56 Airworthiness Directives: 47 airplane, 4 rotorcraft, 4 engine, 1 glider.
AD 2004-13-17 · published Jul 1, 2004, effective Aug 5, 2004
Fokker Model F.28 Mark 0070 and 0100 Series Airplanes
This amendment supersedes an existing airworthiness directive (AD), applicable to certain Fokker Model F.28 Mark 0070 series airplanes, that currently requires a one-time inspection to detect loose bolts attaching the gustlock counter-bracket to the pulley on the elevator tension regulator (control) assembly, and corrective action if necessary. This AD instead requires a modification of the elevator tension control mechanism. This AD also revises the applicability to include additional airplanes. The actions specified by this AD are intended to prevent restricted elevator movement and consequent reduced controllability of the airplane. This AD is intended to address the identified unsafe condition.
AD 2004-13-18 · published Jul 1, 2004, effective Aug 5, 2004
Gulfstream Aerospace LP Model Astra SPX, and 1125 Westwind Astra Series Airplanes; and Model Gulfstream 100 Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Gulfstream Aerospace LP Model Astra SPX, and 1125 Westwind Astra series airplanes; and Model Gulfstream 100 airplanes. This AD requires a one-time inspection of the outboard doors of the main landing gear (MLG) for evidence of impact with the surrounding structure, and for damage to the door seals and seal channels; measurements for adequate gaps and clearances; and related investigative and corrective actions, if necessary. This action is necessary to prevent damage to or breakage of the MLG outboard doors, which could result in the loss of a door during flight, and consequent damage to the airplane and injury to people or damage to property on the ground. This action is intended to address the identified unsafe condition.
AD 2004-13-19 · published Jul 1, 2004, effective Aug 5, 2004
Airbus Model A300 B2 and A300 B4; Model A300 B4-600, B4-600R, C4-605R Variant F, and F4-600R (Collectively Called A300-600); and Model A310 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A300 B2 and A300 B4; Model A300 B4- 600, B4-600R, C4-605R Variant F, and F4-600R (collectively called A300- 600); and Model A310 series airplanes. This AD requires an inspection to determine the part number of certain passenger/crew escape slides; and related investigative action and corrective action, if necessary. This action is necessary to prevent the failure of an escape slide to deploy during emergency evacuation, which could impede an evacuation and result in injury to flightcrew and passengers. This action is intended to address the identified unsafe condition.
AD 2004-13-12 · published Jul 2, 2004, effective Aug 6, 2004
Empresa Brasileira de Aeronautica S.A. (EMBRAER) Model EMB-120 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to all EMBRAER Model EMB-120 series airplanes, that requires revising the Airplane Flight Manual to ensure that the propeller synchronizer switch is "OFF" after engine start and before takeoff and landing. This action is necessary to prevent a possible loss of airplane control and subsequent injury to the flight crew and passengers. This action is intended to address the identified unsafe condition.
AD 2004-03-34 R1 · published Jul 8, 2004, effective Jul 21, 2004
Boeing Model 737-100, -200, -200C, -300, -400, and -500 Series Airplanes
This document corrects a typographical error that appeared in airworthiness directive (AD) 2004-03-34 R1 that was published in the Federal Register on June 16, 2004 (69 FR 33555). A reference to the amendment number was inadvertently omitted from a heading in the AD. This AD is applicable to certain Boeing Model 737-100, -200, -200C, - 300, -400, and -500 series airplanes. This AD requires replacing existing screw, nut, and washers that attach the latch cable assembly to the latch block assembly of the door mounted escape slides, with new, improved screw, nut, and washers.
AD 2004-13-23 · published Jul 9, 2004, effective Aug 13, 2004
McDonnell Douglas DC-9-82 (MD-82) and DC-9-83 (MD-83) Airplanes; and Model MD-88 Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas DC-9-82 (MD-82) and DC-9-83 (MD-83) airplanes; and Model MD-88 airplanes, that requires inspection of the captain's and first officer's seat track locking pins for insufficient engagement caused by seat track misalignment, and corrective actions if necessary. This action is necessary to prevent uncommanded movement of the captain's and first officer's seats during takeoff and landing, which could result in interference with the operation of the airplane and consequent temporary loss of control of the airplane. This action is intended to address the identified unsafe condition.
AD 2004-13-24 · published Jul 9, 2004, effective Aug 13, 2004
Airbus Model A310 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to all Airbus Model A310 series airplanes, that requires inspecting the pressure-off brakes (POBs) installed on the power control units of the slats and flaps to determine their serial numbers; and replacing any POBs having affected serial numbers with new, serviceable, or modified POBs. This action is necessary to prevent failure of the retaining ring on the POBs, which could result in slat or flap blowback or runaway, with consequent reduced controllability of the airplane. This action is intended to address the identified unsafe condition.
AD 2004-13-25 · published Jul 9, 2004, effective Aug 13, 2004
Airbus Model A330, A340-200, and A340-300 Series Airplanes
This amendment supersedes an existing airworthiness directive (AD), applicable to certain Airbus Model A330, A340-200, and A340-300 series airplanes, that currently requires repetitive inspections to check the play of the eye-end of the piston rod of the elevator servo- controls, and follow-on corrective actions if necessary. This amendment requires the replacement of certain elevator servo-controls with new, improved servo-controls. The actions specified by this AD are intended to detect and correct excessive play of the eye-end of the piston rod of the elevator servo-controls, which could result in failure of the elevator servo-control. This action is intended to address the identified unsafe condition.
