Results
2008-23-09: We are adopting a new airworthiness directive (AD) for certain Boeing transport category airplanes. This AD requires replacing any insulation blanket constructed of polyethyleneteraphthalate (PET) film, ORCON Orcofilm® AN-26 (hereafter "AN-26''), with a new insulation blanket. This AD results from reports of in-flight and ground fires on certain airplanes manufactured with insulation blankets covered with AN-26, which may contribute to the spread of a fire when ignition occurs from sources such as electrical arcing or sparking. We are issuing this AD to ensure that insulation blankets constructed of AN-26 are removed from the fuselage. Such insulation blankets could ignite and propagate a fire that is the result of electrical arcing or sparking.
98-13-02: This amendment adopts a new airworthiness directive (AD) that applies to Raytheon Aircraft Company (Raytheon) Models 35, A35, B35, and 35R airplanes (commonly referred to as Beech Models 35, A35, B35, and 35R airplanes). This AD requires fabricating a placard that restricts the never exceed speed (Vne) to no more than 144 miles per hour (MPH) or 125 knots (KTS) indicated airspeed (IAS), and installing this placard on the instrument panel within the pilot s clear view. This AD also requires marking a red line on the airspeed indicator glass at 144 MPH (125 KTS), marking a white slippage mark on the outside surface of the airspeed indicator between the glass and case, and inserting a copy of this AD into the Limitations Section of the airplane flight manual (AFM). This AD is the result of several occurrences of in-flight vibration on the affected airplanes. The actions specified by this AD are intended to prevent in-flight vibrations caused by the affected airplanes operating at excessive speeds, which could result in airplane damage and possible loss of control of the airplane. Comments for inclusion in the Rules Docket must be received on or before August 10, 1998.
2020-15-09: The FAA is adopting a new airworthiness directive (AD) for all Airbus SAS Model A330-941 airplanes. This AD was prompted by a report that seven spoiler servo-controls (SSCs) lost hydraulic locking function due to a sheared seal on the blocking valve. This AD requires repetitive operational tests of the hydraulic locking function on each SSC and replacement if necessary, as specified in a European Union Aviation Safety Agency (EASA), which is incorporated by reference. The FAA is issuing this AD to address the unsafe condition on these products.
85-14-07: 85-14-07 AEROSPATIALE (formerly SUD): Amendment 39-5094. Applies to all Caravelle SE-210 Models I, III, and VIR airplanes, certificated in any category, which do not embody Modification 1753. Accomplish the following, unless previously accomplished: A. Prior to the accumulation of 7000 landings or before the next 100 landings after the effective date of this AD, whichever occurs later, inspect the wing rib 44 web and angle doubler in accordance with SUD Service Bulletin 57-64 dated December 12, 1978. B. Repeat the inspections of paragraph A., above, at intervals not to exceed: 1. rib 44 lower cap - 10,000 landings 2. webs and doublers - 3,000 landings. C. Parts found cracked must be repaired prior to further flight. D. Alternate means of compliance which provide an acceptable level of safety may be used when approved by the Manager, Seattle Aircraft Certification Office, FAA, Northwest Mountain Region. E. Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes to a base for the accomplishment of inspections and/or modifications required by this AD. This amendment becomes effective August 16, 1985.
2003-18-06: This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A319-131 and -132; A320-231, -232, and -233; and A321-131 and -231 series airplanes, that requires installing new anti-swivel plates and weights on the engine fan cowl door latches and a new hold-open device. This action is necessary to prevent separation of the engine fan cowl door from the airplane in flight, which could result in damage to the airplane and hazards to persons or property on the ground. This action is intended to address the identified unsafe condition.
2008-22-15: We are superseding an existing airworthiness directive (AD) for the products listed above. This AD results from mandatory continuing airworthiness information (MCAI) originated by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as: Investigations after a CAS (crew alerting system) message "ENG 1 FIRE DETECT FAIL'' that occurred on an in-service aircraft revealed that the detector threshold tolerances could not permit to identify the failure of one single engine fire detector loop out of the two present on each engine. The fire detection system integrity is therefore not correctly monitored. * * * * * We are issuing this AD to require actions to correct the unsafe condition on these products. DATES: This AD becomes effective December 11, 2008. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in thisAD as of December 11, 2008. The Director of the Federal Register approved the incorporation by reference of Dassault Service Bulletin F2000EX-137, Revision 1, dated December 7, 2006, listed in this AD as of February 2, 2007 (72 FR 2177, January 18, 2007).
