Results
96-18-03: This amendment adopts a new airworthiness directive (AD), applicable to certain Saab Model SAAB SF340A and SAAB 340B series airplanes, that requires installation of an automatic flight idle stop on the control quadrant in the flight compartment. This amendment is prompted by several reports of one or both power levers being moved aft of the flight idle stop on approach. The actions specified by this AD are intended to prevent such movement of the power lever(s) during flight, which could result in the loss of power to one or both engines, as well as severe engine damage.
2011-12-05: We are adopting a new airworthiness directive (AD) for the products listed above. This AD requires replacing the existing unshielded fuel quantity indication system (FQIS) wire bundles with double shielded FQIS wire bundles, installing a new wire feed-through fitting, and grounding the wire shields, as applicable; and doing repetitive low frequency eddy current (LFEC) inspections for cracking of the fuselage skin, and corrective actions if necessary. This AD also requires revising the maintenance program to incorporate certain airworthiness limitations. This AD was prompted by fuel system reviews conducted by the manufacturer. We are issuing this AD to increase the level of protection from lightning strikes and prevent the potential of ignition sources inside fuel tanks, which, in combination with flammable fuel vapors, could result in fuel tank explosions and consequent loss of the airplane.
2011-12-01: We are adopting a new airworthiness directive (AD) for the products listed above. This AD requires determining if affected seats and seating systems and their components are compliant with certain FAA regulations, and removing those seats, seating systems, and their components that are shown to be unsafe from the affected fleet. This AD was prompted by a determination that the affected seats and seating systems may not meet certain flammability, static strength, and dynamic strength criteria. Failure to meet static and dynamic strength criteria could result in injuries to the flightcrew and passengers during emergency landing conditions. In the event of an in-flight or post- emergency landing fire, failure to meet flammability criteria could result in an accelerated fire. We are issuing this AD to prevent accelerated fires and injuries to the flightcrew and passengers.
96-18-02: This amendment supersedes Airworthiness Directive (AD) 96-03-11, which currently requires the following on American Champion Aircraft Corporation (American Champion) Models 8KCAB, 8GCBC, 7GCBC, and 7ECA airplanes that are equipped with metal spar wings: inspecting (one-time) the wing front strut attach fittings for cracks, scratches, or surface deformities; replacing any wing front strut attach fitting with cracks, scratches, or surface deformities; and reporting the inspection results to the Federal Aviation Administration (FAA). This action results from reports submitted as a requirement of the existing AD that reference 24 fittings with cracks, scratches, or surface deformities on 7 different airplanes, and the FAA's determination that improved wing front strut attach fittings (developed by American Champion) are not susceptible to cracks, scratches, or surface deformities. This action requires installing removable inspection hole covers for the wing front strut attachfittings, and replacing the wing front strut attach fittings with fittings of improved design. The action also provides the provision of repetitively inspecting the wing front strut attach fittings (provided no cracks, scratches, or surface deformities are found) if parts have been ordered but are not available. The actions specified by this AD are intended to prevent structural failure of a wing caused by cracked wing front strut attach fittings, which, if not detected and corrected, could result in loss of control of the airplane.
96-17-13: This amendment adopts a new airworthiness directive (AD), applicable to certain Beech (Raytheon) Model BAe 125 series 1000A and Model Hawker 1000 airplanes, that requires a one-time inspection for correct sleeve lengths, an inspection to detect discrepancies of the elevator pulley assembly, and correction of any discrepancy. This amendment is prompted by reports indicating that some aircraft have been fitted with an elevator pulley that was assembled incorrectly during manufacture. The actions specified by this AD are intended to prevent reduced structural integrity of the elevator control circuit due to failure of one or more outer lugs or malfunction of the elevator pulley assembly as a result of incorrect assembly of the pulley.
2022-01-01: The FAA is adopting a new airworthiness directive (AD) for all Airbus Helicopters Model AS350B, AS350BA, AS350B1, AS350B2, AS350B3, AS350D, EC130B4, and EC130T2 helicopters; AS355E, AS355F, AS355F1, AS355F2, AS355N, and AS355NP helicopters; and Model SA-365C1, SA-365C2, SA-365N, SA-365N1, AS-365N2, and AS 365 N3 helicopters. This AD was prompted a report of increased vibration during flight. This AD requires the application of alignment markings on, and repetitive inspections of, the main rotor (MR) pitch rod upper links and, depending on findings, the accomplishment of applicable corrective actions, as specified in a European Union Aviation Safety Agency (EASA) AD, which is incorporated by reference. The FAA is issuing this AD to address the unsafe condition on these products.
