51 Airworthiness Directives: 41 airplane, 2 rotorcraft, 5 engine, 1 propeller, 1 appliance, 1 glider.
AD 2001-06-10 · published Apr 2, 2001, effective May 7, 2001
Airbus Model A300 B4-601, A300 B4-603, A300 B4-620, A300 B4-605R, A300 B4-622R, and A300 F4-605R Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to all Airbus Model A300 B4-601, A300 B4-603, A300 B4-620, A300 B4-605R, A300 B4-622R, and A300 F4-605R airplanes. This AD requires repetitive high frequency eddy current (HFEC) or rototest inspections to detect cracking in the area surrounding the frame feet attachment holes between fuselage frames (FR) 41 and FR46; installation of new fasteners for certain airplanes; and follow-on corrective actions, if necessary. This AD 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 cracking of the center section of the fuselage, which could result in rupture of the frame foot and reduced structural integrity of the airplane.
AD 2001-06-11 · published Apr 2, 2001, effective Apr 17, 2001
Airbus Model A330-301, -321, -322, -341, and -342 Series Airplanes
This amendment adopts a new airworthiness directive (AD) that is applicable to certain Airbus Model A330-301, -321, -322, -341, and - 342 series airplanes. This action requires replacement of the existing fasteners on the vertical web of stringers 13 and 20 of both wings with interference fasteners. This action is necessary to prevent fatigue cracking of the wing bottom skin and vertical webs, which could result in reduced structural integrity of the wing. This action is intended to address the identified unsafe condition.
AD 2001-06-12 · published Apr 2, 2001, effective May 7, 2001
Boeing Model 767 Series Airplanes Powered by General Electric Engines
This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 767 series airplanes powered by General Electric engines, that requires modification of the nacelle strut and wing structure. This amendment is prompted by reports indicating that the actual operational loads applied to the nacelle are higher than the analytical loads that were used during the initial design. Such an increase in loading can lead to fatigue cracking in the primary strut structure prior to an airplane reaching its design service objective. The actions specified by this AD are intended to prevent fatigue cracking in the primary strut structure and consequent reduced structural integrity of the strut.
AD 2001-06-13 · published Apr 2, 2001, effective May 7, 2001
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 inspecting the endcaps of the main landing gear selector valve for leaks of hydraulic oil and, if leaks are detected, replacing the leaking endcaps or the entire selector valve. This amendment also requires eventual replacement or rework of certain selector valves, which will terminate the repetitive inspections. This amendment is prompted by a report of the collapse of the main landing gear due to an external leak of hydraulic oil in the landing gear selector valve, resulting from a fracture of the endcap. The actions specified by this AD are intended to prevent leaks of hydraulic oil from the main landing gear selector valve, which could result in the collapse of the main landing gear.
AD 2001-06-14 · published Apr 2, 2001, effective May 7, 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 installation of a new circuit breaker and related wiring, and relocation of circuit breaker 12FG, if applicable. The actions specified by this AD are intended to prevent loss of the nose wheel steering and reduced controllability of the airplane on the ground. This action is intended to address the identified unsafe condition.
AD 2001-06-15 · published Apr 2, 2001, effective May 7, 2001
Boeing Model 737-600, -700, -700C, and -800 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 737-600, -700, -700C, and -800 series airplanes, that requires inspections of the fasteners in the elevator balance panel assemblies to detect various discrepancies; and corrective actions, if necessary. This amendment is prompted by a report that an elevator balance panel was found disconnected from the horizontal stabilizer due to the improper installation of fasteners during production. The actions specified by this AD are intended to prevent jamming, restricting, or binding of the elevator control surfaces due to loose or missing fasteners, which could make the movement of the elevator difficult and decrease aerodynamic control of the airplane.
AD 2001-07-02 · published Apr 5, 2001, effective Apr 20, 2001
Airbus Model A330-301, -321, -322, -341, and -342 Series Airplanes; and Model A340-211, -212, -213, -311, -312, and -313 Series Airplanes
This amendment adopts a new airworthiness directive (AD) that is applicable to certain Airbus Model A330 and A340 series airplanes. This action requires a one-time inspection for cracks on the attachment holes of the doorstop fitting on the aft passenger/crew doors; repair, if necessary; and modification of the attachment holes. This action is necessary to detect and prevent fatigue cracking of the attachment holes for doorstop fitting number 5, which could result in reduced structural integrity of the door frames. This action is intended to address the identified unsafe condition.
