Results
2018-21-04: We are adopting a new airworthiness directive (AD) for Glasflugel Models Club Libelle 205, H 301 ''Libelle,'' H 301B ''Libelle,'' Kestrel, Mosquito, Standard ''Libelle,'' and Standard Libelle-201B gliders. 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 jamming between the double two-ring end of the towing cable and the deflector angles of the center of gravity (C.G.) release mechanism. We are issuing this AD to require actions to address the unsafe condition on these products.
2007-01-05: This amendment adopts a new airworthiness directive (AD) for the specified Sikorsky Aircraft Corporation (Sikorsky) model helicopters that requires, within a specified time, creating a component history card or equivalent record. The AD also requires recording the hours time-in-service (TIS) and the external lift cycles (lift cycles) for each main gearbox input left and right freewheel unit (IFWU) assembly. Also, the AD requires calculating a moving average of lift cycles per hour TIS at specified intervals on each IFWU assembly. The moving average is used to determine if an IFWU assembly is used in repetitive external lift (REL) or non-REL helicopter operations. If an IFWU assembly is used in REL operations, this AD requires a visual and dimensional inspection of the IFWU assembly at specified intervals. This AD also requires recording certain information and replacing each part that is beyond the wear limits or that exhibits visual surface distress with an airworthy part. Inaddition, this AD requires permanently marking the REL IFWU camshafts and gear housings with the letters "REL" on the surface of these parts. This amendment is prompted by an accident in which the left and right IFWU assembly on a helicopter slipped or disengaged resulting in both engines over speeding, engine shutdowns, and loss of engine power to the transmissions. The actions specified by this AD are intended to prevent slipping in the IFWU assembly, loss of engine power to the transmissions, and subsequent loss of control of the helicopter.
2000-14-17: This amendment supersedes an existing airworthiness directive (AD), applicable to certain Bombardier Model CL-600-2B19 series airplanes, that currently requires revising the Airplane Flight Manual (AFM) to require the flight crew to check, and reset, if necessary, certain instrument settings prior to each takeoff and after any event during which generators are switched. This amendment adds a new revision to the AFM and revises the applicability of the existing AD. This amendment also requires modification of the air data reference systems. 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 prevent uncommanded changes in certain instrument settings on the pilot"s and copilot"s instrument displays, which could result in confusion among the flight crew about the correct position and flight configuration of the airplane.
2007-01-03: 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: During certification works it was found that the cooling liquid EVANS NPG+ is flammable. The liquid cooling circuit of the Stemme S10-VT is not designed to be filled with a flammable liquid without prior modifications. This AD requires actions that are intended to address the unsafe condition described in the MCAI.
2021-15-13: The FAA is adopting a new airworthiness directive (AD) for all Airbus SAS Model A330-841 and -941 airplanes. This AD was prompted by reports of missing or disbonded pressure seals on two thrust reverser (TR) translating cowls. This AD requires a one-time inspection of each thrust reverser for damage, seal bonding rework, and replacement of translating cowl pressure seals if necessary, 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.
2021-15-09: The FAA is adopting a new airworthiness directive (AD) for certain Leonardo S.p.a. Model AB139 and AW139 helicopters. This AD was prompted by two events of uncommanded emergency flotation system (EFS) deployment during flight. This AD requires replacing certain part- numbered EFS control panels and prohibits installing them. The FAA is issuing this AD to address the unsafe condition on these products.
2018-21-02: We are adopting a new airworthiness directive (AD) for Viking Air Limited Model DHC-3 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 pitting corrosion on the shank of the wing strut attach bolts. We are issuing this AD to require actions to address the unsafe condition on these products.
