Results
2018-19-10: We are adopting a new airworthiness directive (AD) for Airbus Helicopters Model AS355E, AS355F, AS355F1, AS355F2, and AS355N helicopters. This AD requires measuring a vibration level in the tail rotor (T/R) drive. This AD was prompted by reports of bearing degradation. The actions of this AD are intended to prevent an unsafe condition on these helicopters.
2006-21-02: The FAA is adopting a new airworthiness directive (AD) for all Raytheon (Beech) Model 400, 400A, and 400T series airplanes; and Raytheon (Mitsubishi) Model MU-300 airplanes. This AD requires revising the airplane flight manual to modify the Operating Limitations, Abnormal Procedures, and Normal Procedures, as applicable, for flight in icing conditions. This AD results from multiple reports of high- altitude, dual-engine flameouts on airplanes operating in certain meteorological conditions. We are issuing this AD to advise the flightcrew that the buildup of ice on certain internal areas of the engine could result in a dual-engine flameout and what action they must take to avoid this hazard.
2006-21-01: The FAA is adopting a new airworthiness directive (AD) for all Boeing Model 737 airplanes. This AD requires repetitive measurement of the freeplay of both aileron balance tabs; repetitive lubrication of the aileron balance tab hinge bearings and rod end bearings; and related investigative and corrective actions if necessary. This AD results from reports of freeplay-induced vibration of the aileron balance tab. The potential for vibration of the control surface should be avoided because the point of transition from vibration to divergent flutter is unknown. We are issuing this AD to prevent excessive vibration of the airframe during flight, which could result in loss of control of the airplane.
2018-19-11: We are adopting a new airworthiness directive (AD) for all Viking Air Limited Models DHC-2 Mk. I, DHC-2 Mk. II, and DHC-2 Mk. III airplanes. This AD results from mandatory continuing airworthiness information (MCAI) issued 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 cracking found in the wing rear spar web at the wing station where the flap outboard hinge is attached. We are issuing this AD to require actions to address the unsafe condition on these products.
2018-19-05: We are adopting a new airworthiness directive (AD) for all Dassault Aviation Model MYSTERE-FALCON 900 airplanes. This AD was prompted by a determination that more restrictive maintenance requirements and airworthiness limitations are necessary. This AD requires revising the maintenance or inspection program, as applicable, to incorporate new and more restrictive maintenance requirements and airworthiness limitations. We are issuing this AD to address the unsafe condition on these products.
84-15-01: 84-15-01 AVIAN BALLOON: Amendment 39-4954. Applies to Avian Balloon Models Sparrow, Falcon II, and Skyhawk, serial numbers 1 through 120, 413, and 810. Compliance required as indicated, unless previously accomplished. To prevent possible separation of the basket from the envelope, accomplish the following: A. Before further flight, install a placard using white lettering at least 2/10 inches high on a red background in full view of the pilot stating that "TETHERED FLIGHT IS PROHIBITED," and B. Before further flight, to ensure the structural integrity of the basket suspension cables on balloons which have been used for tethered flight, accomplish the following: 1. For early production series baskets, which may be identified by the presence of a nico-press sleeve on each cable where it enters the top of the basket handrail, replace the two basket suspension cables with new 5/32-inch diameter stainless steel cables meeting the Mil-W-83402B specification in accordancewith Advisory Circular (AC) 43.13-1A, paragraph 196(b). 2. For later production baskets, which may be identified by a cable load plate on the bottom of the basket, inspect each of the four basket suspension cables from two inches above the top of the basket handrail to two inches below the handrail for broken strands, deformation and kinking. Any damaged or kinked cables must be replaced with new 5/32-inch diameter stainless steel cables meeting Mil-W-83402B specification in accordance with AC 43.13-1A paragraph 196(b). C. No later than August 30, 1984, accomplish the following modification in accordance with Avian Service Bulletin No. 5, dated June 26, 1984: 1. Modify early production series baskets by replacing and relocating the basket suspension cables, replacing the basket skid plates, and adding the steel load plate. 2. Modify later production baskets by replacing and relocating the basket suspension cables. D. Accomplishment of paragraph C., above,eliminates the need to accomplish Paragraphs A. and B., allows the removal of the required placard, and permits tethered flight. E. Alternate means of compliance which provide an equivalent level of safety may be used when approved by the Manager, Seattle Aircraft Certification Office, FAA, Northwest Mountain Region. All persons affected by this directive who have not already received the appropriate service bulletins from the manufacturer may obtain copies upon request to the Avian Balloon Company, South 3722 Ridgeview Drive, Spokane, Washington 99026. These documents also may be examined at the FAA, Northwest Mountain Region, Seattle Aircraft Certification Office, 9010 East Marginal Way South, Seattle, Washington. This amendment becomes effective November 26, 1984, and was effective earlier to those recipients of priority letter AD 84-15-01 dated July 31, 1984.
