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68-25-04: 68-25-04 VICKERS: Amendment 39-691. Applies to Viscount Models 744, 745D and 810 Series Airplane. Compliance required as indicated unless already accomplished. To prevent fatigue failure of the nose wheel steering twin relief valve, P/N 70026 Sh. 35 at the valve body halves P/N 70026, Part 251 and Part 253, accomplish the following: (a) Inspect the valve body halves as specified in paragraph (b) at the following times: (1) Valves having less than 14,650 hours time in service on the effective date of the AD must be inspected prior to the accumulation of 15,000 hours time in service and thereafter at intervals not to exceed 2500 hours time in service. (2) Valves that have accumulated 14,650 or more but less than 20,000 hours time in service on the effective date of this AD must be inspected within the next 350 hours time in service and thereafter at intervals not to exceed 2500 hours time in service. (3) Valves that have accumulated 20,000 or more but lessthat 22,800 hours time in service on the effective date of this AD must be inspected within the next 350 hours time in service and thereafter at intervals not to exceed 1000 hours time in service. (4) Valves that have accumulated 22,800 or more hours time in service on the effective date of this AD must be inspected within the next 350 hours time in service. (b) Inspect the valve body halves for cracks at the fluid transfer holes by a dye penetrant method in accordance with British Aircraft Corporation Viscount Preliminary Technical Leaflet No. 265 Issue 2 (700 Series) or No. 128 Issue 2 (810 Series) or later ARB approved issue or an FAA approved equivalent. (c) Replace the valve body halves in accordance with paragraph (d) at the following times: (1) If cracks are found during the inspections required by paragraph (a), replace the valve body halves prior to further flight. (2) If no cracks are found during the inspections required by paragraph (a), replace the valve body halves as follows: (i) Valves having less than 14,650 hours time in service on the effective date of this AD, must be replaced before the accumulation of 20,000 hours time in service. (ii) Valves having 14,650 or more but less than 22,800 hours time in service on the effective date of this AD must be replaced before the accumulation of 23,500. (iii) Valves having 22,800 or more hours time in service on the effective date of this AD must be replaced within the next 750 hours time in service after the effective date of this AD. (d) Replace valve body halves with parts having the same part numbers which have been inspected and found to have no cracks or with new valve body halves P/N 70026-637-639. (e) Valves of the same part numbers used as replacements must continue to be inspected in accordance with paragraph (a) and replaced in accordance with paragraph (c). Compliance with the inspection and replacement requirements of this AD may be discontinued when new valves P/N 70026-637-639 are incorporated. This amendment becomes effective January 7, 1969.
2004-18-07: This amendment supersedes an existing airworthiness directive (AD), applicable to certain BAE Systems (Operations) Limited Model BAe 146 and Avro 146-RJ series airplanes, that currently requires identifying the part numbers of discharge valves and cabin pressure controllers, and related investigative and corrective actions if necessary. This amendment requires identifying the part number of an additional cabin pressure controller, and related investigative and corrective actions if necessary. The actions specified by this AD are intended to prevent the installation of incorrect pressurization discharge valves and cabin pressure controllers, which could subject the airframe to excess stress and adversely affect the airframe fatigue life. This action is intended to address the identified unsafe condition. DATES: Effective October 13, 2004. The incorporation by reference of a certain publication listed in the regulations is approved by the Director of the Federal Register as of October 13, 2004. The incorporation by reference of a certain other publication listed in the regulations was approved previously by the Director of the Federal Register as of September 10, 2001 (66 FR 40864, August 6, 2001).
2012-18-13 R1: We are revising an existing airworthiness directive (AD) for all The Boeing Company Model 737-100, -200, -200C, -300, -400, and -500 series \n\n((Page 27021)) \n\nairplanes. That AD currently requires repetitive inspections to detect cracking in the web of the aft pressure bulkhead at body station 1016 at the aft fastener row attachment to the ''Y'' chord, various inspections for discrepancies at the aft pressure bulkhead, and related investigative and corrective actions if necessary. This new AD requires clarifying certain actions specified in the existing AD. This AD was prompted by several reports of fatigue cracks in the aft pressure bulkhead. We are issuing this AD to detect and correct such fatigue cracking, which could result in rapid decompression of the fuselage.