2008-23-03: We are adopting a new airworthiness directive (AD) for the products listed above. This AD results from mandatory continuing airworthiness information (MCAI) issued by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as: This Airworthiness Directive (AD) is prompted by a potential problem with the freedom of the brake pedals of some PC-6 series aircraft. The freedom of the brake pedals could be prevented because of an insufficient clearance between the rudder bar lugs on a few aircraft. In such conditions, it is possible that the master brake cylinder is not re-filled with the fluid from the reservoir, which can lead to a degradation of brake effectiveness. Mostly during landing, this can lead to difficulties with the directional control of the aircraft on ground and could cause a runway excursion. We are issuing this AD to require actions to correct the unsafe condition on these products.
2020-15-12: The FAA is superseding Airworthiness Directive (AD) 2018-08-02 for all Rolls-Royce Deutschland Ltd & Co KG (RRD) Trent 1000-A2, Trent 1000-AE2, Trent 1000-C2, Trent 1000-CE2, Trent 1000-D2, Trent 1000-E2, Trent 1000-G2, Trent 1000-H2, Trent 1000-J2, Trent 1000-K2, and Trent 1000-L2 model turbofan engines. AD 2018-08-02 required initial and repetitive ultrasonic or visual inspections of the intermediate- pressure compressor (IPC) stage 1 rotor blades, IPC stage 2 rotor blades, and IPC shaft stage 2 dovetail posts, and removal of any cracked parts from service. This AD requires new inspections based on updated inspection thresholds and intervals for these IPC parts. This AD also adds an optional terminating action, amends the asymmetric power condition for engine inspection, and requires an inspection after a cabin depressurization event. This AD was prompted by IPC blade separations resulting in engine failures. Subsequently, the manufacturer identified the need to add new inspections and an optional terminating action, amend the asymmetric power condition for engine inspection, and require an inspection after a cabin depressurization event. The FAA is issuing this AD to address the unsafe condition on these products.
2007-19-18: We are adopting a new airworthiness directive (AD) for the products listed above. This AD results from mandatory continuing airworthiness information (MCAI) issued by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as: The digital engine indicating system (DEI-NT) and associated control unit must get their latest software update. It has been found out in operation, that some combinations of system states while pressing switches can cause electrical damages to the system. A new software update is mandated to correct this deficiency and to incorporate additional safety functions to the system. We are issuing this AD to require actions to correct the unsafe condition on these products.
94-08-05: This amendment adopts a new airworthiness directive (AD), applicable to General Electric Company (GE) CF6-45/-50 series turbofan engines, that requires installation of a fan stator case stiffening ring assembly, and a new stage one fan shroud. This amendment is prompted by a report of an uncontained stage one fan blade failure, which resulted in an inflight engine shutdown, and damage to the aircraft. The actions specified by this AD are intended to prevent an uncontained stage one fan blade failure, which can result in an inflight engine shutdown, and damage to the aircraft.
83-17-03: 83-17-03 BRITISH AEROSPACE AIRCRAFT GROUP: Amendment 39-4709. Applies to all Model H.S. 748 series 2A airplanes certificated in all categories. To prevent wing structural failure accomplish the following, unless already accomplished: A. For airplanes with wing fuel tanks extending outboard beyond rib 350.366, within the next 1,500 hours or six months time in service, whichever occurs first after the effective date of this AD, inspect the rib/stringer bracket fasteners of the wing bottom surface at rib 224.366 and at stringers 4 and 6 at all ribs on each side of wing access panels W3 to W12 except W10, and perform the actions described in paragraph 2, Accomplishment Instructions, of British Aerospace Aircraft Group H.S. 748 Service Bulletin 57/62 dated June 1980. B. Within the next 500 hours or 60 days time in service, whichever occurs first after the effective date of this AD, inspect the rib/stringer bracket fasteners of wing bottom surface rib 16.071 and stringers 9, 10, 11, and 12 and perform the actions described in paragraph 2, Accomplishment Instructions, of British Aerospace Aircraft Group H.S. 748 Service Bulletin 57/63 dated June 1980. C. Alternate means of compliance which provide an equivalent level of safety may be used when approved by the Manager, Seattle Aircraft Certification Office, FAA, Northwest Mountain Region. Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes to a base for the accomplishment of inspections and/or modifications required by this AD. This amendment becomes effective September 19, 1983.
