Results
2004-24-04: The FAA is superseding an existing airworthiness directive (AD) for RRC models 250-C30R/3, -C30R/3M, -C47B, and -C47M turboshaft engines. That AD currently requires initial and repetitive electrical signal inspections of the hydromechanical unit (HMU) Power Lever Angle (PLA) potentiometer. This ad continues to require those inspections and adds replacement of the existing HMU with a new design HMU as a mandatory terminating action to the repetitive inspection requirements. This AD results from the manufacturer releasing a redesigned HMU that has a dual-element potentiometer. We are issuing this AD to prevent uncommanded and sudden changes in engine power.
2014-05-03: We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 777 airplanes. This AD was prompted by a report of cracking in the fuselage skin underneath the satellite communication (SATCOM) antenna adapter. This AD requires repetitive inspections of the visible fuselage skin and doubler if installed, for cracking, corrosion, and any indication of contact of a certain fastener to a bonding jumper, and repair if necessary. We are issuing this AD to detect and correct cracking and corrosion in the fuselage skin, which could lead to rapid decompression and \n\n((Page 12376)) \n\nloss of structural integrity of the airplane.
2023-03-16: The FAA is adopting a new airworthiness directive (AD) for certain Embraer S.A. Model ERJ 190-300 airplanes. This AD was prompted by failed lockwires on the attachment of the left-hand main landing gear (MLG) trunnion bearing to spar 2. This AD requires inspecting for damage of the left- and right-hand MLG trunnion bearing attaching parts, replacing damaged parts, and modifying the MLG trunnion bearing attaching parts, as specified in an Ag[ecirc]ncia Nacional de Avia[ccedil][atilde]o Civil (ANAC) AD, which is incorporated by reference. The FAA is issuing this AD to address the unsafe condition on these products.
88-03-09: 88-03-09 MCDONNELL DOUGLAS: Amendment 39-5839. Applies to McDonnell Douglas Model DC-9-81, -82, and -83 series airplanes, as listed in McDonnell Douglas Service Bulletin 34-177, dated April 28, 1987, certificated in any category. Compliance required as indicated, unless previously accomplished. \n\n\tTo prevent erroneous information from being transmitted to the Digital Flight Guidance Computer (DFGC) from the Digital Air Data computer (DADC) in the event of an electrical transient, accomplish the following: \n\n\tA.\tWithin 12 months after the effective date of this airworthiness directive (AD), inspect Honeywell P/N HG280D80 DADC in affected airplanes to determine if Modification 8 has been installed, in accordance with Part 2 of the Accomplishment Instructions of McDonnell Douglas Service Bulletin 34-177, dated April 28, 1987, or later revisions approved by the Manager, Los Angeles Aircraft Certification Office, FAA, Northwest Mountain Region. \n\n\t\t1.\tIf Modification 8 has been installed and identified, no further action is necessary. \n\n\t\t2.\tIf Modification 8 has been installed but not identified, identify the DADC in accordance with the service bulletin. \n\n\t\t3.\tIf Modification 8 has not been installed, modify and identify the DADC in accordance with the service bulletin. \n\n\tB.\tAlternate means of compliance which provide an acceptable level of safety may be used when approved by the Manager, Los Angeles 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 in order to comply with the requirements of this AD. \n\n\tAll persons affected by this directive who have not already received the appropriate service information from the manufacturer may obtain copies upon request to McDonnell Douglas Corporation, 3855 Lakewood Boulevard, Long Beach, California 90846, Attention: Director of Publications, C1-L00 (54-60); or Honeywell, Incorporated, Commercial Aviation Division Technical Services, Mail Station MN23-6345, P.O. Box 889, Minneapolis, Minnesota 55440. These documents may be examined at the FAA, Northwest Mountain Region, 17900 Pacific Highway South, Seattle, Washington, or the Los Angeles Aircraft certification Office, 4344 Donald Douglas Drive, Long Beach, California. \n\n\tThis Amendment becomes effective March 11, 1988.
82-26-06: 82-26-06 DeHAVILLAND: Amendment 39-4517. Applies to Model DHC-6 (serial numbers 1 through 709, 711 through 735, 737 through 753, 755 through 761, 763 through 779, and 791) airplanes which incorporate a windscreen washer/deicing system certificated in any category. COMPLIANCE: Required as indicated unless already accomplished. To prevent leakage of isopropyl alcohol in the crew compartment and a possible crew compartment fire, accomplish the following: (a) Within the next 25 hours time-in-service after the effective date of this AD, and each 200 hours time-in-service thereafter inspect the windscreen washer/deicing system for evidence of leaks in accordance with the Accomplishment Instructions of DeHavilland Service Bulletin S/B No. 6/422, Revision A dated June 18, 1982. (1) Replace any defective components which could cause leaks and ensure that all tubing is secured in accordance with Accomplishment Instructions Step 3 and Step 6. (b) On or before November 30, 1983: (1) Install a permanent placard having letters of 1/8 inch minimum height on or near the washer/deicing fluid tank filler which states "DO NOT USE ISOPROPYL ALCOHOL OR ISOPROPYL ALCOHOL MIXTURES." (2) Install a placard having letters of 1/8 inch minimum height adjacent to the windscreen washer/deicing system switch which states "WASHER ONLY" and operate the airplane in accordance with these placard limitations. (3) On airplanes certificated for flight into icing conditions, install an electrically heated windscreen in accordance with DeHavilland Modification S.0.0. 6007, Issue 7 dated May 17, 1982. (c) The inspections per paragraph (a) of this AD need not be accomplished when the placards required by paragraph (b) are installed. (d) The airplane may be flown in accordance with Federal Aviation Regulation 21.197 to a location where this AD can be accomplished. (e) An equivalent method of compliance with this AD may be used if approved by the Manager, New York Aircraft Certification Office, ANE-170, Federal Aviation Administration, 181 South Franklin Avenue, Room 202, Valley Stream, New York 11581, telephone: (516) 791-6680. This amendment becomes effective on December 27, 1982.
