22 Airworthiness Directives: 14 airplane, 4 rotorcraft, 3 engine, 1 glider.
AD 2004-16-01 · published Aug 4, 2004, effective Aug 19, 2004
Airbus Model A330, A340-200, and A340-300 Series Airplanes
The FAA is adopting a new airworthiness directive (AD) for certain Airbus Model A330, A340-200, and A340-300 series airplanes. This AD requires repetitive inspections for cracking of the chromed area of the left and right piston rods for the main landing gear (MLG) retraction actuators, and related investigative and corrective actions if necessary. This AD is prompted by reports of the piston rods for the MLG retraction actuators rupturing during flight. We are issuing this AD to detect and correct corrosion pitting and cracking of the piston rods for the MLG retraction actuators, which could result in rupture of a piston rod, non-damped extension of the MLG, high loads on the fully extended MLG, and consequent reduced structural integrity of the MLG.
AD 2004-16-09 · published Aug 9, 2004, effective Sep 13, 2004
Boeing Model 747 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to all Model 747 series airplanes, that requires repetitive detailed inspections of the aft pressure bulkhead for indications of "oil cans" and previous oil can repairs, and corrective actions, if necessary. An oil can is an area on a pressure dome web that moves when pushed from the forward side. This action is necessary to detect and correct the propagation of fatigue cracks in the vicinity of oil cans on the web of the aft pressure bulkhead, which could result in rapid decompression and overpressurization of the tail section, and consequent loss of control of the airplane. This action is intended to address the identified unsafe condition.
AD 2004-16-10 · published Aug 9, 2004, effective Sep 13, 2004
Boeing Model 767-200 and -300 Series Airplanes Equipped With Off-Wing Escape Slides
This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 767-200 and -300 series airplanes equipped with off-wing escape slides, that requires an inspection of the door-opening actuators for the off-wing slide compartment on the right and left sides of the airplane to determine the actuator cartridge serial number, and corrective actions, if necessary. This action is necessary to prevent the door-opening actuators for the off- wing slide compartment from not firing, which could cause the door to open improperly and prevent the deployment of the off-wing escape slide, leading to the loss of an evacuation route. This action is intended to address the identified unsafe condition.
AD 2004-16-11 · published Aug 9, 2004, effective Sep 13, 2004
Boeing Model 757 and 767 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 757 and 767 series airplanes, that requires inspection to determine the serial number of the hydraulic pump in the ram air turbine (RAT), and corrective action if necessary. This action is necessary to prevent a cracked hanger arm of the hydraulic pump of the RAT that can fracture under load and lead to failure of the RAT to provide hydraulic power to the primary flight control system during an emergency when both engines have failed. Loss of hydraulic power to the primary flight controls could result in loss of control of the airplane. This action is intended to address the identified unsafe condition.
AD 2004-16-13 · published Aug 9, 2004, effective Sep 13, 2004
Bombardier Model DHC-8-400, -401, and -402 Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Bombardier Model DHC-8-400, -401, and -402 airplanes. This AD requires an inspection to determine the serial number of the spoiler lift dump valves installed on the inboard and outboard spoilers, and replacement of certain spoiler lift dump valves. This AD also provides for revising the airplane flight manual to include performance penalties, which allows the replacement of affected spoiler lift dump valves to be deferred. This action is necessary to prevent failure of the ground spoilers to deploy on the ground, which could result in overrunning the end of the runway in the event of a rejected takeoff. This action is intended to address the identified unsafe condition.
AD 2004-16-14 · published Aug 9, 2004, effective Sep 13, 2004
Thales Avionics Traffic Advisory/Resolution Advisory (TA/RA) Vertical Speed Indicator-Traffic Alert and Collision Avoidance System (VSI-TCAS) Indicators, Installed on But Not Limited to Certain Transport Category Airplanes Equipped With TCAS II Change 7 Computers (ACAS II)
This amendment adopts a new airworthiness directive (AD), applicable to certain Thales Avionics TA/RA VSI-TCAS indicators, installed on but not limited to certain transport category airplanes equipped with TCAS II change 7 computers (ACAS II), that requires a revision to the airplane flight manual (AFM) to advise the flightcrew to follow the audio annunciation when an RA fail message is triggered during a multi-aircraft encounter. This action also requires modification of the software for the TA/RA VSI-TCAS indicator, which would terminate the requirement for the AFM revision. This action is necessary to prevent the TA/RA VSI-TCAS indicator from displaying a conflicting "RA FAIL" message during a multi-aircraft encounter, which could result in the flightcrew ignoring the correct aural command and traffic display information if the flightcrew believes the TCAS II computer has malfunctioned, and consequently lead to a mid-air collision with other aircraft. This action is intended to address the identified unsafe condition.
