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92-21-03: 92-21-03 FOKKER: Amendment 39-8383. Docket No. 92-NM-83-AD. Applicability: Model F28 series airplanes; serial numbers 11003 through 11161, inclusive, 11991, and 11992; certificated in any category. Compliance: Required as indicated, unless accomplished previously. To prevent potential failure of the wing-to-fuselage connection, accomplish the following: (a) Prior to the accumulation of 30,000 landings, or prior to June 1, 1997, whichever occurs later, install improved connection angles with reinforcement angles, in accordance with Fokker Service Bulletin F28/53-101, dated May 31, 1991. (b) Accomplishment of the installation required by paragraph (a) of this AD constitutes terminating action for the inspection identified as item 53-10-14 in the Fokker F28 Structural Integrity Program (SIP), which is required by AD 89-07-16 R1, Amendment 39-6444. (c) An alternative method of compliance or adjustment of the compliance time that provides an acceptable level of safety may be used if approved by the Manager, Standardization Branch, ANM-113, FAA, Transport Airplane Directorate. Operators shall submit their requests through an appropriate FAA Principal Maintenance Inspector, who may add comments and then send it to the Manager, Standardization Branch, ANM-113. NOTE: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Standardization Branch, ANM-113. (d) Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate the airplane to a location where the requirements of this AD can be accomplished. (e) The installation shall be done in accordance with Fokker Service Bulletin F28/53-101, dated May 31, 1991. This incorporation by reference was approved by the Director of the Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR Part 51. Copies may be obtained from Fokker Aircraft USA, Inc., 1199 North Fairfax Street, Alexandria, Virginia 22314. Copies may be inspected at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC. (f) This amendment becomes effective on November 24, 1992.
2000-03-18: This document adopts a new airworthiness directive (AD) that applies to all Partenavia Costruzioni Aeronauticas S.p.A. (Partenavia) Models AP68TP 300 "Spartacus" and AP68TP 600 "Viator" airplanes that are equipped with pneumatic deicing boots. This AD requires you to revise the Airplane Flight Manual (AFM) to include requirements for activating the airframe pneumatic deicing boots. This AD is the result of reports of in-flight incidents and an accident that occurred in icing conditions where the airframe pneumatic deicing boots were not activated. The actions specified by this AD are intended to assure that flightcrews have the information necessary to activate the pneumatic wing and tail deicing boots at the first signs of ice accumulation. Without this information, flightcrews could experience reduced controllability of the aircraft due to adverse aerodynamic effects of ice adhering to the airplane prior to the first deicing cycle.
50-17-02: 50-17-02 STINSON: Applies to All Model 108 Series Aircraft. Compliance required as indicated. A number of cases have been reported of broken core strands in the rudder cables where they pass over the pulley at fuselage Station 18.75 (first pulley aft of rudded pedals). To preclude failures, the following is therefore required: 1. Within the next 25 hours and at every 100 hours thereafter the following should be accomplished. Remove the rudder cables from the pulleys, bend the cables in a tight "U" where they pass over the pulley, being careful that permanent kinks are not formed, and inspect either visually or by touch. Replace all cables showing signs of breakage. 2. The above inspection may be discontinued and the normal inspections resumed if the following is done: Remove the AN 210-3A pulleys at fuselage Station 18.75; modify the pulley brackets and install larger pulleys, P/N 41001-2, and two cable guards, P/N SK253-2, in accordance with detailed instructions in PiperService Bulletin No. 114 or an equivalent modification.
2015-12-01: We are adopting a new airworthiness directive (AD) for Airbus Helicopters (previously Eurocopter France) Model AS355E, AS355F, AS355F1, and AS355F2 helicopters with a Fueltron flowmeter installed. This AD requires removing each flowmeter, replacing the fuel system hoses, and disabling the electrical connections for the flowmeter installation. This AD was prompted by a report of particle contamination creating an obstruction in a flowmeter which resulted in an uncontrolled flame-out of the engine. The actions of this AD are intended to prevent obstruction of the fuel supply to the flowmeter, which could result in engine flame-out and subsequent loss of control of the helicopter.