47-42-13: 47-42-13 DOUGLAS: (Was Mandatory Note 10 of AD-781-1.) Applies to DC-6 Serial Numbers 42854 to 42896, Inclusive; 43000 to 43018, Inclusive; 43035 to 43042, Inclusive; 43055 to 43057, Inclusive; 43062 to 43064, Inclusive; and 43105. \n\nTo be accomplished not later than April 1, 1948. \n\nTo prevent the possibility of the gust lock control becoming engaged during flight or in taxiing, a latch control assembly, P/N 4356957, is to be installed to safety the control handle in the gust lock "Off" position. The gust lock link assembly, P/N 4248396, must also be reworked by removing and replacing spring, P/N 2356732, (or 1248420) and plunger, P/N 1248421, with new bolt P/N 1356885. \n\nIn addition to the above, the elevator and rudder gust lock in the tail section and the aileron gust lock in the fuselage center section must be reworked by removing shaft, P/N 1165869, and replacing with new piston, P/N 2356840. After completing the rework, care must be exercised in properly rigging thegust lock control system. (Douglas Service Bulletin DC-6 No. 75 covers this same subject.)
2018-19-08: We are adopting a new airworthiness directive (AD) for Leonardo S.p.A. (Leonardo) Model AW189 helicopters. This AD requires inspecting the tail gearbox (TGB) fitting for a crack. This AD was prompted by a report of a crack on a TGB fitting that was found during a scheduled inspection. The actions of this AD are intended to prevent an unsafe condition on these products.
2006-20-12: The FAA is adopting a new airworthiness directive (AD) for certain McDonnell Douglas Model 717-200 airplanes. This AD requires replacing the lightning critical clamp bases of the fuel tank vent system with improved clamp bases; and checking the electrical bond of the modified self-bonding mounting clamps and corrective action if necessary. This AD results from an investigation that revealed the aluminum foil strip on the nylon base of the ground clamps can fracture or separate from the base. We are issuing this AD to ensure that the fuel pipes are properly bonded to the airplane structure. Improper bonding could prevent electrical energy from a lightning strike from dissipating to the airplane structure, which could result in a fuel tank explosion.
2000-10-15: This amendment supersedes two existing airworthiness directives (AD), applicable to certain Airbus Model A320 series airplanes, that currently require modification of the rear spar web of the wing and cold expansion of certain attachment holes for the forward pintle fitting and certain holes at the actuating cylinder anchorage of the main landing gear (MLG). This amendment adds a requirement for repetitive inspections to detect fatigue cracking in certain areas of the rear spar of the wing, and corrective action, if necessary. This amendment also provides for optional terminating action for the requirements of this AD. This amendment is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified by this AD are intended to detect and correct fatigue cracking, which may lead to reduced structural integrity of the wing and the MLG.
