Results
2022-13-10: The FAA is adopting a new airworthiness directive (AD) for certain The Boeing Company Model 767-200, -300, -300F, and -400ER series airplanes. This AD was prompted by reports of burned Boeing Material Specification (BMS) 8-39 urethane foam, which is a material with fire-retardant properties that deteriorate with age. This AD requires replacing certain BMS 8-39 foam pads with Nomex felt in certain areas, removing certain BMS 8-39 foam pads in a certain area (which includes a general visual inspection to find BMS 8-39 foam pads), and inspecting the corner seals to determine if the corner seals were replaced, and replacing affected corner seals. This AD also prohibits the installation of BMS 8-39 urethane foam seal in certain locations. The FAA is issuing this AD to address the unsafe condition on these products.
96-07-14: 96-07-14 CONSTRUCCIONES AERONAUTICAS, S.A. (CASA): Amendment 39-9564. Docket 92-NM-75-AD. Applicability: All Model C-212-CB, -CC, -CD, -CE, and -CF series airplanes, certificated in any category. NOTE 1: This AD applies to each airplane identified in the preceding applicability provision, regardless of whether it has been otherwise modified, altered, or repaired in the area subject to the requirements of this AD. For airplanes that have been modified, altered, or repaired so that the performance of the requirements of this AD is affected, the owner/operator must request approval for an alternative method of compliance in accordance with paragraph (e) of this AD. The request should include an assessment of the effect of the modification, alteration, or repair on the unsafe condition addressed by this AD; and, if the unsafe condition has not been eliminated, the request should include specific proposed actions to address it. Compliance: Required as indicated, unless accomplished previously. To prevent reduced structural integrity of the airplane, accomplish the following: (a) For Model C-212-CB series airplanes: Prior to the accumulation of 16,500 total landings, or within 6 months after the effective date of this AD, whichever occurs later, replace the horizontal stabilizer-to-fuselage attach fittings, part numbers 212-31101.05 and 212-31102.05, with part numbers 212-31122.03 and 212-31123.05, respectively, in accordance with the CASA C-212 Aircraft Maintenance Manual, Chapter 5, Section 5-20, task number 55.15. NOTE 2: Replacement of the attach fittings on Model C-212-CB series airplanes may be accomplished by replacing part numbers 212-31101.05 and 212-31102.05 with part numbers 212- 31123.30 and 212-31122.29, respectively. (b) For all airplanes: Incorporate a revision into the FAA-approved maintenance inspection program that provides for inspection of the Principal Structural Elements (PSE) defined in CASA SupplementalInspection Document (SID) C-212-PV-01-SID, dated June 1, 1987 (hereinafter referred to as the "Document"), at the later of the times specified in paragraphs (b)(1) and (b)(2) of this AD. NOTE 3: Certain thresholds and intervals for inspections of the wing flap control system required by AD 89-02-08 R1, amendment 39-6280, are more restrictive than those specified in the Document. Where differences exist, the thresholds and intervals specified in AD 89-02-08 R1 prevail. (1) Prior to the accumulation of 20,000 total landings or 20,000 total hours time-in- service, whichever occurs first. Or (2) Within 9 months after the effective date of this AD. (c) Any cracked structure detected during the inspections required by paragraph (b) of this AD must be repaired or replaced, prior to further flight, in accordance with the instructions in the Document, or in accordance with other data meeting the certification basis of the airplane that is approved by the FAA or by theDirecci n General de Aviaci n Civil (DGAC). (d) Within 10 days after accomplishing each inspection required by paragraph (b) of this AD, report the results (positive or negative) of each inspection required by paragraph (b) of this AD to CASA in accordance with the Document. Information collection requirements contained in this regulation have been approved by the Office of Management and Budget (OMB) under the provisions of the Paperwork Reduction Act of 1980 (44 U.S.C. 3501 et seq.) and have been assigned OMB Control Number 2120-0056. (e) An 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, Standardization Branch, ANM- 113, 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, Standardization Branch, ANM-113. NOTE 4: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Standardization Branch, ANM-113. (f) Special flight permits may be issued in accordance with sections 21.197 and 21.199 of the Federal Aviation Regulations (14 CFR 21.197 and 21.199) to operate the airplane to a location where the requirements of this AD can be accomplished. (g) The maintenance program revision shall be done in accordance with CASA Supplemental Inspection Document (SID) C-212-PV-01-SID, dated June 1, 1987. (NOTE: The date of Volumes 2 and 3 of the SID is indicated only on the title page of the volume.) 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 Construcciones Aeronauticas, S.A., Getafe, Madrid, Spain. Copies may be inspected at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; or at theOffice of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC. (h) This amendment becomes effective on May 15, 1996.
