Results
2001-13-14: This amendment adopts a new airworthiness directive (AD) that is applicable to all EMBRAER Model EMB-120 series airplanes. This action requires revising the Airplane Flight Manual, installing a placard on the main instrument panel, and removing the "LIGHT-HEAVY" inflation switch of the leading edge deicing boots. This amendment is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. This action is intended to ensure that the flight crew is provided with accurate indications of the severity of ice accretion and appropriate procedures and actions to prevent reduced controllability of the aircraft due to accretion of ice on the airplane.
2018-12-01: We are superseding Airworthiness Directive (AD) 2012-03-11 for all Safran Helicopter Engines, S.A., Arriel 2B and 2B1 turboshaft engines. AD 2012-03-11 required checking the transmissible torque between the low-pressure (LP) pump impeller and the high-pressure (HP) pump shaft on the HP/LP pump and metering valve assembly, hereafter referred to as the hydro-mechanical metering unit (HMU). Since we issued AD 2012-03-11, the manufacturer determined that incorporating Modification TU 178 is a more effective method to reduce the risk of uncoupling between the LP fuel pump impeller and the HP fuel pump shaft than the prior Modification TU 147. This AD requires inspection and possible replacement of the HMU. This AD was prompted by three cases of uncoupling of the HMU LP fuel pump impeller and the HP fuel pump shaft since AD 2012-03-11 was issued. We are issuing this AD to address the unsafe condition on these products.
92-19-02: 92-19-02 FOKKER: Amendment 39-8359. Docket 92-NM-41-AD. Applicability: Model F28 series airplanes; serial numbers 11003 through 11241, 11991, and 11992; certificated in any category. Compliance: Required as indicated, unless accomplished previously. To prevent reduced structural integrity of the lapjoints between stringers 16 and 17, and consequent decompression, accomplish the following: (a) For airplanes in the post-SBF28/21-16 configuration, repair the lapjoints located between stringers 16 and 17 (58 and 59), between frames 13345 and 14285, in accordance with Fokker Service Bulletin F28/53-121, Revision 1, dated December 13, 1991, and in accordance with the following schedule: (1) For airplanes that have accumulated less than 32,000 flight cycles as of the effective date of this AD, accomplish the repair prior to the accumulation of 32,000 flight cycles or within 35 months after the effective date of this AD, whichever occurs later; (2) For airplanes that have accumulated 32,000 or more flight cycles but less than 40,000 flight cycles as of the effective date of this AD, accomplish the repair prior to the accumulation of 40,000 flight cycles or within 23 months after the effective date of this AD, whichever occurs later; (3) For airplanes that have accumulated 40,000 or more flight cycles as of the effective date of this AD, accomplish the repair within 11 months after the effective date of this AD. (b) For airplanes in the pre-SBF28/21-16 configuration, repair the lapjoints located between stringers 16 and 17, (58 and 59) between frames 13345 and 14285, in accordance with Fokker Service Bulletin F28/53-121, Revision 1, dated December 13, 1991, and in accordance with the following schedule: (1) For airplanes that have accumulated less than 48,000 flight cycles as of the effective date of this AD, accomplish the repair prior to the accumulation of 48,000 flight cycles or within 35 months after the effective dateof this AD, whichever occurs later. (2) For airplanes that have accumulated 48,000 or more flight cycles but less than 60,000 flight cycles as of the effective date of this AD, accomplish the repair prior to the accumulation of 60,000 flight cycles or within 23 months after the effective date of this AD, whichever occurs later. (3) For airplanes that have accumulated 60,000 or more flight cycles as of the effective date of this AD, accomplish the repair within 11 months after the effective date of this AD. (c) Accomplishment of the repairs required by paragraphs (a) and (b) of this AD constitutes terminating action for the inspections identified as item 53-30-08 in the Fokker F-28 Structural Integrity Program (SIP), which are required by AD 89-07-16 R1, Amendment 39-6444. (d) An alternative method of compliance or adjustment of the compliance time that provides an acceptable level of safety may be used if approved by the Manager, Standardization Branch, ANM-113,FAA, Transport Airplane Directorate. Operators shall submit their requests through an appropriate FAA Principal Maintenance Inspector, who may add comments and then send it to the Manager, Standardization Branch, ANM-113. NOTE: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Standardization Branch, ANM-113. (e) Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate the airplane to a location where the requirements of this AD can be accomplished. (f) The repair shall be done in accordance with Fokker Service Bulletin F28/53-121, Revision 1, dated December 13, 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 Fokker Aircraft USA, Inc., 1199 North Fairfax Street, Alexandria, Virginia 22314. Copies may be inspected at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; or at the Office of the Federal Register, 800 North Capitol Street, NW., Suite 700, Washington, DC. (g) This amendment becomes effective on October 8, 1992.
