \n\n\tB.\tAn alternate means of compliance or adjustment of the compliance time, which provide an acceptable level of safety, may be used when approved by the Manager, Seattle Aircraft Certification Office, FAA, Northwest Mountain Region. \n\n\tC.\tSpecial flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes to a base for the accomplishment of inspections and/or modifications required by this AD. \n\n\tAll persons affected by this directive who have not already received the appropriate service document from the manufacturer may obtain copies upon request to Boeing Commercial Airplane Company, P.O. Box 3707, Seattle, Washington 98124. This document may be examined at the FAA, Northwest Mountain Region, 17900 Pacific Highway South, Seattle, Washington, or the Seattle AircraftCertification Office, 9010 East Marginal Way South, Seattle, Washington. \n\n\tThis amendment becomes effective September 5, 1986.
2018-19-23: We are superseding Airworthiness Directive (AD) 2013-01-02, which applied to certain The Boeing Company Model 747-100, 747-100B, 747-100B SUD, 747-200B, 747-200C, 747-200F, 747-300, 747-400, 747-400D, 747-400F, 747SR, and 747SP series airplanes; and Model 757-200, 757- 200PF, and 757-300 series airplanes. AD 2013-01-02 required replacing the control switches of certain cargo doors. This AD requires replacement of certain cargo door control switches with a new, improved switch; installation of an arm switch in certain cargo doors; operational and functional tests; and applicable on-condition actions. This AD also adds airplanes to the applicability. This AD was prompted by reports of uncommanded cargo door operation. We are issuing this AD to address the unsafe condition on these products.
87-20-01: 87-20-01 AEROSPATIALE: Amendment 39-5727. Applies to Model SN601 Corvette airplanes, certificated in any category, except those airplanes on which Modification No. 1390 (Service Bulletin 73-1, replacement of fuel anti-ice additive system by a fuel heating system), has been accomplished. Compliance is required as indicated, unless previously accomplished. To prevent loss of power due to ice clogging of low pressure fuel filters, accomplish the following: A. Within six months after the effective date of this AD, replace the low pressure fuel filters (P/N 433-E25-2) with modified filters (P/N 433-E25-21), in accordance with Aerospatiale Service Bulletin No. 28-10, dated April 25, 1986. 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, Northwest Mountain Region. C. Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes to a base for the accomplishment of the modifications required by this AD. All persons affected by this directive who have not already received the appropriate service document from the manufacturer may obtain copies upon request to Aerospatiale, 316 Route de Bayonne, 31060 Toulouse Cedex 03, France. This document may be examined at the FAA, Northwest Mountain Region, 17900 Pacific Highway South, Seattle, Washington, or the Seattle Aircraft Certification Office, 9010 East Marginal Way South, Seattle, Washington. This amendment becomes effective October 19, 1987.
2006-23-07: The FAA is adopting a new airworthiness directive (AD) for Rolls-Royce plc Trent 768-60, Trent 772-60, and Trent 772B-60 turbofan engines. This AD requires removing from service certain sets of fan blade annulus fillers at a new life limit. This AD results from six reports of fan annulus filler release into the engine. We are issuing this AD to prevent a dual-engine shutdown on twin-engine airplanes.
2006-22-05: The FAA is superseding an existing airworthiness directive (AD), which applies to various aircraft equipped with certain Honeywell Primus II RNZ-850( )/-851( ) integrated navigation units (INUs). That AD, as one alternative for compliance, provides for a one-time inspection to determine whether a certain modification has been installed on the Honeywell Primus II NV-850 navigation receiver module (NRM), which is part of the INU. In lieu of accomplishing this inspection, and for aircraft found to have an affected NRM, the existing AD provides for revising the aircraft flight manual to include new limitations for instrument landing system approaches. This new AD requires inspecting to determine whether certain modifications have been done on the NRM; and doing related investigative, corrective, and other specified actions, as applicable; as well as further modifications to address additional anomalies. This AD results from reports indicating that erroneous glideslope indicationshave occurred on certain aircraft equipped with the subject INUs. We are issuing this AD to ensure that the flightcrew has an accurate glideslope deviation indication. An erroneous glideslope deviation indication could lead to the aircraft making an approach off the glideslope, which could result in impact with an obstacle or terrain.
