30 Airworthiness Directives: 22 airplane, 2 rotorcraft, 3 engine, 1 propeller, 1 appliance, 1 glider.
AD 2001-22-11 · published Nov 1, 2001, effective Dec 6, 2001
Boeing Model 737-600, -700, and -800 Series Airplanes
This amendment supersedes an existing airworthiness directive (AD), applicable to all Boeing Model 737-600, -700, and -800 series airplanes, that currently requires an inspection of the power distribution panels (PDP) to verify proper installation of the power feeder terminals and associated hardware, and corrective actions, if necessary. The existing AD also requires repetitive torque checks of the terminal attachment screws. This amendment adds a requirement for repetitive replacement of the PDP rigid bus assembly with a new assembly and provides an optional terminating action for the repetitive torque checks and the repetitive replacement of the PDP rigid bus assembly. This amendment is prompted by reports of loss of electrical power from the engine-driven generators or the auxiliary power unit due to overheating, melting, and subsequent failure of the power feeder terminals at the PDPs. The actions specified by this AD are intended to prevent such conditions, which could result in increased risk of fire and the loss of electrical power from the associated alternating current power source.
AD 2001-22-13 · published Nov 1, 2001, effective Dec 6, 2001
Boeing Model 737-100, -200, -300, -400, and -500 Series Airplanes; and Model 747, 757, 767, and 777 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 737-100, -200, -300, -400, and -500 series airplanes; and certain Boeing Model 747, 757, 767, and 777 series airplanes; that requires replacing the rudder pedal pushrod fasteners for both the captain's and first officer's pedal assemblies with new, improved fasteners. This action is necessary to prevent loss of rudder control due to improperly torqued fasteners that connect the pushrod to the rudder pedal assembly, which could result in loss of controllability of the airplane. This action is intended to address the identified unsafe condition.
AD 2001-22-15 · published Nov 7, 2001, effective Dec 26, 2001
Pilatus Aircraft Ltd. Models PC-12 and PC-12/45 Airplanes
This amendment adopts a new airworthiness directive (AD) that applies to all Pilatus Aircraft Ltd. (Pilatus) Models PC-12 and PC-12/ 45 airplanes. This AD requires you to inspect the cargo doors to identify front and rear end frames with plain lightening holes and install reinforcing plates on any frame with plain lightening holes. This AD is the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for Switzerland. The actions specified by this AD are intended to prevent cracking at the edges of the unflanged lightening holes, which could result in major structural damage to the airplane. Such damage could result in possible loss of control of the airplane.
AD 2001-22-16 · published Nov 7, 2001, effective Dec 17, 2001
Raytheon Aircraft Company Beech Models 1900, 1900C (C-12J), and 1900D Airplanes
This amendment supersedes Airworthiness Directive (AD) 95-02- 18, which applies to certain Raytheon Aircraft Company (Raytheon) Beech Models 1900, 1900C (C-12J), and 1900D airplanes. AD 95-02-18 requires you to repetitively inspect the engine truss assemblies for cracks, repair or replace any cracked engine truss assembly, and install reinforcement doublers. This AD requires engine truss assembly replacement, periodic inspections and replacements, and the eventual incorporation of a cowling support installation kit as terminating action. The repetitive inspections of AD 95-02-18 will be retained until mandatory engine truss assembly replacement. This AD is the result of continued reports of fatigue cracks found on engine trusses on airplanes in compliance with AD 95-02-18. The actions specified by this AD are intended to detect and correct cracked engine truss assemblies, which could result in failure of the engine truss assembly and consequent loss of airplane control.