AD 2004-14-01 · published Jul 9, 2004, effective Aug 13, 2004
Fokker Model F.28 Mark 0070 and 0100 Series Airplanes
This amendment supersedes an existing airworthiness directive (AD), applicable to certain Fokker Model F.28 Mark 0100 series airplanes, that currently requires repetitive inspections of certain main landing gear (MLG) main fittings to detect forging defects, and rework of the main fittings if necessary. This amendment requires either replacement of each MLG with a MLG that has main fittings that have been inspected and reworked, or various one-time inspections of the main fittings and rework if necessary. Either of these actions constitutes terminating action for the repetitive inspections. This action also revises the applicability by adding airplanes. The actions specified by this AD are intended to detect forging defects of the MLG main fittings, which could lead to cracking and result in significant structural damage to the airplane and possible injury to the occupants. This action is intended to address the identified unsafe condition.
AD 2004-14-03 · published Jul 9, 2004, effective Aug 13, 2004
BAE Systems (Operations) Limited (Jetstream) Model 4101 Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to all BAE Systems (Operations) Limited (Jetstream) Model 4101 airplanes, that requires a one-time inspection of the ailerons to determine if certain actions were accomplished previously, and related investigative and corrective actions if necessary. This action is necessary to prevent damage to the rear spar rib-to-rib attachment cleats and the aft rib elements of the fixed tabs of the ailerons. Such damage could lead to reduced structural integrity and consequent failure of the ailerons, which could result in reduced controllability of the airplane. This action is intended to address the identified unsafe condition.
AD 2004-14-04 · published Jul 9, 2004, effective Aug 13, 2004
BAE Systems (Operations) Limited Model BAe 146 Series Airplanes and Model Avro 146-RJ Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to all BAE Systems (Operations) Limited Model BAe 146 series airplanes and Model Avro 146-RJ series airplanes, that requires performing a detailed inspection for chafing of the fuel quantity indication (FQI) system wiring, and any applicable corrective actions. These actions are necessary to prevent possible failure of the FQI system, which could cause the flightcrew to act on misleading information and possibly lead to in-flight fuel exhaustion. This action is intended to address the identified unsafe condition.
AD 2004-14-05 · published Jul 9, 2004, effective Aug 13, 2004
McDonnell Douglas Model DC-8-11, DC-8-12, DC-8-21, DC-8-31, DC-8-32, DC-8-33, DC-8-41, DC-8-42, DC-8-43, DC-8F-54, and DC-8F-55 Airplanes; and Model DC-8-50, -60, -60F, -70 and -70F Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas airplane models, that requires inspection of the captain's and first officer's seat locking pins for minimum engagement with the detent holes in the seat tracks; inspection of the seat lockpins for excessive wear; and corrective actions, if necessary. This action is necessary to prevent uncommanded seat movement during takeoff and/or landing, which could result in interference with the operation of the airplane and consequent temporary loss of control of the airplane. This action is intended to address the identified unsafe condition.
AD 2004-14-06 · published Jul 9, 2004, effective Aug 13, 2004
Airbus Model A310 Series Airplanes
This amendment supersedes an existing airworthiness directive (AD), applicable to certain Airbus Model A310 series airplanes, that currently requires repetitive inspections of the fuselage skin to detect corrosion or fatigue cracking around and under the chafing plates of the wing root; and corrective actions, if necessary. That AD also provides an optional terminating action for the repetitive inspections. This amendment reinstates repetitive inspections in certain areas where corrosion was detected and reworked as required by the existing AD. The actions specified by this AD are intended to detect and correct fatigue cracks and corrosion around and under the chafing plates of the wing root, which could result in reduced structural integrity of the airplane. This action is intended to address the identified unsafe condition.
AD 2004-14-07 · published Jul 9, 2004, effective Aug 13, 2004
BAE Systems (Operations) Limited (Jetstream) Model 4101 Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to all BAE Systems (Operations) Limited (Jetstream) Model 4101 airplanes, that requires a test for free movement of the capsule/ bearing of the nose landing gear (NLG), and related investigative, significant, and corrective actions. This action is necessary to prevent failure of the NLG to extend fully, which could result in reduced controllability of the airplane during landing. This action is intended to address the identified unsafe condition.
AD 2004-14-09 · published Jul 9, 2004, effective Aug 13, 2004
Airbus Model A320-111, -211, -212, and -231 Series Airplanes
This amendment supersedes an existing airworthiness directive (AD), applicable to certain Airbus Model A320-111, -211, -212, and -231 series airplanes, that currently requires repetitive inspections to detect fatigue cracking of the lower surface panel on the wing center box, and repair if necessary. That AD also requires modification of the lower surface panel on the wing center box, which constitutes terminating action for the repetitive inspections. This amendment reduces the compliance times for the inspections required by the existing AD. The actions specified by this AD are intended to prevent fatigue cracking of the lower surface panel on the wing center box, which could result in reduced structural integrity of the airplane. This action is intended to address the identified unsafe condition.
