Results
91-06-09: 91-06-09 GLASFLUGEL: Amendment 39-6920. Docket No. 90-CE-37-AD. Applicability: Models H301 Libelle, H301B Libelle, Standard Libelle, Standard Libelle 201, Standard Libelle 201B, Standard Libelle 203, Kestrel 604, and BS-1 Gliders (all serial numbers), certificated in any category. Compliance: Required as indicated after the effective date of this AD, unless already accomplished. To prevent failures in the rudder control system, accomplish the following: (a) Within the next 25 hours time-in-service (TIS) after the effective date of this AD, unless already accomplished, replace all DIN specification 055, 6 by 7 inch rudder cables with a diameter of 2.55 mm (.098 in.) having a hemp core, with a 7 by 7, 3/32 inch cable, manufactured in accordance with MIL-W-83420D or MIL-W-1511A, with cable connections constructed in accordance with Actions 2 of Hansjorg Streifeneder Technical Note Nos. 201-26, 301-33, 401- 20, 501-4, all dated March 15, 1987. NOTE: The replacement cables may have been installed pursuant to superseded AD 71- 16-06, Amendment 39-1253, or superseded AD 88-07-05, Amendment 39-5865. (b) Within the next 100 hours TIS after the replacement of the cables required in paragraph (a) of this AD or within the next 100 hours after the effective date of this AD, whichever is applicable, and thereafter at intervals not to exceed 100 hours TIS, visually inspect the rudder cables for wear, fraying, corrosion, twisting or other damage. If damaged cables are found, prior to further flight, replace the damaged cables with cables and connections as specified in paragraph (a) of this AD. (c) 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, Brussels Aircraft Certification Office, Europe, Africa, and Middle East Office, FAA, c/o American Embassy 15 Rue de la Loi, B-1000 Brussels, Belgium. The request should be forwarded through an appropriate FAA Maintenance Inspector, who may add comments and then send it to the Manager, Brussels Aircraft Certification Office. (d) All persons affected by this directive may obtain copies of the documents referred to herein upon request to Hansjorg Streifeneder, Glasflaser Flugzeug Service GmbH, Hofener Weg, D-7431 Grabenstetten, Federal Republic of Germany; or may examine these documents at the FAA, Central Region, Office of the Assistant Chief Counsel, Room 1558, 601 E. 12th Street, Kansas City, Missouri 64106. Airworthiness Directive 91-06-09 supersedes AD 71-16-06, Amendment 39-1253, and AD 88-07-05, Amendment 39-5865. This amendment (39-6920, AD 91-06-09) becomes effective on April 8, 1991.
2021-15-03: The FAA is adopting a new airworthiness directive (AD) for certain Gulfstream Aerospace Corporation (Gulfstream) Model GVII-G500 airplanes. This AD results from flap yoke fittings with design features that cause decreased fatigue life. This AD requires replacing the flap inboard and outboard yoke fitting assemblies and establishing a 20,000 flight cycle life limit for the fittings. The FAA is issuing this AD to address the unsafe condition on these products.
77-07-06: 77-07-06 BEECH: Amendment 39-2863. Applies to Models C90 (Serial Numbers LJ- 640 thru LJ-716), and E90 (Serial Numbers LW-120 thru LW-220, LW-222 and LW-223) airplanes. To assure adequate clearance between the left hand rudder cable and the electrical components on the relay panel located under the left hand cockpit floorboard, accomplish the following: A) Prior to further flight inspect the left hand rudder control cable under the left hand cockpit floorboard in accordance with Steps 1 through 4 of Beechcraft Service Instructions 0896, or later approved revisions, to determine that at least 3/4 inch clearance exists between the rudder control cable and all electrical components located on the relay panel. B) If the inspection required by Paragraph A shows that the clearance is less than 3/8 inch, prior to further flight: 1. If possible, relocate the relay panel to provide at least 3/4 inch clearance, or if the relay panel cannot be relocated to provide at least 3/4 inch clearance, modify the panel in accordance with Steps 6 through 13 of Beechcraft Service Instructions 0896, or later approved revisions, and 2. Inspect the rudder cable to determine if it has been damaged by coming in contact with the electrical components. If the cable has been damaged, install a new cable, Beech P/N 50-524438-17, or an equivalent cable fabricated in accordance with acceptable FAA standards (AC 43.13-1A). C) If the inspection required by Paragraph A shows that the clearance is between 3/8 and 3/4 inches, within 25 hours' time in service after the effective date of this AD, accomplish the requirements of Paragraphs B(1) and B(2). D) If the inspection required by Paragraph A shows that the clearance is 3/4 inch or more, make an entry in the aircraft's maintenance records indicating that this AD has been accomplished and the airplane may be returned to service. E) Airplanes may be flown in accordance with FAR 21.197 to a location where the needed electrical system modification or rudder cable replacement required by this AD may be accomplished. Prior to authorizing a flight under FAR 21.197, the FAA District Office involved should contact the Chief, Engineering and Manufacturing Branch, FAA, Central Region, for appropriate operating limitations. F) Any equivalent method of compliance with this AD must be approved by the Chief, Engineering and Manufacturing Branch, FAA, Central Region. This amendment becomes effective April 11, 1977, to all persons except those to whom it has already been made effective by air mail letter from the Federal Aviation Administration dated March 14, 1977.