AD 2004-16-02 · published Aug 10, 2004, effective Sep 14, 2004
Short Brothers Model SD3 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to all Short Brothers Model SD3 series airplanes, that requires installing a new warning annunciator light on the central warning panel and revising the Normal Procedures Section of the Aircraft Flight Manual to provide the flightcrew with procedures related to the new light. This action is necessary to prevent an engine shut-down in icing conditions, which could result in loss of control of the airplane and consequent injury to flightcrew and passengers. This action is intended to address the identified unsafe condition.
AD 2004-16-03 · published Aug 10, 2004, effective Sep 14, 2004
Gulfstream Aerospace LP Model Galaxy and Model Gulfstream 200 Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Gulfstream Aerospace LP Model Galaxy and Model Gulfstream 200 airplanes, that requires a one-time detailed inspection of the wing flap actuators for proper bonding of the flap actuator fairings to the lower skin of the wings, and related corrective or preventative actions. These actions are necessary to prevent possible separation of the flap actuator fairings from the lower skin of the wings from causing possible damage to adjacent structural elements (such as the horizontal stabilizer), which could result in reduced controllability of the airplane. These actions are intended to address the identified unsafe condition.
AD 2004-16-04 · published Aug 10, 2004, effective Sep 14, 2004
Short Brothers Model SD3 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to all Short Brothers Model SD3 series airplanes. This AD requires testing for stiffness of the aft pintle pin bushing of the main landing gear (MLG), and inspecting and measuring the aft pintle pin bushings of the MLG for damage, and for out-of-limit dimensions of the bushing bore. This AD also requires corrective action if necessary. This action is necessary to detect and correct corrosion and deterioration of the aft pintle pin bushings of the MLG. Corrosion and deterioration of the bushings, if not detected and corrected, could result in the MLG not extending fully during landing, with consequent damage to the airplane structure. This action is intended to address the identified unsafe condition.
AD 2004-16-05 · published Aug 10, 2004, effective Sep 14, 2004
Boeing Model 747 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to all Boeing Model 747 series airplanes, that requires a one-time inspection to determine whether the outer cylinder of the wing landing gear has certain part numbers, and replacement of the outer cylinder of the wing landing gear with a new, improved, or reworked part if necessary. This amendment also requires removal of the load evening system, if such a system is installed. This action is necessary to prevent fracture of the outer cylinder of the wing landing gear, which could result in collapse of the wing landing gear. This action is intended to address the identified unsafe condition.
AD 2004-16-06 · published Aug 10, 2004, effective Sep 14, 2004
BAE Systems (Operations) Limited Model Avro 146-RJ Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to all BAE Systems (Operations) Limited Model Avro 146-RJ series airplanes, that requires replacing the existing digital flight guidance computer(s) (DFGC) with a new or modified DFGC(s). This action is necessary to prevent a premature flare from occurring on approach due to erroneous data being provided to the DFGC(s); and also to prevent uncertainty about autopilot engagement status, which could cause the pilot to apply unneeded force to the control column and possibly result in a runaway condition of the autotrim. Either condition could lead to reduced controllability of the airplane. This action is intended to address the identified unsafe conditions.
AD 2004-17-01 · published Aug 13, 2004, effective Sep 26, 2004
Cessna Aircraft Company Models 208 and 208B Airplanes
The FAA supersedes Airworthiness Directive (AD) AD 2002-22-17, which applies to all Cessna Aircraft Company (Cessna) Models 208 and 208B airplanes; and AD 2003-21-04, which applies to certain Cessna Models 208 and 208B airplanes. This AD requires you to repetitively inspect the flap bellcranks for cracks and eventually replace these bellcranks. The installation of a newly designed bellcrank to increase the life limits is terminating action for the repetitive inspections. This AD is the result of these developments: Since FAA issued AD 2002- 22-17 and AD 2003-21-04, Cessna designed a new flap bell crank with a life limit of 40,000 landings instead of 7,000 landings. Also, FAA has done more analysis and examination of cracks and missing/incomplete welds in all of the bell cranks. This failure could lead to damage to the flap system and surrounding structure and result in reduced or loss of control of the airplane.