2006-11-05: The FAA is superseding an existing airworthiness directive (AD) for Rolls-Royce plc (RR) RB211-22B series, RB211-524B, -524C2, - 524D4, -524G2, -524G3, and -524H series, and RB211-535C and -535E series turbofan engines with high pressure compressor (HPC) stage 3 disc assemblies, part numbers (P/Ns) LK46210, LK58278, LK67634, LK76036, UL11706, UL15358, UL22577, UL22578, and UL24738 installed. This AD requires removing from service certain disc assemblies before they reach their full published life if not modified with anticorrosion protection. This AD results from the manufacturer's reassessment of the corrosion risk on HPC stage 3 disc assemblies that have not yet been modified with sufficient application of anticorrosion protection. We are issuing this AD to prevent corrosion-induced uncontained disc failure, resulting in damage to the airplane. The Director of the Federal Register previously approved the incorporation by reference of certain publications listed in the regulations as of February 24, 2004 (69 FR 2661, January 20, 2004).
2021-10-27: The FAA is adopting a new airworthiness directive (AD) for all BAE Systems (Operations) Limited Model BAe 146 and Model Avro 146-RJ series airplanes. This AD was prompted by a report indicating that during a routine battery capacity check on the emergency light power units, the printed circuit boards (PCBs) for certain power units were found to show signs of burning. This AD requires replacing each Honeywell emergency light power unit having a certain part number with a serviceable emergency light power unit. The FAA is issuing this AD to address the unsafe condition on these products.
2021-07-09: The FAA is superseding Airworthiness Directive (AD) 2007-07- 03, which applied to certain The Boeing Company Model 747-100, 747- 100B, 747-100B SUD, 747-200B, 747-200C, 747-200F, 747-300, 747-400, 747-400D, 747-400F, 747SR, and 747SP series airplanes. AD 2007-07-03 required repetitive tests to detect hot air leaking from the trim air diffuser ducts or sidewall riser duct assemblies (collectively referred to as TADDs), related investigative actions, and corrective actions if necessary. AD 2007-07-03 also provided an optional terminating action for the repetitive tests. This AD requires repetitive inspections of all TADD material for damage and applicable on-condition actions. This AD was prompted by reports that high temperature composite material TADDs installed as specified in AD 2007-07-03 have also failed. The FAA is issuing this AD to address the unsafe condition on these products.
2018-18-21: We are adopting a new airworthiness directive (AD) for all Airbus SAS Model A300 B4-600, B4-600R, and F4-600R series airplanes, and Model A300 C4-605R Variant F airplanes (collectively called Model A300-600 series airplanes), and Model A310 series airplanes. This AD was prompted by a determination that new or more restrictive maintenance requirements and airworthiness limitations are necessary. This AD requires revising the maintenance or inspection program, as applicable, to incorporate new or more restrictive maintenance requirements and airworthiness limitations. We are issuing this AD to address the unsafe condition on these products.
86-03-04: 86-03-04 FOKKER B.V.: Amendment 39-5220. Applies to Model F27 airplanes, certificated in any category, serial numbers 10102 to 10642 inclusive, and 10644. Compliance required within 60 days after the effective date of this AD, unless already accomplished: A. To prevent unselected flap extension, isolate the prestall warning power supply wires from the flap down limit switch in accordance with Fokker Service Bulletin F27/34-52, dated March 23, 1983. B. Alternate means of compliance which provide an acceptable level of safety may be used when approved by the Manager, Standardization Branch, ANM-113, FAA, Northwest Mountain Region. C. Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes to a base for the accomplishment of inspections and/or modifications required by this AD. All persons affected by this directive who have not already received the appropriate service documents from the manufacturer may obtain copies uponrequest to the Manager, Maintenance and Engineering, Fokker B.V., Product Support, P.O. Box 7600, 11172J Schiphol Oost, The Netherlands. These documents may be examined at the FAA, Northwest Mountain Region, 17900 Pacific Highway South, Seattle, Washington, or the Seattle Aircraft Certification Office, 9010 East Marginal Way South, Seattle, Washington. This amendment becomes effective February 28, 1986.
2000-10-05: This amendment adopts a new airworthiness directive (AD) that applies to Eurocopter France Model SE.3160, SA.316B, SA.316C, SA.319B, SA330F, SA330G, SA330J, SA341G, and SA342J helicopters. This AD requires inspecting each inflation head and union nut on certain emergency flotation gear nitrogen cylinders and replacing each cracked inflation head with an airworthy inflation head. This amendment is prompted by the discovery of cracked inflation heads during routine maintenance inspections of emergency flotation systems. The actions specified by this AD are intended to prevent an emergency flotation gear nitrogen cylinder from exploding with resultant high velocity shrapnel, which could cause airframe damage or personal injury and subsequent loss of control of the helicopter.