93-25-01: 93-25-01 DE HAVILLAND, INC.: Amendment 39-8767. Docket 93-NM-91-AD. Applicability: Model DHC-8-311 series airplanes, serial numbers 240 through 279 inclusive, certificated in any category. Compliance: Required as indicated, unless accomplished previously. To prevent failure of the left- and right-hand underwing fairing angles, which could result in reduced structural integrity of the wing-to-fuselage attachment, accomplish the following: (a) Prior to the accumulation of 6,830 total landings, or within 100 landings after the effective date of this AD, whichever occurs later, perform a detailed visual inspection to detect cracking on the rear face of the left- and right-hand underwing fairing angles, having part number 85350927, in accordance with de Havilland Alert Service Bulletin S.B. A8-53-46, Revision 'A', dated May 25, 1993. (1) If no cracked fairing angle is found, repeat the inspection thereafter at intervals not to exceed 6,930 landings, in accordance with the service bulletin. (2) If any cracked fairing angle is found, prior to further flight, replace the cracked fairing angle with a new, non-reworked fairing angle, having part number 85350927-107SP or 85350927-108SP, in accordance with the service bulletin. (b) Replacement of the currently-installed left- and right-hand underwing fairing angles with new, non-reworked fairing angles, having part number 85350927-107SP or 85350927-108SP, in accordance with de Havilland Alert Service Bulletin S.B. A8-53-46, Revision 'A', dated May 25, 1993, constitutes terminating action for the repetitive inspection requirement of paragraph (a)(1) of this AD. (c) An alternative method of compliance or adjustment of the compliance time that provides an acceptable level of safety may be used if approved by the Manager, New York Aircraft Certification Office (ACO), FAA, Engine and Propeller Directorate. Operators shall submit their requests through an appropriate FAA Principal Maintenance Inspector, who may add comments and then send it to the Manager, New York ACO. NOTE: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the New York ACO. (d) Special flight 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. (e) The inspections and replacement shall be done in accordance with de Havilland Alert Service Bulletin S.B. A8-53-46, Revision 'A', dated May 25, 1993. This incorporation by reference was approved by the Director of the Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR Part 51. Copies may be obtained from de Havilland, Inc., Garratt Boulevard, Downsview, Ontario M3K 1Y5, Canada. Copies may be inspected at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; or at the FAA, Engine and Propeller Directorate, New York Aircraft Certification Office, 181 South Franklin Avenue, Room 202, Valley Stream, New York; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC. (f) This amendment becomes effective on January 19, 1994.
84-20-08: 84-20-08 GULFSTREAM AEROSPACE CORPORATION: Amendment 39-4927. Applies to Model G-159 airplanes certificated in all categories. Compliance required as indicated, unless already accomplished. To detect and prevent corrosion or failure of the forward and aft engine mount assemblies, Vickers Drawing Number 81037, Sheet 29, and Gulfstream Aerospace Drawing Numbers 159W10432-1 (L/H) and 159W10432-3 (R/H), respectively, accomplish the following unless already accomplished: (a) Within 200 hours time in service or four months after the effective date of this AD, whichever is sooner, inspect the forward and aft engine mounts, L/H and R/H, in accordance with Gulfstream I Customer Bulletin (CB) Number 241C, dated July 10, 1984, or in an equivalent manner approved by the Manager, Atlanta Aircraft Certification Office, FAA, Central Region. (b) If corrosion is indicated: (1) Replace corroded tubes in accordance with Customer Bulletin 241C before further flight, then revert to the inspections required under Category A, as stated in paragraph (d), below; or (2) If continued flight is desired, ascertain the remaining wall thickness of the corroded tubes and categorize in accordance with Customer Bulletin No. 241C, and perform the operations for each category as indicated by paragraph (d), below. (c) If corrosion is not indicated, perform the operations described in paragraph (d), below, for Category A. (d) Category A - Reinspect as in paragraph (a) of this AD for corrosion at intervals not exceeding six years from last inspection. Category B - Treat the tubes within 50 hours time in service in accordance with Addendum 1 or 4 of Customer Bulletin 241C and reinspect for corrosion as in paragraph (a) of this AD at annual intervals for at least two years after treatment. If there are no changes in the thickness measurements, reinspect at intervals not exceeding two years. Categories C and D - Replace corroded tubes in accordancewith Customer Bulletin 241C within 150 hours time in service or three months, whichever is sooner; then revert to the inspections required under Category A. Category E - Replace corroded tubes in accordance with Customer Bulletin 241C before further flight; then revert to inspections required under Category A. (e) To prevent failure of Category B Gulfstream "Grumman mounts," replace the mounts prior to the accumulation of 7500 landings or within the next 25 