30 Airworthiness Directives: 24 airplane, 2 rotorcraft, 2 engine, 2 propeller.
AD 2006-13-18 · published Jul 5, 2006, effective Aug 9, 2006
McDonnell Douglas Model DC-9-31, DC-9-32, DC-9-32F, DC-9-33F, DC-9-34, and DC-9-34F Airplanes; and Model DC-9-40 and DC-9-50 Series Airplanes
The FAA is adopting a new airworthiness directive (AD) for certain transport category airplanes, identified above. This AD requires installing a bonding jumper from the boost pump volute to the fuel tank structure, and related investigative/corrective actions. This AD results from fuel system reviews conducted by the manufacturer. We are issuing this AD to prevent point-contact arcing or filament heating in the fuel tank, which, in the event of a short or ground fault inside the fuel tank, could result in a fuel tank explosion and consequent loss of the airplane.
AD 2006-14-01 · published Jul 5, 2006, effective Aug 9, 2006
Airbus Model A330-200, A330-300, A340-200, and A340-300 Series Airplanes, and Model A340-541 and A340-642 Airplanes
The FAA is adopting a new airworthiness directive (AD) for certain Airbus Model A330-200, A330-300, A340-200, and A340-300 series airplanes, and Model A340-541 and A340-642 airplanes. This AD requires inspecting to determine if certain emergency escape slides/slide rafts (referred to as slide/rafts) are installed in certain crew/passenger doors; and, if so, performing a one-time inspection to determine if the electrical harnesses of the slide/rafts are properly routed, and rerouting the harnesses if necessary. This AD results from report that a slide/raft failed to deploy properly during a deployment test. We are issuing this AD to detect and correct improper routing of the electrical harnesses of certain slide/rafts, which could prevent proper deployment of the slide/rafts and delay evacuation of passengers and flightcrew during an emergency.
AD 2006-14-02 · published Jul 5, 2006, effective Aug 9, 2006
Airbus Model A330-200 and A330-300 Series Airplanes, and Airbus Model A340-200 and A340-300 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A330-200 and A330-300 series airplanes; and Airbus Model A340-200 and A340-300 series airplanes. This AD requires lubrication of the upper and lower shortening mechanism (SM) link of the main landing gear, and consequent detection of resistance or blockage of the greaseway. Depending upon the resistance finding and upon whether or not the airplane has a certain modification, this AD also requires various other actions including unblocking the greaseway; accomplishing all necessary repairs; performing various inspections; and accomplishing the eventual replacement of the SM8 pin, if necessary. This action is necessary to prevent failure of the landing gear lengthening system, which could result in reduced controllability of the airplane on the ground during landing. This action is intended to address the identified unsafe condition.
AD 2006-14-06 · published Jul 7, 2006, effective Aug 11, 2006
Airbus 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 A300 F4-600R series airplanes and Model A300 C4- 605R Variant F airplanes. This AD requires modifying certain structure in the fuselage zone at the lavatory venturi installation in the nose section, and performing a related investigative action and corrective action if necessary. This AD results from an analysis that revealed that airplanes equipped with Airbus Modification 08909 had a concentration of loads higher than expected in the fuselage zone (high stress) at the lavatory venturi installation in the nose section, which could be the origin of cracks that developed in the fuselage skin and propagated from the edge of the air vent hole. We are issuing this AD to prevent fatigue cracking of the fuselage skin, which could result in loss of the structural integrity of the fuselage and consequent rapid depressurization of the airplane.