2022-13-14: The FAA is adopting a new airworthiness directive (AD) for all Airbus Helicopters Model AS-365N2, AS 365 N3, EC 155B, EC155B1, and SA- 365N1 helicopters. This AD was prompted by a large amount of critical scale particles found on the tail rotor gearbox (TGB) chip detector magnetic plug during an unscheduled check of the TGB. The particles belonged to the double bearing (pitch control rod bearing) installed inside the TGB. This AD requires repetitive inspections of the TGB chip detector for particles, analyzing any particles collected, performing a double bearing washing, repetitive replacements of certain part- numbered double bearings, and corrective actions if necessary, 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.
47-47-12: 47-47-12 REPUBLIC: (Was Mandatory Note 12 of AD-769-2.) Applies to RC-3 Aircraft Serial Numbers 5 Through 1035 Inclusive Except the Following Which Have Been Modified at the Factory: 767, 915, 948, 949, 957, 959 Through 999 Inclusive, 1004 Through 1010 Inclusive, 1014, 1019 Through 1025 Inclusive. Serial 1036 and up Have Been Modified at the Factory Prior to Delivery. Compliance required not later than December 31, 1947. To prevent excessive drop-off in engine r.p.m. when carburetor heat is used, anti-swirl vanes, Republic P/N 17P 68014-20 must be installed in the air duct below the carburetor. (Republic Seabee Service Bulletin No. 18 dated August 26, 1947, covers this same subject.)
59-14-02: 59-14-02 MOONEY: Applies to M-20 Airplanes Serial Numbers 1175 Through 1200 and M-20A Airplanes Serial Numbers 1201 Through 1375. Compliance required prior to August 1, 1959. To guard against fuel selector valve failure and inability to change selector valve position the following inspection and replacement is required prior to August 1, 1959. Replacement valves obtained from the factory after April 27, 1959, and installed need not comply with this AD. (a) Remove fuel tank selector valve. (b) Remove lower part of valve housing and remove plastic core. (c) Determine if the shaft and plastic core are pinned together. If not, replace complete valve assembly with replacement valve P/N 311-221-1/4D obtained from Mooney. (Mooney Service Letter 20-48 concerns this subject.)
92-11-06: 92-11-06 BRITISH AEROSPACE: Amendment 39-8256. Docket No. 92-NM-06-AD. Applicability: British Aerospace Model BAe 146-100A, 200A, and 300A series airplanes, certificated in any category. Compliance: Required as indicated, unless accomplished previously. To prevent the generation of incorrect air speed and altitude information, accomplish the following: (a) For British Aerospace Model BAe 146-200A series airplanes with Serial Numbers E2164 and subsequent; and Model BAe 146-300A series airplanes with Serial Numbers E3118, E3163, and subsequent: Within 30 days after the effective date of this AD, accomplish the actions specified in paragraphs (a)(1), (a)(2), and (a)(3) of this AD, in accordance with instructions in British Aerospace Service Bulletin SB.34-128-00950J, dated March 22, 1991: (1) Replace existing pitot-static system hoses at specified location with shorter hoses. (2) Check the clamp block bolts installation. If any discrepancy is detected, correct it prior to further flight. (3) Conduct a leak test of the pitot-static system. If any discrepancy is detected, correct it prior to further flight. (b) For British Aerospace Model BAe 146-100A, 200A, and 300A series airplanes equipped with a True Airspeed Computer No. 1 in accordance with modification HCM40159B or HCM40297G, along with a Mode "S" Transponder in accordance with modification HCM30118B or HCM40277A: Within 90 days after the effective date of this AD, accomplish the actions specified in paragraphs (b)(1) and (b)(2) of this AD, in accordance with instructions in British Aerospace Service Bulletin SB.34-131-46041A, dated June 24, 1991: (1) Replace existing pitot-static system hoses at specified locations with shorter hoses. (2) Conduct a leak test of the pitot-static system. If any discrepancy is detected, correct it prior to further flight. (c) For British Aerospace Model BAe 146-100A, 200A, and 300A series airplanes equipped with a True Airspeed Computer No. 2 in accordance with modification HCM40160C or HCM40298G, along