Results
2021-14-20: The FAA is adopting a new airworthiness directive (AD) for all The Boeing Company Model 737 airplanes. This AD was prompted by reports of latent failures of the cabin altitude pressure switches. This AD requires repetitive functional tests of the pressure switches, and on- condition actions, including replacement, if necessary. The FAA is issuing this AD to address the unsafe condition on these products.
2004-07-04: This amendment supersedes an existing airworthiness directive (AD), applicable to certain McDonnell Douglas Model DC-9 series airplanes, that currently requires replacing the transformer ballast assembly in the pilot's console with a new, improved ballast assembly. This amendment expands the applicability of the existing AD to include additional airplanes and provides an optional method for accomplishing the requirements of the existing AD. The actions specified by this AD are intended to prevent overheating of the ballast transformers due to aging fluorescent tubes that cause a higher power demand on the ballast transformers, which could result in smoke in the cockpit. This action is intended to address the identified unsafe condition. \n\nDATES: Effective May 5, 2004. \n\n\tThe incorporation by reference of a certain publication, as listed in the regulations, is approved by the Director of the Federal Register as of May 5, 2004. \n\n\tThe incorporation by reference of a certain other publication, as listed in the regulations, was approved previously by the Director of the Federal Register as of February 8, 2002 (67 FR 497, January 4, 2002).
96-13-07: This amendment supersedes an existing airworthiness directive (AD), applicable to all Fokker Model F27 Mark 100, 200, 300, 400, 500, 600, and 700 series airplanes, that currently requires supplemental structural inspections to detect fatigue cracks, and repair or replacement, as necessary, to ensure the continued airworthiness of these airplanes. This amendment adds and revises certain significant structural items for which inspection and repair or replacement is necessary. This amendment is prompted by a structural re-evaluation conducted by the manufacturer, which identified additional structural elements where fatigue damage is likely to occur. The actions specified by this AD are intended to prevent reduced structural integrity of these airplanes.
95-25-07: This amendment adopts a new airworthiness directive (AD) that applies to certain Fairchild Aircraft SA226 series airplanes that are equipped with a part number 27-55001-229 actuator assembly. This action requires replacing the main landing gear door actuator tang and associated hardware with parts of improved design. Reports of the main landing gear doors hanging up and locking the landing gear links on the affected airplanes prompted this action. The actions specified by this AD are intended to prevent the inability to extend the main landing gear because of the main landing gear door actuation roller contacting the lower edge of the tang and causing the linkage to lock over-center.
2004-07-07: This amendment supersedes an existing airworthiness directive (AD), applicable to certain Boeing Model 757-200 series airplanes, that currently requires modifications to the attachment installation of the forward lavatory. This amendment adds airplanes to the applicability of the existing AD. The actions specified by this AD are intended to prevent failure of the attachment installation of the forward lavatory during an emergency landing, which could result in injury to the crew and passengers. This action is intended to address the identified unsafe condition. \n\nDATES: Effective May 5, 2004. \n\n\tThe incorporation by reference of Boeing Special Attention Service Bulletin 757-25-0181, Revision 1, dated November 21, 2000, as listed in the regulations, is approved by the Director of the Federal Register as of May 5, 2004. \n\n\tThe incorporation by reference of Boeing Service Bulletin 757-25- 0181, dated June 26, 1997; and Boeing Alert Service Bulletin 757- 25A0187, dated September 18, 1997; as listed in the regulations, was approved previously by the Director of the Federal Register as of June 1, 1999 (64 FR 20146, April 26, 1999).
2011-13-06: 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: Bombardier Aerospace has completed a system safety review of the aeroplanes fuel system against fuel tank safety standards introduced in Chapter 525 of the Airworthiness Manual through Notice of Proposed Amendment (NPA) 2002-043 [which corresponds with the FAA's Special Federal Aviation Regulation (SFAR) 88]. The identified non- compliances were then assessed using Transport Canada Policy Letter No. 525-001, to determine if mandatory corrective action is required. The assessment showed that a number of modifications to the fuel system are required to mitigate unsafe conditions that could result in potential ignition source within the fuel system.We are issuing this AD to require actions to correct the unsafe condition on these products.
2021-13-13: The FAA is adopting a new airworthiness directive (AD) for all \n\n((Page 38210)) \n\nLeonardo S.p.a. Model AW189 helicopters. This AD was prompted by the identification of misleading information in the emergency procedure for the ''1(2) FUEL LOW'' caution message. This AD requires revising the existing Rotorcraft Flight Manual (RFM) for your helicopter. The FAA is issuing this AD to address the unsafe condition on these products.
