Results
2017-18-11: We are adopting a new airworthiness directive (AD) for certain Textron Aviation Inc. Model 390 airplanes (type certificate previously held by Beechcraft Corporation). This AD was prompted by reports of hydraulic fluid loss from the engine driven pumps (EDPs) on three different airplanes. This AD requires an inspection to determine if an affected EDP is installed with replacement as necessary. We are issuing this AD to address the unsafe condition on these products.
2011-01-08: We are superseding an existing airworthiness directive (AD) that applies to 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: Two reports have been received where, during inspection of the vertical stabilizer of F28 Mark 0100 aeroplanes, one of the bolts that connect the horizontal stabilizer control unit actuator with the dog-links was found broken (one on the nut side & one on the head side). In both occasions, the bolt shaft was still present in the connection and therefore the horizontal stabilizer function was not affected. If a single dog-link connection fails, the complete stabilizer load is taken up by the remaining dog-link connection. * * * To address and correct this unsafe condition EASA [European Aviation Safety Agency] issued AD 2007-0287[corresponding FAA AD 2008-22-14] that required a one-time inspection of the affected bolts, * * * and replacement of failed bolts with serviceable parts. EASA AD 2007-0287 also required the installation of a tie wrap through the lower bolts of the horizontal stabilizer control unit, to keep the bolt in place in the event of a bolt head failure. Recent examination revealed that the bolts failed due to stress corrosion, attributed to excessive bolt torque. Investigation of the recently failed bolts showed that the modification as required by AD 2007-0287 is not adequate. * * * * * Loss of horizontal stabilizer function could result in partial loss of control of the airplane. We are issuing this AD to require actions to correct the unsafe condition on these products.
2011-01-13: 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: During a routine maintenance check on an A300-600 aeroplane, the operator found the pitch uncoupling unit installed at an incorrect location. The pitch uncoupling unit was inverted with the rod assembly. After a complete inspection of all A300-600 aeroplanes of its fleet, the operator identified the same incorrect installation on another aeroplane. * * * * * This condition, if not detected and corrected, in combination with particular failure modes, could lead to loss of control of the aeroplane during the takeoff phase. * * * * * This AD requires actions that are intended to address the unsafe condition described in the MCAI.
2023-03-05: The FAA is superseding Airworthiness Directive (AD) 2022-09- 06, which applied to certain Airbus SAS Model A350-941 and -1041 airplanes. AD 2022-09-06 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 2022-09- 06 and requires revising the existing maintenance or inspection program, as applicable, to incorporate additional new or more restrictive airworthiness limitations, as specified in a European Union Aviation Safety Agency (EASA) AD. The FAA is issuing this AD to address the unsafe condition on these products.
93-14-17: 93-14-17 AEROSPATIALE: Amendment 39-8641. Docket 93-NM-15-AD. Applicability: Model ATR72-100 and -200 series airplanes on which Modification 3196 has not been installed; certificated in any category. Compliance: Required as indicated, unless accomplished previously. To prevent reduced structural integrity of the wing spar fittings, accomplish the following: (a) Within 12 months after the effective date of this AD, perform a one-time detailed visual inspection of the fastener holes on the front and rear wing spar fittings to ensure that spotfacing of the fastener holes has been accomplished, in accordance with Aerospatiale Service Bulletin ATR72-57-1008, dated November 19, 1992. (1) If spotfacing of the fastener holes has been accomplished, no further action is required by this AD. (2) If spotfacing of the fastener holes has not been accomplished, prior to further flight, perform a one-time general visual inspection of the fastener holes for peening or cracks, in accordance with the service bulletin. (i) If no peening or crack is found, prior to further flight, install a shim and replace existing nuts with self-aligning nuts, in accordance with the service bulletin. (ii) If any peening or crack is found, prior to further flight, repair in accordance with a method approved by the Manager, Standardization Branch, ANM-113, FAA, Transport Airplane Directorate. (b) An alternative method of compliance or adjustment of the compliance time that provides an acceptable level of safety may be used if approved by the Manager, Standardization Branch, ANM-113, FAA, Transport Airplane Directorate. Operators shall submit their requests through an appropriate FAA Principal Maintenance Inspector, who may add comments and then send it to the Manager, Standardization Branch, ANM-113. NOTE: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Standardization Branch, ANM-113. (c) Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate the airplane to a location where the requirements of this AD can be accomplished. (d) The inspections, installation, replacement, and repair shall be done in accordance with Aerospatiale Service Bulletin ATR72-57-1008, dated November 19, 1992. 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 Aerospatiale, 316 Route de Bayonne, 31060 Toulouse, Cedex 03, France. Copies may be inspected at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC. (e) This amendment becomes effective on September 16, 1993.
