Results
75-16-08: 75-16-08 ROLLS ROYCE (1971) LIMITED: Amendment 39-2274. Applies to Rolls Royce RB211 series engines, serial numbers 10389 and prior. Compliance required by December 31, 1975, unless already accomplished. To prevent damage in the intermediate and high pressure compressors that contributes to the frequency of high power surges, accomplish the following: 1. Modify the inlet guide vane spherical trunnions, bearing pads, actuating rings, and bearing support segments in accordance with Rolls-Royce (1971) Limited Service Bulletin RB211-72-3326, dated November 14, 1973, or an FAA-approved equivalent. 2. Modify the intermediate pressure (IP) compressor inlet guide vanes in accordance with Rolls-Royce (1971) Limited Service Bulletin RB211-72-3335, Revision 2, dated March 12, 1974, or an FAA-approved equivalent. 3. Modify the IP compressor stator vanes in the 4th and 5th stage stator assemblies in accordance with Rolls-Royce (1971) Limited Service Bulletin RB211-72-3482, dated April 9, 1974, or an FAA-approved equivalent. This amendment becomes effective August 22, 1975.
2014-23-10: We are superseding Airworthiness Directive (AD) 2008-17-03 for certain The Boeing Company Model 737-100, -200, -200C, -300, -400, and -500 series airplanes. AD 2008-17-03 required repetitive inspections to detect fuselage frame cracking, and corrective action if necessary. AD 2008-17-03 also provided for optional terminating action (repair/ preventive change) for the repetitive inspections. This new AD adds airplanes to the applicability, but does not provide terminating action for the newly added airplanes. This AD was prompted by reports of cracks found at the cutout in the web of body station \n\n((Page 71297)) \n\nframe 303.9 inboard of stringer 16L, as well as a new report of cracking found on an airplane not identified in the applicability of AD 2008-17-03. We are issuing this AD to detect and correct fuselage frame cracking, which could prevent the left forward entry door from sealing correctly, and could cause in-flight decompression of the airplane.
2014-22-10: We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model DC-8-55, DC-8F-54, and DC-8F-55 airplanes, Model DC-8-60 series airplanes, Model DC-8-60F series airplanes, Model DC-8-70 series airplanes, and Model DC-8-70F series airplanes. This AD was prompted by multiple reports of cracking of the upper aft skin panel of \n\n((Page 70788)) \n\nthe fuselage. An evaluation by the design approval holder (DAH) indicates that the upper aft skin panel of the fuselage is subject to widespread fatigue damage (WFD). This AD requires removing any previously installed local repairs; installing a full-length improvement modification with or without finger doublers, or a full- length repair with or without finger doublers, as applicable; and doing repetitive inspections for cracking of the doublers, and repair if necessary. We are issuing this AD to detect and correct fatigue cracking of the upper aft skin panel of the fuselage, which could result in loss of structural integrity and consequent rapid decompression of the airplane.
2014-23-09: We are superseding Airworthiness Directive (AD) 2000-17-03 for all Fokker Services B.V. Model F.28 Mark 0100 airplanes. AD 2000-17- [[Page 70454]] 03 required inspections of the nose landing gear (NLG) main fitting to detect cracking of the NLG main fitting subassembly, and corrective actions if necessary. This new AD retains the requirements of AD 2000- 17-03, requires installing a new part number NLG unit that terminates the repetitive inspections, and adds airplanes to the applicability. This AD was prompted by a report of an NLG main fitting failure. We are issuing this AD to prevent cracking of the NLG main fitting, which could lead to collapse of the NLG during takeoff and landing, and possible injury to the flight crew and passengers.
2020-23-04: The FAA is adopting a new airworthiness directive (AD) for certain Gulfstream Aerospace Corporation (Gulfstream) Model GVII-G500 and Model GVII-G600 airplanes. This AD requires revising your existing airplane flight manual (AFM) and airplane maintenance manual (AMM) to include information pertaining to the fuel boost pump. This AD was prompted by a report of misassembled impellers onto the shaft of the fuel boost pump during production. The FAA is issuing this AD to address the unsafe condition on these products.
2014-23-14: We are adopting a new airworthiness directive (AD) for certain Bombardier, Inc. Model DHC-8-400 series airplanes. This AD was prompted by reports of swing arm assemblies of engine fuel feed ejector pumps detaching from the outlet port of the engine fuel feed ejector pump and partially blocking the engine fuel feed line. This AD requires installing a restrictor into the engine fuel feed line. We are issuing this AD to prevent blocked engine fuel flow and possible engine flameout.
