43 Airworthiness Directives: 34 airplane, 2 rotorcraft, 6 engine, 1 propeller.
AD 2006-05-02 · published Mar 2, 2006, effective Apr 6, 2006
Boeing Model 747-200F, 747-200C, 747-400, 747-400D, and 747-400F Series Airplanes
The FAA is adopting a new airworthiness directive (AD) for all Boeing Model 747-200F, 747-200C, 747-400, 747-400D, and 747-400F series airplanes. This AD requires repetitive inspections for cracking of certain fuselage internal structure, and repair if necessary. This AD results from fatigue tests and analysis that identified areas of the fuselage where fatigue cracks can occur. We are issuing this AD to prevent loss of the structural integrity of the fuselage, which could result in rapid depressurization of the airplane.
AD 2006-03-15 · published Mar 6, 2006, effective Apr 10, 2006
Boeing Model 747SP, 747SR, 747-100, -100B, -100B SUD, -200B, -200C, -200F, and -300 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to all Boeing Model 747SP, 747SR, 747-100, -100B, -100B SUD, -200B, -200C, -200F, and -300 series airplanes, that requires modification of the escape slide/raft pack assembly and cable release sliders, as applicable. The actions specified by this AD are intended to prevent improper deployment of the escape slide/raft or blockage of the passenger/crew doors in the event of an emergency evacuation, which could result in injury to passengers or crewmembers. This action is intended to address the identified unsafe condition.
AD 2006-05-06 · published Mar 9, 2006, effective Apr 13, 2006
Boeing Model 747 Airplanes
The FAA is superseding three existing airworthiness directives (ADs) that apply to certain Boeing Model 747 airplanes. The existing ADs currently require repetitive inspections of the body station (BS) 2598 bulkhead, and corrective action if necessary. This new AD adds a requirement to modify the bulkhead, including a one-time inspection and corrective action if necessary, which terminates certain repetitive inspections. This AD also requires a post-modification inspection of the modified area. This AD results from new reports of cracking in all three areas that require inspection in accordance with the existing ADs. We are issuing this AD to prevent fatigue cracking of the BS 2598 bulkhead structure, which could result in inability of the structure to carry horizontal stabilizer flight loads, and loss of controllability of the airplane.
AD 2006-05-07 · published Mar 9, 2006, effective Apr 13, 2006
Aerospatiale Model ATR42-200, -300, and -320 Airplanes
The FAA is adopting a new airworthiness directive (AD) for certain Aerospatiale Model ATR42-200, -300, and -320 airplanes. This AD requires doing repetitive inspections of the upper arms of the main landing gear (MLG) side braces for missing or inadequately bonded identification plates; doing an ultrasonic inspection of the upper arm of the MLG side brace for any defects and related investigative/ corrective actions if necessary; and replacing the side brace assembly with a modified part. This AD results from an operator who reported experiencing an unlock warning for the MLG on the right side of the airplane. We are issuing this AD to prevent cracking of the upper arms of the side braces of the MLG, which could result in failure of the MLG during landing and possible damage to the airplane and injury to the flightcrew and passengers.
AD 2006-05-08 · published Mar 9, 2006, effective Apr 13, 2006
Boeing Model 777-200 Series Airplanes
The FAA is adopting a new airworthiness directive (AD) for certain Boeing Model 777-200 series airplanes. This AD requires installing a new washer between the lower wing surface and the jam nut of the sump drain valve assembly. This AD results from fuel system reviews conducted by the manufacturer. We are issuing this AD to prevent energy from a lightning strike on the bushing for the sump drain valve from arcing to the inside of the center fuel tank wall, which could create an ignition source in the fuel tank and result in a fuel tank explosion.
AD 2006-05-09 · published Mar 9, 2006, effective Apr 13, 2006
Boeing Model 747-200C, -200F, -400, -400D, and -400F Series Airplanes
The FAA is adopting a new airworthiness directive (AD) for certain Boeing Model 747-200C, -200F, -400, -400D, and -400F series airplanes. This AD requires repetitive inspections for cracks in the overlapping (upper) skin, upper fastener row of the lap joints of the fuselage skin in sections 41, 42, and 46; and related investigative and corrective actions, if necessary. This AD results from fatigue tests and an analysis that identified areas of the fuselage lap joints where fatigue cracks can occur. We are issuing this AD to detect and correct fatigue cracks in the overlapping (upper) skin, upper fastener row of the lap joints of the fuselage skin in sections 41, 42, and 46, which could adversely affect the structural integrity of the airplane.