AD 2004-14-10 · published Jul 9, 2004, effective Aug 13, 2004
McDonnell Douglas Model MD-11 and -11F Airplanes
This amendment supersedes an existing airworthiness directive (AD), applicable to certain McDonnell Douglas Model MD-11 and -11F airplanes, that currently requires, among other actions, replacing the ground support bracket(s); and rerouting the ground cables of the galley external power and main external power, as applicable. This amendment requires replacing ground support brackets with new brackets, and replacing ground cables of the galley external power and main external power with new cables; as applicable. This amendment also requires an inspection to detect the presence of a fillet seal at the ground brackets and to detect excessive length and correct terminations of the ground cables of the galley and main external power, as applicable; and corrective actions if necessary. The actions specified by this AD are intended to prevent arcing and heat damage to the attachment points of the main external and galley power receptacle ground wire, insulation blankets outboard and aft of the receptacle area, and adjacent power cables, which could result in smoke and fire in the forward cargo compartment. This action is intended to address the identified unsafe condition.
AD 2004-14-11 · published Jul 9, 2004, effective Aug 13, 2004
Saab Model SAAB 2000 Series Airplanes
This amendment supersedes an existing airworthiness directive (AD), applicable to certain Saab Model SAAB 2000 series airplanes, that currently requires repetitive inspections for discrepancies of the upper and lower areas of the backup struts in the left and right nacelles; and corrective actions, if necessary. This amendment requires repetitive inspections for cracks in the lower areas of the backup struts, and corrective actions if necessary. This action also requires the eventual replacement of the backup struts with new, improved struts, which terminates the repetitive inspections. The actions specified by this AD are intended to prevent failure of the backup struts in the left and right nacelles due to fatigue cracking, which could result in loss of fail-safe redundancy in the design of the nacelle in terms of load capability, and consequent separation of the engine from the airplane and subsequent reduced controllability of the airplane. This action is intended to address the identified unsafe condition.
AD 2004-14-12 · published Jul 9, 2004, effective Aug 10, 2004
The New Piper Aircraft, Inc., Models PA-28-161, PA-28-181, PA-28R-201, PA-32R-301 (HP), PA-32R-301T, PA-32-301FT, PA-32-301XTC, PA-34-220T, PA-44-180, PA-46-350P, and PA-46-500TP Airplanes
The FAA is adopting a new airworthiness directive (AD) for certain The New Piper Aircraft, Inc. (Piper), Models PA-28-161, PA-28- 181, PA-28R-201, PA-32R-301 (HP), PA-32R-301T, PA-32-301FT, PA-32- 301XTC, PA-34-220T, PA-44-180, PA-46-350P, and PA-46-500TP airplanes. This AD requires you to inspect the control wheel attaching hardware for proper installation, replace if required, add Loctite thread- locking compound to the screw installation, and install a retainer clip to the control wheel attachment. This AD is the result of inadequate control wheel attachment design. The screw used to attach the control wheel to the control column is too short in some installations, and the nut-plate does not have adequate locking features. In addition, the screw is installed from the bottom of the control wheel and will depart quickly after thread disengagement. We are issuing this AD to detect and correct inadequate control wheel attachment design features, which could result in loss of control of the ailerons and elevator. This failure could lead to loss of control of the aircraft.
AD 2004-14-14 · published Jul 9, 2004, effective Aug 13, 2004
Israel Aircraft Industries, Ltd., Model 1121, 1121A, 1121B, 1123, 1124, and 1124A Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to all Israel Aircraft Industries, Ltd., Model 1121, 1121A, 1121B, 1123, 1124, and 1124A series airplanes, that requires a one-time inspection to detect cracking and other discrepancies of both sides of the rudder skins and ribs, forward to aft on each spar, to detect cracks below the skin surface; and corrective action if necessary. This action is necessary to detect and correct cracking of the skins of the rudder assembly, which could result in reduced structural capability of the rudder and reduced controllability of the airplane. This action is intended to address the identified unsafe condition.
AD 2004-14-15 · published Jul 9, 2004, effective Aug 13, 2004
Bombardier Model DHC-8-400 Airplanes
This amendment supersedes an existing airworthiness directive (AD), applicable to certain Bombardier Model DHC-8-400 airplanes. That AD currently requires revising the Normal and Abnormal sections of the airplane flight manual (AFM) to include procedures that enable the flightcrew to determine if the main landing gear (MLG) is extended before landing, and to take appropriate actions if necessary. This amendment adds an airplane to the applicability, and requires replacing the existing MLG downlock proximity sensors with new, improved sensors. After the replacement, this action also requires removing from the AFM the revision to the Normal and Abnormal sections required by the existing AD. The actions specified by this AD are intended to prevent failure of the MLG downlock proximity sensors on the same MLG at the same time, which could result in the MLG's failure to extend during landing, and cause injury to flightcrew and passengers. This action is intended to address the identified unsafe condition.
AD 2004-14-16 · published Jul 9, 2004, effective Aug 13, 2004
Bombardier Model CL-600-2B19 (Regional Jet Series 100 & 440) Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Bombardier Model CL-600-2B19 (Regional Jet Series 100 & 440) airplanes, that requires repetitive detailed and eddy current inspections on the main fittings of the main landing gears (MLG) to detect discrepancies, and related investigative/corrective actions if necessary. This action also requires servicing the shock strut of the MLGs; inspecting the shock strut of the MLGs for nitrogen pressure, visible chrome dimension, and oil leakage; and servicing any discrepant strut. This action is necessary to detect and correct premature cracking of the main fittings of the MLGs, which could result in failure of the fittings and consequent collapse of the MLGs during landing. This action is intended to address the identified unsafe condition.
