Results
2023-09-08: The FAA is adopting a new airworthiness directive (AD) for certain Bombardier, Inc., Model BD-700-2A12 airplanes. This AD was prompted by a report that certain environmental control system (ECS) pre-cooler clamp assemblies may not conform to specifications. This AD requires an inspection of the pre-cooler clamps and replacement of non- conforming pre-cooler clamps. The FAA is issuing this AD to address the unsafe condition on these products.
2002-08-11: This amendment supersedes an existing airworthiness directive (AD), that is applicable to certain Pratt & Whitney JT9D series turbofan engines. That AD currently requires revisions to the Airworthiness Limitations Section (ALS) of the manufacturer's Instructions for Continued Airworthiness (ICA) to include required enhanced inspection of selected critical life-limited parts at each piece-part exposure. This action adds additional critical life-limited parts for enhanced inspection. This amendment is prompted by an FAA study of in-service events involving uncontained failures of critical rotating engine parts. The actions specified by this AD are intended to prevent critical life-limited rotating engine part failure, which could result in an uncontained engine failure and damage to the airplane.
80-01-08: 80-01-08 PIPER: Amendment 39-3653. Applies to Models PA-31T serial numbers 31T-7920001 thru 7920068, 7920070 thru 7920080; and PA-31T1 serial numbers 31T-7904001 thru 7904044. Compliance required within the next 25 hours of operation as indicated unless already accomplished. To preclude the necessity of inflight engine shutdown due to oil loss caused by leakage of the oil cooler inlet hose assembly, accomplish the following on each engine: Remove engine cowlings and remove oil cooler inlet hose, P/N 80026-05. Cap engine outlet immediately upon removal of hose. Remove the band clamp from the 90-degree fitting end of the fire sleeve and pull fire sleeve back as far as possible to inspect steel braiding for kinking. If kinking is found, replace hose. (Note: Kinking will usually be noticed on the steel braiding between the midpoint of the hose and the 90-degree fitting end.) If no evidence of kinking is found and with band clamp still removed, pressure test hose to 500 psi using dry nitrogen with hose submerged in water. (Note: A suitable pressure test arrangement is to cap both ends of the hose with appropriate AN hardware items, one of which has been drilled and fitted with a Schrader valve.) If leakage is observed, replace hose with a new oil inlet hose, P/N 80026-05. If test indicates no leakage, install new band clamp on fire sleeve. Reinstall tested hose or new hose as required per above instructions. Reinstall support clamp, maintaining the maximum possible bend ratios to prevent kinking of hose, check engine oil supply, and replenish if necessary. Run engine; insure that no oil leaks exist, and reinstall cowling. Equivalent methods of compliance must be approved by the Chief, Engineering and Manufacturing Branch, Federal Aviation Administration (FAA), Eastern Region. As permitted by FAR 21.197, aircraft may be flown to a base where maintenance required by this Airworthiness Directive can be accomplished. Piper Telex F.L.31-22A dated August 17, 1979, and Emergency Airworthiness Directive dated August 13, 1979, pertain to this subject. This amendment is effective January 14, 1980, and was effective upon receipt by all addressees of an airmail letter, dated August 13, 1979, on this same matter.
80-09-04: 80-09-04 PIPER AIRCRAFT CORPORATION: Amendment 39-3749. Applies to Model PA-34-200, serial numbers 34-E4, 34-7250001 through 34-7450220, Model PA-34-200T, serial numbers 34-7570001 through 34-7770441, airplanes certificated in all categories. Compliance is required as indicated, unless already accomplished. To prevent elongation or cracking of fitting holes and wearing of attaching nuts and bolts of the vertical fin attachment fittings and stabilator attachment and stabilator hinge assembly, accomplish the following within 25 hours time in service after the effective date of this AD: a. Inspect, replace parts and modify, as necessary, the vertical fin attachment fittings and stabilator attachment and stabilator hinge assembly in accordance with Piper Aircraft Corporation Service Bulletin No. 579, dated November 14, 1977, or in an equivalent manner approved by the Chief, Engineering and Manufacturing Branch, FAA, Southern Region. b. Make appropriate maintenancerecord entry. This amendment becomes effective April 24, 1980.
