Results
2023-22-04: The FAA is adopting a new airworthiness directive (AD) for all Rolls-Royce Deutschland Ltd & Co KG (RRD) Model 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 engines. This AD was prompted by reports of cracking and separation of certain low-pressure turbine (LPT) stage 1 blade assemblies. This AD requires initial and repetitive inspections of affected LPT stage 1 blade assemblies for cracking or separation and, depending on the results of the inspections, reduction of the inspection interval or replacement of the LPT stage 1 blade set and disk, as specified in a European Union Aviation Safety Agency (EASA) AD, which is incorporated by reference. The FAA is issuing this AD to address the unsafe condition on these products.
2005-05-13: The FAA is superseding an existing airworthiness directive (AD) for Pratt & Whitney (PW) JT9D-59A, -70A, -7Q, and -7Q3 turbofan engines. That AD currently requires fluorescent penetrant inspection (FPI) of high pressure turbine (HPT) second stage airseals, part numbers (P/Ns) 5002537-01, 788945, 753187, and 807410, knife-edges for cracks, each time the engine's HPT second stage airseal is accessible. This AD requires replacing each existing HPT second stage airseal with an improved design HPT second stage airseal and modifying the 2nd stage HPT vane cluster assembly and 1st stage retaining blade HPT plate assembly at next piece-part exposure, but no later than five years after the effective date of this AD. These actions are considered terminating action to the repetitive inspections required by AD 2002- 10-07. This AD results from the manufacturer introducing an improved design HPT second stage airseal and modifications to increase cooling. We are issuing this AD to prevent failure of the HPT second stage airseal due to cracks in the knife-edges, which if not detected, could result in uncontained engine failure and damage to the airplane.
2023-22-14: The FAA is adopting a new airworthiness directive (AD) for Airbus Helicopters Model SA-365C1, SA-365C2, and SA-365N helicopters. This AD was prompted by reports of damaged control rod dual bearings (dual bearings) that are installed on the tail rotor gearbox (TGB). This AD requires repetitively inspecting the TGB magnetic plug for particles, analyzing any particles collected, taking corrective actions if necessary, and reporting certain information. Finally, this AD allows an affected dual bearing to be installed on a helicopter if certain actions are accomplished, as specified in a European Union Aviation Safety Agency (EASA) AD, which is incorporated by reference. The FAA is issuing this AD to address the unsafe condition on these products.
2015-05-05: We are superseding Airworthiness Directive (AD) 2014-04-14 for Agusta S.p.A. (Agusta) Model A109S, AW109SP, A119, and AW119 MKII helicopters. AD 2014-04-14 required removing certain rod end assemblies from service because of reports of fractures. This new AD retains the requirements of AD 2014-04-14 but expands the scope of applicable rod end assemblies. This AD was prompted by reports of additional fractured rod end assemblies. We are issuing this AD to prevent failure of a rod end assembly, which could result in damage to the main rotor assembly and loss of control of the helicopter.
47-51-12: 47-51-12 DOUGLAS: Applies to All converted C-47 Series Aircraft With Ram Non-ram (Hydraulic) Type Carburetor Airscoop. \n\nTo be accomplished not later than March 1, 1948. \n\nCompliance with the following items is necessary to preclude carburetor icing: \n\n1.\tThe carburetor alcohol system must be used. \n\n2.\tThe accessory cowling and engine fire seal must maintain not more than 1/4-inch clearance of the collector ring. \n\n3.\tThe cable system for operation of the hot air door must be rigged to 30 pounds tension. \n\n(Part B of Douglas Service Bulletin DC-3 No. 251 dated April 15, 1947, covers this same subject. Part A of the same Bulletin is not mandatory, but optional compliance may be accomplished when parts are available.)
