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2004-19-11: This amendment supersedes an existing airworthiness directive (AD), applicable to certain Airbus Model A320 series airplanes, that currently requires modification of the rear spar web of the wing, cold expansion of certain attachment holes for the forward pintle fitting and certain holes at the actuating cylinder anchorage of the main landing gear (MLG), repetitive inspections for fatigue cracking in certain areas of the rear spar of the wing, and corrective action if necessary. That AD also provides for optional terminating action for the requirements of the AD. This amendment revises certain compliance times for the inspection. The actions specified by this AD are intended to detect and correct fatigue cracking, which may lead to reduced structural integrity of the wing and the MLG. This action is intended to address the identified unsafe condition. DATES: Effective November 5, 2004. The incorporation by reference of a certain publication, as listed in the regulations, is approved by the Director of the Federal Register as of November 5, 2004. The incorporation by reference of certain other publications, as listed in the regulations, was approved previously by the Director of the Federal Register as of June 30, 2000 (65 FR 34069, May 26, 2000); February 14, 1994 (59 FR 1903, January 13, 1994); and June 11, 1993 (58 FR 27923, May 12, 1993).
96-22-06: This amendment adopts a new airworthiness directive (AD), applicable to all McDonnell Douglas Model DC-10-15 airplanes, that requires, among other things, inspections to detect discrepancies at various locations of pylons 1 and 3, and correction of any discrepancy found. This amendment is prompted by a report of internal structural damage to the wing engine pylon that occurred during maintenance of a Model DC-10 series airplane. The actions specified by this AD are intended to ensure the integrity of the structure and attachment of the wing engine pylon.
92-17-03: 92-17-03 BOEING: Amendment 39-8332. Docket No. 91-NM-270-AD. \n\n\tApplicability: Model 767 series airplanes; as listed in Boeing Alert Service Bulletin 767-57A0038, Revision 2, dated February 20, 1992; certificated in any category. \n\n\tCompliance: Required as indicated, unless accomplished previously. \n\n\tTo prevent damage to the wing rear spar and prevent fuel leakage in the event of a main landing gear (MLG) breakaway, accomplish the following: \n\n\t(a)\tWithin the next 30 days after the effective date of this AD, inspect the MLG forward trunnion support fitting fuse pins to determine if the correct part-numbered pins are installed, in accordance with Boeing Alert Service Bulletin 767-57A0038, Revision 1, dated November 21, 1991; or Revision 2, dated February 20, 1992. \n\n\t\t(1)\tIf incorrect fuse pins are installed, prior to further flight, replace the fuse pins in accordance with Boeing Alert Service Bulletin 767-57A0038, Revision 1, dated November 21, 1991; or Revision 2, dated February 20, 1992. \n\n\t\t(2)\tIf correct fuse pins are installed, no further action is required. \n\n\t(b)\tWithin 10 days after completion of the inspection required by paragraph (a) of this AD, submit a report of findings of discrepancies to the Manager, Seattle Manufacturing Inspection District Office, FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, Washington, 98055-4056; fax (206) 227-1187. Information collection requirements contained in this regulation have been approved by the Office of Management and Budget (OMB) under the provision of the Paperwork Reduction Act of 1980 (44 U.S.C. 3501 et seq.) and have been assigned OMB Control Number 2120-0056. \n\n\t(c)\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 FAAPrincipal Maintenance Inspector, who may add comments and then send it to the Manager, Seattle ACO. \n\n\tNOTE: 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(d)\tSpecial 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. \n\n\t(e)\tThe inspection and replacement shall be done in accordance with Boeing Alert Service Bulletin 767-57A0038, Revision 1, dated November 21, 1991; or Boeing Alert Service Bulletin 767-57A0038, Revision 2, dated February 20, 1992. (NOTE: The issue date of Boeing Alert Service Bulletin 767-57A0038, Revision 1, is indicated only on page 1 of the document; no other page of the document is dated.) 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 obtainedfrom Boeing Commercial Airplane Group, P.O. Box 3707, Seattle, Washington 98124. Copies may be inspected at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, Washington; or at the Office of the Federal Register, 800 North Capitol Street NW., 7th Floor, Suite 700, Washington, DC. \n\n\t(f)\tThis amendment becomes effective on September 28, 1992.
2022-17-07: The FAA is adopting a new airworthiness directive (AD) for all Airbus SAS Model A350-941 airplanes. This AD was prompted by a report indicating that the inflatable free aisle restrictor (IFAR) on certain single lane slide-rafts demonstrated inconsistent release behavior in aft wind conditions. This AD requires replacing an affected part with a serviceable part, as specified in a European Union Aviation Safety Agency (EASA) AD, which is incorporated by reference. This AD also prohibits the installation of affected parts. The FAA is issuing this AD to address the unsafe condition on these products.