AD 2001-07-04 · published Apr 10, 2001, effective May 15, 2001
Cessna Model 750 Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Cessna Model 750 airplanes, that requires removal of a certain existing bulkhead web doubler, installation of left and right bulkhead web doublers, and enlargement of the lightening holes. This action is necessary to prevent jamming of the roll control system, due to inadequate clearance between the control cable and the web, which could result in reduced controllability of the airplane.
AD 2001-07-05 · published Apr 10, 2001, effective May 15, 2001
Boeing Model 767 Series Airplanes Powered by General Electric or Pratt & Whitney Engines
This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 767 series airplanes powered by General Electric or Pratt & Whitney engines, that requires repetitive inspections to detect discrepancies of the aft-most fastener holes in the horizontal tangs of the midspar fitting of the strut, and corrective actions, if necessary. This AD also provides an optional terminating action for the repetitive inspections. These actions are necessary to prevent fatigue cracking in primary strut structure and reduced structural integrity of the strut, which could result in separation of the strut and engine. This action is intended to address the identified unsafe condition.
AD 2001-07-06 · published Apr 10, 2001, effective May 15, 2001
Saab Model SAAB 2000 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Saab Model SAAB 2000 series airplanes, that requires a modification involving nondestructive test inspections of the 34 fastener holes in each rear wing spar, corrective action, if necessary, and cold working of the holes to increase fatigue life of the rear spar web. 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 fatigue cracking, which could result in fuel leakage and reduced structural integrity of the wings.
AD 2001-07-08 · published Apr 10, 2001, effective Apr 25, 2001
McDonnell Douglas Model MD-11 Series Airplanes Equipped With Pratt & Whitney Model PW4400 Series Engines
This amendment adopts a new airworthiness directive (AD) that is applicable to all McDonnell Douglas Model MD-11 series airplanes equipped with Pratt & Whitney Model PW4400 series engines. This action requires revising the Airplane Flight Manual (AFM) to advise the flight crew of applicable operational limits. This action is necessary to ensure that the flight crew is informed of applicable limitations in airplane performance, and to prevent reduced acceleration and climb performance relative to performance data in the AFM, which could result in the airplane overrunning the end of the runway during takeoff or landing, or impacting obstacles or terrain. This action is intended to address the identified unsafe condition.
AD 2001-07-07 · published Apr 11, 2001, effective May 16, 2001
Fokker Model F.28 Mark 0070 and Mark 0100 Series Airplanes
This amendment supersedes an existing airworthiness directive (AD), applicable to all Fokker Model F.28 Mark 0070 and Mark 0100 series airplanes, that currently requires revising the Airplane Flight Manual (AFM) to provide the flightcrew with instructions not to arm the liftdumper system prior to commanding the landing gear to extend. For Model F.28 Mark 0100 series airplanes, the existing AD also requires modification of the grounds of the shielding of the wheelspeed sensor wiring of the main landing gear (MLG) and installation of new electrical grounds for the wheelspeed sensor channel of the anti-skid control box of the MLG. This amendment removes the previous revision of the AFM and requires a new limitation and a new warning. 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 inadvertent deployment of the liftdumpers during approach for landing or reduced brake pressure during low speed taxiing, and consequent reduced controllability and performance of the airplane.
AD 2001-07-10 · published Apr 12, 2001, effective Apr 27, 2001
McDonnell Douglas Model DC-9-81, -82, -83, and -87 Series Airplanes, Model MD-88 Airplanes, and Model MD-90-30 Series Airplanes
This amendment adopts a new airworthiness directive (AD) that is applicable to certain McDonnell Douglas Model DC-9-81, -82, -83, and -87 series airplanes, Model MD-88 airplanes, and Model MD-90-30 series airplanes. This action requires a revision to the applicable Airplane Flight Manual (AFM) to provide the flightcrew with the appropriate landing distance and flap positions, if applicable, for wet or icy runways. This AD also provides for an optional terminating action for the applicable AFM revision. This action is necessary to prevent the flightcrew from performing a scheduled landing on a runway of potentially insufficient length due to failure of the weight-on-wheels spoiler lockout mechanism system and possible inactivation of the autospoiler actuator, which could result in the airplane overrunning the end of the runway during landing on a wet or icy runway. This action is intended to address the identified unsafe condition.