AD 2004-14-08 · published Jul 13, 2004, effective Aug 17, 2004
Airbus Model A300 B4-600, B4-600R, C4-605R Variant F, and F4-600R (Collectively Called A300-600), and A310 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A300-600 and A310 series airplanes, that requires modification of the attachment system of the insulation blankets of the forward cargo compartment and related corrective action. This action is necessary to prevent failure of the attachment system of the cargo insulation blankets, which could result in detachment and consequent tearing of the blankets. Such tearing could result in blanket pieces being ingested into and jamming the forward outflow valve of the pressure regulation subsystem, which could lead to cabin depressurization and adversely affect continued safe flight of the airplane. This action is intended to address the identified unsafe condition.
AD 2004-14-13 · published Jul 13, 2004, effective Aug 17, 2004
Boeing Model 747-100, 747-200B, 747-200C, 747-200F, 747-300, 747-400, 747-400D, 747-400F, and 747 SR Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 747- 100, 747-200B, 747-200C, 747-200F, 747-300, 747-400, 747-400D, 747- 400F, and 747 SR series airplanes, that requires inspection of fire extinguisher bottles in the engine and the auxiliary power unit (APU) to determine the part number; and replacement of the fire extinguisher bottles with new fire extinguisher bottles, if necessary. This action is necessary to prevent fractured discharge heads, which could cause the fire extinguishing agent to leak, which could result in an uncontrolled engine fire that could spread to the strut and wing, or an uncontrolled APU fire that could spread to the airplane structure. This action is intended to address the identified unsafe condition.
AD 2004-14-17 · published Jul 13, 2004, effective Aug 17, 2004
Airbus Model A300 B4-600, B4-600R, and F4-600R (Collectively Called A300-600) Series Airplanes; and Model A310 Series Airplanes; Equipped With Pratt & Whitney JT9D-7R4 or 4000 Series Engines
This amendment supersedes an existing airworthiness directive (AD), applicable to certain Airbus Model A300-600 and A310 series airplanes, that currently requires deactivating both thrust reversers and revising the airplane flight manual (AFM) to ensure safe and appropriate performance during certain takeoff conditions. This amendment requires installing modifications that will add an independent third line of defense on the thrust reversers, which would enhance their redundancy and terminate the requirements of the existing AD. The actions specified by this AD are intended to prevent in-flight deployment of the thrust reversers, which could result in reduced controllability of the airplane. This action is intended to address the identified unsafe condition.
AD 2004-14-18 · published Jul 13, 2004, effective Aug 17, 2004
Bombardier Model DHC-8-102, -103, and -106 Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Bombardier Model DHC-8-102, -103, and -106 airplanes, that requires repetitive detailed inspections of the left and right aileron tab actuator arm channels for cracking, and corrective actions if necessary. This proposal also provides an optional terminating action for the repetitive inspections. This action is necessary to prevent increased roll forces due to cracking of the left and right aileron tab actuator arms, which could be interpreted by the pilot as a flight control problem and might lead to loss of control of the airplane. This action is intended to address the identified unsafe condition.
AD 2004-14-20 · published Jul 13, 2004, effective Aug 23, 2004
The Cessna Aircraft Company Model 525 Airplanes
The FAA supersedes Airworthiness Directive (AD) 2003-21-07, which applies to certain The Cessna Aircraft Company (Cessna) Model 525 airplanes. AD 2003-21-07 currently requires you to disengage the pitch trim circuit breaker and AP servo circuit breaker and then tie strap each of them to prevent them from being engaged. Not utilizing this equipment prevents a single-point failure. This AD is the result of Cessna having now developed and made changes in the design of the affected trim printed circuit board (PCB) assembly to allow the use of the assembly and the prevention of the single-point failure, and identification of additional airplanes that have the same unsafe condition. Consequently, this AD requires you to remove and replace an old trim PCB assembly with a new design assembly or modify an old trim PCB assembly to the new design. We are issuing this AD to correct this single-point failure in the electric pitch trim system, which will result in a runaway pitch trim condition where the pilot could not disconnect using the control wheel autopilot/trim disconnect switch. Failure of the electric trim system would result in a large pitch mistrim and would cause excessive control forces that the pilot could not overcome.
AD 2004-14-19 · published Jul 16, 2004, effective Aug 20, 2004
Boeing Model 767 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to all Boeing Model 767 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 of the passenger cabin, possible damage or interference with the airplane control systems that pass through the bulkhead, and consequent loss of control of the airplane. This action is intended to address the identified unsafe condition.
AD 2004-14-23 · published Jul 19, 2004, effective Aug 23, 2004
Airbus Model A319-111, -112, -113, and -114; A320-111, -211, -212, and -214; and A321-111, -112, and -211 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A319, A320, and A321 series airplanes, that requires a one-time inspection to identify the serial number of the actuator of the thrust reverser blocker door, and corrective action if necessary. This action is necessary to prevent inadvertent deployment of the thrust reverser door, which could result in reduced controllability of the airplane. This action is intended to address the identified unsafe condition.
AD 2004-14-24 · published Jul 19, 2004, effective Aug 23, 2004
Empresa Brasileira de Aeronautica S.A. (EMBRAER) Model EMB-120 Series Airplanes
This amendment supersedes an existing airworthiness directive (AD), applicable to certain Empresa Brasileira de Aeronautica S.A. (EMBRAER) Model EMB-120 series airplanes, that currently requires measuring the gap between the bellcrank and the body of the rotary variable inductive transducers (RVITs) of the aileron and elevator, performing corrective action if necessary, and torquing the bolt that attaches the bellcrank to the RVIT shaft. This amendment requires replacing the aileron and elevator RVIT bellcranks with new, improved bellcranks. The actions specified by this AD are intended to prevent restricted movement of the aileron or elevator, which could result in reduced controllability of the airplane. This action is intended to address the identified unsafe condition.