AD 2001-22-17 · published Nov 13, 2001, effective Dec 18, 2001
McDonnell Douglas Model DC-9-81, -9-82, -9-83, and -9-87 Series Airplanes; Model MD-88 Airplanes; and Model MD-90-30 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model DC-9-81, -9-82, -9-83, and -9-87 series airplanes; Model MD-88 airplanes; and Model MD-90-30 series airplanes. This action requires repetitive inspections of the electric motors (or motors) of the auxiliary hydraulic pump for electrical resistance, continuity, mechanical rotation, and associated wiring resistance/voltage; and corrective actions, if necessary. The actions specified by this AD are intended to prevent various failures of the electric motor(s) of the auxiliary hydraulic pump and associated wiring, which could result in fire at the auxiliary hydraulic pump and consequent damage to the adjacent electrical equipment and/or structure. This action is intended to address the identified unsafe condition.
AD 2001-23-01 · published Nov 14, 2001, effective Dec 19, 2001
Boeing Model 737-600, -700, and -800 Series Airplanes
This amendment supersedes an existing airworthiness directive (AD), applicable to certain Boeing Model 737-600, -700, and -800 series airplanes, that currently requires repetitive inspections of certain elevator hinge plates, and corrective action, if necessary. That AD also provides for an optional replacement of the elevator hinge plates with new, improved hinge plates, which would end the repetitive inspections. This amendment requires accomplishment of the previously optional replacement of the elevator hinge plates with new, improved hinge plates, as terminating action for the repetitive inspections. The actions specified by this AD are intended to prevent fatigue cracking of the elevator hinge plates, which could lead to the loss of the attachment of the elevator to the horizontal stabilizer, and consequent reduced controllability of the airplane. This action is intended to address the identified unsafe condition.
AD 2001-01-07 · published Nov 15, 2001, effective Jan 7, 2002
Reims Aviation S.A. Model F406 Airplanes
This amendment adopts a new airworthiness directive (AD) that applies to certain Reims Aviation S.A. (Reims) Model F406 airplanes. This AD requires you to repetitively inspect the canted rib upper cap in the center wing carry-through area for cracks, and, if cracks are found, immediately repair the cracks or modify this area depending on the extent of any cracks found. This AD also requires you to modify the canted rib upper cap at a certain time period as terminating action for the repetitive inspections. This AD is the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for France. The actions specified by this AD are intended to detect and correct cracks in the canted rib upper cap in the center wing carry-through area, which could result in structural failure of the wing with possible loss of control of the airplane.
AD 2001-23-03 · published Nov 15, 2001, effective Dec 27, 2001
Cessna Aircraft Company Models 172N, 172P, R172K, 172RG, F172N, F172P, FR172J, and FR172K Airplanes
This amendment supersedes Airworthiness Directive (AD) 80-04- 08, which requires inspecting (one-time) the fuel line and map light switch in the left hand forward door post for chafing or arcing on certain Cessna Aircraft Company (Cessna) Model 172N, R172K, F172N, and FR172K airplanes and repairing any damage found. AD 80-04-08 also requires providing at least a 0.50-inch clearance between the map light switch and the fuel line; and installing a switch cover (insulator) over the map light switch. This AD requires you to extend the inspections and installation of the switch cover requirement to certain 172N, 172P, R172K, 172RG, F172N, F172P, FR172J, and FR172K series airplanes. This AD also requires replacement of the fuel line, if damaged; and makes the switch cover inspection and replacement repetitive. This AD is the result of FAA receiving several reports of incidents of electrical shorts on Cessna Model 172N airplanes. The actions specified by this AD are intended to detect and correct any chafing between the map light switch and the bordering fuel line, which could result in a fuel leak and an in-flight fire.
AD 2001-23-04 · published Nov 19, 2001, effective Jan 4, 2002
SOCATA-Groupe Aerospatiale Models TB 9, TB 10, TB 20, TB 21, and TB 200 Airplanes
This amendment adopts a new airworthiness directive (AD) that applies to all SOCATA--Groupe Aerospatiale (SOCATA) Models TB 9, TB 10, TB 20, TB 21, and TB 200 airplanes. This AD requires you to repetitively inspect the lower rudder hinge fitting for cracks. This AD also requires you to repair any crack found in accordance with a repair scheme obtained from the manufacturer through the Federal Aviation Administration (FAA). This AD is the result mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for France. The actions specified by this AD are intended to detect and correct fatigue cracks in the lower rudder hinge fitting. This condition could cause the lower rudder to detach from the control linkage with consequent loss of control of the airplane.