99-23-18: This amendment adopts a new airworthiness directive (AD) applicable to Bell Helicopter Textron Canada (BHTC) Model 407 helicopters. This action requires, before further flight, revising the life limits for certain parts and replacing each part that has exceeded its life limit. The AD also requires revising the applicable component history cards or equivalent records and the Airworthiness Limitations Schedule of the BHTC Model 407 maintenance manual to reflect these new life limits. This amendment is prompted by an engineering evaluation of additional flight test data, which resulted in redefining the service life for certain parts and revising the Airworthiness Limitations Schedule. The actions specified in this AD are intended to prevent a fatigue failure of certain parts that may have exceeded revised life limits and subsequent loss of control of the helicopter.
91-26-05 R1: 91-26-05 R1 BOEING: Amendment 39-8887. Docket 93-NM-64-AD. Revises AD 91-26-05, Amendment 39-8116. \n\n\tApplicability: Model 747-400 series airplanes, excluding airplanes having production line numbers 816, 839, and 961 and subsequent; certificated in any category. \n\n\tCompliance: Required as indicated, unless accomplished previously. \n\n\tNOTE 1: Paragraph (a) of this AD restates the requirements of paragraph (a) of AD 91-26-05, amendment 39-8116. As allowed by the phrase, "unless accomplished previously," if the requirements of AD 91-26-05 have been accomplished previously, paragraph (a) of this revised AD does not require the insertion of the Airplane Flight Manual (AFM) limitation to be repeated. \n\n\tTo prevent loss of all very high frequency (VHF) radio voice communication transmission capability, accomplish the following: \n\n\t(a)\tWithin 14 days after December 30, 1991 (the effective date of AD 91-26-05, amendment 39-8116): Add the following statement to the Limitations Section of the FAA- approved AFM. This may be accomplished by placing a copy of this AD in the AFM. \n\n\n\t"ELECTRONIC SYSTEMS \n\t\tVHF RADIO VOICE COMMUNICATIONS \n\n\t\tRight VHF radio (VHF R) communication system must be operational for dispatch." \n\n\t(b)\tReplacement of the currently-installed audio management unit (AMU) of the VHF radio communication system having Boeing part numbers S220U000-101, -102, or -104, (Hughes-Avicom part numbers 1167014-140, -141, or -142), with a modified AMU having Boeing part number S220U000-105 (Hughes part number 1167014-143), in accordance with Boeing Service Bulletin 747-23-2321, dated May 20, 1993, constitutes terminating action for the requirements of this AD. Following accomplishment of this replacement, the AFM limitation required by paragraph (a) of this AD may be removed. \n\n\t(c)\tAs of the effective date of this AD, no AMU having Boeing part numbers S220U000-101, -102, or -104, (Hughes-Avicom part numbers 1167014-140, -141, or -142), shall be installed on any airplane, unless the requirements of paragraph (a) of this AD have been accomplished. \n\n\t(d)\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 2: 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(e)\tSpecial flight permits may be issued in accordance with sections 21.197 and 21.199 Federal Aviation Regulations (14 CFR sections 21.197 and 21.199) to operate the airplane to a location where the requirements of this AD can be accomplished. \n\n\t(f)\tThis amendment becomes effective on May 20, 1994.