87-08-07: 87-08-07 MCDONNELL DOUGLAS: Amendment 39-5611. Applies to McDonnell Douglas Model DC-9-81, -82, and -83 airplanes, certificated in any category, equipped with Goodyear main landing gear wheel assemblies, Part Number 5007897. \n\n\tCompliance required as indicated, unless previously accomplished. \n\n\tTo minimize the potential for a wheel failure, accomplish the following: \n\n\tA.\tWithin the next 150 landings after the effective date of this AD, unless the wheel was inspected within the last 150 landings, inspect the wheel assembly for cracks in accordance with McDonnell Douglas Alert Service Bulletin A32-219, dated February 17, 1987, or later revision approved by the Manager, Los Angeles Aircraft Certification Office, FAA, Northwest Mountain Region. \n\n\tB.\tIf no cracks are found, repeat the inspections specified in paragraph A., above, at each tire change or every 300 landings, whichever occurs first. \n\n\tC.\tIf crack(s) are found, replace the wheel before further flight. \n\n\tD.Replacement with Goodyear wheel assembly Part Number 5007897-1 constitutes terminating action for the inspections required by paragraphs A. and B., above. \n\n\tE.\tAlternate means of compliance which provides an acceptable level of safety may be used when approved by the Manager, Los Angeles Aircraft Certification Office, FAA, Northwest Mountain Region. \n\n\tAll persons affected by this directive who have not already received the appropriate service information from the manufacturer may obtain copies upon request to McDonnell Douglas Corporation, 3855 Lakewood Boulevard, Long Beach, California 90846, Attention: Director, Publications and Training, C1-750 (54-60). This information may be examined at the FAA, Northwest Mountain Region, 17900 Pacific Highway South, Seattle, Washington, or the Los Angeles Aircraft Certification Office, 4344 Donald Douglas Drive, Long Beach, California. \n\n\tThis amendment becomes affective May 11, 1987.
2006-26-12: The FAA is superseding an existing airworthiness directive (AD), which applies to all Airbus Model A330, A340-200, and A340-300 series airplanes. That AD currently requires repetitive inspections of a certain bracket that attaches the flight deck instrument panel to the airplane structure; replacement of the bracket with a new, improved bracket; and related investigative and corrective actions if necessary. This new AD requires replacement of the existing bracket with a titanium-reinforced bracket, which ends the repetitive inspections in the existing AD. This AD also requires related investigative and corrective actions while accomplishing the replacement, and reduces the applicability in the existing AD. This AD results from a report of cracking damage found on certain brackets that were replaced per the requirements in the existing AD. We are issuing this AD to prevent a cracked bracket. Failure of this bracket, combined with failure of the horizontal beam, could result incollapse of the left part of the flight deck instrument panel, and consequent reduced controllability of the airplane.
2006-26-07: We are adopting a new airworthiness directive (AD) for the products listed above. 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: A simultaneous interruption of the lubrication on both engines may lead to a double non-commanded in-flight shutdown. The condition described in the MCAI can lead to a forced autorotation landing or an accident. This AD requires actions that are intended to address the unsafe condition described in the MCAI.
2021-15-12: The FAA is adopting a new airworthiness directive (AD) for all Pratt & Whitney Canada Corp. (P&WC) PW210A and PW210S model turboshaft engines. This AD was prompted by a report from the manufacturer that the Automated Damage Tracking System (ADTS) may under-count the number of cycles accrued by the impeller and the high-pressure compressor (HPC) rotor. This AD requires use of the manual low-cycle fatigue (LCF) counting method in place of the ADTS counting method to determine the number of cycles accrued by the impeller and HPC rotor. The FAA is issuing this AD to address the unsafe condition on these products.