85-26-03: 85-26-03 SCOTT AVIATION: Amendment 39-5182. Applies to Scott Aviation oxygen connectors, Part Numbers 289-56 and 289-56-1. NOTE: The constant-flow oxygen masks to which the above connectors might be fitted include, but are not necessarily limited to, the following Scott Part Numbers: 289-127 289-127-2 289-127-4 289-128 289-128-2 289-360 289-395 289-701-23 289-701-24 289-701-223 289-601-6 289-601-13 289-601-17 289-601-206 289-601-213 289-601-217. Compliance is required within thirty (30) days after the effective date of this AD, unless previously accomplished. To prevent the blockage of oxygen flow due to incompletely drilled oxygen connectors, accomplish the following: A. Inspect the oxygen mask connectors in accordance with Scott Aviation Service Bulletin 289-35-10 dated May 27, 1985. Improperly drilled connectors must be replaced prior to return to service. B. Alternate means of compliance which provide an acceptable level ofsafety may be used when approved by the Manager, Western Aircraft Certification Office, FAA, Northwest Mountain Region. All persons affected by this directive who have not already received these documents from the manufacturer may obtain copies upon request to Scott Aviation, 123 East Montecito Avenue, Sierra Madre, California 91024. These documents may be examined at the FAA, Northwest Mountain Region, 17900 Pacific Highway South, C-68966, Seattle, Washington, or at the Western Aircraft Certification Office, 15000 Aviation Boulevard, Hawthorne, California. This amendment becomes effective on December 30, 1985.
2018-19-24: We are adopting a new airworthiness directive (AD) for all BAE Systems (Operations) Limited Model 4101 airplanes. This AD was prompted by a determination that inspection requirements for a number of maintenance tasks are incorrect. This AD requires a one-time detailed inspection of a certain fuselage frame and repair, if necessary, and a revision of the maintenance or inspection program, as applicable, to incorporate new or revised maintenance instructions and airworthiness limitations. We are issuing this AD to address the unsafe condition on these products.
86-24-08: 86-24-08 BRITISH AEROSPACE (BAe): Amendment 39-5476. Applies to Model 3101 Jetstream (Serial Numbers 601, 603, 604, 606 to 610, 614, 620, 622, 624 to 626, 628 to 632, 634 to 636, and 638 to 653 inclusive) airplanes 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 ensure that adequate lighting supply to the standby artificial horizon and altitude alert controller indicator (if fitted) is maintained during loss of the main busbar supply, accomplish the following: (a) Incorporate British Aerospace (BAe) modification JM7490 in accordance with the "Accomplishment Instructions" contained in BAe Alert Service Bulletin No. 24-A-JM7490 dated October 30, 1985, Revision No. 1 dated July 22, 1986, by changing the electrical supply source for the right upper center panel instrument lighting converter unit (1LH9) from the 28V d.c. main busbar to the 28V d.c. essential busbar. (b) Aircraft may be flown in accordance with Federal Aviation Regulations 21.197 to a location where this AD can be accomplished. (c) An equivalent means of compliance with this AD may be used if approved by the Manager, Aircraft Certification Staff, AEU-100, Europe, Africa and Middle East Office, FAA c/o American Embassy, 1000 Brussels, Belgium. All persons affected by this directive may obtain copies of the document referred to herein upon request to British Aerospace, Engineering Department, Post Office Box 17414, Dulles International Airport, Washington, D.C. 20041; Telephone (703) 435-9100; or FAA, Office of the Regional Counsel, Room 1558, 601 East 12th Street, Kansas City, Missouri 64106. This amendment becomes effective on January 7, 1987.