2000-11-04: This amendment adopts a new airworthiness directive (AD) that applies to certain Commander Aircraft Company (Commander) Model 114TC airplanes. This AD requires you to replace the existing Aeroquip V-band exhaust clamp with a new clamp of improved design. This AD is the result of reports of this clamp failing on 4 of the affected airplanes. This clamp attaches the exhaust stack to the turbocharger. The actions specified in this AD are intended to prevent the exhaust stack from detaching from the turbocharger due to failure of the V-band exhaust clamp. This could result in the release of high temperature gases inside the engine compartment with a consequent airplane cabin fire.
92-18-05: 92-18-05 AEROSPATIALE: Amendment 39-8349. Docket 91-NM-165-AD. Applicability: Model ATR42-300 and ATR42-320 series airplanes; as listed in Aerospatiale Service Bulletin ATR42-53-0043, Revision 4, dated April 30, 1991; certificated in any category. Compliance: Required as indicated, unless accomplished previously. To prevent the collapse of the main landing gear, accomplish the following: (a) Prior to the accumulation of 10,000 landings since new, or within 30 days after the effective date of this AD, whichever occurs later, accomplish the following in accordance with Aerospatiale Service Bulletin ATR42-53-0043, Revision 4, dated April 30, 1991: (1) Install a new machined reinforcement fitting (Modification 1281) on the left and right sides of the main landing gear (MLG) in accordance with the service bulletin. (2) Perform a one-time eddy current inspection of the fastener holes on the left and right sides of the MLG to detect fatigue cracks in accordance with the service bulletin. If any cracks are found, prior to further flight, repair in accordance with the service bulletin. (3) Install doublers on Stringer 15 at Frame 25 on the reinforcement plate in accordance with the service bulletin. NOTE: Previous editions of this service bulletin erroneously referred to Stringer 15 as Stringer 14. The doubler can only be installed at Stringer 15. (4) Perform cold working procedures of two fastener holes on the left and right sides of the MLG in accordance with the service bulletin. (b) Airplanes modified prior to the effective date of this AD in accordance with earlier versions of Aerospatiale Service Bulletin ATR42-53-0043 issued prior to Revision 4 need not be inspected or modified further. (c) An alternative method of compliance or adjustment of the compliance time that provides an acceptable level of safety may be used if approved by the Manager, Standardization Branch, ANM-113, FAA, Transport AirplaneDirectorate. Operators shall submit their requests through an appropriate FAA Principal Maintenance Inspector, who may add comments and then send it to the Manager, Standardization Branch. NOTE: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Standardization Branch. (d) Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate the airplane to a location where the requirements of this AD can be accomplished. (e) The installation, inspection, and cold working shall be done in accordance with Aerospatiale Service Bulletin ATR42-53-0043, Revision 4, dated April 30, 1991, which includes the following list of effective pages: Page Number Revision Level Date 1-2, 29 4 April 30, 1991 3-6, 10-28, 30-32 3 October 30, 1990 7-9 Original April 21, 1989 This incorporation by reference was approved by the Director of the Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR Part 51. Copies may be obtained from Aerospatiale, 316 Route de Bayonne, 31060 Toulouse, Cedex 03, France. Copies may be inspected at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; or at the Office of the Federal Register, 800 North Capitol Street, NW., Suite 700, Washington, DC. (f) This amendment becomes effective on October 13, 1992.
2015-11-08: We are superseding airworthiness directive (AD) 2014-02-08 for Agusta Model A109C, A109S, A109K2, A109E, and AW109SP helicopters. AD 2014-02-08 required inspecting the lock wires securing the tail rotor (T/R) duplex bearing locking nut (locking nut) to determine whether any lock wires are missing or damaged. This AD retains some of the requirements of AD 2014-02-08 but removes the terminating action, expands the applicability, and adds a daily pilot check. This AD was prompted by reports of loosening T/R locking nuts. These actions are intended to prevent failure of the T/R and subsequent loss of control of the helicopter.