79-26-05: 79-26-05 AIRCRAFT METAL PRODUCTS CORPORATION: Amendment 39-3645. Applies to all general aviation airplanes with Aircraft Metal Products oil and fuel system hoses P/N 762506 installed. The subject hose is known to be installed on, but not limited to, certain Piper Model PA-28 and PA-32 aircraft. To prevent possible fire or explosion in the engine compartment or engine failure due to loss of engine oil, accomplish the following within 10 hours time in service from the effective date of this AD: (a) Inspect hoses for fluid leakage, excessive abrasion or excessive length. Replace hose if fluid leakage, excessive abrasion or excessive length exists. (b) Loosen each coupling fitting and notice if hose moves in direction of fitting, indicating a pre-existing hose twist. Replace the hose if there is evidence of a pre-existing hose twist. (c) Retighten each coupling fitting, gripping the collar just behind the fitting with pliers with just enough force to keep the hose from turning with the retightened fitting. If the hose turns with the retightened fitting, loosen the coupling fitting and repeat the retightening procedure. (d) Inspect the hose installation for adequate separation between metal hose and other parts of the airplane. If there is contact between metal parts, then complete insulation must be provided using AN742 cushion clamps and/or KOROSEAL lacing or equivalent. (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 required by this AD. (f) Alternative inspections, modifications or other actions which provide an equivalent level of safety may be used when approved by the Chief, Aircraft Engineering Division, FAA Western Region. This amendment becomes effective January 3, 1980.
2023-09-11: The FAA is superseding Airworthiness Directive (AD) 2019-24- 13, which applied to certain Airbus SAS Model A318 series airplanes; Model A319-111, -112, -113, -114, -115, -131, -132, and -133 airplanes; Model A320-211, -212, -214, -216, -231, -232, and -233 airplanes; and Model A321-111, -112, -131, -211, -212, -213, -231, and -232 airplanes. AD 2019-24-13 required repetitive high-frequency eddy current (HFEC) inspections for cracking of a stiffener of a certain lateral window frame, and applicable related investigative and corrective actions. This AD was prompted by a determination that certain inspection times need to be revised. This AD retains the requirements of AD 2019-24-13, with amended compliance times, 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.
2023-09-12: The FAA is adopting a new airworthiness directive (AD) for certain Pilatus Aircraft Ltd. (Pilatus) Model PC-12, PC-12/45, PC-12/ 47, and PC-12/47E airplanes. This AD is prompted by 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 identifies the unsafe condition as insufficient grounding of the vapor cycle cooling system (VCCS) compressor/condenser. This AD requires inspecting the power return and chassis grounding cable attachment points at frame 37, including the attachment parts, and depending on the inspection results, corrective action. This AD also requires modifying the installation of the VCCS compressor/condenser power return cables and installing an additional isolated VCCS chassis ground cable. The FAA is issuing this AD to address the unsafe condition on these products.
2002-08-16: This amendment supersedes an existing airworthiness directive (AD) for the specified Eurocopter France (ECF) model helicopters. That AD currently requires replacing each affected unairworthy main rotor head torsion tie bar (tie bar) with an airworthy tie bar and revising the limitations section of the maintenance manual by adding a life limit for certain tie bars. This amendment requires additional revisions to the limitations section of the maintenance manual by further reducing the life limit for certain tie bars. This amendment is prompted by an accident involving an ECF Model SA341G helicopter due to the failure of a tie bar. The actions specified by this AD are intended to prevent failure of a tie bar, loss of a main rotor blade, and subsequent loss of control of the helicopter.
2011-02-04: We are adopting a new airworthiness directive (AD) for the products listed above. This AD requires repetitively inspecting the cockpit heated windshields for damage and replacing damaged windshields. This AD was prompted by reports from the windshield manufacturer of inner glass ply fracture. We are issuing this AD to detect and correct damage to the cockpit heated windshield, which could result in failure of the windshield with consequent rapid cabin decompression and loss of control of the airplane.
86-16-09: 86-16-09 BRITISH AEROSPACE VISCOUNT: Amendment 39-5377. Applies to Vickers Viscount Model 800 series airplanes, certificated in any category. Compliance is required as indicated, unless previously accomplished. To prevent nose landing gear collapse as a result of a faulty hydraulic cut out valve, accomplish the following: A. Within the next 1,000 hours time-in-service or nine months after the effective date of this AD, whichever occurs first, modify the cut out valve, Part Number AIR 41916, in accordance with Automotive Products Modification Standard SA 3490, dated December 16, 1959 (reference BAe Technical News Sheet No. 232, Issue 1, dated August 5, 1985). B. An 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, Standardization Branch, ANM-113, FAA, Northwest Mountain Region. C. Special flight permits may be issued in accordance with FAR 21.197 and 21.199 tooperate airplanes to a base for the accomplishment of inspections and/or modifications required by this AD. All persons affected by this directive, who have not already received the appropriate service document from the manufacturer, may obtain copies upon request to British Aerospace, Inc., Box 17414, Dulles International Airport, Washington, D.C. 20041. This document may be examined at the FAA, Northwest Mountain Region, 17900 Pacific Highway South, Seattle, Washington, or the Seattle Aircraft Certification Office, 9010 East Marginal Way South, Seattle, Washington. This amendment becomes effective September 8, 1986.