AD 2006-05-10 · published Mar 9, 2006, effective Apr 13, 2006
BAE Systems (Operations) Limited Model BAe 146 and Model Avro 146-RJ Airplanes
The FAA is adopting a new airworthiness directive (AD) for certain BAE Systems (Operations) Limited Model BAe 146 and Model Avro 146-RJ airplanes. This AD requires a one-time detailed inspection for corrosion of the hinge bracket assembly of the left and right main landing gear (MLG) doors, and corrective action if necessary. This AD results from in-service reports of hinge bracket failures on the MLG doors. We are issuing this AD to prevent failure of the hinge bracket on the MLG door, which could result in separation of the door, consequent structural damage to the airplane, and possible injury to people on the ground.
AD 2006-05-11 · published Mar 10, 2006, effective Mar 27, 2006
Bombardier Inc. Airplanes
The FAA is superseding an existing airworthiness directive (AD) that applies to certain Bombardier Model CL-600-2B19 (Regional Jet Series 100 & 440) airplanes. The existing AD currently requires revising the airworthiness limitations section of the Instructions for Continued Airworthiness of the aircraft maintenance manual (AMM) by incorporating procedures for repetitive functional tests of the pilot input lever of the pitch feel simulator (PFS) units. This AD requires new repetitive functional tests of the pilot input lever of the PFS unit, and corrective actions if necessary. After initiating the new tests, this AD also requires removal of the existing procedures for the repetitive functional tests from the AMM. This AD results from a report that the shear pin located in the input lever of two PFS units failed due to fatigue. We are issuing this AD to prevent undetected failure of the shear pin of both PFS units simultaneously, which could result in loss of pitch feel forcesand consequent reduced control of the airplane. DATES: This AD becomes effective March 27, 2006. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in the AD as of March 27, 2006. On February 13, 2004 (69 FR 4234, January 29, 2004), the Director of the Federal Register approved the incorporation by reference of Bombardier Temporary Revision 2B-1784, dated October 24, 2003, to the CL-600-2B19 Canadair Regional Jet Maintenance Requirements Manual, Part 2, Appendix B, "Airworthiness Limitations.'' We must receive any comments on this AD by May 9, 2006.
AD 2006-01-11 R1 · published Mar 16, 2006, effective Feb 22, 2006
The Cessna Aircraft Company Models 208 and 208B Airplanes
This document clarifies the intent of AD 2006-01-11, which was published in the Federal Register on January 12, 2006 (71 FR 1941). AD 2006-01-11 applies to Cessna Models 208 and 208B airplanes and requires the installation of a pilot assist handle and deicing boots on the cargo pod and landing gear fairings; and the incorporation of changes to the Pilot's Operating Handbook (POH) and FAA-Approved Airplane Flight Manual (AFM). The compliance time for the AFM/POH change currently reads "prior to further flight" after the installation of the pilot assist handle, which is required within 125 days after the effective date. The AFM/POH change is related to operation in ground icing conditions and should not be attributed to the pilot assist handle installation. Therefore, the compliance time should also be within 125 days after the effective date. Additionally, the requirement of installing the accessory kit or installing a placard should only apply to those airplanes equipped with a cargo pod and pneumatic deicing boots. The way it currently is written makes it apply to all airplanes equipped with pneumatic deicing boots. This AD action rewords the compliance time and the wording for the installation or placard requirement to reflect the above concerns.
AD 2006-06-03 · published Mar 16, 2006, effective Apr 20, 2006
Cessna Model 500, 501, 550, S550, 551, and 560 Airplanes
The FAA is adopting a new airworthiness directive (AD) for certain Cessna Model 500, 501, 550, S550, 551, and 560 airplanes. This AD requires revising the airplane flight manual (AFM) to prohibit use of the wing fuel boost pumps for defueling under certain conditions; installing a placard; doing other specified investigative and corrective actions as necessary; and modifying the boost pumps. This AD also requires the subsequent removal of the AFM revision and placard. This AD results from a report of a chafed electrical wiring harness, which was arcing inside the fuel tank. We are issuing this AD to prevent potential fuel vapor ignition in a fuel tank, which could result in explosion and loss of the airplane.
AD 2006-06-04 · published Mar 16, 2006, effective Apr 20, 2006
McDonnell Douglas Model DC-9-10, -20, -30, -40 and -50 Series Airplanes, and Model DC-9-81 (MD-81), and DC-9-82 (MD-82) Airplanes
The FAA is superseding an existing airworthiness directive (AD), which applies to certain McDonnell Douglas Model DC-9-10, -20, - 30, -40 and -50 series airplanes, and Model DC-9-81 (MD-81), and DC-9- 82 (MD-82) airplanes. That AD currently requires installing a water drain system for the slant pressure panels in the left and right wheel wells of the main landing gear (MLG). This new AD also requires inspecting the seal assemblies of the overwing emergency exit doors for defects and constant gap; replacing defective door seals; performing repetitive operational checks of the water drain system auto drain valve and corrective actions if necessary; and, for certain airplanes, modifying the insulation blankets on the slant pressure panels in the left and right MLG wheel wells. This AD results from reports of water runoff from the slant pressure panels in the left and right MLG wheel wells, which subsequently froze on the lateral control mixer and control cable assemblies. We are issuing this AD to prevent ice from forming on the lateral control mixer and control cable assemblies, which could reduce controllability of the airplane.