AD 2004-14-25 · published Jul 19, 2004, effective Aug 23, 2004
Empresa Brasileira de Aeronautica S.A. (EMBRAER) Model EMB-120 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Empresa Brasileira de Aeronautica S.A. (EMBRAER) Model EMB-120 series airplanes, that requires installing a lightning bonding jumper from the lower rotating beacon to the airframe. This action is necessary to prevent possible multiple avionics failures caused by a lightning strike, which could reduce the ability of the flightcrew to control the airplane. This action is intended to address the identified unsafe condition.
AD 2004-15-01 · published Jul 22, 2004, effective Aug 23, 2004
Raytheon Aircraft Company Model 390 Airplanes
The FAA is adopting a new airworthiness directive (AD) for certain Raytheon Aircraft Company (Raytheon) Model 390 airplanes. This AD requires you to inspect the hydraulic tube/hose assemblies, the engine fuel feed tube assemblies, and the engine wire harnesses for proper clearance and damage (as applicable). If improper clearance or damage is found on any assembly, you must replace and/or modify the affected assembly. This AD is the result of reports of loss of the hydraulic system functions during different operations caused by improper clearance between certain components. This resulted in damage to the tubing in the hydraulic system assemblies. Analysis shows a similar condition on the engine fuel feed assemblies. We are issuing this AD to detect, correct, and prevent such damage or improper clearance in the affected areas, which could result in failure of one or more of these systems. These failures could lead to loss of hydraulic system operations, engine shutdown, and false readings for fuel pressure, oil pressure, and other oil indications. These conditions could consequently result in reduced or loss of control of the airplane.
AD 2004-15-04 · published Jul 27, 2004, effective Aug 31, 2004
Boeing Model 737-200, -200C, -300, -400, and -500 Series Airplanes
This amendment supersedes an existing airworthiness directive (AD), applicable to certain Boeing airplane models, that currently requires either inspections for discrepancies of the fueling float switch wiring in the center fuel tank and follow-on actions, or deactivation of the float switch. This amendment requires replacing the float switches in the center and wing fuel tanks with new, improved parts; installing a conduit liner system in the center fuel tank; and replacing conduit assemblies in the wing fuel tanks with new parts, which terminates the existing requirements. For certain airplanes, this amendment also requires replacing certain existing sections of the electrical conduit in the center fuel tank with new conduit. This amendment also adds one additional airplane model to the applicability and removes another. The actions specified by this AD are intended to prevent contamination of the fueling float switch by moisture or fuel, and chafing of the float switch wiring against the fuel tank conduit, which could present an ignition source inside the fuel tank that could cause a fire or explosion. This action is intended to address the identified unsafe condition.
AD 2004-15-05 · published Jul 27, 2004, effective Aug 31, 2004
BAE Systems (Operations) Limited Model BAe 146 and Avro 146-RJ Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain BAE Systems (Operations) Limited Model BAe 146 and Avro 146-RJ series airplanes, that requires replacing the existing bellows inlet duct of the auxiliary power unit (APU) system with a new, improved rectangular metallic bellows inlet duct. This action is necessary to prevent air from the APU bay being ingested into the flight deck and passenger cabin resulting in poor air quality and, if the air is contaminated, possible incapacitation of the flightcrew and passengers. This action is intended to address the identified unsafe condition.
AD 2004-15-06 · published Jul 27, 2004, effective Aug 31, 2004
BAE Systems (Operations) Limited (Jetstream) Model 4101 Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to all BAE Systems (Operations) Limited (Jetstream) Model 4101 airplanes, that requires various inspections of the fuselage nose structure between stations 4 and 11, and corrective actions if necessary. This action is necessary to detect and correct fatigue cracking in the primary structure of the nose of the airplane at the forward avionics bay (fuselage stations 4 to 11), which could result in reduced structural integrity of the airplane. This action is intended to address the identified unsafe condition.
AD 2004-15-07 · published Jul 27, 2004, effective Aug 31, 2004
Airbus Model A310 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A310 series airplanes, that requires repetitive inspections for fatigue cracking of the area around the fasteners of the landing plate of the aileron access doors of the bottom skin panel of the wings, and related corrective action. This amendment also provides for an optional terminating action, which ends the repetitive inspections. This action is necessary to prevent fatigue cracking of the area around the fasteners of the landing plate of the aileron access doors and the bottom skin panel of the wings, which could result in reduced structural integrity of the wings. This action is intended to address the identified unsafe condition.
AD 2004-15-08 · published Jul 27, 2004, effective Aug 31, 2004
Fokker Model F.28 Mark 0070 and 0100 Series Airplanes
This amendment supersedes an existing airworthiness directive (AD), applicable to all Fokker Model F.28 Mark 0070 and 0100 series airplanes, that currently requires revising the Airworthiness Limitations section of the Instructions for Continued Airworthiness to incorporate life limits for certain items and inspections to detect fatigue cracking in certain structures. This amendment requires revising the Airworthiness Limitations section of the Instructions for Continued Airworthiness to incorporate updated Airworthiness Limitation Items, Safe Life Items, and Certification Maintenance Requirements. The actions specified by this AD are intended to ensure the structural integrity of the airplane by ensuring that fatigue cracking of certain structural elements is detected and corrected in a timely manner. This action is intended to address the identified unsafe condition.