79-12-02: 79-12-02 PIPER AIRCRAFT CORPORATION: Amendment 39-3484 as amended by Amendment 39-3501. Applies to the following Model PA-31 series airplanes, certificated in all categories: PA-31; PA-31-300; PA-31-325, S/N 31-5 through 31-7912049 inclusive; PA-31-350, S/N 31-5001 through 31-7952091 inclusive; PA-31P, S/N 31P-1 and up; PA-31T, S/N 31T-7400002 through 31T-7920060 inclusive; and PA-31T1, S/N 31T-7804001 through 31T-7904031 inclusive. Compliance required within the next 25 hours' time in service after the effective date of this AD,unless already accomplished. To prevent the possible restriction of elevator surface travel, accomplish the following: a. Remove the upper and lower tail cone halves and gain access to the elevator hinge assembly (Piper P/N 40249-00, 45253-00, or 45253-03 as applicable). b. Inspect the elevator stop bolts (Piper P/N 419 991) and lock nuts (Piper P/N 404 224) for signs of looseness or damage, or evidence of movement. Repair or replace,as necessary, in accordance with the airplane service manual. c. Verify proper elevator travel in accordance with Section 5 of the airplane service manual. Elevator surface travel limits are also given in the airplane Type Certificate Data Sheet. d. Torque elevator stop bolt lock nuts to 20-25 inch/pounds, and recheck elevator surface travel. e. Paint or install a slip stripe or torque seal on lock nuts and stop bolts. f. Reinstall tail cone. g. If above inspections find any indications of loose or damaged stop bolts and/or lock nuts, or if elevator surface travel does not meet specification surface travel limits, report findings within 10 days to Chief, Engineering and Manufacturing Branch, FAA, Southern Region, P.O. Box 20636, Atlanta, Georgia 30320, also giving the airplane serial number, the owner/operator of the airplane, and the person and/or facility conducting the inspection. (Reporting approved by the Office of Management and Budget under OMB No. 04-R0174.) Piper Service Bulletin No. 649 also pertains to this subject. Compliance with the provisions of this AD may be accomplished in an equivalent manner approved by the Chief, Engineering and Manufacturing Branch, FAA, Southern Region. Amendment 39-3484 was effective June 14, 1979. This amendment 39-3501 is effective July 2, 1979.
2023-09-07: The FAA is superseding Airworthiness Directive (AD) 2022-02-01 for Sikorsky Aircraft Corporation Model S-92A helicopters with certain part-numbered main rotor stationary swashplate assemblies (swashplate assemblies) that had accumulated 1,600 or more total hours time-in- service (TIS) installed. AD 2022-02-01 required visually inspecting the swashplate assembly at specified intervals and depending on the results, removing the swashplate assembly from service. Since the FAA issued AD 2022-02-01, the FAA determined it was necessary to expand the applicability and require more detailed inspections to address the unsafe condition. This AD retains the actions of AD 2022-02-01, expands the applicability, adds a detailed recurring visual inspection, and requires either eddy current inspections (ECI) or fluorescent penetrant inspections (FPI). The FAA is issuing this AD to address the unsafe condition on these products.
2002-08-10: This amendment adopts a new airworthiness directive (AD) that is applicable to certain Boeing Model 747 series airplanes. This action requires a one-time inspection to identify all alloy steel bolts on the body station 1480 bulkhead splice, and corrective action if necessary. This action provides for optional terminating action for certain requirements of this AD. This action is necessary to detect and correct cracked or broken bolts, which could result in structural damage and rapid depressurization of the airplane. This action is intended to address the identified unsafe condition.