AD 2006-14-05 · published Jul 11, 2006, effective Aug 15, 2006
Bombardier Model CL-600-2C10 (Regional Jet Series 700, 701, and 702) Airplanes, Model CL-600-2D15 (Regional Jet Series 705) Airplanes, and Model CL-600-2D24 (Regional Jet Series 900) Airplanes
The FAA is superseding an existing airworthiness directive (AD), which applies to certain Bombardier Model CL-600-2C10 (Regional Jet Series 700 and 701) and CL-600-2D24 (Regional Jet Series 900) series airplanes. That AD currently requires repetitive detailed inspections for cracking or deformation, or pulled or missing fasteners, on the lower panel of the left- and right-hand main landing gear (MLG) doors, as applicable, and corrective actions if necessary. This new AD reduces the repetitive inspection interval for certain airplanes. This new AD also adds airplanes to the applicability. This AD results from a report of a MLG door departing from an airplane. We are issuing this AD to prevent failure of the lower panel of the MLG door, departure of the lower panel from the airplane, and consequent damage to airplane structure, which could adversely affect the airplane's continued safe flight and landing.
AD 2006-13-17 · published Jul 13, 2006, effective Jul 13, 2006
Boeing Model 757-200 Series Airplanes Modified by Supplemental Type Certificate (STC) SA979NE
The FAA is correcting a typographical error in an existing airworthiness directive (AD) that was published in the Federal Register on June 28, 2006 (71 FR 36671). The error resulted in the misidentification of the manufacturer name in the product identification line of the regulatory text. This AD applies to certain Boeing Model 757-200 series airplanes. This AD requires a one-time deactivation of the auxiliary fuel system, repetitive venting and draining of the auxiliary fuel tank sumps, and revising the Limitations section of the airplane flight manual to limit the maximum cargo weight.
AD 2006-14-07 · published Jul 17, 2006, effective Aug 21, 2006
Boeing Model 737-100, -200, and -200C Series Airplanes
The FAA is superseding an existing airworthiness directive (AD), which applies to certain Boeing Model 737 series airplanes. That AD currently requires inspection of the elevator tab inboard hinge support structure to detect fatigue cracking and corrective action if necessary. That AD also provides an optional terminating action. This new AD adds airplanes to the applicability and requires new repetitive inspections. For airplanes having elevators with laminated rear spars, this new AD requires repetitive inspections for interlaminar corrosion, delamination, or disbonding in the rear spar, repetitive inspections for cracking in the spar web, and repair including related investigative/corrective actions if necessary. For airplanes having elevators with solid rear spars, this new AD requires repetitive inspections for cracking in the spar web and repair including related investigative/corrective actions if necessary. This AD results from reports of cracks in the elevator rear spar web at the tab hinge bracket locations. We are issuing this AD to detect and correct cracking, corrosion, interlaminar corrosion, delamination, and disbonding in the elevator rear spar, which may reduce elevator stiffness and lead to in-flight vibration. In-flight vibration may lead to elevator and horizontal stabilizer damage and reduced controllability of the airplane.
AD 2006-14-08 · published Jul 17, 2006, effective Aug 21, 2006
Mitsubishi Heavy Industries MU-2B Series Airplanes
The FAA adopts a new airworthiness directive (AD) for some Mitsubishi Heavy Industries (MHI) MU-2B series airplanes. This AD requires you to verify that the current flight idle blade angles are set at 12 degrees. If not already set at that angle, set the flight idle blade angles to 12 degrees. This AD results from a recent safety evaluation that used a data-driven approach to analyze the design, operation, and maintenance of the MU-2B series airplanes in order to determine their safety and define what steps, if any, are necessary for their safe operation. Part of that evaluation was the identification of unsafe conditions that exist or could develop on the affected type design airplanes. We are issuing this AD to prevent incorrect flight idle blade angle settings. This unsafe condition, if not corrected, could lead to an asymmetric thrust situation in certain flight conditions, which could result in airplane controllability problems.
AD 2006-14-09 · published Jul 17, 2006, effective Aug 21, 2006
Airbus Model A330-200 and -300, and A340-200 and -300 Series Airplanes
The FAA is adopting a new airworthiness directive (AD) for certain Airbus Model A330-200 and -300, and A340-200 and -300 series airplanes. This AD requires modifying certain rotary actuator assemblies for the leading edge slat. This AD results from a leak found at the seal of the torque limiter output shaft of the Type A rotary actuator of leading edge slat No. 1. We are issuing this AD to prevent a decrease in the torque limiter function, which could result in degradation and damage to the attachment bolts of the leading edge slat, loss of the slat, and consequent reduced control of the airplane.
