Results
2008-13-25: We are adopting a new airworthiness directive (AD) for certain Boeing Model 737-300 and -400 series airplanes. This AD requires testing and inspecting a certain web panel of the main wheel well pressure deck to determine the material type and thickness; and related investigative and corrective actions if necessary. This AD results from several reports indicating that cracks ranging from 0.8 to 8.0 inches long were found on a certain web panel of the main wheel well pressure deck. We are issuing this AD to prevent fatigue cracking in the web panel of the main wheel well pressure deck, which could result in venting and consequent decompression of the airplane.
2001-20-12: This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 757 series airplanes, that requires revising the Airworthiness Limitations Section of the maintenance manual (757 Airworthiness Limitations Instructions (ALI)). The revision will incorporate into the ALI certain inspections and compliance times to detect fatigue cracking of principal structural elements (PSE). This amendment is prompted by analysis of data that identified specific initial inspection thresholds and repetitive inspection intervals for certain PSEs to be added to the ALI. The actions specified by the proposed AD are intended to ensure that fatigue cracking of various PSEs is detected and corrected; such fatigue cracking could adversely affect the structural integrity of these airplanes.
2001-20-18: This amendment adopts a new airworthiness directive (AD) for Robinson Helicopter Company (RHC) Model R44 helicopters that requires establishing a life limit of 2200 hours time-in-service (TIS) for affected horizontal stabilizers. This amendment is prompted by engineering analysis which indicates that certain vertical-to-horizontal stabilizer attach channels (channels) will crack sooner than the original life limit of the horizontal stabilizer. The actions specified by this AD are intended to prevent a crack through a channel, separation of the stabilizers, and subsequent loss of directional control of the helicopter.
2023-11-10: The FAA is adopting a new airworthiness directive (AD) for all Lockheed Martin Corporation/Lockheed Martin Aeronautics Company Model 382, 382B, 382E, 382F, 382G, and 382J airplanes; and Model C-130A, HP- C-130A, EC-130Q, 282-44A-05 (C-130B), C-130B, and C-130H airplanes. This AD was prompted by a report indicating a quality audit found aft fuselage sloping longerons manufactured with an overaged condition. This AD requires a conductivity check on certain aft fuselage sloping longerons and applicable on-condition actions. This AD also limits the installation of certain aft fuselage sloping longerons under certain conditions. The FAA is issuing this AD to address the unsafe condition on these products.
2020-18-02: The FAA is adopting a new airworthiness directive (AD) for certain The Boeing Company Model 747-400, 747-400D, and 747-400F series airplanes. This AD was prompted by the FAA's analysis of the Model 747 fuel system reviews conducted by the manufacturer. This AD requires \n\n((Page 62982)) \n\nmodifying the fuel quantity indicating system (FQIS) to prevent development of an ignition source inside the center fuel tank due to electrical fault conditions. This AD also provides alternative actions for cargo airplanes. The FAA is issuing this AD to address the unsafe condition on these products.
2001-19-52: This document publishes in the Federal Register an amendment adopting Airworthiness Directive (AD) 2001-19-52 which was sent previously to all known U.S. owners and operators of Bell Helicopter Textron Canada (BHTC) Model 222, 222B, 222U, and 230 helicopters by individual letters. This AD requires removing certain serial-numbered main rotor pendulum weight supports from service and replacing with airworthy main rotor pendulum weight supports. This AD is prompted by the failure of a main rotor pendulum weight support (support) resulting in shedding of the weights and an increased level of main rotor vibration. The actions specified by this AD are intended to prevent failure of a support, loss of a weight set resulting in main rotor vibration, and subsequent loss of control of the helicopter. Effective October 30, 2001, to all persons except those persons to whom it was made immediately effective by Emergency AD 2001-19-52, issued on September 21, 2001, which contained the requirements of this amendment. Comments for inclusion in the Rules Docket must be received on or before December 14, 2001.