2021-13-16: The FAA is adopting a new airworthiness directive (AD) for certain General Electric Company (GE) GEnx-2B67, GEnx-2B67/P, and GEnx- 2B67B model turbofan engines. This AD was prompted by a report of a crack in the lower fuel manifold causing fuel leakage. This AD requires an ultrasonic inspection (USI) or a fluorescent penetrant inspection (FPI) of the lower fuel manifold. Depending on the results of the USI or FPI, this AD requires replacement of the lower fuel manifold with a part eligible for installation. The FAA is issuing this AD to address the unsafe condition on these products.
2004-07-01: This amendment adopts a new airworthiness directive (AD) that is applicable to certain Bombardier Model CL-600-2C10 (Regional Jet Series 700 & 701) and CL-600-2D24 (Regional Jet Series 900) series airplanes. This action requires revising the airplane flight manual to advise the flightcrew to monitor the fuel quantity in the center fuel tank throughout the flight. This action also requires repetitive tests to detect a fuel leak between the wing fuel tanks and the center fuel tank; and further related investigative and corrective actions, if necessary. For certain airplanes, this AD also requires installation of flexible hoses and brackets in the fuel feed system. This action is necessary to detect and correct cracking in the primary fuel ejector. Cracking in the primary fuel ejector could cause fuel leakage into the center fuel tank, which could result in engine shutdown during flight. This action is intended to address the identified unsafe condition.
2021-14-19: The FAA is adopting a new airworthiness directive (AD) for certain International Aero Engines AG (IAE) V2500 model turbofan engines. This AD was prompted by a review of investigative findings from an event involving an uncontained failure of a high-pressure turbine (HPT) 1st-stage disk that resulted in high-energy debris penetrating the engine cowling. This AD requires performance of an ultrasonic inspection (USI) of the HPT 1st-stage disk and HPT 2nd-stage disk and, depending on the results of the inspections, replacement of the HPT 1st-stage disk or HPT 2nd-stage disk with a part eligible for installation. The FAA is issuing this AD to address the unsafe condition on these products.
91-08-07: 91-08-07 TEXTRON LYCOMING: Amendment 39-6962. Docket No. 91-ANE-08. Applicability: TIO-360 Series engines with serial numbers up to L-215-64A inclusive; TIO-540 Series engines with serial numbers up to L-9245-61/61A inclusive, except TIO-540-AE2A engines for which the requirements of AD 89-15-10 are met; LTIO-540 Series engines with serial numbers up to L-2911-68A inclusive; TIGO-541 Series engines with serial numbers up to L-780-62 inclusive; all TIO-541 Series engines; and all TIVO-540 Series engines. Also applies to overhauled and remanufactured engines of these models shipped from the factory prior to November 15, 1990, and to any Textron Lycoming engine that has been modified to use a turbocharger and that has the fuel pump vent vented to the induction system. Compliance: Required within the next 15 hours in service for paragraph (a) and within the next 50 hours in service for paragraph (b), after the effective date of this AD, unless already accomplished. To prevent engine power loss and possible loss of the aircraft, accomplish the following: (a) Perform a fuel leak check at the fuel pump vent hose fitting as follows: (1) Disconnect the fuel pump vent hose at the engine fuel pump. Then proceed to turn on the aircraft boost pump and visually inspect for any fuel draining out from the engine pump vent port. (2) Prior to further flight, remove and replace with a serviceable pump, engine fuel pumps which exhibit leakage. Repeat the leak check following pump replacement to verify no fuel is passing through the fuel pump vent port. (3) Reconnect the fuel pump vent hose at the engine fuel pump. (b) Inspect and replace if necessary, the fuel pump vent restrictor fitting as follows: (1) Remove fitting from the pump vent port and measure the orifice opening using an appropriate size wire gauge or drill bit. The orifice diameter must be within .014-.020 inch and the fitting must have the code letter "R" impression stamped on a flat surface. (2) Prior to further flight, replace any restrictor fitting that has an orifice diameter out of limits, or if no restrictor orifice exists. Install