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2011-16-02: We are adopting a new airworthiness directive (AD) for the products listed above. This AD requires revising the airplane flight manual (AFM) to advise the flightcrew to use certain procedures during descent in certain icing conditions. This AD was prompted by reports of several in-flight engine flameouts, including multiple dual engine flameout events and one total power loss event, in ice-crystal icing conditions. We are issuing this AD to ensure that the flightcrew has the proper procedures to follow in certain icing conditions. These certain icing conditions could cause a multiple engine flameout during flight with the potential inability to restart the engines, and consequent forced landing of the airplane.
2018-03-04: We are adopting a new airworthiness directive (AD) for Rosemount Aerospace Model 851AK pitot probes that were repaired by CSI Aerospace, Inc. between January 2013 and July 2014 that are installed on airplanes. This AD was prompted by a report that certain pitot probes are indicating the wrong airspeed during flight. This AD requires inspecting the airplane to determine the number of affected pitot probes installed and replacing the affected pitot probes. We are issuing this AD to address the unsafe condition on these products.
2003-02-06: This amendment adopts a new airworthiness directive (AD) for Bell Helicopter Textron Canada Limited (Bell) Model 407 helicopters. This action requires visually inspecting certain tailboom gearbox support castings (castings) for cracks and replacing the tailboom assembly if a crack is found. This amendment is prompted by an incident in which a crack was discovered on the casting that holds the tail rotor gearbox and vertical fin. The actions specified in this AD are intended to detect a crack in the casting and prevent failure of the casting, loss of the vertical fin and tail rotor, and subsequent loss of control of the helicopter.
49-41-01: 49-41-01 LOCKHEED: Applies to All Models 649, 749 and 749A Aircraft Equipped With Curtiss Model C632S-A Propellers and Wright Model 749C18BD-1 Engines. Compliance required on items 1, 2 and 3 by October 11, 1949. In order to reduce the possibility of subjecting propellers to excessive stresses and to detect hub cracks which may have been caused by such stresses, the following steps are to be taken: 1. Change present 2,100-2,375 r.p.m. restriction to 2,050-2,375. Placard airplane or mark tachometer with green radial line for single point operation at 2,025 r.p.m. Other restrictions listed in AD 48-26-01 still apply. 2. Limit gross weight to 102,000 pounds maximum. 3. On hubs having more than 1,500 hours total service time, visually inspect for cracks the rear outboard portions of the hub barrels. Inspection is to be continued at intervals as close to 10 hours as practical but not exceeding 20 hours maximum. It is strongly recommended that whenever the necessary equipment is available, magnetic inspections be made at the same intervals in accordance with Curtiss Instruction entitled "Field Magnetic Inspection of C6832S-A Hubs." Remove from service any hub showing a crack. To facilitate these inspections, the propeller power unit is covered or sealed to prevent the entrance of water in the unit. As an alternate to the removal of the spinner, these inspections may be conducted through three 5-inch diameter holes located in the side of the spinner in accordance with instructions issued by Curtiss. 4. All C632S-A hubs (P/N 116366) with over 2,000 hours total time shall be retired from service as soon as possible and not later than November 30, 1949. 5. Items 1 and 2 also apply when the C-632S-B hub (P/N 129914) is used to replace the C632S-A hub (P/N 116366).
89-02-12 R1: 89-02-12 R1 GULFSTREAM: Amendment 39-8825. Docket 93-NM-58-AD. Revises AD 89-02-12, Amendment 39-6155. Applicability: Model G-IV airplanes, as listed in Gulfstream Aircraft Service Change No. 110, dated January 24, 1989, certificated in any category. Compliance: Required as indicated, unless accomplished previously. NOTE 1: Paragraphs (a) and (b) of this AD merely restate the requirements of paragraphs A. and B. of AD 89-02-12, Amendment 39-6155. As allowed by the phrase, "unless accomplished previously," if those requirements of AD 89-02-12 have already been accomplished, paragraphs (a) and (b) of this AD do not require that those actions be repeated. To prevent hazardous deviations from the intended course, accomplish the following: (a) Prior to further flight after April 3, 1989 (the effective date of AD 89-02-12, Amendment 39-6155), discontinue use of the Bendix instrument landing system (ILS) radios for any type of approach. Pull both circuit breakers (C/B) on the co-pilot's C/B panel labeled "ILS #1" and "ILS #2." Tie-wrap the C/B's out, using TY23M or equivalent tie-wraps. Affix placards (Gulfstream decal #1159F40000-911 or equivalent) to the control heads and the C/B's, labeling them "INOP." (b) Within 10 hours of airplane operation after April 3, 1989 (the effective date of AD 89-02-12, Amendment 39-6155), modify the wiring to the #1 and #2 electronic display controllers, in accordance with Gulfstream Aircraft Service Change No. 110, dated January 24, 1989. (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, Atlanta Aircraft Certification Office (ACO), FAA, Small Airplane Directorate. Operators shall submit their requests through an appropriate FAA Principal Maintenance Inspector, who may add comments and then send it to the Manager, Atlanta ACO. NOTE 2: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Atlanta 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) Accomplishment of the actions specified in both paragraphs (e)(1) and (e)(2) of this AD constitutes terminating action for the requirements of this AD: (1) Modify the Bendix ILS systems in accordance with Gulfstream Aircraft Service Change No. 110A, dated April 9, 1993; and (2) Prior to further flight after accomplishing the actions specified in paragraph (e)(1) of this AD, reactivate the Bendix ILS systems after relocating the forward radome mounted AM/FM entertainment antenna system in accordance with a method approved by the Manager, Atlanta ACO, FAA, Small Airplane Directorate. (f) The modifications shall be done in accordance with Gulfstream Aircraft Service Change No. 110, dated January 24, 1989, and Gulfstream Aircraft Service Change No. 110A, dated April 9, 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 Gulfstream Aerospace Corporation, P.O. Box 2206, M/S D-10, Savannah, Georgia 31402-2206. Copies may be inspected at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; or at the FAA, Small Airplane Directorate, Atlanta Aircraft Certification Office, 1669 Phoenix Parkway, Suite 210C, Atlanta, Georgia; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC. (g) This amendment becomes effective on March 21, 1994.