with a Mode "S" Transponder in accordance with modification HCM30118B or HCM40277A: Within 90 days after the effective date of this AD, accomplish the actions specified in paragraphs (c)(1) and (c)(2) of this AD, in accordance with instructions in British Aerospace Service Bulletin SB.34-132-46042A, dated June 24, 1991: (1) Replace existing pitot-static system hoses at specified locations with shorter hoses. (2) Conduct a leak test of the pitot-static system. If any discrepancy is detected, correct it prior to further flight. (d) 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. The request shall be forwarded through an FAA Principal Maintenance Inspector, who may concur or comment and then send it to the Manager, Standardization Branch, ANM-113. (e) 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. (f) The inspections and modifications shall be done in accordance with British Aerospace Service Bulletin SB.34-128-00950J, dated March 22, 1991; British Aerospace Service Bulletin SB.34-131-46041A, dated June 24, 1991; or British Aerospace Service Bulletin SB.34-132-46042A, dated June 24, 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 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 SW., Renton, Washington; or at the Office of the Federal Register, 1100 L Street NW., Room 8401, Washington, DC. (g) This amendment becomes effective on July 9, 1992.
2004-18-11: This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model DC-9-14, DC-9-15, and DC- 9-15F airplanes; and Model DC-9-20, DC-9-30, DC-9-40, and DC-9-50 series airplanes. This amendment requires, among other actions, performing repetitive inspections for cracking of the counterbore of the two lower mounting holes and the lower forward edge of the outboard idler hinge fitting of the left and right wing flap at station Xw=333.148, and replacing the flap idler hinge fitting with a new or serviceable part. This action is necessary to prevent failure of the outboard idler hinge fitting of the left and right wing flap at station Xw=333.148 due to fatigue cracking, which could result in a deflected flap that may cause asymmetric lift and consequent reduced controllability and structural integrity of the airplane. This action is intended to address the identified unsafe condition.
2022-13-04: The FAA is superseding Airworthiness Directive (AD) 2017-24- 10, which applied to certain The Boeing Company Model 757-200, -200PF, and -300 series airplanes. AD 2017-24-10 required repetitive inspections for any cracking of a certain fuselage frame inner chord; identification of the material of a certain fuselage frame inner chord for certain airplanes; and applicable corrective actions. This AD was prompted by reports of cracking found at a certain fuselage frame inner chord. This AD retains the requirements of AD 2017-24-10, adds airplanes, and requires new inspection types in certain areas, an expanded inspection area, additional inspections, and applicable corrective actions. The FAA is issuing this AD to address the unsafe condition on these products.
2013-08-16: We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 737-700 and -700C series airplanes. This AD was prompted by reports of early fatigue cracks at chem-mill areas on the crown skin panels. This AD requires repetitive inspections for cracking of the fuselage skin at certain locations at chem-mill areas, and repair if necessary. We are issuing this AD to detect and correct fatigue cracking of the skin panel at the specified chem-mill step locations, which could result in rapid decompression of the airplane.
2013-03-18: We are adopting a new airworthiness directive (AD) for Eurocopter Deutschland GmbH (Eurocopter) Model MBB-BK 117 C-2 helicopters. This AD requires inspecting the long tail rotor drive shaft assembly for blind rivets, and if any blind rivets are installed, replacing that shaft assembly. This AD was prompted by the discovery that some helicopters have blind rivets installed in the place of solid rivets in the long tail rotor drive shaft. The actions of this AD are intended to detect blind rivets installed in the long tail rotor drive shaft, which could lead to failure of the tail rotor drive shaft and subsequent loss of control of the helicopter.