84-09-05: 84-09-05 BURKHART-GROB FLUGZEUGBAU INDUSTRIESTRABE: Amendment 39-4849. Applies to Model G102 ASTIR CS sailplanes, serial numbers 1001 through 1536 inclusive, certificated in any category. Compliance is required within the next 100 hours time in service, or within 120 days, whichever occurs first, after the effective date of this AD, unless already accomplished. To prevent bolt and pin failure, install modified spheric locking bolt, P/N 102-3500.21, and special nut, P/N 102-3510.21, in the forward horizontal stabilizer connection to the vertical stabilizer, and install new locking pins, P/N 102-2142.46, in the aft connecting plate for the horizontal stabilizer in accordance with instruction 1 and 2 of Grob Technical Information TM 306-17, dated June 10, 1981, or an FAA approved equivalent. Equivalent means of compliance may be approved by the Manager, Aircraft Certification Staff, AEU-100, Europe, Africa and Middle East Office, FAA, c/o American Embassy, Brussels, Belgium. The Burkhart Grob Flugzeugbau Industriestrabe Technical Information TM 306-17, dated June 10, 1981, identified and described in this directive is incorporated herein and made a part hereof pursuant to 5 U.S.C. 552(a)(1). All persons affected by this directive who have not already received this document from the manufacturer may obtain copies upon request to Burkhart Grob Flugzeugbau Industriestrabe, D-8948 Mindelheim-Mattsies, West Germany or upon request to Burkhart Grob of America, Inc., 1070 Navajo Drive, Bluffton, Ohio. These documents also may be examined at the Office of the Regional Counsel, 12 New England Executive Park, Burlington, Massachusetts 01803. This amendment becomes effective on May 3, 1984.
82-13-06: 82-13-06 SCHWEIZER (GULFSTREAM AMERICAN-GRUMMAN): Amendment 39-4410. Applies to Models G-164B (S/N 1B thru 656B), G-164C (S/N 1C thru 44C), and G164D (S/N 1D thru 16D) airplanes certificated in any category. COMPLIANCE: Required as indicated unless already accomplished. To detect elongation of the aileron cable attach holes and to eliminate the possibility of P/N A1450-281 bushings becoming dislodged from the aileron bellcrank, accomplish the following: a) Within 25 hours time-in-service after the effective date of this AD and every 12 months thereafter, on airplanes not modified in accordance with Gulfstream American Service Bulletin No. 75 (either original issuance or Revision "A" dated January 25, 1980), visually inspect the aileron bellcrank for elongation of the aileron cable attach holes per Part A of the revised service bulletin. If excessive elongation is found, prior to further flight, modify or replace the aileron bellcrank in accordance with Parts B and C of the revised service bulletin. b) Within 25 hours time-in-service after the effective date of this AD, on airplanes that have been modified in accordance with the original issue of Gulfstream American AG-CAT Service Bulletin No. 75, visually inspect the aileron bellcranks and if the bushings are loose or have less than .230 inch edge distance, replace the aileron bellcrank in accordance with Part D of Revision "A" of the Service Bulletin dated January 25, 1980. c) The repetitive inspections required by paragraph a) of this AD may be discontinued upon accomplishing the modifications described in Parts B and C of Gulfstream American AG-CAT Service Bulletin No. 75, Revision "A", dated January 25, 1980. d) Upon request, with substantiating data submitted through an FAA Maintenance Inspector, the compliance times specified in this AD may be adjusted by the Chief, New York Aircraft Certification Office, FAA, JFK International Airport, Jamaica, New York 11430. e) Aircraft may be flown in accordance with FAR 21.197 to a location where this AD may be accomplished. f) An equivalent method of compliance with this AD may be used if approved by the Chief, New York Aircraft Certification Office, FAA, JFK International Airport, Jamaica, New York 11430. This amendment supersedes Amendment 39-3882 (44 FR 11034) AD 80-17-08, effective August 15, 1980. This Amendment becomes effective on July 5, 1982.
