Results
2017-23-08: We are superseding Airworthiness Directive (AD) 2014-24-02 for Agusta S.p.A. (Agusta) Model AB139 and AW139 helicopters. AD 2014-24-02 required repetitively inspecting the main rotor (M/R) rotating scissors, removing certain lower half scissor spherical bearings (bearings) from service, and installing a special nut. This new AD revises the inspection requirements and requires replacing the bearings. This AD is prompted by a new report of a dislodged bearing of an M/R rotating scissor. The actions of this AD are intended to correct an unsafe condition on these products.
2002-03-01: This amendment adopts a new airworthiness directive (AD), that is applicable to Honeywell International, Inc., (formerly AlliedSignal, Inc., and Textron Lycoming) T5311A, T5311B, T5313B, T5317A, T5317B, and former military T53-L-11, T53-L-11A, T53-L-11B, T53-L-11C, T53-L-11D, T53-L-11A S/SA, T53-L-13B, T53-L-13B S/SA, T53-L-13B S/SB, and T53-L-703 series turboshaft engines. This amendment requires initial and repetitive special vibration tests of the engine, and if necessary replacement with a serviceable reduction gearbox assembly, or a serviceable engine before further flight. This amendment is prompted by reports of tachometer drive spur gear failure, resulting in potential engine overspeed, loss of power turbine speed (N2) instrument panel indication, and hard landings. The actions specified in this AD are intended to prevent excessive vibrations produced by the reduction gearbox assembly that could cause failure of the tachometer drive spur gear.
2017-23-04: We are adopting a new airworthiness directive (AD) for certain Airbus Model A300 B4-600R series airplanes; Model A300 B4-603, B4-620, and B4-622 airplanes; Model A300 C4-605R Variant F airplanes; and Model A300 F4-605R airplanes. This AD was prompted by a determination that the top stringer joints at rib 18 are an area of uniform stress distribution, which indicates that cracks may develop in adjacent stringers at the same time. This AD requires an inspection of the upper wing skin and top stringer joints, and modification of the stringer joint couplings if necessary. We are issuing this AD to address the unsafe condition on these products.
2017-23-05: We are adopting a new airworthiness directive (AD) for all The Boeing Company Model 737-100, -200, -200C, -300, -400, and -500 series airplanes. This AD was prompted by reports of crack indications in the right wing upper aft skin, originating from fastener holes common to the rear spar upper chord. This AD requires repetitive inspections for cracking of the wing upper aft skin, and applicable on-condition actions. We are issuing this AD to address the unsafe condition on these products.
2005-17-01: The FAA adopts a new airworthiness directive (AD) for all Pilatus Aircraft Ltd. (Pilatus) (also identified as Fairchild Republic Company and Fairchild Heli Porter) Model PC-6 airplanes. This AD requires you to repetitively inspect the stabilizer-trim attachment and structural components for cracks, corrosion, and discrepancies and replace any defective part with a new part. This AD also requires you to replace all Fairchild connecting pieces, part number (P/N) 6232.0026.XX, with a Pilatus connecting piece and requires you to replace fittings without an index after the P/N with an improved part. This AD results from mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for Switzerland. We are issuing this AD to detect and correct defective stabilizer-trim attachments and surrounding structural components, which could result in failure of the stabilizer-trim attachment. This failure could lead to loss of control of the airplane.
84-20-02: 84-20-02 CESSNA: Amendment 39-4922. Applies to Models 402C (S/Ns 402C0001 thru 402C0802); 404 (S/Ns 404-0001 thru 404-0859); 414A (S/Ns 414A0001 thru 414A1003); 421C (S/Ns 421C0001 thru 421C1402); 425 (S/Ns 425-0002 thru 425-0190); 441 (S/Ns 441-0001 thru 441-0333) airplanes certificated in any category. Compliance: Required within the next 200 hours time-in-service after the effective date of this AD, unless already accomplished. To preclude collapse of the nose landing gear: (a) Replace the nose landing gear actuator rod ends on Models 425 and 441 airplanes in accordance with Cessna Service Information Letter (CSIL) PJ84-10 dated March 2, 1984, and on Models 402C, 404, 414A and 421C airplanes in accordance with CSIL ME84-10 dated March 9, 1984. (b) The aircraft may be flown in accordance with Federal Aviation Regulation 21.197 to a location where this AD can be accomplished. (c) An equivalent means of compliance with this AD may be used if approved by the Manager, Aircraft Certification Office, Federal Aviation Administration, Room 100, 1801 Airport Road, Mid-Continent Airport, Wichita, Kansas 67209; telephone (316) 946-4400. This amendment becomes effective on November 1, 1984.