AD 2006-15-01 · published Jul 17, 2006, effective Aug 21, 2006
Twin Commander Aircraft Corporation Models 690, 690A, and 690B Airplanes
We are adopting a new airworthiness directive (AD) for all Twin Commander Aircraft Corporation (Twin Commander) Models 690, 690A, and 690B airplanes. This AD requires you to inspect, visually and using fluorescent dye penetrant, the support structures for the inboard and center aileron hinge fittings on both wings for cracks and replace any cracked support structure. This AD requires you to reinforce the support structures for the inboard and center aileron hinge fittings on both wings. This AD results from reports that cracks were found in the support structures for the inboard and center aileron hinge fittings on both wings. We are issuing this AD to detect and correct cracks in the support structures for the inboard and center aileron hinge fittings on both wings, which could result in aileron failure. This failure could lead to reduced controllability or loss of control of the airplane.
AD 2006-15-02 · published Jul 19, 2006, effective Aug 23, 2006
Pilatus Aircraft Ltd. Models PC-6, PC-6-H1, PC-6-H2, PC-6/350, PC-6/350-H1, PC-6/350-H2, PC-6/A, PC-6/A-H1, PC-6/A-H2, PC-6/B-H2, PC-6/B1-H2, PC-6/B2-H2, PC-6/B2-H4, PC-6/C-H2, and PC-6/C1-H2 Airplanes
We are adopting a new airworthiness directive (AD) that supersedes AD 2003-09-01, which applies to certain Pilatus Aircraft Ltd (Pilatus) Model PC-6 airplanes. AD 2003-09-01 currently requires you to inspect and correct, as necessary, the aileron control bellcrank assemblies at the wing and fuselage locations. Since we issued AD 2003- 09-01, the FAA determined the action should also apply to all the models of the PC-6 airplanes listed in the type certificate data sheet of Type Certificate (TC) No. 7A15 that were produced in the United States through a licensing agreement between Pilatus and Fairchild Republic Company (also identified as Fairchild Industries, Fairchild Heli Porter, or Fairchild-Hiller Corporation). In addition, the intent of the applicability of AD 2003-09-01 was to apply to all the affected serial numbers of the airplane models listed in TC No. 7A15. This AD retains all the actions of AD 2003-09-01, adds those Fairchild Republic Company airplanes to the applicability of this AD, and lists the individual specific airplane models. We are issuing this AD to detect and correct increased friction in the aileron control bellcrank assemblies, which could result in failure of the aileron flight-control system. Such failure could lead to problems in controlling flight.
AD 2006-15-03 · published Jul 19, 2006, effective Aug 23, 2006
Pilatus Aircraft Ltd. Models PC-6, PC-6-H1, PC-6-H2, PC-6/350, PC-6/350-H1, PC-6/350-H2, PC-6/A, PC-6/A-H1, PC-6/A-H2, PC-6/B-H2, PC-6/B1-H2, PC-6/B2-H2, PC-6/B2-H4, PC-6/C-H2, and PC-6/C1-H2 Airplanes
We are adopting a new airworthiness directive (AD) that supersedes AD 2003-13-04, which applies to certain Pilatus Aircraft Ltd (Pilatus) Model PC-6 airplanes. AD 2003-13-04 currently requires you to inspect the integral fuel tank wing ribs for cracks and the top and bottom wing skins for distortion, repair any cracks or distortion before further flight, and do a fuel tank ventilating system installation. Since we issued AD 2003-13-04, the FAA determined the action should also apply to all the models of the PC-6 airplanes listed in the type certificate data sheet of Type Certificate (TC) No. 7A15 that were produced in the United States through a licensing agreement between Pilatus and Fairchild Republic Company (also identified as Fairchild Industries, Fairchild Heli Porter, or Fairchild-Hiller Corporation). In addition, the intent of the applicability of AD 2003- 13-04 was to apply to all the affected serial numbers of the airplane models listed in TC No. 7A15. This AD retains all the actions of AD 2003-13-04, adds those Fairchild Republic Company airplanes to the applicability of this AD, and lists the individual specific airplane models. We are issuing this AD to detect and correct cracks in the ribs of the inboard integral fuel tanks in the left and right wings, which could lead to wing failure during flight with consequent loss of control of the airplane.