AD 2000-23-04 R1 · published Apr 16, 2001, effective Dec 19, 2000
Aerospatiale Model ATR42-500 Series Airplanes
This amendment revises an existing airworthiness directive (AD), applicable to all Aerospatiale Model ATR42-500 series airplanes. This amendment continues to require revising the Airworthiness Limitations Section of the Instructions for Continued Airworthiness to incorporate life limits for certain items and inspections to detect fatigue cracking in certain structures. This amendment also adds information pertaining to certain material incorporated by reference. This amendment is prompted by issuance of a new revision of the "Time Limits" section of the ATR42-400/500 Maintenance Planning Document, which specifies new inspections and compliance times for inspection and replacement actions. This amendment is intended to ensure that fatigue cracking of certain structural elements is detected and corrected; such fatigue cracking could adversely affect the structural integrity of these airplanes.
AD 2001-07-11 · published Apr 16, 2001, effective May 1, 2001
Learjet Model 23, 24, 25, 28, 29, 31, 35, 36, and 55 Series Airplanes
This amendment adopts a new airworthiness directive (AD) that is applicable to all Learjet Model 23, 24, 25, 28, 29, 31, 35, 36, and 55 series airplanes. This action requires an inspection to determine if tires on the main landing gear have a certain part number and certain serial numbers, and replacement with a tire having a part number that does not contain those certain serial numbers, if necessary. This action is necessary to prevent separation of the tread of main landing gear tires, which could cause damage to the structure and major systems of the airplane, and consequent reduced controllability of the airplane on the ground during takeoff and landing. This action is intended to address the identified unsafe condition.
AD 2001-08-08 · published Apr 20, 2001, effective Jun 7, 2001
Raytheon Aircraft Company Beech Models 35-C33A, E33A, E33C, F33A, F33C, S35, V35, V35A, V35B, 36, and A36 Airplanes
This amendment adopts a new airworthiness directive (AD) that applies to all Raytheon Aircraft Company (Raytheon) Beech Models 35- C33A, E33A, E33C, F33A, F33C, S35, V35, V35A, V35B, 36, and A36 airplanes that incorporate a certain Teledyne Continental engine configuration. This AD requires you to repetitively replace the existing Aeroquip V-band exhaust clamp. The actions specified by this AD are intended to prevent the tailpipe from detaching from the turbocharger due to failure of the V-band exhaust clamp. Clamp failure could result in the release of high temperature gases inside the engine compartment with the potential for a consequent fire in the engine compartment.
AD 2001-08-09 · published Apr 20, 2001, effective May 7, 2001
Boeing Model 737-600, -700, -800, and -700C Series Airplanes
This amendment supersedes an existing airworthiness directive (AD), applicable to certain Boeing Model 737-600, -700, -800, and -700C series airplanes, that currently requires initial and repetitive inspections of the elevator tab assembly to detect any damage or discrepancy; and corrective actions, if necessary. This amendment clarifies the applicability and certain requirements of the AD. This amendment is prompted by requests for such clarification. The actions specified in this AD are intended to prevent excessive in-flight vibrations of the elevator tab, which could lead to loss of the elevator tab and reduced controllability of the airplane.
AD 2001-08-02 · published Apr 23, 2001, effective May 8, 2001
Boeing Model 707 and 720 Series Airplanes
This amendment supersedes two existing airworthiness directives (AD), applicable to all Boeing Model 707 and 720 series airplanes, that currently require inspections of the upper chords of the wing front and rear spars, repair, if necessary, and application of corrosion inhibitor to the inspected areas. This amendment requires repetitive inspections of the upper and lower chords on the wing front and rear spars, repair, if necessary, and application of corrosion inhibitor to the inspected areas. These actions are necessary to find and fix stress corrosion cracking of the upper and lower chords on the wing front and rear spars, which could result in reduced structural integrity of the wing. This action is intended to address the identified unsafe condition.
AD 2001-08-03 · published Apr 23, 2001, effective May 8, 2001
Boeing Model 777-200 Series Airplanes
This amendment adopts a new airworthiness directive (AD) that is applicable to certain Boeing Model 777-200 series airplanes. This action requires repetitive inspections of the upper housing assembly of the forward trunnion of the main landing gear (MLG) for discrepancies (migrated or missing wearplates, loose or fractured attachment screws); and corrective action, if necessary. This action also provides for an optional modification of the upper housing assembly for airplanes without discrepant wearplates, which would end the repetitive inspections. This action is necessary to prevent migration or loss of the upper housing wearplate, which could result in loss of the MLG during the takeoff roll; consequent damage to the airplane structure; and injury to flight crew, passengers, or ground personnel. This action is intended to address the identified unsafe condition.