2023-22-03: The FAA is superseding Airworthiness Directive (AD) 2021-08-02 for all Safran Helicopter Engines, S.A. (Safran) (type certificate previously held by Turbomeca, S.A.) Model Arriel 2D and Arriel 2E engines. AD 2021-08-02 required replacing certain critical parts before reaching their published in-service life limits, performing scheduled maintenance tasks before reaching their published periodicity, and performing unscheduled maintenance tasks when the engine meets certain conditions. Since the FAA issued AD 2021-08-02, Safran has revised the airworthiness limitation section (ALS) of the existing maintenance and overhaul manuals, introducing new and more restrictive instructions and maintenance tasks, which prompted this AD action. This AD requires updating the ALS of the existing engine maintenance manual (EMM) or instructions for continued airworthiness (ICA) and the existing approved maintenance or inspection program, as applicable, by incorporating the actions and associated thresholds and intervals, including life limits, as specified in a European Union Aviation Safety Agency (EASA) AD, which is incorporated by reference. The FAA is proposing this AD to address the unsafe condition on these products.
2004-22-07: The FAA is adopting a new airworthiness directive (AD) for GE CF6-80C2 turbofan engines with certain part number (P/N) high pressure turbine stage 2 nozzle guide vanes (HPT S2 NGVs) installed. This AD requires flex borescope inspections of HPT S2 NGVs installed in CF6- 80C2 turbofan engines. This AD results from an uncontained engine failure due to HPT S2 NGV distress. We are issuing this AD to prevent blade separation from HPT S2 NGV distress, which could result in an uncontained engine failure.
91-24-12: 91-24-12 BRITISH AEROSPACE: Amendment 39-8098. Docket No. 91-NM-133-AD. Applicability: Model ATP series airplanes, equipped with hydraulic selector valves part number AIR44880 and AIR44882, certificated in any category. Compliance: Required as indicated, unless previously accomplished. To prevent a gear-up landing, accomplish the following: (a) Within 12 months after the effective date of this AD, modify and test the landing gear hydraulic selector valves in accordance with AP Precision Hydraulics Service Bulletin AIR44880-29-01, dated April 1991. NOTE: British Aerospace Service Bulletin ATP-29-6, dated April 12, 1991, references AP Precision Hydraulics Service Bulletin AIR44880-29-01, dated April 1991. (b) 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. (c) 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. (d) The modification and testing requirements shall be done in accordance with AP Precision Hydraulics Service Bulletin AIR44880-29-01, dated April 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 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. This amendment (39-8098, AD 91-24-12) becomes effective on January 7, 1992.
2015-04-07: We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 767-200 and -300 series airplanes equipped with Pratt & Whitney Model JT9D or PW4000 engines. This AD was prompted by a report of several cases of low hydraulic pressure or loss of electrical power to the alternating current motor pump (ACMP) on the left engine. This AD requires inspecting for damage of the wiring bundles in the left engine's strut and corrective actions if necessary, and installing new wire support brackets and bundle clamps. We are issuing this AD to detect and correct chafed wire bundles due to rubbing against structure or a hydraulic piping elbow, which could result in electrical arcing in a flammable fluid leakage zone, and provide a possible ignition source for fuel vapors and hydraulic fluids. Ignited fuel vapors or hydraulic fluid in an area without a fire detection or suppression system could result in an uncontained engine strut fire and structural damage to the engine strut.
2000-22-05: This amendment supersedes an existing airworthiness directive (AD), applicable to all Short Brothers Model SD3-60 SHERPA series airplanes, that currently requires a one-time visual inspection to determine the part number of the power control cable assemblies and pulleys of the engine controls; and replacement of the power control cable assemblies and pulleys (as applicable) with new parts, if necessary. This amendment requires accomplishment of the inspection and replacement in accordance with revised procedures. This amendment is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified by this AD are intended to prevent breakage of the power control cable assemblies due to the inflexible construction of the cable, which could result in loss of engine power and consequent reduced controllability of the airplane.
95-21-06: This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A330 and A340 series airplanes. This action requires replacement of the fire extinguisher distribution pipe and attachments in the lower deck cargo compartment fire extinguishing system. This amendment is prompted by a report indicating that, in response to a smoke warning in the forward cargo compartment on one airplane, bottle 2 of the fire extinguishing system did not discharge extinguishing agent into the cargo compartment due to a blockage of the discharge pipe by debris within it. The actions specified in this AD are intended to ensure that, in the event of a fire, adequate fire extinguishing agent is discharged into the cargo compartment.