AD 2001-23-05 · published Nov 19, 2001, effective Jan 4, 2002
SOCATA-Groupe Aerospatiale Models TB 9, TB 10, TB 20, TB 21, and TB 200 Airplanes
This amendment adopts a new airworthiness directive (AD) that applies to all SOCATA--Groupe Aerospatiale (SOCATA) Models TB 9, TB 10, TB 20, TB 21, and TB 200 airplanes that do not have factory Modification 165, any edition, incorporated on the front seats. This AD requires you to modify the front seats that have solid metal seat pans. This AD is the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for France. The actions specified by this AD are intended to eliminate the potential for the front seats to inadvertently unlock from their fixed positions. Such uncontrolled movement could prevent the pilot from making the necessary flight maneuvers to control the airplane.
AD 2001-23-06 · published Nov 19, 2001, effective Dec 27, 2001
SOCATA-Groupe Aerospatiale Model TBM 700 Airplanes
This amendment adopts a new airworthiness directive (AD) that applies to certain SOCATA--Groupe Aerospatiale (Socata) Model TBM 700 airplanes. This AD requires you to inspect for defective Amendment A fuel tank air vent valves and replace with parts of improved design. This AD is the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for France. The actions specified by this AD are intended to prevent in-flight damage to the wing skins caused by abnormal venting conditions of the wing fuel tank, which could result in severe handling problems or reduced structural capability. Continued operation with such structural deformation or handling problems could result in loss of control of the airplane.
AD 2001-23-10 · published Nov 21, 2001, effective Dec 13, 2001
Raytheon Aircraft Company 33, T-34, 35, 36, 55, 56, 58, and 95 Series Airplanes
This amendment adopts a new airworthiness directive (AD) that applies to certain Raytheon Aircraft Company (Raytheon) 33, T-34, 35, 36, 55, 56, 58, and 95 Series airplanes. This AD requires you to inspect the left-hand and right-hand flap flex shaft assemblies to determine the manufacture date. This AD also requires you to replace any flap flex shaft assemblies manufactured from January 2000 through April 2001. This AD is the result four separate reports of flap drive cable separation. The actions specified by this AD are intended to prevent separation of the flap flex shaft assembly caused by improper heat treatment. Such a condition could lead to an asymmetric flap condition, resulting in uncommanded roll of the airplane.
AD 2001-17-28 R1 · published Nov 26, 2001, effective Dec 11, 2001
Boeing Model 767 Series Airplanes
This amendment revises an existing airworthiness directive (AD), applicable to all Boeing Model 767 series airplanes, that currently requires a one-time inspection to detect abrasion damage and installation discrepancies of the wire bundles located below the P37 panel, corrective action if necessary, relocating the wire support standoff, and installing protective sleeving over the wire bundles. This amendment removes the requirements to relocate the wire support standoff and install the protective sleeving, and revises the applicability by removing certain airplanes. The actions specified in this AD are intended to detect and correct such abrasion damage and installation discrepancies, which could result in arcing to structure and consequent fire or loss of function of affected systems.
AD 2001-23-12 · published Nov 26, 2001, effective Dec 31, 2001
Saab Model SAAB SF340A and SAAB 340B Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Saab Model SAAB SF340A and SAAB 340B series airplanes, that requires a one-time review of records to determine whether an airplane has been repainted since its delivery from the factory; and a one-time inspection to detect damage associated with improper preparation for the repainting, and corrective action if necessary. This amendment is prompted by mandatory continuing airworthiness information from a foreign civil airworthiness authority. The actions specified by this AD are intended to detect and correct damage to the aluminum skin of the airplane, which could result in a weakening of the structure of the airplane.