2000-10-16: This amendment supersedes an existing airworthiness directive (AD), applicable to certain Airbus Model A319, A320, and A321 series airplanes, that currently requires repetitive inspections for discrepancies of the lock bolt for the pintle pin on the main landing gear (MLG), and follow-on corrective actions, if necessary. This amendment requires additional follow-on actions for certain airplanes. This amendment also provides for optional terminating action for the requirements of this 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 detect and correct a rotated, damaged, or missing lock bolt, which could result in disengagement of the pintle pin from the pintle fitting bearing, and consequent collapse of the MLG during landing.
2000-10-21: This amendment adopts a new airworthiness directive (AD) that is applicable to certain Boeing Model 737 series airplanes. This action requires a one-time general visual inspection of the seat locks and seat tracks of the flightcrew seats to ensure that the seats lock in position and to verify that lock nuts and bolts of adequate length are installed on the rear tracklock bracket, and corrective action, if necessary. This action is necessary to prevent uncommanded movement of the flightcrew seats during acceleration and take-off of the airplane, which could result in reduced controllability of the airplane. This action is intended to address the identified unsafe condition.
2015-11-02: We are superseding Airworthiness Directive (AD) 95-26-11 for all Lockheed Martin Corporation/Lockheed Martin Aeronautics Company Model L-1011 series airplanes. AD 95-26-11 required repetitive inspections to detect cracking of the fittings that attach the aft pressure bulkhead to the fuselage stringers, repetitive inspections to detect cracking of the fittings and of the splice tab of the aft pressure bulkhead, and corrective actions if necessary. This new AD requires repetitive inspections to detect cracking of the fittings that attach the aft pressure bulkhead to the fuselage stringers, repetitive inspections to detect cracking of the fittings and of the splice tab of the aft pressure bulkhead, repetitive inspections for cracking of [[Page 32442]] certain aft fuselage skin panels, a structural modification, a post- modification inspection program, and corrective actions if necessary. This AD was prompted by a determination that the fittings at stringer attachments tothe upper region of the aft pressure bulkhead are subject to widespread fatigue damage (WFD). We are issuing this AD to prevent simultaneous failure of multiple stringer end fittings through fatigue cracking at the aft pressure bulkhead, which could lead to rapid decompression of the airplane.
2000-11-01: This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model DC-9-80 and MD-90-30 series airplanes, and Model MD-88 airplanes, that requires a determination be made of whether, and at what locations, metallized polyethyleneteraphthalate (MPET) insulation blankets are installed, and replacement of MPET insulation blankets with new insulation blankets. This amendment is prompted by reports of in- flight and ground fires on certain airplanes manufactured with insulation blankets covered with MPET, which may contribute to the spread of a fire when ignition occurs from small ignition sources such as electrical arcing or sparking. The actions specified by this AD are intended to ensure that insulation blankets constructed of MPET are removed from the fuselage. Such insulation blankets could propagate a small fire that is the result of an otherwise harmless electrical arc and could lead to a much larger fire.