95-18-05: This amendment adopts a new airworthiness directive (AD) that applies to certain Fairchild Aircraft Models SA226-AT and SA226-TC airplanes. This action requires replacing the two lower aluminum cargo door receptacles with steel receptacles. A report of cargo door failure on one of the affected airplanes prompted this action. Fatigue of the two bottom cargo door receptacles caused the bottom third of the cargo door to bend outward and upward, causing damage to the fuselage door frame. The actions specified by this AD are intended to prevent decompression injuries and the cargo door from breaking off and striking the empennage or the elevator, which could cause substantial structural failure and loss of control of the airplane.
2000-23-12: This amendment adopts a new airworthiness directive (AD), applicable to CFE Company model CFE738-1-1B turbofan engines, that requires new life limits for certain HPC rotor components in all engines. This amendment is prompted by a reduction in the calculated service life of certain compressor rotor rotating parts to values below currently approved service lives. The actions specified by this AD are intended to prevent failure of certain HPC rotor components, which could result in an uncontained engine failure and damage to the airplane.
2008-13-22: The FAA is adopting a new airworthiness directive (AD) for certain Boeing Model 747-400, 747-400D, and 747-400F series airplanes. This AD requires replacement of an electronic flight instrument system/ engine indicating and crew alerting system (EFIS/EICAS) interface unit (EIU) located on the E2-6 shelf of the main equipment center with a new or modified EIU. This AD results from two instances where all six integrated display units (IDUs) on the flight deck panels went blank in flight. We are issuing this AD to prevent loss of the IDUs due to failure of all three EIUs, which could result in the inability of the flightcrew to maintain safe flight and landing of the airplane.
2008-13-27: 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: This AD is issued following a case of non-commanded in-flight engine shut-down which occurred on an ARRIUS 2F turboshaft engine, following the seizing of the gas generator. The result may be an emergency autorotation landing or, at worst, an accident. Investigations of this event have revealed that the seizing of the gas generator was caused by the fracture of the separator cage of the gas generator front bearing, due to high-cycle fatigue cracks initiated in the lubrication slots of the separator cage. We are issuing this AD to prevent uncommanded shutdown of the engine, which could lead to an accident.
2017-24-10: We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 757-200, -200PF, and -300 series airplanes. This AD was prompted by reports of cracking found at a certain fuselage frame inner chord. This AD requires repetitive inspections for any cracking of a certain fuselage frame inner chord; identification of the material of a certain fuselage frame inner chord for certain airplanes; and applicable corrective actions. We are issuing this AD to address the unsafe condition on these products.
2008-13-17: The FAA adopts a new airworthiness directive (AD) for certain Hawker Beechcraft Corporation F33 series and Models G33, V35B, A36, A36TC, B36TC, 95-B55, D55, E55, A56TC, 58, 58P, 58TC, G58, and 77 airplanes. This AD requires you to replace certain circuit breaker toggle switches with improved design circuit breaker toggle switches. This AD results from reports of certain circuit breaker toggle switches used in various electrical systems throughout the affected airplanes overheating. We are issuing this AD to prevent failure of the circuit breaker toggle switch, which could result in smoke in the cockpit and the inability to turn off the switch.
62-11-04: 62-11-04 HUGHES: Amdt. 438 Part 507 Federal Register May 15, 1962. Applies to Model 269A Helicopters Equipped With Lycoming Model 0-360-C2D Engines of Serial Numbers L-3816-36 Through L-4599-36 and L-4601-36 Through L-4640-36. Compliance required within 50 hours' time in service after the effective date of this directive. Because of revisions to the operating limitations necessitated by changes in engine camshafts which resulted in a reduction in maximum horsepower, the FAA approved Flight Manual shall be revised to incorporate the new operating limitations as set forth in Hughes Model 269A Flight Manual revised page 24A. When engines modified to incorporate a new camshaft in accordance with Lycoming Service Instructions are installed, the aircraft may be operated in accordance with original operating limitations. This directive effective May 15, 1962.