2003-02-04: This amendment adopts a new airworthiness directive (AD), that is applicable to CFM International CFM56-5 and -5B series turbofan engines. This amendment requires the establishment of an exhaust gas temperature (EGT) baseline and trend monitoring using the System for Analysis of Gas Turbine Engines (SAGE), or equivalent, as an option to EGT harness replacement, and if necessary, replacement of certain EGT harnesses and EGT couplings as soon as a slow and continuous EGT drift downward is noticed after the effective date of this AD. This amendment is prompted by reports of erroneous EGT readings. The actions specified by this AD are intended to prevent unexpected deterioration of critical rotating engine parts due to higher than desired engine operating EGT's.
2002-13-05 R1: This amendment revises an airworthiness directive (AD) for the specified MD Helicopters, Inc. (MDHI) helicopters that currently requires identifying the part number (P/N) of the bolts that attach the tail rotor gearbox to the tailboom and replacing any bolt of inadequate grip length with an airworthy bolt. That AD also requires adding an additional washer if more than four threads protrude from the nutplate. This amendment requires the same actions as the existing AD but reduces the applicability to only certain tailboom serial numbers and parts modified in accordance with either Supplemental Type Certificate (STC) SH5055NM or SH4801NM. This amendment also corrects a typographical error and clarifies that a slippage mark needs to be reapplied to each bolt regardless of the outcome of the required torque test. This amendment is prompted by the need to correct and clarify the applicability and other portions of the existing AD. The actions specified by this AD are intended to prevent loss of a tail rotor gearbox due to bolts of inadequate grip length and subsequent loss of control of the helicopter.
2021-19-20: The FAA is adopting a new airworthiness directive (AD) for all Dassault Aviation Model FALCON 7X airplanes. This AD was prompted by a report of defects on the piston hole associated with the O2 saver feature that may prevent efficient deactivation of the O2 saver function. This AD requires amending the existing airplane flight manual (AFM) to incorporate a check and an operating limitation regarding the O2 saver function, as specified in a European Union Aviation Safety Agency (EASA) AD, which is incorporated by reference. This AD also limits the installation of affected parts under certain conditions. The FAA is issuing this AD to address the unsafe condition on these products.
92-15-04: 92-15-04 BRITISH AEROSPACE: Amendment 39-8297. Docket No. 91-NM-275-AD. Applicability: Model 125-800A series airplanes, certificated in any category. Compliance: Required as indicated, unless accomplished previously. To prevent excessive wear and premature structural failure of the main landing gear, accomplish the following: (a) Within 180 days after the effective date of this AD, install steel torque links on the right and left main landing gear, and reduce torque link and knuckle axial clearances, by installing British Aerospace Modification Number 253257A in accordance with British Aerospace Service Bulletin SB.32-226-3257A, dated May 3, 1991. (b) 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, Standardization Branch, ANM-113, FAA, Transport Airplane Directorate. Operators shall submit their requests through an appropriate FAA Principal Maintenance Inspector, who may add comments and then send it to the Manager, Standardization Branch, ANM-113. NOTE: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Standardization Branch, ANM-113. (c) 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. (d) The installation and modification shall be done in accordance with British Aerospace Service Bulletin SB.32-226-3257A, dated May 3, 1991. 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 British Aerospace, PLC, Librarian for Service Bulletins, P.O. Box 17414, Dulles International Airport, Washington DC. 20041-0414. Copies may be inspected at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, Washington; or at the Office of the Federal Register, 1100 L Street NW., Room 8401, Washington, DC. (e) This amendment becomes effective on August 20, 1992.
97-10-02: This amendment adopts a new airworthiness directive (AD) that is applicable to all Boeing Model 777 series airplanes. This action requires repetitive corrosion/resistance inspections to measure the resistance of each wire bundle of the flight control system; and repair of the receptacle bond, repair of the bundle connector backshells, or replacement of the wire bundles with new components, if necessary. This amendment is prompted by reports of corroded connectors and numerous other discrepancies of the wire bundles, such as loose backshells and loose shield retention bands, due to the presence of moisture inside the wire bundles. The actions specified in this AD are intended to detect and correct such corrosion, which could reduce system protection against lightning strikes or high intensity radiated field (HIRF) events, and consequently could adversely affect wire bundles used for the flight control system. This situation could result in loss of function of certain flight control surface actuators in the event of a lightning strike.