Results
2007-16-17: The FAA is superseding an existing airworthiness directive (AD), which applies to certain Airbus Model A300-600, A310-200, and A310-300 series airplanes. That AD currently requires inspecting for certain serial numbers on elevators, and doing a detailed inspection, visual inspection with a low-angle light, and tap-test inspection of the upper and lower surfaces of the external skins on certain identified elevators for any damage (i.e., debonding of the graphite fiber reinforced plastic/Tedlar film protection, bulges, debonding of the honeycomb core to the carbon fiber reinforced plastic, abnormal surface reflections, and torn-out plies), and doing corrective actions if necessary. This new AD also requires inspecting for damage of the identified elevators in accordance with a new repetitive inspection program, at new repetitive intervals; and would provide an optional terminating action for the repetitive inspections. This AD results from reports of damage caused by moisture/water inside the elevator. We are issuing this AD to detect and correct debonding of the skins on the elevators, which could cause reduced structural integrity of an elevator and reduced controllability of the airplane. DATES: This AD becomes effective September 18, 2007. The Director of the Federal Register approved the incorporation by reference of certain publications listed in the AD as of September 18, 2007. On February 3, 2006 (70 FR 77301, December 30, 2005), the Director of the Federal Register approved the incorporation by reference of Airbus All Operators Telex A300-600-55A6032, dated June 23, 2004; and Airbus All Operators Telex A310-55A2033, dated June 23, 2004.
76-03-05: 76-03-05 BEECH: Amendment 39-2510. Applies to Models 35-B33, 35-C33, E-33, F-33 and G-33 (Serial Numbers CD-388 thru CD-981 and CD-983 thru CD-1304); and Model P-35 (Serial Numbers D-6842 thru D-7139 and D-7141 thru D-7309) airplanes. Compliance: Required as indicated unless already accomplished. To preclude contact of the tachometer cable housing with the battery relay, within the next 50 hours' time in service after the effective date of this AD, install a tachometer cable housing stand-off bracket on the battery box and secure the tachometer cable housing to this bracket in accordance with Beechcraft Service Instruction No. 0784-241 or later FAA-approved revisions or by any equivalent method approved by the Chief, Engineering and Manufacturing Branch, FAA, Central Region. This amendment becomes effective February 17, 1976.
95-17-14: This amendment adopts a new airworthiness directive (AD) that is applicable to certain Bombardier Model CL-600-1A11, CL-600-2A12, and CL-600-2B16 series airplanes. This action requires functional testing of the brake of the horizontal stabilizer trim actuator (HSTA); and exercising the pitch trim system, revising the FAA-approved Airplane Flight Manual (AFM), operational testing of the HSTA, and replacing the HSTA or horizontal stabilizer trim control unit, if necessary. This amendment is prompted by reports of overspeed annunciation of the pitch trim due to slippage of the no-back device on the HSTA. The actions specified in this AD are intended to prevent uncommanded movement of the HSTA due to failure of the no-back device on the HSTA to operate properly; this condition could adversely affect the controllability of the airplane.
2007-16-08: The FAA is superseding an existing airworthiness directive (AD), which applies to all Boeing Model 747-100, 747-100B, 747-100B SUD, 747-200B, 747-200C, 747-300, 747-400, 747-400D, and 747SR series airplanes. That AD currently requires repetitive inspections for cracking of the station 800 frame assembly, and repair if necessary. This new AD revises certain applicabilities and compliance times in the existing AD. This AD results from several reports of cracks of the station 800 frame assembly on airplanes that had accumulated fewer total flight cycles than the initial inspection threshold in the original AD. We are issuing this AD to detect and correct fatigue cracks that could extend and fully sever the frame, which could result in development of skin cracks that could lead to rapid depressurization of the airplane. \n\n\nDATES: This AD becomes effective September 13, 2007. \n\n\tOn July 17, 2006 (71 FR 33595, June 12, 2006), the Director of the Federal Register approved the incorporation by reference of Boeing Alert Service Bulletin 747-53A2451, Revision 1, dated November 10, 2005. \n\n\tOn August 30, 2001 (66 FR 38891, July 26, 2001), the Director of the Federal Register approved the incorporation by reference of Boeing Alert Service Bulletin 747-53A2451, including Appendix A, dated October 5, 2000.