99-19-22: This document publishes in the Federal Register an amendment adopting Airworthiness Directive (AD) 99-19-22 which was sent previously to all known U.S. owners and operators of Eurocopter Deutschland GMBH (ECD) Model BO-105A, BO-105C, BO-105 C-2, BO-105 CB-2, BO-105 CB-4, BO-105S, BO-105 CS-2, BO-105 CBS-2, BO-105 CBS-4, and BO-105LS A-1 helicopters by individual letters. This AD requires, before further flight, creating a component log card or equivalent record and determining the age and number of flights on each tension-torsion (TT) strap. The AD also requires inspecting and removing, as necessary, certain unairworthy TT straps. This amendment is prompted by an accident in which a main rotor blade (blade) separated from an ECD Model MBB-BK 117 helicopter because of fatigue failure of the TT strap. The ECD Model MBB-BK 117 and the BO-105 helicopters use the same part-numbered TT strap. The actions specified by this AD are intended to prevent failure of a TT strap, lossof a blade, and subsequent loss of control of the helicopter.
2013-08-15: We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 737-800 series airplanes. This AD was prompted by reports of early fatigue cracks at chem-mill areas on the crown skin panels. This AD requires repetitive inspections for cracking of the fuselage skin along chem-mill steps at certain crown skin and shear wrinkle areas, and repair if necessary. We are issuing this AD to detect and correct fatigue cracking of the skin panel at the specified chem-mill step locations, which could result in rapid decompression of the airplane.
96-18-17: This amendment adopts a new airworthiness directive (AD), applicable to AlliedSignal Inc. (formerly Garrett) TSCP700-4B, -4E, and -5 auxiliary power units (APUs), that requires removal from service of certain high pressure turbine (HPT) disks identified by serial number, and replacement with serviceable parts. This amendment is prompted by the discovery of a material defect in certain HPT disk forgings that may result in HPT disk rupture prior to reaching the disk cyclic life limit. The actions specified by this AD are intended to prevent an HPT disk rupture.
70-06-02: 70-06-02 BELL: Amdt. 39-955. Applies to all Model 204B 205A and 205A-1 helicopters and to any other helicopter incorporating tail rotor hub assembly, P/N 204-011-801-5 or -7 or P/N 204-011-701-11, -13 or -19 and to all spare tail rotor hub assemblies P/N 205-011-801-5 or -7 or P/N 204-011-701-11, -13 or -19. Compliance required as indicated. To prevent failure of the grip assemblies, P/N 204-011-728 or P/N 204-011-706, accomplish the following one time inspection on all tail rotor grip assemblies for proper hardness or conductivity before further flight, unless already accomplished after February 27, 1970. These inspections may be conducted with the grips installed on the helicopter. Determine the hardness of the grip assembly using a Rockwell Hardness or Eddy Current Tester, a Magnatest FM-120 (Magnaflux Corp.) or equivalent. Readings should be taken adjacent to vibro etched serial number between the blade retention bolts on grip face. Inspect all spare grip assemblies before installation. Remove grip assemblies with readings below Rockwell 79 on the "B" scale or above conductivity of 39 on International Annealed Copper Standard. This supersedes Amendment 39-953 (AD 70-06-01) issued by telegram dated February 27, 1970. This amendment is effective March 13, 1970, and was effective for all recipients of the telegram dated March 4, 1970 which contained this amendment.
2004-18-10: This amendment adopts a new airworthiness directive (AD), applicable to certain Bombardier Model DHC-8-102, -103, -106, -201, - 202, -301, -311, and -315 airplanes, that requires inspection of the fitting assemblies located on the vent and scavenge lines routed immediately below the fuel tank access covers on both wings for proper installation, and corrective actions if necessary. This amendment also requires inspection of the stiffeners on the underside of fuel tank access covers on both wings for signs of chafing damage caused by incorrect orientation of the lockwire tail, and removal of damage. This action is necessary to prevent contact between the lockwire pigtail of the fitting and the stiffener located on the inside surface of the fuel access covers of the wings, which could serve as a potential ignition source within the fuel tank if a cover is struck by lightning and result in possible fuel tank explosion. This action is intended to address the identified unsafe condition.
