Results
2005-04-07: The FAA is adopting a new airworthiness directive (AD) for all Bombardier Model CL-600-2B19 (Regional Jet Series 100 & 440) airplanes and Model CL-600-1A11 (CL-600), CL-600-2A12 (CL-601), and CL-600-2B16 (CL-601-3A, CL-601-3R, and CL-604) series airplanes. This AD requires revising the airplane flight manuals to include a new cold weather operations limitation. This AD is prompted by a report that even small amounts of frost, ice, snow, or slush on the wing leading edges or forward upper wing surfaces can cause an adverse change in the stall speeds, stall characteristics, and the protection provided by the stall protection system. We are issuing this AD to prevent possible loss of control on take-off resulting from even small amounts of frost, ice, snow, or slush on the wing leading edges or forward upper wing surfaces.
2005-04-09: This amendment supersedes an existing airworthiness directive (AD) for the specified Bell Helicopter Textron Canada (BHTC) model helicopters that currently requires certain checks and inspections of the tail rotor blades. If a crack is found, the existing AD requires replacing the tail rotor blade (blade) with an airworthy blade before further flight. This amendment requires the same checks and inspections as the existing AD, but expands the applicability with the addition of two BHTC Model 430 helicopter serial numbers. This amendment is prompted by the manufacturer issuing revised service information that includes the additional two serial numbers. The actions specified by this AD are intended to detect a crack in the blade, and to prevent loss of a blade and subsequent loss of control of the helicopter.
2005-03-09: This amendment adopts a new airworthiness directive (AD) for the specified Eurocopter France (Eurocopter) model helicopters. This action requires an initial and repetitive borescope inspection of the main gearbox (MGB) planet gear carrier or an initial and repetitive visual inspection of the MGB planet gear carrier for a crack. Replacing any MGB that has a cracked planet gear carrier is required before further flight. This amendment is prompted by the discovery of cracks in the web of the planet gear carrier. The actions specified in this AD are intended to detect a crack in the web of the planet gear carrier, which could lead to a MGB seizure and subsequent loss of control of the helicopter.
2005-03-10: This amendment supersedes an existing airworthiness directive (AD) for Bell Helicopter Textron, A Division of Textron Canada (BHTC) Model 222, 222B, 222U, and 230 helicopters, that currently requires a visual check of each main rotor grip (grip) and pitch horn assembly without disassembling the main rotor hub assembly (hub assembly), and a visual inspection at specified intervals of each affected grip and pitch horn assembly for a crack using a 10-power or higher magnifying glass. If a crack is found, the existing AD requires replacing each unairworthy grip or pitch horn with an airworthy part before further flight. This amendment requires those same actions, and also requires an additional inspection of the grip and pitch horn assembly for a crack in the disassembled hub assembly, and replacing any cracked part with an airworthy part. This amendment is prompted by the determination that an additional enhanced inspection is needed to ensure the integrity of the hub assembly. The actions specified by this AD are intended to prevent failure of the grip or pitch horn and subsequent loss of control of the helicopter.
2005-01-04: This document incorporates corrections to Airworthiness Directive (AD) 2005-01-04, which was published in the Federal Register on January 6, 2005 (70 FR 1169) with regulatory corrections published on January 27, 2005 (70 FR 3871). AD 2005-01-04 applies to certain Raytheon Aircraft Company 90, 99, 100, 200, and 300 series airplanes. This action incorporates the corrections into one document to help eliminate any confusion. We are re-issuing the AD in its entirety.
2005-03-01: This amendment adopts a new airworthiness directive (AD), applicable to all Boeing Model 747 series airplanes, that requires repetitive inspections of the nacelle strut-to-wing attachment structure, and repetitive overhaul of the diagonal brace and spring beam load paths, to maintain damage tolerance requirements and ensure long-term structural integrity; and follow-on and corrective actions if necessary. This action is necessary to ensure the structural integrity of the strut-to-wing load path and prevent separation of the strut and engine from the airplane. This action is intended to address the identified unsafe condition.
2005-01-18: The FAA adopts a new airworthiness directive (AD) to supersede AD 93-25-07, which applies to Raytheon Aircraft Company (Raytheon) Beech 100, 200, and 300 series airplanes. AD 93-25-07 currently requires you to repetitively inspect the fuselage stringers for cracks and modify at certain times depending on the number of cracked stringers. This AD is the result of FAA's policy (since 1996) to not allow airplane operation when known cracks exist in primary structure. The fuselage structure is considered primary structure and operation is currently allowed for a certain period of time if less than five fuselage stringers are cracked. Consequently, this AD retains the inspection and modification requirements of AD 93-25-07, but requires you to repair any cracked fuselage stringers. We are issuing this AD to detect and correct any cracked fuselage stringers in the rear pressure bulkhead area, which could result in structural damage to the fuselage. This damage could lead to failure of the fuselage with potential loss of control of the airplane.