AD 2004-16-12 · published Aug 17, 2004, effective Sep 21, 2004
Boeing Model 767-200, -300, and -300F Series Airplanes
This amendment supersedes three existing airworthiness directives (AD); applicable to certain Boeing Model 767-200, -300, and -300F series airplanes. One AD currently requires modification of the nacelle strut and wing structure for certain Boeing Model 767-200, -- 300, and --300F series airplanes powered by Pratt & Whitney engines. The second AD currently requires a similar modification for certain Boeing Model 767-200, -300, and -300F series airplanes powered by General Electric engines. The third AD currently requires repetitive inspections for cracking of the outboard pitch load fittings of the wing front spar, and corrective action if necessary, for certain Boeing Model 767-200 series airplanes. The third AD also provides a terminating action for the repetitive inspections, which is optional for uncracked pitch load fittings. This amendment requires, for airplanes subject to the first and second existing ADs on which certain modifications have been accomplished previously, reworking the aft pitch load fitting, and installing a new diagonal brace fuse pin. This amendment also requires, for airplanes subject to the third existing AD, replacing the outboard pitch load fitting of the wing front spar with a new, improved fitting, which terminates certain currently required repetitive inspections. The actions specified by this amendment are intended to prevent fatigue cracking in primary strut structure, which could result in separation of the strut and engine from the airplane. This action is intended to address the identified unsafe condition.
AD 2004-17-02 · published Aug 20, 2004, effective Oct 4, 2004
Raytheon Aircraft Company 65, 90, 99, 100, 200, 300, and 1900 Series Airplanes
The FAA adopts a new airworthiness directive (AD) for certain Raytheon Aircraft Company (Raytheon) 65, 90, 99, 100, 200, 300, and 1900 series airplanes. This AD requires you to repetitively inspect the engine controls/cross shaft/pedestal for proper installation and torque, re-torque the cross shaft attach bolt, modify the pedestal, and replace the engine controls cross shaft hardware. Modification of the pedestal and replacement of the engine controls cross shaft hardware is terminating action for the repetitive inspection requirements. This AD is the result of numerous reports of loose bolts on the pedestal attachment of the throttle/prop cross shaft assembly. We are issuing this AD to detect and correct loose bolts not securing the pedestal cross shaft, which could result in limited effectiveness of the control levers. This failure could lead to an aborted takeoff.
AD 2004-15-21 · published Aug 2, 2004, effective Aug 17, 2004
Agusta S.p.A. Model A109K2 Helicopters
This amendment adopts a new airworthiness directive (AD) for Agusta S.p.A. (Agusta) Model A109K2 helicopters. This action requires dye-penetrant inspecting the tail rotor trunnion (trunnion) assembly for a crack at specified intervals, replacing any cracked trunnion with an airworthy trunnion, and reporting any failed trunnion. This amendment is prompted by the report of an accident involving a tail rotor hub and blade assembly separating from the helicopter due to fatigue failure of the trunnion. The cause for the crack in the trunnion has not been determined and is still under investigation. This condition, if not detected, could result in failure of the trunnion, loss of the tail rotor hub and blade assembly, and subsequent loss of control of the helicopter.
AD 2004-15-22 · published Aug 2, 2004, effective Sep 7, 2004
Sikorsky Aircraft Corporation Model S-61L, S-61N, S-61-NM, and S-61R Helicopters
This amendment adopts a new airworthiness directive (AD) for the specified Sikorsky Aircraft Corporation (Sikorsky) model helicopters that requires installing a Number 5 bearing chip detector in each engine, installing an on-board chip detector annunciation system, and revising the Rotorcraft Flight Manual (RFM) to add procedures for crew response to an on-board chip detector annunciation. This amendment is prompted by reports of the failure of the engine's Number 5 bearing that resulted in erratic movement of the high-speed engine-to-transmission shaft (shaft), oil leakage, an in-flight fire and an emergency landing. The actions specified by this AD are intended to detect an impending engine bearing (bearing) failure, which, if undetected and not addressed by appropriate crew action, may result in oil leakage, severing of the shaft housing, an uncontained in-flight fire, and a subsequent emergency landing.
AD 2004-16-08 · published Aug 10, 2004, effective Aug 25, 2004
MD Helicopters Inc. Model MD900 Helicopters
This amendment adopts a new airworthiness directive (AD) for MD Helicopters, Inc. Model MD900 helicopters. This action requires installing a fan input force limiting control rod assembly fail-safe device (fail-safe device). This AD also requires, after installing a fail-safe device, before the first flight of each day, checking the fail-safe device for bent clips, taut lanyards, and piston rod movement. If any of these conditions are found, this AD requires replacing the control rod assembly with an airworthy control rod assembly before further flight. This amendment is prompted by an accident report of fatigue failure of the piston rod in the spring capsule on a control rod assembly. The actions specified in this AD are intended to provide a temporary backup support system in the event of a piston rod failure and to prevent subsequent loss of control of the helicopter.