2004-19-03: This amendment supersedes an existing airworthiness directive (AD), applicable to certain EMBRAER Model EMB-135 and EMB-145 series airplanes, that currently requires revising the airplane flight manual and eventual disconnection of the precooler differential pressure switches. This amendment expands the applicability of the existing AD. This amendment also requires a one-time inspection of those additional airplanes to ensure the disconnection and insulation of the electrical connectors of certain precooler differential pressure switches located in the left and right pylons; and disconnection and insulation of the connectors, if necessary. The actions specified by this AD are intended to prevent incorrect operation of the precooler differential pressure switches, which could result in inappropriate automatic shutoff of the engine bleed valve, and consequent inability to restart a failed engine using cross-bleed from the other engine or possible failure of the anti-ice system.This action is also necessary to ensure that the flightcrew is advised of the procedures necessary to restart an engine in flight using the auxiliary power unit. This action is intended to address the identified unsafe condition.
95-15-05: This amendment adopts a new airworthiness directive (AD), applicable to certain British Aerospace Model BAe 146-100A, -200A, and -300A airplanes, that requires modification of the elevator control system of the flight controls. This amendment is prompted by reports of low frequency constant amplitude oscillations of the elevator control system and non-centering of the pitch control upon autopilot disconnect. The actions specified by this AD are intended to prevent uncommanded descent upon autopilot disconnect and reduced controllability of the airplane due to low frequency constant amplitude oscillations.
2022-13-18: The FAA is adopting a new airworthiness directive (AD) for certain The Boeing Company Model 737-700, 737-800, 747-400, 747-8, 767- 400ER, and 777-200 airplanes. This AD was prompted by a report that there is the potential for electrical current to pass through low pressure (LP) oxygen flex-hoses in the gaseous passenger oxygen system. This AD requires replacing each conductive oxygen flex-hose installed on LP gaseous passenger oxygen systems with a serviceable non- conductive oxygen flex-hose. This AD also prohibits installation of a conductive oxygen flex-hose on LP gaseous passenger oxygen systems. The FAA is issuing this AD to address the unsafe condition on these products.
2022-15-06: The FAA is adopting a new airworthiness directive (AD) for all The Boeing Company Model 777 airplanes. This AD was prompted by high electrical resistance within the gust suppression sensor (GSS) transorb modules due to corrosion on the transorb module threads. This AD requires disconnecting the connectors and capping and stowing the wires that had been attached to the affected transorb modules. The FAA is issuing this AD to address the unsafe condition on these products.
92-20-04: 92-20-04 CANADAIR, LTD.: Amendment 39-8378. Docket No. 91-NM-248-AD. Supersedes AD 91-17-02, Amendment 39-8000. Applicability: Model CL-600-2A12 (CL-601) and CL-600-2B16 (CL-601-3A) series airplanes equipped with a tail cone fuel tank, installed in accordance with the Original Issue, Revision 1, or Revision 2 of Canadair Service Bulletin 601-0262, certificated in any category. Compliance: Required as indicated, unless accomplished previously. To prevent the presence of fuel vapors in the aft equipment bay, which could result in an in-flight fire in the event of a lightning strike or other ignition source in the area, accomplish the following: (a) Within 5 days after August 28, 1991 (the effective date of AD 91-17-02, Amendment 39-8000), or prior to refuelling of the tail cone fuel tank, whichever occurs later, perform a visual inspection of the unshrouded portion of the sensing line in the aft equipment bay to detect any damage or deformation, in accordance with Canadair Alert Wire TA601-0381-003, dated June 11, 1991. Thereafter, repeat the inspection prior to each refuelling. If damage or deformation of the sensing line is found as a result of the visual inspection, accomplish either subparagraph (a)(1) or (a)(2) of this AD, in accordance with the alert wire: (1) Prior to further flight, drain the tail cone fuel tank, and continue flight operations with