2007-19-04: We are adopting a new airworthiness directive (AD) for the products listed above. This AD results from mandatory continuing airworthiness information (MCAI) originated by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as: Further to cases of parking brake loss at the gate, a pressure switch system had been introduced on some A300-600 aircraft. The aim of this modification was to recover pedals braking authority if parking brake is not efficient, without having to set the parking brake handle to OFF. However, it appears that in case of failure of the pressure switch system, there is the risk of double (normal and alternate) pressurization of the brakes potentially leading to undetected residual braking, which may lead to a loss of performances of the aircraft at Take-Off. The loss of performance could result in runway overrun or impact with obstacles or terrain during takeoff. We are issuing this AD to require actions to correct the unsafe condition on these products.
2020-15-11: The FAA is adopting a new airworthiness directive (AD) for PZL Swidnik S.A. Model PZL W-3A helicopters. This AD requires repetitively inspecting the main rotor (M/R) vibration absorber star and depending on the inspection outcome, performing more in-depth inspections and repairing, replacing, or removing the vibration absorber star from service. This AD was prompted by a report of corrosion detected on an M/R vibration absorber star. The actions of this AD are intended to address an unsafe condition on these products.
84-06-01: 84-06-01 AIRBUS INDUSTRIE: Amendment 39-4832. Applies to Model A300 B2 and B4 series airplanes, certificated in all categories. To prevent failure of the flap and slat control linkages, within 120 days after the effective date of this AD or upon reaching the landing thresholds specified in the service bulletins, whichever occurs later, accomplish the following, unless previously accomplished: A. Inspect, repair, and modify, as necessary, the slat and flap linkages in accordance with the service bulletins listed below: Airbus Industrie A300-27-151, Revision 4, dated December 20, 1982; Airbus Industrie A300-27-159, Revision 2, dated December 20, 1982; Airbus Industrie A300-27-158, Revision 1, dated March 9, 1982; Airbus Industrie A300-27-101, Revision 2, dated March 2, 1982; Lucas Aerospace 704-27-599, Revision 1, dated September 25, 1981; Lucas Aerospace 704-27-1053, Revision 1, dated October 11, 1982; and Lucas Aerospace 704-27-602, Revision 1, dated November 27, 1981. B. Alternate means of compliance which provide an equivalent level of safety may be used when approved by the Manager, Seattle Aircraft Certification Office, FAA, Northwest Mountain Region. C. Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes to a base for the accomplishment of inspections and/or modifications required by this AD. This amendment becomes effective May 14, 1984.
94-06-09: This document publishes in the Federal Register an amendment adopting airworthiness directive (AD) 94-06-09 that was sent previously to all known U.S. owners and operators of Teledyne Continental Motors (TCM) (formerly Bendix) SC-20, SC-200, and S-1200 series magnetos by individual letters. This AD requires inspection to determine if capacitors that may have an intermittent open circuit condition are installed in magnetos, and replacement, if necessary, with serviceable capacitors. This amendment is prompted by reports that TCM produced and delivered magneto capacitors that have the potential for an intermittent open circuit condition that may exist between the internal through-lead and the p-lead stud terminal. The actions specified by this AD are intended to prevent possible injury or death to ground personnel due to a non-grounded magneto.
84-11-01: 84-11-01 HUGHES HELICOPTERS, INC. (HUGHES HELICOPTERS): Amendment 39-4870. Applies to certain Model 369D and 369E helicopters certificated in all categories. Compliance is required within 10 hours time in service after the effective date of this AD, unless already accomplished. To prevent interference or binding and possible loss of longitudinal cyclic control in flight, accomplish the following: For Hughes Helicopters, Inc., Model 369D, Serial No. 110871D only, and Model 369E Helicopters, Serial Nos. 0001E through 0027E, 0029E through 0036E, and 0038E through 0043E, with longitudinal mixer control rod Part Number (P/N) 369A7011, and doubler P/N 369D22509-51 installed. (a) Comply with procedures a., b., and d. through k. under PART I of Hughes Helicopters, Inc., Mandatory Service Information Notice EN-13 or equivalent procedures approved under paragraph (c) of this AD. NOTE: Procedure c. under PART I concerns an inspection for proper number of rivets in P/N 369D22509-21. Compliance with this procedure and installation of rivets are recommended. (b) If the control rod is damaged or control rod clearance is less than 0.21 inch, while performing procedures f. or g. under PART I or approved equivalent procedures, comply with PART II of Mandatory Service Information Notice EN-13 or an equivalent method approved under paragraph (c) of this AD. (c) Alternative inspections, modifications, or other actions which provide an equivalent level of safety may be used when approved by the Manager, Western Aircraft Certification Office, Hawthorne, California. (d) Special flight permits may be issued in accordance with Federal Aviation Regulations 21.197 and 21.199 to ferry aircraft to a maintenance base in order to comply with the requirements of this AD. This amendment becomes effective May 31, 1984.