AD 2001-08-05 · published Apr 23, 2001, effective May 29, 2001
Bombardier Model DHC-7-100, -101, -102, and -103 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Bombardier Model DHC-7-100, -101, -102, and -103 series airplanes, that requires inspecting the endcaps of the main landing gear selector valve for leaks of hydraulic oil and, if leaks are detected, replacing the leaking endcaps or the entire selector valve. This amendment also requires eventual replacement or rework of certain selector valves, which would terminate the repetitive inspections. This amendment is prompted by a report of the collapse of the main landing gear due to an external leak of hydraulic oil in the landing gear selector valve, resulting from a fracture of the endcap. The actions specified by this AD are intended to prevent leaks of hydraulic oil from the main landing gear selector valve, which could result in the collapse of the main landing gear.
AD 2001-08-06 · published Apr 23, 2001, effective May 29, 2001
Airbus Model A300 B4-620, A310-203, A310-221, and A310-222 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A300 B4-620, A310-203, A310-221, and A310-222 series airplanes, that requires repetitive inspections of fuselage frame 07 in the upper frame section assemblies of the lateral cockpit windows, and corrective action, if necessary. Accomplishment of certain corrective actions extends the repetitive inspection interval. The actions specified by this AD are intended to detect and correct fatigue cracking in that area, which could result in reduced structural integrity of the airplane.
AD 2001-08-07 · published Apr 23, 2001, effective May 29, 2001
Boeing Model 737-200 and -300 Series Airplanes Equipped with a Main Deck Cargo Door Installed in Accordance with Supplemental Type Certificate (STC) SA2969SO
This amendment supersedes an existing airworthiness directive (AD), applicable to certain Boeing Model 737-200 and -300 series airplanes, that currently requires a one-time inspection to detect cracks of the lower frames and reinforcing angles of the main deck cargo door where the door latch fittings attach between certain fuselage stations and water lines, and replacement of any cracked part with a new part having the same part number. That AD was prompted by reports that, during the inspections required by the existing AD, cracks were found in the reinforcing angles of the main deck cargo door frame. This amendment requires, among other actions, an inspection to detect cracks of the lower frames and reinforcing angles of the main deck cargo door; replacement of any lower frame or reinforcing angle of the main deck cargo door when it has reached its maximum life limit. The actions specified by this AD are intended to detect and correct cracking of the lower portion of the main deck cargo door frames, which could result in sudden depressurization, loss or opening of the main deck cargo door during flight, and loss of control of the airplane.
AD 2000-26-09 R1 · published Apr 25, 2001, effective Feb 7, 2001
Dornier Model 328-100 Series Airplanes
This amendment revises an existing airworthiness directive (AD), applicable to all Dornier Model 328-100 series airplanes, that currently requires revising the Airworthiness Limitations Section of the Instructions for Continued Airworthiness to incorporate life limits for certain items and inspections to detect fatigue cracking in certain structures. This amendment adds information pertaining to certain material incorporated by reference. This amendment is prompted by the issuance of revisions to the Dornier 328 Airworthiness Limitations Document. The actions specified by this AD are intended to ensure that fatigue cracking of certain structural elements is detected and corrected; such fatigue cracking could adversely affect the structural integrity of these airplanes.
AD 2001-08-24 · published Apr 25, 2001, effective May 10, 2001
Boeing Model 737 Series Airplanes
This amendment adopts a new airworthiness directive (AD) that is applicable to all Boeing Model 737 series airplanes. This action requires revising the Airplane Flight Manual to prohibit extended dry operation of the center tank fuel pumps (with no fuel passing through the pumps). This action is necessary to prevent ignition of fuel vapors due to the generation of sparks and a potential ignition source inside the center tank caused by metal-to-metal contact during dry fuel pump operation, which could result in a fire or explosion of the fuel tank. This action is intended to address the identified unsafe condition.
AD 2001-08-10 · published Apr 26, 2001, effective Jun 12, 2001
Aerostar Aircraft Corporation Models PA-60-600 (Aerostar 600), PA-60-601 (Aerostar 601), PA-60-601P (Aerostar 601P), PA-60-602P (Aerostar 602P), and PA-60-700P (Aerostar 700P) Airplanes
This amendment adopts a new airworthiness directive (AD) that applies to certain Aerostar Aircraft Corporation (Aerostar) Models PA- 60-600, PA-60-601, PA-60-601P, PA-60-602P, and PA-60-700P airplanes. This AD requires you to replace both of the existing main landing gear lower side brace assemblies with parts of improved design. This AD is the result of several reports of cracking of the main landing gear lower side brace at the upper bolt lug discovered on preflight inspection. The actions specified by this AD are intended to correct damage or cracks in the main landing gear lower side brace at the upper bolt lug where the upper and lower side braces connect. This could result in failure of the main landing gear lower side brace. Such failure could lead to loss of control of the airplane.