90-05-07: 90-05-07 BRITISH AEROSPACE: Amendment 39-6526. Docket No. 89-NM-232-AD. Applicability: Model BAe 146-200A and -300A series airplanes, equipped with Modification HCM30107C and HCM30300A, as listed in British Aerospace Inspection Service Bulletin 25-A157, dated August 14, 1989, certificated in any category. Compliance: Required within 30 days after the effective date of this AD, unless previously accomplished. To ensure unrestricted passage of air from above the cabin floor to below the floor in the event of rapid decompression, accomplish the following: A. Inspect the cabin insulation bags between frames 19 to 26, and frames 32 to 40, inclusive, both left and right sides of the cabin, to ensure the lower edge of the insulation bag is 4 inches above the level of the floor structure, in accordance with British Aerospace Service Bulletin 25-A157, dated August 14, 1989. 1. If sufficient clearance is found, reassemble parts and return the airplane to service.2. If insufficient clearance is found, prior to further flight, modify the insulation bags by folding under the lower edge and securing the insulation bags, in accordance with the service bulletin. B. An alternate means of compliance or adjustment of the compliance time, which provides an acceptable level of safety, may be used when approved by the Manager, Standardization Branch, ANM-113, FAA, Northwest Mountain Region. NOTE: The request should be forwarded through an FAA Principal Maintenance Inspector (PMI), who will either concur or comment and then send it to the Manager, Standardization Branch, ANM-113. C. Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes to a base in order to comply with the requirements of this AD. All persons affected by this directive who have not already received the appropriate service documents from the manufacturer may obtain copies upon request to British Aerospace, Librarian for Service Bulletins, P.O. Box 17414, Dulles International Airport, Washington, D.C. 20041. These documents may be examined at the FAA, Northwest Mountain Region, Transport Airplane Directorate, 17900 Pacific Highway South, Seattle, Washington, or the Standardization Branch, 9010 East Marginal Way South, Seattle, Washington. This amendment (39-6526, AD 90-05-07) becomes effective on April 9, 1990.
2007-15-05: The FAA is adopting a new airworthiness directive (AD) for all transport category airplanes identified above. This AD requires an inspection to determine if a certain fuel pump housing electrical connector is installed. This AD also requires a revision to the FAA- approved airplane flight manual (AFM) to advise the flightcrew of the appropriate procedures for disabling certain fuel pump electrical circuits following failure of a fuel pump housing electrical connector if applicable. This AD also requires the deactivation of certain fuel tanks or fuel pumps and the installation of placards if applicable. This AD allows the optional replacement of the fuel pump housing electrical connectors with new, improved parts, which would terminate the AFM revisions, deactivation of certain fuel tanks and fuel pumps, and placard installation. This AD results from a report of two failures of the fuel pump housing electrical connector. We are issuing this AD to prevent continued arcing following a short circuit of the fuel pump housing electrical connector, which could damage the conduit that protects the power lead inside the fuel tank; this condition could create an ignition source inside the fuel tank, which, in combination with flammable fuel vapors, could result in a fuel tank explosion and consequent loss of the airplane.
78-01-08: 78-01-08 BOEING: Amendment 39-3113. Applies to all Model 727 series airplanes certificated in all categories with autospeed brake system installed and airplanes with auto wheel brakes in conjunction with JT8D-17R engines and Boeing automatic throttle clutches, except airplanes with Engine Pressure Ratio (EPR) activated takeoff warning system. \n\tCompliance required as indicated. \n\tWithin 2000 hours time in service after the effective date of this AD, unless already accomplished, set the thrust lever operated switches S197, S784, S553, and S555 to provide actuation down to and including -65 degrees F per applicable part of Boeing Service Bulletin 727-31-30, or later FAA approved revisions, or equivalent approved by the Chief, Engineering and Manufacturing Branch, FAA Northwest Region.\n \tFor airplanes which have automatic throttles not designed by Boeing, the modification kits available from Boeing may not be applicable. Operators of those airplanes must submit their proposed modifications to the Chief, Engineering and Manufacturing Branch, FAA Northwest Region, 9010 East Marginal Way South, Seattle, Washington 98108. \n\n\tThis amendment becomes effective January 16, 1978.
96-22-15: This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A310 and A300-600 series airplanes, that requires repetitive Tap Test inspections to detect debonding of the elevator skins, and corrective actions, if necessary. This amendment is prompted by a report of a debonded area of the upper skin of an elevator that was discovered during a visual inspection. The actions specified by this AD are intended to prevent the presence of water in the elevator, which could cause debonding of the elevator skins and, consequently, adversely affect the structural integrity of the elevator.
2007-13-09: The FAA is adopting a new airworthiness directive (AD) for certain McDonnell Douglas Model 717-200 airplanes. This AD requires modifying the fuel boost pump container of the center tank. This AD results from fuel system reviews conducted by the manufacturer. We are issuing this AD to prevent exposing the fuel pump container vapor area to electrical arcing during a fuel pump motor case or connector burn through, which could result in a fuel tank explosion.
96-07-04: This amendment adopts a new airworthiness directive (AD), applicable to certain Fokker Model F27 Mark 050 and Model F28 Mark 0100 series airplanes, that requires an inspection to verify that adequate clearance exists between the insulation screen and the two adjacent terminal bolts, and replacement of the circuit breaker terminal bolts with new bolts, if necessary. This amendment is prompted by a report that circuit breaker terminal bolts that were too long were discovered installed in the circuit breaker panels. The actions specified by this AD are intended to prevent damage to the insulation screen between adjacent rows of circuit breakers, as the result of a circuit breaker terminal bolt being too long; this condition could lead to electrical arcing and loss of the associated electrical system, which could result in the potential for an electrical fire.