96-22-01: This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 747-200, -300, and -400 series airplanes, that requires modification of the left and right inboard elevator servo assemblies and the hydraulic routing of the right inboard elevator power control package (PCP). This amendment is prompted by a report of an uncommanded right elevator deflection after takeoff and reports of elevator/control column bumps during landing gear retraction on these airplanes. The actions specified by this AD are intended to prevent uncommanded elevator deflection, which could result in structural damage and reduced controllability of the airplane.
78-01-11: 78-01-11 MCDONNELL DOUGLAS: Amendment 39-3116. Applies to all passenger and passenger/cargo Model DC-9 airplanes certificated in all categories, including C-9A, C-9B and VC-9C. \n\n\tCompliance required within 180 days from the effective date of this AD, unless already accomplished. \n\n\tTo identify the location and operation of the tail cone emergency exit release handle, accomplish the following: \n\n\tModify the tail cone emergency exit release handle locating and operating markings in accordance with McDonnell Douglas Service Bulletin 53-134, Revision 1, dated December 16, 1977 or later FAA approved revision, or an equivalent modification approved by the Chief, Aircraft Engineering Division, FAA Western Region. \n\n\tThis Amendment becomes effective February 13, 1978.
2004-20-01: The FAA is adopting a new airworthiness directive (AD) for Pratt & Whitney Canada (PWC) models PW123, PW123B, PW123C, PW123D, PW123E, PW123AF, PW124B, PW125B, PW126A, PW127, PW127E, PW127F, and PW127G turboprop engines. This AD requires initial and repetitive gap inspections of the bypass valve cover, on certain part number (P/N) mechanical fuel controls (MFCs), and replacement of those MFCs as mandatory terminating action to the repetitive inspections. This AD is prompted by sixteen reports of loss of engine throttle response and overspeed, eight of which resulted in in-flight shutdown. We are issuing this AD to prevent loss of throttle response and overspeed, resulting in engine in-flight shutdown.
90-21-13: 90-21-13 BOEING: Amendment 39-6751. Docket No. 90-NM-67-AD. \n\n\tApplicability: Model 747 series airplanes, line position 001 through 331, identified in Boeing Service Bulletin 747-29-2051, Revision 1, dated August 8, 1980, certificated in any category.\n \n\tCompliance: Required within the next 4,000 flight hours or 12 months after the effective date of this AD, whichever occurs first, unless previously accomplished. \n\n\tTo prevent damage to hydraulic and pneumatic systems and flight deck/cabin air contamination, accomplish the following: \n\n\tA.\tModify the hydraulic system in the number 2 and 3 struts in accordance with the Accomplishment Instructions of Boeing Service Bulletin 747-29-2051, Revision 1, dated August 8, 1980.\n \n\tB.\tAn 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, Seattle Aircraft Certification Office, FAA, Northwest Mountain Region.\n \n\tNOTE: The request should be forwarded through an FAA Principal Inspector (PI), who will either concur or comment, and then send it to the Manager, Seattle Aircraft Certification Office. \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 documents from the manufacturer may obtain copies upon request to The Boeing Commercial Airplane Group, P.O. Box 3707, Seattle, Washington 98124. These documents may be examined at the FAA, Northwest Mountain Region, Transport Airplane Directorate, 1601 Lind Avenue S.W., Renton, Washington. \n\n\tThis amendment (39-6751, AD 90-21-13) becomes effective on November 12, 1990.
