Results
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.
95-17-15: This amendment adopts a new airworthiness directive (AD), applicable to General Electric Company (GE) CF6-45/-50 series turbofan engines, that requires an initial and repetitive on-wing visual inspection of the side links of the five-link forward mount assembly for cracks, and replacement of the side links and pylon attachment bolts, and inspection of the fail-safe bolt and platform lug, if the side links are found cracked. This AD also requires a shop-level refurbishment of the side links as a terminating action to the on-wing inspection program. This amendment is prompted by four reports of cracked side links detected during routine engine shop visits. The actions specified by this AD are intended to prevent a side link fracture, which could result in the failure of the second side link, or the forward engine mount pylon attachment bolts, and possible separation of the engine from the aircraft.
2008-13-06: The FAA adopts a new airworthiness directive (AD) for certain Cessna Aircraft Company (Cessna) Models 208 and 208B airplanes. This AD requires you to inspect the left and right wing wire bundle(s) and repair or replace damaged wire. This AD also requires inspecting the wire bundles for correct attachment to the anchor points and correcting any deficient attachments. This AD results from chafed wiring found on wire bundles in the left and right wings containing the auto-control wing de-ice system, fuel quantity indication, and low fuel annunciation on the Cessna 208B airplanes. Improper installation of wire bundle supporting hardware can cause chafed wiring in the affected bundles. We are issuing this AD to detect and correct damaged wiring of the auto- control wing de-ice system, fuel quantity indication, and low fuel annunciation systems. This condition could result in incorrect fuel quantity indications, loss of low fuel quantity annunciations, or loss of the autocontrol wing de-ice system.
2000-10-08 R1: This amendment revises an existing airworthiness directive (AD) for Eurocopter France (ECF) Model SA-365N1, AS-365N2, and SA-366G1 helicopters. That AD currently requires inspecting each tail rotor blade for bonding separation, measuring the clearance between the tip of each tail rotor blade and the circumference of the air duct, and replacing the blade if necessary. This amendment requires the same actions but allows the pilot to perform the daily visual check and contains a damage allowance for certain blades. This amendment is prompted by FAA determination that the pilot can check for a cracked, blistered, or wrinkled blade and that some debonding of the blade is acceptable. The actions specified by this AD are intended to allow a pilot check, to prevent unacceptable damage to a tail rotor blade, and to prevent loss of tail rotor control and subsequent loss of control of the helicopter.
95-18-02: This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 757 and 767 series airplanes, that requires replacement of the hydraulic pressure transfer tube of the ram air turbine (RAT) system with a new hose assembly. This amendment is prompted by reports that, during flight tests, the hydraulic pressure transfer tube of the RAT cracked when the RAT was extended on a Model 767 series airplane due to overload of the hydraulic transfer tube. The actions specified by this AD are intended to prevent such overload, which could result in cracking of the hydraulic transfer tube. Such cracking subsequently could lead to the loss of hydraulic fluid of the center system and the inability of the RAT to pressurize the center system; this situation could lead to loss of all hydraulic system power in the event that power is lost in both engines.
2020-17-15: The FAA is adopting a new airworthiness directive (AD) for all MHI RJ Aviation ULC Model CL-600-2B19 (Regional Jet Series 100 & 440), CL-600-2C10 (Regional Jet Series 700, 701 & 702), CL-600-2C11 (Regional Jet Series 550), CL-600-2D15 (Regional Jet Series 705), CL-600-2D24 (Regional Jet Series 900), and CL-600-2E25 (Regional Jet Series 1000) airplanes. This AD was prompted by a determination that certain airplanes have outdated magnetic variation (MV) tables inside navigation systems. This AD requires revising the existing airplane flight manual (AFM) to update the Flight Management System (FMS), Inertial Reference System (IRS), and Attitude and Heading Reference System (AHRS) limitations. The FAA is issuing this AD to address the unsafe condition on these products.
