Results
2005-06-13: The FAA is adopting a new Airworthiness Directive (AD) to supersede AD 99-06-02, which currently applies to certain Fairchild Aircraft (Fairchild) SA226 and SA227 series airplanes. AD 99-06-02 requires you to repetitively inspect the wing spar center web cutout on both wings for cracks between Wing Station (WS) 8 and WS 17.5. That AD also requires you to repair any area found cracked before further flight. The repair will eliminate the need for the repetitive inspections on that particular wing spar. Since that AD became effective, we have determined that we inadvertently omitted certain Model SA227-CC/DC airplane serial numbers from the applicability. This AD retains the actions of AD 99-06-02 and adds additional Model SA227- CC/DC airplanes to the Applicability section. The actions specified in this AD are intended to detect and correct fatigue cracking of the wing spar center web cutout area, which could result in structural failure of the wing spar. This could lead to lossof control of the airplane. DATES: This AD becomes effective on May 2, 2005. On April 16, 1999 (64 FR 11761, March 10, 1999), the Director of the Federal Register approved the incorporation by reference of Fairchild Airframe Airworthiness Limitations Manual ST-UN-M001, Rev. No. C-6, dated April 7, 1998; Fairchild Airframe Inspection Manual ST- UN-M002, Rev. No. A-6, dated December 8, 1997; Fairchild Airframe Airworthiness Limitations Manual ST-UN-M003, Rev. No. 5, dated April 7, 1998; Fairchild SA226/227 Series Structural Repair Manual, part number (P/N) 27-10054-079, pages 57 through 90; Initial Issue: March 1, 1983; Revision 28, dated June 24, 1998; and Fairchild SA227 Series Structural Repair Manual, P/N 27-10054-127, pages 47 through 60; Initial Issue: December 1, 1991; Revision 7, dated June 24, 1998. As of May 2, 2005, the Director of the Federal Register approved the incorporation by reference of Fairchild Airframe Airworthiness Limitations Manual ST-UN-M001, SA227 Series, Reissue C, dated January 18, 1991; Fairchild Airframe Inspection Manual ST-UN-M002, SA226 Series, Reissue A, dated December 9, 1986; and Fairchild Airframe Airworthiness Limitations Manual ST-UN-M003, SA227 Commuter Category, Initial issue dated December 6, 1991.
2005-06-05: The FAA is adopting a new airworthiness directive (AD) for all McDonnell Douglas Model DC-8 airplanes. This AD requires an inspection of the pushrod assemblies for the left and right elevator control tabs to determine if the pushrod assemblies are made of aluminum or steel, replacing any assembly made of aluminum with an assembly made of steel or modifying existing steel assemblies, and other specified actions. This AD also requires an inspection of the crank assemblies for the inboard and outboard geared tabs of the elevator to determine if the crank assemblies are made of aluminum or steel, replacing any assembly made of aluminum with an assembly made of steel, and other specified actions. This AD is prompted by an accident involving a DC-8 airplane. The probable cause of the accident was a loss of pitch control resulting from the disconnection of the pushrod for the right elevator control tab. The pushrod dropped down and jammed in front of the control tab crank, causing alarge deflection of the control tab. We are issuing this AD to minimize the possibility of a control tab offset. A control tab offset could cause elevator deflection, an elevator airplane-nose-up condition, and reduced controllability of the airplane. This AD is also prompted by a report that the elevator on a McDonnell Douglas Model DC-8 airplane did not respond to command inputs from the flightcrew. We are also issuing this AD to minimize the possibility of crank assembly failure when the assembly is exposed to abnormal load conditions. Failure of a crank assembly could result in a jammed elevator and consequent reduced controllability of the airplane.
2005-05-15: The FAA is adopting a new airworthiness directive (AD) for Honeywell International Inc. (formerly AlliedSignal Inc. and Garrett Turbine Engine Co.) TFE731-2 and -3 series turbofan engines with certain part number (P/N) low pressure turbine (LPT) stage 1 disks installed. This AD requires for TFE731-2 and -2C series engines, initial and repetitive measurements and calculations to determine acceptance, and adjustment or replacement if necessary, of the LPT stage 1 nozzle assembly. This AD also requires for TFE731-3, -3A, -3AR, -3B, -3BR, and -3R series engines, replacement of LPT stage 1 disks with serviceable disks. This AD also allows replacement of the LPT stage 1 disk with a disk having a part number not listed in the AD as optional terminating action to the repetitive actions. This AD results from a report of an uncontained failure of the LPT stage 1 disk installed in a TFE731-3-1H turbofan engine. We are issuing this AD to prevent additional uncontained failure of the LPT stage 1 disk, and possible damage to the airplane.