AD 2006-15-04 · published Jul 20, 2006, effective Aug 24, 2006
Airbus Model A300 B2 and B4 Series Airplanes; and Model A300 B4-600, B4-600R, and F4-600R Series Airplanes, and Model C4-605R Variant F Airplanes (Collectively Called A300-600 Series Airplanes)
The FAA is superseding two existing airworthiness directives (AD) that apply to certain Airbus Model A300 B2, A300 B4, and A300-600 series airplanes. One AD currently requires an inspection for cracks of the lower outboard flange of gantry No. 4 in the main landing gear (MLG) bay area, and repair if necessary. The other AD currently requires, among other actions, repetitive inspections of the gantry lower flanges, and repair if necessary. This new AD requires new repetitive inspections for cracks in the lower flange of certain gantries, and repair if necessary, which ends the existing inspection requirements. This new AD also provides for optional terminating actions for the new repetitive inspections. This AD results from a report of a large fatigue crack along the outboard flange of beam No. 4 and a subsequent determination that existing inspections are inadequate. We are issuing this AD to detect and correct fatigue cracks in the lower flanges of gantries 1 through 5 inclusive in the MLG bay area, which could result in reduced structural integrity of the fuselage, and consequent rapid decompression of the airplane.
AD 2006-15-05 · published Jul 20, 2006, effective Aug 24, 2006
Boeing Model 737-200, -300, and -400 Series Airplanes
The FAA is adopting a new airworthiness directive (AD) for certain Boeing Model 737-200, -300, and -400 series airplanes. This AD requires replacing the existing fueling float switch in the auxiliary fuel tank with a new, improved fueling float switch, installing a new liner system inside the float switch conduit, and performing related investigative and other specified actions. This AD results from reports of chafing of the direct-current-powered float switch wiring insulation in the center fuel tank. We are issuing this AD to prevent contamination of the fueling float switch of the auxiliary fuel tank by moisture or fuel, and chafing of the float switch wiring against the float switch conduit in the fuel tank, which could present an ignition source inside the fuel tank that could cause a fire or explosion.
AD 2006-15-06 · published Jul 20, 2006, effective Aug 24, 2006
Airbus Model A300 B2-203 and A300 B4-203 Airplanes; Model A300 B4-600, B4-600R, and F4-600R Series Airplanes, and Model C4-605R Variant F Airplanes (Collectively Called A300-600 Series Airplanes); and Model A310-200 and -300 Series Airplanes
The FAA is superseding an existing airworthiness directive (AD), which applies to certain Airbus Model A300 series airplanes and all Model A300-600 and A310 series airplanes. That AD currently requires repetitive inspections of the pitch trim system to detect continuity defects in the autotrim function, and follow-on corrective actions if necessary. For certain airplanes, this new AD requires replacing the flight augmentation computers (FACs) with new improved FACs. This AD also revises the applicability of the existing AD. This AD results from the development of a final action intended to address the unsafe condition. We are issuing this AD to prevent a sudden change in pitch due to an out-of-trim condition combined with an autopilot disconnect, which could result in reduced controllability of the airplane.