92-02-02: 92-02-02 BRITISH AEROSPACE: Amendment 39-8138. Docket 91-NM-203-AD. Supersedes AD 90-21-12, Amendment 39-6764. Applicability: Model ATP series airplanes, certificated in any category. Compliance: Required as indicated, unless accomplished previously. To prevent reduced structural integrity of the fuselage, accomplish the following: (a) Within 50 hours time-in-service after October 29, 1990 (the effective date of AD 90-21-12, Amendment 39-6764), and thereafter at intervals not to exceed 50 hours time-in-service, apply an icing inhibitor to the propeller blades in accordance with British Aerospace Service Bulletin ATP-61-2, Revision 1, dated October 31, 1989, or Revision 2, dated October 25, 1990, or Revision 3, dated April 19, 1991. (b) Installation of Modification 10129A (installation of ice guards on both the left and right sides of the fuselage) in accordance with British Aerospace Service Bulletin ATP-53-10, dated March 7, 1990; or installation of Modification 10174A (installation of a new propeller digital ice control timer unit and a new propeller blade and roller assembly) in accordance with British Aerospace Service Bulletin ATP-30-13, Revision 1, dated February 15, 1991, constitutes terminating action for the repetitive applications of icing inhibitor to the propeller blades as required by paragraph (a) of this AD. (c) An alternative method of compliance or adjustment of the compliance time, which provides an acceptable level of safety, may be used when approved by the Manager, Standardization Branch, ANM-113, FAA, Transport Airplane Directorate. NOTE: The request should be forwarded through an FAA Principal Maintenance Inspector, who may concur or comment and then send it to the Manager, Standardization Branch, ANM-113. (d) Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate the airplane to a location where the requirements of this AD can be accomplished. (e) Theicing inhibitor application requirements of this AD must be done in accordance with British Aerospace Service Bulletin ATP-61-2, Revision 1, dated October 31, 1989; or Revision 2, dated October 25, 1990; or Revision 3, dated April 19, 1991; which include the following list of effective pages: Service Bulletin Page number Revision Level Date ATP-61-2, Revision 1 1 1 October 31, 1989 2, 3 (Original) July 29, 1989 ATP-61-2, Revision 2 1, 2, 3 2 October 25, 1990 ATP-61-2, Revision 3 1, 2 3 April 19, 1991 3 2 October 25, 1990 The modifications specified in this AD must be done in accordance with British Aerospace Service Bulletin ATP-53-10, dated March 7, 1990 (for Modification 10129A); and British Aerospace Service Bulletin ATP-30-13, Revision 1, dated February 15, 1991 (for Modification 10174A). This incorporation by reference was approved by the Director of the Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR Part 51. Copies maybe obtained from British Aerospace, PLC, Librarian for Service Bulletins, P.O. Box 17414, Dulles International Airport, Washington, D.C. 20041-0414. Copies may be inspected at the FAA, Transport Airplane Directorate, 1601 Lind Avenue S.W., Renton, Washington; or at the Office of the Federal Register, 1100 L Street N.W., Room 8401, Washington, D.C. (f) This amendment (39-8138), AD 92-02-02, becomes effective on April 13, 1992.
2000-11-02: This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model DC-10-10F, DC-10-15, DC-10-30, DC-10-30F, and DC-10-40 series airplanes, and Model MD-11 and -11F series airplanes, that requires a determination be made of whether, and at what locations, metallized polyethyleneteraphthalate (MPET) insulation blankets are installed, and replacement of MPET insulation blankets with new insulation blankets. This amendment is prompted by reports of in-flight and ground fires on certain airplanes manufactured with insulation blankets covered with MPET, which may contribute to the spread of a fire when ignition occurs from small ignition sources such as electrical arcing or sparking. The actions specified by this AD are intended to ensure that insulation blankets constructed of MPET are removed from the fuselage. Such insulation blankets could propagate a small fire that is the result of an otherwise harmless electrical arc and could lead toa much larger fire.
93-05-06: 93-05-06 ACS PRODUCTS COMPANY AND GERDES PRODUCTS COMPANY: Amendment 39-8511. Docket 92-NM-165-AD. Applicability: ACS and Gerdes ignition switches; as installed in, but not limited to, Piper Model PA-38-112 series airplanes, Schweizer Model G-164 series (including Model G-164A, G-164B, and G-164C) airplanes, Schweizer Model 2-37 and 2-37A series airplanes, and the following Cessna airplanes; certificated in any category: Cessna Model Serial Numbers 150 15074428 through 15079405 A150 A1500389 through A1500734 F150 F15001024 through F15001428 FRA150 FRA1500212 through FRA1500336 152 15279406 through 15286033 A152 A1520735 through A1521049 F152 