AD 2004-15-09 · published Jul 27, 2004, effective Aug 31, 2004
Bombardier Model DHC-8-101, -102, -103, -106, -201, -202, -301, -311, and -315 Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Bombardier Model DHC-8-101, -102, -103, -106, - 201, -202, -301, -311, and -315 airplanes. This amendment requires an inspection of the fuel tube assembly of the auxiliary power unit (APU) for clearance from adjacent components; and an inspection of the fuel tube assembly and the bleed air duct shroud for discrepancies (insufficient clearance, nicks, dents, chafing, or other damage); and related investigative and corrective actions if necessary. This amendment also requires relocation of certain support clamps on the APU fuel tube assembly. This action is necessary to prevent a fuel leak caused by chafing of the APU fuel tube assembly, which could result in fire in the center wing area. This action is intended to address the identified unsafe condition.
AD 2004-15-10 · published Jul 27, 2004, effective Aug 31, 2004
Saab Model SAAB SF340A Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Saab Model SAAB SF340A series airplanes, that requires replacing certain power wires with a modification harness; and testing the new harness installation. These actions are necessary to prevent a momentary loss of data on the left-hand electronic flight instrumentation system (LH EFIS) screens, which could lead to the pilot's loss of situational awareness during initial climb or approach/ landing, and possibly result in reduced control of the airplane. This action is intended to address the identified unsafe condition.
AD 2004-15-12 · published Jul 29, 2004, effective Sep 2, 2004
Airbus Model A330-202, -203, -223, and -243 Airplanes, and A330-300 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A330-202, -203, -223, and -243 airplanes, and A330-300 series airplanes, that requires modification of the control box of the auxiliary power unit (APU). This action is necessary to prevent uncommanded in-flight shutdown of the APU, which could result in loss of critical electrical systems when the airplane is operated in emergency electrical configuration, and consequent reduced controllability of the airplane. This action is intended to address the identified unsafe condition.
AD 2004-15-13 · published Jul 29, 2004, effective Sep 2, 2004
McDonnell Douglas Model DC-9-81 (MD-81), DC-9-82 (MD-82), DC-9-83 (MD-83), DC-9-87 (MD-87), and Model MD-88 Airplanes
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), DC-9-87 (MD-87), and Model MD-88 airplanes, that requires replacement of certain freeze protection ribbon heaters in the lavatory water supply system, and flushing, cleaning, and sterilizing the potable water system; disconnecting, coiling, and stowing the wiring of the freeze protection ribbon heater; or removal of freeze protection heaters. This action is necessary to prevent failure of freeze protection ribbon heaters, which could result in the charring, scorching, smoking, and shorting out of freeze protection ribbon heaters in the lavatory water supply system. This condition, if not corrected, could also result in electrical arcing of freeze protection ribbon heaters, leading to fire and damage to water lines and components under the lavatory sink. This action is intended to address the identified unsafe condition.
AD 2004-15-14 · published Jul 29, 2004, effective Aug 13, 2004
Airbus Model A319-131, -132, and -133; A320-231, -232, and -233; and A321-131 and -231 Series Airplanes
The FAA is adopting a new airworthiness directive (AD) for certain Airbus Model A319-131, -132, and -133; A320-231, -232, and - 233; and A321-131 and -231 series airplanes. This AD requires revising the airplane flight manual (AFM) to advise the flightcrew of procedures associated with the intermittent interruption of the electrical power. Under certain conditions, this AD also requires inspecting for signs of arcing and performing any necessary corrective actions. This AD also provides for optional terminating action for the requirements of the AD. This AD is prompted by reports of fretting and consequent arcing of the electrical harness of the integrated drive generator (IDG) at the pin-to-socket connector at the firewall. We are issuing this AD to prevent transient loss of certain systems and consequent reduced ability of the flightcrew to cope with adverse flight conditions.
AD 2004-15-15 · published Jul 30, 2004, effective Sep 7, 2004
Air Tractor, Inc. Models AT-401, AT-401B, AT-402, AT-402A, AT-402B, AT-501, AT-502, AT-502A, AT-502B, AT-503A, AT-602, AT-802, and AT-802A Airplanes
The FAA supersedes Airworthiness Directive (AD) 2002-19-10, which applies to certain Air Tractor, Inc. (Air Tractor) Models AT-402, AT-402A, AT-402B, AT-602, AT-802, and AT-802A airplanes. AD 2002-19-10 currently requires you to repetitively inspect the upper longeron and upper diagonal tube on the left hand side of the aft fuselage structure for cracks and contact the manufacturer for a repair scheme if cracks are found. This AD is the result of reports of the same cracks recently found on AT-500 series airplanes. The manufacturer has also issued new and revised service information that incorporates a modification to terminate the repetitive inspection requirements. Consequently, this AD retains the inspection actions required in AD 2002-19-10, adds certain AT-500 series airplanes to the applicability section, changes the compliance times, and incorporates new and revised manufacturer service information that contains a terminating action for the repetitive inspection requirement. We are issuing this AD to detect and correct cracks in the upper aft longeron, which could cause the fuselage to fail. Such failure could result in loss of control of the airplane.
AD 2004-15-16 · published Jul 30, 2004, effective Sep 3, 2004
Airbus Model A310 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A310 series airplanes, that requires modification of certain wires in the right-hand wing. This action is necessary to ensure that fuel quantity indication wires are properly separated from wires carrying 115-volt alternating current (AC). Improper separation of such wires, in the event of wire damage, could lead to a short circuit and a possible ignition source, which could result in a fire in the airplane. This action is intended to address the identified unsafe condition.
