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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.