Results
2001-13-11: This amendment adopts a new airworthiness directive (AD) that is applicable to all Dassault Model Falcon 10 series airplanes. This action requires an inspection to verify proper installation of the pins in the dual non-return valves of the fire extinguishing system for the engines, and replacement of any defective valve with a new valve. This action is necessary to prevent failure of a fire extinguisher bottle to discharge, which could result in the inability to extinguish a fire in an engine. This action is intended to address the identified unsafe condition.
2001-12-16: This amendment adopts a new airworthiness directive (AD) for Eurocopter France Model AS332L2 helicopters. This AD requires, at specified time intervals, visually inspecting the main rotor blade sleeve yoke (sleeve) for cracks, corrosion, fretting, or bonding separation; the bearing surface of the metal bushing (bushing) for fretting or cracks; and the sleeve-to-damper attachment bolt (bolt) for corrosion and deterioration of the fluorimid varnish coating. Replacing any cracked or nonairworthy sleeve, bushing, or bolt is also required before further flight. This AD is prompted by the discovery of extensive deterioration of the fluorimid varnish coating on the bolt; cracks in the bushing; and fretting and corrosion of the sleeve. The actions specified in this AD are intended to detect corrosion and cracks in the yoke, which could result in separation of the blade damper assembly and subsequent loss of control of the helicopter.
2004-24-07: The FAA is adopting a new airworthiness directive (AD) for certain Boeing Model 737-600, -700, -700C, -800, and -900 series airplanes. This AD requires replacing the bracket for the wire bundle of the fuel quantity indicating system (FQIS), performing a general visual inspection of the FQIS wire bundle for damage, and doing corrective actions if necessary. This AD is prompted by a report of an incorrectly installed FQIS wire bundle. We are issuing this AD to prevent chafing of the FQIS wire(s) in the center fuel tank, which, when combined with a lightning strike or a power wire short to the FQIS wire(s), could result in arcing in the center fuel tank and consequent fuel tank explosion.
2004-23-20: The FAA is superseding an existing airworthiness directive (AD) that applies to all Airbus Model A300 B4-601, A300 B4-603, A300 B4-620, A300 B4-605R, A300 B4-622R, and A300 F4-605R airplanes. That AD currently requires repetitive inspections for cracking in the area surrounding certain fuselage attachment holes, installation of new fasteners for certain airplanes, and certain follow-on corrective actions if necessary. This new AD requires modifying certain fuselage frames, which would terminate certain repetitive inspections. This AD also adds airplanes to the applicability. This AD is prompted by the development of a modification intended to prevent cracking of the center section of the fuselage, which could result in a ruptured frame foot and reduced structural integrity of the airplane.
2001-13-10: This amendment adopts a new airworthiness directive (AD), applicable to certain Saab Model SAAB 2000 series airplanes, that requires testing of certain components of the emergency pitch trim system (EPTS), and corrective action, if necessary. The actions specified by this AD are intended to prevent faulty activation of the emergency pitch trim actuator (EPTA), which could cause damage to the elevator front spar, resulting in reduced structural integrity of the elevator and a non-functioning EPTS. This action is intended to address the identified unsafe condition.
2001-13-07: This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 737-300, 737-400, 737-500, 737-600, 737-700, 737-800, 757-200, 757-200PF, 757-200CB, and 757-300 series airplanes. This AD requires a test of the two electrical circuits that close the fuel shutoff valve on the wing spar, and repair, if necessary. This action is necessary to prevent inability to shut off the flow of fuel to an engine after an uncontained engine failure, which could result in a fire spreading to other parts of the airplane. This action is intended to address the identified unsafe condition.
94-15-18: This amendment supersedes an existing airworthiness directive (AD), applicable to certain Boeing Model 747 series airplanes, that currently requires that the FAA-approved maintenance inspection program include inspections which will give no less than the required damage tolerance rating (DTR) for each Structural Significant Item (SSI). This amendment requires the inclusion of additional airplanes to the candidate fleet. This amendment is prompted by a recommendation from the Airworthiness Assurance Working Group, Model 747 Structures Task Group. The actions specified by this AD are intended to ensure the continued structural integrity of the total Boeing Model 747 fleet.
