Results
2006-02-03: The FAA is adopting a new airworthiness directive (AD) for certain Raytheon Model Hawker 800XP airplanes. This AD requires inspecting to determine if the correct fuse is installed on the hydraulic over-temperature switch on panel ZK in the rear equipment bay, and replacing the existing fuse if necessary. This AD results from a report of the installation of an incorrect fuse on the over- temperature switch on panel ZK in the rear equipment bay during airplane maintenance. We are issuing this AD to prevent a short circuit in the fuse and consequent heat damage to associated wiring and surrounding equipment, which could result in smoke or fire on the airplane.
2008-18-03: We are adopting a new airworthiness directive (AD) for the products listed above. 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 describes the unsafe condition as: During manufacturing of A330/A340 aircraft framework, cracks have been found on Frame (FR) 12, left (LH) and right (RH) sides. It has been confirmed that a defect of the FR12 forming tool press is the root cause of the cracks. If undetected such damage could affect, after propagation, the structural integrity of the aircraft. * * * * * * * We are issuing this AD to require actions to correct the unsafe condition on these products.
81-02-08: 81-02-08 LOCKHEED-CALIFORNIA: Amendment 39-4023. Applies to all Model L-1011 series airplanes certificated in all categories. Compliance required within 300 hours time-in-service after the effective date of this AD. To assure availability of emergency passenger oxygen, accomplish the following: A. Replace all one-man fixed chemical oxygen generators, Scott Aviation P/N 801462-01 with Scott Aviation P/N 801462-04 oxygen generators, in accordance with a method approved by the Chief, Los Angeles Area Aircraft Certification Office. (NOTE: Accomplishment of Lockheed Service Bulletin 093-35-030, dated September 15, 1980, has been approved as a means of compliance with this requirement.) B. Alternative means of compliance or other actions which provide an equivalent level of safety may be used when approved by the Chief, Los Angeles Area Aircraft Certification Office, FAA Northwest Region. C. Special flight permits may be issued in accordance with FAR 21.197 and 21.199to operate airplanes to a base in order to comply with the requirements of this AD. This amendment becomes effective January 27, 1981.
81-20-04 R1: 81-20-04 R1 BOEING: Amendment 39-4225 as amended by Amendment 39-4250. Applies to Boeing Model 727-200 series and 737 airplanes, certificated in all categories, using the following Hamilton Standard electronic pressurization controllers that have not been previously modified to HS reference number P57: \n\n\nHS Part Number\nBoeing Part Number \n710204-7\n10-61209-13 \n710204-8\n10-61209-14 \n761260-7\n10-61209-19 \n761260-8\n10-61209-18 \n\n\tTo prevent inflight fires, on or before May 12, 1982, accomplish the following, unless already accomplished: Modify the Hamilton Standard pressurization controllers listed above in accordance with Boeing Service Bulletins 727-21 A96 and 737-21 A1064, published August 28, 1981, or later FAA approved revision, or in a manner approved by the Chief, Seattle Area Aircraft Certification Office. \n\tThe Assurance of Serviceability testing described in Paragraph B(16) of Hamilton Standard Service Bulletin 21-88, Revision 1, dated October 13, 1981, may be used in lieu of the complete functional test specified in the Boeing Service Bulletins listed above.\n \n\tThe manufacturer's specifications and procedures identified and described in this directive are incorporated herein and made a part hereof pursuant to 5 U.S.C. 552(a)(1). All persons affected by this directive who have not already received the above specified Alert Service Bulletin from the manufacturer may obtain copies upon request to Boeing Commercial Airplane Company, P.O. Box 3707, Seattle, Washington 98124, or it may also be examined at FAA Northwest Region, 9010 East Marginal Way South, Seattle, Washington 98108. \n\n\tAmendment 39-4225 became effective October 13, 1981. \n\tThis amendment 39-4250 becomes effective November 13, 1981.
2006-02-05: The FAA is adopting a new airworthiness directive (AD) for certain Bombardier Model CL-600-2B19 (Regional Jet Series 100 & 440) airplanes. This AD requires replacing the Camloc fasteners on the sidewall of the center pedestal. This AD results from reports of the Camloc fasteners on the sidewall of the center pedestal disengaging and interfering with an inboard rudder pedal. We are issuing this AD to prevent these fasteners from disengaging and interfering with an inboard rudder pedal, which could reduce directional controllability of the airplane.