2000-10-11: This amendment adopts a new airworthiness directive (AD), applicable to certain Gulfstream Model G-159 series airplanes, that requires an inspection to determine the type of pneumatic deicing boots, and an Airplane Flight Manual (AFM) revision only for those airplanes equipped with "modern" boots. This amendment is prompted by reports of inflight incidents and an accident that occurred in icing conditions where the airframe pneumatic deicing boots were not activated. The actions specified by this AD are intended to ensure that flightcrews activate the pneumatic wing and tail deicing boots at the first signs of ice accumulation. This action will prevent reduced controllability of the aircraft due to adverse aerodynamic effects of ice adhering to the airplane prior to the first deicing cycle.
2018-18-20: We are adopting a new airworthiness directive (AD) for all Airbus SAS Model A300 B4-600, B4-600R, and F4-600R series airplanes, and Model A300 C4-605R Variant F airplanes (collectively called Model A300-600 series airplanes); and Model A310 series airplanes. This AD was prompted by a determination that more restrictive maintenance requirements and airworthiness limitations are necessary. This AD requires revising the maintenance or inspection program, as applicable, to incorporate new or more restrictive maintenance requirements and airworthiness limitations. We are issuing this AD to address the unsafe condition on these products.
87-06-02: 87-06-02 HONEYWELL, INC., SPERRY COMMERCIAL FLIGHT SYSTEMS DIVISION (SPERRY CORPORATION, AEROSPACE AND MARINE GROUP): Amendment 39-5610. Applicable to the following models of Sperry Electronics Flight Instrument Systems (EFIS) Symbol Generators, which have not been modified to Mod Level S or subsequent: MODEL SPERRY PART NUMBER SG-810 7004544-901 SG-811 7004544-811 SG-610 7004544-902 NOTE: These systems are known to be installed in, but not limited to, deHavilland Model DHC-8, British Aerospace Model BAe 125-800, Cessna Model 650, and Aerospatiale Model ATR-42 series airplanes. Compliance is required as indicated, unless previously accomplished. To reduce the possibility of AHRS attitude and heading computations being contaminated, which can result in frozen attitude and heading displays on both instrument panels, accomplish the following: A. Prior to further flight, install a placard adjacent to the first pilot's electronic attitude direction indicator (EADI), in full view of the pilot, stating "FLIGHT INTO KNOWN IMC PROHIBITED." B. Modification of the Sperry EFIS Symbol Generator models listed above to Mod Level S or subsequent, or installation of the following Sperry EFIS Symbol Generator models, constitutes terminating action of the operational and placard requirements of paragraph A., above: MODEL SPERRY PART NUMBERS MOD LEVEL (OR SUBSEQUENT) SG-811 7004544-211 V SG-811 7004544-311 AD SG-811 7004544-411 U SG-611 7004544-611 S All persons affected by this directive who have not already received the appropriate service documents from the manufacturer, may obtain copies upon request to Honeywell Inc., Sperry Commercial Flight Systems Division (formerly Sperry Corporation, Aerospace and Marine Group), P.O. Box 29000, Phoenix, Arizona 85038-9000. These documents may be examined at the FAA, Northwest Mountain Region, 17900 Pacific Highway South, Seattle, Washington, or the Western Aircraft Certification Office, 15000 Aviation Boulevard, Hawthorne, California. This Amendment becomes effective May 11, 1987, as to all persons, except those persons to whom it was made immediately effective by Priority Letter AD 87-06-02, issued March 13, 1987.