a new or serviceable restrictor fitting with a proper size orifice, and identified with the letter "R", using Loctite hydraulic sealant or equivalent on the pipe threads. (3) Ensure that the orientation of the reinstalled fitting is the same as the original fitting. (4) Reconnect the pump vent line. NOTE: Textron Lycoming Service Bulletin Nos. 494 and 497 and Service Instruction No. 1446 pertain to this subject. Fuel pump vent fittings supplied by Textron Lycoming with the proper size orifice are identified by the letter "R" stamped on each fitting. Engine Models TIO-541 and TIVO-540 series are not specified in the service bulletins, for these engines the engine driven pump and vent fitting were furnished by the aircraft manufacturer. (c) Aircraft may be ferried in accordance with the provisions of FederalAviation Regulations 21.197 and 21.199 to a base where the AD can be accomplished. (d) Upon submission of substantiating data by an owner or operator through an FAA Inspector (maintenance, avionics, or operations, as appropriate), an alternate method of compliance with the requirements of this AD or adjustments to the compliance schedule specified in this AD may be approved by the Manager, New York Aircraft Certification Office, Engine & Propeller Directorate, Aircraft Certification Service, FAA, New England Region, Room 202, 181 South Franklin Avenue, Valley Stream, New York 11581. All persons affected by this directive who have not already received the appropriate service information from the manufacturer may obtain copies upon request to Textron Lycoming/Subsidiary of Textron Inc., 652 Oliver Street, Williamsport, Pennsylvania 17701. This information may be examined at the FAA, New England Region, Office of the Assistant Chief Counsel, Room 311, 12 New England Executive Park, Burlington, Massachusetts. This amendment becomes effective on May 6, 1991.
2011-12-16: We are superseding an existing emergency airworthiness directive (EAD) for the specified Schweizer model helicopters that was previously sent to all known U.S. owners and operators. That EAD currently requires removing each locknut and verifying sufficient drag torque and retorquing, or if the locknut does not have sufficient drag torque, replacing the locknut with an airworthy locknut. This AD retains the existing EAD requirements but also requires within a specified time, modifying the expandable bolts and installing a cotter pin. This AD is prompted by a locknut working loose from a bolt attaching the tailboom support strut at the aft cluster fitting because the locknut installed on the expandable bolt did not have the proper threads. We are issuing this AD to modify each expandable bolt to allow adding a cotter pin to prevent the strut and driveshaft separating from the helicopter and subsequent loss of control of the helicopter.
2011-11-03: We are adopting a new airworthiness directive (AD) for the products listed above. This AD results from mandatory continuing airworthiness information (MCAI) issued by the aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as: During a production process review, a deviation in hardening of certain Part Number (P/N) 944072 washers has been detected, which exceeds the hardness of the design specification. The affected washers are part of the magneto ring flywheel hub installation and have been installed on a limited number of engines. No defective washers have been shipped as spare parts. This condition, if not corrected, could lead to cracks in the washer, loosening of the magneto flywheel hub and consequent ignition failure, possibly resulting in damage to the engine, in- flight engine shutdown and forced landing, damage to the aeroplane and injury to occupants. ThisAD requires actions that are intended to address the unsafe condition described in the MCAI.
98-04-14: This amendment adopts a new airworthiness directive (AD) that is applicable to Pratt & Whitney PW4164 and PW4168 series turbofan engines. This action requires initial and repetitive inspections for loose or broken front pylon mount bolts, replacement, if necessary, with new bolts, and establishment of a new cyclic life limit. This amendment is prompted by new flight test data that indicate higher than predicted loads. The actions specified in this AD are intended to prevent front pylon mount bolt failure, which could result in engine separation from the aircraft.