2020-15-06: The FAA is adopting a new airworthiness directive (AD) for certain PZL Swidnik S.A. (PZL) Model W-3A helicopters. This AD requires repetitive inspections of the main transmission (Main XSMN) case for a crack, and depending on the inspection outcome, removing the WR-3 Main XSMN from service before further flight. This AD was prompted by a report of cracks in a Main XSMN case. The actions of this AD are intended to address an unsafe condition on these products.
2003-18-05: This amendment supersedes an existing airworthiness directive (AD), applicable to certain Boeing Model 757 series airplanes, that currently requires modification of the nacelle strut and wing structure. This amendment reduces a certain compliance time in the existing AD. The actions specified by this AD are intended to prevent fatigue cracking in primary strut structure and consequent reduced structural integrity of the strut. This action is intended to address the identified unsafe condition.
81-16-09: 81-16-09 CESSNA: Amendment 39-4182. Applies to the following airplanes certificated in any category: \n\n\n\nModel\nSerial Numbers\n172N, 172P\n17271035 thru 17274523 \nR172K\nR1722930 thru R1723425\n172RG\n172RG0001 thru 172RG0789\nF172\nF17201750 thru F17202134 \nFR172\nFR1720631 thru FR1720675\n\n\n\tCOMPLIANCE: Required as indicated unless already accomplished in accordance with AD 81-04-04, Amendment 39-4042. \n\n\tTo ensure the integrity of the elevator control system, accomplish the following within the next 25 hours time-in-service after the effective date of this AD. \n\n\tA)\tRemove the MS24665-134 cotter pins, AN310-3 nuts and AN23-12 clevis bolts that attach both elevator cable clevises (forks) to the aft elevator bellcrank. \n\n\tB)\tClean the mating surfaces of the bellcrank and elevator cable clevises (forks). \n\n\tC)\tVisually inspect to assure that there is clearance between the elevator cable clevises (forks) and bellcrank. \n\n\tD)\tInstall the AN23-12 clevis bolts with the head to the right side for the upper bolt and left side for the lower bolt and the AN310-3 nuts removed in paragraph A. Install new MS24665-134 cotter pins. Assure that the elevator cable clevises (forks) can swivel freely. \n\n\tE)\tCheck elevator cable tension, 30 ñ 10 lbs. \n\n\tF)\tConduct operational check of elevator control system. \n\n\tNOTE: While Cessna Single Engine Service Information Letter SE80-78, Revision 1, dated July 13, 1981, pertains to this subject, the action required in this AD is more comprehensive. \n\n\tThis amendment supersedes AD 81-04-04, Amendment 39-4042. \n\n\tThis amendment becomes effective August 13, 1981.
2008-21-11: The FAA is adopting a new airworthiness directive (AD) for General Electric Company (GE) CF6-80C2 series and CF6-80E1 series turbofan engines. This AD requires installing skin doubler pads and deflectors on stage 5 of certain low-pressure turbine (LPT) cases, or replacing those LPT cases with LPT cases that have skin doubler pads and deflectors already installed. This AD results from four events in which hardware fragments were liberated into the engine flowpath and wore through LPT cases on CF6-80C2 and CF6-80E1 series engines. We are issuing this AD to prevent an uncontained release of engine debris and loss of the structural integrity of the mount system that supports the engine. Loss of the mount system structural integrity could result in the engine separating from the airplane.