AD 2004-15-17 · published Jul 30, 2004, effective Sep 3, 2004
Fokker Model F27 Mark 100, 200, 300, 400, 500, 600, and 700 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Fokker Model F27 Mark 100, 200, 300, 400, 500, 600, and 700 series airplanes, that requires a one-time inspection to determine the part number of the engine mounting frames, brace struts, and attachment fittings; and related corrective action. This action is necessary to ensure the structural integrity of the engine-to-wing load path and prevent possible separation of the engine from the airplane. This action is intended to address the identified unsafe condition.
AD 2004-15-18 · published Jul 30, 2004, effective Sep 12, 2004
Cessna Aircraft Company Models 172R, 172S, 182S, 182T, T182T, 206H, and T206H Airplanes
The FAA supersedes Airworthiness Directive (AD) 2003-24-13, which applies to certain Cessna Aircraft Company (Cessna) Models 172R, 172S, 182S, 182T, T182T, 206H, and T206H airplanes that are equipped with a certain Honeywell KAP 140 autopilot computer system installed on the center instrument control panel near the throttle. AD 2003-24-13 currently requires you to install an update to the operating software of certain KAP 140 autopilot computer system, change the unit's part number, and change the software modification identification tab. This AD is the result of the FAA inadvertently omitting four affected Honeywell KAP 140 autopilot computer system part numbers and an affected airplane serial number from the applicability section of AD 2003-24-13. This AD retains the actions required in AD 2003-24-13, corrects the applicability section, and incorporates a revised installation bulletin issued by Honeywell.
AD 2004-15-19 · published Jul 30, 2004, effective Sep 13, 2004
The New Piper Aircraft, Inc. Model PA-46-500TP Airplanes
The FAA adopts a new airworthiness directive (AD) for certain the New Piper Aircraft, Inc. (Piper) Model PA-46-500TP airplanes. This AD requires you to inspect (one-time) for the existence of any protective cover over the percussion caps or silicon tube installed over the end of the trigger mechanism pin of the oxygen generators, and remove any protective cover or silicon tube found. This AD is the result of reports of the above conditions found on the affected airplanes. We are issuing this AD to detect and remove any protective cover over the percussion cap, or any silicon tube over the end of the trigger mechanism pin, which could result in failure of the emergency oxygen system. This failure could lead to the crew and passengers not being able to get oxygen in an emergency situation.
AD 2004-15-20 · published Jul 30, 2004, effective Sep 3, 2004
Empresa Brasileira de Aeronautica S.A. (EMBRAER) Model EMB-135 and -145 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain EMBRAER Model EMB-135 and -145 series airplanes, that requires replacing the electrical harness for the tail boom strobe light with a new, improved harness that has a built-in metallic overbraid, and performing an operational test following the replacement. This action is necessary to ensure that there is sufficient lightning bonding at the electrical harness for the tail boom strobe light, and to prevent the simultaneous failure of multiple avionics systems in the event of a lightning strike, which could result in reduced controllability of the airplane. This action is intended to address the identified unsafe condition.
AD 2003-13-15 R1 · published Jul 6, 2004, effective Aug 10, 2004
Schweizer Aircraft Corporation Model 269A, 269A-1, 269B, 269C, and TH-55A Helicopters
This amendment revises an existing airworthiness directive (AD), for the specified Schweizer Aircraft Corporation (Schweizer) model helicopters, that currently requires inspecting the lugs on certain aft cluster fittings and each aluminum end fitting on certain tailboom struts. Modifying or replacing each strut assembly within a specified time period and serializing certain strut assemblies are also required. Additionally, a one-time inspection and repair, if necessary, of certain additional cluster fittings, and replacement and modification of certain cluster fittings within 150 hours time-in- service (TIS) or 6 months, whichever occurs first, is required. This amendment requires the same actions as the existing AD, but revises the Applicability section of the AD. This amendment is prompted by the discovery of an error in the Applicability section of the existing AD. The actions specified by this AD are intended to prevent failure of a tailboom support strut or a cluster fitting, which could cause rotation of a tailboom into the main rotor blades, and subsequent loss of control of the helicopter.
AD 95-26-05 R1 · published Jul 6, 2004, effective Jul 6, 2004
Robinson Helicopter Company Model R44 Helicopters
This amendment rescinds an existing Airworthiness Directive (AD) for Robinson Helicopter Company (Robinson) Model R44 helicopters, which currently requires revisions to the R44 Rotorcraft Flight Manual (RFM). The RFM revisions limit operations in high winds and turbulence. The RFM revisions also provide information about main rotor stall and mast bumping with recommendations for avoiding these situations and additional emergency procedures for use in certain conditions. This amendment is prompted by the FAA's determination that the limitations and the procedures required by that AD are no longer necessary to correct an unsafe condition. The actions specified by this AD rescind all the requirements of AD 95-26-05, Amendment 39-9463, Docket 95-SW- 30-AD.
AD 2004-13-26 · published Jul 7, 2004, effective Jul 22, 2004
Kaman Aerospace Corporation Model K-1200 Helicopters
This amendment adopts a new airworthiness directive (AD) for Kaman Aerospace Corporation (Kaman) Model K-1200 helicopters. This action requires certain initial and repetitive visual inspections of the main rotor blade (blade) grips for a crack. If a crack is found, this AD requires replacing the blade grip before further flight. This amendment is prompted by an accident involving the loss of all blades because of a crack in a blade grip on the upper surface around the bolthole. The actions specified in this AD are intended to prevent failure of a blade grip, loss of a blade, and subsequent loss of control of the helicopter.