2014-23-12: We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 787-8 airplanes. This AD was prompted by a report indicating that, on a different Boeing airplane model, there was an oxygen-fed fire, which caused extensive damage to the flight deck. This AD requires replacing the low-pressure oxygen hoses with non- conductive hoses in the crew oxygen system. We are issuing this AD to prevent inadvertent electrical current from passing through an internal, anti-collapse spring of the low pressure oxygen hose, which can cause the low-pressure oxygen hose to melt or burn, leading to an oxygen-fed fire and/or smoke beneath the flight deck in the forward electronics equipment bay.
2003-14-08: This amendment adopts a new airworthiness directive (AD); applicable to all Boeing Model 737-600, 737-700, 737-700C, 737-800, 737-900, 757, and 767 series airplanes; that requires revising the Airplane Flight Manual (AFM) to advise the flightcrew to don oxygen masks as a first and immediate step when a cabin altitude warning occurs. This action is necessary to prevent incapacitation of the flightcrew due to lack of oxygen, which could result in loss of control of the airplane. This action is intended to address the identified unsafe condition.
2014-23-06: We are adopting a new airworthiness directive (AD) for certain Bombardier, Inc. Model CL-600-2B19 (Regional Jet Series 100 & 440) airplanes. This AD was prompted by a report indicating that inboard and outboard hydraulic lines of the brakes were found connected to the incorrect ports on the swivel assembly of the main landing gear (MLG). This AD requires modifying the MLG by installing a new bracket on the left and right lower aft-wing planks. We are issuing this AD to prevent incorrect installation of the brake hydraulic lines, which could cause the brakes and the anti-skid system to operate incorrectly, and consequent catastrophic failure of the airplane during a high-speed rejected takeoff.
2014-23-04: We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 777-200LR, -300, -300ER, and 777F series airplanes. This AD was prompted by reports of dual pitch rate sensor (PRS) failures causing the primary flight computers to transition from primary mode to secondary mode, resulting in autopilot disconnects. This AD requires an inspection to determine the PRS part number, and replacement if necessary. We are issuing this AD to prevent a dual PRS failure that could cause an automatic disengagement of the autopilot and autoland, which may prevent continued safe flight and landing if disengagement occurs at low altitude and the flight crew is unable to safely assume control and execute a go-around or manual landing.
2014-22-08: We are adopting a new airworthiness directive (AD) for all Airbus Model A318, A319, A320, and A321 series airplanes. This AD was prompted by a determination that more restrictive airworthiness limitations are necessary. This AD requires revising the maintenance or inspection program as applicable. We are issuing this AD to prevent a safety-significant latent failure (which is not annunciated) which, in combination with one or more other specific failures or events, would result in a hazardous or catastrophic failure condition.
2014-22-07: We are superseding Airworthiness Directive (AD) 2013-16-08 for certain Bombardier, Inc. Model CL-600-2C10 (Regional Jet Series 700, 701, & 702) airplanes, Model CL-600-2D15 (Regional Jet Series 705) airplanes, and Model CL-600-2D24 (Regional Jet Series 900) airplanes. AD 2013-16-08 required inspection of the main landing gear (MLG) retraction actuator components; corrective actions if necessary; and, for certain retraction actuators, installation of a new jam nut. This new AD continues to require those actions. This AD was prompted by a determination that a certain part was incorrectly identified in a certain section of AD 2013-16-08. We are issuing this AD to prevent disconnection of the MLG retraction actuator, which could result in extension of the MLG without damping, and consequent structural damage and collapse of the MLG during landing.
2014-22-04: We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model DC-9-10, DC-9-20, and DC-9-30 series airplanes. This AD was prompted by an evaluation by the design approval holder (DAH) indicating that the improved (shot-peened) aft fuselage non-ventral pressure bulkhead tee is subject to widespread fatigue damage (WFD). This AD requires repetitive inspections for cracking of the improved (shot-peened) non-ventral aft pressure bulkhead tees, and replacement if necessary. We are issuing this AD to detect and correct fatigue cracking of the improved (shot-peened) non-ventral aft pressure bulkhead tees connecting the bulkhead web to the fuselage, which could result in reduced structural integrity and rapid decompression of the airplane.
2014-20-18: We are superseding Airworthiness Directive (AD) 2005-23-08 for certain Airbus Model A300 B4-605R and B4-622R airplanes; Model A300 F4- 605R airplanes; and Model A300 C4-605R Variant F airplanes. AD 2005-23- 08 required repetitive inspections to detect cracks of certain attachment holes, installation of new fasteners, follow-on inspections or repair if necessary, and modification of the angle fittings of fuselage frame FR47. This new AD adds new repetitive ultrasonic inspections for cracks of the center wing box lower panel; and repair if necessary. This new AD also removes certain airplanes from the applicability. This AD was prompted by reports of cracks found on the horizontal flange of the Frame 47 internal corner angle fitting while accomplishing the modification required by AD 2005-23-08. We are issuing this AD to detect and correct fatigue cracking of the forward fitting of fuselage frame FR47, which could result in reduced structural integrity of the frame.
