Results
2008-23-15: We are adopting a new airworthiness directive (AD) for certain Boeing Model 767-200, -300, and -400ER series airplanes. This AD requires installing new relay(s), circuit breakers as applicable, and wiring to allow the flightcrew to turn off electrical power to the in- flight entertainment (IFE) systems and certain circuit breakers through a utility bus switch, and doing other specified actions. This AD results from an IFE systems review. We are issuing this AD to ensure that the flightcrew is able to turn off electrical power to IFE systems and other non-essential electrical systems through a switch in the flight compartment. The flightcrew's inability to turn off power to IFE systems and other non-essential electrical systems during a non-normal or emergency situation could result in the inability to control smoke or fumes in the airplane flight deck or cabin.
2009-07-07: We are adopting a new airworthiness directive (AD) for certain McDonnell Douglas Model 717-200 airplanes. This AD requires modifying the wire installation of the auxiliary hydraulic pump in the right wheel well of the main landing gear (MLG). This AD results from fuel system reviews conducted by the manufacturer. We are issuing this AD to prevent a tire burst when the MLG is in the retracted position from causing damage to the wire assembly of the auxiliary hydraulic pump and subsequent electrical arcing, creating the potential of an ignition source to the center wing tank, which, in combination with flammable fuel vapors, could result in a fuel tank explosion and consequent loss of the airplane.
2006-08-08 R1: We are adopting a new airworthiness directive (AD) to revise AD 2006-08-08, which applies to certain Air Tractor, Inc. (Air Tractor) Models AT-400, AT-401, AT-401B, AT-402, AT-402A, and AT-402B airplanes. AD 2006-08-08 currently requires you to repetitively eddy current inspect the wing lower spar cap in order to reach the safe life and, for certain Models AT-402A and AT-402B airplanes and those that incorporate or have incorporated Marburger Enterprises, Inc. (Marburger) winglets, lowers the safe life for the wing lower spar cap. Since we issued AD 2006-08-08, we have received information to update inspection intervals for the Models AT-401B, AT-402A, and AT-402B airplanes based on a revised damage tolerance analysis. Consequently, this AD would not only retain the actions of AD 2006-08-08, but would reduce the number of repetitive inspections for all affected Model AT- 401B airplanes and certain Models AT-402A and AT-402B airplanes. We are issuing this AD to prevent fatiguecracks from occurring in the wing lower spar cap before the originally established safe life is reached. Fatigue cracks in the wing lower spar cap, if not detected and corrected, could result in wing separation and loss of control of the airplane. \n\n\nDATES: This AD becomes effective on May 5, 2009. \n\tAs of April 21, 2006 (71 FR 19986, April 19, 2006), the Director of the Federal Register approved the incorporation by reference of Snow Engineering Co. Drawing 21088, dated November 3, 2004; Snow Engineering Co. Process Specification 197, page 1, revised June 4, 2002, pages 2 through 4, dated February 23, 2001, and page 5, dated May 3, 2002; and Snow Engineering Co. Service Letter 202, page 3, dated October 16, 2000, listed in this AD.
2009-07-08: We are adopting a new airworthiness directive (AD) for certain Piper Aircraft, Inc. Models PA-46-350P and PA-46R-350T airplanes. This AD requires you to inspect the 35-amp and 250-amp current limiters to verify they are installed in the proper locations and correct the installation if the current limiters are not installed in the proper locations. This AD also limits operation to "only under day visual flight rules (VFR)'' until the current limiter installation is inspected and corrected. This AD results from three reports of incorrectly installed current limiters. We are issuing this AD to detect and correct incorrect installation of 35-amp and 250-amp current limiters, which could result in failure of the 35-amp current limiter if installed in the 250-amp location. This failure could lead to a total loss of electrical power.
2009-07-06: The FAA is adopting a new airworthiness directive (AD) for Hamilton Sundstrand Propellers model 568F propellers with certain part number (P/N) and serial number (SN) blades. This AD requires removing affected propeller blades from service for rework. This AD results from reports of blades with corrosion pits in the tulip area of the blades. We are issuing this AD to prevent cracks from developing in the tulip area of the blade, which could result in separation of the blade and loss of airplane control.
86-02-05: 86-02-05 BRITISH AEROSPACE: Amendment 39-5204. Applies to Vickers Viscount Model 700 series airplanes certificated in any category. Compliance is required as follows, unless previously accomplished. To prevent nose landing gear collapse as a result of a faulty hydraulic cut out valve, accomplish the following: A. Within the next 1000 hours time-in-service or nine months after the effective date of this AD, whichever occurs first, modify the aircraft hydraulic system cut out valve, Part Number AIR 41916, in accordance with Automotive Products Modification Standard SA 3490, dated December 16, 1959 (reference BAe Technical News Sheet No. 369, Issue 1, dated August 5, 1985). B. Alternate means of compliance which provide an acceptable level of safety may be used when approved by the Manager, Standardization Branch, ANM-113, 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. All persons affected by this directive who have not already received these documents from the manufacturer may obtain copies upon request to British Aerospace Inc., Box 17414, Dulles International Airport, Washington, D.C. 20041. These documents may be examined at the FAA, Northwest Mountain Region, 17900 Pacific Highway South, Seattle, Washington, or the Seattle Aircraft Certification Office, 9010 East Marginal Way South, Seattle, Washington. This amendment becomes effective February 3, 1986.
2009-06-17: 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: Following in-flight test deployments, several Air-Driven generators (ADGs) failed to come on-line. Investigation revealed that, as a result of a wiring anomaly that had not been detected during ADG manufacture, a short circuit was possible between certain internal wires and their metallic over-braided shields, which could result in the ADG not providing power when deployed. * * * The unsafe condition is that failure of the ADG could lead to loss of several functions essential for safe flight. We are issuing this AD to require actions to correct the unsafe condition on these products.
2009-06-09: 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: \n\n\tDuring overhaul on a Dornier 328-100 landing gear unit, parts of the MLG (main landing gear) main body and trailing arm bushings have been found corroded. Investigation showed that over time, these bushings can migrate, creating the risk of corrosion in adjacent areas. Such corrosion, if not detected, could cause damage to the MLG, possibly resulting in MLG functional problems or failure. \n\n* * * * *\nFunctional problems or failure of the MLG could result in the inability of the MLG to extend or retract. We are issuing this AD to require actions to correct the unsafe condition on these products.
2009-06-08: The FAA is adopting a new airworthiness directive (AD) for certain Boeing Model 767 airplanes. This AD requires repetitive inspections for cracking of the wing skin, and related investigative/ corrective actions if necessary. This AD results from reports of cracks found in the lower wing skin originating at the forward tension bolt holes of the aft pitch load fitting. We are issuing this AD to detect and correct cracking in the lower wing skin for the forward tension bolt holes at the aft pitch load fitting, which could result in a fuel leak and reduced structural integrity of the airplane.
2009-06-10: We are adopting a new airworthiness directive (AD) for certain Boeing Model 727-100 and 727-200 series airplanes. This AD requires repetitive internal and external high frequency eddy current, mid frequency eddy current, low frequency eddy current, and magneto optic imaging inspections to detect cracks, corrosion, delamination, and materials loss in the lower fastener row of the lower skin and the upper fastener row of the upper skin, and corrective actions if necessary. This AD results from a report of decompression in a Boeing Model 737 airplane at flight level 290. We are issuing this AD to detect and correct scratches and excessive reduction in material thickness from excessive blend-out or corrosion, which could lead to premature cracking in the lap joint. Such cracking could adversely affect the structural integrity of the airplane.