F15201429 through F15201980 FA152 FA1520337 through FA1520425 172 17261486 through 17276673 R172 R1722000 through R1723454 172RG 172RG0001 through 172RG1191 F172 F17201045 through F17202254 FR172 FR17200441 through FR17200675 177 17701890 through 17702752 177RG 177RG0342 through 177RG1366 F177RG F177RG0093 through F177RG0177 180 18052317 through 18053203 182 18261786 through 18268615 R182 R18200001 through R18202041 A182 A182-0137 through A182-0148 F182 F18200001 through F18200169 FR182 FR18200001 through FR18200070 185 18502154 through 18504448 U206 U20601980 through U20607020 207 20700222 through 20700788 210 21059893 through 21065009 P210 P21000001 through P21000874 Compliance: Required as indicated, unless accomplished previously. To prevent failure of ignition switches, accomplish the following: (a) Within 100 flight hours after the effective date of this AD, or at the next annual inspection, whichever occurs first, perform an inspection of the ignition switch to detect wear and corrosion, and lubricate the switch, in accordance with ACS Service Bulletin SB92-01, dated August 15, 1992; or Cessna Service Bulletin SEB91-5, Revision 1, June 14, 1991. If wear or corrosion is detected,prior to further flight, replace the switch in accordance with the service bulletin. Repeat this inspection and lubricate the ignition switch in accordance with the service bulletin, thereafter, at intervals not to exceed 2,000 flight hours. NOTE: ACS ignition switches that do not have a "start" position (models A-510-1 and A-510-5) or were manufactured on or after February 20, 1989, and have not accumulated 2,000 flight hours, need not be lubricated. The manufacture date is stamped on the switch body. These switches are identifiable by red paint in the screw heads on the back of the switch. However, manufacturer lubricated switches that have a "start" position, but do not have a starter solenoid diode, must be inspected and modified. (b) Within 100 flight hours after the effective date of this AD, or at the next annual inspection, whichever occurs first, inspect the ignition switch installation to determine if a diode or other surge suppresser is installed on the starter solenoid. If one is not installed, prior to further flight, install a starter solenoid diode in accordance with ACS Service Bulletin SB92-01, dated August 15, 1992; or Cessna Service Bulletin SEB91-5, Revision 1, dated June 14, 1991. NOTE: For operators using the Cessna service bulletin to install the diode in the starter solenoid: The procedures for installation are contained in Attachment to Service Bulletin SEB91-5R1, Revision 1, dated June 14, 1991. (c) An alternative method of compliance or adjustment of the compliance time that provides an acceptable level of safety may be used if approved by the Manager, Los Angeles Aircraft Certification Office (ACO), FAA, Transport Airplane Directorate. Operators shall submit their requests through an appropriate FAA Principal Maintenance Inspector, who may add comments and then send it to the Manager, Los Angeles ACO. NOTE: Information concerning the existence of approved alternative methods of compliance with this AD,if any, may be obtained from the Los Angeles ACO. (d) Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate the airplane to a location where the requirements of this AD can be accomplished. (e) The inspection, lubrication, replacement, and modification shall be done in accordance with ACS Service Bulletin SB92-01, dated August 15, 1992; or Cessna Service Bulletin SEB91-5, Revision 1, dated June 14, 1991, which includes Attachment to Service Bulletin SEB91-5R1, Revision 1, dated June 14, 1991. This incorporation by reference was approved by the Director of the Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR Part 51. Copies may be obtained from ACS Products Company, P.O. Box 152, 1585 Copper Drive, Lake Havasu City, Arizona 86403-0008; or Cessna Aircraft Company, Customer Services, P.O. Box 7704, Wichita, Kansas 67277. Copies may be inspected at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; or at the Los Angeles Aircraft Certification Office, 3229 East Spring Street, Long Beach, California; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC. (f) This amendment becomes effective on April 29, 1993.