94-17-03: This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 767 series airplanes, that requires inspections, adjustments, and functional checks of the thrust reverser system; installation of a terminating modification; and repetitive operational checks of the gearbox locks and the air motor brake following accomplishment of the modification. This amendment is prompted by the identification of a modification that ensures that the level of safety inherent in the original type design of the thrust reverser system is further enhanced. The actions specified by this AD are intended to prevent possible discrepancies that exist in the current thrust reverser control system, which could result in an inadvertent deployment of a thrust reverser during flight.
2008-03-03: The FAA is adopting a new airworthiness directive (AD) for certain EMBRAER Model EMB-135 airplanes; and Model EMB-145, -145ER, - 145MR, -145LR, -145XR, -145MP, and -145EP airplanes. This AD requires inspections to detect discrepancies of the components of the elevator control system, repetitive movements of the control column to observe the normal response of the elevators, repetitive inspections to detect discrepancies of the skin of the elevators, and applicable related investigative actions and corrective actions. This AD also provides for optional terminating actions for the inspections and measurements. This AD results from a report indicating that a Model EMB-145 airplane did not rotate in response to the command from the yoke during take-off, which resulted in a rejected take-off. We are issuing this AD to detect and correct discrepancies of the elevator control system, which could result in reduced control of the elevators and consequent reduced controllability of theairplane.
2001-13-04: This amendment adopts a new airworthiness directive (AD) for Eurocopter France Model EC 155B helicopters. This AD requires, before each takeoff with a cabin sliding door in the open position, visually checking each sliding door to ensure that each door roller is inside its rail. If a roller is outside its rail, before further flight, each roller on each door must be replaced inside its rail. This AD also revises the Limitations section of the Rotorcraft Flight Manual (RFM) by prohibiting the opening and closing of a cabin sliding door in flight. This AD is prompted by the loss of a cabin sliding door in flight. The actions specified by this AD are intended to prevent in- flight loss of a cabin sliding door, impact with the main rotor or fenestron, and subsequent loss of control of the helicopter.
2020-06-14: The FAA is adopting a new airworthiness directive (AD) for all The Boeing Company Model 787-8, 787-9, and 787-10 airplanes. This AD requires repetitive cycling of the airplane electrical power. This AD was prompted by a report that the stale-data monitoring function of the common core system (CCS) may be lost when continuously powered on for 51 days. This could lead to undetected or unannunciated loss of common data network (CDN) message age validation, combined with a CDN switch failure. The FAA is issuing this AD to address the unsafe condition on these products.
2008-02-16: The FAA is adopting a new airworthiness directive (AD) for certain Boeing Model 767-200 and 767-300 series airplanes. This AD requires reworking certain duct assemblies in the environmental control system (ECS). This AD results from reports of duct assemblies in the ECS with burned Boeing Material Specification (BMS) 8-39 polyurethane foam insulation. This AD also results from a report from the airplane manufacturer that airplanes were assembled with duct assemblies in the ECS wrapped with BMS 8-39 polyurethane foam insulation, a material of which the fire retardant properties deteriorate with age. We are issuing this AD to prevent a potential electrical arc from igniting the BMS 8-39 polyurethane foam insulation on the duct assemblies of the ECS, which could propagate a small fire and lead to a larger fire that might spread throughout the airplane through the ECS.
2008-02-15: 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: Some taperlocks used in the wing-to-fuselage junction at rib 1 were found to be non-compliant with the applicable specification, resulting in a loss of pre-tension in the fasteners. In such conditions, the structural integrity of the aircraft could be affected. We are issuing this AD to require actions to correct the unsafe condition on these products.