no fuel in the tail cone fuel tank; or (2) Prior to further flight, drain the tail cone fuel tank, replace the level control valve sensing line, and continue flight operations with fuel in the tail cone fuel tank. (b) After each refuelling of the tail cone fuel tank, inspect for any signs of leakage from the fuel sensing line in the aft equipment bay and at the fuel shroud drain, in accordance with Canadair Alert Wire TA601-0381-003, dated June 11, 1991. If leakage is found, prior to further flight, either drain the tail cone fuel tank, or replace the tail cone fuel tanklevel control valve sensing line, in accordance with the alert wire. (c) Within 6 months after the effective date of this AD, modify the sensing line; perform functional tests of the refuel/defuel line, tail tank fuel shroud, and tail tank sensing line; and perform an electrical bonding and resistance test on all fuel lines installed during this modification; in accordance with Canadair Alert Service Bulletin A601-0381, Revision 2, dated January 27, 1992. (d) Modification of the sensing line, as required by paragraph (c) of this AD, constitutes terminating action for the repetitive inspections required by paragraphs (a) and (b) of this AD. (e) An 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, New York Aircraft Certification Office (ACO), FAA, Engine and Propeller Directorate. Operators shall submit their requests through an appropriate FAA Principal Maintenance Inspector, who may add comments and then send it to the Manager, New York ACO. NOTE: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the New York ACO. (f) 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. (g) The modification and test shall be done in accordance with Canadair Alert Service Bulletin A601-0381, Revision 2, dated January 27, 1992. 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. The inspection shall be done in accordance with Canadair Alert Wire TA601-0381-003, dated June 11, 1991. This incorporation by reference was approved previously by the Director of the Federal Register as of August 28, 1991 (56 FR 38337, August 13, 1991). Copies may be obtained from Bombardier, Inc., Canadair, Aerospace Group, P.O. Box 6087, Station A, Montreal, Quebec H3C 3G9, Canada. Copies may be inspected at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; or at the FAA, New York Aircraft Certification Office, 181 South Franklin Avenue, Room 202, Valley Stream, New York 11581; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC. (h) This amendment becomes effective on November 17, 1992.
2004-19-05: This amendment supersedes an existing airworthiness directive (AD), applicable to certain McDonnell Douglas Model MD-11 and MD-11F airplanes, that currently requires replacing terminal strips and supports above the main cabin area and avionics compartment with new strips and supports, as applicable. That AD also requires performing an inspection to detect arcing damage of the surrounding structure of the terminal strips and electrical cables in the avionics compartment, and repairing or replacing any damaged component with a new component. This amendment expands the applicability of the existing AD to include additional airplanes. For certain airplanes, this action also requires replacement of the terminal board for the applicable item numbers in the aft passenger compartment. The actions specified by this AD are intended to prevent electrical arcing caused by power feeder cable terminal lugs grounding against terminal strip support brackets, which could result in smoke and fire in the main cabin or avionics compartment. This action is intended to address the identified unsafe condition.
96-21-11: This amendment supersedes Airworthiness Directive (AD) 93-25-08, which currently requires replacing the main landing gear (MLG) actuator reinforcement bracket with a part of improved design on certain The New Piper Aircraft, Inc. (Piper) PA31, PA31P, and PA31T series airplanes. This AD action will require the same action as AD 93-25-08. An incorrect designation of Piper Model PA31-310 airplanes made in AD 93-25-08 prompted the proposed AD action. The actions specified by this AD are intended to prevent the MLG from extending, when not selected and while the airplane is in flight, caused by actuator reinforcement bracket failure, which could result in substantial airplane damage or loss of control of the airplane.