2014-20-19: We are superseding Airworthiness Directive (AD) 2013-10-06, for all Airbus Model A330-200 Freighter, A330-200, A330-300, A340-200, A340-300, A340-500, and A340-600 series airplanes. AD 2013-10-06 required an inspection to identify the installed windshields, and replacement of any affected windshield. This new AD requires expanding the inspection area to 15 additional windshields' serial numbers. This AD was prompted by several reports of a burning smell and/or smoke in the cockpit during cruise phase, leading in some cases, to [[Page 65888]] diversion to alternate airports. We are issuing this AD to prevent significantly increased workload for the flightcrew, which could, under some flight phases and/or circumstances, constitute an unsafe condition.
2021-26-08: The FAA is adopting a new airworthiness directive (AD) for certain Bell Textron Canada Limited Model 206, 206A, 206A-1, 206B, 206B-1, 206L, 206L-1, 206L-3, and 206L-4 helicopters. This AD was prompted by reports of cracked or missing nuts on the tail rotor drive shaft (TRDS) disc pack (Thomas) couplings. This AD requires removing certain nuts from service, installing newly designed nuts, and applying a specific torque and a torque stripe to each newly installed nut. This AD then requires, after the installation of each newly designed nut, inspecting the torque and, depending on the inspection results, either applying a torque stripe or performing further inspections and removing certain parts from service. Finally, this AD prohibits installing any affected nut on any TRDS Thomas coupling. The FAA is issuing this AD to address the unsafe condition on these products.
2014-22-05: We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model DC-9-10, DC-9-20, DC-9-30, DC-9-40, and DC-9- 50 series airplanes. This AD was prompted by an evaluation by the design approval holder (DAH) indicating that the bulkhead dome tees, which connect the bulkhead web to the fuselage, are subject to widespread fatigue damage (WFD). This AD requires repetitive inspections of the improved ventral aft pressure bulkhead tees, and replacement if necessary. We are issuing this AD to detect and correct fatigue cracking of the bulkhead dome tees, which could result in reduced structural integrity and rapid decompression of the airplane.
75-04-06: 75-04-06 BOEING: Amendment 39-2086. Applies to all Model 747 airplanes, certificated in all categories, listed in Boeing Service Bulletin 747-34-2058 dated January 31, 1974, or later FAA approved revisions. To prevent erroneous information from being displayed on flight instruments: \n\tWithin the next 3,500 hours time in service after the effective date of this AD, modify the pitot-static tubing to include a vertical rise just inboard of each pitot-static probe in accordance with Work Package 1, 2, and 3 of Boeing Service Bulletin 747-34-2058, dated January 31, 1974, or later FAA approved revisions, or in a manner approved by the Chief, Engineering and Manufacturing Branch, FAA Northwest Region. \n\tThe manufacturer's specifications and procedures identified and described in this directive are incorporated herein and made a part hereof pursuant to 5 U.S.C. 552(a)(1). \n\tAll persons affected by this directive who have not already received these documents from the manufacturer may obtain copies upon request to the Boeing Commercial Airplane Company, P. O. Box 3707, Seattle, Washington 98124. The documents may be examined at FAA Northwest Region, 9010 East Marginal Way, Seattle, Washington 98108. \n\tThis amendment becomes effective March 10, 1975.
2021-17-02: The FAA is superseding Airworthiness Directive (AD) 2020-23- 13, which applied to all ATR--GIE Avions de Transport R(eacute)gional Model ATR42-200, -300, and -320 airplanes. AD 2020-23-13 required a one-time inspection for discrepancies of the wire bundles between the left- and right-hand angle of attack (AOA) probes and the crew alerting computer, and, depending on findings, applicable corrective actions. This AD continues to require the actions in AD 2020-23-13, and also requires for certain airplanes, modifying the captain stick shaker wiring, and for all airplanes, revising the existing aircraft flight manual (AFM) and applicable corresponding operational procedures to incorporate procedures for the stick pusher/shaker, as specified in a European Union Aviation Safety Agency (EASA) AD, which is incorporated by reference. This AD was prompted by false activation of the stall warning system due to wiring damage on the wire bundle between an AOA probe and the crew alerting computer, and the development of a wiring modification and AFM update to address the unsafe condition. The FAA is issuing this AD to address the unsafe condition on these products.