AD 2006-15-07 · published Jul 20, 2006, effective Aug 24, 2006
Mitsubishi Heavy Industries, Ltd. MU-2B Series Airplanes
We are adopting a new airworthiness directive (AD) for certain Mitsubishi Heavy Industries, Ltd. (MHI) MU-2B series airplanes. This AD requires you to incorporate text from the service information into the Limitations Section of the FAA-approved Airplane Flight Manual (AFM). This AD results from a recent safety evaluation that used a data-driven approach to analyze the design, operation, and maintenance of the MU-2B series airplanes in order to determine their safety and define what steps, if any, are necessary for their safe operation. Part of that evaluation was the identification of unsafe conditions that exist or could develop on the affected type design airplanes. Field reports indicate an unsafe condition of improper rigging and/or adjustment of the propeller feathering linkage. Service centers found the unsafe condition during inspections. We are issuing this AD to detect and correct improper rigging of the propeller feathering linkage. The above issue, if uncorrected, could result in degraded performance and poor handling qualities with consequent loss of control of the airplane.
AD 2006-15-09 · published Jul 25, 2006, effective Aug 29, 2006
Airbus Model A300 Airplanes; Model A310 Airplanes; and 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 all Airbus Model A300 airplanes and Model A310 airplanes, and for certain Airbus Model A300-600 series airplanes. This AD requires an inspection of the wing and center fuel tanks to determine if certain P-clips are installed and corrective action if necessary. This AD also requires an inspection of electrical bonding points of certain equipment in the center fuel tank for the presence of a blue coat and related investigative and corrective actions if necessary. This AD also requires installation of new bonding leads and electrical bonding points on certain equipment in the wing, center, and trim fuel tanks, as necessary. This AD results from fuel system reviews conducted by the manufacturer. We are issuing this AD to ensure continuous electrical bonding protection of equipment in the wing, center, and trim fuel tanks and to prevent damage to wiring in the wing and center fuel tanks, due to failed P-clips used for retaining the wiring and pipes, which could result in a possible fuel ignition source in the fuel tanks.
AD 2006-15-10 · published Jul 25, 2006, effective Aug 29, 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); and Airbus Model A310-200 and -300 Series Airplanes
The FAA is adopting a new airworthiness directive (AD) for all 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); and Model A310-200 and -300 series airplanes. This AD requires a one-time inspection of the trimmable horizontal stabilizer actuator (THSA), corrective actions if necessary, and follow-on repetitive tasks. This AD results from reports of THSAs that have reached their design operational life. We are issuing this AD to extend the operational life of the THSA to prevent a possible failure of high- time THSAs, which could result in reduced controllability of the airplane.
AD 2006-15-11 · published Jul 25, 2006, effective Aug 29, 2006
Construcciones Aeronauticas, S.A. (CASA), Model C-212-CC Airplanes
The FAA is adopting a new airworthiness directive (AD) for certain CASA Model C-212-CC airplanes. This AD restricts the operation of the airplane to carrying either passengers or cargo (but not both) in the same compartment, unless the airplane is modified to include an approved protective liner between the passengers and the cargo. This AD results from our determination that affected airplanes, when carrying both cargo and passengers in the same compartment, cannot achieve the required level of performance. We are issuing this AD to prevent a hazardous quantity of smoke, flames, and/or fire extinguishing agent from the cargo compartment from entering a compartment occupied by passengers or crew.
AD 2006-15-12 · published Jul 25, 2006, effective Aug 29, 2006
Construcciones Aeronauticas, S.A. (CASA), Model C-212-CC Airplanes
The FAA is adopting a new airworthiness directive (AD) for certain CASA Model C-212-CC airplanes. This AD restricts the operation of the airplane to carrying either passengers or cargo (but not both) in the same compartment, unless the airplane is modified to include an approved protective liner between the passengers and the cargo. This AD results from our determination that affected airplanes, when carrying both cargo and passengers in the same compartment, cannot achieve the required level of performance. We are issuing this AD to prevent a hazardous quantity of smoke, flames, and/or fire extinguishing agent from the cargo compartment from entering a compartment occupied by passengers or crew.