2017-18-14: We are superseding Airworthiness Directive (AD) 2015-02-22 for certain Rolls-Royce Corporation (RRC) model 250 turboprop and turboshaft engines. AD 2015-02-22 required repetitive visual inspections and fluorescent-penetrant inspection (FPIs) on certain 3rd- stage and 4th-stage turbine wheels for cracks in the turbine wheel blades. This AD requires repetitive visual inspections and FPIs of 3rd- stage turbine wheels while removing from service 4th-stage turbine wheels. We are also revising the applicability to remove all RRC turboprop engines and add additional turboshaft engines. This AD was prompted by our finding that it is necessary to remove the 4th-stage wheels at the next inspection. We are issuing this AD to address the unsafe condition on these products.
2002-01-10: This amendment adopts a new airworthiness directive (AD) that applies to certain Raytheon Aircraft Company (Raytheon) Beech Models 65-90, 65-A90, 65-A90-1, 65-A90-4, B90, C90, C90A, E90, and H-90 airplanes. This AD requires you to repetitively inspect the main landing gear upper torque knees and lower torque knees for evidence of fatigue cracks; and replace any torque knee with evidence of fatigue cracks. This AD is the result of reports of many incidents of main landing gear torque knees cracking or breaking on the above-referenced airplanes. The actions specified by this AD are intended to detect and replace cracked main landing gear torque knees, which could result in failure of the main landing gear and consequent loss of control of the airplane during takeoff, landing, or other ground operations.
89-22-01 R1 L: 89-22-01 R1 BELL HELICOPTER TEXTRON, INC. (BHTI): Priority Letter AD 89-22-01 as revised by Priority Letter AD 89-22-01 R1. Docket No. 89-ASW-54. Applicability: Model 206A, 206B, 206L, 206L-1, and 206L-3 helicopters, certificated in any category, with main rotor blades part numbers (P/N) 206-015-001-001, 206-015-001-103, 206-015-001-105, or 206-010-200-033 installed. Compliance: Required before further flight, unless already accomplished. To prevent failure and separation of the main rotor blades and subsequent loss of the helicopter, accomplish the following: (a) Visually inspect the Model 206A and 206B main rotor blades and determine if one of the following S/N blades is installed: TAC-0089, TAC-0542, TAC-0607, TAC-0614, TAC-0624, TAC-1643, TAC-1749, TAC-1776, TAC-1831, TAC-1911, TAC-1922, TAC-2399, TAC-2768, TAC-5742, TKK-9794, TKK-9883, or TKK-9933. If any one of these main rotor blades is installed, remove and replace with a serviceable part prior tofurther flight. (b) Visually inspect the Model 206L, 206L-1, and 206L-3 main rotor blades and determine if one of the following S/N blades is installed: T-92, T-245, T-417, TLY-0075, TLY- 0095, TLY-0764, TLY-0770, TLY-0973, TLY-1438, TLY-1619, TLY-1653, TLY-1697, TLY- 1766, TLY-1801, TLY-1858, TLY-1953, TLY-1984, TLY-2031, TLY-2039, TLY-2064, TLY- 2081, TLY-2148, TLY-2335, TLY-2337, TLY-2549, TLY-2603, TLY-2604, TLY-2625, TLY- 2633, TLY-2648, TLY-2745, TLY-2786, TLY-2951, or TLY-2954. If any one of these main rotor blades is installed, remove and replace with a serviceable part prior to further flight. NOTE: The serial number may be found on the Bell Helicopter data plate located on top of the blade at the root end and is also marked on the root end of the lower grip plate in the 1.5 inch radius. (c) If the serial number of the main rotor blade matches one listed in paragraph (a) or (b) of this AD, report the registration number and serial number of the affected helicopter and provide a copy of the parts tag with which the part was delivered, if available. This report is to be made to the Manager, Rotorcraft Certification Office, Southwest Region, Federal Aviation Administration, Fort Worth, Texas 76193-0170, telephone (817) 624-5170, within 10 days of the inspection. (Reporting approved by the Office of Management and Budget under OMB No. 2120-0056.) (d) An alternate method of compliance which provides an equivalent level of safety, may be used if approved by the Manager, Rotorcraft Certification Office, Southwest Region, Federal Aviation Administration, Fort Worth, Texas 76193-0170, telephone (817) 624-5170. This Priority Letter AD (89-22-01 R1) issued on November 21, 1989, revises Priority Letter AD 89-22-01, issued on October 18, 1989, and becomes effective immediately upon receipt.