2005-02-02: The FAA is adopting a new airworthiness directive (AD) for certain Boeing Model 767-200, -300, and -300F series airplanes. This AD requires repetitive high frequency eddy current inspections and detailed inspections of the left and right butt line (BL) 25 vertical chords for cracks, and corrective actions if necessary. This AD is prompted by findings of cracks in the fillet radii of the left and right BL 25 vertical chords common to the nose wheel well bulkhead at station 287. We are issuing this AD to detect and correct cracks in the left and right BL 25 vertical chords, which could grow downward into a critical area that serves as a primary load path for the nose landing gear (NLG) and result in the collapse of the NLG during landing.
2004-26-04: The FAA is superseding existing airworthiness directive (AD) 99-22-14 for Pratt & Whitney (PW) JT8D-200 series turbofan engines. That AD currently requires removing low pressure turbine (LPT)-to- exhaust case bolts and nuts and replacement with improved LPT-to- exhaust case bolts and nuts on JT8D-209, -217, -217A, -217C, and -219 engines. That AD also requires installation of improved high pressure turbine (HPT) containment hardware on JT8D-217C, and -219 engines. This AD requires installation of improved HPT containment hardware on JT8D- 209, -217, -217A, -217C, and -219 engines. This AD results from four reports of uncontained HPT failures of JT8D-200 series engines, since AD 99-22-14 was issued. We are issuing this AD to prevent uncontained HPT events resulting from HPT shaft fractures.
2005-01-16: The FAA is superseding an existing airworthiness directive (AD) for Rolls-Royce plc (RR) RB211 Trent 768-60, Trent 772-60, and Trent 772B-60 turbofan engines with low pressure compressor (LPC) fan blade part numbers FK22580, FK23411, FK25441, and FK25968 installed. That AD currently requires initial ultrasonic inspections of the fan blade root with blades removed, repetitive ultrasonic inspections of the fan blade root with blades removed or installed, and ultrasonic inspection of the fan blade root to be done with the fan blades removed at least every third inspection. This AD requires the same inspections but at lower thresholds and intervals, and eliminates the requirement for ultrasonic inspection with the fan blades removed at least every third inspection. This AD results from analysis of flight data returned to RR, that shows a need for consistent inspection thresholds for all engine models. We are issuing this AD to prevent possible multiple LPC fan blade failures, which could result in an uncontained engine failure and damage to the airplane.
2005-01-08: The FAA is adopting a new airworthiness directive (AD) for certain Airbus Model A310 series airplanes; and Model A300 B4-600, B4-600R, and F4-600R series airplanes, and Model C4 605R Variant F airplanes (collectively called A300-600). This AD requires relocating contactor 9DG located at rack (relay box) 107VU and adding protective sleeves to the two wire (cable) looms near the door hinge of rack 107VU. This AD is prompted by reports that interference was noticed during production between the wire looms located near the door hinge of rack 107VU and the terminals of contactor 9DG. We are issuing this AD to prevent possible short circuits in the wire looms supplying the fuel pump systems and the pitot probe heating system, which could lead to a possible loss of function of flight-critical systems and reduced controllability of the airplane.
2004-25-03: The FAA is superseding an existing airworthiness directive (AD), which applies to certain Airbus Model A320 series airplanes. That AD currently requires repetitive inspections to detect fatigue cracking in certain areas of the fuselage, and corrective action if necessary. That AD also provides for an optional terminating action for the repetitive inspections. This new AD revises the compliance threshold and repetitive intervals for the inspections required by the existing AD. This AD is prompted by a full-scale fatigue survey on the Model A320 fleet. We are issuing this AD to detect and correct fatigue cracking of the fuselage, which could result in reduced structural integrity of the airplane. DATES: This AD becomes effective February 10, 2005. The incorporation by reference of Airbus Service Bulletin A320-53- 1034, Revision 02, dated December 4, 2001, as listed in the AD, is approved by the Director of the Federal Register as of February 10, 2005. On February 12, 1999 (64 FR 1118, January 8, 1999), the Director of the Federal Register approved the incorporation by reference of Airbus Service Bulletin A320-53-1034, dated March 30, 1992.