2014-21-10: We are adopting a new airworthiness directive (AD) for certain Airbus Model A330-200 and -300 series airplanes, and Model A340-200 and -300 series airplanes. This AD was prompted by a report of contact between certain electrical harnesses and the hatrack rod that could cause chafing between the harnesses and surrounding structure. This AD requires modifying the routing of certain electrical harnesses. We are issuing this AD to prevent chafing and possible short circuit of two oxygen chemical generator containers in different wiring routes, which could result in malfunction of the electrical opening of all the containers connected to these routes. Such conditions, during a sudden depressurization event, could result in lack of oxygen and consequent injuries to airplane occupants.
2014-21-07: We are adopting a new airworthiness directive (AD) for certain Bombardier, Inc. Model CL-600-2C10 (Regional Jet Series 700, 701, & 702) airplanes, Model CL-600-2D24 (Regional Jet Series 900) airplanes, and Model CL-600-2E25 (Regional Jet Series 1000) airplanes. This AD was prompted by a report that certain parts of the aft baggage door did not conform to the design specifications and were of degraded strength. This AD requires repetitive inspections for cracking and deformations of certain stop fittings and striker plates of the aft baggage bay door; and replacement, which would terminate the repetitive inspections. We are issuing this AD to prevent cracking and deformations of certain stop fittings and striker plates, which could result in the opening of the aft baggage bay door and rapid decompression or reduced controllability of the airplane.
75-22-17: 75-22-17 BRITTEN NORMAN LTD: Amendment 39-2407. Applies to Model BN-2A Mark III airplanes, all series, certificated in all categories. Compliance is required as indicated, unless already accomplished. To prevent possible loss of rudder trim control, accomplish the following: (a) Prior to the first flight of each day after the effective date of this AD, inspect the rudder trim jack lower mounting brackets and rudder structure for cracks in accordance with paragraphs 1, 2, and 3 of Britten Norman Service Bulletin No. BN-2/SB.62, dated June 22, 1973, or an FAA-approved equivalent. (b) If a crack is found during an inspection required by paragraph (a) of this AD, replace the cracked part with a part of the same part number or an FAA-approved equivalent before further flight, except that the airplane may be flown in accordance with FAR Section 21.197 and 21.199 to a base where the repair can be accomplished. (c) Within the next 300 hours' time in service after the effective date of this AD, modify the rudder trim jack lower mounting bracket and the rudder structure in accordance with Britten Norman Modification Leaflet No. BN-2/NB/M/596, dated June 22, 1973, or an FAA- approved equivalent. (d) Upon incorporation of the modification required by paragraph (c) of this AD, the inspections required by paragraph (a) of this AD, may be discontinued. This amendment becomes effective November 5, 1975.
2014-21-03: We are adopting a new airworthiness directive (AD) for Airbus Helicopters Model AS332L2 helicopters with a certain yaw control damper support (support) installed. This AD requires repetitively inspecting the support attachment points for a crack. This AD is prompted by a report that the front attachment points of several supports were found to have cracks. These actions are intended to detect a crack in a support, which could result in failure of the support, separation of the yaw damper unit, blocking of the yaw flight control channel, and reduced control of the helicopter.
2020-21-05: The FAA is superseding Airworthiness Directive (AD) 2017-25- 16, which applied to all Airbus SAS Model A330-200 Freighter, A330-200, A330-300, A340-200, A340-300, A340-500, and A340-600 series airplanes. AD 2017-25-16 required repetitive inspections of certain fuel pumps for cavitation erosion, corrective action if necessary, and revision of the minimum equipment list (MEL). This AD continues to require those actions, and also requires expanding the inspection area, adding certain maintenance actions, and expanding the applicability, as specified in a European Union Aviation Safety Agency (EASA) AD, which is incorporated by reference. This AD was prompted by reports of a fuel pump showing cavitation erosion that exposed the fuel pump power supply wires, and by new findings that suggest the need to expand the inspection area and the applicability. The FAA is issuing this AD to address the unsafe condition on these products.
2014-21-01: We are superseding airworthiness directives (ADs) 90-26-01, 91-20-02, and 2009-05-02 for all General Electric Company (GE) CF6-80C2 and CF6-80E1 series turbofan engines. This AD retains the requirements of those ADs and requires removal of additional fuel manifold part numbers (P/Ns), additional repetitive inspections, replacement as required of certain fuel manifold P/Ns and tube (block) clamps, and replacement of loop clamps. This AD was prompted by a report of an under-cowl fire caused by a manifold high-pressure fuel leak, and several additional reports of fuel leaks. We are issuing this AD to prevent failure of the fuel manifold, which could lead to uncontrolled engine fire, engine damage, and damage to the airplane.