2011-14-09: We are adopting a new airworthiness directive (AD) for the products listed above that will supersede an existing AD. This AD results from mandatory continuing airworthiness information (MCAI) issued by the aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as: During a production process review, a deviation in hardening of certain Part Number (P/N) 944072 washers has been detected, which exceeds the hardness of the design specification. The affected washers are part of the magneto ring flywheel hub installation and have been installed on a limited number of engines. No defective washers have been shipped as spare parts. This condition, if not corrected, could lead to cracks in the washer, loosening of the magneto flywheel hub and consequent ignition failure, possibly resulting in damage to the engine, in- flight engine shutdown and forced landing, damage to the aeroplaneand injury to occupants. This AD requires actions that are intended to address the unsafe condition described in the MCAI.
89-23-19: 89-23-19 BOEING: Amendment 39-6382. Docket No. 89-NM-212-AD. \n\n\tApplicability: Model 747 series airplanes, listed in Boeing Alert Service Bulletin 747- 53A2314, dated July 31, 1989, certificated in any category. \n\n\tCompliance: Required within 60 days after the effective date of this AD, unless previously accomplished. \n\n\tTo ensure structural integrity of the horizontal stabilizer hinge fitting backup structure and to prevent possible detachment of longitudinal braces from the backup fitting with resultant hinge fitting movement adversely affecting airplane controllability, accomplish the following: \n\n\tA.\tConduct a one-time inspection for undersized and missing fasteners, in accordance with Boeing Alert Service Bulletin 747-53A2314, dated July 31, 1989. If any fastener is undersized or missing, prior to further flight, install a new fastener in accordance with that service bulletin. \n\n\tB.\tAn alternate means of compliance or adjustment of the compliance time, which provides an acceptable level of safety, may be used when approved by the Manager, Seattle Aircraft Certification Office, FAA, Northwest Mountain Region. \n\n\tC.\tSpecial 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. \n\n\tAll persons affected by this directive who have not already received the appropriate service documents from the manufacturer may obtain copies upon request to Boeing Commercial Airplanes, P.O. Box 3707, Seattle, Washington 98124. These documents may be examined at the FAA, Northwest Mountain Region, Transport Airplane Directorate, 17900 Pacific Highway South, Seattle, Washington, or Seattle Aircraft Certification Office, 9010 East Marginal Way South, Seattle, Washington. \n\n\tThis amendment (39-6382, AD 89-23-19) becomes effective on November 20, 1989.
2021-14-09: The FAA is adopting a new airworthiness directive (AD) for certain Airbus Canada Limited Partnership Model BD-500-1A10 and BD-500- 1A11 airplanes. This AD was prompted by a design review that identified rib 0 of the center wing box (CWB) as an area where a single failure of a clamshell type refuel/defuel line coupling could lead to the accumulation of dangerous levels of electrostatic charges within the fuel tank. This AD requires replacing the clamshell type refuel/defuel line coupling in the CWB at rib 0 with a threaded type fuel coupling, and installing an additional support bracket and clamp in the CWB at rib 0, as specified in a Transport Canada Civil Aviation (TCCA) AD, which is incorporated by reference. The FAA is issuing this AD to address the unsafe condition on these products.
2021-14-20: The FAA is adopting a new airworthiness directive (AD) for all The Boeing Company Model 737 airplanes. This AD was prompted by reports of latent failures of the cabin altitude pressure switches. This AD requires repetitive functional tests of the pressure switches, and on- condition actions, including replacement, if necessary. The FAA is issuing this AD to address the unsafe condition on these products.
2004-07-04: This amendment supersedes an existing airworthiness directive (AD), applicable to certain McDonnell Douglas Model DC-9 series airplanes, that currently requires replacing the transformer ballast assembly in the pilot's console with a new, improved ballast assembly. This amendment expands the applicability of the existing AD to include additional airplanes and provides an optional method for accomplishing the requirements of the existing AD. The actions specified by this AD are intended to prevent overheating of the ballast transformers due to aging fluorescent tubes that cause a higher power demand on the ballast transformers, which could result in smoke in the cockpit. This action is intended to address the identified unsafe condition. \n\nDATES: Effective May 5, 2004. \n\n\tThe incorporation by reference of a certain publication, as listed in the regulations, is approved by the Director of the Federal Register as of May 5, 2004. \n\n\tThe incorporation by reference of a certain other publication, as listed in the regulations, was approved previously by the Director of the Federal Register as of February 8, 2002 (67 FR 497, January 4, 2002).
