21 Airworthiness Directives: 13 airplane, 2 rotorcraft, 5 engine, 1 appliance.
AD 2001-18-02 · published Sep 6, 2001, effective Oct 11, 2001
Fokker Model F.28 Mark 1000, 2000, 3000, and 4000 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to all Fokker Model F.28 Mark 1000, 2000, 3000, and 4000 series airplanes, that requires a one-time eddy current inspection for cracks of the fuselage butt joint which is forward of the emergency exits on the left- and right-hand sides of the airplane at the level of stringers 27/48. This proposal would also require repair of any cracks detected. This amendment is prompted by issuance of mandatory continuing airworthiness information by a foreign airworthiness authority. The actions specified by this AD are intended to detect and correct cracks in the area of the emergency escape hatches, which, if undetected, could result in depressurization during flight, possibly leading to structural failure of the airplane.
AD 2001-18-03 · published Sep 6, 2001, effective Oct 11, 2001
Fokker Model F27 Mark 100, 200, 300, 400, 500, 600, and 700 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to all Fokker Model F27 Mark 100, 200, 300, 400, 500, 600, and 700 series airplanes, that requires a one-time inspection for correct installation of the left- and right-hand fuel differential pressure (FDP) switches and for correct connection of the pressure sensing lines to the switches, and corrective action, if necessary. The actions specified by this AD are intended to ensure that a warning light goes on when the fuel filter is partially blocked by ice, so that the blockage of the fuel filter does not increase, leading to reduced fuel flow to the engine and possibly to an engine flame-out. This action is intended to address the identified unsafe condition.
AD 2001-18-04 · published Sep 6, 2001, effective Sep 21, 2001
Boeing Model 747-400 Series Airplanes
This amendment supersedes an existing airworthiness directive (AD), applicable to certain Boeing Model 747-400 series airplanes, that currently requires repetitive inspections to detect damage or deflection of the crew rest heat exchanger, and follow-on actions, if necessary. This amendment adds a new requirement for a one-time inspection to determine the part number and shop code of the shell of the crew rest heat exchanger; and follow-on actions, if necessary; which terminate the currently required repetitive inspections. This action is necessary to prevent cracking and buckling of the front edge of the crew rest heat exchanger, which could result in a jam of the rudder or elevator control cables, and consequent reduced controllability of the airplane. This action is intended to address the identified unsafe condition.
AD 2001-18-07 · published Sep 6, 2001, effective Oct 12, 2001
Raytheon Aircraft Company Beech Models 1900, 1900C, and 1900D Airplanes
This amendment adopts a new airworthiness directive (AD) that applies to certain Raytheon Aircraft Company (Raytheon) Beech Models 1900, 1900C, and 1900D airplanes. This AD requires you to inspect all four flap flexible shaft assemblies for the correct diagonal wrap and the correct installation. This AD also requires you to replace any flap flexible shaft assembly that has an incorrect diagonal wrap or incorrect installation. This AD is the result of several occurrences of flap extension/retraction failures on the affected airplanes due to the inner flexible shaft ends separating or disengaging. The actions specified by this AD are intended to prevent these flap extension/ retraction failures due to incorrectly configured flap flexible shaft assemblies. Such failure could result in an asymmetric flap condition during flight if the flap safety switch fails to function properly.
AD 2001-18-08 · published Sep 6, 2001, effective Oct 11, 2001
Boeing Model 767-300 Series Airplanes Modified by Supplemental Type Certificate SA7019NM-D
This amendment adopts a new airworthiness directive (AD), applicable to all Boeing Model 767-300 series airplanes modified by supplemental type certificate SA7019NM-D, that requires modification of the in-flight entertainment (IFE) system to install a switch to remove power from the IFE system, and revision of flight crew and cabin crew procedures. This action is necessary to ensure that the flight crew and cabin crew are able to remove electrical power from the IFE system when necessary and are advised of appropriate procedures for such action. Inability to remove power from the IFE system during a non-normal or emergency situation could result in inability to control smoke or fumes in the airplane flight deck or cabin. This action is intended to address the identified unsafe condition.