91-25-05: 91-25-05 GULFSTREAM AEROSPACE CORPORATION: Amendment 39-8107. Docket No. 91-NM-236-AD. Applicability: Model G-1159A (G-III) series airplanes, serial numbers 357, and 402 through 498; and Model G-IV series airplanes, serial numbers 1000 through 1180; certificated in any category. Compliance: Required as indicated, unless previously accomplished. To prevent avionics system failures which would severely inhibit the ability of the flight crew to deal with adverse operating conditions, as well as their ability to conduct a safe flight and landing, accomplish the following: (a) Within 25 hours time-in-service after the effective date of this AD, perform a one-time inspection to detect chafing or damage of the electrical feeder cable located between the power distribution box and the co-pilot's junction box, in accordance with Gulfstream Alert Customer Bulletins No. 6A (for Model G-III series airplanes), or No. 7A (for Model G-IV series airplanes), both dated October1, 1991, as applicable. (b) If chafing or damage is detected as a result of the inspection required by paragraph (a) of this AD, prior to further flight, repair the electrical feeder cable in accordance with a manner approved by the Manager, Atlanta Aircraft Certification Office (ACO), FAA, Small Airplane Directorate. (c) An alternative method of compliance or adjustment of the compliance time, which provides an acceptable level of safety, may be used when approved by the Manager, Atlanta Aircraft Certification Office (ACO), FAA, Small Airplane Directorate. The request should be forwarded through an FAA Principal Maintenance or Avionics Inspector, who may concur or comment and then send it to the Manager, Atlanta ACO. (d) Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes to a base in order to comply with the requirements of this AD. (e) The inspection requirements shall be done in accordance with Gulfstream Alert Customer Bulletin No. 6A, dated October 1, 1991, or Gulfstream Alert Customer Bulletin No. 7A, dated October 1, 1991, as applicable. This incorporation by reference was approved by the Director of the Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR Part 51. Copies may be obtained from Gulfstream Aerospace Corporation, P.O. Box 2206, M/S D-10, Savannah, Georgia 31402-9980. Copies may be inspected at the FAA, Transport Airplane Directorate, 1601 Lind Avenue S.W., Renton, Washington; at the FAA, Small Airplane Directorate, Atlanta Aircraft Certification Office, 1669 Phoenix Parkway, Suite 210C, Atlanta, Georgia; or at the Office of the Federal Register, 1100 L Street N.W., Room 8401, Washington, D.C. (f) This amendment (39-8107, AD 91-25-05) becomes effective on December 18, 1991.
2015-11-04: We are adopting a new airworthiness directive (AD) for all The Boeing Company Model 707 airplanes, and Model 720 and 720B series airplanes. This AD was prompted by reports of cracked midspar fittings on the inboard and outboard nacelle struts. This AD requires repetitive inspections for cracking of the inboard and outboard midspar fittings of the nacelle struts and of the torque bulkhead, midspar chords, drag fitting, and front spar support, and doing applicable related investigative and corrective actions; replacing the midspar fittings; and doing other specified actions. We are issuing this AD to detect and correct cracking in the midspar fittings of the inboard and outboard nacelle struts, which could result in the loss of the structural integrity of the midspar fitting. This condition could cause an unsafe separation of the engine and consequent wing fire.
2000-10-22: This amendment adopts a new airworthiness directive (AD) that applies to certain REVO, Incorporated (REVO) Models Lake LA-4, Lake LA-4A, Lake LA-4P, Lake LA-4-200, and Lake Model 250 airplanes. This AD requires you to: inspect the left and right wing upper and lower spar doublers for cracks; replace any cracked parts; and incorporate a modification kit. This AD is the result of a report of a fatigue crack found at the second most inboard wing attachment bolt hole on one of the affected airplanes. Similar fatigue cracking has since been reported on seven more of the affected airplanes, including incidents where the fatigue cracking occurred on airplanes with less than 500 hours time- in-service (TIS). The actions specified by this AD are intended to detect and correct cracks in the wing spars, which could result in the wing separating from the airplane with consequent loss of control.
2000-10-12: This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 747-400 series airplanes. This action requires repetitive inspections to detect damage or deflection of the crew rest heat exchanger, and follow-on actions, if necessary. This amendment is prompted by reports of cracking and buckling of the front edge of the crew rest heat exchanger on several airplanes. The actions specified in this AD are intended to detect and correct damage or deflection of the crew rest heat exchanger, which could result in jamming of the rudder or elevator control cables, and consequent reduced controllability of the airplane.
2000-10-10: This amendment supersedes an existing airworthiness directive (AD) that applies to Eurocopter France Model AS-350B, BA, B1, B2, and D, and Model AS-355E, F, F1, F2, and N helicopters and requires inspecting the main gearbox suspension bidirectional cross-beam (cross-beam) for cracks, and replacing the cross-beam if a crack is found. This amendment requires the same inspections as the existing AD, but adds the time intervals for performing repetitive dye-penetrant inspections on cross-beams with 5,000 or more hours time-in-service (TIS). This amendment is prompted by the discovery that time intervals for performing the required dye-penetrant inspections are not included in the existing AD. The actions specified by this AD are intended to prevent failure of the cross-beam that could lead to rotation of the main gearbox, resulting in severe vibrations and a subsequent forced landing.