69-22-02: 69-22-02 PIPER: Amdt. 39-865 as amended by Amendment 39-1288 is further amended by Amendment 39-3521. Applies to the following models: PA-28-140, /-150, /-160, /-180, /-235, and PA-32-260/-300. The following are affected serial numbers: PA-28-140, 28-20001 through 28-7725290 inclusive; PA-28-150/-160/-180, 28-1 through 28-4377 inclusive; PA-28-235, 28- 10001 through 28-11039 inclusive; PA-32-260, 32-1 through 32-1110 inclusive; and PA-32-300, 32-40001 through 32-40565 inclusive. Compliance required within 25 hours time in service from the effective date of this AD, unless already accomplished within the last 75 hours time in service, and thereafter at intervals not to exceed 100 hours time in service from the last inspection. To prevent possible failure of the control wheel, accomplish the following: (a) Remove the Piper medallion from the face of each control wheel. (b) Inspect each control wheel for cracks which may extend radially from the retaining pin.Cracks may be evident on the bottom of the control wheel hub where the pin enters the wheel as line cracks on the face or back of the hub as a crack in the hub cavity in line with the pin. The inspection is to be done using either of the following methods: (1) Use a small pen light next to the surface and inspect under at least a three-power glass. Inspect in at least a 1/2" path from the top of the pin to the bottom on the front and back of the control wheel hub. Cracks, either needle shaped or extending across the entire surface will show as black lines in the light field. If a line is only a scratch, the bottom will always be visible. The wheel should be cleaned with ordinary detergent and water only. The use of chemical cleaners and/or solvents such as acetone must be avoided. (2) An equivalent inspection method approved by the Chief, Engineering and Manufacturing Branch, FAA Southern Region. (c) If cracks are found in the path along the hub as described in (b)(1), replace the control wheel before further time in service. This AD is applicable to new control wheels of the same part number installed in accordance with this paragraph. (d) The control wheel medallion may be replaced with regular contact cement which has been allowed to dry thoroughly before assembly or with any commercial 2-part epoxy adhesive. Under no circumstances use acetate adhesive or other plastic cements or any form of Locktite as these materials may not be compatible with the plastic material in the wheel. (e) The repetitive inspection requirements of this AD may be terminated by replacing the plastic control wheel(s) with metal ramshorn type control wheel Piper part number 78729-02V (.750" o.d. shaft) or 79276-00V (1.125" o.d. shaft) as applicable. Replacement of one control wheel (i.e., left or right) does not terminate the requirement for continuing repetitive inspections of the other control wheel, if that other control wheel is the molded plastic type. (f) Piper Service Letter No. 527D, dated June 21, 1978, or later approved revisions, pertains to this same subject. (g) Make appropriate logbook entry indicating compliance with the provisions of this AD. Amendment 39-865 became effective November 4, 1969. Amendment 39-1288 became effective September 15, 1971. This amendment 39-3521 becomes effective July 30, 1979.
2023-08-04: The FAA is adopting a new airworthiness directive (AD) for certain The Boeing Company Model 787-8, 787-9, and 787-10 airplanes. This AD was prompted by reports of a loss of water pressure during flight and water leaks that affected multiple pieces of electronic equipment. This AD requires a detailed visual inspection of all door 1 and door 3 lavatory and galley potable water systems for any missing or incorrectly installed clamshell couplings, and applicable on-condition actions. The FAA is issuing this AD to address the unsafe condition on these products.
79-13-03: 79-13-03 PIPER AIRCRAFT CORPORATION: Amendment 39-3485. Applies to the following Piper models of aircraft certificated in all categories: PA-28-161, S/N 28-7816340 through 28-7916410; PA-28-181, S/N 28-7890276 through 28-7990429; PA-28-236, S/N 28-7911001 through 28-7911167; PA-28-201T, S/N 28-7921001 through 28-7921028; PA-28R-201, S/N 28R-7837150 through 28R-7837317; PA-28R-201T, S/N 28R-7803185 through 28R-7803373; PA-28RT-201, S/N 28R-7918001 through 28R-7918128; PA-28RT-201T, S/N 28R-7931001 through 28R-7931187. \n\n\tCompliance is required as indicated, unless already accomplished. \n\n\tTo prevent a potential fire hazard, accomplish the following: \n\n\t(a)\tPrior to the next flight after the effective date of this AD and prior to each flight thereafter until compliance with the requirements of paragraph (b)(1) through (b)(7) have been accomplished, check for evidence of fuel leaks, wetting, fuel stains, and/or fumes at inboard area of both wings, and in the cabin area. Makeappropriate maintenance record entry. \n\n\t(b)\tIf, as a result of checks required by paragraph (a), leakage, wetting, fuel stains or fumes are evident, accomplish the following prior to further flight: \n\n\t\t(1)\tGain access