AD 2001-08-11 · published Apr 26, 2001, effective May 31, 2001
Aerospatiale Model ATR42-200, -300, and -320 Series Airplanes
This amendment supersedes an existing airworthiness directive (AD), applicable to all Aerospatiale Model ATR42-300 and -320 series airplanes, that currently requires repetitive ultrasonic inspections to detect cracking of certain lugs on the main landing gear (MLG), replacement of cracked lugs with new or serviceable parts, and a follow-on inspection; and provides for an optional terminating action for the repetitive inspections. This amendment removes that terminating action and requires new repetitive inspections of the rubber sealant to detect shearing, and corrective action, if necessary. This action also requires new one-time visual and fluorescent penetrant inspections to detect discrepancies of certain lugs, and refurbishment of the MLG barrel and swing lever assemblies, which terminates the requirements of this AD. This action also revises the applicability of the existing AD. 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 discrepancies of the MLG barrel lower lugs, which could result in reduced structural integrity and possible collapse of the MLG.
AD 2001-08-12 · published Apr 26, 2001, effective May 11, 2001
Airbus Model A340 Series Airplanes Equipped With CFM International CFM56-5C Engines
This amendment adopts a new airworthiness directive (AD) that is applicable to certain Model A340 series airplanes. This action requires repetitive inspections of the pivoting door roller fittings of the upper and lower thrust reversers for cracks, and corrective action, if necessary. This action is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. This action is intended to detect and correct cracking of the pivoting door roller fittings of the thrust reversers, which could result in failure of the primary locking mechanism of the thrust reversers during flight, leading to reduced controllability of the airplane. This action is intended to address the identified unsafe condition.
AD 2001-08-16 · published Apr 26, 2001, effective May 31, 2001
McDonnell Douglas Model DC-8 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model DC-8 series airplanes, that requires a one-time inspection to determine the manufacturer of the circuit breakers, and corrective action, if necessary. This amendment is prompted by reports of smoke and electrical odor in the flight compartment and cabin area as a result of failure of circuit breakers. The actions specified by this AD are intended to prevent internal overheating and arcing of the circuit breakers and airplane wiring due to long-term use and breakdown of internal components of the circuit breakers, which could result in smoke and fire in the flight compartment and main cabin.
AD 2001-08-17 · published Apr 26, 2001, effective May 31, 2001
McDonnell Douglas Model DC-8 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model DC-8 series airplanes, that requires an inspection of the antifogging or heating wiring to detect chafing or damage, as applicable; inspection of the insulation blankets to detect damage; and repair, if necessary. This amendment also requires revising the clearview window heating wiring installations. This amendment is prompted by a report of an electrical short that resulted in damage to the antifogging circuit wiring and insulation blanket above the Captain's clearview window. The actions specified by this AD are intended to prevent chafed and damaged wires as a result of a sharp bend and restricted space between the fuselage frame and the clearview window in the full open position, which could result in an electrical short, damage to the antifogging circuit wiring and insulation blanket, and consequent smoke and fire in the flight deck.
AD 2001-08-18 · published Apr 26, 2001, effective May 31, 2001
McDonnell Douglas Model DC-8 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model DC-8 series airplanes, that requires installation of heat shrinkable tubing or application of Peel-Kote on each terminal connection of all cabin lighting switches in the forward and aft cabin electrical service panels. This action is necessary to prevent a short circuit within the cabin electrical service panel due to a foreign object being lodged between the terminals of a cabin light switch. Such a short circuit could result in overheating and damage to light circuits, and consequent smoke and fire in the main cabin of the airplane. This action is intended to address the identified unsafe condition.
AD 2001-08-19 · published Apr 26, 2001, effective May 31, 2001
McDonnell Douglas Model DC-8 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model DC-8 series airplanes, that requires replacing certain transformer ballast assemblies in the first officer's console and electrical power center with certain new, improved ballast assemblies. This action is necessary to prevent overheating of ballast transformers due to high power demands resulting from aging, which could result in smoke in the cockpit. This action is intended to address the identified unsafe condition.
AD 2001-08-20 · published Apr 26, 2001, effective May 31, 2001
McDonnell Douglas Model DC-8 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model DC-8 series airplanes, that requires replacing the toilet flushing circuit breakers of the lavatory with new circuit breakers, and marking applicable nameplates. This action is necessary to prevent overheating of the flush pump motor, which could result in damage to the flush pump motor cover, and consequent smoke in the lavatory area. This action is intended to address the identified unsafe condition.