2023-21-08: The FAA is superseding Airworthiness Directive (AD) 2021-21-13 for certain Rolls-Royce Deutschland Ltd & Co KG (RRD) Model Trent 1000 engines. AD 2021-21-13 required the operator to revise the airworthiness limitation section (ALS) of their existing approved aircraft maintenance program (AMP) by incorporating the revised tasks of the applicable time limits manual (TLM) for each affected model engine. Since the FAA issued AD 2021-21-13, the manufacturer has revised the TLM, introducing new and more restrictive instructions. This AD is prompted by the manufacturer revising the engine TLM life limits of certain critical rotating parts. This AD requires revisions to the ALS of the operator's existing approved AMP, as specified in a European Union Aviation Safety Agency (EASA) AD, which is incorporated by reference. The FAA is issuing this AD to address the unsafe condition on these products.
2023-22-11: The FAA is adopting a new airworthiness directive (AD) for certain Embraer S.A. (Embraer) Model EMB-505 airplanes. This AD was prompted by an occurrence of corrosion on the clutch retaining bolt of the aileron autopilot servo mount. This AD requires repetitively replacing the clutch retaining bolt and washer of the aileron autopilot servo mount, as specified in an Ag[ecirc]ncia Nacional de Avia[ccedil][atilde]o Civil (ANAC) AD, which is incorporated by reference. The FAA is issuing this AD to address the unsafe condition on these products.
97-07-03: This amendment supersedes Airworthiness Directive (AD) 81-11-04 that applies to The New Piper Aircraft, Inc. (Piper) Models PA31, PA31-300, PA31-325, and PA31-350 airplanes that have Cleveland nose wheel assembly part number (P/N) 40-76B installed. AD 81-11-04 currently requires inspecting the nose wheel flange for cracks. The repetitive inspections terminate by replacing the nose wheel assembly with Cleveland P/N 40-140, which is an improved design. This action is prompted by the lack of designation of Piper Model PA31P in the Applicability section of AD 81-11-04, and the subsequent failure of a nose wheel assembly on a Piper Model PA31P airplane during taxiing operations. The actions specified by this AD are intended to prevent the failure of the nose wheel, which if not corrected, could result in loss of control of the airplane during taxiing, take-off, or landing operations.
76-20-08: 76-20-08 LOCKHEED-CALIFORNIA COMPANY: Amendment 39-2742 as amended by Amendment 39-2916. Applies to Model L-1011-385 series airplanes, certificated in all categories. Compliance required as indicated. To prevent possible collapse of a main landing gear assembly due to failure of one or both of the two main landing gear upper side brace spherical bearing trunnion retaining bolts, accomplish the following: (a) Within the next 75 hours' time in service after the effective date of this AD accomplish the following checks, inspections, repairs or replacements as necessary, in accordance with accomplishment instructions of the Lockheed-California Company Alert Service Bulletin 093- 32-A115, dated September 1, 1976, or later FAA-approved revisions. (1) Prior to each flight, perform a visual check of each main landing gear upper side brace trunnion joint and verify that the two trunnion bearing cap retaining bolts P/Ns 76754-18-71 or 69680v18-71 or 69680-18-71 are in place and that no obvious structural deformation of the trunnion bearing caps P/Ns 1504393-109 or -110 has occurred. (2) If one or both retaining bolts P/Ns 76754-18-71 or 69680v18-71 or 69680-18-71 are missing or if a structural deformation of the trunnion bearing caps P/Ns 1504393-109 or -110 appears to have occurred, before further flight replace both retaining bolts and inspect the side brace support fitting P/Ns 1504393-107 or -108 and the trunnion bearing caps P/Ns 1504393-109 or -110 for structural damage and replace or repair as necessary the parts found to be damaged. (3) The checks required by this AD may be performed by a flight crew member. (b) Equivalent checks, inspections, repairs and replacements may be used when approved by the Chief, Aircraft Engineering Division, FAA, Western Region. (c) Compliance is required on or before March 31, 1978, unless already accomplished: Accomplish the modification of the main landing gear upper side brace trunnion jointsin accordance with Paragraph 2, Accomplishment Instructions, of the FAA approved Lockheed-California Company Service Bulletin 093-32-115, Revision I, dated March 18, 1977 or later FAA approved revisions. (d) Accomplishment of the modification of the upper side brace trunnion joints in accordance with paragraph (c) will remove the need for accomplishment of the requirements of paragraph (a). Amendment 39-2742 became effective October 18, 1976. This amendment 39-2916 becomes effective June 17, 1977.
