Results
58-07-06: 58-07-06 VICKERS: Applies to All Viscount 700 Series Aircraft Fitted With Heavy- Duty Wing Root Terminals and Aluminum Cables, Incorporating Modification D.1255. Compliance required as indicated. Cases have occurred of heavy-duty wing root terminals with their associated aluminum cables overheating as a result of poor electrical contact between the aluminum cable lug and the wing root terminal assembly. The poor electrical contact is attributed to the relaxation of the connection and the spreading and indentation of the aluminum cable lug by repetitive torque loading. To prevent the possibility of damage to the cable lug, a special washer, 80236 Part 3043, has been introduced by Mod. D.2628 to replace the existing washer 72436 Part 2069. The new washer is of increased thickness with an electro-tinned finish and has an outside diameter equal to the width of the cable lug. Vickers-Armstrong has issued the following corrective measures which the British Air registration Board considers mandatory. The FAA concurs and considers compliance therewith mandatory. Inspect all wing root connections for signs of looseness and overheated condition within the next 135 flying hours and take the following action: 1. Where signs of overheat are apparent the wing root terminal and cable lug assembly should be dismantled, and the overheated cable and components renewed. 2. Where loose connections are found these should be retightened after first inspecting the cable lug to ensure that the faces of the lug are clean, flat and free from signs of burning. 3. If signs of burning or damage are found on either face of the lug when complying with the recommendations in paragraphs 1 and 2, the lug and its associated cable should be replaced. 4. Where no signs of overheated or loose connections are found, existing terminal connections may be considered serviceable. All wing root connections should, however, be further inspected within every subsequent 135 flying hours until the new washer 80236 Part 3043 is fitted in place of washer 72436 Part 2069. 5. All wing root connections must have washer 80236 Part 3043 installed within 800 flying hours. (Vickers-Armstrong PTL No. 186, Issue 1, dated February 11, 1958, and Modification Bulletin No. D.2628 covers the same subject.)
2018-19-15: We are adopting a new airworthiness directive (AD) for certain GEVEN S.p.A. (Geven) Type D1-02 and D1-03 seat assemblies. This AD was prompted by a report that seat belt attachment bolts were found detached or partially detached from the seat. This AD requires inspection, torque verification, and modification of certain model seats. We are issuing this AD to address the unsafe condition on these products.
2018-19-27: We are adopting a new airworthiness directive (AD) for certain Dassault Aviation Model FALCON 2000EX airplanes. This AD was \n\n((Page 50480)) \n\nprompted by the manufacturer revising the airplane maintenance manual (AMM) maintenance requirements and airworthiness limitations. This AD requires revising the maintenance or inspection program, as applicable, to incorporate new maintenance requirements and airworthiness limitations. We are issuing this AD to address the unsafe condition on these products.
2006-23-03: The FAA adopts a new airworthiness directive (AD) for all B-N Group Ltd. BN-2, BN-2A, BN-2B, BN-2T, and BN-2T-4R series (all individual models included in Type Certificate Data Sheet (TCDS) A17EU, Revision 16, dated December 9, 2002) airplanes. This AD requires you to inspect the horizontal stabilizer attachment bolts and anchor nuts for damage and wear and replace damaged and/or worn parts with new, modified parts. If no damaged or worn parts are found during the inspection, this AD requires you to replace the horizontal stabilizer attachment bolts and anchor nuts at a specified time with new, modified parts. This AD results from mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for the United Kingdom. We are issuing this AD to detect and correct damaged and/or worn horizontal stabilizer attachment bolts and anchor nuts, which could result in failure of the horizontal stabilizer. This failure could result in loss of control.
2006-23-01: The FAA adopts a new airworthiness directive (AD) for certain Pilatus Aircraft Ltd. (Pilatus) Model PC-7 airplanes. This AD requires you to do repetitive eddy-current, non-destructive inspections of the nose skin and adjacent structure above the left and right main landing gear bay and repetitive visual inspections of the forward support structure of the floor panel for crack damage. If you find any crack damage, this AD requires you to contact Pilatus to obtain a repair solution and incorporate the repair. This AD results from mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for Switzerland. We are issuing this AD to detect and correct cracks in the nose skin and adjacent structure above the left and right main landing gear bay and in the forward support structure of the floor panel. Crack propagation in certain areas could lead to failure of the main wing torsion box, which could result in loss of control.
2018-19-07: We are adopting a new airworthiness directive (AD) for all Airbus SAS Model A300 series airplanes; Model A300 B4-600, B4-600R, and F4-600R series airplanes, and Model A300 C4-605R Variant F airplanes (collectively called Model A300-600 series airplanes); and Model A310 series airplanes. This AD was prompted by a report of yellow hydraulic system failure, including both braking accumulators, due to failure of the parking brake operated valve (PBOV). This AD requires replacement of a certain PBOV with a different PBOV. We are issuing this AD to address the unsafe condition on these products.
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.
2021-11-13: The FAA is adopting a new airworthiness directive (AD) for Bell Textron Canada Limited (Bell) Model 429 helicopters. This AD requires inspecting certain serial-numbered Emergency Flotation System (EFS) inflation hoses and depending on the results of those inspections, marking certain parts or removing certain parts from service. This AD was prompted by a report that a float compartment on an EFS did not inflate. The FAA is issuing this AD to address the unsafe condition on these products.
