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91-20-14 R1: 91-20-14 R1 BEECH AIRCRAFT CORPORATION: Amendment 39-8992; Docket No. 91-CE- 76-AD; Revises AD 91-20-14, Amendment 39-8168. Applicability: The following model and serial number airplanes, certificated in any category: Model Serial Numbers B300 FL-1 through FL-110 B300C FM-1 through FM-8 Compliance: Required within 10 hours time-in-service after February 20, 1992 (the effective date of AD 91-20-14), unless already accomplished. To ensure that the affected airplanes achieve required minimum takeoff and climb performance for each approved combination of takeoff configuration, weight, pressure altitude, and temperature, accomplish the following: (a) Incorporate the takeoff and climb performance charts, B2 revision, part number (P/N) 130-590031-1, dated September 1991, into the Model B300 and B300C Pilot's Operating Handbook and FAA Approved Airplane Flight Manual (AFM/POH). NOTE 1: The charts sent in the priority letter AD 91-20-14 package and B2 revision, P/N 130- 590031-1, dated September 1991, are the same. (b) Incorporating the climb and takeoff charts as required by this AD may be performed by the owner/operator holding at least a private pilot certificate as authorized by section 43.7 of the Federal Aviation Regulations (14 CFR 43.7), and must be entered into the aircraft records showing compliance with this AD in accordance with section 43.11 of the Federal Aviation Regulations (14 CFR 43.11). (c) 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. (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, Wichita Aircraft Certification Office (ACO), FAA, 1801 Airport Road, Room 100, Wichita, Kansas 67209. The request shouldbe forwarded through an appropriate FAA Maintenance Inspector, who may add comments and send it to the Manager, Wichita ACO. NOTE 2: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Wichita ACO. (e) The takeoff and climb performance limitations required by this AD shall be done in accordance with the Beech Pilot's Operating Handbook and FAA Approved Airplane Flight Manual, B2 revision, part number 130-590031-1, dated September 1991. This incorporation by reference was previously approved by the Director of the Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR part 51 as of February 20, 1992. Copies may be obtained from the Beech Aircraft Corporation, P.O. Box 85, Wichita, Kansas 67201-0085. 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, 800 North Capitol Street, NW., suite 700, Washington, DC. (f) This amendment (39-8992) revises AD 91-20-14, Amendment 39-8168. (g) This amendment becomes effective on September 12, 1994.
2022-18-08: The FAA is adopting a new airworthiness directive (AD) for all Airbus SAS Model A350-941 and -1041 airplanes. This AD was prompted by a report indicating that the vertical stop support fitting (VSSF) of certain captain's, first officer's, and third occupant's seats could fail. This AD requires modifying or replacing each affected seat, as specified in a European Union Aviation Safety Agency (EASA) AD, which is incorporated by reference. This AD also limits the installation of affected parts under certain conditions. The FAA is issuing this AD to address the unsafe condition on these products.
77-13-09 R1: 77-13-09 R1 HAWKER SIDDELEY AVIATION, LTD: Amendment 39-2934 as amended by Amendment 39-4854. Applies to Model DH/BH 125 airplanes series 1A up to and including series 600A certificated in all categories. A. Prior to the accumulation of 6600 total landings or upon reaching 10 years after the date of manufacture of the airplane, whichever occurs first, if not already accomplished, incorporate Hawker Siddeley modifications 25-2402 and 25-2207 in accordance with Section 2, Accomplishment Instructions, of Hawker Siddeley Aviation, Ltd., Service Bulletin 53-46-(2402), Revision 2, dated February 16, 1976. Airplanes which have already exceeded 6500 landings or are over 9-1/2 years from date of manufacture must be modified within the next 100 landings or 6 months after the effective date of this amendment, whichever occurs first. B. Alternate means of compliance which provide an equivalent level of safety may be used when approved by the Manager, Seattle Aircraft CertificationOffice, FAA, Northwest Mountain Region. C. Special 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. Amendment 39-2934 became effective July 25, 1977. This Amendment 39-4854 becomes effective June 1, 1984.
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.