2022-13-05: The FAA is adopting a new airworthiness directive (AD) for certain Bombardier, Inc., Model BD-700-1A10 and BD-700-1A11 airplanes. This AD was prompted by reports of the loss of all air data system information provided to the flightcrew during flight; the air data system information was recovered as the airplane descended to lower altitudes. This AD requires revising the existing airplane flight manual (AFM) to update the Unreliable Airspeed and Landing Distance Factor emergency procedures, which provide instructions for the flightcrew to stabilize the airspeed and altitude. The FAA is issuing this AD to address the unsafe condition on these products.
96-19-07: 96-19-07 BURKHART GROB LUFT-UND RAUMFAHRT: Priority Letter issued on September 6, 1996. Docket No. 96-CE-50-AD. Applicability: Models G115C, G115C2, G115D, and G115D2 airplanes (all serial numbers), certificated in any category. 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 request approval for an alternative method of compliance in accordance with paragraph (f) of this AD. The request should include an assessment of the effect of the modification, alteration, or repair on the unsafe condition addressed by this AD; and, if the unsafe condition has not been eliminated, the request should include specific proposed actions to address it. Compliance: Required prior to further flight after receipt of this priority letter AD, unless already accomplished. To prevent loss of control of the airplane caused by excessive speed or aerobatic maneuvers, accomplish the following: (a) Install, on the limitation placard at the left-hand cabin wall, the airspeed placard that is included with Grob Service Bulletin (SB) 1078-59/2, dated September 2, 1996. This placard reduces the maximum airspeed to 296 kilometers per hour (km/h); equal to 160 knots per hour. (b) Modify the airspeed indicator glass by accomplishing the following: (1) Place a red radial line on the indicator glass at 296 km/h (160 knots). The minimum dimensions for this radial line are 0.05 inches wide and 0.30 inches in length. (2) Place a white 0.05 inch minimum width slippage index mark connecting both the instrument glass and bezel. Locate this slippage index mark so that it does not obscure any airspeed markings. (c) Install, near the airspeed indicator,the red placard included with Grob SB 1078-59/2 that has the words: "Aerobatic maneuvers are prohibited." (d) Insert a copy of this AD into the Limitations Section of the airplane flight manual. (e) Special flight permits may be issued in accordance with sections 21.197 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 compliance time that provides an equivalent level of safety may be approved by the Manager, Brussels Aircraft Certification Division, FAA, Europe, Africa, and Middle East Office, c/o American Embassy, B-1000 Brussels, Belgium. The request shall be forwarded through an appropriate FAA Maintenance Inspector, who may add comments and then send it to the Manager, Brussels Aircraft Certification Division. NOTE 2: Information concerning the existence of approved alternative methodsof compliance with this AD, if any, may be obtained from the Brussels Aircraft Certification Division. (g) The service information and placards specified in this priority letter may be obtained from Burkhart Grob Luft-und Raumfahrt, D-8939 Mattsies, Germany. This information may also be examined at the FAA, Central Region, Office of the Assistant Chief Counsel, Room 1558, 601 E. 12th Street, Kansas City, Missouri 64106. (h) Priority Letter AD 96-19-07, issued September 6, 1996, becomes effective immediately upon receipt.
96-19-17: This amendment adopts a new airworthiness directive (AD) that is applicable to certain Boeing Model 757 series airplanes. This action requires a one-time inspection to detect discrepancies of the main battery shunt, and replacement with a serviceable part, if necessary. This action also requires inspection of certain wires, washers, and brass jam nuts to detect any discrepancy, and replacement with a serviceable part, if necessary. Additionally, this action requires inspection, and adjustment if necessary, of the torque and resistance of the installation of the main battery ground stud. This amendment is prompted by a report of interruption of electrical power during flight due to improper installation of the main battery shunt and ground stud connection of the main battery. The actions specified in this AD are intended to prevent such electrical power interruptions, which could result in loss of battery power to the source of standby power for the airplane.