2017-18-09: We are adopting a new airworthiness directive (AD) for all Airbus Defense and Space S.A. Model CN-235, CN-235-100, CN-235-200, CN- 235-300, and C-295 airplanes. This AD was prompted by reports of excessive play between bushings and their respective fitting housings at certain elevator fittings. This AD requires a one-time detailed inspection and repetitive eddy current inspections of the elevator hinge fitting and bracket assembly, and corrective actions if necessary. We are issuing this AD to address the unsafe condition on these products.
2017-18-06: We are superseding Airworthiness Directive (AD) 2012-05-03, which applied to certain The Boeing Company Model 747-100, 747-100B, 747-100B SUD, 747-200B, 747-200C, 747-200F, 747-300, 747-400, 747-400D, 747-400F, 747SR, and 747SP series airplanes. AD 2012-05-03 required modifying the fluid drain path in the leading edge area of the wing. This AD requires additional work to seal those drainage holes in the wing access panels. This AD was prompted by a design review following a ground fire \n\n((Page 41327)) \n\nincident and reports of flammable fluid leaks from the wing leading edge area onto the engine exhaust area. We are issuing this AD to address the unsafe condition on these products.
2010-24-05: 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: As a result of a change in the low-cycle fatigue lifing methodology for the IMI 834 material, the recommended service life of certain PW305A and PW305B Impellers has been reduced, as published in the Airworthiness Limitations (AWL) section of Engine Maintenance Manual (EMM). The in-service life of impellers P/N 30B2185, 30B2486 and 30B2858-01 has been reduced from 12,000 to 7,000 cycles; and of P/N 30B4565-01 from 8,500 to 7,000 cycles. We are issuing this AD to prevent failure of the impeller, which could result in an uncontained event and possible damage to the airplane.
2002-01-14: This amendment supersedes an existing airworthiness directive (AD), applicable to certain Airbus Model A319, A320, and A321 series airplanes, that currently requires an in-situ one-time detailed visual inspection of Draeger Type I oxygen containers, located in the passenger service units, and Draeger Type II oxygen containers, located in the utility areas, for the presence of foam pads. That action also currently requires the installation of a new foam pad, if necessary; and other actions to ensure proper operation of the masks. This amendment retains those requirements and expands the applicability of the existing AD to include additional airplanes that were inadvertently excluded from that AD. The actions specified in this AD are intended to prevent failure of the oxygen containers to deliver oxygen to the passengers in the event of a rapid decompression or cabin depressurization. This action is intended to address the identified unsafe condition.
