Results
2007-07-13: 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: Avionics and electrical wire harnesses are routed behind the Primary Flight Displays (PFD) tray at the rear of the instrument panel. In some cases, the wire harness has been found to be chafing on the PFD tray. That could result in electrical arcing and shorting and subsequent loss of systems essential for safe flight. This AD requires actions that are intended to address the unsafe condition described in the MCAI.
2000-24-07: This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 747 series airplanes, that requires inspections to detect cracking of the frame web, doubler, and inner chord of the forward edge frame of main entry door number 1, and various follow-on actions. This amendment is prompted by reports of cracking in the frame web, doubler, inner chord, and strap of the forward edge frame of main entry door number 1. The actions specified by this AD are intended to prevent cracks in the frame web and doubler of the forward edge frame of main entry door number 1, which could result in inability of the edge frame to react door stop loads, and consequent rapid depressurization of the airplane.
2017-26-04: We are superseding Airworthiness Directive (AD) 2009-25-07 for Airbus Helicopters Model EC120B helicopters. AD 2009-25-07 required amending the rotorcraft flight manual supplement (RFMS) and pre-flight checking the emergency flotation gear before each flight over water. Since we issued AD 2009-25-07, Airbus Helicopters developed a terminating action and identified an additional part- [[Page 60293]] numbered emergency floatation gear part with the unsafe condition. This new AD retains the requirements of AD 2009-25-07, expands the applicability, and adds a terminating action for the repetitive inspections. The actions of this AD are intended to correct an unsafe condition on these helicopters.
87-02-04: 87-02-04 BRITISH AEROSPACE: Amendment 39-5497. Applies to Models HP 137 Mk.1 (all serial numbers), Jetstream Series 200 (all serial numbers), and Jetstream Model 3101 airplanes (serial numbers 601 to 606) equipped with Main Landing Gear Type Numbers 1863 and 1864 (all suffixes), certificated in any category. Compliance: Required as indicated after the effective date of this AD, unless already accomplished. To prevent the development of hazardous cracks in the main landing gear pintle housing, accomplish the following: (a) Within 300 landings and every 1200 landings thereafter: Conduct an eddy current inspection in accordance with Section 2 "Accomplishment Instructions", Part A "Non- destructive Testing" of British Aerospace (BAe) Mandatory Service Bulletin (MSB) No. 32-A- JA851226 dated December 19, 1985, Section 2 "Accomplishment Instructions" of BAe Air Weapons Division (AWD) Service Bulletin (S/B) No. 32-19 dated December 19, 1985. If cracks are found, before further flight, carry out repairs in accordance with AWD S/B No. 32-19. (b) At intervals of 300 landings after the initial inspection, required by paragraph (a) of this AD, conduct a visual inspection in accordance with Section 2 "Accomplishment Instructions," Part B, "Visual Inspections" of AWD S/B No. 32-19. If indications of cracks are discovered, conduct an eddy current inspection in accordance with paragraph (a) of this AD. If cracks are found, before further flight, carry out repairs in accordance with AWD S/B No. 32-19. (c) Within 300 landings after a heavy or abnormal landing, conduct an eddy current inspection in accordance with paragraph (a) of this AD. (d) If the actual number of landings is unknown for the purpose of complying with this AD, one landing may be substituted for each one-half hour of flight unless the operator substantiates a different flight hours to landings ratio. This substantiation must be submitted to, and approved by, the Manager, Aircraft Certification Staff, address below. (e) Airplanes may be flown in accordance with FAR 21.197 to a location where this AD may be accomplished. (f) The intervals between the repetitive inspections required by this AD may be adjusted up to 10 percent of the specified interval to allow accomplishment of these inspections concurrent with other scheduled maintenance on the airplane. (g) An equivalent means of compliance with this AD may be used if approved by the Manager, Aircraft Certification Staff, AEU-100, Europe, Africa and Middle East Office, FAA, c/o American Embassy, B-1000 Brussels, Belgium. All persons affected by this directive may obtain copies of the documents referred to herein upon request to British Aerospace, Engineering Department, P.O. Box 17414, Dulles International Airport, Washington, D.C. 20041; Telephone (703) 435-9100; or FAA, Office of the Regional Counsel, Room 1558, 601 East 12th Street, Kansas City, Missouri 64106. This amendment becomes effective on January 30, 1987.