AD 2006-06-06 · published Mar 16, 2006, effective Mar 24, 2006
The Cessna Aircraft Company Models 208 and 208B Airplanes
The FAA is adopting a new airworthiness directive (AD) to supersede AD 2005-07-01, which applies to all The Cessna Aircraft Company (Cessna) Models 208 and 208B airplanes. AD 2005-07-01 currently requires you to incorporate information into the applicable section of the Airplane Flight Manual (AFM). This AD is the result of several accidents/incidents with the affected airplanes during operations in icing conditions, FAA evaluation of Cessna flight test data, Cessna issuing AFM revisions, and FAA determining these revisions are necessary for safe operation. Consequently, this AD updates the actions of AD 2005-07-01 that require incorporation of text in the AFM and requires the insertion of new text in the AFM, and the fabrication and installation of placards. We are issuing this AD to assure that the pilot has enough information to prevent loss of control of the airplane while in-flight during icing conditions.
AD 2006-06-05 · published Mar 17, 2006, effective Apr 3, 2006
Boeing Model 720 and 720B Series Airplanes
The FAA is adopting a new airworthiness directive (AD) for all Boeing Model 720 and 720B series airplanes. This AD requires repetitive inspections for any crack, corrosion, or sign of damage (e.g., finish scratches, blistering, or signs of fuel leaking) of the front spar upper chords under the fairing web, and repair if necessary. This AD results from a report that inspections required by a previous AD action are inadequate for Boeing Model 720 and 720B series airplanes. We are issuing this AD to detect and correct any crack, corrosion, or sign of damage of the front spar upper chords under the fairing web, which could result in structural failure of the wing.
AD 2006-06-07 · published Mar 22, 2006, effective Apr 26, 2006
Fokker Model F.28 Mark 0070 and 0100 Airplanes
The FAA is adopting a new airworthiness directive (AD) for certain Fokker Model F.28 Mark 0070 and 0100 airplanes. This AD requires inspecting the main landing gear (MLG) main fitting for cracks, and repair if necessary. This AD also requires installing a placard and revising the airplane flight manual to include procedures to prohibit the application of brakes during backward movement of the airplane. This AD results from a report that an MLG main fitting failed on an airplane that was braking while moving backward. We are issuing this AD to detect and correct cracks in the MLG main fitting, which could result in reduced structural integrity of the MLG main fitting.
AD 2006-06-09 · published Mar 22, 2006, effective Apr 26, 2006
Empresa Brasileira de Aeronautica S.A. (EMBRAER) Model ERJ 170 Airplanes
The FAA is adopting a new airworthiness directive (AD) for all EMBRAER Model ERJ 170 airplanes. This AD requires revising the Airworthiness Limitations section (ALS) of the airplane maintenance manual (AMM) to include new, specific maintenance tasks related to the incorporation of a new horizontal stabilizer actuator. This AD also requires revising the ALS of the AMM to include revised repetitive inspection intervals for certain tasks in the maintenance plan related to the aileron and flap/slat flight controls system. This AD results from safety assessments of the aileron and flap/slat flight controls system, conducted after the type certification of the airplane, which showed that some dormant faults did not comply with the safety assessment criteria. We are issuing this AD to prevent failure of the aileron and flap/slat controls system, which could result in reduced controllability of the airplane.
AD 2006-06-10 · published Mar 22, 2006, effective Apr 26, 2006
Boeing Model 747-100, 747-100B, 747-100B SUD, 747-200B, 747-200C, 747-300, 747-400, 747-400D, and 747SR Series Airplanes
The FAA is adopting a new airworthiness directive (AD) for all Boeing Model 747-100, 747-100B, 747-100B SUD, 747-200B, 747-200C, 747- 300, 747-400, 747-400D, and 747SR series airplanes. This AD requires a one-time inspection to determine whether any steel doubler (small or large) is installed at the lower forward and upper aft corners of the fuselage cutout at main entry doors (MEDs) number 3. Depending on the results of this inspection, this AD also requires repetitive inspections for cracks of the skin, bearstrap, and small steel doubler (if installed) at the applicable corner or corners of the fuselage cutouts, and related investigative/corrective actions if necessary. This AD also provides the optional terminating action for the repetitive inspections of installing a large steel doubler at the affected corners. This AD results from reports of cracks in the skin and bearstrap at the upper aft corner and at the lower forward corner of the fuselage cutout at MEDs number 3. We are issuing this AD to detect and correct cracks in the skin, bearstrap, and small steel doubler (if installed), which could propagate and result in rapid decompression of the airplane.