AD 2001-08-26 · published Apr 26, 2001, effective May 11, 2001
Airbus Model A319 and A320 Series Airplanes Equipped with Elevator and Aileron Computer (ELAC) L80 Standard
This amendment adopts a new airworthiness directive (AD) that is applicable to certain Airbus Model A319 and A320 series airplanes. This action requires revising the Airplane Flight Manual (AFM) to specify procedures for landing under certain conditions of gusty winds and turbulence. This action is prompted by a report of a recent hard landing on a Model A320 series airplane equipped with ELAC L80 standard, which was caused by activation of the high angle-of-attack protection during a landing in gusty winds and turbulence. This action is necessary to prevent activation of the high angle-of-attack protection during final approach for landing, which could result in loss of ability to flare properly during landings. This action is intended to address the identified unsafe condition.
AD 2001-08-21 · published Apr 27, 2001, effective Jun 1, 2001
Lockheed Model L-1011-385 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to all Lockheed Model L-1011-385 series airplanes, that requires a visual inspection of the fuel level control switch, the fuel level control switch wiring harness, and the wiring harness conduit for damage, wear or chafing, broken or missing O-rings, or indications of electrical arcing. This amendment also requires replacement of a certain conduit in the fuel level control switch wiring harness, installation of electrical sleeving over the fuel level control switch wiring harness, and installation of the fuel level control switch which has been so modified. The actions specified by this AD are intended to prevent chafing of the fuel level control switch wiring harness, which could cause arcing and result in a fire in the fuel tank.
AD 2001-08-22 · published Apr 27, 2001, effective Jun 1, 2001
Boeing Model 767-200 and -300 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 767-200 and -300 series airplanes, that requires replacement of the existing potable water fill line tube with a new hose. This action is necessary to prevent fracture of a clamshell coupling on the potable water fill line, which could cause water to flow into the aft cargo compartment. A large amount of water in the cargo compartment could cause large shifts in the airplane's center of gravity, which could result in reduced controllability of the airplane. This action is intended to address the identified unsafe condition.
AD 2001-08-23 · published Apr 27, 2001, effective May 14, 2001
Boeing Model 767-200 Series Airplanes
This amendment adopts a new airworthiness directive (AD) that is applicable to certain Boeing Model 767-200 series airplanes. This action requires repetitive inspections for cracking of the outboard pitch load fittings of the wing front spar, and corrective action, if necessary. This action also provides a terminating action for the repetitive inspections, which is optional for uncracked pitch load fittings. This action is necessary to find and fix cracking of the outboard pitch load fittings of the wing front spar, which could lead to loss of the upper link load path and result in separation of the strut and engine from the airplane. This action is intended to address the identified unsafe condition.
AD 2001-08-25 · published Apr 27, 2001, effective May 14, 2001
Airbus Model A330-301, -321, -322, and -342 Series Airplanes and Airbus Model A340 Series Airplanes
This amendment adopts a new airworthiness directive (AD) that is applicable to certain Airbus Model A330-301, -321, -322, and -342 series airplanes and certain Airbus Model A340 series airplanes. This action requires reinforcement of the wing structure at the inboard pylon rear pickup area. This action is necessary to prevent fatigue cracking of the bottom skin and reinforcing plate of the wing due to bending, which could lead to reduced structural integrity of the airplane wing. This action is intended to address the identified unsafe condition.
AD 2001-08-27 · published Apr 27, 2001, effective May 14, 2001
Lockheed Model L-1011 Series Airplanes
This amendment adopts a new airworthiness directive (AD) that is applicable to certain Lockheed Model L-1011 series airplanes. This action requires inspection of the windshield heat wire bundle for chafing or damage, and inspection of the harness clamps of the wire bundle for damage; and corrective actions, if necessary. For certain airplanes, this action also requires rerouting of the windshield heat wire bundle. This action is necessary to prevent chafing or damage of the windshield heat wire bundle, which could cause arcing and result in smoke and fire in the cockpit. This action is intended to address the identified unsafe condition.
AD 2001-08-28 · published Apr 27, 2001, effective Jun 1, 2001
Boeing Model 767 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 767 series airplanes, that requires revising the Airworthiness Limitations Section of the maintenance manual (767 Airworthiness Limitations Instructions (ALI)). The revision will incorporate into the ALI certain inspections and compliance times to detect fatigue cracking of principal structural elements (PSE). This amendment is prompted by analysis of data that identified specific initial inspection thresholds and repetitive inspection intervals for certain PSE's to be added to the ALI. The actions specified by this AD are intended to ensure that fatigue cracking of various PSE's is detected and corrected; such fatigue cracking could adversely affect the structural integrity of these airplanes.