75-26-03: 75-26-03 BELL: Amendment 39-2451. Applies to Bell Models 204B, 205A-1, and 212 helicopters certificated in all categories. Compliance required within 100 hours' time in service after the effective date of this AD unless already accomplished and, thereafter, at intervals not to exceed 300 hours' time in service from the last inspection. To deter unauthorized access to the emergency exit operating handle and to improve identification of the emergency exit handle and the main sliding door handle, accomplish the following: (a) Inspect the helicopter main passenger doors and the four emergency exits for proper and legible placards and for proper exit handle covers, both inside and outside the helicopter, in accordance with the figures in Bell Helicopter Company Service Bulletins noted in paragraph (c). (b) If proper and legible placards and proper exit handle covers are not installed, install the placards and handle covers as specified in Bell Helicopter Company Service Bulletins noted in paragraph (c). (c) The following Bell Helicopter Company service bulletins, or later approved revisions thereto, apply to the noted helicopter models. (1) Bell Helicopter Company Service Bulletin No. 204-75-2 dated September 16, 1975, for Model 204B. (2) Bell Helicopter Company Service Bulletin No. 205-75-6, Revision A, dated August 22, 1975, for Model 205A-1. (3) Bell Helicopter Company Service Bulletin No. 212-75-7, Revision A, dated August 22, 1975, for Model 212. (d) Equivalent means of compliance with this AD may be approved by the Chief, Engineering and Manufacturing Branch, Flight Standards Division, Federal Aviation Administration, Southwest Region, Fort Worth, Texas. (e) Upon request of the operator, an FAA maintenance inspector, subject to prior approval of the Chief, Engineering and Manufacturing Branch, Flight Standards Division, Federal Aviation Administration, Southwest Region, may adjust the repetitive inspection intervals specified in this AD to permit compliance at an established inspection period of the operator if the request contains substantiating data to justify the increase for that operator. (f) The manufacturer's specifications and procedures identified and described in this directive are incorporated herein and made a part hereof pursuant to 5 U.S.C. 552(a)(1). All persons affected by this directive who have not already received these documents from the manufacturer may obtain copies upon request to Service Manager, Bell Helicopter Company, P. O. Box 482, Fort Worth, Texas 76101. These documents may also be examined at the Office of the Regional Counsel, Southwest Region, Federal Aviation Administration, 4400 Blue Mound Road, Fort Worth, Texas, and at FAA headquarters, 800 Independence Avenue, S.W., Washington, D.C. A historical file on this AD which includes the incorporated material in full is maintained by the FAA at its headquarters in Washington, D.C., and at the Office ofRegional Counsel, Southwest Region, Federal Aviation Administration, 4400 Blue Mound Road, Fort Worth, Texas. This amendment becomes effective January 19, 1976.
2017-17-19: We are adopting a new airworthiness directive (AD) for all The Boeing Company Model DC-9-81 (MD- \n\n((Page 41161)) \n\n81), DC-9-82 (MD-82), DC-9-83 (MD-83), and DC-9-87 (MD-87) airplanes, and Model MD-88 airplanes. This AD was prompted by reports of cracking of various structures in the bulkhead. This AD requires an inspection for cracking in these structures, and corrective actions if necessary. We are issuing this AD to address the unsafe condition on these products.
2002-01-05: This amendment adopts a new airworthiness directive (AD) that applies to all British Aerospace Model HP.137 Jetstream Mk.1, Jetstream Series 200, Jetstream Series 3101, and Jetstream Model 3201 airplanes that are equipped with certain main landing gear (MLG) radius rods. This AD requires you to inspect the MLG radius rod cylinders for the required conductivity or hardness standard. This AD also requires you to replace any MLG radius rod cylinder that does not meet this standard. This AD is the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for the United Kingdom. The actions specified by this AD are intended to prevent failure of the MLG due to incorrectly heat treated MLG radius rod cylinders. Such failure during takeoff, landing, or taxi operations, could lead to loss of airplane control.
78-05-01: 78-05-01 SIKORSKY AIRCRAFT: Amendment 39-3146. Applies to all Model S-58T series helicopters. Compliance required prior to May 25, 1978. To preclude possible fuel starvation of the PT6T-3 and PT6T-6 engines resulting from oil-to-fuel heater contamination, relocate the impending fuel bypass sensor lines on both engine power sections in accordance with the instructions set forth in Part II, Paragraph A, of Sikorsky Service Bulletin No. 58B30-12C, dated January 12, 1976. This amendment becomes effective March 31, 1978.