2008-02-14: The FAA is adopting a new airworthiness directive (AD) for certain Boeing airplanes listed above. This AD requires an inspection of certain lighted pushbutton switches in the flight compartment for configuration 'D' master modules and part numbers and corrective action if necessary. This AD also provides an option to inspect panel assemblies for part numbers. This AD results from a report indicating that the integrated drive generator failed in flight due to a possible switch malfunction. We are issuing this AD to ensure that certain lighted pushbutton switches in the flight compartment do not malfunction and cause the flightcrew to be unable to control critical airplane systems and continue safe airplane operation.
2001-13-08: This amendment adopts a new airworthiness directive (AD), applicable to certain Dornier Model 328-300 series airplanes, that requires replacing the brake assemblies with modified brake assemblies. The actions specified by this AD are intended to prevent overheating of the brakes, which could result in cracked pistons and consequent leakage and burning of the hydraulic fluid. This action is intended to address the identified unsafe condition.
2020-05-15: The FAA is adopting a new airworthiness directive (AD) for all Airbus SAS Model A319-131, -132, and -133 airplanes, Model A320-231, - 232, and -233 airplanes, and Model A321-131, -231, and -232 airplanes. This AD was prompted by a report of rupture of a hydraulic reservoir air pressurization hose on an in-service airplane, leading to air leakage that was undetectable during normal operation, and found during subsequent zonal inspection. This AD requires modifying the airplane by replacing the affected bleed air hoses with a modification of hydraulic pressurization lines, 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.
94-15-17: This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 747 series airplanes, that requires inspections to detect cracking of certain fuselage longitudinal lap joints, repair of any cracking found, and replacement of the countersunk fasteners in those lap joints with protruding head fasteners. This amendment is prompted by a structural reassessment of Model 747 series airplanes. The actions specified by this AD are intended to prevent skin cracking in the longitudinal lap joints of certain stringers, which can lead to rapid decompression of the airplane.
2008-02-05: The FAA is adopting a new airworthiness directive (AD) for certain Boeing Model 777-200 and -300 series airplanes. This AD requires revising the airplane flight manual to provide the flightcrew with new ground procedures for shedding core ice during long taxi periods in freezing fog with visibility of 300 meters or less. For airplanes unable to perform the shedding procedure after prolonged taxiing in freezing fog with visibility of 300 meters or less, this AD requires certain investigative and corrective actions. This AD results from reports of engine surges and internal engine damage due to ice accumulation during extended idle thrust operation in ground fog icing conditions. We are issuing this AD to prevent internal engine damage due to ice accumulation and shedding, which could cause a shutdown of both engines, and result in a forced landing of the airplane.
2001-13-01: This amendment adopts a new airworthiness directive (AD), for Bell Helicopter Textron, Inc. (BHTI) Model 205A-1, 205B, 212, 412, 412EP, and 412CF helicopters. This AD requires removing each existing tail rotor counterweight bellcrank (bellcrank) retention nut (retention nut), replacing each retention nut with a zero hours time-in-service (TIS) retention nut; and follow-up inspections of installed retention nuts. This AD is prompted by an in-flight loss of a bellcrank due to failure of the retention nut. The actions specified by this AD are intended to prevent failure of the retention nut, which could result in the bellcrank migrating off the crosshead spindle, loss of tail rotor control, and subsequent loss of control of the helicopter.
2020-04-19: The FAA is superseding Airworthiness Directive (AD) 2017-15- 01, which applied to certain The Boeing Company Model 777 airplanes. AD 2017-15-01 required replacing the existing mode control panel (MCP) with a new MCP having a different part number. This AD retains the requirements of AD 2017-15-01, expands the applicability to include certain other airplanes, and adds a new requirement for certain airplanes to identify and replace the affected parts. This AD was prompted by a determination that the affected parts may be installed on airplanes outside of the original applicability of AD 2017-15-01. The FAA is issuing this AD to address the unsafe condition on these products.
94-15-15: This amendment adopts a new airworthiness directive (AD) that is applicable to certain Raytheon Corporate Jets Model BAe 125-1000A and Hawker 1000 series airplanes. This action requires an inspection to detect damage and to determine the clearance between the hydraulic pipes, adjacent pipes/components, and electrical looms/cables; and repair or replacement, if necessary. This amendment is prompted by reports of chafing of an electrical loom/cable on a hydraulic pipe and of chafing between a hydraulic pipe and an adjacent pipe. The actions specified in this AD are intended to prevent loss of hydraulic pressure, electrical malfunction, or an in-flight fire due to abrasion of electrical loom/cable insulation, eventual electrical shorting of the cable, and subsequent burning of a pinhole in a pipe. Comments for inclusion in the Rules Docket must be received on or before September 27, 1994.