2006-26-08: The FAA is adopting a new airworthiness directive (AD) to supersede AD 2006-02-51, which applies to certain Raytheon Aircraft Company Model 390 airplanes. AD 2006-02-51 currently requires you to inspect the left engine hydraulic pump outlet tube and the clamp; replace the clamp at each inspection; replace the hydraulic pump outlet tube immediately if any problem is found; and report the results of each inspection or replacement to the FAA. This AD is the result of several hydraulic pump outlet tube failures after issuance of AD 2006- 02-51, including failures on the right engine. This AD requires you to visually inspect the hydraulic pump outlet tube on both engines on a recurring basis and immediately replace the tube if damage is found. This AD also requires incorporation of an Airplane Flight Manual (AFM) change to not allow operation of an engine with its associated firewall hydraulic shutoff valve closed. In addition, this AD requires you to replace the hydraulic pump outlet tube if an engine is operated with its firewall hydraulic shutoff valve closed. We are issuing this AD to prevent failure of the hydraulic pump outlet tube and consequent leaking of hydraulic fluid. Such leakage could result in a fire. There is also a risk of loss of hydraulic system functions including normal gear extensions, speed brakes, roll spoilers, lift dump, and normal brakes. DATES: This AD becomes effective on December 28, 2006. The Director of the Federal Register previously approved the incorporation by reference of the documents listed in this AD on February 2, 2006 (71 FR 5581, February 2, 2006). We must receive any comments on this AD by February 26, 2007.
87-03-04: 87-03-04 CASA: Amendment 39-5515. Applies to CASA Model C-212 series airplanes listed in CASA Service Bulletins 212-27-30 and 212-27-31, both dated October 23, 1985, certificated in any category. Compliance is required within 8 months after the effective date of this AD. To reduce the potential for a mis-trimmed takeoff, accomplish the following, unless previously accomplished: A. Replace the trim control markings and placards in accordance with CASA Service Bulletins 212-27-30 (CC series airplanes) or 212-27-31 (CB series airplanes), both dated October 23, 1985, as applicable. B. 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. 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 the modifications required bythis AD. All persons affected by this directive who have not already received the appropriate service document from the manufacturer may obtain copies upon request to Construcciones Aeronauticas S.A., Getafe, Madrid Spain. This document 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 19, 1987.
2006-26-02: 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: a leaking brass fuel connection (part no. 10AB-75) was found during maintenance check. This AD requires actions that are intended to address the unsafe condition described in the MCAI.
2018-22-03: We are superseding Airworthiness Directive (AD) 2016-24-03, which applied to certain Bombardier, Inc., Model DHC-8-400 series airplanes. AD 2016-24-03 required repetitive detailed inspections of barrel nuts and cradles, a check of the bolt torque of the preload indicating (PLI) washers, and corrective actions if necessary. This AD retains the requirements of AD 2016-24-03 and requires modifying the airplane by installing a sealing disk to a certain location and replacing certain barrel nuts. This AD was prompted by reports of cracked and corroded barrel nuts found at the mid-spar location of the horizontal-stabilizer-to-vertical-stabilizer attachment joint, and the issuance of new service information that includes a terminal modification. We are issuing this AD to address the unsafe condition on these products.
2006-26-01: The FAA is adopting a new airworthiness directive (AD) for certain CFM International CFM56 Series turbofan engines. This AD requires replacing certain fuel filters manufactured under parts manufacturer approvals (PMA). This AD results from 12 reports of failed fuel filters. We are issuing this AD to prevent the loss of engine thrust that could result in loss of control during takeoff or landing.
85-23-06: 85-23-06 CESSNA: Amendment 39-5225. Applies to Model T303 (Serial Numbers T30300001 thru T30300315) airplanes certificated in any category. Compliance: Required within the next 10 hours time-in-service from the effective date of this AD, unless already accomplished. To preclude the possibility of the fuel metering unit tee fittings from leaking and causing a fire, accomplish the following: (a) Remove both engine cowlings to the extent required to adequately examine the turbocharger inlet area and fuel metering units. Visually inspect the turbocharger inlet and surrounding area for evidence of significant damage caused by exhaust gas leakage. If noted, prior to further flight, repair the damage and eliminate the cause of the leak. (b) With the aircraft auxiliary fuel pumps on and the mixture control in the idle cutoff position, visually inspect the fuel metering unit tee fitting for cracking and leakage in the threaded area that goes into the fuel metering unit. If a crack and resultant leak is detected, prior to further flight replace the fitting, using a wrench on the fitting, to isolate the effects of attaching and tightening the fuel lines. Do not over torque the fitting when installing it on the metering unit. (c) The aircraft may be flown in accordance with FAR 21.197 to a location where this AD can be accomplished. (d) Within five (5) days of accomplishing this AD, report, in writing, all defects found during accomplishment of this AD to the Manager, Wichita Aircraft Certification Office, 1801 Airport Road, Room 100, Mid-Continent Airport, Wichita, Kansas 67209. (Reporting approved by the Offices of Management and Budget under OMB No. 2120-0056.) (e) An equivalent method of compliance may be used when approved by the Manager, Wichita Aircraft Certification Office, Federal Aviation Administration, Central Region, 1801 Airport Road, Room 100, Mid-Continent Airport, Wichita, Kansas 67209. This amendment becomes effective on February 5, 1986, to all persons except those persons to whom it has already been made effective by priority letter from the FAA dated November 14, 1985, and is identified as AD 85-23-06.