AD 2006-06-11 · published Mar 22, 2006, effective Apr 26, 2006
Boeing Model 747-100B SUD, 747-200B, 747-300, 747-400, and 747-400D Series Airplanes
The FAA is adopting a new airworthiness directive (AD) for all Boeing Model 747-100B SUD, 747-300, 747-400, and 747-400D series airplanes; and Model 747-200B series airplanes having a stretched upper deck. This AD requires repetitively inspecting for cracking or discrepancies of the fasteners in the tension ties, shear webs, and frames at body stations 1120 through 1220, and performing related investigative and corrective actions if necessary. This AD results from new reports of severed tension ties, as well as numerous reports of cracked tension ties, broken fasteners, and cracks in the frame, shear web, and shear ties adjacent to tension ties for the upper deck. We are issuing this AD to detect and correct cracking of the tension ties, shear webs, and frames of the upper deck, which could result in rapid decompression of the airplane.
AD 2006-06-12 · published Mar 27, 2006, effective May 1, 2006
Aerospatiale Model ATR72 Airplanes
The FAA is adopting a new airworthiness directive (AD) for certain Aerospatiale Model ATR72 airplanes. This AD requires a one-time general visual inspection for contamination of the surface of the upper arms of the main landing gear (MLG) secondary side brace assemblies; and repetitive eddy current inspections for cracking of the upper arms, and related specified and corrective actions if necessary. This AD also mandates eventual replacement of aluminum upper arms with steel upper arms, which would end the repetitive inspections. This AD results from two reports of rupture of the upper arm of the MLG secondary side brace due to fatigue cracking. We are issuing this AD to prevent cracking of the upper arms of the secondary side brace assemblies of the MLG, which could result in collapse of the MLG during takeoff or landing, damage to the airplane, and possible injury to the flightcrew and passengers.
AD 2006-06-13 · published Mar 27, 2006, effective May 1, 2006
Airbus Model A330-200 and -300 Series Airplanes; and Model A340-200 and -300 Series Airplanes
The FAA is adopting a new airworthiness directive (AD) for certain Airbus Model A330-200 and A330-300 series airplanes; and Model A340-200 and -300 series airplanes. This AD requires repetitive detailed inspections for discrepancies of the inboard and outboard actuator fittings of the aileron servo controls, corrective actions if necessary, and eventual replacement of all the attachment bolts of the aileron servo controls. This AD results from several cases of bushing migration on the inboard and outboard actuator fittings of the aileron servo controls; in one case the bushing had migrated completely out of the actuator fitting and the fitting was cracked. We are issuing this AD to prevent rupture of the inboard and outboard actuator fittings of the aileron servo controls, which could result in airframe vibration and consequent reduced structural integrity of the airplane.
AD 2006-06-14 · published Mar 27, 2006, effective May 1, 2006
Airbus Model A318-100 and A319-100 Series Airplanes, A320-111 Airplanes, A320-200 Series Airplanes, and A321-100 and A321-200 Series Airplanes
The FAA is adopting a new airworthiness directive (AD) for certain Airbus Model A318-100 and A319-100 series airplanes, A320-111 airplanes, A320-200 series airplanes, and A321-100 and A321-200 series airplanes. This AD requires operators to review the airplane's maintenance records to determine the part numbers of the magnetic fuel level indicators (MFLI) of the wing fuel tanks, and related investigative and corrective actions if necessary. This AD results from several in-service incidents of wear and detachment of the top-stops from the MFLI. Such detachment allows the top-stop to move around the wing fuel tank, and the top-stop could come into contact or in close proximity with a gauging probe, resulting in compromise of the air gap between the probe and the structure and creating a potential ignition source. We are issuing this AD to prevent an ignition source in the wing fuel tank in the event of a lightning strike, which could result in a fire or explosion.
AD 2006-06-15 · published Mar 27, 2006, effective May 1, 2006
Airbus Model A318-100 Series Airplanes; Model A319-100 Series Airplanes; Model A320-111 Airplanes; Model A320-200 Series Airplanes; Model A321-100 Series Airplanes; and Model A321-200 Series Airplanes
The FAA is adopting a new airworthiness directive (AD) for certain Airbus Model A318-100 series airplanes; Model A319-100 series airplanes; Model A320-111 airplanes; Model A320-200 series airplanes; Model A321-100 series airplanes; and Model A321-200 series airplanes. This AD requires replacing the water drain valves in the forward and aft cargo doors with new valves. This AD results from a report indicating that, during a test of the fire extinguishing system, air leakage through the water drain valves in the forward and aft cargo doors reduced the concentration of fire extinguishing agent to below the level required to suppress a fire. We are issuing this AD to prevent air leakage through the water drain valves, which, in the event of a fire in the forward or aft cargo compartment, could result in an insufficient concentration of fire extinguishing agent and consequent inability of the fire extinguishing system to suppress the fire.