2008-02-09: We are adopting a new airworthiness directive (AD) for the products listed above. This AD results from mandatory continuing airworthiness information (MCAI) issued by the aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as: On the pre-flight check of a SZD-50-3 glider, the Right Hand (RH) wing airbrake was found impossible to retract. Investigation revealed that the occurrence was caused by a loose bolt of the "V'' shape airbrake bellcrank, named hereafter intermediate control lever. The Left Hand (LH) wing lever also presented, to a lesser extent, a loose bolt. This AD requires actions that are intended to address the unsafe condition described in the MCAI.
2001-13-05: This amendment adopts a new airworthiness directive (AD), applicable to certain Raytheon Model BAe.125 series 800A (C-29A and U-125 military), 1000A, and 1000B airplanes; Hawker 800 (U-125A military) airplanes; and Hawker 800XP and 1000 series airplanes, that requires removal of existing clamps, bedding tapes, and rubber connecting sleeves at the ends of the turbine air discharge duct and the water separator, and replacement of the clamps and rubber connecting sleeves with new, improved components. This AD also requires, for certain airplanes, removal of aluminum bedding strips that are installed under the existing clamps. The actions specified by this AD are intended to prevent the turbine air discharge duct or water separator outlet duct from disconnecting from the cold air unit turbine or from the water separator, resulting in the loss of air supply to maintain adequate cabin pressure. Loss of adequate cabin pressure at high altitude would require emergency procedures, suchas use of oxygen, auxiliary pressurization, or emergency descent.
2001-08-13: This amendment adopts a new airworthiness directive (AD) that is applicable to certain Gulfstream Model G-1159, G-1159A, G-1159B, G-IV, and G-V series airplanes. This action requires an inspection to determine if certain door control valves of the landing gear are installed, and modification of the valve, if necessary. This action is necessary to prevent loss of hydraulic system fluid due to failure of the door control valve of the landing gear, which could require the flight crew to use alternate gear extension procedures (landing gear blow down) for landing of all models. This action is intended to address the identified unsafe condition.
94-15-12: This amendment supersedes an existing airworthiness directive (AD), applicable to certain Boeing Model 747-100SR series airplanes, that currently requires that the FAA-approved maintenance inspection program include inspections which will give no less than the required damage tolerance rating (DTR) for each Structural Significant Item (SSI). That AD was prompted by a structural re-evaluation of this airplane model by the FAA. The actions specified in that AD are intended to ensure the continued structural integrity of the total Boeing Model 747-100SR fleet. This amendment revises the applicability of the rule by removing airplanes and adding others.
2008-02-07: 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: Bombardier Aerospace has completed a system safety review of the CL-600-2B19 aircraft fuel system * * *. The assessment showed that if the fuel boost pump reducer coupling is anodized, insufficient electrical bonding between the boost pump canister and the pressure pick-up line could occur. Insufficient electrical bonding between the boost pump canister and the pressure pick-up line, if not corrected, could result in arcing and potential ignition source inside the fuel tank during lightning strikes and consequent fuel tank explosion. * * * We are issuing this AD to require actions to correct the unsafe condition on these products.
2020-05-12: The FAA is adopting a new airworthiness directive (AD) for all Gulfstream Aerospace Corporation Model GVII-G500 and GVII-G600 airplanes. This AD requires revising the airplane flight manual (AFM) for your airplane to incorporate revised limitations and procedures. This AD was prompted by a report of a landing incident where the alpha limiter engaged in the landing flare in unstable air while on the approach, resulting in a high rate of descent landing and damage to the airplane. The FAA is issuing this AD to address the unsafe condition on these products.