2023-03-22: The FAA is superseding Airworthiness Directive (AD) 2015-09-04 R1, which applied to DG Flugzeugbau GmbH Model DG-1000T gliders equipped with a Solo Kleinmotoren GmbH (currently Solo Vertriebs-und Entwicklungs-GmbH) (Solo) Model 2350 C engine. AD 2015-09-04 R1 prohibited operation of the engine and required performing a magnetic particle or dye penetrant inspection of the propeller shaft and reporting the results of the inspection to Solo. This AD is 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 occurrences of rupture of the eccentric axle on Solo Model 2350 C engines (installed on DG Flugzeugbau GmbH Model DG-1000T gliders in the United States) and an occurrence on a Solo Model 2350 D engine (installed on Schempp-Hirth Flugzeugbau GmbH (Schempp-Hirth) Model Duo Discus T gliders in the United States). This AD requires repetitive replacement of the eccentric axle, adds the Schempp-Hirth Model Duo Discus T gliders to the applicability, and retains from AD 2015-09-04 R1 the option of operating the glider with the engine non-operative instead of replacing the eccentric axle. The FAA is issuing this AD to address the unsafe condition on these products.
2004-23-18: The FAA is adopting a new airworthiness directive (AD) for certain Airbus Model A319, A320, and A321 series airplanes. This AD requires revising the airplane flight manual (AFM) to prohibit operators from performing CAT 2 or CAT 3 automatic landings or roll- outs at certain airports. This AD also provides for an optional terminating action for the AFM revision. This AD is prompted by data showing that the magnetic variation table installed in the Honeywell inertial reference system (IRS) is obsolete at certain airports. We are issuing this AD to prevent the airplane from departing the runway during a CAT 2 or CAT 3 automatic landing or roll-out, due to magnetic and IRS deviations.
2004-23-19: This amendment supersedes an existing airworthiness directive (AD), applicable to certain EMBRAER Model EMB-135 and -45 series airplanes. The existing AD currently requires a one-time inspection to detect incorrect wiring of the electrical connectors to the pressure switches and cartridges on the fire extinguisher bottles for the engines and the auxiliary power unit (APU); disconnection and reconnection of the wiring, as necessary; and adjustment of the length of the harnesses on the fire extinguisher bottles to avoid future misconnections. This amendment requires additional adjustment of the length of the harnesses; installation of a color-coded identification system to avoid misconnections during maintenance; and a functional test of the engine fire extinguisher system. This amendment also expands the applicability of the existing AD to include additional airplanes. The actions specified by this AD are intended to prevent the issuance of erroneous commands or the receipt oferroneous information pertaining to the fire extinguisher system for the engines and the APU, which could result in the inability to put out a fire in an engine or in the APU. This action is intended to address the identified unsafe condition.
2023-02-16: The FAA is adopting a new airworthiness directive (AD) for certain BAE Systems (Operations) Limited Model Avro 146-RJ series airplanes. This AD was prompted by a report that certain inertial reference units (IRUs) have out-of-date magnetic variation (MagVar) tables. This AD requires assessing the values between the MagVar tables of the affected IRUs and the most recently published MagVar data tables, and corrective actions if necessary. The FAA is issuing this AD to address the unsafe condition on these products.
86-05-11 R1: 86-05-11 R1 BOEING: Amendment 39-5255 as amended by Amendment 39-5335. Applies to all Model 747 series airplanes, certificated in any category, listed in Boeing Alert Service Bulletin 747-57A2233, Revision 2, dated May 9, 1986. \n\n\tTo detect faulty self-locking nuts that could lead to separation of an engine, accomplish the following, unless already accomplished: \n\n\tA.\tWithin 100 landings after the effective date of this AD, perform a one-time inspection of the outboard attach fitting nuts of all nacelle struts for adequate self-locking torque of the nuts, part number BACN10HR162, in accordance with Boeing Alert Service Bulletin 747- 57A2233, Revision 2, dated May 9, 1986, or later FAA-approved revisions. \n\n\tB.\tWithin 600 landings after the effective date of this AD, perform a one-time inspection of the inboard attach fitting nuts of all nacelle struts for adequate self-locking torque of the nuts, part number BACN10HR162, in accordance with Boeing Alert Service Bulletin 747-57A2233, Revision 2, dated May 9, 1986, or later FAA-approved revisions. \n\n\tC.\tDefective nuts must be replaced prior to further flight. \n\n\tD.\tUpon the request of an operator, an FAA Principal Maintenance Inspector, subject to prior approval of the Manager, Seattle Aircraft Certification Office, FAA, Northwest Mountain Region, may adjust the inspection time in this AD to permit compliance at an established inspection period of that operator, if the request contains substantiating data to justify the change for that operator. \n\n\tE.\tAlternate means of compliance 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\tF.\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 proposal who have not already receivedinformation on inspection procedures from the manufacturer may obtain copies upon request to the Boeing Commercial Airplane Company, P.O. Box 3707, Seattle, Washington 98124-2207. This information 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. \n\n\tAmendment 39-5255 became effective March 31, 1986. \n\tThis Amendment 39-5335 becomes effective July 7, 1986.