AD 2001-23-13 · published Nov 26, 2001, effective Dec 31, 2001
Boeing Model 747 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 747 series airplanes, that requires an inspection of the flap drive transmission of the trailing edge flaps at positions 2 and 7 to determine if a discrepant torque brake is installed; and corrective action, if necessary. The action specified by this AD are intended to prevent damage to the flap system, adjacent systems, or structural components; or excessive skew of the trailing edge flap, which could result in flap asymmetry and consequent reduced controllability of the airplane. This action is intended to address the identified unsafe condition.
AD 2001-23-14 · published Nov 26, 2001, effective Dec 31, 2001
Boeing Model 757 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 757 series airplanes, that requires a review of maintenance records or an inspection to determine the serial numbers of geared rotary actuators (GRA) for the leading edge slats, and replacement of certain actuators with new or reworked actuators. This action is necessary to prevent a fractured spring washer in a GRA, which could lead to a disconnect in the GRA, and result in a slat skew condition and consequent reduced controllability of the airplane. This action is intended to address the identified unsafe condition.
AD 2001-24-03 · published Nov 26, 2001, effective Dec 11, 2001
Dassault Model Mystere-Falcon 50 Series Airplanes
This amendment adopts a new airworthiness directive (AD) that is applicable to certain Dassault Model Mystere-Falcon 50 series airplanes. This action requires revising the Airplane Flight Manual to prohibit flight operation under reduced vertical separation minimum (RVSM). This action is necessary to prevent near misses or collision with other aircraft during flight, due to incorrect altitude information.
AD 2001-24-01 · published Nov 30, 2001, effective Jan 4, 2002
Boeing Model 767 Series Airplanes Powered by Pratt & Whitney Model PW4000 Series Engines
This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 767 series airplanes, that requires a one-time detailed visual inspection of certain wire bundles located in the aft section of the strut forward fairing panel of both engine struts to detect chafing damage, and repair or replacement of wiring, if necessary. This amendment also requires replacement of wires repaired by splicing and damaged wires that require splicing, and replacement of the support brackets of the existing wire bundles with new brackets and clamps, which would terminate the existing requirements. The actions specified by this AD are intended to prevent the potential for dual wire faults from grounded, separated, or shorted wires; which could result in inadvertent takeoff thrust overboost, in- flight loss of thrust, or engine shutdown.
AD 2001-24-02 · published Nov 30, 2001, effective Jan 4, 2002
Boeing Model 707-100, -100B, -300, and -E3A (Military Airplanes); 727-100 and -200; 737-200, -200C, -300, -400, and -500; 747SP and 747SR; 747-100B, -200B, -200C, -200F, -300, -400, and -400D; 757-200 and -200PF; and 767-200 and -300 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 707-100, -100B, -300, and -E3A (military airplanes); 727-100 and -200; 737-200, -200C, -300, -400, and -500; 747SP and 747SR; 747-100B, -200B, -200C, -200F, -300, -400, and - 400D; 757-200 and -200PF; and 767-200 and -300 series airplanes. This AD requires inspection of the attachment of the shoulder restraint harness to the mounting bracket on certain observer and attendant seats to determine if a C-clip is used in the attachment, and corrective action, if necessary. This action is necessary to prevent detachment of the shoulder restraint harness of the attendant or observer seat from its mounting bracket during service, which could result in injury to the occupant of the seat. This action is intended to address the identified unsafe condition.
AD 2001-24-04 · published Nov 30, 2001, effective Jan 4, 2002
McDonnell Douglas Model MD-90-30 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model MD-90-30 series airplanes, that requires an inspection of the wiring in the left-hand tunnel area of the forward cargo compartment for evidence of chafing, and repair, if necessary. The actions specified by this AD are intended to prevent such chafing, which could result in subsequent shorting to structure, and consequent smoke and possible fire in the airplane. This action is intended to address the identified unsafe condition.