AD 2006-07-01 · published Mar 27, 2006, effective May 1, 2006
Empresa Brasileira de Aeronautica S.A. (EMBRAER) Model EMB-135 Airplanes and Model EMB-145, -145ER, -145MR, -145LR, -145XR, -145MP, and -145EP Airplanes
The FAA is adopting a new airworthiness directive (AD) for certain EMBRAER Model EMB-135 airplanes and Model EMB-145, -145ER, - 145MR, -145LR, -145XR, -145MP, and -145EP airplanes. This AD requires replacing the horizontal stabilizer control unit (HSCU) with a modified and reidentified or new, improved HSCU. For certain airplanes, this AD also requires related concurrent actions as necessary. This AD is prompted by reports of loss of the pitch trim system due to a simultaneous failure of both channels of the HSCU. We are issuing this AD to prevent loss of pitch trim and reduced controllability of the airplane.
AD 2006-05-11 R1 · published Mar 28, 2006, effective Mar 27, 2006
Bombardier Model CL-600-2B19 (Regional Jet Series 100 & 440) Airplanes
The FAA is revising an existing airworthiness directive (AD), which applies to certain Bombardier Model CL-600-2B19 (Regional Jet Series 100 & 440) airplanes. The existing AD currently requires revising the airworthiness limitations section of the Instructions for Continued Airworthiness of the maintenance requirements manual (MRM) by incorporating procedures for repetitive functional tests of the pilot input lever of the pitch feel simulator (PFS) units. That AD also requires new repetitive functional tests of the pilot input lever of the PFS unit, and corrective actions if necessary; and after initiating the new tests, requires removal of the existing procedures for the repetitive functional tests from the MRM. This AD retains the requirements of the existing AD and further clarifies the requirements of the AD. This AD results from a report that the shear pin located in the input lever of two PFS units failed due to fatigue. We are issuing this AD to prevent undetected failure of the shear pin of both PFS units simultaneously, which could result in loss of pitch feel forces and consequent reduced control of the airplane.
AD 2006-07-02 · published Mar 30, 2006, effective May 4, 2006
Bombardier Model DHC-8-301, -311, and -315 Airplanes
The FAA is adopting a new airworthiness directive (AD) for certain Bombardier Model DHC-8-301, -311, and -315 airplanes. This AD requires replacing the pressure control valve of the Type 1 emergency door. This AD results from reports that the pressure control valve of the Type 1 emergency door is susceptible to freezing. We are issuing this AD to ensure that the pressure control valve does not freeze and prevent the door seal from deflating, which could result in the inability to open the door in an emergency.
AD 2006-07-03 · published Mar 30, 2006, effective May 4, 2006
Airbus Model A321-100 and -200 Series Airplanes
The FAA is adopting a new airworthiness directive (AD) for certain Airbus Model A321-100 and -200 series airplanes. This AD requires replacing the crashworthiness pins on the side-stay of the main landing gear (MLG) with new pins having an increased internal notch diameter. This AD results from testing on the side-stay crashworthiness pins on the MLG, which revealed that, in the case of an emergency landing, the crashworthiness pins installed will not ensure a correct MLG collapse. We are issuing this AD to prevent a punctured fuel tank, which could cause damage to the airplane or injury to passengers.
AD 2006-07-04 · published Mar 30, 2006, effective May 4, 2006
Boeing Model 737-600, -700, -700C, -800, and -900 Series Airplanes
The FAA is adopting a new airworthiness directive (AD) for certain Boeing Model 737-600, -700, -700C, -800, and -900 series airplanes. This AD requires repetitive general visual inspections for dirt, debris, and drain blockage and cleaning of the aft fairing cavities of the engine struts; and modification of the aft fairings, which terminates the repetitive general visual inspections. This AD results from a report indicating that water had accumulated in the cavities of the engine strut aft fairings. We are issuing this AD to prevent drain blockage by debris that, when combined with leaking, flammable fluid lines passing through the engine strut aft fairing, could allow flammable fluids to build up in the cavity of the aft fairing, and consequently could be ignited by the engine exhaust nozzle located below the engine strut, resulting in an explosion or uncontrolled fire.