2006-22-08: The FAA adopts a new airworthiness directive (AD) for all Air Tractor, Inc. Models AT-602, AT-802, and AT-802A airplanes. This AD requires you to repetitively inspect the engine mount for any cracks, repair or replace any cracked engine mount, and report any cracks found to the FAA. This AD results from reports of cracked engine mounts. We are issuing this AD to detect and correct cracks in the engine mount, which could result in failure of the engine mount. Such failure could lead to separation of the engine from the airplane.
2021-12-15: The FAA is adopting a new airworthiness directive (AD) for all Airbus SAS Model A330-243, A330-243F, A330-341, A330-342, and A330-343 airplanes. This AD was prompted by a report of an in-flight turnback due to loss of green and blue hydraulic systems in cruise. This AD requires inspecting for discrepancies of the hydraulic pressure switch harnesses of affected engines, and applicable corrective actions, 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.
2018-20-06: We are superseding Airworthiness Directive (AD) 2016-25-03, which applied to certain Airbus Model A300 F4-600R series airplanes. AD 2016-25-03 required repetitive high frequency eddy current (HFEC) inspections of the aft lower deck cargo door (LDCD) frame forks; a one- time check of the LDCD clearances; and a one-time detailed visual inspection of hooks, eccentric bushes, and x-stops; and corrective actions if necessary. This AD requires repetitive HFEC inspections of the aft LDCD frame forks; a one-time check of the LDCD clearances; and a one-time detailed visual inspection of hooks, eccentric bushes, and x-stops; and corrective actions if necessary. This AD was prompted by a report of two adjacent frame forks that were found cracked on the aft LDCD of two airplanes during scheduled maintenance, and the introduction of frame fork reinforcement or repair procedures that, when done, allow an extension of repetitive inspection intervals. We are issuing this AD to address the unsafe condition on these products.
2006-22-07: The FAA is adopting a new airworthiness directive (AD) for all Airbus Model A300 and A310 airplanes and A300-600 series airplanes. This AD requires inspecting for discrepancies of all electrical bundles located in the leading and trailing edges of the wings, and performing corrective actions if necessary. This AD results from fuel system reviews conducted by the manufacturer. We are issuing this AD to prevent an ignition source, which, in combination with flammable fuel vapors, could result in a fuel tank explosion and consequent loss of the airplane.
2021-11-01: The FAA is superseding Airworthiness Directive (AD) 2013-20-13 for certain Bell Helicopter Textron Canada Limited (now Bell Textron Canada Limited) (Bell) Model 206B and 206L helicopters. AD 2013-20-13 required installing a placard beneath the engine power dual tachometer and revising the Operating Limitations section of the existing Rotorcraft Flight Manual (RFM) for your helicopter. This AD was prompted by the engine manufacturer expanding the RPM (N2) steady-state operation avoidance range limits. This AD retains certain requirements of AD 2013-20-13, and requires revising certain sections of the existing RFM for your helicopter and installing or replacing a placard. The FAA is issuing this AD to address the unsafe condition on these products.
2021-12-10: The FAA is adopting a new airworthiness directive (AD) for Leonardo S.p.a. Model AB139 and AW139 helicopters with 3-stretcher kit part number 139084-501 installed. This AD was prompted by a report of a design deficiency which affects the primary stretcher unit of the 3- stretcher kit. This AD requires installing a placard on the primary stretcher. The FAA is issuing this AD to address the unsafe condition on these products.
2018-19-29: We are adopting a new airworthiness directive (AD) for all Airbus SAS Model A330-200 Freighter, -200, and -300 series airplanes; and Airbus SAS Model A340-200, -300, -500, and -600 series airplanes. This AD was prompted by a report of deficient fatigue performance of high strength steel used in forgings. Components made from the affected high strength steel are installed on the main landing gear (MLG), nose landing gear (NLG), and center landing gear (CLG). This AD requires identifying the part number and serial number of certain components installed on the MLG, NLG, and CLG; replacing affected parts; identifying the airplane's weight variant; and determining the applicable life limit for certain components installed on the MLG, NLG, and CLG. We are issuing this AD to address the unsafe condition on these products.
85-23-05: 85-23-05 BELL HELICOPTER TEXTRON, INC.: Letter issued November 8, 1985. Applies to all Bell Helicopter Model 214B and 214ST series helicopters certified in all categories that have collective sleeve part number 214-010-411-001 or -003 with serial number Al9-00001 through Al9-00738 or serial number A-1 through A-10 installed. Compliance is required before further flight after receipt of this AD, unless previously accomplished, and thereafter at 250 hour intervals. To prevent failure of the collective sleeve, accomplish the following: a. Before further flight after receipt of this priority letter AD, perform a magnetic particle inspection of the affected sleeves using the procedures described in Bell Alert Service Bulletin 214-84-26, dated March 12, 1984, or 214ST-84-17, dated March 12, 1984, as appropriate. NOTE: It is essential that the paint and primer be removed as described in the service bulletins prior to performing the magnetic particle inspection.b. Repeat the magnetic particle inspection every 250 hours time in service. c. If cracks are found, replace with serviceable parts. d. An alternative means of compliance or adjustment of the compliance time, which provides an equivalent level of safety, must be approved by the Manager, Helicopter Certification Branch, Aircraft Certification Division, FAA, Southwest Region. This airworthiness directive is effective upon receipt.