AD 2004-16-15 · published Aug 19, 2004, effective Sep 3, 2004
Eurocopter France Model AS-365N2, AS 365 N3, EC 155B, EC155B1, SA-365N and N1, and SA-366G1 Helicopters
This amendment adopts a new airworthiness directive (AD) for the specified Eurocopter France (Eurocopter) helicopters. This action requires inspecting the main gearbox (MGB) baseplate for a crack and replacing the MGB if a crack is found in the MGB base plate. This amendment is prompted by the discovery of a crack in a MGB base plate. The actions specified in this AD are intended to detect a crack in a MGB base plate and prevent failure of one of the MGB attachment points to the frame, which could result in severe vibration and subsequent loss of control of the helicopter.
AD 2004-16-07 · published Aug 6, 2004, effective Aug 23, 2004
General Electric Company (GE); CT7-2D1 Turboshaft Engines.
The FAA is adopting a new airworthiness directive (AD) for GE CT7-2D1 turboshaft engines. This AD requires replacing certain turbine stage 2 aft cooling plates, part number (P/N) 6064T0P02. This AD results from an uncontained failure of a turbine stage 2 aft cooling plate in a GE CT7 turboprop engine. We are issuing this AD to prevent a similar uncontained failure of turbine stage 2 aft cooling plates in GE CT7-2D1 turboshaft engines.
AD 2004-15-03 R1 · published Aug 16, 2004, effective Jul 30, 2004
General Electric Aircraft Engines Engines
The FAA is revising an existing airworthiness directive (AD) for General Electric Company (GE) CF34-3A1 and -3B1 series turbofan engines with certain serial numbers (SNs) of stage 5 low pressure turbine (LPT) disks, part number (P/N) 6078T92P01, and/or certain SNs of stage 6 LPT disks, P/N 6078T89P01. That AD currently requires initial and repetitive visual and eddy current inspections of those disks. That AD also allows as optional terminating action to the repetitive inspections, replacement of those SN disks. Also, that AD requires replacement of certain stage 5 and stage 6 LPT disks. This ad requires the same actions. This AD results from the discovery that an incorrect part number for stage 6 LPT disks was published in the existing AD and from the need to allow credit for actions completed per previous releases of Alert Service Bulletin CF34-AL S/B 72-A0173. We are issuing this AD to prevent LCF failure of stage 5 LPT disks and stage 6 LPT disks, which could lead to uncontained engine failure.
AD 2004-17-03 · published Aug 20, 2004, effective Sep 24, 2004
Pratt & Whitney Canada PW206A and PW206E Turboshaft Engines
The FAA is superseding an existing airworthiness directive (AD) for Pratt & Whitney Canada (PWC) PW206A and PW206E turboshaft engines. That AD currently requires: <bullet> Initial and repetitive borescope inspections of compressor turbine and power turbine blades for blade axial shift. <bullet> Replacement of blade retaining rivets and certain rotor air seals as terminating action for the repetitive borescope inspections. This ad requires the same actions as AD 2003-NE-25-AD but the extent of engine disassembly that triggers the required part replacements needs clarification. This AD results from reports of engine shutdowns and emergency landings due to severe vibration, resulting in exhaust gases escaping from the engine-to-exhaust nozzle interface, thereby triggering in-flight engine fire warnings. We are issuing this AD to prevent turbine blade axial shift, which could cause high levels of vibration, loss of engine torque, in-flight engine shutdown, and loss of the airframe exhaust duct.
AD 2004-17-04 · published Aug 23, 2004, effective Oct 7, 2004
Grob-Werke Gmbh & Co KG Models G102 CLUB ASTIR III, G102 CLUB ASTIR IIIb, and G102 STANDARD ASTIR III Sailplanes
The FAA supersedes Airworthiness Directive (AD) 2001-26-25, which applies to all Grob-Werke Gmbh & Co KG (Grob) Models G102 CLUB ASTIR III, G102 CLUB ASTIR IIIb, and G102 STANDARD ASTIR III sailplanes. AD 2001-26-25 currently requires you to apply a red mark and install a placard on the airspeed indicator to restrict the Vne airspeed. This AD requires you to install additional mass balance in the elevator and ailerons and determine resultant empty weight and empty weight center of gravity; incorporate a revision in the sailplane maintenance manual; and remove the red mark and the red placard on the airspeed indicator (both required by AD 2001-26-25). This AD is the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for Germany. We are issuing this AD to prevent elevator flutter, which could cause structural damage. Such damage could result in loss of control of the sailplane.