96-13-07: This amendment supersedes an existing airworthiness directive (AD), applicable to all Fokker Model F27 Mark 100, 200, 300, 400, 500, 600, and 700 series airplanes, that currently requires supplemental structural inspections to detect fatigue cracks, and repair or replacement, as necessary, to ensure the continued airworthiness of these airplanes. This amendment adds and revises certain significant structural items for which inspection and repair or replacement is necessary. This amendment is prompted by a structural re-evaluation conducted by the manufacturer, which identified additional structural elements where fatigue damage is likely to occur. The actions specified by this AD are intended to prevent reduced structural integrity of these airplanes.
95-25-07: This amendment adopts a new airworthiness directive (AD) that applies to certain Fairchild Aircraft SA226 series airplanes that are equipped with a part number 27-55001-229 actuator assembly. This action requires replacing the main landing gear door actuator tang and associated hardware with parts of improved design. Reports of the main landing gear doors hanging up and locking the landing gear links on the affected airplanes prompted this action. The actions specified by this AD are intended to prevent the inability to extend the main landing gear because of the main landing gear door actuation roller contacting the lower edge of the tang and causing the linkage to lock over-center.
2004-07-07: This amendment supersedes an existing airworthiness directive (AD), applicable to certain Boeing Model 757-200 series airplanes, that currently requires modifications to the attachment installation of the forward lavatory. This amendment adds airplanes to the applicability of the existing AD. The actions specified by this AD are intended to prevent failure of the attachment installation of the forward lavatory during an emergency landing, which could result in injury to the crew and passengers. This action is intended to address the identified unsafe condition. \n\nDATES: Effective May 5, 2004. \n\n\tThe incorporation by reference of Boeing Special Attention Service Bulletin 757-25-0181, Revision 1, dated November 21, 2000, as listed in the regulations, is approved by the Director of the Federal Register as of May 5, 2004. \n\n\tThe incorporation by reference of Boeing Service Bulletin 757-25- 0181, dated June 26, 1997; and Boeing Alert Service Bulletin 757- 25A0187, dated September 18, 1997; as listed in the regulations, was approved previously by the Director of the Federal Register as of June 1, 1999 (64 FR 20146, April 26, 1999).
2011-13-06: 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: Bombardier Aerospace has completed a system safety review of the aeroplanes fuel system against fuel tank safety standards introduced in Chapter 525 of the Airworthiness Manual through Notice of Proposed Amendment (NPA) 2002-043 [which corresponds with the FAA's Special Federal Aviation Regulation (SFAR) 88]. The identified non- compliances were then assessed using Transport Canada Policy Letter No. 525-001, to determine if mandatory corrective action is required. The assessment showed that a number of modifications to the fuel system are required to mitigate unsafe conditions that could result in potential ignition source within the fuel system.We are issuing this AD to require actions to correct the unsafe condition on these products.
2021-13-13: The FAA is adopting a new airworthiness directive (AD) for all \n\n((Page 38210)) \n\nLeonardo S.p.a. Model AW189 helicopters. This AD was prompted by the identification of misleading information in the emergency procedure for the ''1(2) FUEL LOW'' caution message. This AD requires revising the existing Rotorcraft Flight Manual (RFM) for your helicopter. The FAA is issuing this AD to address the unsafe condition on these products.
91-10-06: 91-10-06 BRITISH AEROSPACE (BAe): Amendment 39-6987; Docket No. 90-CE-46-AD. Applicability: Beagle B121 Pup series 1, 2, and 3 (all serial numbers) airplanes, certificated in any category. Compliance: Required within the next 30 calendar days after the effective date of this AD, unless already accomplished, and thereafter at intervals not to exceed 60 calendar months. To avoid loss of control of the airplane, accomplish the following: (a) Replace the flight control column handgrips, part number BE-45-10283, in accordance with the instructions in BAe Mandatory Pup Service Bulletin (SB) B121/95, Revision 2, dated January 28, 1991. (b) Special 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. (c) An alternative method of compliance or adjustment of the initial or repetitive compliance times that provides an equivalent level of safety may be approvedby the Manager, Brussels Aircraft Certification Office, FAA, Europe, Africa, and Middle East Office, c/o American Embassy, B-1000 Brussels, Belgium. The request should be forwarded through an appropriate FAA Maintenance Inspector, who may add comments and then send it to the Manager, Brussels Aircraft Certification Office. (d) The replacements required by this AD shall be done in accordance with British Aerospace Mandatory Pup SB B121/95, Revision 2, dated January 28, 1991. This incorporation by reference was approved by the Director of the Federal Register in accordance with 5 U.S.C. Section 552(a) and 1 CFR Part 51. Copies may be obtained from British Aerospace PLC, Manager Product Support, Commercial Aircraft Airlines Division, Prestwick Airport, Ayrshire, KA9 2RW Scotland; or British Aerospace, Inc., Librarian, Box 17414, Dulles International Airport, Washington, DC, 20041. 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, 1100 L Street, NW, Room 8401, Washington, DC. This amendment (39-6987, AD 91-10-06) becomes effective on May 22, 1991.