82-06-12: 82-06-12 AIR TRACTOR: Amendment 39-4350. Applies to Models AT-300 (S/Ns 300-0001 through 300-9999); AT-301 (S/Ns 301-0001 through 301-9999); AT-302 (S/Ns 302-0001 through 302-9999); AT-400 (S/Ns 400-0244 through 400-9999); and AT-400A (S/Ns 400A-0397 through 400A-9999) airplanes certified in any category and equipped with 1-inch-thick (P/N 40007-2 or P/N 40058-1) main landing gear struts. COMPLIANCE: Required as indicated, unless already accomplished. To prevent possible failure of the P/N 40007-2 or P/N 40058-1 main landing gear struts accomplish the following: (a) Models AT-300 and AT-301 airplanes: (1) On struts having exceeded, or upon accumulating, 1,000 hours time-in- service or 5,000 landings, whichever occurs first, within 20 hours time-in-service or 100 landings, whichever occurs first, after the effective date of this AD and thereafter at intervals of 100 hours time-in-service or 500 landings, whichever occurs first, inspect and replace as necessary the landing gear struts in accordance with paragraph (c). (2) On struts having exceeded, or upon accumulating, 2,000 hours time-in- service or 7,500 landings, whichever occurs first, prior to further flight, replace the struts with new struts of the same part number. (b) Models AT-302, AT-400 and AT-400A airplanes: (1) On struts having exceeded, or upon accumulating, 600 hours time-in- service or 3,000 landings, whichever occurs first, within 20 hours time-in-service or 100 landings, whichever occurs first, after the effective date of this AD and thereafter at intervals of 100 hours time-in-service or 500 landings, whichever occurs first, inspect the struts and replace as necessary in accordance with paragraph (c). (2) On struts having exceeded, or upon accumulating, 1,200 hours time-in- service, or 6,000 landings, whichever occurs first, prior to further flight, replace the struts with new struts of the same part number. (c) Remove the left and right outboard fuselage clamp blocks. Remove all minor corrosion on both main landing gears by sandblasting. Inspect both main landing gears using dye penetrant or magnetic particle inspection procedures with special attention in the areas of strut contact with the clamp blocks. Replace all parts which are damaged, cracked, or have severe corrosion pitting with new parts of the same part number before further flight. All struts returned to service must be painted. (d) The aircraft hours and landings may be used as the time-in-service or landings on the struts if time-in-service or landings on the struts cannot be established by the airplane maintenance records. (e) A special flight permit may be issued in accordance with FAR 21.197 to allow flight of the aircraft to a location where this AD can be accomplished. (f) An equivalent method of compliance with this AD may be used when approved by the Chief, Aircraft Certification Division, Federal Aviation Administration, 4400 Blue Mound Road, Fort Worth, Texas 76101. Snow Engineering Company Service Letter No. 45, dated November 1, 1981, covers the subject matter of this AD. Compliance with this Service Letter within the last 100 hours time-in-service or 500 landings, whichever comes first, satisfies the initial inspection requirement of paragraphs (a) and (b) of this AD. This amendment becomes effective on March 25, 1982.
92-08-51: 92-08-51 TEXTRON LYCOMING: Amendment 39-8344. Docket 92-ANE-13. Applicability: Textron Lycoming Model ALF502R series turbofan engines installed on British Aerospace BAe-146 airplanes. Compliance: Required as indicated, unless accomplished previously. To prevent uncommanded in-flight engine power reduction of engines during inclement weather or icing conditions, accomplish the following: (a) Replace the existing engine fuel control, Part Number (P/N) 2-163-810-07, 2-163-810-12, or 2-163- 810-15 with an improved fuel control, P/N 2-163-810-20, 2-163-810-21, or 2-163-810-23, or rework the existing engine fuel control, in accordance with Textron Lycoming Alert Service Bulletin (ASB) No. A-ALF 502R 73-12, Revision 1, dated April 7, 1992, at the first maintenance access of the engine fuel control or within 300 operating cycles after the effective date of this AD, whichever occurs first. (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, Engine Certification Office, FAA, Engine and Propeller Directorate. The request should be forwarded through an FAA Principal Maintenance Inspector, who may add comments and then send it to the Manager, Engine Certification Office. NOTE: Information concerning the existence of approved alternative methods of compliance with this airworthiness directive, if any, may be obtained from the Engine Certification Office. (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 replacement or rework of the engine fuel control shall be done in accordance with the following Textron Lycoming Alert Service Bulletin (ASB): Document No. Pages Version Date Textron Lycoming 1,2,4,5 Rev. 1 April 7, 1992 ASB A-ALF-502R 73-12 3,6,7,8 Original April 1, 1992 Total pages: 8This 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 Textron Lycoming, Stratford Division, 550 Main Street, Stratford, Connecticut 06497. Copies may be inspected at the FAA, Office of the Assistant Chief Counsel, 12 New England Executive Park, Burlington, Massachusetts; or at the Office of the Federal Register, 800 North Capitol Street, NW., Suite 700, Washington, DC 20001. (e) This amendment becomes effective on March 18, 1993, to all persons except those persons to whom it was made immediately effective by telegraphic AD T92-08-51, issued April 8, 1992, which contained the requirements of this amendment.
2023-04-05: The FAA is superseding Airworthiness Directive (AD) 2022-09- 11, which applied to certain Airbus SAS Model A350-941 and -1041 airplanes. AD 2022-09-11 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- 11 and requires 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.
2023-04-02: The FAA is adopting a new airworthiness directive (AD) for all Gulfstream Aerospace LP Model Gulfstream G280 airplanes. This AD was prompted by a determination that the existing wet runway performance tables in the airplane flight manual (AFM) may not provide an acceptable level of safety. This AD requires revising the existing AFM to incorporate new wet runway performance tables, as specified in a Civil Aviation Authority of Israel (CAAI) AD, which is incorporated by reference. The FAA is issuing this AD to address the unsafe condition on these products.