2006-25-17: The FAA is adopting a new airworthiness directive (AD) for certain Bombardier Model DHC-8-400 series airplanes. This AD requires repetitive cleaning/inspecting of the drain hole of each pitot static probe and repetitive cleaning of the pitot lines in the pitot static system. This AD results from reports of incidents of airspeed mismatch between the pilot, co-pilot, and standby airspeed indications caused by contamination in the pitot static system. We are issuing this AD to prevent erroneous/misleading altitude and airspeed information from a contaminated pitot static system to the flightcrew, which could reduce the ability of the flightcrew to maintain the safe flight and landing of the airplane.
2021-14-13: The FAA is adopting a new airworthiness directive (AD) for all Pratt & Whitney (PW) PW2037, PW2037M, PW2040, and F117-PW-100 model turbofan engines. This AD was prompted by a report of an uncontained engine failure resulting from cracks in the knife edge of the high- pressure turbine (HPT) 2nd-stage air seal assembly. This AD requires fluorescent penetrant inspections (FPIs) and visual inspections of the HPT 2nd-stage air seal assembly and, depending on the results of the inspections, replacement of the HPT 2nd-stage air seal assembly with a part eligible for installation. This AD also requires replacement of the affected HPT 2nd-stage air seal assembly, depending on the engine model, at either the next engine shop visit or the next piece-part opportunity. The FAA is issuing this AD to address the unsafe condition on these products.
89-10-02: 89-10-02 AEROSPATIALE: Amendment 39-6201. Applicability: Model ATR42-300 series airplanes up to and including serial number 120, which have not been modified in accordance with Service Bulletin ATR42-28-0013, Revision 2, dated January 6, 1989, certificated in any category. Compliance: Required as indicated, unless previously accomplished. To prevent a fuel fire in the nacelle, accomplish the following: A. Within 300 flight hours after the effective date of this AD and thereafter at intervals not to exceed 300 flight hours, and at each engine removal/installation, inspect the engine fuel supply hoses for fuel leakage in accordance with Aerospatiale Service Bulletin ATR42-28-0012, dated September 9, 1988. If leakage is found, before further flight, repair or replace the leaking fuel line, in accordance with the service bulletin. B. Replacement of the engine fuel supply hoses in accordance with Aerospatiale Service Bulletin ATR42-28-0013, Revision 2, datedJanuary 6, 1989, constitutes terminating action for the repetitive inspections required by paragraph A., above. 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 may add any comments 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 inspections and/or modification 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 upon request to Aerospatiale, 316 Route de Bayonne, 31060 Toulouse, Cedex 03, France. These documents may be examined atthe FAA, Northwest Mountain Region, 17900 Pacific Highway South, Seattle, Washington, or at the Seattle Aircraft Certification Office, 9010 East Marginal Way South, Seattle, Washington. This amendment (39-6201, AD 89-10-02) becomes effective on May 29, 1989.