2007-07-14: The FAA is adopting a new airworthiness directive (AD) for all Empresa Brasileira de Aeronautica S.A. (EMBRAER) Model EMB-135BJ airplanes. This AD requires modifying the forward and aft auxiliary fuel tanks. This AD results from a fuel system reassessment according to SFAR 88 criteria, which revealed the possibility of sparks due to chafing between the harnesses of the forward and aft auxiliary fuel tanks, between certain harnesses attached to the aircraft structure, or between certain harnesses attached to certain mechanical components. We are issuing this AD to prevent a potential ignition source inside a fuel tank, which, in combination with flammable fuel vapors, could result in a fuel tank explosion.
2000-24-20: This amendment adopts a new airworthiness directive (AD), applicable to all Boeing Model 707 and 720 series airplanes, that requires repetitive inspections of certain stringers and around certain fastener holes of the lower skin of the wings to detect fatigue cracking, and repair, if necessary. This action is necessary to detect and correct such cracking and consequent damage to adjacent structure, which could result in reduced structural integrity of the airplane. This action is intended to address the identified unsafe condition.
2000-24-17: This amendment supersedes an existing airworthiness directive (AD), applicable to certain McDonnell Douglas Model MD-11 series airplanes, that currently requires deactivation of the forward and center cargo control units (CCU). This amendment requires, among other actions, a general visual inspection to verify that all six external connectors of suspect CCU's have a certain part number stamped on the connector bodies on all CCU assemblies, and follow-on actions, which would constitute terminating action for the deactivation requirements. The actions specified by this amendment are intended to prevent overheating of the electrical pins inside the CCU's and subsequent release of hot gases and flames, which could result in smoke and fire in the cargo compartment.
2011-08-08: 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: It has been found occurrence of screw units manufactured with metallographic non-conformity that may increase their susceptibility to brittle fracture. The screw failure may result in loss of the related balance washer causing a possible ram air turbine (RAT) imbalance event, which may result in RAT structural failure, which associated with an electrical emergency situation, could result in loss of power to airplane flight controls hydraulic back-up system. * * * * * Loss of power to the hydraulic back-up system for airplane flight controls could reduce the ability of the flightcrew to maintain the safe flight and landing of the airplane. We are issuing this AD to require actions to correct the unsafe condition on these products. [[Page 20504]]
2007-07-06: The FAA is adopting a new airworthiness directive (AD) for Columbia Aircraft Manufacturing (previously The Lancair Company) Models LC40-550FG, LC41-550FG, and LC42-550FG airplanes. This AD requires you to add information to the Limitations section of the Airplane Flight Manual (AFM). This AD also requires you to repetitively inspect the aileron and the elevator linear bearings and control rods for foreign object debris, scarring, or damage and take all necessary corrective actions. This AD results from reports of possible foreign object contamination of the linear bearings. We are issuing this AD to prevent jamming in the aileron and elevator control systems, which could result in failure. This failure could lead to loss of control.
80-02-15: 80-02-15 PIPER: Amendment 39-3676. Applies to Model PA-31P, Serial Nos. 31P-1 thru 31P-7730012, Model PA-31T, Serial Nos. 31T-7400002 thru 31T-7920075 and Model PA- 31T1, Serial Nos. 31T-7804001 thru 31T-7904036 and 31T-7904038 thru 31T-79O4044 certificated in all categories except aircraft incorporating Piper Kit No. 763 943. To prevent possible hazards in flight associated with cracks in the elevator butt ribs and adjoining area accomplish the following: a. Within the next 100 hours in service from the effective date of this AD or upon the attainment of 400 hours in service, whichever is later, inspect and alter the elevators in accordance with Piper Kit No. 763 943 or equivalent. b. Equivalent inspections or alterations must be approved by the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region. c. Upon submission of substantiating data by an owner or operator through an FAA Maintenance Inspector, the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region may adjust the inspection intervals specified in this AD. (Piper Service Bulletin No. 658 dated July 31, 1979, refers to this subject.) This amendment is effective January 29, 1980.