landings, whichever occurs later within the following time period, in accordance with Gulfstream Aerospace Corporation Gulfstream I Customer Bulletin No. 241C, dated July 10, 1984, or equivalent manner approved by the Manager, Atlanta Aircraft Certification Office, FAA, Central Region: (1) For airplanes that have accumulated 7500 landings prior to the effective date of this AD, within the next 25 landings after the effective date of this AD; (2) For airplanes with less than 7500 landings on the effective date of this AD, within the next 25 landings after the accumulation of 7500 landings. (f) To qualify for service beyond 7500 landings, Category A Gulfstream "Grumman mounts" must accomplish paragraph (g), below, within the following period: (1) For airplanes that have accumulated 7500 landings prior to the effective date of this amendment, within the next 30 days or within 12 months of the last successful mount inspection in accordance with Gulfstream Aerospace Corporation Gulfstream I Customer Bulletin 289, Amendment 1, dated 26 May 1977, whichever occurs later, or (2) For airplanes with less than 7500 landings on the effective date of this amendment, no later than the next 30 days after the accumulation of 7500 landings. (g) Perform the ultrasonic and visual inspections in accordance with Gulfstream Aerospace Corporation Gulfstream I Inspection Schedule, Section V, Special Inspections, Engine Mounts, dated July 31, 1984, or in an equivalent manner approved by theManager, Atlanta Aircraft Certification Office, FAA, Central Region. If the inspections indicate negligible or no corrosion and no cracks, then the Grumman mount initially qualifies for the 20,000 landing life limit in accordance with Gulfstream Aerospace Corporation Gulfstream I Inspection Schedule, Section IV, Life Limited Components, dated July 31, 1984, and is no longer required to comply with the inspection requirements of paragraph (a) of this AD. Throughout this extended life limit, the inspections must be repeated at intervals not to exceed 12 months to maintain qualification for the 20,000 landing life limit. If, during such inspection, any mount subassemblies are found to have negligible or no internal corrosion and no cracks, those subassemblies may continue to be used if a detailed record of each life limited subassembly usage is maintained by the operator. If any inspection indicates the presence of unacceptable internal corrosion, replace the affected mount subassembly within the next 25 landings or 30 days, whichever occurs first. If a mount crack is found by any inspection, notify Gulfstream Aerospace Corporation, Technical Services Department, for dispositon before further flight. All life limited subassemblies that are not replaced during the repetitive inspections must be replaced by the end of the 20,000 landing life limit established by Gulfstream Aerospace Corporation Gulfstream I Inspection Schedule dated July 31, 1984. All persons affected by this directive who have not already received these documents from the manufacturer may obtain copies upon request to Gulfstream Aerospace Corporation, P.O. Box 2206, Savannah, Georgia 31402. These documents also may be examined at the FAA, Northwest Mountain Region, 17900 Pacific Highway South, Seattle, Washington. This supersedes Airworthiness Directive 74-03-01, Amendment 39-3667 (38 FR 23962). This amendment becomes effective January 22, 1985.
2021-26-27: The FAA is adopting a new airworthiness directive (AD) for certain Airbus Canada Limited Partnership Model BD-500-1A10 and BD-500- 1A11 airplanes. This AD was prompted by a report indicating that during production, the manual opening and closing of the over-wing emergency exit door (OWEED) prior to the installation of the OWEED interior panel could have resulted in damaged insulation blankets below the left and right OWEEDs. This AD requires a one-time inspection for damage of the insulation blankets below the left and right OWEEDs, and replacement if necessary, as specified in a Transport Canada Civil Aviation (TCCA) AD, which is incorporated by reference. The FAA is issuing this AD to address the unsafe condition on these products.
96-17-05: This amendment adopts a new airworthiness directive (AD) that is applicable to certain Saab Model SAAB SF340A and SAAB 340B series airplanes. This action requires the installation of a mechanical flight idle stop on the control quadrant of the flight compartment. This action also requires a revision of the Airplane Flight Manual to ensure the use of certain operating procedures after the mechanical flight idle stop is installed. Additionally, this action provides an optional terminating action for the requirements of this AD. This amendment is prompted by a report indicating that the means of protection against the selection of the "beta" range of propeller operation during flight has been reduced on certain modified control quadrants. Additionally, there have been reports indicating that power levers on the control quadrant have been moved aft of the flight idle position during flight due to improper usage of the mechanical beta stop. The actions specified in this AD areintended to prevent such movement of the power lever(s) during flight, which could result in propeller overspeed, engine damage, and loss of power to one or both engines.