2008-13-16: 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 two incidents of fan blade dislodgements due to blade fracture on relatively hi-time PW305 engines (over 5000 Hrs). The blade dislodgement in both cases was contained. However, engine installations sustained considerable collateral damage. The root cause of fan blade fracture was determined to be the under-minimum material condition at the fracture location. This AD requires actions that are intended to address the unsafe condition described in the MCAI, which could result in an engine shutdown and damage to the airplane.
2001-20-04: This amendment adopts a new airworthiness directive (AD) for Agusta S.p.A. (Agusta) Model A109E helicopters that requires modifying the passenger compartment sliding doors by installing certain locking mechanism kits. This amendment is prompted by accidental opening of a passenger compartment sliding door (door) in flight due to a door locking mechanism that is too easy to accidentally open. The actions specified by this AD are intended to prevent accidental opening of a door in flight and subsequent loss of objects that could damage the rotor system.
95-18-03: This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 767 series airplanes, that requires modification of the off-wing ramp/slide evacuation systems. This amendment is prompted by reports of punctured tubes on certain BFGoodrich off- wing ramp/slide evacuation systems installed on these airplanes. The actions specified by this AD are intended to prevent such tube punctures, which could delay or impede the evacuation of passengers during an emergency.
2008-13-18: 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 Airworthiness Directive (AD) is prompted due to a potential problem with the tail landing gear locking mechanism of PC-6 series aircraft. Investigation, carried out after an incident report, determined that both screws of the tail-wheel locking mechanism had ruptured, rendering the mechanism inoperative. We are issuing this AD to require actions to correct the unsafe condition on these products.
2020-19-13: The FAA is adopting a new airworthiness directive (AD) for certain Bombardier, Inc., Model CL-600-1A11 (600), CL-600-2A12 (601), and CL-600-2B16 (601-3A, 601-3R, and 604 Variants) airplanes. This AD was prompted by a report that fast and easy access to the portable oxygen bottle may be prevented by the portable oxygen bottle installation's upper bracket latch assembly catching on the pressure gauge tube or on the pressure gauge bezel of the portable oxygen bottle. This AD requires a check to identify the manufacturer and part number of the portable oxygen bottle installation, and, if necessary, modification of the portable oxygen bottle installation. The FAA is issuing this AD to address the unsafe condition on these products.
2008-12-19: 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: This Airworthiness Directive (AD) is issued following the discovery of a potential chafing between the feeder bundle and the right side partition wall separating the cabin from the lavatory at frames 22/23. This chafing may damage the feeder bundle and cause a sustained smoke-generating short-circuit between the feeder and the partition wall made of resistive composite material. Strong smoke and a difficult-to-localize short-circuit may result in a hazardous situation. The unsafe condition is sustained smoke in the cabin, which may lead to reduced ability of the flightcrew to operate the airplane. We are issuing this AD to require actions to correctthe unsafe condition on these products.
95-18-14: This amendment adopts a new airworthiness directive (AD) that is applicable to General Electric Company (GE) CF6 series turbofan engines. This action requires a more detailed fluorescent penetrant inspection process for GE CF6 series high pressure compressor rotor (HPCR) stage 3-9 spools. This amendment is prompted by an uncontained failure of the HPCR stage 3-9 spool attributed to a material defect located in the hub to web transition area of the stage 6 disk. The actions specified in this AD are intended to prevent an uncontained HPCR engine failure, which can result in damage to the aircraft.
2008-13-10: 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: Investigation following incidents on the production line has shown that power feeders inside the Secondary Power Distribution Boxes (SPDB) may be damaged because of interference with other internal parts. This condition, if not corrected, may lead to losing essential feeders. The resulting power shortage may reduce aircraft operability and affect flight safety margins. * * * * * Damaged secondary power distribution boxes could lead to loss of electrical power resulting in depressurization with loss of passenger oxygen supply and uncommanded slat retraction. This AD requires actions that are intended to address the unsafe condition described in theMCAI.