AD 2001-18-01 · published Sep 10, 2001, effective Oct 15, 2001
Airbus Model A340-211 Series Airplanes Modified by Supplemental Type Certificate ST09092AC-D
This amendment adopts a new airworthiness directive (AD), applicable to all Airbus Model A340-211 series airplanes modified by supplemental type certificate ST09092AC-D, that requires modifying the passenger entertainment system (PES) and revising the Flight Crew Operating Manual. This action is necessary to ensure that the flight crew is able to remove electrical power from the entire PES when necessary and is advised of appropriate procedures for such action. Inability to remove power from the PES during a non-normal or emergency situation could result in inability to control smoke or fumes in the airplane flight deck or cabin. This action is intended to address the identified unsafe condition.
AD 2001-18-09 · published Sep 12, 2001, effective Oct 17, 2001
Boeing Model 777-200 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 777-200 series airplanes, that requires inspections for cracking of the web of the horizontal and sloping pressure decks of the fuselage and certain stiffener splice angles and stiffener end fittings, and repair, if necessary. This amendment also provides an optional preventative modification, which ends the repetitive inspections. The actions specified by this AD are intended to find and fix cracking of the web of the horizontal and sloping pressure decks, which could result in rapid in-flight decompression of the airplane. This action is intended to address the identified unsafe condition.
AD 2001-18-10 · published Sep 13, 2001, effective Oct 18, 2001
Empresa Brasileira de Aeronautica S.A. (EMBRAER) Model EMB-135 and EMB-145 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain EMBRAER Model EMB-135 and EMB-145 series airplanes, that requires replacement of the engine oil pressure sensors with new sensors, and installation of an oil tank pressure relief kit. Additionally, this amendment requires revision of the Airplane Flight Manual that would specify new oil pressure limits. This action is necessary to prevent rejected takeoffs due to exceeding engine oil pressure limits, which could result in reduced controllability of the airplane. This action is intended to address the identified unsafe condition.
AD 2001-18-12 · published Sep 13, 2001, effective Sep 28, 2001
Boeing Model 767-200, -300, -300F and -400ER Series Airplanes
This amendment adopts a new airworthiness directive (AD) that is applicable to certain Boeing Model 767-200, -300, -300F and -400ER series airplanes. This action requires repetitive inspections to find discrepancies of the wire bundles located between the P50 panel and the nose wheel well structure, and corrective actions, if necessary. This action is necessary to find and fix such discrepancies, which could result in electrical arcing, smoke, or fire in the cabin, and failure of certain systems essential to safe flight and landing of the airplane. This action is intended to address the identified unsafe condition.
AD 2001-18-11 · published Sep 14, 2001, effective Oct 1, 2001
McDonnell Douglas Model 717 Series Airplanes
This amendment adopts a new airworthiness directive (AD) that is applicable to certain McDonnell Douglas Model 717 series airplanes. This action requires a one-time inspection of the support seal tubes of the rudder trim and load-feel actuator assembly of the rudder trim control system, located in the aft accessory compartment, for proper clearance between the actuator support seal tube and spring capsule assembly, and applicable follow-on/corrective actions. This action is necessary to detect and correct the accumulation of moisture in the rudder trim and load-feel actuator of the rudder trim control system. Such moisture could freeze and cause stiff operation, binding, or jamming of the rudder trim control system and consequent jamming of the rudder; and adversely affect directional control of an airplane.
AD 2001-19-01 · published Sep 14, 2001, effective Oct 1, 2001
Bombardier Model DHC-8-301 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Bombardier Model DHC-8-301 series airplanes. This action requires removal of the access panels of the upper wings to determine the manufacturing date of the panels to verify compliance with Model 301 wing specifications, and corrective action, if necessary. This action is necessary to find and fix panels that do not meet such specifications, which could result in elongation of the attachment holes in the panels due to critical design loads, and consequent reduced structural integrity of the wings. This action is intended to address the identified unsafe condition.
AD 2001-19-04 · published Sep 21, 2001, effective Oct 9, 2001
Boeing Model 767-200 and -300 Series Airplanes
This amendment adopts a new airworthiness directive (AD) that is applicable to certain Boeing Model 767-200 and -300 series airplanes. This action requires repetitive inspections to find discrepancies of the barrel nuts that attach the vertical fin to body section 48, and follow-on actions. For certain airplanes, this action requires replacement of certain bolts with new bolts. This action also provides for optional terminating actions for the repetitive inspections. This action is necessary to find and fix corroded, cracked or broken barrel nuts that attach the vertical fin to body section 48, which could result in reduced structural integrity of the vertical fin attachment joint, loss of the vertical fin, and consequent loss of controllability of the airplane. This action is intended to address the identified unsafe condition.