91-10-06: 91-10-06 BRITISH AEROSPACE (BAe): Amendment 39-6987; Docket No. 90-CE-46-AD. Applicability: Beagle B121 Pup series 1, 2, and 3 (all serial numbers) airplanes, certificated in any category. Compliance: Required within the next 30 calendar days after the effective date of this AD, unless already accomplished, and thereafter at intervals not to exceed 60 calendar months. To avoid loss of control of the airplane, accomplish the following: (a) Replace the flight control column handgrips, part number BE-45-10283, in accordance with the instructions in BAe Mandatory Pup Service Bulletin (SB) B121/95, Revision 2, dated January 28, 1991. (b) Special 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. (c) An alternative method of compliance or adjustment of the initial or repetitive compliance times that provides an equivalent level of safety may be approvedby the Manager, Brussels Aircraft Certification Office, FAA, Europe, Africa, and Middle East Office, c/o American Embassy, B-1000 Brussels, Belgium. The request should be forwarded through an appropriate FAA Maintenance Inspector, who may add comments and then send it to the Manager, Brussels Aircraft Certification Office. (d) The replacements required by this AD shall be done in accordance with British Aerospace Mandatory Pup SB B121/95, Revision 2, dated January 28, 1991. This incorporation by reference was approved by the Director of the Federal Register in accordance with 5 U.S.C. Section 552(a) and 1 CFR Part 51. Copies may be obtained from British Aerospace PLC, Manager Product Support, Commercial Aircraft Airlines Division, Prestwick Airport, Ayrshire, KA9 2RW Scotland; or British Aerospace, Inc., Librarian, Box 17414, Dulles International Airport, Washington, DC, 20041. 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, 1100 L Street, NW, Room 8401, Washington, DC. This amendment (39-6987, AD 91-10-06) becomes effective on May 22, 1991.
78-18-05: 78-18-05 PIPER AEROSTAR: Amendment 39-3295. Applies to Piper Aerostar Model 600, 601 and 601P airplanes certificated in all categories, serial numbers 150 through 520. \n\n\tCompliance required as indicated. To prevent reversed readings of left and right wing tank fuel quantity accomplish the following: \n\n\t(a)\tWithin 10 hours time in service after the effective date of this AD, unless already accomplished, with LH and RH wing tanks at least 50% depleted from tank capacity: \n\n\t\t1)\tRead and record fuel quantity indication for LH and RH wing fuel tanks. \n\n\t\t2)\tAdd 10 gallons of fuel to one wing tank only. \n\n\t\t3)\tRead and record fuel quantity for each wing tank. \n\n\t\t4)\tDetermine that the added fuel registers on the correct wing tank fuel quantity indicator selector position. \n\n\t\t5)\tIf the correct wing tank fuel quantity selector position registers the added fuel, the system is normal and no further action is required under this AD. \n\n\t(b)\tIf the appropriate wing tank fuel indicator position does not correctly register the added fuel the system may be improperly wired or the selector may be improperly indexed. In this event, prior to further flight: \n\n\t\tCorrect the fuel quantity indicating system malfunction. Refer to figure 1 for details of proper switch installation. \n\n\t(c)\tWithin 10 hours time in service after the effective date of this AD, on those airplanes with the fuel quantity indicating selector switch relabelled as an interim solution under (B)(2) of the original message of July 7, 1978, correct the fuel quantity indicating system as in (b) of this AD and revert to standard switch labelling. \n\n\t(d)\tSpecial flight permits may be issued in accordance with FARs 21.197 and 21.199 to operate aircraft to a base for accomplishment of the repair required by paragraph (b) of this AD. \n\n\t(e)\tEquivalent inspections and repairs may be used when approved by the Chief, Aircraft Engineering Division, FAA Western Region. \n\n\tThis amendment becomes effective September 13, 1978.
2004-07-05: This amendment supersedes an existing airworthiness directive (AD), applicable to certain McDonnell Douglas Model DC-9-10, DC-9-20, DC-9-30, DC-9-40, and DC-9-50 series airplanes, and C-9 (military) airplanes, that currently requires repetitive ultrasonic or magnetic particle inspections to detect cracking of the engine pylon aft upper spar straps (caps); and if necessary, replacement of the strap with a new strap, or modification of the engine pylon rear spar straps, which constitutes terminating action for the repetitive inspections. This amendment requires new, improved repetitive ultrasonic inspections, and corrective actions if necessary. This amendment also requires, among other items, a terminating action for the repetitive inspection requirements. The actions specified by this AD are intended to detect and correct fatigue cracking, which could result in major damage to the adjacent structure of the pylon aft upper spar cap, and consequent reduced structural integrity of the airplane. This action is intended to address the identified unsafe condition.