AD 2001-09-04 · published Apr 30, 2001, effective May 15, 2001
Dornier Model 328-300 Series Airplanes Equipped with Motive Flow Check Valves Having Part Number 106-0007-01
<RM>This amendment adopts a new airworthiness directive (AD) that is applicable to certain Dornier Model 328-300 series airplanes. This action requires repetitive inspections of motive flow check valves and adjacent parts for fuel leaks, and replacement of the valves, if leaks are detected. This action is necessary to prevent leakage of fuel from the motive flow check valves, which could result in fuel vapors coming into contact with fuel ignition sources. This action is intended to address the identified unsafe condition.
AD 2001-09-06 · published Apr 30, 2001, effective May 18, 2001
Cessna Aircraft Company Models 206H and T206H Airplanes
<RM>This amendment adopts a new airworthiness directive (AD) that applies to certain Cessna Aircraft Company (Cessna) Models 206H and T206H airplanes. This AD requires you to visually inspect the horizontal stabilizer attachment reinforcement brackets for the existence of seam welds and replace any reinforcement bracket found without seam welds. This AD is the result of a report that these parts were manufactured without seam welds. The actions specified by this AD are intended to detect and replace structurally deficient horizontal stabilizer attachment brackets. Continued use of such brackets could result in structural failure of the horizontal stabilizer with reduced or loss of control of the airplane.
AD 2001-07-09 · published Apr 16, 2001, effective May 1, 2001
MD Helicopters Inc. Model MD-900 Helicopters
This amendment supersedes an existing emergency airworthiness directive (AD) that applies to MD Helicopters Inc. (MDHI) Model MD-900 helicopters. That emergency AD requires, within 6 hours time-in-service (TIS), or before further flight after January 31, 2000, whichever occurs first, inspecting the main rotor upper hub assembly drive plate attachment flange (flange) and determining the torque of each flange nut (nut). If a crack is found, the hub assembly must be replaced before further flight. The emergency AD also requires, within 25 hours TIS or before further flight after January 31, 2000, whichever occurs first, inspecting the hub assembly and verifying that the torque on the nuts is correct. Replacing a cracked hub assembly with an airworthy hub assembly is required before further flight. This amendment requires the same actions as the existing emergency AD but removes the January compliance dates and corrects errors in the existing emergency AD. This amendment is prompted by the discovery that there are several errors in the emergency AD. The actions specified by this AD are intended to prevent failure of the hub assembly, loss of drive to the main rotor, and subsequent loss of control of the helicopter.
AD 2001-08-04 · published Apr 18, 2001, effective May 3, 2001
Bell Helicopter Textron Inc. Model 205A-1, 205B, 212, 412, 412CF, and 412EP Helicopters
This amendment supersedes an existing airworthiness directive (AD) for Bell Helicopter Textron Inc. (BHTI) Model 205A-1, 205B, 212, 412, and 412CF helicopters. That AD currently requires inspecting the locking washer on each main rotor actuator (actuator) for twisting or damage to the tab and replacing any locking washer that has a twisted or damaged tab. Replacing certain locking washers, regardless of condition, is also required within a specified time period. Installing a certain airworthy locking device on each actuator constitutes terminating action for the requirements of that AD. This amendment requires the same actions as the existing AD but adds the BHTI Model 412EP helicopters to the applicability. This amendment is prompted by the discovery that the BHTI Model 412EP helicopter was inadvertently omitted from the existing AD. The actions specified by this AD are intended to prevent an actuator piston from unthreading from its rod end, loss of control of the main rotor, and subsequent loss of control of the helicopter.
AD 2001-08-51 · published Apr 10, 2001
CFM International, S.A. Engines
AD 2001-08-52 · published Apr 13, 2001
Pratt & Whitney Division Engines
AD 2001-08-14 · published Apr 26, 2001, effective May 31, 2001
Turbomeca S.A. Arrius Models 2B, 2B1, and 2F Turboshaft Engines
This amendment adopts a new airworthiness directive (AD), that is applicable to Turbomeca S.A. Arrius Models 2B, 2B1, and 2F turboshaft engines. This amendment requires the replacement of the right injector half manifold, left injector half manifold, and privilege injector pipe. This amendment is prompted by reports from the Direction Generale de L'Aviation Civile (DGAC), which is the airworthiness authority for France, of partially or totally blocked fuel injection manifolds, which were found during inspections at a repair workshop. The actions specified by this AD are intended to prevent engine flameout during rapid deceleration, or the inability to maintain the 2.5 minutes one engine inoperative (OEI) rating. The actions are also intended to prevent air path cracks, due to blockage of the fuel injection manifolds.