2005-05-09: This amendment adopts a new airworthiness directive (AD), applicable to certain EMBRAER Model EMB-135 and -145 series airplanes. This AD requires modification of the mid, aft, and forward upper liners in the baggage compartment. The modification involves replacing the plastic lens protection grids on all upper liners with new, light metal lens protection grids. This AD is necessary to prevent the plastic lens protection grids from breaking away and exposing the lens as a source of fire, which could lead to fire damage to the aircraft systems and structure, and expose the passengers and crew to hazardous quantities of smoke. This action is intended to address the identified unsafe condition.
2005-05-06: The FAA is superseding an existing airworthiness directive (AD) for Rolls-Royce plc (RR) models RB211 Trent 768-60, Trent 772-60, and Trent 772-60 turbofan engines. That AD currently requires initial and repetitive surge margin testing of engines. This AD requires the same actions but at updated intervals. This AD also requires installation of updated software for the engine electronic controllers (EECs), and adds a terminating action for the surge margin testing requirement. This AD supersedure results from RR requiring EEC software to be revised, and extending the repetitive interval for surge margin testing for engines that have incorporated the software update for the EECs. This AD also results from RR introducing a stage 1 high pressure (HP) compressor casing and intermediate case outer location ring with wear-resistant coating, to reduce wear to prevent reduction in surge margin. We are issuing this AD to prevent a possible dual-engine in- flight surge, which could result in dual engine power loss.
2005-04-51: This document publishes in the Federal Register an amendment adopting airworthiness directive (AD) 2005-04-51 that was sent previously to all known U.S. owners and operators of certain Boeing Model 747-100B SUD, -200B, -200C, -200F, and -300 series airplanes by individual notices. This AD requires repetitive external detailed inspections for cracked skin or loose or missing fasteners of the body skin between body stations (BS) 420 and 460 inclusive and between stringers S-8 and S-12 inclusive on the left and right sides of the airplane, and a high frequency eddy current inspection for cracked frames if necessary. This AD also requires repair of any cracked frame or skin, and replacement of any loose or missing fastener. This AD is prompted by reports of large cracks common to fuselage frames in the upper deck area and severed or nearly severed adjacent frames. We are issuing this AD to detect and correct fatigue cracks in the frames and body skin at BS 420, 440, and 460 between stringers S-8 and S-12 inclusive, which could lead to severed frames, and consequent rapid decompression and loss of the structural integrity of the airplane.
2005-04-08: The FAA is superseding an existing Priority Letter Airworthiness Directive (AD) for Hartzell Propeller Inc. model HC-B3TN- 5( )/T10282( ) propellers. That AD currently requires initial and repetitive inspections of the blade pilot tube bore area. This ad requires the same inspections. This AD results from a review of all currently effective ADs. That review determined that Priority Letter AD 88-24-15 was not published in the Federal Register to make it effective to all operators, as opposed to just the operators who received actual notice of the original Priority Letter AD. This AD also results from the discovery that the original AD omitted an airplane model with a certain Supplemental Type Certificate (STC) from the applicability. We are issuing this AD to prevent possible blade failure near the hub which can result in blade separation, engine separation, damage to the airplane, and possible loss of the airplane.
2005-05-03: The FAA is adopting a new airworthiness directive (AD) for all BAE Systems (Operations) Limited Model BAe 146 and Avro 146-RJ series airplanes. This AD requires repetitive detailed inspections of the center and rear fuselage skin including all the lap joints at stringers 2, 10, 19, and 30, and repair if necessary. This AD is prompted by evidence of cracking due to fatigue along the edges of certain chemi- etched pockets in the rear fuselage upper skin. We are issuing this AD to prevent a possible sudden loss of cabin pressure and consequent injury to passengers and flightcrew.
2005-04-11: The FAA is superseding an existing airworthiness directive (AD), which applies to all Airbus Model A300 B2 and B4, A300-600, and A310 series airplanes. That AD currently requires identification of the part number and serial number of the parking brake operated valve (PBOV); and, if necessary, inspections of the PBOV, including a functional check of the PBOV, and follow-on and corrective actions. That AD also provides for optional terminating action for the requirements of that AD. This new AD requires modification of all affected PBOVs, or replacement with new, non-affected PBOVs, which would terminate the requirements of the existing AD. This AD is prompted by a decision by the FAA and a civil airworthiness authority to require modification or replacement of all affected PBOVs. We are issuing this AD to prevent loss of the yellow hydraulic system, which provides all the hydraulics for certain spoilers; elements of the hydraulics for flaps, stabilizer, pitch and yaw feel systems, pitch and yaw autopilot, and yaw damper; and elevator, rudder, and aileron.
2005-04-12: The FAA is adopting a new airworthiness directive (AD) for certain Saab Model SAAB SF340A and SAAB 340B series airplanes. This AD requires repetitive inspections for wear of the brushes and leads and for loose rivets of the direct current (DC) starter generator, and related investigative/corrective actions if necessary. This AD is prompted by reports of premature failures of the DC starter generator prior to scheduled overhaul. We are issuing this AD to prevent failure of the starter generator, which could cause a low voltage situation in flight and result in increased pilot workload and reduced redundancy of the electrical powered systems.
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.