2005-05-04: The FAA is adopting a new airworthiness directive (AD) for all Aerospatiale Model ATR 42-200, -300, and -320 series airplanes. This AD requires inspecting to determine the part and serial number of the swinging lever of the main landing gears (MLG) and replacing the swinging lever if necessary. This AD is prompted by a report that, on an airplane lined up for takeoff, the swinging lever of the left MLG collapsed when engine power was applied. We are issuing this AD to prevent fracture of the MLG swinging lever, which could result in collapse of the swinging lever and reduced structural integrity and possible collapse of the MLG during operations on the ground.
2023-21-09: The FAA is adopting a new airworthiness directive (AD) for all The Boeing Company Model 777-200, 777-200LR, 777-300, 777-300ER, and 777F series airplanes. This AD was prompted by a report of a ''FLAPS DRIVE'' caution message in flight due to the torque trip indicator of the No. 2 trailing edge (TE) flap transmission assembly being in the set position, which resulted in an air turn-back. This AD requires an inspection or records review to determine the serial numbers of the TE flap transmission and gearbox assemblies, and applicable on-condition corrective actions. This AD also limits the installation of affected parts. The FAA is issuing this AD to address the unsafe condition on these products.
95-19-02: This amendment adopts a new airworthiness directive (AD), applicable to certain Fokker Model F28 Mark 0100 series airplanes, that requires replacement of the flight control lock (FCL) handle and switch with a modified unit. This amendment is prompted by a report of sudden engagement of the FCL system during approach for landing. The actions specified by this AD are intended to prevent inadvertent engagement of the FCL system during flight and subsequent reduced controllability of the airplane.
2005-05-01: The FAA is adopting a new airworthiness directive (AD) for certain Boeing Model 757 series airplanes. This AD requires identification of the part number for the cable assembly for the lower anti-collision light, and related \ninvestigative and corrective actions if necessary. This AD is prompted by a report of damage caused by an electrical arc in a connector on the cable assembly for the lower anti-collision light. We are issuing this AD to prevent an electrical arc in the cable assembly for the lower anti-collision light, which could result in a fire in a flammable leakage zone of the airplane.
2015-02-25: We are adopting a new airworthiness directive (AD) for certain Bombardier, Inc. Model DHC-8-400 series airplanes. This AD was prompted by fuel system reviews conducted by the manufacturer. This AD requires replacing a fitting that is part of the refuel control solenoid valve assembly. We are issuing this AD to prevent the potential of ignition sources inside fuel tanks, which, in combination with flammable fuel vapors, could result in fuel tank explosions and consequent loss of the airplane.
2000-22-01: This amendment adopts a new airworthiness directive (AD) that is applicable to certain Pratt & Whitney (PW) PW4000 series turbofan engines that are equipped with the high pressure compressor (HPC) cutback stator (CBS) configuration and that are used on Boeing 747, Boeing 767, and McDonnell Douglas MD-11 series airplanes. This action requires Operators to limit the number of engines with the HPC CBS configuration to one per airplane, and prohibits installation of engines with HPC modules modified after the effective date of this AD to incorporate the HPC CBS configuration. This amendment is prompted by reports of HPC surges in engines that have the HPC CBS configuration. The actions specified in this AD are intended to prevent a multiple-engine power loss due to HPC surges, which could result in engine power loss at a critical phase of flight such as takeoff or climb.
94-04-11: This amendment adopts a new airworthiness directive (AD) that applies to certain Twin Commander Aircraft Corporation (Twin Commander) Models 500S and 690B airplanes. This action requires removing a sample of the wing front spar lower cap (spar cap) material for examination, and, depending upon the results of that examination, inspecting or replacing the Airworthiness Directives: Twin Commander Aircraft Corporation Models 500S and 690B Airplanes . Reports of cracks caused by stress corrosion in the spar cap on several of the affected airplanes prompted this action. The actions specified by this AD are intended to prevent failure of the wing structure caused by cracks in the spar cap.