2020-20-10: The FAA is superseding Airworthiness Directive (AD) 2018-06- 07, which applied to certain The Boeing Company Model 757-200, -200CB, and -300 series airplanes. AD 2018-06-07 required inspecting the fuselage frame at a certain station for existing repairs, repetitive inspections, and applicable repairs. This AD requires the actions in AD 2018-06-07, with an expanded inspection area, additional inspections, a modified inspection type, and applicable repairs. This AD was prompted by a report of fatigue cracking found in the fuselage frame at a certain station, which severed the inner chord and web. The FAA is issuing this AD to address the unsafe condition on these products.
2017-24-09: We are superseding Airworthiness Directive (AD) 2016-20-11, which applied to certain Airbus 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 Airbus Model A310 series airplanes. AD 2016-20-11 required repetitive inspections of the external area of the aft cargo door sill beam for cracking, repetitive inspections for fatigue cracking of the cargo door sill beam, lock fitting, and torsion box plate, and repair if necessary. This new AD retains the inspections for cracking, and repair if necessary; and requires reinforcement of the aft cargo door sill beam area. This AD was prompted by the development of a reinforcement modification of the aft cargo door sill beam area, which constitutes terminating action for the repetitive inspections. We are issuing this AD to address the unsafe condition on these products.
95-18-12: This amendment adopts a new airworthiness directive (AD) that applies to Mooney Aircraft Corporation (Mooney) Model M20K airplanes. This action requires inspecting to see if the airplane is equipped with a Gerdes fuel selector valve, part number (P/N) A-2580, and replacing any Gerdes fuel selector valve with an Airight fuel selector valve. Malfunction of a Gerdes fuel selector valve on an affected airplane, where the valve did not allow the operator to select the appropriate fuel tank, prompted this action. The actions specified by this AD are intended to prevent fuel selector valve malfunction, which, if not detected and corrected, will prevent the airplane operator from selecting the appropriate fuel tank, resulting in an unscheduled landing.
2008-13-08: 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 aircraft fuel system against fuel tank safety standards * * *. [A]ssessment showed that supplemental maintenance tasks [inspections of various fuel system components such as shields, harnesses, sleeves, and sealant] are required to prevent potential ignition sources inside the fuel system, which could result in a fuel tank explosion. * * * We are issuing this AD to require actions to correct the unsafe condition on these products.
2008-13-21: We are adopting a new airworthiness directive (AD) for certain Boeing Model 767-200, -300, and -400ER series airplanes. This AD requires an inspection to determine the manufacturer and manufacture date of the oxygen masks in the passenger service units and the flight attendant and lavatory oxygen boxes, as applicable. This AD also requires related investigative/corrective actions if necessary. This AD results from a report that several passenger masks with broken in-line flow indicators were found following a mask deployment. We are issuing this AD to prevent the in-line flow indicators of the passenger oxygen masks from fracturing and separating, which could inhibit oxygen flow to the masks and consequently result in exposure of the passengers and cabin attendants to hypoxia following a depressurization event.
2001-20-07: This amendment adopts a new airworthiness directive (AD), applicable to certain Raytheon (Beech) Model 400A series airplanes, that requires replacement of certain bus bars connecting the battery and external power receptacle to the airframe ground with a new, improved bus bar. This amendment is prompted by reports of electrical arcing at the battery and external power receptacle of the airframe ground in the aft fuselage due to a deficiency in the bus bar and washer design. The actions specified by this AD are intended to prevent overheating or arcing of the ground connection in the aft fuselage area, which could result in a fire hazard due to ignition of fuel fumes during an engine start sequence.
2022-26-02: The FAA is superseding Airworthiness Directive (AD) 2013-05-13 for certain Rolls-Royce Deutschland Ltd & Co KG (RRD) BR700-710 series turbofan engines. AD 2013-05-13 required replacing the affected fuel pump splined couplings. Since the FAA issued AD 2013-05-13, the manufacturer has revised the time limits manual (TLM), introducing new and more restrictive instructions, including the replacement of the fuel pump splined coupling. This AD is prompted by service experience that demonstrated premature wear of the splined coupling on the fuel pump and subsequent manufacturer revision of the TLM to incorporate revised life limits and updated mandatory inspection intervals, including replacement of the fuel pump splined coupling. This AD expands the applicability by adding a model turbofan engine and also requires revisions to the airworthiness limitations section (ALS) of the operator's existing approved aircraft maintenance program (AMP), 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.