2004-18-05: The FAA is adopting a new airworthiness directive (AD) for certain Bombardier Model DHC-8-311 airplanes. This AD requires reviewing the airplane maintenance records to determine if you did the most recent bonding integrity inspection according to a certain revision of the Maintenance Program Support Manual (PSM), and doing related investigative and corrective actions if necessary. This AD is prompted by the discovery that a certain revision of the PSM omits several fuselage skin panels from a list of skin panels that must be inspected. We are issuing this AD to prevent disbonding of the subject skin panels, which could reduce the load-carrying capacity of the skin panels and result in reduced structural integrity of the airplane.
2022-13-08: The FAA is adopting a new airworthiness directive (AD) for certain De Havilland Aircraft of Canada Limited Model DHC-8-401 and - 402 airplanes. This AD was prompted by reports of nose wheel steering (NWS) hydraulic motors jamming during pushback or towing. This AD requires doing an inspection to determine the part number and serial number of the NWS hydraulic motor, and re-identifying or replacing the NWS hydraulic motor if necessary. This AD also prohibits the installation of certain NWS hydraulic motors. The FAA is issuing this AD to address the unsafe condition on these products.
68-06-05: 68-06-05 FAIRCHILD-HILLER: Amdt. 39-565. Applies to FH-1100 type helicopters serial numbers 10 thru 76 inclusive and 83. Compliance required as indicated unless already accomplished. To preclude the possibility of failure of the engine-to-transmission coupling shaft due to corrosion resulting from water contamination, accomplish the following: (a) Within the next 100 helicopter hours' time in service following the effective date of this AD, remove Bendix coupling shaft P/N 19E49-3A and inspect for any corrosion and if found, replace with P/N 19E49-3B or if corrosion is absent modify in accordance with accomplishment instructions contained in Fairchild Hiller Service Bulletin No. FH-1100-24-1 dated January 25, 1968, or later FAA approved revision, or an equivalent inspection procedure or modification approved by the Chief, Engineering and Manufacturing Branch, FAA Eastern Region. (b) Upon request, with substantiating data submitted through an FAA maintenance inspector, the compliance time may be increased by the Chief, Engineering and Manufacturing Branch, FAA Eastern Region. This amendment is effective March 23, 1968.
2022-14-02: The FAA is adopting a new airworthiness directive (AD) for certain CFM International, S.A. LEAP-1A23, LEAP-1A24, LEAP-1A24E1, LEAP-1A26, LEAP-1A26CJ, LEAP-1A26E1, LEAP-1A29, LEAP-1A29CJ, LEAP-1A30, LEAP-1A32, LEAP-1A33, LEAP-1A33B2, and LEAP-1A35A (LEAP-1A) model turbofan engines. This AD was prompted by a manufacturer investigation that revealed that certain high-pressure turbine (HPT) rotor stage 1 disks (HPT stage 1 disks) and a stages 6-10 compressor rotor spool were manufactured from material suspected to contain iron inclusion. This AD requires the replacement of certain HPT stage 1 disks and a stages 6-10 compressor rotor spool. The FAA is issuing this AD to address the unsafe condition on these products.
2004-18-02: This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 737-600, 737-700, 737-700C, 737-800, and 737-900 series airplanes, that requires measuring the electrical resistance of the support bracket for the fire extinguisher bottle located in the left main landing gear wheel well to ensure that it does not exceed the maximum allowed resistance; and corrective actions, if necessary. This action is necessary to prevent high electrical resistance in the squib firing circuit, which could result in insufficient electrical current to fire the fire extinguisher bottle squib and discharge the fire extinguishing agent, which could lead to an uncontrolled engine fire. This action is intended to address the identified unsafe condition.
2022-13-19: The FAA is superseding Airworthiness Directive (AD) 2022-11- 03, which applied to certain Airbus SAS Model A350-941 and -1041 airplanes. AD 2022-11-03 required revising the existing airplane flight manual (AFM), and revising the operator's existing FAA-approved minimum equipment list (MEL) by incorporating certain master minimum equipment list (MMEL) provisions, to include limitations and procedures to mitigate the risk of elevator failure during flare. Since the FAA issued AD 2022-11-03, an updated software standard for the PRIMary flight control computers (PRIMs) has been developed to address the unsafe condition. This AD continues to require the actions in AD 2022- 11-03, and also requires installing an updated PRIM software standard, 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.