92-10-14: 92-10-14 LOCKHEED AERONAUTICAL SYSTEMS COMPANY-GEORGIA: Amendment 39-8249. Docket No. 91-NM-69-AD. Supersedes AD 89-15-03, Amendment 39- 6265. Applicability: Model 382 series airplanes, serial numbers 3946 through 5305, inclusive, certificated in any category. Compliance: Required as indicated, unless accomplished previously. To prevent fatigue cracking and subsequent decompression of the airplane, accomplish the following: (a) For airplanes that had accumulated 6,300 hours time-in-service prior to July 31, 1989 (the effective date of AD 89-15-03, Amendment 39-6265), within the next 10 hours time-in-service after July 31, 1989, accomplish the following: (1) Incorporate the following statement into the Limitations Section of the FAA-approved Airplane Flight Manual (AFM). This may be accomplished by including a copy of this AD in the AFM. "Aircraft cabin operating pressure is limited to 10 inches of mercury." (2) Temporarily reduce cabin operating pressure in accordance with paragraph (a)(1) of this AD. (b) For all other airplanes not subject to paragraph (a) of this AD: Within 10 hours time-in-service after the effective date of this AD, or prior to the accumulation of 6,300 hours time- in-service, whichever occurs later, accomplish the following: (1) Incorporate the following into the Limitations Section of the FAA-approved Airplane Flight Manual (AFM). This may be accomplished by including a copy of this AD in the AFM. "Aircraft cabin operating pressure is limited to 10 inches of mercury." (2) Temporarily reduce cabin operating pressure in accordance with paragraph (b)(1) of this AD. (c) For airplanes that had accumulated 6,300 hours time-in-service prior to July 31, 1989 (the effective date of AD 89-15-03, Amendment 39-6265), and have not been inspected in accordance with AD 89-15-03: Within 45 days after the effective date of this AD, perform an inspection of the following areas of the pressurized fuselage fairing support (FS) structure according to the specified Work Card procedures of Standard Maintenance Publication (SMP) 515-A/C, as specified in Lockheed Aeronautical Systems Company (LASC)-Georgia Service Bulletin 382-53-50, Revision 1, dated December 13, 1991: FS477 to FS517 General Area Work Card SP-126 FS477 Upper Web Flange Work Card SP-224 FS497 Overhead Bulkhead Web and Tee-Outboard S/N 3946 through S/N 4932 Work Card SP-224 S/N 4933 through S/N 5305 Work Card SP-126 FS497 Overhead Bulkhead Upper Attach Angle Work Card SP-224 (d) For airplanes that have been inspected in accordance with AD 89-15-03: Within 3,000 hours time-in-service since the last inspection, perform an inspection of the following areas of the pressurized fuselage FS structure according to the specified Work Card procedures of Hercules Maintenance Program Plan SMP 515-A/C, as shown in LASC-Georgia Service Bulletin 382-53-50, Revision 1, dated December 13, 1991: FS477 to FS517 General Area Work Card SP-126 FS477 Upper Web Flange Work Card SP-224 FS497 Overhead Bulkhead Web and Tee Outboard S/N 3946 through S/N 4932 Work Card SP-224 S/N 4933 through S/N 5305 Work Card SP-126 FS497 Overhead Bulkhead Upper Attach Angle Work Card SP-224 (e) For all other airplanes, not subject to paragraph (c) or (d) of this AD: Prior to the accumulation of 6,300 hours time-in-service, or within 45 days after the effective date of this AD, whichever occurs later, perform an inspection of the following areas of the pressurized fuselage FS structure according to the specified Work Card procedures of Hercules Maintenance Program Plan SMP 515-A/C, as shown in LASC-Georgia Service Bulletin 382-53-50, Revision 1, dated December 13, 1991: FS477 to FS517 General Area Work Card SP-126 FS477 Upper Web Flange Work Card SP-224 FS497 Overhead BulkheadWeb and Tee Outboard S/N 3946 through S/N 4932 Work Card SP-224 S/N 4933 through S/N 5305 Work Card SP-126 FS497 Overhead Bulkhead Upper Attach Angle Work Card SP-224 (f) For all airplanes: At intervals not to exceed 3,600 hours time-in-service, repeat the inspections specified in, and in accordance with, the specified Work Card procedures of Hercules Maintenance Program Plan SMP 515-A/C, as shown in