AD 2001-24-05 · published Nov 30, 2001, effective Jan 4, 2002
Airbus Model A319, A320, and A321 Series Airplanes
This amendment supersedes an existing airworthiness directive (AD), applicable to certain Airbus Model A320 series airplanes, that currently requires modification of the autopilot mode engagement/ disengagement lever of the rudder artificial feel unit. This amendment requires a different modification of the lever. This amendment also revises the applicability to include Airbus Model A319 and A321 series airplanes, as well as all Model A320 series airplanes. This amendment is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified by this AD are intended to prevent reduced controllability of the airplane due to the failure of the rudder artificial feel unit to disengage properly from autopilot mode during approach and landing.
AD 2001-24-06 · published Nov 30, 2001, effective Jan 4, 2002
Bombardier Model DHC-8-100, -200, and -300 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Bombardier Model DHC-8-100, -200, and -300 series airplanes, that requires installation of a backup pressure regulating valve on the oil pump of the propeller control unit (PCU) on both engines. The actions specified by this AD are intended to prevent a build-up of oil pressure in the oil pump of the PCU should the existing valve fail. Such failure of the pressure regulating valve could lead to oil leaks, fracture of the pump, inability to maintain engine oil pressure, and inability to feather the propeller, with consequent reduced controllability of the aircraft. This action is intended to address the identified unsafe condition.
AD 2001-19-51 · published Nov 23, 2001, effective Dec 10, 2001
Eurocopter France Model SA341G, SA342J, and SA-360C Helicopters
This document publishes in the Federal Register an amendment adopting Airworthiness Directive (AD) 2001-19-51, which was sent previously to all known U.S. owners and operators of Eurocopter France (ECF) Model SA341G, SA342J, and SA-360C helicopters by individual letters. This AD requires, before further flight, replacing a certain unairworthy main rotor head torsion tie bar (tie bar) with an airworthy tie bar. This AD also requires revising the limitations section of the maintenance manual by adding a life limit for certain tie bars. This AD is prompted by an accident involving an ECF Model SA341G helicopter due to the failure of a tie bar. The actions specified by this AD are intended to prevent failure of a tie bar, loss of a main rotor blade, and subsequent loss of control of the helicopter.
AD 2001-23-11 · published Nov 26, 2001, effective Dec 11, 2001
Eurocopter France Model EC 155B Helicopters
This amendment supersedes an airworthiness directive (AD) for Eurocopter France Model EC 155B helicopters that currently requires, before each flight, visually checking each sliding door to ensure that each door roller is inside its rail. This amendment requires modifying the cabin sliding door rails and replacing the roller fitting. This amendment is prompted by the development of a modification that mechanically restrains the roller within its rail. The actions specified by this AD are intended to prevent in-flight loss of a cabin sliding door, impact with the main rotor or fenestron, and subsequent loss of control of the helicopter.
AD 2001-22-18 · published Nov 13, 2001, effective Dec 18, 2001
Rolls-Royce, plc Models Tay 650-15 and 651-54 Turbofan Engines
This amendment adopts a new airworthiness directive (AD), that is applicable to Rolls-Royce, plc models Tay 650-15 and 651-54 turbofan engines. This amendment requires initial and repetitive visual and ultrasonic inspections of fan blades for cracks, and, if necessary, replacement with serviceable parts. In addition, this AD requires recording instances when engines are operated in a stabilized manner in newly prohibited ranges. This amendment is prompted by reports of fan blade failures. The actions specified by this AD are intended to prevent fan blade failures, which can result in an uncontained engine failure, engine fire, and damage to the airplane.
AD 2001-23-09 · published Nov 16, 2001, effective Dec 21, 2001
Honeywell International Inc. TFE731-2, -3, and -4 Series Turbofan Engines
This amendment supersedes two existing airworthiness directives (ADs), applicable to Honeywell International Inc. (formerly AlliedSignal Inc. and Garrett Turbine Engine Co.) TFE731-2, -3, and -4 series turbofan engines. Those AD's currently require removing certain fan rotor discs from service in accordance with a drawdown schedule, and establishing new fan rotor disc life limits. This amendment requires stricter life limits for certain fan rotor discs. This amendment is prompted by the availability of an improved fan rotor disc and by a reduction in the probability of fan rotor disc failure by terminating the life of the older, high-stressed, fan rotor disc. The actions specified in this AD are intended to prevent failure of the fan rotor disc due to fatigue cracking in the dovetail slots, which could result in in-flight engine shutdown, uncontained engine failure, and damage to the airplane.