76-22-10: 76-22-10 AVIONS MARCEL DASSAULT (AMD): Amendment 39-2766. Applies to Model Fan Jet Falcon (Falcon 20) airplanes, all series, certificated in all categories, with installed Messier/Hispano Main Landing Gear Actuating Cylinders P/N A23721 (L.H.) and A23722 (R.H.) serial numbers 1 through 807, 809 through 813, 816, 818, and 820 not modified in accordance with AMD Service Bulletin No. 529, dated September 5, 1975. Compliance is required as indicated. To prevent possible failure of main landing gear down-locks, accomplish the following: (a) Inspect the following actuating cylinders for corrosion in accordance with Messier Hispano Technical Instruction DME361-5, or an FAA-approved equivalent: (1) For S/N 1 through 699, within the next 50 hours time in service or three months, whichever occurs first, after the effective date of this AD, unless already accomplished within the preceding three months, and thereafter at intervals not to exceed six months from the dateof the last inspection. (2) For S/N 700 through 807, 809 through 813, 816, 818, and 820, within the next 200 hours time in service or four months, whichever occurs first, after the effective date of this AD, unless already accomplished within the preceding two months, and thereafter at intervals not to exceed six months from the date of the last inspection. (b) If the inspection required by paragraph (a) of this AD reveals the presence of a corrosion condition classified as "very corroded," in accordance with the classification criteria of paragraph 1.c. of AMD Service Bulletin No. 528, dated July 17, 1975 (Revision 2, February 19, 1976), or an FAA-approved equivalent, within the next three months after this inspection - (1) Replace the actuator with a serviceable part of the same part number and continue the periodic inspections specified in paragraph (a) of this AD; or (2) Modify the actuator in accordance with AMD Service Bulletin No. 529, dated September 5, 1975, or an FAA-approved equivalent. (c) The inspections required by paragraphs (a) and (b)(1) of this AD may be discontinued upon the incorporation of the modification specified in paragraph (b)(2) of this AD. This amendment becomes effective November 22, 1976.
96-09-05: This amendment adopts a new airworthiness directive (AD) that is applicable to Diamond Aircraft Industries (Diamond) Model DA 20-A1 airplanes. This action requires inspecting the aft wing cavities for manufacturing debris, removing any debris found, and modifying the aileron pushrod fairings to allow them to flex. Several reports of the aileron controls becoming blocked because of manufacturing debris getting jammed between the short aileron pushrod and the pushrod exit fairing on both left and right wings prompted this action. The actions specified by this AD are intended to prevent the aileron controls from becoming blocked causing jamming between the short aileron pushrod and the pushrod fairing exit, which, if not detected and corrected, could cause loss of control of the airplane.
96-20-01: This amendment adopts a new airworthiness directive (AD) that is applicable to certain Boeing Model 777-200 series airplanes. This action requires a one-time inspection to determine the serial numbers of various switch modules on the overhead panel and control stand, and replacement of switch modules with new improved modules. This AD also requires repetitive tests of the cargo fire extinguishing system, and one-time tests of the fuel crossfeed valve, pack, trim air, and alternate flap control switches; and repair or replacement of switch modules with new improved modules, if necessary. This amendment is prompted by a report indicating that the flight crew received a warning of fire in the forward cargo compartment during flight; later inspection revealed that the metered fire bottles failed to discharge due to suspected contamination of the arming switch contacts of the cargo fire extinguishing system. The actions specified in this AD are intended to minimize contamination of the switch contacts and consequent failure of the switches, which, if not corrected, could result in inability of the flight crew to activate the cargo fire extinguishing, fuel, air conditioning, and alternate flap systems.
2022-16-01: The FAA is superseding Airworthiness Directive (AD) 2022-08- 07, which applied to all Embraer S.A. Model ERJ 170-100 STD, -100 LR, - 100 SU, and -100 SE airplanes; Model ERJ 170-200 STD, -200 LR, and -200 SU airplanes; Model ERJ 190-100 STD, -100 LR, -100 IGW, and -100 ECJ airplanes; and Model ERJ 190-200 STD, -200 LR, and -200 IGW airplanes. AD 2022-08-07 required determining if certain NORDAM passenger windows are installed, inspecting affected parts for cracks, and replacing cracked parts. AD 2022-08-07 also required repetitive inspections of uncracked affected parts until all affected parts are replaced. This AD was prompted by a determination that additional airplanes are affected by the unsafe condition identified in AD 2022-08-07. This AD retains certain requirements of AD 2022-08-07, revises the applicability of AD 2022-08-07 to include the affected parts for clarification, and adds a certain airplane model to the applicability. This AD also prohibits the installation of affected parts. The FAA is issuing this AD to address the unsafe condition on these products.