2001-12-20: This amendment adopts a new airworthiness directive (AD) that is applicable to General Electric Company (GE) CF6-50 turbofan engines. This amendment requires removal of old high pressure compressor (HPC) air ducts and mating hardware and replacement with newly designed air ducts and reworked mating hardware. This amendment also requires the repetitive inspection of certain reworked mating hardware. This amendment is prompted by reports of an uncontained low pressure turbine (LPT) disk failure that resulted from an air duct failure that caused a fan mid shaft (FMS) separation. The actions specified by this AD are intended to prevent HPC air duct failures that could result in FMS failures, that in turn could result in rejected takeoffs or uncontained LPT events, and to prevent HPC rear shaft failures that could result in uncontained engine failures.
91-13-04: 91-13-04 MCDONNELL DOUGLAS: Amendment 39-7035. Docket No. 91 NM-108-AD. \n\n\tApplicability: Model DC-9-87 (MD-87) series airplanes, certificated in any category. \n\n\tCompliance: Required as indicated, unless previously accomplished. \n\n\tTo prevent chafing and subsequent arcing of wires which could cause a fire resulting in the loss of engine controls and/or passengers becoming asphyxiated due to smoke inhalation, accomplish the following: \n\n\t(a)\tWithin 30 days after the effective date of this AD, modify the airplane by rerouting the wire assembly located on the right side of the airplane between stations Y=1022.000 and Y=1062.000 at longeron 3 in accordance with McDonnell Douglas Alert Service Bulletin A24-123, dated March 19, 1991. \n\n\t(b)\tAn alternative method of compliance or adjustment of the compliance time, which provides an acceptable level of safety, may be used when approved by the Manager, Los Angeles Aircraft Certification Office (ACO), FAA, Transport Airplane Directorate. \n\n\tNOTE: The request should be forwarded through an FAA Principal Maintenance Inspector, who may concur or comment and then send it to the Manager, Los Angeles ACO. \n\n\t(c)\tSpecial 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. \n\n\t(d)\tThe modification requirements shall be done in accordance with McDonnell Douglas Alert Service Bulletin A24-123, dated March 19, 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 McDonnell Douglas Corporation, Douglas Aircraft Company, P.O. Box 1771, Long Beach, California 90801, Attention: Business Unit Manager, Service Bulletins, Service Change and Modification Kits, Product Support, Mail Code 73-30. This information may be examined at the FAA, Northwest Mountain Region, Transport Airplane Directorate, 1601Lind Avenue S.W., Renton, Washington, or the Los Angeles Aircraft Certification Office, 3229 East Spring Street, Long Beach, California, or at the Office of the Federal Register, 1100 L Street N.W., Room 8401, Washington, D.C. \n\n\tThis amendment (39-7035, AD 91-13-04) becomes effective on June 27, 1991.
2007-26-14: The FAA is superseding an existing airworthiness directive (AD), which applies to all Airbus Model A300 B2 and B4 series airplanes; and all Model A300 B4-600, B4-600R, and F4-600R (collectively called A300-600) series airplanes. That AD currently requires repetitive inspections to detect cracking of the upper radius of the forward fitting of frame 47, and repair if necessary. This new AD retains those requirements, but reduces inspection thresholds and repetitive intervals, and adds related investigative and corrective actions. This AD also provides an optional terminating action for the repetitive inspections only for airplanes with cracking that is within certain limits, and a post-repair inspection program following the optional terminating action. This AD results from reports of additional cracking in airplanes that were inspected in accordance with the existing AD. We are issuing this AD to detect and correct fatigue cracking of the left and right upper radius at frame 47, which could propagate and result in reduced structural integrity of the airplane.
2001-12-21: This amendment supersedes an existing airworthiness directive (AD), applicable to all Boeing Model 747 series airplanes, that currently requires revising the Airplane Flight Manual to include procedures to prevent dry operation of the center wing fuel tank override/jettison pumps and, for certain airplanes, to prohibit operation of the horizontal stabilizer tank transfer pumps in-flight. For certain airplanes, this amendment requires installation of improved fuel pumps, which terminates the requirements of the existing AD. This amendment is prompted by new information received from the fuel pump manufacturer. The actions specified by this AD are intended to prevent contact between the rotating paddle wheel and the stationary end plates within the center wing tank override/jettison fuel pumps or horizontal stabilizer tank transfer pumps, which could cause sparks and/or a hot surface condition and consequent ignition of fuel vapor in the center wing tank or horizontal stabilizertank during dry pump operation (no fuel flowing).