2015-10-04: We are superseding Airworthiness Directive (AD) 2012-09-09 for all International Aero Engines AG (IAE) V2500-A1, V2525-D5, and V2528- D5 turbofan engines, and certain serial numbers (S/Ns) of IAE V2522-A5, V2524-A5, V2527-A5, V2527E-A5, V2527M-A5, V2530-A5, and V2533-A5 turbofan engines. AD 2012-09-09 required cleaning, eddy current inspection (ECI) or fluorescent penetrant inspection (FPI), and initial and repetitive ultrasonic inspections (USIs) of certain high-pressure compressor (HPC) stage 3 to 8 drums, as well as replacement of the drum attachment nuts. This new AD expands the affected population for initial and repetitive USIs of the HPC stage 3 to 8 drum, revises the inspection intervals, requires performing ECI or FPI, requires removal of the affected attachment nuts and any HPC stage 3 to 8 drum found cracked, and adds a mandatory terminating action. This AD was prompted by the discovery that additional attachment nuts for certain HPC stage 3 to 8 drums are affected.We are issuing this AD to prevent failure of the HPC stage 3 to 8 drum, which could result in uncontained drum failure, damage to the engine, and damage to the airplane.
59-05-07: 59-05-07 VICKERS: Applies to All Viscount Model 745D Which Have PB.10 Automatic Pilot Installed. Compliance required as soon as possible but not later than December 1, 1959. In order to permit the pilots to positively disengage the trim servo clutch either by the emergency cutoff buttons on the pilots control wheel, or by the mechanical disconnect lever, a control relay (Plessey P/N 7LZ.107352 or P/N 7CZ.97508/1) should be installed in the A.C. junction box. The British Air Registration Board considers this mandatory. The FAA concurs with this action and considers compliance therewith mandatory. (Vickers-Armstrongs Modification Bulletin No. 2703 and associated Modification Leaflet covers this subject.)
60-23-03: 60-23-03 PIAGGIO: Amdt. 220 Part 507 Federal Register November 8, 1960. Applies to All Model P.136-L2 Aircraft. Compliance required within 25 hours' time in service from the effective date of this directive. In order to prevent hazardous quantities of oil from flowing into the engine compartment in the event of a fire, the engine oil system lines must be rerouted in accordance with Piaggio Change Order No. 36-55 which covers this same subject. This directive effective December 8, 1960.
2000-10-14: This amendment adopts a new airworthiness directive (AD) for BHTC Model 222, 222B, 222U, and 230 helicopters that requires inspecting each flapping bearing to yoke attachment bolt (bolt) and replacing each bolt that shows thread damage, shank wear, or corrosion pitting with an airworthy bolt. This amendment is prompted by the discovery of a fractured bolt during a post-flight inspection. The actions specified by this AD are intended to prevent a fracture of a bolt, failure of the bearing and yoke interface, and subsequent loss of control of the helicopter.
95-13-02: 95-13-02 TWIN COMMANDER AIRCRAFT CORPORATION: Amendment 39-9283; Docket No. 94-CE-27-AD. Applicability: The following airplane models and serial numbers, certificated in any category, that do not have the vertical stabilizer modified in accordance with the ACCOMPLISHMENT INSTRUCTIONS: PART II - MODIFICATION section of Twin Commander Service Bulletin (SB) No. 218, dated May 19, 1994, including Revision Notices 1 and 2, dated July 11, 1994, and September 23, 1994, respectively: Model Serial Numbers 685 12000 through 12066 690 11000 through 11079 690A 11100 through 11344 690B 11350 through 11566 690C 11600 through 11735 690D 15001 through 15042 695 95000 through 95084 695A 96001 through 96100 NOTE 1: This AD applies to each airplane identified in the preceding applicability provision, regardless of whether it has been modified, altered, or repaired in the area subject to the requirements of this AD. For airplanes that have been modified, altered, or repaired so that the performance of the requirements of this AD is affected, the owner/operator must use the authority provided in paragraph (f) of this AD to request approval from the FAA. This approval may address either no action, if the current configuration eliminates the unsafe condition, or different actions necessary to address the unsafe condition described in this AD. Such a request should include an assessment of the effect of the changed configuration on the unsafe condition addressed by this AD. In no case does the presence of any modification, alteration, or repair remove any airplane from the applicability of