2002-01-07: This amendment adopts a new airworthiness directive (AD) for Bell Helicopter Textron Canada (BHTC) Model 430 helicopters that requires changes to the electrical power distribution system. This amendment is prompted by design deficiencies in the electrical systems. The actions specified by this AD are intended to prevent failure of both generators, loss of primary electrical power, and subsequent loss of control of the helicopter.
74-12-06: 74-12-06 LOCKHEED: Amendment 39-1867 as amended by Amendment 39-2512 is further amended by Amendment 39-3361. Applies to all Model 382 series airplanes, Serial Numbers 3946 and 4101 through 4541 certificated in all categories. Compliance as indicated. a) For airplanes with 5000 or more hours total time in service on the effective date of this AD comply with paragraph (c) within the next 50 hours time in service, and thereafter at intervals not to exceed 1000 hours time in service from the last inspection. b) For airplanes with less than 5000 hours total time in service on the effective date of the AD comply with paragraph (c) before the accumulation of 5050 hours total time in service, and thereafter at intervals not to exceed 1000 hours time in service from the last inspection. c) Inspect outer wing lower forward beam cap, web, and skin for cracks in the area extending from outer wing stations 144 to 165 and 195 to 214, both left and right in accordance with Lockheed Hercules Airfreighter Inspection Procedures, SMP 515-A, Card SP-75, revised October 15, 1978, or in an equivalent manner approved by the Chief, Engineering and Manufacturing Branch, FAA, Southern Region. d) Repair of the beam cap shall be in accordance with Lockheed Service Bulletin A382-169, Revision 7, and repair of the beam web in accordance with SMP 583, Lockheed Hercules Structural Repair Manual, or in an equivalent manner approved by the Chief, Engineering and Manufacturing Branch, FAA, Southern Region. e) Before the accumulation of 30,000 flight hours, preventive modification shall be installed in accordance with Lockheed Service Bulletin 382-152, Revision 2, and Alert Service Bulletin A382-169, Revision 7, or in an equivalent manner approved by the Chief, Engineering and Manufacturing Branch, FAA, Southern Region. f) Recurring inspections shall be performed in accordance with the following: 1) Recurring inspections for unmodified airplanes will be in accordance with paragraphs (a), (b), and (c) of this amendment. 2) Recurring inspections for airplanes with preventive modifications shall be in accordance with Lockheed Airfreighter Inspection Procedures, SMP 515-A, Card SP-75, revised October 15, 1978, or in an equivalent manner approved by the Chief, Engineering and Manufacturing Branch, FAA, Southern Region, and a detailed visual inspection of the front beam lower cap and adjacent structure including modifications across the entire length of the outer wing dry bays from outer wing stations 144 to 214 at each "C" check. 3) In addition to the recurring inspections of paragraphs (f)(1) and (f)(2), recurring inspections for airplanes with repairs shall be a detailed visual inspection of the front beam lower cap and adjacent structure, including repairs, across the entire length of the outer wing dry bays from outer wing stations 144 to 214 at each "C" check. g) Upon request of the operator, an FAA Maintenance Inspector, subjectto prior approval of the Chief, Engineering and Manufacturing Branch, FAA, Southern Region, may adjust the repetitive inspection intervals specified in this amendment to permit compliance at an established inspection period of the operator if the request contains substantiating data to justify the increase for such operator. h) Airplanes may be flown to a base for performance of the inspections required by this amendment in accordance with Federal Aviation Regulations 21.197 and 21.199. i) Report inspection findings to Chief, Engineering and Manufacturing Branch, FAA, Southern Region, P.O. Box 20636, Atlanta, Georgia 30320. Lockheed-Georgia Alert Service Bulletin A382-169, dated May 30, 1974, covers this same subject. Amendment 39-1867 became effective May 30, 1974. Amendment 39-2512 became effective February 13, 1976. This amendment 39-3361 becomes effective December 8, 1978.