95-18-13: This amendment adopts a new airworthiness directive (AD) that applies to certain HOAC AUSTRIA GmbH (HOAC) HK 36R "Super Dimona" gliders. This action requires inspecting the exhaust system for corrosion, replacing the exhaust system if corrosion is found, and installing a carbon monoxide detector. Reports received by the Federal Aviation Administration (FAA) of severe exhaust system corrosion on the affected gliders, including one of excessive corrosion (rusting through), prompted this action. The actions specified by this AD are intended to prevent carbon monoxide leakage caused by a corroded exhaust system, which, if not detected and corrected, could lead to passenger injuries.
2008-11-10: 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: There have been reports of inter-rivet cracking on several wing front spar adapter assemblies (P/N C6WM1027-1) on the horizontal and vertical flanges. It was determined that the cracking was caused by stress corrosion in the short transverse grain initiated by local riveting induced stresses. We are issuing this AD to require actions to correct the unsafe condition on these products.
2001-20-16: This amendment adopts a new airworthiness directive (AD) that is applicable to certain Airbus Model A319 and A320 series airplanes. This action requires revising the Airplane Flight Manual to advise the flight crew of performance corrections necessary to ensure adequate runway lengths for certain takeoff and landing conditions. This action is necessary to prevent the airplane from departing the end of the runway during a landing or a rejected takeoff due to reduced braking performance.
90-19-03: 90-19-03 PIPER: Amendment 39-6718. Docket No. 90-CE-03-AD. Applicability: Model PA-38-112 (all serial numbers) airplanes certificated in any category. Compliance: Required within the next 100 hours time-in-service after the effective date of this AD, unless already accomplished. To preclude loosening of the landing gear attachments and possible gear separation, accomplish the following: (a) Modify the main landing gear system in accordance with Piper Service Bulletin 673B, dated October 2, 1986. (b) Airplanes may be flown in accordance with FAR 21.197 to a location where this AD may be accomplished. (c) An alternate method of compliance or adjustment of the compliance time, which provides an equivalent level of safety, may be approved by the Manager, Atlanta Aircraft Certification Office, 1669 Phoenix Parkway, Suite 210C, Atlanta, Georgia 30349. NOTE: The request should be forwarded through an FAA Maintenance Inspector, who may add comments and send it to the Manager, Atlanta Aircraft Certification Office. All persons affected by this directive may obtain copies of the document referred to herein upon request to the Piper Aircraft Corporation, 2926 Piper Drive, Vero Beach, Florida 32960, telephone (407) 567-4361; or may examine this document at the FAA, Central Region, Office of the Assistant Chief Counsel, Room 1558, 601 East 12th Street, Kansas City, Missouri 64106. Airworthiness Directive 90-19-03 supersedes AD 83-05-04 (Amendment 39-4581) which superseded AD 80-11-09 (Amendment 39-3779). This amendment (39-6718, AD 90-19-03) becomes effective on October 15, 1990.
2018-20-12: We are adopting a new airworthiness directive (AD) for certain Bombardier, Inc., Model DHC-8-102, -103, and -106 airplanes, Model DHC- 8-200 series airplanes, and Model DHC-8-300 series airplanes. This AD was prompted by reports of arcing and smoke emanating from the windshield, caused by loose or damaged windshield heater terminal lugs. This AD requires revising the maintenance or inspection program to incorporate maintenance review board (MRB) tasks for general visual inspections of the windshield moisture seal. This AD also requires re- torqueing the windshield heater terminal lugs, applying a coating to the windshield heater screw heads, doing a chemical cleaning of the wiring and components, doing a visual inspection of the wiring and components, doing an operational test of the pilot's and co-pilot's windshield heating system, and repair if necessary We are issuing this AD to address the unsafe condition on these products.