LASC-Georgia Service Bulletin 382-53-50, Revision 1, dated December 13, 1991: FS477 to FS517 General Area Work Card SP-126 FS477 Upper Web Flange Work Card SP-224 FS497 Overhead Bulkhead Web and Tee Outboard S/N 3946 through S/N 4932 Work Card SP-224 S/N 4933 through S/N 5305 Work Card SP-126 FS497 Overhead Bulkhead Upper Attach Angle Work Card SP-224 (g) If cracks are found, prior to further flight, repair in accordance with the procedures contained in Appendix A of LASC-Georgia Service Bulletin 382-53-50, Revision 1, dated December 13, 1991; or in a manner approved by the Manager, Atlanta Aircraft Certification Office, ACE-115A, FAA, Small Airplane Directorate. After repair, continue to perform the repetitive inspections required by paragraph (f) of this AD. (h) The limitations required by paragraphs (a) and (b) of this AD may be removed if one of the conditions specified in either paragraph (h)(1), (h)(2), (h)(3), or (h)(4) of this AD, is applicable: (1) If no cracks were found as a result of the inspections performed in accordance with AD 89-15-03, Amendment 39-6265; or (2) If any cracks were found as a result of the inspections performed in accordance with AD 89-15-03, Amendment 39-6265 were repaired in accordance with paragraph C. of that AD; or (3) If no cracks are found as a result of the inspections required by paragraphs (c), (d), (e), or (f) of this AD; or (4) If cracks are found as a result of the inspections required by paragraphs (c), (d), (e), or (f) of this AD, and they are repaired in accordance with paragraph (g) of this AD. (i) 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), ACE-115A, FAA, Small Airplane Directorate. The request shall be forwarded through an FAA Principal Maintenance Inspector, who may concur or comment and then send it to the Manager, Atlanta ACO. (j) 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. (k) The inspections and repairs shall be done in accordance with Lockheed Aeronautical Systems Company (LASC)-Georgia Service Bulletin 382-53-50, Revision 1, dated December 13, 1991, which includes the following list of effective pages: Page Number Revision Level Date 1 - 11, A7, A8 1 December 13,1991 A-1 Original February 14, 1990 A2 - A6, A9 - A33 Original Undated 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 Lockheed Aeronautical Systems Company-Georgia, Attn: Commercial and Customer Support, Dept. 73-05, Zone 0199, 86 South Cobb Drive, Marietta, Georgia 30063. Copies may be inspected at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, Washington; or 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 NW., Room 8401, Washington, DC. (l) This amendment becomes effective on June 29, 1992.
2005-04-16: The FAA is adopting a new airworthiness directive (AD) for certain Pilatus Aircraft Ltd. Models PC-12 and PC-12/45 airplanes. This AD requires you to do a one-time inspection of the windshield de-ice wiring system for heat damage and incorrect wire sizes and to replace any wires that are damaged or the incorrect size. This AD results from mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for Switzerland. We are issuing this AD to detect and replace windshield de-ice wiring of the incorrect size, which could result in heat damage of the windshield de-ice wiring. This failure could lead to possible fire in the overhead panel of the flight compartment.
2023-21-01: The FAA is superseding Airworthiness Directive (AD) 2020-01- 13, which applied to all Dassault Aviation Model MYSTERE-FALCON 200 airplanes. AD 2020-01-13 required revising the existing maintenance or inspection program, as applicable, to incorporate new or more restrictive airworthiness limitations. This AD was prompted by a determination that new or more restrictive airworthiness limitations are necessary. This AD continues to require the actions in AD 2020-01- 13 and require revising the existing maintenance or inspection program, as applicable, to incorporate new or more restrictive airworthiness limitations; as specified in a European Union Aviation Safety Agency (EASA) AD, which is incorporated by reference. The FAA is issuing this AD to address the unsafe condition on these products.