78-18-05: 78-18-05 PIPER AEROSTAR: Amendment 39-3295. Applies to Piper Aerostar Model 600, 601 and 601P airplanes certificated in all categories, serial numbers 150 through 520. \n\n\tCompliance required as indicated. To prevent reversed readings of left and right wing tank fuel quantity accomplish the following: \n\n\t(a)\tWithin 10 hours time in service after the effective date of this AD, unless already accomplished, with LH and RH wing tanks at least 50% depleted from tank capacity: \n\n\t\t1)\tRead and record fuel quantity indication for LH and RH wing fuel tanks. \n\n\t\t2)\tAdd 10 gallons of fuel to one wing tank only. \n\n\t\t3)\tRead and record fuel quantity for each wing tank. \n\n\t\t4)\tDetermine that the added fuel registers on the correct wing tank fuel quantity indicator selector position. \n\n\t\t5)\tIf the correct wing tank fuel quantity selector position registers the added fuel, the system is normal and no further action is required under this AD. \n\n\t(b)\tIf the appropriate wing tank fuel indicator position does not correctly register the added fuel the system may be improperly wired or the selector may be improperly indexed. In this event, prior to further flight: \n\n\t\tCorrect the fuel quantity indicating system malfunction. Refer to figure 1 for details of proper switch installation. \n\n\t(c)\tWithin 10 hours time in service after the effective date of this AD, on those airplanes with the fuel quantity indicating selector switch relabelled as an interim solution under (B)(2) of the original message of July 7, 1978, correct the fuel quantity indicating system as in (b) of this AD and revert to standard switch labelling. \n\n\t(d)\tSpecial flight permits may be issued in accordance with FARs 21.197 and 21.199 to operate aircraft to a base for accomplishment of the repair required by paragraph (b) of this AD. \n\n\t(e)\tEquivalent inspections and repairs may be used when approved by the Chief, Aircraft Engineering Division, FAA Western Region. \n\n\tThis amendment becomes effective September 13, 1978.
2004-07-05: This amendment supersedes an existing airworthiness directive (AD), applicable to certain McDonnell Douglas Model DC-9-10, DC-9-20, DC-9-30, DC-9-40, and DC-9-50 series airplanes, and C-9 (military) airplanes, that currently requires repetitive ultrasonic or magnetic particle inspections to detect cracking of the engine pylon aft upper spar straps (caps); and if necessary, replacement of the strap with a new strap, or modification of the engine pylon rear spar straps, which constitutes terminating action for the repetitive inspections. This amendment requires new, improved repetitive ultrasonic inspections, and corrective actions if necessary. This amendment also requires, among other items, a terminating action for the repetitive inspection requirements. The actions specified by this AD are intended to detect and correct fatigue cracking, which could result in major damage to the adjacent structure of the pylon aft upper spar cap, and consequent reduced structural integrity of the airplane. This action is intended to address the identified unsafe condition.
2011-13-02: 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: During Landing Gear retraction/extension ground checks performed on the P2006T, a loose Seeger ring was found on the nose landing gear hydraulic actuator cap. The manufacturer has identified the root cause of this discrepancy in a design deficiency of the hydraulic actuator caps. This condition, if not corrected, could determine uncommanded and improper extension of the nose or main landing gear. We are issuing this AD to require actions to correct the unsafe condition on these products.
2021-13-08: The FAA is adopting a new airworthiness directive (AD) for all Safran Helicopter Engines, S.A. Arriel 2C and Arriel 2S1 model turboshaft engines. This AD was prompted by reports of error messages on the full authority digital engine control (FADEC) B digital engine control unit (DECU), caused by blistering of the varnish on the DECU circuit board. This AD requires the replacement of certain FADEC B DECUs. The FAA is issuing this AD to address the unsafe condition on these products.