2004-25-01: The FAA is adopting a new airworthiness directive (AD) for certain Gulfstream Aerospace LP Model Gulfstream 100 airplanes; and Model Astra SPX and 1125 Westwind Astra series airplanes. This AD requires adjusting the ground contact switches of the main landing gear. This AD is prompted by two occurrences of uncommanded deployments of the ground airbrakes during descent. We are issuing this AD to prevent a false ``Ground'' position signal, which could result in deployment of the ground airbrakes and reduced controllability of the airplane.
2004-26-11: This amendment adopts a new airworthiness directive (AD) for the specified Bell Helicopter Textron (BHTC) model helicopters. This action requires certain checks and inspections of the tail rotor blades. If a crack is found, before further flight, this AD requires replacing the tail rotor blade (blade) with an airworthy blade. This amendment is prompted by three reports of cracked blades found during scheduled inspections. The actions specified in this AD are intended to detect a crack in the blade and prevent loss of a blade and subsequent loss of control of the helicopter.
2004-25-15: The FAA adopts a new airworthiness directive (AD) for certain Raytheon Aircraft Company, Model 390, Premier 1 airplanes. This AD requires you to inspect the routing and security of the left and right main landing gear (MLG) squat switch wire harness installations for damage, repair any damage or replace components, and reinstall the squat switch wire harness. We are issuing this AD to prevent damage to the wire harnesses, which could result in loss of pressurization, loss of transponder responses to interrogations, and failure of other systems utilizing air/ground status signals. This failure could lead to loss of control of the airplane.
2004-25-22: The FAA supersedes Airworthiness Directive (AD) 79-20-08, which applies to all Great Lakes Aircraft Company, LLC, (Great Lakes) Models 2T-1A-1 and 2T-1A-2 airplanes with a Lycoming IO-360-B1F6 or AIO-360-B1G6 engine installed. AD 79-20-08 currently requires you to inspect the engine induction system and the alternate air door for any signs of damage and repairing or replacing any damaged components. AD 79-20-08 also requires you to inspect the induction system for the presence of a drain fitting. If the drain fitting is blocked, restricted, or does not exist, AD 79-20-08 requires you to clear the fitting or drill a hole in the elbow at the fitting location. This AD is the result of the FAA inadvertently omitting Lycoming engine AEIO- 360-B1G6 from the applicability section of AD 79-20-08. Consequently, this AD retains the actions required in AD 79-20-08 and adds Lycoming engine AEIO-360-B1G6 to the applicability section. We are issuing this AD to prevent the aircraft inductionsystem from becoming blocked or restricted, which could result \nin engine failure. This failure could lead to loss of control of the airplane.
2004-25-13: The FAA is superseding an existing airworthiness directive (AD), which applies to certain Short Brothers Model SD3-60 and SD3-SHERPA series airplanes. That AD currently requires a one-time inspection to detect cracks and/or corrosion of the gland nut on the shock absorber of the main landing gear (MLG), and follow-on actions. That AD also requires repair or replacement of any cracked/corroded gland nut with a new nut. This new AD adds airplanes to the applicability; adds repetitive inspections and corrective actions; and provides an optional action that ends the repetitive inspections. This AD is prompted by reports of cracked aluminum alloy gland nuts that had been inspected previously using the existing AD. We are issuing this AD to prevent failure of the aluminum alloy gland nut on the MLG shock absorber, which could cause the MLG to collapse.
2004-25-04: The FAA adopts a new airworthiness directive (AD) for all Mooney Aircraft Corporation (Mooney) Models M20B, M20C, M20D, M20E, M20F, M20G, and M20J airplanes equipped with an O & N Bladder Fuel Cell installed per Supplemental Type Certificate (STC) SA2277CE or STC SA2350CE. The STCs apply to all the affected airplane models except for Model M20B airplanes. Model M20B airplanes could have one of the STCs incorporated by field approval. This AD requires you to inspect the drain valve to assure that it is inserted fully into the drain nipple and modify any drain valve found not to be inserted fully into the drain nipple. This AD also requires certain modifications and replacements on the affected fuel cells to reduce the chances of water/ ice contamination. This AD is the result of reports of rainwater entering the fuel bladders and the information from the subsequent evaluation of the fuel systems. The actions specified by this AD are intended to assist in preventing water from entering the fuel bladders, which could result in rough engine operation or complete loss of engine power.