2013-05-11: We are superseding an existing airworthiness directive (AD) for certain Airbus Model A318, A319, A320, and A321 series airplanes. That AD currently requires one-time and repetitive inspections of specific areas and, when necessary, corrective actions for those rudders where production rework has been identified. This new AD adds airplanes with certain rudders to the AD applicability; changes an inspection type for certain reinforced rudder areas; requires pre- inspections and repairs if needed; and requires permanent restoration of vacuum loss holes. This AD also requires additional inspections for certain rudders and repair if needed, and requires replacement of certain rudders with new rudders. This AD was prompted by reports of surface defects on rudders that were the result of debonding between the skin and honeycomb core. We are issuing this AD to detect and correct extended de-bonding, which might degrade the structural integrity of the rudder. The loss of the rudder leads to degradation of the handling qualities and reduces the controllability of the airplane.
95-24-12: This amendment adopts a new airworthiness directive (AD) that applies to Jetstream Aircraft Limited (JAL) Model 3201 airplanes. This action requires repetitively inspecting the main landing gear (MLG) bay forward lower edge wing skin structure for cracks, replacing any cracked doubler with a joggled doubler of improved design to reinforce the area and prevent future cracking, and eventually incorporating these doublers on all affected airplanes. Cracking found at the MLG bay forward lower edge wing skin structure during fatigue testing of the JAL Model 3201 prompted this action. The actions specified by this AD are intended to prevent the MLG bay forward lower edge wing skin structure from cracking, which, if not detected and corrected, could cause failure of the wing structure and loss of control of the airplane.
2022-12-10: The FAA is adopting a new airworthiness directive (AD) for all Dassault Aviation Model FALCON 7X airplanes. This AD was prompted by a report of a weak point identified in the Falcon 7X 'EASy' avionics architecture, which, coupled with theoretical generic input/output (I/ O) card failure, could lead to misleading data on display units. This AD requires revising the existing airplane flight manual (AFM) to provide emergency procedures for inconsistent or unreliable flight data and emergency and abnormal operations procedures for the GEN I/O internal module failure, and revising the operator's existing FAA- approved minimum equipment list (MEL) items for the multi-function probe heating, air data, and inertial reference systems, as specified in a European Union Aviation Safety Agency (EASA) AD, which is incorporated by reference. This AD also requires revising the existing AFM to incorporate additional information in the emergency procedures. The FAA is issuing this AD to address the unsafe condition on these products.
2022-12-11: The FAA is adopting a new airworthiness directive (AD) for certain Embraer S.A. Model ERJ 190-100 ECJ airplanes. This AD was prompted by a determination that new or more restrictive airworthiness limitations are necessary and that some life limits on some components used on the main landing gear (MLG) may not be properly controlled, due to interchanging those parts between airplane models with different operational loads during repair or overhaul. This AD requires revising the existing maintenance or inspection program, as applicable, to incorporate new or more restrictive airworthiness limitations; reviewing maintenance records of the MLG assemblies to determine if any life-limited item has been replaced and reporting those findings; and re-identifying the MLG assemblies and certain components; as specified in an Ag[ecirc]ncia Nacional de Avia[ccedil][atilde]o Civil (ANAC) AD, which is incorporated by reference. This AD also prohibits installing certain part numbers. The FAA is issuing this AD to address the unsafe condition on these products.
2004-18-04: The FAA is adopting a new airworthiness directive (AD) for all McDonnell Douglas MD-10-10F, MD-10-30F, MD-11, MD-11F, and 717-200 airplanes. This AD requires a revision to the Limitations section of the Airplane Flight Manual (AFM) to prohibit use of the flight management system (FMS) profile (PROF) mode for descent and/or approach operations unless certain conditions are met. This AD is promoted by a report of two violations of the selected flight control panel (FCP) altitude during FMS PROF descents. We are issuing this AD to prevent, under certain conditions during the FMS PROF descent, the uncommanded descent of an airplane below the selected level-off altitude, which could result in an unacceptable reduction in the separation between the airplane and nearby air traffic or terrain.