to all Parker-Hannifin unions (identified D1 or D1PH6) located at inboard areas of both wings, under the left cabin side panel and in the spar box area. For 201T models only, include vent line fitting at lower aft corner of the door. \n\n\t\t(2)\tTorque each fitting to the requirements of Table I. \n\n\t\t(3)\tMeasure the distance between the face of union and face of tubing fitting. Refer to Figure I. \n\n\t\t(4)\tIf torque and/or dimensions are not in accordance with the requirements of Table I and Figure I, comply with paragraph (c). \n\n\t\t(5)\tFill the airplane tanks full of fuel and run engine for three (3) to five (5) minutes on each tank. \n\n\t\t(6)\tInspect fittings for leakage and if no leaks are found, no further action is necessary except for the appropriate maintenance record entry. \n\n\t\t(7)\tIf leakage is still evident, comply with the requirements of paragraph (c). \n\n\t(c)\tIf as a result of checks or inspections required by this Airworthiness Directive, the fittings or unions are found damaged, they continue to leak, or they do not comply with the requirements of Table I and Figure I, correct in accordance with (1), (2), or (3) below and accomplish paragraphs (b)(4), (b)(5), and (b)(6). \n\n\t\t(1)\tRemove the leaking union and replace it using a standard "AN" fitting as outlined in AC 43.13-1A, paragraphs 393 and 709, or \n\n\t\t(2)\tReplace with Piper preswaged and preseated tube and union and apply thread lube as outlined in Table II. Carefully align the tube, snug up the nut finger tight, and tighten the nut one (1) to two (2) flats (1/6 to 1/3 of a turn). Maintain dimensional tolerance of Figure I, or \n\n\t\t(3)\tRepair by using the same size Parker-Hannifin unions and fittings which have not been preswaged or preseated. Apply thread lube asoutlined in Table II, snug up the nut finger tight, and using a tube wrench tighten the nut one and one-quarter (1-1/4) turns. \n\n\t(d)\tWithin the next 100 hours time in service after the effective date of this Airworthiness Directive, comply with the requirements of paragraphs (b)(1) through (b)(7), unless already accomplished. \n\n\t(e)\tChecks specified in paragraph (a) may be accomplished by the pilot. \n\n\t(f)\tCompliance with the provisions of this Airworthiness Directive may be accomplished in an equivalent manner approved by the Chief, Engineering and Manufacturing Branch, Southern Region. \n\n\n\n\nTABLE I \nTUBE SIZE\nAPPLIED TORQUE\nEQUIPMENT \n1/4 OD\n75-95 inch pounds\nUse a tubing crows foot\n3/8 OD\n175-195 inch pounds\n\n\n\nTABLE II\nSlip spray lubricant (Dupont), or equivalent.\nFerulube (Parker-Hannifin), or equivalent. \nApply the lubricant to the male connector thread. \nDo not allow lubricant to enter the throat of the connector seat or contact the ferrule seat face.\n\t\n\n\t\n\n\n\tPiper Service Bulletin No. 638 pertains to this subject. \n\n\tThis amendment becomes effective June 8, 1979, except those for whom it became effective May 2, 1979 by airmail letter.
2023-09-02: The FAA is adopting a new airworthiness directive (AD) for all MHI RJ Aviation ULC Model CL-600-2B19 (Regional Jet Series 100 & 440); CL-600-2C10 (Regional Jet Series 700, 701, & 702); CL-600-2C11 (Regional Jet Series 550); CL-600-2D15 (Regional Jet Series 705); CL-600-2D24 (Regional Jet Series 900); and CL-600-2E25 (Regional Jet Series 1000) airplanes. This AD was prompted by a determination that aircraft maintenance manual (AMM) tasks and certification maintenance requirement (CMR) tasks are necessary. This AD requires revising the existing maintenance or inspection program, as applicable, to incorporate new or more restrictive AMM and CMR tasks. The FAA is issuing this AD to address the unsafe condition on these products.
2001-25-52: This document publishes in the Federal Register an amendment adopting Airworthiness Directive (AD) 2001-25-52, which was sent previously to all known U.S. owners and operators of Schweizer Aircraft Corporation (Schweizer) Model 269A, 269A-1, 269B, 269C, and TH-55A helicopters by individual letters. This AD supersedes an existing AD that requires inspecting and modifying or replacing, if necessary, the aluminum end fittings of each tailboom support strut (strut). That AD also requires inspecting the tailboom center attach fittings and center frame aft cluster fittings for damage, and if damaged parts are found, replacing the damaged parts. This AD requires inspecting and replacing, if necessary, each strut clevis lug (lug) on each tailboom center frame aft cluster fitting (cluster fitting), certain strut assemblies, certain tailboom attachments, and certain frame aft cluster fittings. Modifying or replacing each strut assembly within a certain time period and serializing certain strut assemblies are also required. This AD is prompted by an accident in the United Kingdom involving the in-flight structural failure of a Schweizer Model 269C helicopter. The actions specified by this AD are intended to prevent failure of a lug on a cluster fitting, rotation of a tailboom into the main rotor blades, and subsequent loss of control of the helicopter.