AD 2006-07-05 · published Mar 30, 2006, effective May 4, 2006
Airbus Model A319-131, -132, and -133; A320-232 and -233; and A321-131, -231, and -232 Airplanes
The FAA is adopting a new airworthiness directive (AD) for certain Airbus Model A319-131, -132, and -133; A320-232 and -233; and A321-131, -231, and -232 airplanes. This AD requires inspecting for cracks or failure of the primary load path components of the engine forward mount, and corrective action if necessary. This AD also requires removing, re-installing, and re-torquing the attachment bolts for the secondary load path. This AD results from a report that, during modification of certain engine forward mount assemblies of the left and right engines done at an engine shop visit, an incorrect torque was applied to the attachment bolts. We are issuing this AD to prevent structural failure of the secondary load path of the forward engine mount, which, if combined with failure of the primary load path, could result in separation of the engine from the airplane.
AD 2006-07-06 · published Mar 30, 2006, effective May 11, 2006
Cirrus Design Corporation Models SR20 and SR22 Airplanes
The FAA adopts a new airworthiness directive (AD) for certain Cirrus Design Corporation (CDC) Models SR20 and SR22 airplanes. This AD requires you to inspect the fuel line and wire bundles for any chafing damage; replace any damaged fuel line and repair any damaged wires or sheathing of the wire harness if any chafing damage is found; and install (to prevent any chafing damage to the fuel line and wire bundles) the forward loop clamp, fuel line shield, aft loop clamp, and anti-chafe tubing. This AD results from reports of fuel line leaks resulting from wire chafing on the fuel lines. We are issuing this AD to detect, correct, and prevent damage to the fuel line and wire bundles, which could result in fuel leaks. This failure could lead to unsafe fuel vapor within the cockpit and possible fire.
AD 2006-07-13 · published Mar 30, 2006, effective Mar 30, 2006
Airbus Model A310 Airplanes, Model A300 B4-600 Series Airplanes, Model A300 B4-600R Series Airplanes, Model A300 F4-600R Series Airplanes, and Model A300 C4-605R Variant F Airplanes
The FAA is adopting a new airworthiness directive (AD) for certain Airbus Model A310 airplanes, Model A300 B4-600 series airplanes, Model A300 B4-600R series airplanes, Model A300 F4-600R series airplanes, and Model A300 C4-605R Variant F airplanes. This AD requires inspections of the rudder for discrepancies and corrective action if necessary. This AD also requires reporting all inspection results to the airplane manufacturer and the FAA. This AD results from two separate findings of inner skin disbonding discovered while undergoing unrelated repair and maintenance procedures. We are issuing this AD to detect discrepancies of the rudder, which could result in reduced structural integrity of the rudder.
AD 2006-07-07 · published Mar 31, 2006, effective Apr 17, 2006
Airbus Model A300 B4-600, B4-600R, and F4-600R Series Airplanes, and Model C4-605R Variant F Airplanes (Collectively Called A300-600 Series Airplanes)
The FAA is adopting a new airworthiness directive (AD) for certain Airbus Model A300-600 series airplanes. This AD requires modifying nine bolt holes in the vertical flange to prevent cracking before the inspection threshold of AD 98-18-02. This AD results from reports of cracking in the vertical web of the center spar sealing angles of the wing earlier than the inspection interval specified in the existing AD. We are issuing this AD to prevent crack formation in the sealing angles; such cracks could rupture the sealing angle and lead to subsequent crack formation in the bottom skin of the wing, and resultant reduced structural integrity of the center spar section of the wing.
AD 2006-07-08 · published Mar 31, 2006, effective May 5, 2006
McDonnell Douglas Model DC-9-10, DC-9-20, DC-9-30, DC-9-40, and DC-9-50 Series Airplanes
The FAA is adopting a new airworthiness directive (AD) for certain McDonnell Douglas Model DC-9-10, DC-9-20, DC-9-30, DC-9-40, and DC-9-50 series airplanes. This AD requires repetitive inspections for stress corrosion cracks of the main fuselage frame, and corrective actions if necessary. This AD also provides an optional terminating action for the repetitive inspections. This AD results from several reports of cracking of the main fuselage frame. We are issuing this AD to detect and correct stress corrosion cracking of the main fuselage frame, which could result in extensive damage to adjacent structure and reduced structural integrity of the airplane.
AD 2006-07-09 · published Mar 31, 2006, effective May 5, 2006
Airbus Model A318-100 and A319-100 Series Airplanes; Model A320-111 Airplanes; and Model A320-200, A321-100, and A321-200 Series Airplanes
The FAA is adopting a new airworthiness directive (AD) for all Airbus Model A318-100 and A319-100 series airplanes; Model A320-111 airplanes; and Model A320-200, A321-100, and A321-200 series airplanes. This AD requires repetitive detailed inspections of the trimmable horizontal stabilizer actuator (THSA) attachments for proper clearances, and any crack, damage, or metallic particles; related corrective actions if necessary; and a report of the inspection results to the manufacturer. This AD results from a report that during lab testing to verify the performance of the THSA's secondary load path with a simulated failure of the THSA's primary load path, the secondary load path's nut did not jam (as it was supposed to do). We are issuing this AD to ensure the integrity of the THSA's primary load path, which if failed, could result in latent (undetected) loading and eventual failure of the THSA's secondary load path and consequent uncontrolled movement of the horizontal stabilizer and loss of control of the airplane.
