Results
98-21-37: This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model DC-10-10, -15, -30, and -40 series airplanes, that requires installation of a new protector cap in all fuel tank boost/transfer pump housings. This amendment is prompted by reports of inoperative fuel boost/transfer pumps due to arcing or burning of the electrical connectors. The actions specified by this AD are intended to prevent damage to the fuel tank boost/transfer pump housings in case of an electrical connector malfunction, which could result in increased risk of a fuel tank explosion or fire.
2013-08-09: We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 777-200, -200LR, -300, -300ER, and 777F series airplanes. This AD was prompted by a report that during a test of the oxygen system, an operator found that the passenger oxygen masks did not properly flow oxygen, and that a loud noise occurred in the overhead area, which was caused by the flex line separating from the hard line due to a missing clamshell coupler. This AD requires, for certain airplanes, performing a detailed inspection of certain areas of the airplane oxygen system to ensure clamshell couplers are installed and fully latched, and corrective actions if necessary. For all airplanes, this AD requires performing and meeting the requirements of the low pressure leak test. We are issuing this AD to prevent the oxygen system flex line from separating from the hard line, which could cause an oxygen leak and a drop in the oxygen system pressure, resulting in improper flow of oxygen through the passenger masks and injury to passengers if emergency oxygen is needed.
98-21-33: This amendment adopts a new airworthiness directive (AD), applicable to all Fokker Model F.28 Mark 0070 and 0100 series airplanes, that requires a one-time inspection of the torque links of the main landing gear (MLG) assemblies to determine if the lockwire is present on the apex bolt; and corrective action, if necessary. This amendment is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified by this AD are intended to prevent failure of the MLG due to loose connections between the upper and lower torque links of the MLG.
68-01-02: 68-01-02 VICKERS: Amendment 39-540. Applies to Viscount Models 744, 745D, and 810 Series airplane Compliance required as indicated unless already accomplished. (a) For airplanes with 12,500 or more hours' time in service on the effective date of this AD (1) Comply with paragraph (c) and (d) within the next 250 hours' time in service, and thereafter comply with paragraph (c) at intervals not to exceed 500 hours' time in service from the last inspection performed in accordance with either paragraph (c) or (e); and (2) Comply with paragraph (e) within the next 2,750 hours' time in service, and thereafter at intervals not to exceed 3,000 hours' time in service. (b) For airplanes with less than 12,500 hours' time in service on the effective date of this AD (1) Comply with paragraphs (c) and (d) before the accumulation of 12,750 hours' time in service, and thereafter comply with paragraph (c) at intervals not to exceed 500 hours' time in service from the last inspection performed in accordance with either paragraph (c) or (e); and (2) Comply with paragraph (e) before the accumulation of 15,250 hours' time in service and thereafter at intervals not to exceed 3,000 hours' time in service. (c) Visually inspect the full length of the wear pattern made by the three rollers of the guide assembly at wing station 387 on both the left and right aileron control rod tubes, for surface cracks and holes, in accordance with British Aircraft Corporation (BAC) Preliminary Technical Leaflets (PTLs) No. 266 (700 Series) and No. 129 (810 Series), Issue 1, dated May 30, 1967, or later ARB-approved issue, or an FAA-approved equivalent. (d) Check the roller assembly for correct adjustment between the control rod tube and the third roller, to provide a minimum clearance of .005 inches and a maximum clearance of .010 inches at the least worn part of the wear pattern, in accordance with BAC PTLs No. 266 (700 Series) and No. 129 (810 Series), Issue 1, dated May 30, 1967, or later ARB-approved issue, or an FAA-approved equivalent. (e) Remove the aileron control rod tube located at wing station 387, inspect for cracks using dye penetrant, or an FAA-approved equivalent, and measure the outside diameter across all sections of the wear pattern, in accordance with BAC PTLs No. 266 (700 Series) and No. 129 (810 Series), Issue 1, dated May 30, 1967, or later ARB-approved issue, or an FAA- approved equivalent. (f) If cracks or holes are detected or the tube outside diameter across any section of the wear pattern is less than 1.11 inches in diameter during the inspections required by paragraphs (c) and (e), replace the aileron rod control tube before further flight with a new tube of the same part number. When 12,500 hours' time in service have accumulated on the new replacement tube, begin inspecting the tube in accordance with the inspection requirements of paragraph (a). (g) Upon request of the operator, an FAA maintenance inspector, subject to prior approval of the Chief, Aircraft Certification Staff, FAA, Europe, Africa and Middle East Region, may adjust the repetitive inspection intervals specified in this AD to permit compliance at an established inspection period of the operator if the request contains substantiating data to justify the increase for such operator. This amendment becomes effective February 8, 1968.
2022-10-03: The FAA is adopting a new airworthiness directive (AD) for certain Viking Air Limited (type certificate previously held by Bombardier, Inc. and de Havilland, Inc.) Model DHC-6-1, DHC-6-100, DHC- 6-200, DHC-6-300, and DHC-6-400 airplanes. This AD was prompted by mandatory continuing airworthiness information (MCAI) originated by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI identifies the unsafe condition as loose quadrants on the rudder pedal torque tube and signs of loose rivets or rivet joint wear due to inadequate manufacturing tolerances. This AD requires inspecting the rudder pedal torque tube quadrant for looseness and taking corrective action as necessary. The FAA is issuing this AD to address the unsafe condition on these products.