92-25-05: 92-25-05 BRITISH AEROSPACE: Amendment 39-8420. Docket No. 91-NM-269-AD. Applicability: All Model ATP series airplanes, certificated in any category. Compliance: Required as indicated, unless accomplished previously. To prevent structural failure of certain brake torque plates and accompanying brake failure, accomplish the following: (a) Within 400 landings after the effective date of this AD, revise the FAA-approved Mandatory Life Limitations (Airframe) Section, Chapter 5, Section 05-10-11, Table 1, page 4, of the British Aerospace ATP Aircraft Maintenance Manual, by deleting the existing life limitations for brake torque plates, part numbers AHA 1777 and AHA 1650, and adding the component life limitations listed in Table 1 below. The Maintenance Manual revision may be accomplished by inserting a copy of this AD into the Mandatory Life Limitations (Airframe) Section of the ATP Aircraft Maintenance Manual. Once this revised page of the Maintenance Manual is available from British Aerospace and is inserted into the Maintenance Manual, the copy of this AD may be removed. TABLE 1 continued MSI/SSI ITEM DESCRIPTION PART NUMBER LIFE LIMITATION 32-42-00-022 Brake torque plate (Post Dunlop Mod 2541) AHM8857 Assembly AHA 1777 14,500 landings 32-42-00-022 Brake torque plate (Pre Dunlop Mod 2541) AHM8857 Assembly AHA 1650 10,000 landings (b) An 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, Standardization Branch, ANM-113, 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, Standardization Branch, ANM-113. NOTE: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Standardization Branch, ANM-113. (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) This amendment becomes effective on December 22, 1992.
2022-14-14: The FAA is adopting a new airworthiness directive (AD) for all Alexander Schleicher GmbH & Co. Segelflugzeugbau Model ASW-15 gliders. This AD results from 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 wing root damage. This AD requires repetitively inspecting the wing root ribs for cracks, looseness, and damage and replacing any root rib with a crack, a loose rib or lift pin bushing, or any damage. The FAA is issuing this AD to address the unsafe condition on these products.
2013-11-07: We are adopting a new airworthiness directive (AD) for certain Embraer S.A. Model ERJ 190 airplanes. This AD was prompted by reports of cracks on the side stay of the main landing gear (MLG). This AD requires repetitive measurements of the left-hand (LH) and right-hand (RH) MLG side stay support fitting to detect bushing migration, and eventual replacement of the bushing; and a detailed inspection for damage on the LH and RH MLG side stay support assembly, and related investigative and corrective actions if necessary. We are issuing this AD to prevent excessive bearing friction, which might compromise the MLG free fall extension and cause fatigue cracking on the MLG side stay and on its support assembly, resulting in reduced structural integrity of the MLG.
2013-11-13: We are adopting a new airworthiness directive (AD) for all Rolls-Royce plc (RR) Viper Mk. 601-22 turbojet engines. This AD requires reducing the life of certain critical parts. This AD was prompted by a review carried out by RR of the lives of these parts. We are issuing this AD to prevent failure of life-limited parts, damage to the engine, and damage to the airplane.
97-02-21: This amendment adopts a new airworthiness directive (AD), applicable to certain EMBRAER Model EMB-120 series airplanes, that requires repetitive inspections to detect cracks in the wing rib-to-skin support brackets (shear clips), and replacement of cracked brackets with new or serviceable brackets. This amendment also requires the eventual replacement of certain brackets with new brackets, which terminates the requirement for the inspections. This amendment is prompted by reports of cracks in certain wing rib-to-skin support brackets in both the lower and upper skin of the wings. The actions specified by this AD are intended to prevent cracking of those support brackets, which can subsequently lead to the loosening of the rivets in the wing skin, leakage of fuel through the rivet holes, and, ultimately, the reduction of the structural integrity of the wing.