AD 2006-07-11 · published Mar 31, 2006, effective May 5, 2006
McDonnell Douglas Model DC-9-81 (MD-81), DC-9-82 (MD-82), DC-9-83 (MD-83), DC-9-87 (MD-87), MD-88, and MD-90-30 Airplanes
The FAA is adopting a new airworthiness directive (AD) for all McDonnell Douglas airplanes identified above. This AD requires a one- time inspection of the aft attach fitting assembly of the spoiler link to determine the part number, and further investigative action and replacement of the assembly with a new or serviceable assembly, if necessary. This AD results from a determination that the holes of certain aft attach fitting assemblies of the spoiler link were not cold-worked during production. We are issuing this AD to prevent fatigue cracking of the aft attach fitting of the spoiler link and consequent failure of the fitting. Failure of the fitting could result in an asymmetrical lift condition and consequent reduced controllability of the airplane.
AD 2006-07-12 · published Mar 31, 2006, effective May 5, 2006
Boeing Model 737-100, -200, -200C, -300, -400, and -500 Series Airplanes
The FAA is adopting a new airworthiness directive (AD) for all Boeing Model 737-100, -200, -200C, -300, -400, and -500 series airplanes. This AD requires a one-time inspection for scribe lines and cracks in the fuselage skin at certain lap joints, butt joints, external repair doublers, and other areas; and related investigative/ corrective actions if necessary. This AD results from reports of fuselage skin cracks adjacent to the skin lap joints on airplanes that had scribe lines. Scribe line damage can also occur at many other locations, including butt joints, external doublers, door scuff plates, the wing-to-body fairing, and areas of the fuselage where decals have been applied or removed. We are issuing this AD to prevent rapid decompression of the airplane due to fatigue cracks resulting from scribe lines on pressurized fuselage structure.
AD 2006-06-02 · published Mar 13, 2006, effective Apr 17, 2006
Eurocopter France Model SA-365N, SA-365N1, AS-365N2, and SA-366G1 Helicopters
This amendment supersedes an existing airworthiness directive (AD) that currently applies to Eurocopter France (ECF) Model SA 365N, N1, and AS 365N2 helicopters. That AD currently requires inspecting the main gearbox (MGB) suspension diagonal cross-member (diagonal cross-member) for cracks and replacing it with an airworthy part if any crack is found. This amendment requires more frequent inspections of the diagonal cross-member and adding the Model SA-366G1 helicopters to the applicability. This amendment is prompted by several reports of cracks in the diagonal cross-member. The actions specified by this AD are intended to prevent failure of the diagonal cross-member, pivoting of the MGB, severe vibrations, and a subsequent forced landing.
AD 2006-06-01 · published Mar 14, 2006, effective Apr 18, 2006
Eurocopter France Model EC 155B and B1 Helicopters
This amendment adopts a new airworthiness directive (AD) for the specified Eurocopter France (ECF) model helicopters that requires inspecting an electrical cable bundle for wear. If wear is present, the AD requires installing an airworthy cable bundle and modifying the routing of the electrical cable bundles. This amendment is prompted by reports of a short circuit in the wiring, which led to failure of the normal and emergency landing gear operation modes. The actions specified by this AD are intended to prevent interference of the wiring with the structure resulting in an electrical short circuit, failure of the landing gear to extend, and an emergency landing.
AD 2006-05-01 · published Mar 1, 2006, effective Mar 16, 2006
Rolls-Royce plc RB211 Trent 500, 700 and 800 Series Turbofan Engines
The FAA is adopting a new airworthiness directive (AD) for Rolls-Royce plc (RR) RB211 Trent 500, 700, and 800 series turbofan engines. This AD requires inspecting all engines to determine those that are equipped with a suspect oil filler cap assembly. This AD also requires, within seven days of the effective date of this AD, an initial and repetitive check of oil cap security following oil servicing of multiple-engine airplanes having more than one suspect oil filler cap assembly installed. Finally, this AD requires replacing affected oil filler cap assemblies. This AD results from four in- service oil loss events since March 2005, following failures to properly install the oil tank filler cap after oil servicing. We are issuing this AD to prevent oil loss that could result in multiple engine in-flight shutdowns during a flight.