2013-07-12: We are adopting a new airworthiness directive (AD) for certain BRP-Powertrain GmbH & Co KG Rotax 912 F2; 912 F3; 912 F4; 912 S2; 912 S3; 912 S4; 914 F2; 914 F3; and 914 F4 reciprocating engines. This AD requires a one-time visual inspection for excessive oil deposits or carbon deposits on the No. 2 and No. 3 spark plug center and grounding electrodes, and if found, replacement of the cylinder head before further flight. This AD was prompted by a report of certain No. 2 and No. 3 cylinder heads not manufactured to proper specification. We are issuing this AD to prevent excessive oil consumption, which could result in an in-flight engine shutdown, forced landing, and damage to the airplane.
98-21-24: This amendment adopts a new airworthiness directive (AD), applicable to Pratt & Whitney JT8D series turbofan engines, that requires removal, visual inspection, eddy current inspection, repair or replacement of affected compressor disks. This amendment is prompted by reports of improper fixturing during the electrolytic cleaning process of certain compressor disks at a certified repair station, Avial or Greenwich Air Services, currently GE Engine Services Dallas LP, certificate number RA1R445K of Dallas, Texas, that can result in damage to the disks in the form of arc burns. The actions specified by this AD are intended to prevent compressor disk cracking from arc burns in tie rod holes, shielding holes, or pressure balance holes, which could lead to a fracture of a compressor disk, resulting in uncontained release of engine fragments, inflight engine shutdown, and airframe damage.
98-21-32: This amendment supersedes an existing airworthiness directive (AD), applicable to all Airbus Model A300, A310, and A300-600 series airplanes, that currently requires performing a ram air turbine (RAT) extension test; removing and disassembling the RAT uplock mechanism; performing an inspection to detect corrosion of the RAT uplock mechanism, and replacement with a new assembly, if necessary; and cleaning all the parts of the RAT control shaft and its bearing component parts. This amendment requires modification of the RAT unlocking control unit, which constitutes terminating action for the repetitive tests and inspections. This amendment also limits the applicability of the existing AD. This amendment is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified by this AD are intended to prevent corrosion of the RAT uplock pin/shaft and needle, which could result in failure of the RAT to deployand consequent loss of emergency hydraulic power to the flight controls in the event that power is lost in both engines.
91-19-06: 91-19-06 I.A.M. RINALDO PIAGGIO S.P.A.: Amendment 39-8033. Docket No. 91-CE-68-AD. Applicability: Model Avante P180 airplanes (serial numbers 1004, 1006, 1007, and 1009 through 1015), certificated in any category. Compliance: Required as indicated, unless already accomplished. To prevent movement or separation of the vertical stabilizer caused by failure of the No. 1 spar attachment, which could result in loss of control of the airplane, accomplish the following: (a) Within the next 25 hours time-in-service (TIS) after the effective date of this AD, and thereafter at intervals not to exceed 50 hours TIS until the modification described in paragraphs (a) (2) and (b) of this AD is accomplished, perform an endoscope inspection of the No. 1 spar of the vertical stabilizer attachment for cracks in accordance with the paragraphs (1) through (3) of Part A of 2. ACCOMPLISHMENT INSTRUCTIONS in Piaggio Avante P180 Service Bulletin 80-0008, Revision No. 1, dated June 26,1991. (1) If no cracks are found, prior to further flight, remove the endoscope, install an inspection plastic plug, return the airplane to service, and accomplish the repetitive inspection requirements. NOTE: The modification described in paragraphs (a) (2) and (b) of this AD may be accomplished as terminating action for the inspection requirements of this AD provided that no cracks are found per the inspections required in paragraph (a) of this AD. (2) If cracks are found, prior to further flight, modify the No. 1 spar of the vertical stabilizer spar attachment and install a reinforcement kit in accordance with paragraphs (1) through (15) of Part B of 2. ACCOMPLISHMENT INSTRUCTIONS in Piaggio Avante P180 Service Bulletin 80-0008, Revision No. 1, dated June 26, 1991. (b) Within the next 500 hours TIS after the effective date of this AD, unless already accomplished in accordance with paragraph (a) (2) of this AD, modify the vertical stabilizer spar attachment andinstall a reinforcement kit in accordance with paragraphs (4) through (15) of Part B of 2. ACCOMPLISHMENT INSTRUCTIONS in Piaggio Avante P180 Service Bulletin 80-0008, Revision No. 1, dated June 26, 1991. (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, Brussels Aircraft Certification Office, Europe, Africa, Middle East office, FAA, c/o American Embassy, 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 Office. (e) The inspections and modification required by this AD shall be done in accordance with Piaggio Avante P180 Service Bulletin 80-0008, Revision No. 1, dated June 26, 1991. 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 I.A.M. Rinaldo Piaggio S.p.A., Via Cibrario, 4, 16154 Genoa, Italy. 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 (39-8033, AD 91-19-06) becomes effective on October 10, 1991.
98-21-23: This amendment adopts a new airworthiness directive (AD) that is applicable to CFM International, S.A. (CFMI) CFM56-7B series turbofan engines. This action supersedes telegraphic AD T98-18-51 that currently requires an inspection of electronic engine control (EEC) fault messages on both engines for the presence of any of the hydromechanical unit (HMU) fuel metering valve (FMV) signal faults identified in the All Operators Wire every 20 flight cycles or 3 calendar days, whichever occurs first, and, if necessary, removing the HMU and replacing it with a serviceable HMU. This action also requires installation of improved EEC software that constitutes terminating action to the repetitive fault message inspections. This amendment is prompted by development of improved EEC software that obviates the need for the repetitive fault message inspections. The actions specified by this AD are intended to prevent an uncommanded engine acceleration event, or inflight engine shutdown.