89-19-01: 89-19-01 AIRBUS INDUSTRIE: Amendment 39-6317. (Docket No. 89-NM-77-AD) Applicability: Model A310 series airplanes, as listed in Airbus Industrie Service Bulletin A310-52-2017, Revision 2, dated December 22, 1987, certificated in any category. Compliance: Required as indicated, unless previously accomplished. To prevent frozen condensation from blocking the emergency exit doors' operating mechanism, accomplish the following: A. Within 100 hours time-in-service after the effective date of this AD, modify the emergency exit doors' opening mechanism, in accordance with paragraphs C.(1), C.(2), and C.(3) of Airbus Industrie Service Bulletin A310-52-2017, Revision 2, December 22, 1987. B. Within 9 months after the effective date of this AD, replace all sealing rings on the hinge rods, in accordance with paragraph C.(4) of Airbus Industrie Service Bulletin A310-52- 2017, Revision 2, dated December 22, 1987. C. 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. D. Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes to a base for the accomplishment of 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 Airbus Industrie, Airbus Support Division, Avenue Didier Daurat, 31700 Blagnac, France. These documents may be examined at the FAA, Northwest Mountain Region, Transport Airplane Directorate, 17900 Pacific Highway South, Seattle, Washington, or at the Seattle Aircraft Certification Office, 9010 East Marginal Way South, Seattle, Washington. This amendment (39-6317, AD 89-19-01) becomes effective on October 13, 1989.
97-06-13R1: This amendment rescinds airworthiness directive (AD) 97-06-13 for Rolls-Royce plc (RR) models RB211 Trent 892, 884, 877, 875, and 892B series turbofan engines. That AD requires inspecting and replacing certain angle gearbox and intermediate gearbox hardware, and on-going repetitive inspections of the magnetic chip detectors. That AD resulted from reports of loss of oil from the angle drive upper shroud tube, the intermediate gearbox housing, the external gearbox lower bevel box housing, and by reports of bearing failures. We intended the requirements of that AD to prevent loss of oil, which could cause an engine fire, and to prevent in-flight engine shutdowns and airplane diversions caused by oil loss and from bearing failures. Since we issued that AD, we determined that the inspections and replacements required by that AD are no longer required to correct an unsafe condition.
96-17-06: This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A310 series airplanes, that requires repetitive inspections to detect discrepancies of the slat universal joint and steady bearing assemblies, and replacement of any discrepant assembly with a new, like assembly. This amendment also requires replacement of all slat universal joint and steady bearing assemblies with improved assemblies, which would terminate the repetitive inspections. This amendment is prompted by reports of broken or missing inner races on the slat universal joint and steady bearing assemblies of the slat transmission system. The actions specified by this AD are intended to prevent cracking of the inner race, which could cause it to break off and, consequently, allow the slat universal joint and steady bearing assemblies to become worn; this situation could result in failure of the shaft of the slat transmission system, and subsequent uncommanded movement of the associated slat.
2018-18-18: We are adopting a new airworthiness directive (AD) for all Airbus SAS Model A300 series airplanes. This AD was prompted by a revision of an airworthiness limitation items (ALI) document. This AD requires revising the maintenance or inspection program, as applicable, to incorporate the specified maintenance requirements and airworthiness limitations. We are issuing this AD to address the unsafe condition on these products.
2006-20-01: The FAA is adopting a new airworthiness directive (AD) for all Airbus Model A310 airplanes. This AD requires revising the Limitations section of the airplane flight manual by incorporating restrictions for high altitude operations. This AD results from several incidents of pitch oscillations with high vertical loads that occurred during turbulence at high altitudes. We are issuing this AD to prevent pitch oscillations during turbulence, which could result in reduced controllability of the airplane.
2006-19-12: The FAA is adopting a new airworthiness directive (AD) for certain Boeing Model 777-200 and -300 series airplanes. This AD requires inspecting the lower web of the aft fairing of engine struts for any discoloration and doing any related investigative and corrective action if necessary; inspecting the heat shield castings for any damage and doing any corrective action if necessary; installing gap cover strips; and replacing insulation blankets with new insulation blankets. This AD results from a report that several discolored fairing lower webs and some damaged/deteriorated insulation blankets were found in the aft fairings of engine struts. We are issuing this AD to prevent cracking of lower webs of the aft fairings, which could result in flammable hydraulic fluid leaking onto or near an ignition source, and possibly result in an uncontrollable fire in the engine strut area.