2023-09-06: The FAA is adopting a new airworthiness directive (AD) for all CFM International, S.A. (CFM) 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), forward outer seals, and compressor rotor stages 6-10 spools were manufactured from material suspected to have reduced material properties due to iron inclusion. This AD requires replacement of certain HPT stage 1 disks, forward outer seals, and compressor rotor stages 6-10 spools. The FAA is issuing this AD to address the unsafe condition on these products.
2023-08-07: The FAA is adopting a new airworthiness directive (AD) for Allied Ag Cat Productions, Inc. (Allied Ag Cat) Model G-164A and G-164B airplanes with certain supplemental type certificates (STCs) installed. This AD was prompted by an accident involving an Allied Ag Cat Model G- 164B airplane where the airplane's propeller pitch control (PPC) linkage detached from the PPC of the engine and resulted in an accident that significantly damaged the airplane and injured the pilot. This AD requires installing a secondary retention feature (bolt, washer, and safety wire) on the PPC lever and the PPC assembly. The FAA is issuing this AD to address the unsafe condition on these products.
2002-08-09: This amendment adopts a new airworthiness directive (AD) that is applicable to one McDonnell Douglas Model DC-9-31 airplane. This action requires an inspection to determine if a certain alternating current (AC) cross-tie relay is installed; replacement of a certain AC cross-tie relay with a new AC cross-tie relay; and repetitive cleaning, inspection, repair, and testing of a certain AC cross-tie relay. This action is necessary to prevent AC cross-tie relay failures, which could result in internal arcing of the relay and smoke and/or fire in the cockpit and cabin. This action is intended to address the identified unsafe condition.
2002-08-08: This amendment adopts a new airworthiness directive (AD) that is applicable to certain Bombardier Model CL-600-2B16 (CL-601-3R and CL-604) series airplanes. This action requires a one-time inspection to detect chafing and other damage of the integrated drive generator (IDG) cables on both left and right engines between the service pylon connections to the IDG, corrective action if necessary, and installation of protective Teflon tubing and additional clamps on the IDG cable harnesses. This action is necessary to prevent electrical arcing between the IDG cable and the engine cowling, which could result in in-flight fire and/or loss of electrical power. This action is intended to address the identified unsafe condition.
2023-07-06: 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 corrosion on the horizontal stabilizer lower center skin panel, including a finding of corrosion where the skin thickness had been substantially reduced, which affected design margins. This AD requires inspecting the horizontal stabilizer lower center skin panel for corrosion, and reworking, repairing, or replacing the lower center skin panel if necessary. The FAA is issuing this AD to address the unsafe condition on these products.
2002-06-01: This amendment supersedes two existing airworthiness directives (ADs), applicable to certain Airbus Model A319, A320, and A321 series airplanes. The first AD currently requires removing the existing forward pintle nut and cross bolt on the main landing gear (MLG), and installing a new nylon spacer and cross bolt and nut. The second AD currently requires repetitive inspections for discrepancies of the lock bolt for the pintle pin on the MLG, follow-on corrective actions if necessary, and retorquing of the forward pintle pin lock bolt for certain airplanes. That AD also provides an optional terminating action. This amendment cancels the requirements of the first AD, continues the requirements of the second AD, and requires the previously optional terminating action that the second AD provides. 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 a rotated, damaged, or missing lock bolt, which could result in disengagement of the pintle pin from the pintle fitting bearing, and consequent collapse of the MLG during landing.
2025-11-02: The FAA is adopting a new airworthiness directive (AD) for certain Airbus SAS Model A319-151N, -153N, -171N, and -173N airplanes; A320-251N, -252N, -253N, -271N, -272N, and -273N airplanes; A321-251N, -251NX, -252N, -252NX, -253N, -253NX, -253NY, -271N, -271NX, -272N, and -272NX airplanes. This AD was prompted by reports of lost synchronization between radio management panels (RMPs). This AD requires revising the existing airplane flight manual (AFM) by providing instructions to address dual loss of RMP data synchronization. The FAA is issuing this AD to address the unsafe condition on these products.