AD 2004-15-11 · published Jul 30, 2004, effective Sep 3, 2004
Eurocopter France Model EC155B and B1 Helicopters
This amendment adopts a new airworthiness directive (AD) for the specified Eurocopter France (ECF) model helicopters that requires cleaning the auxiliary system unit (ASU) board and modifying the wiring and wiring harness. If a temporary modification is done, the AD requires inserting a placard regarding on- ground operation of the emergency landing gear pump (pump). Also, this AD revises the Limitations section of the Rotorcraft Flight Manual (RFM) to limit the operation of the pump. Permanently modifying the wiring and wiring harness and removing the placard and limitations from the RFM is terminating action for the requirements of this AD. This amendment is prompted by the report of an emergency landing with the landing gear retracted. The landing gear failed to extend in normal and emergency extension modes following failure of the ASU board 10 Alpha 2. The actions specified by this AD are intended to prevent an electrical short circuit, failure of landing gear to extend, and a landing gear-up emergency landing.
AD 2004-14-02 · published Jul 9, 2004, effective Jul 26, 2004
Rolls-Royce Corporation (Formerly Allison Engine Company, Allison Gas Turbine Division, and Detroit Diesel Allison) Models 250-C28, -C28B, and -C28C Turboshaft Engines
The FAA is adopting a new airworthiness directive (AD) for Rolls-Royce Corporation (formerly Allison Engine Company, Allison Gas Turbine Division, and Detroit Diesel Allison) (RRC) models 250-C28, - C28B, and -C28C turboshaft engines with certain serial number (SN) third-stage turbine wheels, part number (P/N) 6899383. This AD requires replacing certain SN third-stage turbine wheels, P/N 6899383, before reaching new reduced life limits. This AD results from three reports of third-stage turbine blade and shroud failures. We are issuing this AD to prevent loss of power and uncommanded engine shutdown due to failure of third-stage turbine blades and shrouds.
AD 2004-14-22 · published Jul 19, 2004, effective Aug 3, 2004
Pratt & Whitney Canada PW206B, PW206C, PW206E, PW207D, and PW207E Turboshaft Engines
The FAA is adopting a new airworthiness directive (AD) for Pratt & Whitney Canada (PWC) PW206B engines that have incorporated PWC Service Bulletin (SB) No. 28119, and PW206C, PW206E, PW207D, and PW207E turboshaft engines. This AD requires checking the automatic low-cycle- fatigue (LCF) counting data made by the engine Data Collection Unit (DCU) on installed engines, and validating proper DCU automatic LCF counting before an engine is installed. This AD results from two reports of irregular LCF counting, observed between engines on the same helicopter, during weekly recording of LCF data in the engine log books. We are issuing this AD to prevent critical rotating parts from exceeding published life limits, which could result in uncontained engine failure and possible loss of the helicopter.
AD 2004-15-02 · published Jul 28, 2004, effective Sep 1, 2004
Rolls-Royce plc RB211 Trent 800 Series Turbofan Engines
The FAA is adopting a new airworthiness directive (AD) for Rolls-Royce plc (RR) models RB211 Trent 875-17, Trent 877-17, Trent 884-17, Trent 884B-17, Trent 892-17, Trent 892B-17, and Trent 895-17 turbofan engines with low pressure (LP) compressor fan blades part number (P/N) FW18548, installed. This AD requires LP compressor fan blade replacement with new or previously reworked blades, or rework of the existing LP compressor fan blades. This AD results from a number of new production LP compressor fan blades found with surfaces formed outside of design intent. Findings included sharp edges, burrs, and damage present in the area at the top of the shear key slots. We are issuing this AD to prevent possible multiple uncontained LP compressor fan blade failure, due to cracking in the blade root caused by increased stresses in the shear key slots.
AD 2004-15-03 · published Jul 30, 2004, effective Aug 16, 2004
General Electric Company CF34-3A1 and -3B1 Series Turbofan Engines
The FAA is adopting a new 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 6089T89P01. This AD requires initial and repetitive visual and eddy current inspections of those disks. This AD also allows as optional terminating action to the repetitive inspections, replacement of those SN disks. This AD also requires replacement of certain stage 5 and stage 6 LPT disks. This AD results from a report of a stage 5 LPT disk that failed due to cracking from low-cycle-fatigue (LCF) during factory testing. 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 2004-14-21 · published Jul 13, 2004, effective Aug 21, 2004
Stemme GmbH & Co. Models S10, S10-V, and S10-VT Sailplanes
The FAA adopts a new airworthiness directive (AD) for all Stemme GmbH & Co. Models S10, S10-V, and S10-VT sailplanes. This AD requires you to remove the drive shaft assembly and ship it to the service department of Stemme GmbH & Co. The engine is mounted behind the two side-by-side seats. The engine combined with the carbon fiber drive shaft turn the centrifugally extended propeller. After an initial visual inspection, the service department will perform an operational check to determine whether the drive shaft can be further used or must be replaced. Once corrective action is identified, a drive shaft will be shipped to you for installation. This AD is the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for Germany. We are issuing this AD to detect and correct incorrectly glued drive shafts, which could result in drive shaft failure. During self-takeoff or critical periods of landing, failure of the drive shaft could lead to loss of control of the sailplane.