91-22-05: 91-22-05 BOEING: Amendment 39-8065. Docket No. 91-NM-55-AD. \n\n\tApplicability: Model 747 series airplanes, line numbers 001 through 708, except Model 747-400 and freighters, certificated in any category. \n\n\tCompliance: Required within 36 months after the effective date of this AD, unless previously accomplished. \n\n\tTo prevent injury to passengers and flight attendants, accomplish the following: \n\n\t(a)\tFor airplanes listed in Boeing Service Bulletin 747-25-2734, Revision 1, dated May 25, 1989:\n\n\t\t(1)\tFor those stowage bins used for stowage, accomplish the following in accordance with Section III of Boeing Service Bulletin 747-25-2734, dated November 3, 1988, or Revision 1, dated May 25, 1989: \n\n\t\t\t(i)\tReplace the overhead stowage compartment doors and counterbalance assemblies; \n\n\t\t\t(ii)\tRework and adjust compartments; \n\n\t\t\t(iii)\tInstall new wiring provisions; and \n\n\t\t\t(iv)\tPerform operational checks of associated equipment. \n\n\t\t(2)\tFor those bins that are notused for stowage of any item, in lieu of the procedures required by paragraph (a)(1) of this AD, operators may accomplish the following: \n\n\t\t\t(i)\tConduct a visual inspection of the existing latches for wear of the latching handle locking grooves and ensure full travel of the latch pins. If wear or other discrepancies are indicated, repair in accordance with FAA-approved procedures. \n\n\t\t\t(ii)\tInstall a placard indicating "NO STOWAGE;" and \n\n\t\t\t(iii)\tDisable the bin to prevent its opening, in a manner approved by the FAA Principal Maintenance Inspector. \n\n\t(b)\tFor airplanes not listed in Boeing Service Bulletin 747-25-2734, Revision 1, dated May 25, 1989: \n\n\t\t(1)\tFor those stowage bins used for stowage, accomplish the following in a manner similar to that described in the service bulletin and approved by the Manager, Seattle Aircraft Certification Office (ACO), FAA, Transport Airplane Directorate: \n\n\t\t\t(i)\tReplace the overhead stowage compartment doors and counterbalance assemblies; \n\n\t\t\t(ii)\tRework and adjust compartments; \n\n\t\t\t(iii)\tInstall new wiring provisions; and \n\n\t\t\t(iv)\tPerform operational checks of associated equipment. \n\n\t\t(2)\tFor those bins that are not used for stowage of any item, in lieu of the procedures required by paragraph (b)(1) of this AD, operators may accomplish the following: \n\n\t\t\t(i)\tConduct a visual inspection of the existing latches for wear of the latching handle locking grooves and ensure full travel of the latch pins. If wear or other discrepancies are indicated, repair, in accordance with FAA-approved procedures. \n\n\t\t\t(ii)\tInstall a placard indicating "NO STOWAGE;" and \n\n\t\t\t(iii)\tDisable the bin to prevent its opening, in a manner approved by the FAA Principal Maintenance Inspector. \n\n\t(c)\tAn alternative method of compliance or adjustment of the compliance time, which provides an acceptable level of safety, may be used when approved by the Manager, Seattle ACO, FAA, Transport Airplane Directorate. \n\n\tNOTE:The request should be forwarded through an FAA Principal Maintenance Inspector (PMI) who may concur or comment and then sent it to the Manager, Seattle ACO. \n\n\t(d)\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\t(e)\tThe requirements for replacement, rework and adjustment, inspections, and operational checks shall be done in accordance with Boeing Service Bulletin 747-25-2734, dated November 3, 1988; or in accordance with Boeing Service Bulletin 747-25-2734, Revision 1, dated May 25, 1989, which includes the following list of effective pages: \n\n\n\nPAGE NUMBER\t\t\nREVISION LEVEL\n\nDATE\n 1-2, 4, 7, 9-13, 17-27, 76-77 \n\n1\nMay 25, 1989\n3, 5-6, 8, 14-16, 28-75, 78-83 \n(Original)\nNovember 3, 1988\n\nThis 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 Boeing Commercial Airplane Group, P.O. Box 3707, Seattle, Washington 98124. Copies may be inspected at the FAA, Northwest Mountain Region, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, Washington, or at the Office of the Federal Register, 1100 L Street NW., Room 8401, Washington, D.C. \n\n\tThis amendment (39-8065, AD 91-22-05) becomes effective on November 29, 1991.
73-13-11: 73-13-11 MITCHELL INDUSTRIES, INC., doing business as EDO-AIRE MITCHELL: Amendment 39-1677. Applies to Mitchell automatic pilot instruments installed in various Beech aircraft with a mechanical wing flap control system in accordance with the following Supplemental Type Certificates: STC NO. BEECH AIRPLANE MODELS AUTOPILOT MODEL SA1346SW 23, A23, A23A, A23-19, 19A, A24, Century I A24R, B19, M19A, A23-24, B23,C23 Model AK341 SA1348SW 23, A23, A23A, A23-19, 19A, B19, Century IIB M19A, A23-24, B23, C23, A24, A24R Model AK342 Compliance required within the next ten (10) hours' time in service after the effective date of this AD, unless already accomplished. To prevent interference of the flap control system with the automatic pilot roll servo, which may result in loss of aileron control, accomplish the following: Remove the automatic pilot roll servo assembly and all servo installation brackets from the airplanes or install the cable tensioner Kit PKMB-8 in accordance with Edo-Aire Mitchell Service Bulletin No. MB-8 dated June 7, 1973, or later FAA approved revision, or any other method approved by the Chief, Engineering and Manufacturing Branch, Southwest Region, Federal Aviation Administration, Fort Worth, Texas. The bulletin mentioned herein may be obtained from Edo-Aire Mitchell, P. O. Box 610, Mineral Wells, Texas 76067. This amendment becomes effective June 29, 1973.