Results
97-25-15: This amendment adopts a new airworthiness directive (AD) that is applicable to certain Boeing Model 727 series airplanes. This action requires repetitive inspections to detect cracking of the rear spar web or fuel leakage of the wing center section, and repair, if necessary. This amendment also provides for an optional modification of the rear spar web that constitutes terminating action for the repetitive inspections. This amendment is prompted by several reports of fuel leakage due to cracking of the rear spar web of the wing center section. The actions specified in this AD are intended to detect and correct such cracking of the rear spar web, which could permit fuel leakage into the airflow multiplier, and could result in an electrical short that could cause a fire.
2003-03-19: This amendment adopts a new airworthiness directive (AD) that is applicable to all Boeing Model 747 series airplanes. This action requires a one-time inspection of the fuselage skin of the aft lower body for certain repair doublers, and follow-on inspections and corrective actions if such doublers are installed. For certain airplanes, this action includes optional repetitive inspections of the fuselage skin for scratches or cracking. This action is necessary to find and fix possible fatigue cracking of the fuselage skin concealed under certain repair doublers, which could result in rapid decompression of the airplane. This action is intended to address the identified unsafe condition.
72-03-02: 72-03-02 SIAI-MARCHETTI: Amendment 39-1386. Applies to Model S.205, Serial Numbers 001 through 003, 101 through 104, 106 through 108, 110 through 399, 4-101 through 4- 104, 4-106 through 4-133, 4-135 through 4-165, 4-167 through 4-202, 4-204 through 4-206, 4- 208 through 4-235, 4-237 through 4-252, 4-256 through 4-268, 4-271, 4-273, 4-274, 4-277 through 4-282, 4-285, 5-302, and 5-303; and to Model S.208, Serial Numbers 001 through 003, 1-03 through 1-12, 1-14, 1-15, 2-16 through 2-19, 2-48 through 2-50, 3-100, and 4-51 airplanes. Compliance required as indicated. To prevent structural failure of the wing front spar attachments to the fuselage frame, accomplish the following: (a) For airplanes with 500 or more hours' time in service on the effective date of this AD, within the next 100 hours' time in service after the effective date of this AD comply with paragraph (c). (b) For airplanes with less than 500 hours' time in service on the effective date of this AD, -(1) Within the next 100 hours' time in service after the effective date of this AD, and thereafter at intervals not to exceed 100 hours' time in service from the last inspection, until modified in accordance with paragraph (c), visually inspect, using a magnifying glass of at least 5 powers, the wing front spar attachments to the fuselage frame 2BIS, P/N 205-1-043-01, for cracks in accordance with SIAI-Marchetti Service Bulletin No. 205B28, dated May 11, 1971, or an FAA-approved equivalent. If cracks are found during an inspection required by this paragraph, before further flight comply with paragraph (c). (2) Before the accumulation of 600 hours' time in service comply with paragraph (c). (c) Modify both sides of the fuselage frame No. 2BIS, P/N 205-1-043-01, in accordance with SIAI-Marchetti Service Bulletin No. 205B28, dated May 11, 1971, or an FAA- approved equivalent. This amendment becomes effective February 25, 1972.
2011-21-02: 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 flight tests, unexpected fatigue high loads were measured on the hinges integrated on the 12 o'clock beam which form the upper extreme edge of the thrust reverser unit C duct. This situation, if not corrected, could lead to the separation of the thrust reverser from the aeroplane and therefore to damage of the aeroplane and hazards to persons or property on the ground. * * * * * This AD requires actions that are intended to address the unsafe condition described in the MCAI.
2003-03-20: This amendment adopts a new airworthiness directive (AD), that is applicable to Hartzell Propeller Inc. model HC-C2YR-4CF propellers. This amendment requires the reduction of the original hub and blades certified service (fatigue) life from unlimited hours to 2,000 hours. This amendment is prompted by a reevaluation by Hartzell Propeller Inc. of the original hub and blades service life certification calculations. The actions specified by this AD are intended to prevent fatigue failure of the original propeller hub and blades which may result in loss of airplane control.
2011-21-03: We are adopting a new airworthiness directive (AD) for the products listed above. This AD requires installing foreign object debris (FOD) rubber shields over the primary and secondary external power connectors for certain airplanes, and wrapping silicone tape around the hydraulic tube for certain other airplanes. This AD was prompted by a report of a fire in the main equipment center due to failure of an external power connector, which \n\n((Page 63164)) \n\ncaused high-temperature arcing and subsequent splatter of molten copper on an adjacent hydraulic tube, creating a hole in the tube and spraying hydraulic fluid into the power connector, resulting in a fire. In addition there were several reports of overheating or arcing of external power connectors, and one report of a fire due to arcing caused by FOD. We are issuing this AD to prevent FOD from entering the primary and secondary external power connectors, which could result in overheating or arcing and consequent fire in the main equipment center.
2003-03-11: This amendment adopts a new airworthiness directive (AD) that is applicable to a certain Air Cruisers Company Emergency Evacuation Slide/Raft System. This amendment requires a one-time unpacking and subsequent repacking of the slide/raft system, identified by serial numbers (SN's), and mandates repacking of all other slide/raft systems of the same design at the next required normal maintenance schedule of the slide/raft system. This amendment is prompted by reports of separation of the lower aspirator during a number of deployments. The actions specified by this AD are intended to prevent failure of the slide/raft to properly inflate, which could impede the emergency evacuation of passengers in the event of an airplane emergency.
69-03-04: 69-03-04 SLINGSBY: Amdt. 39-721. Applies to Slingsby Model T.53B Gliders. Compliance required within the next 25 hours' time in service after the effective date of this AD, unless already accomplished. To prevent interference between the elevator control lever and its support bracket, replace the existing bracket P/N 53B-10-81 with new bracket P/N 53B-10-1117 in accordance with Slingsby Technical Instruction No. 36, dated November 1968, or later ARB-approved issued or an FAA approved equivalent. This amendment becomes effective February 14, 1969.
97-24-12: This amendment supersedes an existing airworthiness directive (AD), applicable to all British Aerospace Model BAC 1-11 200 and 400 series airplanes, that currently requires a one-time inspection to determine the tension of the control cables of the thrust reversers, and to detect breakage, damage, wear, or signs of corrosion; and corrective actions, if necessary. This amendment requires that the inspections be repeated at certain intervals. This amendment is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified by this AD are intended to prevent failure of the control cables, which may lead to the inability of the thrust reverser to deploy and/or an uncommanded deployment of the thrust reverser while the airplane is in flight.
56-26-04: 56-26-04 VICKERS-ARMSTRONG: Applies to All Viscount Model 745D Aircraft. Compliance required as indicated. Service experience has indicated that cracks may develop in certain pre-Modification D.1031 engine nacelle attachment brackets. Accordingly, Vickers-Armstrong (Aircraft) Ltd. issued Preliminary Technical Leaflet No. 111, Issue 1, dated October 19, 1956, covering this subject. The British Air Registration Board considers the inspections recommended therein mandatory, in which the FAA concurs. When brackets to Mod. D.1031 are installed, the special inspections detailed in PTL No. 111 do not apply. This supersedes AD 55-22-05.