86-17-09: 86-17-09 BELL HELICOPTER TEXTRON, INC.: Letter issued August 21, 1986. Applies to all Bell Helicopter Model 212 helicopters, S/N 30501 through 30999, 31101 through 31273, and 31275; 32101 through 32142 and 32201 through 32262 that have T/R hub and blade assembly, P/N 212-011-701-001 installed, certified in any category. Compliance required as indicated unless already accomplished. To prevent failure of the tail rotor control, accomplish the following: (a) Within 25 hours' time in service after receipt of this AD, visually inspect the T/R hub assembly P/N 212-011-701-3, in accordance with Part 1 of Bell Helicopter Textron, Inc. (BHTI), Alert Service Bulletin (ASB) 212-86-39, Revision "A," dated July 23, 1986. (1) If the (P/N) 212-011-716-1 T/R trunnion housing is cracked or there is axial play in the T/R trunnion, or if there are excess balance washers, comply with Part II of the Alert Service Bulletin before further flight. (2) Repeat this inspection every 25 hours' time in service until paragraph (b) of this AD is accomplished. (b) Remove the 212-011-701-1 T/R hub and blade assembly and inspect the trunnion bearing housing, P/N 212-011-716-1, as detailed in Part II of BHTI ASB 212-86-39, Revision "A", dated July 23, 1986, within 150 hours' time in service or within 60 days after the issue date of this AD, whichever occurs first. Replace any housing having an end web thickness of .059 inch or less with a serviceable part. An alternate method of compliance or adjustment of the compliance time, which provides an equivalent level of safety, may be approved by the Manager, Helicopter Certification Branch, Aircraft Certification Division, FAA, Southwest Region. This airworthiness directive becomes effective upon receipt.
2006-25-10: The FAA is adopting a new airworthiness directive (AD) for all BAE Systems (Operations) Limited Model BAe 146 and Model Avro 146-RJ airplanes. This AD requires calculating the current life of each lift spoiler jack, and eventually replacing each lift spoiler jack. This AD results from a review of all system components as part of the life- extension program for the affected airplanes that indicated the fatigue life limit of certain lift spoiler jacks cannot be extended from the current life limit. We are issuing this AD to prevent failure of the lift spoiler jack, and consequent increased drag and uncommanded roll inputs, which could reduce the flightcrew's ability to control the airplane.
2006-25-11: The FAA is adopting a new airworthiness directive (AD) for certain Lockheed Model L-1011 series airplanes. This AD requires a one- time detailed inspection of the C112 harness clamp assembly for proper installation, a one-time detailed inspection of the C112 and C162 harness assemblies for damage, and corrective actions if necessary. This AD results from a report of electrical arcing of the essential bus feeder cables behind hinged circuit breaker panel CB3 P-K. We are issuing this AD to prevent arcing of essential bus feeder cables due to improper installation of the harness C112 clamp assembly, which could result in loss of electrical systems and smoke and/or fire behind the CB3 P-K hinged circuit breaker panel in the flight compartment.
2021-11-10: The FAA is adopting a new airworthiness directive (AD) for certain Airbus Helicopters Model SA-365N, SA-365N1, AS-365N2, and AS 365 N3 helicopters. This AD was prompted by a report that damage (scorch marks) was found on an internal life raft installation that contained a half rescue kit. This AD requires identifying the part number and serial number of each half rescue kit located in the internal life raft installation and, depending on the findings, inspecting the life raft for damage, inspecting the condition of the flashlight battery, testing the flashlight battery, and replacing the life raft or flashlight battery (including the leak test) as applicable, as specified in a European Aviation Safety Agency (now 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.
2021-14-01: The FAA is adopting a new airworthiness directive (AD) for certain Bombardier, Inc., Model BD-100-1A10 airplanes. This AD was prompted by a report that certain airplanes have navigation units with outdated magnetic variation (MagVar) tables. This AD requires revising the existing airplane flight manual (AFM) and applicable corresponding operational procedures to update the flight management system (FMS) limitations. The FAA is issuing this AD to address the unsafe condition on these products.