AD 2006-15-15 · published Jul 31, 2006, effective Sep 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), and MD-88 Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas airplane models, that requires a one-time inspection for chafing or signs of arcing of the wire bundle for the auxiliary hydraulic pump, and other specified and corrective actions, as applicable. This AD also requires that, for certain airplanes, installation of additional protective sleeving on the upper portion of the auxiliary hydraulic pump wire assembly. This AD results from reports of shorted wires and evidence of arcing on the power cables of the auxiliary hydraulic pump, as well a fuel system reviews conducted by the manufacturer. We are issuing this AD to prevent shorted wires or arcing at the auxiliary hydraulic pump, which could result in loss of auxiliary hydraulic power, or a fire in the wheel well of the airplane. The actions specified by this AD are also intended to reduce the potential of an ignition source adjacent to the fuel tanks, which, in combination with flammable fuel vapors, could result in a fuel tank explosion and consequent loss of the airplane.
AD 2006-15-16 · published Jul 31, 2006, effective Sep 5, 2006
Raytheon (Beech) Model 400 and 400A Series Airplanes
The FAA is adopting a new airworthiness directive (AD) for certain Raytheon (Beech) Model 400 and 400A series airplanes. This AD requires, among other actions, reviewing the airplane logbook to determine whether certain generator control unit (GCU) installation kits are installed, and replacing any incorrect GCU. This AD results from reports of over-voltage conditions of the direct current (DC) starter generator. We are issuing this AD to prevent such over-voltage conditions due to the incompatibility between certain GCUs, which could result in the loss of normal electrical power, damage to some electrical components, or blown fuses during flight, and consequent unrecoverable loss of some or all essential equipment.
AD 2006-15-17 · published Jul 31, 2006, effective Sep 5, 2006
Fokker Model F.28 Mark 0070 and 0100 Airplanes
The FAA is adopting a new airworthiness directive (AD) for all Fokker Model F.28 Mark 0070 and 0100 airplanes. This AD requires modification of the wiring distribution of the alternating current bus transfer power system and the right-hand and left-hand windshield anti- icing system, as necessary. This AD results from a report of electrical sparks coming out of the flight deck from a panel behind the left seat. We are issuing this AD to prevent failure of the sliding window heating element(s), due to electrical overload, which could result in smoke and fire in the cockpit.
AD 2006-15-18 · published Jul 31, 2006, effective Sep 5, 2006
Boeing Model 737-300, -400, -500, -600, -700, -700C, -800, and -900 Series Airplanes
The FAA is adopting a new airworthiness directive (AD) for certain Boeing Model 737-300, -400, -500, -600, -700, -700C, -800, and -900 series airplanes. This AD requires modifying the wiring for the master dim and test system. For certain airplanes, this AD also requires related concurrent actions as necessary. This AD results from a report that the master dim and test system circuit does not have wiring separation of the test ground signal for redundant equipment in the flight compartment. We are issuing this AD to prevent a single fault failure in flight from simulating a test condition and showing test patterns instead of the selected radio frequencies on the communications panels, which could inhibit communication between the flightcrew and the control tower, affecting the continued safe flight of the airplane.
AD 2004-16-15 R1 · published Jul 26, 2006, effective Aug 30, 2006
Eurocopter France Model AS-365N2, AS 365 N3, EC 155B, EC155B1, SA-365N, N1, and SA-366G1 Helicopters
This amendment revises an existing airworthiness directive (AD) for Eurocopter France (Eurocopter) Model AS-365N2, AS 365 N3, EC 155B, EC155B1, SA-365N, N1, and SA-366G1 helicopters that currently requires inspecting the main gearbox (MGB) base plate for a crack and replacing the MGB if a crack is found. This amendment increases the time intervals for inspecting the MGB base plate and includes minor editorial changes throughout the AD. This amendment is prompted by crack growth tests that indicate that the inspection intervals can be increased without affecting safety. The actions specified by this AD are intended to detect a crack in an MGB base plate and prevent failure of one of the MGB attachment points to the frame, which could result in severe vibration and subsequent loss of control of the helicopter.