2023-03-03: The FAA is adopting a new airworthiness directive (AD) for all Leonardo S.p.a. Model AB139 and AW139 helicopters. This AD was prompted by a report of a damaged tail rotor duplex bearing (TRDB). This AD requires repetitively inspecting certain TRDBs and depending on the results, replacing the TRDB or tail rotor actuator (TRA), or as an option, replacing the sliding control assembly. This AD also requires replacing an affected TRDB with a serviceable TRDB at a specified threshold and prohibits the installation of certain TRDBs or sliding control assemblies on any helicopter, 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.
2017-17-13: We are adopting a new airworthiness directive (AD) for certain Bombardier, Inc., Model BD-100-1A10 airplanes. This AD was prompted by reports of low clearance in the aft equipment bay between auxiliary power unit (APU) generator power cables and a hydraulic line, which can cause damage to wire insulation. This AD requires an inspection of the APU generator power cables and the adjacent hydraulic line for damage, and repair, if necessary; and modification of the APU generator power cable installation. We are issuing this AD to address the unsafe condition on these products.
2002-01-08: This amendment adopts a new airworthiness directive (AD) that is applicable to certain Israel Aircraft Industries, Ltd., Model Galaxy airplanes. This action requires disabling the baggage compartment heating blanket system. This action is necessary to prevent a short circuit between the baggage compartment heating blankets and the electrical connectors, which could result in fire and smoke in the baggage compartment. This action is intended to address the identified unsafe condition.
2004-08-01: This amendment adopts a new airworthiness directive (AD), applicable to certain Fokker Model F.28 Mark 0070 and 0100 series airplanes, that requires a magnetic inspection of the sliding members of the main landing gear (MLG) for cracking, and replacement of the sliding members with serviceable parts, if necessary. This action is necessary to prevent fatigue cracking of the sliding member, which could result in possible separation of the MLG from the airplane and consequent reduced controllability of the airplane upon landing and possible injury to passengers. This action is intended to address the identified unsafe condition.
2017-16-12: We are superseding Airworthiness Directive (AD) 2013-19-09 and AD 2014-25-51, which applied to all Airbus Model A318, A319, A320, and A321 series airplanes. AD 2013-19-09 required replacing Angle of Attack (AOA) sensor conic plates with AOA sensor flat plates. AD 2014-25-51 required revising the airplane flight manual (AFM) to advise the flightcrew of emergency procedures for abnormal Alpha Protection (Alpha Prot). This new AD requires replacing certain AOA sensors; and doing a detailed inspection and a functional heating test for discrepancies on certain AOA sensors, and replacing the affected AOA sensors. This AD was prompted by a report indicating that a Model A321 airplane encountered a blockage of two AOA probes during climb, leading to activation of the Alpha Prot while the Mach number increased. We are issuing this AD to address the unsafe condition on these products.
2025-11-03: The FAA is adopting a new airworthiness directive (AD) for certain General Electric Company (GE) Model GEnx-1B64, GEnx-1B64/P1, GEnx-1B64/P2, GEnx-1B67, GEnx-1B67/P1, GEnx-1B67/P2, GEnx-1B70, GEnx- 1B70/75/P1, GEnx-1B70/75/P2, GEnx-1B70/P1, GEnx-1B70/P2, GEnx-1B70C/P1, GEnx-1B70C/P2, GEnx-1B74/75/P1, GEnx-1B74/75/P2, GEnx-1B76/P2, GEnx- 1B76A/P2, and GEnx-2B67/P engines. This AD was prompted by a manufacturer's investigation that revealed certain high-pressure turbine (HPT) stage 1 and HPT stage 2 disks were manufactured from powder metal material suspected to contain iron inclusion. This AD requires replacement of affected HPT stage 1 and HPT stage 2 disks with parts eligible for installation. The FAA is issuing this AD to address the unsafe condition on these products.
2002-01-01: This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 737-100, -200, -200C, -300, -400, and -500 series airplanes, that requires initial and repetitive inspections of the elevator tab assembly to find any damage or discrepancy; and corrective actions, if necessary. The actions specified by this AD are intended to prevent excessive in-flight vibrations of the elevator tab, which could lead to loss of the elevator tab and consequent loss of controllability of the airplane. This action is intended to address the identified unsafe condition.