AD 2001-08-15 · published Apr 27, 2001, effective May 14, 2001
Rolls-Royce Corporation (Formerly Allison Engine Company) AE 3007 Series Turbofan Engines
This amendment adopts a new airworthiness directive (AD) that is applicable to Rolls-Royce Corporation (formerly Allison Engine Company) AE 3007A, AE 3007A1/1, AE 3007A1/2, AE 3007A1, AE 3007A1/3, AE 3007A1P, and AE 3007A3 turbofan engines. This action requires initial and repetitive inspections for bearing material contamination of the engine oil system. This amendment is prompted by reports of rapid failures of the No. 1 bearing. The actions specified in this AD are intended to detect the rapid failure of the No. 1 bearing, which could result in smoke in the cabin and an uncommanded in-flight engine shutdown.
AD 2001-09-07 · published Apr 27, 2001, effective May 14, 2001
Pratt and Whitney PW4000 Series Turbofan Engines
This amendment supersedes an emergency airworthiness directive (AD) 2001-08-52 that was sent previously to all known U.S. owners and operators of Pratt and Whitney (PW) model PW4050, PW4052, PW4056, PW4060, PW4060A, PW4060C, PW4062, PW4152, PW4156, PW4156A, PW4158, PW4160, PW4460, PW4462, and PW4650 turbofan engines by individual letters. That emergency AD requires limiting the number of PW4000 engines, listed by serial number (SN) in that AD, with potentially reduced stability to no more than one engine on each airplane; removal of certain PW4000 engines, listed by SN in this AD, before exceeding cyclic limits that are determined by airplane model; removal of certain PW4000 engines, listed by SN in this AD, that have a high pressure compressor with 1,500 or more cycles-since-overhaul (CSO) greater than the high pressure turbine (HPT) CSO; and requires a minimum rebuild standard for engines that are returned to service. This amendment supersedes emergency AD 2001-08-52 to provide clarifications and additions to the compliance and applicability of certain paragraphs of AD 2001-08-52. This AD is prompted by a report of a dual-engine surge event during take-off on an Airbus Industrie A300 airplane. The actions specified by this AD are intended to prevent multiple-engine power losses due to high pressure compressor (HPC) surge at a critical phase of flight such as takeoff or climb.
AD 2001-07-03 · published Apr 4, 2001, effective Jun 4, 2001
Hartzell Propeller Inc. Y-Shank Series Propellers
This amendment adopts a new airworthiness directive (AD) that is applicable to certain Hartzell Propeller Inc. Y-shank series propellers, identified by hub serial numbers, that were returned to service by Brothers Aero Services Company, Inc. (BASCO). This AD requires maintenance actions amounting to an overhaul of affected propellers. This amendment is prompted by reports of propellers returned to service by BASCO as overhauled that had numerous unsafe conditions after being returned to service by BASCO. The actions specified by this AD are intended to prevent propeller failure of the propellers returned to service by BASCO, and possible loss of airplane control.
AD 2001-08-01 · published Apr 17, 2001, effective May 10, 2001
JanAero Devices 14D11 and 23D04 Series Fuel Regulator and Shutoff Valves
This amendment adopts a new airworthiness directive (AD) that applies to certain JanAero Devices (JanAero) fuel regulator and shutoff valves used with JanAero combustion heaters that are installed on airplanes. This AD requires you to visually inspect and pressure test for leaks, and, if leaks are found, replace the fuel regulator and shutoff valve used with JanAero combustion heaters. This AD is the result of numerous reports of fuel regulator and shutoff valves leaking fuel. The actions specified by this AD are intended to prevent fuel leakage in airplanes with these combustion heaters with a consequent hazardous fire.
AD 2001-07-01 · published Apr 5, 2001, effective May 26, 2001
DG Flugzeugbau GmbH Model DG-800B Sailplanes
This amendment adopts a new airworthiness directive (AD) that applies to certain DG Flugzeugbau GmbH (DG Flugzeugbau) Model DG-800B sailplanes. This AD requires you to install an additional filter for the primer valve; inspect and align the exhaust system; modify the placement of the fuel lines if the fuel filter is installed at the front mounting point of the spindle drive; and secure the gas strut piston rod end using Loctite if the piston rod does rotate. This AD is the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for Germany. The actions specified by this AD are intended to prevent failure of the fuel line, exhaust system, and piston rod of the gas strut, which could result in failure of the engine. Such failure could lead to loss of power during critical stages of flight.