AD 2006-15-14 · published Jul 27, 2006, effective Aug 31, 2006
Eurocopter Canada Limited Model BO 105 LS A-3 Helicopters
This amendment adopts a new airworthiness directive (AD) for Eurocopter Canada Limited (Eurocopter) Model BO 105 LS A-3 helicopters that requires replacing certain fixed bolts and nuts, re-identifying certain main rotor nuts, and revising the Airworthiness Limitations-- Time Change Items (TCI) list to reflect the new life limits and new part numbers. This amendment is prompted by a re-evaluation of certain fatigue-critical parts, which resulted in establishing new life limits for certain like-numbered parts and re-identifying a certain existing part with a different part number, or in some cases, replacing them with new parts. The actions specified by this AD are intended to prevent fatigue failure of the fixed bolts and nuts, and subsequent loss of control of the helicopter.
AD 2006-14-03 · published Jul 5, 2006, effective Aug 9, 2006
Honeywell International Inc. TPE331 Series Turboprop, and TSE331-3U Model Turboshaft Engines
The FAA is adopting a new airworthiness directive (AD) for certain Honeywell International Inc. TPE331 series turboprop, and TSE331-3U model turboshaft engines. This AD requires implementing a new flight cycle counting method for first, second, and third-stage turbine rotors used in aircraft that make multiple takeoffs and landings without an engine shutdown, and removing turbine rotors from service that have reached or exceeded their cycle life limits. This new flight cycle counting method requires determining total equivalent cycles accrued. This AD results from several reports of uncontained turbine rotor separation on engines used in special-use operations. We are issuing this AD to prevent uncontained failure of the turbine rotor due to low-cycle-fatigue (LCF), and damage to the aircraft.
AD 2006-15-08 · published Jul 20, 2006, effective Aug 24, 2006
Honeywell International Inc. TPE331 Series Turboprop Engines
The FAA is adopting a new airworthiness directive (AD) for Honeywell International Inc. TPE331 series turboprop engines with certain part numbers of Woodward fuel control unit (FCU) assemblies installed. This AD requires initial and repetitive dimensional inspections of the fuel control drive, for wear or damage. This AD results from reports of loss of the fuel control drive, leading to engine overspeed, overtorque, overtemperature, uncontained rotor failure, and asymmetric thrust in multi-engine airplanes. We are issuing this AD to prevent destructive overspeed that could result in uncontained rotor failure, and damage to the airplane.
AD 2006-15-13 · published Jul 26, 2006, effective Aug 10, 2006
McCauley Propeller Systems Propeller Models B5JFR36C1101/114GCA-0, C5JFR36C1102/L114GCA-0, B5JFR36C1103/114HCA-0, and C5JFR36C1104/L114HCA-0
The FAA is adopting a new airworthiness directive (AD) for McCauley Propeller Systems propeller models B5JFR36C1101/114GCA-0, C5JFR36C1102/L114GCA-0, B5JFR36C1103/114HCA-0, and C5JFR36C1104/ L114HCA-0. This AD requires a onetime fluorescent penetrant inspection (FPI) and eddy current inspection (ECI) of propeller blades for cracks, and if any crack indications are found, removing the blade from service. This AD results from a report of two propeller blades on the same propeller assembly, found cracked during propeller overhaul. We are issuing this AD to detect cracks in the propeller blade that could cause failure and separation of the propeller blade and loss of control of the airplane.
AD 2006-16-01 · published Jul 31, 2006, effective Aug 30, 2006
Hamilton Sundstrand Model 14RF-19 Propellers
The FAA is superseding an existing airworthiness directive (AD) for Hamilton Sundstrand model 14RF-19 propellers. That AD currently requires replacing certain actuator yokes with improved actuator yokes. This AD requires the same actions. This AD results from the discovery of a part number (P/N) error in the applicability paragraph of AD 2006-12-19. We are issuing this AD to prevent actuator yoke arms breaking during flight, which could cause high propeller vibration and contribute to reduced controllability of the airplane.