this AD. Compliance: Required upon the accumulation of 2,000 hours time-in-service (TIS) on a vertical stabilizer or within the next 50 hours TIS after the effective date of this AD, whichever occurs later, unless already accomplished, and thereafter as indicated in the body of this AD. To prevent failure of the vertical stabilizer as a result of cracks, which, if notdetected and corrected, could result in loss of control of the airplane, accomplish the following: (a) Inspect the vertical stabilizer for cracks in accordance with the ACCOMPLISHMENT INSTRUCTIONS: PART I - INSPECTION section of Twin Commander SB No. 218, dated May 19, 1994, including Revision Notices 1 and 2, dated July 11, 1994, and September 23, 1994, respectively. (b) If damage or cracks are found within the limits of Figures 1 and 2 of the service information referenced above, prior to further flight, modify the vertical stabilizer in accordance with the ACCOMPLISHMENT INSTRUCTIONS: PART II - MODIFICATION section of Twin Commander SB No. 218, dated May 19, 1994, including Revision Notices 1 and 2, dated July 11, 1994, and September 23, 1994, respectively. (c) If damage or cracks are found outside the limits referenced in Figures 1 and 2 of the service information referenced above or if cracks intersect, prior to further flight, replace the damaged parts with new parts in accordance with the applicable maintenance manual instructions. The requirements of this AD still apply when the damaged parts are replaced, unless the stabilizer is modified as specified in paragraph (b) of this AD. (d) If no cracks are found, accomplish one of the following: (1) Reinspect at intervals not to exceed 500 hours TIS, and modify any damaged or cracked vertical stabilizer as specified in paragraph (b) and (c) of this AD; or (2) Prior to further flight, modify the vertical stabilizer in accordance with the ACCOMPLISHMENT INSTRUCTIONS: PART II - MODIFICATION section of Twin Commander SB No. 218, dated May 19, 1994, including Revision Notices 1 and 2, dated July 11, 1994, and September 23, 1994, respectively. This modification may be accomplished prior to further flight after any repetitive inspection as terminating action for the repetitive inspections provided no cracks are found. (e) Special flight permits may be issued in accordance with sections21.197 and 21.199 of the Federal Aviation Regulations (14 CFR 21.197 and 21.199) to operate the airplane to a location where the requirements of this AD can be accomplished. (f) An alternative method of compliance or adjustment of the initial or repetitive compliance times that provides an equivalent level of safety may be approved by the Manager, Seattle Aircraft Certification Office (ACO), FAA, Northwest Mountain Region, 1601 Lind Avenue S.W., Renton, Washington 98055-4056. The request shall be forwarded through an appropriate FAA Maintenance Inspector, who may add comments and then send it to the Manager, Seattle ACO. NOTE 2: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Seattle ACO. (g) The inspections and modification required by this AD shall be done in accordance with Twin Commander Service Bulletin 218, dated May 19, 1994, including Revision Notices 1 and 2, dated July 11, 1994, and September 23, 1994, respectively. This incorporation by reference was approved by the Director of the Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. Copies may be obtained from Twin Commander Aircraft Corporation, 19003 59th Drive, NE., Arlington, Washington 98223. Copies may be inspected at the FAA, Central Region, Office of the Assistant Chief Counsel, Room 1558, 601 E. 12th Street, Kansas City, Missouri, or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC. (h) This amendment becomes effective on July 22, 1995.
2000-10-13: This amendment adopts a new airworthiness directive (AD) applicable to Eurocopter France Model SA-365N, SA-365N1, AS-365N2 and AS-365N3 helicopters. This action requires inspecting the installation of each window panel on the enlarged sliding door (door). If any window panel is installed on the outside of the door, this AD requires installing and sealing the window panel on the inside. This amendment is prompted by the loss of a window panel in flight that was incorrectly sealed with the window installed on the outside of the door. This condition, if not corrected, could result in loss of a window panel in flight. The actions specified in this AD are intended to prevent loss of a window panel, impact with a main rotor blade, and subsequent loss of control of the helicopter.