2004-25-11: The FAA is adopting a new airworthiness directive (AD) for certain Airbus Model A318, A319, A320, and A321 series airplanes. This AD requires removing two maintenance lights in the hydraulics bay, disconnecting the wiring for the lights, and modifying the switches. This AD is prompted by underlying safety issues involved in fuel tank explosions on several large transport airplanes. We are issuing this AD to prevent an ignition source for fuel vapor in the hydraulics bay, which could result in fire or explosion in the adjacent center wing fuel tank.
2004-25-06: The FAA is adopting a new airworthiness directive (AD) for certain Boeing Model 747-100, 747-100B, 747-100B SUD, 747-200B, 747- 200C, 747-200F, and 747-300 series airplanes; and Model 747SP and 747SR series airplanes. This AD requires revising the airplane flight manual to prohibit operation of the autopilot/flight director in command mode with performance management system selected on the speed mode switch during cruise in reduced vertical separation minimum (RVSM) airspace. This AD is prompted by reports of unexpected autopilot disconnects induced by the passing of another airplane within 1,000 feet below the airplane while they were operating in RVSM airspace. We are issuing this AD to prevent unexpected disconnect of the autopilot during operation in RVSM airspace due to close passage of another airplane, which may result in altitude deviation, and consequently, could lead to a possible mid-air collision or a near miss with aggressive evasive action (by either or both airplanes). Aggressive maneuvering at cruise altitudes and airspeeds could result in loss of control of the airplane and/or injury to passengers and crew.
2004-22-15: This amendment supersedes an existing airworthiness directive (AD), applicable to certain Boeing Model 747-400 series airplanes, that currently requires installation of strap assemblies on the ceiling panels and rails that support the video monitors. For certain airplanes, this amendment requires replacement of certain plate assemblies within the ceiling panel strap assemblies with new, improved plate assemblies. This amendment also revises the applicability by adding airplanes. The actions specified by this AD are intended to prevent ceiling panels from falling into the passenger cabin area in the event of failure of certain latch assemblies on the ceiling panels, which could result in consequent injury to the flightcrew and passengers. This action is intended to address the identified unsafe condition.
2004-24-01: The FAA adopts a new airworthiness directive (AD) for all Bombardier Inc. Model (Otter) DHC-3 airplanes that have been modified by 524085 BC, Ltd. Supplemental Type Certificate (STC) Number ST01243NY or SA01243NY. This AD requires you to replace the existing Viking Air Ltd. elevator servo tab assembly with a redesigned Viking Air Ltd. elevator servo tab assembly. This AD results from mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for Canada. There has been one failure of the elevator servo tab assembly. We are issuing this AD to prevent the structural failure of the elevator servo tab. This failure could lead to loss of control of the airplane.
2004-23-21: This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model DC-9-81 (MD-81), DC-9-82 (MD-82), DC-9-83 (MD-83), and DC-9-87 (MD-87) airplanes; and Model MD- 88 airplanes. This amendment requires a general visual inspection for chafing of the power feeder cables of the auxiliary power unit (APU), and repair if necessary. This amendment also requires replacement of a support bracket located on the left side of the lower cargo compartment with a new "U" shaped bracket. This action is necessary to prevent chafing of the power feeder cables of the APU, which could result in electrical arcing to adjacent structure and consequent fire in the airplane. This action is intended to address the identified unsafe condition.
2004-24-02: The FAA adopts a new airworthiness directive (AD) for certain Ostmecklenburgische Flugzeugbau GmbH (OMF) Model OMF-100-160 airplanes. This AD requires you to inspect the outside tube (cage) that supports the main landing gear leg for cracks, repair if cracks are found, and inspect the thickness of the tube if no cracks were found and reinforce the tube as necessary. This AD results from mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for Germany. We are issuing this AD to detect, correct, and prevent future cracks in the outside tube of the main landing gear leg, which could result in structural failure of the fuselage tubing assembly. This failure could lead to loss of control of the airplane.
2004-23-06: This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 757-200, -200PF, -200CB, and -300 series airplanes, that requires inspection for damage of the W2800 wire bundle insulation, wire conductor, the wire bundle clamp bracket, and the BACC10GU( ) clamp, and repair or replacement with new or serviceable parts, if necessary. This amendment also requires installation of spacers between the clamp and the bracket. This action is necessary to prevent contact between the power feeder wires of the auxiliary power unit (APU) and the clamp bracket aft of the STA 1720 bulkhead due to chafing damage of the Adel clamp and "L" shaped bracket, which could result in electrical arcing and fire, or loss of APU electrical power in the airplane. This action is intended to address the identified unsafe condition.