AD 2001-17-09 R1 · published Sep 27, 2001
McDonnell Douglas Model MD-11 Series Airplanes
This amendment rescinds Airworthiness Directive (AD) 2000-17- 09, which is applicable to certain McDonnell Douglas Model MD-11 series airplanes. That AD requires an inspection of the upper avionics circuit breaker panel at the main observer's station to detect damage of the wires and to verify the correct routing of the wire bundles; corrective actions, if necessary; and installation of a new clamp, spacer, and sta-straps. The requirements of that AD were intended to prevent chafing in the upper avionics circuit breaker panel of the main observer's station, which could result in arcing and consequent smoke and/or fire in the cockpit. Since the issuance of that AD, the FAA has determined that the improper procedures specified by the service bulletin referenced in that AD could lead to wiring pre-load conditions and consequent wire damage, and arcing in the upper avionics circuit breaker panel. Such conditions could result in arcing and consequent smoke and/or fire in the cockpit.
AD 2001-18-13 · published Sep 14, 2001, effective Oct 1, 2001
Eurocopter Deutschland GmbH Helicopters
This amendment adopts a new airworthiness directive (AD) for Eurocopter Deutschland GmbH (Eurocopter) Model EC135 P1 and EC135 T1 helicopters. This action requires, before further flight, adding a copy of this AD or a statement to the Emergency Procedures section of the Rotorcraft Flight Manual (RFM) to inform the pilot to reduce power and land as soon as practicable if a thump-like sound followed by unusual vibration occurs during flight. This action also requires visually inspecting for a crack or a break in certain main rotor drive torque strut (strut) assemblies at specified time intervals and recording details of the inspections in the historical or equivalent record. This AD also requires re-marking and relocating the strut as appropriate and replacing any unairworthy strut assembly with an airworthy strut assembly before further flight. Also, this AD establishes a life limit of 1000 hours time-in-service (TIS) for certain struts with an additional 1000 hours TIS for struts re-marked right-hand (RH) or left-hand (LH) before installing in the new location. This amendment is prompted by a report of a thump-like sound heard during flight followed by unusual vibrations due to failure of the RH strut between the main transmission and the fuselage. The actions specified in this AD are intended to prevent failure of a strut, failure of a worn or ineffective back-up emergency stop, and subsequent loss of control of the helicopter.
AD 2001-13-51 · published Sep 21, 2001, effective Oct 9, 2001
Bell Helicopter Textron Canada Model 206L-4, 407, and 427 Helicopters
This document publishes in the Federal Register an amendment adopting Airworthiness Directive (AD) 2001-13-51, which was sent previously to all known U.S. owners and operators of Bell Helicopter Textron Canada (BHTC) Model 206L-4, 407, and 427 helicopters by individual letters. This AD requires visually inspecting certain driveshafts for a crack, a loose bolt or nut, or red powder residue. If a crack, a loose bolt or nut, or red powder residue is found, replacing the driveshaft before further flight and notifying the FAA within 10 days is also required. This amendment is prompted by a driveshaft failure on a BHTC Model 407 helicopter that resulted in an engine shutdown and an emergency landing. Failure of the driveshaft was due to cracking of the flexframe on the forward end of the driveshaft. In addition, three other incidents of a cracked flexframe on the forward end of the driveshaft on other Model 407 helicopters have been reported. The actions specified by this AD are intended to prevent failure of a driveshaft, loss of drive to the main rotor system, and a subsequent emergency forced landing.
AD 2001-18-06 · published Sep 13, 2001, effective Oct 18, 2001
General Electric Company T58 and CT58 Series Turboshaft Engines
This amendment surpersedes two existing airworthiness directives (AD's), applicable to General Electric Company (GE) T58 and CT58 series turboshaft engines. The current AD's revised the counting method for hours in repetitive heavy-lift (RHL) service and reduced the life limit for rotating components. Life-limited rotating components must be removed from service in accordance with the multiplying factors and retirement lives contained in General Electric Alert Service Bulletin (ASB) CT58 A72-162 (CEB-258), dated July 9, 1979. This amendment requires applying an additional multiplying factor to life- limited rotating parts when the engine is used in heavy lifting operations. This amendment is prompted by a review of the current AD's, AD-69-23-02 and AD-79-23-04, and a determination that the requirements of those AD's may conflict. This amendment will prevent RHL and utility service multiplier factors from being applied incorrectly. The actions specified in this AD are intended to prevent low-cycle fatigue failure of rotating parts that could result in uncontained engine failure and damage to the rotorcraft.