AD 2006-05-04 · published Mar 3, 2006, effective Apr 7, 2006
General Electric Company CF34 Series Turbofan Engines
The FAA is superseding an existing airworthiness directive (AD) for General Electric Company (GE) CF34-1A, -3A, -3A1, -3A2, -3B, and -3B1 turbofan engines. That AD currently requires a onetime inspection, and if necessary replacing certain fan disks for electrical arc-out indications. That AD also reduces the life limit of certain fan disks. This AD requires the same actions and adds one disk part number (P/N) and serial number (SN) to the affected fan disks. This AD results from an error in the first part number and serial number listed in Table 1 of the original AD. We are issuing this AD to prevent rupture of the fan disk due to cracks that initiate at an electrical arc-out, which could result in an uncontained failure of the engine.
AD 2006-05-03 · published Mar 6, 2006, effective Mar 27, 2006
Rolls-Royce plc Models RB211 Trent 768-60, Trent 772-60, and Trent 772B-60 Turbofan Engines
The FAA is adopting a new airworthiness directive (AD) for Rolls-Royce plc (RR) models RB211 Trent 768-60, Trent 772-60, and Trent 772B-60 turbofan engines. This AD requires initial and repetitive borescope inspections of the high pressure-intermediate pressure (HP- IP) turbine bearing internal oil vent tube, scavenge tube, and tube heat shields for wear and cracking, and removing tubes from service if found with any cracks beyond serviceable limits. This AD also requires installation of a new or modified HP-IP turbine bearings support as terminating action for the repetitive borescope inspections. This AD results from two reports of RR RB211 Trent 700 series engines found with the HP-IP internal oil vent tube and scavenge tube fretted by damaged heat shields on the tubes. We are issuing this AD to prevent oil ejecting from the HP-IP turbine bearings chamber and igniting. Burning oil can cause the intermediate pressure (IP) shaft to fracture, the IP turbine to overspeed, and possible uncontained failure of the engine.
AD 2006-06-08 · published Mar 21, 2006, effective Apr 25, 2006
General Electric Company Model CF6-80C2D1F Turbofan Engines
The FAA is adopting a new airworthiness directive (AD) for General Electric Company (GE) Model CF6-80C2D1F turbofan engines. This AD requires modifying the latching system of the fan reverser. This AD results from 13 reports of released thrust reverser hardware. We are issuing this AD to prevent release of the thrust reverser cascade on landing, which could result in runway debris and a possible hazard to other aircraft.
AD 2006-06-16 · published Mar 23, 2006, effective Apr 27, 2006
Lycoming Engines (Formerly Textron Lycoming) AEIO-360, IO-360, O-360, LIO-360, and LO-360 Series Reciprocating Engines
The FAA is adopting a new airworthiness directive (AD) for certain Lycoming Engines (formerly Textron Lycoming) AEIO-360, IO-360, O-360, LIO-360, and LO-360 series reciprocating engines. This AD requires replacing certain crankshafts. This AD results from a crankshaft failure in a Lycoming LO-360-A1H6 reciprocating engine. We are issuing this AD to prevent failure of the crankshaft, which could result in total engine power loss, in-flight engine failure, and possible loss of the aircraft.
AD 2006-06-17 · published Mar 23, 2006, effective Apr 27, 2006
Turbomeca Arriel 1B, 1D, and 1D1 Turboshaft Engines
The FAA is adopting a new airworthiness directive (AD) for Turbomeca Arriel 1B, 1D, and 1D1 turboshaft engines. This AD requires inspecting the 2nd stage nozzle guide vanes (NGV2) for wall thickness. This AD results from one instance of a fractured 2nd stage turbine blade followed by an uncommanded engine shutdown. We are issuing this AD to detect and prevent perforation of the NGV2 that could cause fracture of a turbine blade that could result in an uncommanded engine in-flight shutdown on a single-engine helicopter.
AD 2006-05-05 · published Mar 6, 2006, effective Apr 10, 2006
MT-Propeller Entwicklung GmbH Propellers
The FAA is adopting a new airworthiness directive (AD) for certain MT-Propeller Entwicklung GmbH variable pitch and fixed pitch propellers with serial numbers (SNs) below 95000, which have not been overhauled since April 1994. This AD requires overhauling the propeller blades of these propellers within 30 days after the effective date of the AD. This AD also requires performing initial and repetitive visual inspections of affected propeller blades. This AD also requires removing all propeller blades from service with damaged erosion sheath bonding or loose erosion sheaths and installing any missing or damaged polyurethane protective strips. This AD results from reports of stainless steel leading edge erosion sheaths separating from propeller blades and reports of propeller blades with damaged or missing polyurethane protective strips (PU-protection tape) due to insufficient inspection procedures in older MT-Propeller Entwicklung GmbH Operation & Installation Manuals. We are issuing this AD to prevent erosion sheath separation leading to damage of the airplane.