2020-05-22: The FAA is adopting a new airworthiness directive (AD) for certain Yabor(atilde) Ind(uacute)stria Aeron(aacute)utica S.A. (Type Certificate Previously Held by Embraer S.A.) Model ERJ 170 airplanes. This AD was prompted by a report of erroneous indications of certain engine parameters and reports of ''pitch up'' and ''pitch down'' uncommanded attitudes with autopilot engaged in cruise flight. This AD requires installing updated PRIMUS EPIC LOAD software, as specified in an Ag(ecirc)ncia Nacional de Avia(ccedil)(atilde)o Civil (ANAC) Brazilian AD, which is incorporated by reference. The FAA is issuing this AD to address the unsafe condition on these products.
2001-13-06: This amendment adopts a new airworthiness directive (AD); applicable to certain Boeing Model 747-100, -200, -300, and 747SP series airplanes; that requires certain inspections to find missing and alloy-steel taperlock fasteners (bolts) in the diagonal brace underwing fittings; and corrective actions, if necessary. For airplanes with missing or alloy-steel fasteners, this AD also mandates replacement of certain fasteners with new fasteners, which constitutes terminating action for the repetitive inspections. This action is necessary to prevent loss of the underwing fitting load path due to missing or damaged alloy-steel taperlock fasteners, which could result in separation of the engine and strut from the airplane. This action is intended to address the identified unsafe condition.
94-15-16: This amendment adopts a new airworthiness directive (AD), applicable to Pratt & Whitney JT9D series turbofan engines, that requires a one-time modification and overhaul of engine control system accessories. This amendment is prompted by multiple engine surge and power loss events caused by deterioration of internal components of engine control system accessories. The actions specified by this AD are intended to prevent the loss of engine compressor surge margin caused by the deterioration of engine control system accessories, resulting in an engine surge, and subsequent power loss or inflight engine shutdown.
2008-02-18: We are adopting a new airworthiness directive (AD) for certain Cessna Aircraft Company 172 series airplanes with the BRS-172 Parachute System installed via Supplemental Type Certificate (STC) No. SA01679CH and Cessna Aircraft Company 182 series airplanes that are equipped with the BRS-182 Parachute System installed via STC No. SA01999CH. This AD requires you to replace the pick-up collar support and nylon screws for the BRS-172 and BRS-182 Parachute System. This AD results from notification by Ballistic Recovery Systems, Inc. (BRS) that the pick-up collar assembly may prematurely move off the launch tube and adversely affect rocket trajectory during deployment. We are issuing this AD to prevent premature separation of the collar, which could result in the parachute failing to successfully deploy.
2001-13-13: This amendment adopts a new airworthiness directive (AD) that is applicable to all Airbus Model A330 and A340 series airplanes. This action requires revising the Airplane Flight Manual to advise the flight crew of appropriate procedures to follow in the event of lost or erroneous airspeed indications. This action is necessary to prevent inadvertent excursions outside the normal flight envelope. This action is intended to address the identified unsafe condition.
2020-05-19: The FAA is adopting a new airworthiness directive (AD) for certain Airbus SAS Model A319-112, -115, and -132 airplanes; and Model A320-214, -216, -232, and -233 airplanes. This AD was prompted by a report that a possible interference was identified between 1M and 2M wiring harnesses and the tapping units, and that the interference could adversely affect the lavatory smoke detection system and/or the passenger oxygen system. This AD requires modifying the 1M and 2M harness routing, 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.
2004-24-08: This amendment adopts a new airworthiness directive (AD) for the specified Bell Helicopter Textron Canada (BHTC) model helicopters. This action requires an initial inspection and, at specified intervals, certain repetitive checks and inspections of the tail rotor blade (blade) for a deformation, a crack, and a bent or deformed tail rotor weight (weight). Also, this action requires, before further flight, replacing each blade with an airworthy blade if a deformation, a crack, or a bent or deformed weight is found. This amendment is prompted by three reports of skin cracks originating near the blade trailing edge balance weight. This condition, if not detected, could result in blade failure and subsequent loss of control of the helicopter.
2001-13-02: This amendment adopts a new airworthiness directive (AD) for Bell Helicopter Textron Canada (BHTC) Model 407 helicopters that requires replacing certain cockpit warning horns. This amendment is prompted by reports that pilots have had difficulty in distinguishing between the FADEC Fail horn, the Engine Out horn, and the Low Rotor RPM horn. The actions specified by this AD are intended to assist the pilot in properly identifying a specific cockpit warning horn (horn) and prevent an inappropriate pilot response to a horn, which could cause an engine overspeed and subsequent uncommanded reduction to flight-idle engine power.
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.