AD 2001-19-02 · published Sep 24, 2001, effective Oct 9, 2001
General Electric Aircraft Engines Engines
This amendment adopts a new airworthiness directive (AD) that is applicable to GE CF34-3A1, -3B, and -3B1 turbofan engines with scavenge screens part numbers (P/N's) 4047T95P01 and 5054T86G02 installed in the B-sump oil scavenge system. This action requires initial and repetitive visual inspections and cleaning of the B-sump scavenge screens. This amendment is prompted by five reports of B-sump oil scavenge system failure causing engine in-flight shutdowns. The actions specified in this AD are intended to prevent B-sump scavenge screen blockage due to coking, which could result in ignition of B-sump oil in the secondary air system, fan drive shaft separation, and uncontained engine failure.
AD 2001-19-03 · published Sep 24, 2001, effective Oct 29, 2001
Rolls-Royce Corporation Engines
This amendment adopts a new airworthiness directive (AD), that is applicable to Rolls-Royce Corporation (formerly Allison Engine Company) Model AE 3007A and AE 3007C turbofan engines with a certain part number high pressure turbine (HPT) 1st to 2nd stage turbine spacer installed. This amendment requires removal and replacement of that HPT 1st to 2nd stage turbine spacer before it reaches its new reduced engine cycle life limit.This amendment is prompted by the results of a detailed component analysis that indicates that the HPT 1st to 2nd stage turbine spacer stresses are higher than predicted. The actions specified by this AD are intended to prevent HPT 1st to 2nd stage turbine spacer failure which could result in an uncontained engine failure and damage to the airplane.
AD 2001-19-05 · published Sep 26, 2001, effective Oct 11, 2001
Rolls-Royce plc Engines
This amendment adopts a new airworthiness directive (AD) that is applicable to Rolls-Royce plc. (RR) models RB211-535C-37, RB211-535E4-37, RB211-535E4-B-37, and RB211-535E4-B-75 turbofan engines, with radial drive steady bearing, part number (P/N) LK76084. This action requires the replacement of certain radial drive steady bearings, installed in the high speed gearbox drive. This amendment is prompted by five reports of radial drive steady bearing failures. The actions specified in this AD are intended to reduce the risk of engine in-flight shutdown, due to failure at low life of radial drive steady bearings.
AD 2001-19-06 · published Sep 28, 2001, effective Oct 15, 2001
Rolls-Royce plc Dart 525, 525F, 528, 528D, 529, 529D, 530, 532, 535, 542, and 552 Series Turboprop Engines
This amendment adopts a new airworthiness directive (AD) that is applicable to Rolls-Royce plc (RR) Dart 525, 525F, 528, 528D, 529, 529D, 530, 532, 535, 542, and 552 series turboprop engines. This action requires the removal of certain part number (P/N) high pressure turbine (HPT) discs and replacement with serviceable discs. This amendment is prompted by three reports of uncontained HPT disc failures and the manufacturer's investigation into disc failure. The actions specified in this AD are intended to prevent HPT disc failure, which could result in an uncontained engine failure and damage to the airplane.
AD 2001-18-05 · published Sep 4, 2001, effective Sep 24, 2001
Goodyear Tire and Rubber Company Flight Eagle Tires, 34X9.25-16 18PR 210MPH, Part Number 348F83-2
This amendment adopts a new airworthiness directive (AD) that applies to certain Goodyear Tire and Rubber Company (Goodyear) Flight Eagle tires, 34X9.25-16 18PR 210MPH, Part Number (P/N) 348F83-2, that are installed on aircraft. This AD requires you to inspect these tires to determine if they are within a certain serial number range and replace any tires within this serial number range. This AD is the result of several instances of main landing gear (MLG) tire tread separations on Gulfstream aircraft. The actions specified by this AD are intended to remove these tires from service to prevent the potential of these tires experiencing tread separations during operation. These tread separations could result in structural damage to the aircraft, including damage to the flaps, engine nacelles, and wheel wells.