69-13-03: 69-13-03 PIPER: Amdt. 39-785 as amended by Amendment 39-1749. Applies to Piper PA-23, PA-23-160, PA-23-235, PA-23-250, PA-E23-250 and PA-30 airplanes equipped with Stewart-Warner "Southwind" model 940 series heater. To prevent carbon monoxide from entering the airplane cabin, accomplish the following: (a) Within 25 hours' time-in-service after the effective date of this airworthiness directive, unless already accomplished, remove the heater exhaust tube shroud and by means of a magnet determine if Stewart-Warner P/N 486238 exhaust extension (Piper P/N 754-708) is mild steel (magnetic) or stainless steel (non-magnetic). Mild steel extensions, regardless of condition, must be replaced with stainless steel extensions, when available. (b) If stainless steel extensions are not available, a mild steel extension may continue to be used but must be visually inspected for deterioration at intervals not to exceed 25 hours time-in-service. If inspection reveals deteriorationin the form of cracks, corrosion, rust or flaking, the exhaust tube must be replaced and if with a new or non-deteriorated mild steel P/N 486238 tube, it must continue to be inspected in accordance with this paragraph. (c) (1) For heaters having 900 or more hours' time in service, unless already accomplished within the last 400 hours' time in service after the effective date of this airworthiness directive, overhaul the heater assembly within the next 100 hours' time in service and every 500 hours thereafter in accordance with Stewart-Warner Service Manual PM-10035 dated July, 1966 or an equivalent procedure approved by the Chief, Engineering & Manufacturing Branch, FAA Eastern Region. An overhaul consists of a complete disassembly, cleaning, repair, reassembly and test as described in the above service manual. (2) Heaters having less than 900 hours' time in service on the effective date of this AD shall be overhauled in accordance with paragraph (1) prior to the accumulation of 1000 hours' time in service and every 500 hours thereafter. (3) In complying with (1) and (2) above, if the owner or operator cannot document heater operating time, aircraft time should be used. (d) If the overhaul described in paragraphs (c)(1) and (c)(2) above includes replacement of heat exchanger P/N G488636 with a new unit, the time to next overhaul may be extended to 1000 hours in lieu of 500 hours provided a new nameplate Stewart-Warner P/N 704897 or an equivalent approved by the Chief, Engineering & Manufacturing Branch, FAA, Eastern Region, is attached to the heater adjacent to the existing nameplate, and inscribed with unit Model No., Serial No., Aircraft Registration No. and hours of service time at installation. (Stewart-Warner Corp. South Wind Division Service Bulletin No. 73-2 covers this subject.) Amendment 39-785 was effective July 2, 1969. This amendment 39-1749 is effective December 14, 1973.
93-16-10: 93-16-10 AIRBUS INDUSTRIE: Amendment 39-8667. Docket 93-NM-34-AD. Applicability: Model A320 series airplanes having manufacturer's serial numbers (MSN) 002 through 021 inclusive, certificated in any category. Compliance: Required as indicated, unless accomplished previously. To detect fatigue cracking in the upper stringer which may result in loss of structural integrity, accomplish the following: (a) Prior to the accumulation of 10,000 total landings after the effective date of this AD, perform a detailed visual inspection to detect cracks in the front and rear faces and at the crown fittings of the upper stringers of the center wing box between frame (FR)36 and FR42, in accordance with Airbus A320 Service Bulletin No. A320-57-1030, dated August 12, 1991. NOTE 1: Particular attention should be paid to the strut fittings and reinforcing plate ends when performing this inspection. (1) If no crack is found, repeat the inspection thereafter at intervalsnot to exceed 7,500 landings, in accordance with the service bulletin. (2) If any crack is found, prior to further flight, repair in accordance with a method approved by the Manager, Standardization Branch, ANM-113. Following accomplishment of this repair, no further action is required by this AD. (b) 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 2: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Standardization Branch, ANM-113. (c) 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. (d) The inspection shall be done in accordance with Airbus A320 Service Bulletin No. A320-57-1030, dated August 12, 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 Airbus Industrie, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, 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. (e) This amendment becomes effective on October 13, 1993.
2020-14-08: The FAA is adopting a new airworthiness directive (AD) for all Airbus SAS Model A318 series airplanes, Model A319 series airplanes, Model A320 series airplanes, and Model A321 series airplanes. This AD was prompted by reports of main landing gear (MLG) torque link apex pin rupture in service. This AD requires replacement of certain MLG torque link apex pins and, for certain other pins, a one-time magnetic particle inspection (MPI) for cracking, and replacement if necessary, as specified in a European Union Aviation Safety Agency (EASA) AD 2020- 0130, which is incorporated by reference. The FAA is issuing this AD to address the unsafe condition on these products.