95-17-08: This amendment adopts a new airworthiness directive (AD) that applies to Stemme GmbH (Stemme) S10 gliders. This action requires modifying the rudder control cable system. Rupture of a turnbuckle eye bolt in the rudder control cable system on one of the affected gliders prompted this action. The actions specified by this AD are intended to prevent rudder control cable system failure caused by rupture of the turnbuckle eye bolt, which, if not detected and corrected, could result in loss of rudder control and eventual loss of control of the glider.
2001-19-06: This amendment adopts a new airworthiness directive (AD) that is applicable to Rolls-Royce plc (RR) Dart 525, 525F, 528, 528D, 529, 529D, 530, 532, 535, 542, and 552 series turboprop engines. This action requires the removal of certain part number (P/N) high pressure turbine (HPT) discs and replacement with serviceable discs. This \namendment is prompted by three reports of uncontained HPT disc failures and the manufacturer's investigation into disc failure. The actions specified in this AD are intended to prevent HPT disc failure, which could result in an uncontained engine failure and damage to the airplane.
95-18-01: This amendment adopts a new airworthiness directive (AD) that applies to Scheibe Flugzeugbau GmbH SF34 and SF34B gliders. This action requires adding armature (supportive covering) to both wings, modifying the root rib of the left wing and incorporating changes and operating limitations to the flight manual. Failure of the left wing root rib on one of the affected gliders while in flight prompted this action. The actions specified by this AD are intended to prevent fatigue failure of the wing, which could result in loss of control of the glider.
2008-12-16: We are adopting a new airworthiness directive (AD) for certain M7 Aerospace LP SA226 and SA227 series airplanes. This AD requires you to inspect electrical wires/components, hydraulic and bleed air tube assemblies at left-hand (LH) and right-hand (RH) inboard wing leading edge/battery box areas, LH/RH wing stations 51.167 to 81.174, and at all feed-through locations into the LH/RH inboard keelson. If chafing/ arcing is found, this AD requires you to reposition, repair, and/or replace all chafed electrical wires, components, and hydraulic and bleed air tube assemblies, as required. This AD also requires you to reposition the battery lead cables, cover four-gauge wires leaving the battery box with firesleeving and secure with clamps, and protect the battery power cable. This AD results from five reports of chafing between the bleed air tube and the electrical starter cables with one incident resulting in a fire. We are issuing this AD to detect and correct chafing/arcing of electrical wires, components, and bleed air lines. This condition could result in arcing of the exposed wires and burn a hole in the bleed air line or the nearby hydraulic line, and lead to a possible hydraulic fluid leak and fire in the engine nacelle compartment.
2001-19-05: This amendment adopts a new airworthiness directive (AD) that is applicable to Rolls-Royce plc. (RR) models RB211-535C-37, RB211-535E4-37, RB211-535E4-B-37, and RB211-535E4-B-75 turbofan engines, with radial drive steady bearing, part number (P/N) LK76084. This action requires the replacement of certain radial drive steady bearings, installed in the high speed gearbox drive. This amendment is prompted by five reports of radial drive steady bearing failures. The actions specified in this AD are intended to reduce the risk of engine in-flight shutdown, due to failure at low life of radial drive steady bearings.
2020-20-03: The FAA is adopting a new airworthiness directive (AD) for certain Airbus Helicopters Model AS350B2 helicopters. This AD requires performing a test of the main rotor RPM (NR) indicator, and depending on the results, altering the wiring. This AD was prompted by reports of some NR indicators displaying incorrect information. The actions of this AD are intended to address an unsafe condition on these products.
95-17-04: This amendment supersedes an existing airworthiness directive (AD), applicable to all Jetstream Model ATP airplanes, that currently requires revising the Airplane Flight Manual (AFM) to prohibit flight in freezing precipitation conditions. This amendment adds a requirement to install modifications of the engine air intake system. This amendment is prompted by the development of modifications of the engine air intake system intended to permit operation of these airplanes in freezing precipitation conditions. The actions specified by this AD are intended to prevent engine power rollback in flight during freezing precipitation conditions.