AD 2001-23-02 · published Nov 19, 2001, effective Dec 24, 2001
Rolls-Royce plc RB211 Turbofan Engines
This amendment adopts a new airworthiness directive (AD), that is applicable to Rolls-Royce plc model RB211-535E4-37, RB211-535E4-B- 37, RB211-535C-37, RB211-535E4-B-75 and RB211-22B-02 turbofan engines. This amendment requires inspection of certain high pressure (HP) turbine disks, manufactured between 1989 and 1999, for cracks in the rim cooling air holes, and, if necessary, replacement with serviceable parts. This amendment is prompted by reports of cracks in two high life Trent 800 disk rim cooling air holes produced at the same manufacturing facility using the same tooling as the RB211 turbofan engine HP turbine disks. The actions specified by this AD are intended to prevent possible disk failure, which could result in an uncontained engine failure and damage to the aircraft.
AD 2001-23-08 · published Nov 19, 2001, effective Dec 24, 2001
Hartzell Propeller Inc. ( )HC-( )2Y( )-( ) Propellers
This amendment supersedes priority letter AD 90-02-23, that is applicable to certain Hartzell Propeller Inc. ( )HC-( )2Y( )-( ) propellers. That priority letter currently requires repetitive visual inspections of propeller hubs for cracks using a 10X glass and, if necessary, removal of cracked hubs and replacement with serviceable parts. This amendment changes the frequency and method of inspection by requiring initial and repetitive eddy current inspections (ECI) of the propeller hub fillet radius for cracks and requires that certain model propeller hubs be removed from service. In addition, this AD allows installation of an improved design propeller hub as terminating action to the repetitive ECI. This amendment is prompted by reports of cracked propeller hubs found in service after they had been inspected in accordance with the visual inspections required by the current AD. The actions specified in this AD are intended to prevent failure of the propeller hub resulting from cracks, that can cause blade separation and subsequent loss of aircraft control.
AD 2001-22-14 · published Nov 2, 2001, effective Dec 10, 2001
Overland Aviation Services Fire Extinguishing System Bottle Cartridges
This amendment adopts a new airworthiness directive (AD) that applies to certain Overland Aviation Services (OAS) fire extinguishing system bottle cartridges that were distributed during a certain time period and are installed on aircraft. This AD requires you to remove from service any of these fire extinguishing system bottle cartridges. This AD is the result of several incidents where the fire extinguishing system bottle cartridges activated with excessive energetic force. In one instance, the discharge valve outlet screen fractured and the screen material went through the distribution manifold. The actions specified by this AD are intended to prevent damage to fire extinguishing system components caused by a fire extinguishing system bottle cartridge activating with excessive energetic force, which could result in the fire extinguishing system operating improperly.
AD 2001-23-16 · published Nov 26, 2001, effective Dec 7, 2001
Aeromot-Industria Mecanico Metalurgica Itda. Models AMT-100 and AMT-200 Powered Sailplanes
This amendment adopts a new airworthiness directive (AD) that applies to certain Aeromot-Industria Mecanico Metalurgica Itda. (Aeromot) Models AMT-100 and AMT-200 powered sailplanes. This AD requires you to inspect (one-time) the main landing gear lever and elevator control rod for interference, warping, or incorrect gaps; and requires you to reconfigure or replace discrepant parts. This AD also requires you to report to the Federal Aviation Administration (FAA) any instances of interference, warping, or incorrect gaps. This AD is the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for Brazil. The actions specified by this AD are intended to detect and correct bending or warping in the main landing gear lever before it interferes with the elevator control rod. Such interference could result in the elevator control becoming jammed with consequent loss of control of the powered sailplane.