2002-26-10: This amendment supersedes an existing airworthiness directive (AD), applicable to certain McDonnell Douglas DC-9-10, -20, -30, -40, and -50 series airplanes, that currently requires a one-time visual inspection to determine the modification status of the corners of the forward lower cargo doorjamb; low-frequency eddy current or X-ray inspections to detect cracks of the fuselage skin and doubler at all corners of the forward lower cargo doorjamb; various follow-on repetitive inspections; and modification, if necessary. This amendment retains those requirements but requires certain high-frequency, rather than low-frequency, eddy current inspections for certain conditions. The actions specified by this AD are intended to detect and correct cracking, which could result in rapid decompression of the fuselage and consequent reduced structural integrity of the airplane. This action is intended to address the identified unsafe condition.
64-02-06 R1: 64-02-06 R1 SIKORSKY AIRCRAFT: Amendment 674 as amended by Amendment 39-6090. Applies to all Sikorsky Model S-58 series helicopters. Compliance is required as indicated unless already accomplished. Fatigue cracks have been found in the area of the rear three bolt holes of upper pylon folding hinge fitting P/N S1620-63130-2, the forward bolt holes of mating fitting P/N S1620-64127, the forward bolt hole of the lower pylon hinge fitting P/N S1620-64131, and the lug through which the hinge bolt passes of fittings P/N's S1620-64127 and S1620-64127-7. In order to preclude propagation of fatigue cracks in these areas and subsequent serious weakening of the pylon attachment, accomplish the following: (a) As of the effective date of this AD, conduct daily visual inspections of the area around the fitting bolt holes of all pylon and tail cone folding hinge fittings for cracks. Replace any cracked fittings before further flight. (b) Unless already accomplished, accomplish the following in accordance with Sikorsky Service Bulletin No. 58B20-11A within 100 hours' time in service after the effective date of this AD on all upper pylon hinge fittings P/N S1620-64127 with 1,900 hours' or more time in service, or prior to the accumulation of 2,000 hours' time in service on all fittings having less than 1,900 hours' time in service as of the effective date of this AD: (1) Remove all bushings from the hinges. (2) Rework and inspect the bore of each hole. (3) Install oversized replacement bushings P/N S1620-63129-7. (c) Upon request, an alternate means of compliance which provides an equivalent level of safety with the requirements of this AD may be used when approved by the Manager, Rotorcraft Standards Staff, Rotorcraft Directorate, Aircraft Certification Service, ASW-110, FAA, Fort Worth, Texas 76193-0110. (d) In accordance with Sections 21.197 and 21.199, the helicopter may be flown to a base where compliance may be accomplished. Airworthiness Directive 63-09-02 was superseded by AD 64-02-06 (Amendment 674; 29 FR 559; January 21, 1964) which was effective January 31, 1964. This amendment (39-6090, AD 64-02-06 R1) revises AD 64-02-06 and becomes effective December 27, 1988.
2001-08-14 R1: The FAA is revising an existing airworthiness directive (AD) for Turbomeca S.A. Arrius Models 2B, 2B1, and 2F turboshaft engines. That AD currently requires replacing the right injector half manifold, left injector half manifold, and privilege injector pipe. This AD requires the same actions, but relaxes the compliance time for the repetitive replacements on Arrius 2F engines. This AD results from Turbomeca relaxing the repetitive replacement interval for Arrius 2F engine fuel nozzles based on review of returned fuel nozzles to Turbomeca. We are issuing this AD to prevent engine flameout during rapid deceleration, or the inability to maintain the 2.5 minutes one engine inoperative (OEI) rating, and to prevent air path cracks due to blockage of the fuel injection manifolds.
99-07-06: This amendment adopts a new airworthiness directive (AD) that is applicable to certain Boeing Model 767 series airplanes. This action requires repetitive inspections to detect cracking or damage of the forward and aft lugs of the diagonal brace of the nacelle strut, and follow-on actions, if necessary. This action also provides optional terminating action for the repetitive inspections. This amendment is prompted by a report that a fractured diagonal brace lug was found during a routine maintenance inspection. The actions specified in this AD are intended to detect and correct cracking of the diagonal brace of the nacelle strut, which could result in failure of the diagonal brace, and consequent fatigue failure of a strut secondary load path and separation of the engine and strut.
99-04-15: This document publishes in the Federal Register an amendment adopting Airworthiness Directive (AD) 99-04-15 that was sent previously to all known U.S. owners and operators of Porsche PFM3200N01, N02, and N03 reciprocating engines by individual letters. This AD requires replacement of valve springs prior to further flight on PFM3200N01, N02, and N03 engines. This amendment is prompted by reports of six cases of undetected fatigue failures of valve springs, with one valve spring failure causing an in-flight engine failure that ended in an emergency landing. The actions specified by this AD are intended to prevent an in-flight engine shutdown due to undetected fatigue failures of valve springs.