Results
2013-09-09: We are superseding an existing airworthiness directive (AD) for all Slingsby Sailplanes Ltd. Models Dart T.51, Dart T.51/17, and Dart T.51/17R sailplanes equipped with aluminum alloy spar booms. 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 an incident of glue joint failure on a starboard wing caused by water entering the area of the airbrake box that resulted in delamination and corrosion in the area of the aluminum alloy spar booms and the wing attach fittings. We are issuing this AD to require actions to address the unsafe condition on these products.
98-23-13: This amendment supersedes an existing airworthiness directive (AD), applicable to all British Aerospace Model Viscount 700, 800, and 810 series airplanes, that currently requires repetitive inspections to detect cracks and corrosion in the inboard and outboard engine nacelle structures on the wings; replacement of any cracked fittings and mating struts; and treatment or replacement of any corroded fittings or struts. This amendment requires repetitive inspections to detect cracking or corrosion of the eye end fittings of the outboard engine lower support or of the bore of the taper pin holes, and repair, if necessary. This amendment also limits the applicability of the existing AD. This amendment is prompted by reports of cracked and separated lower eye end fittings. The actions specified by this AD are intended to detect and correct cracking of the eye end fittings of the outboard engine lower support, which could result in reduced structural integrity of the engine nacelle support structures.
98-22-16: This document publishes in the Federal Register an amendment adopting Airworthiness Directive (AD) 98-22-16 which was sent previously to all known U.S. owners and operators of RHC Model R44 helicopters by individual letters. This amendment supersedes AD 98-12-19, issued August 5, 1998, applicable to RHC Model R44 helicopters, that currently requires main rotor blade inspections and replacement if a crack is found. This amendment requires the same inspections as AD 98-12-19, but mandates replacement of all the affected main rotor blades prior to further flight after November 15, 1998. This amendment is prompted by an incident in which a crack was discovered in a main rotor blade. The actions specified by this AD are intended to prevent failure of a main rotor blade and subsequent loss of control of the helicopter.
98-23-05: This amendment supersedes an existing airworthiness directive (AD), applicable to certain Boeing Model 767 series airplanes, that currently requires an inspection to detect damage of the wire bundles in the left side of the flight compartment in the vicinity of the stowage box for the captain's oxygen mask, and repair, if necessary; a continuity check on repaired wires; installation of sleeving over the wire bundles; and rerouting of the wire bundles. This amendment requires modifications of the captain's and first officer's consoles in the flight compartment to ensure adequate clearance between oxygen equipment and adjacent wire bundles. This amendment is prompted by reports indicating that chafed wiring and wire insulation wear occurred in the vicinity of the stowage box for the captain's oxygen mask due to interference between oxygen line fittings and adjacent wire bundles. The actions specified by this AD are intended to prevent such chafing and inadequate clearance,which could result in electrical arcing and consequent oxygen leakage in the vicinity of the stowage box; these conditions, if not corrected, could result in a fire in the flight compartment.
91-15-01: 91-15-01 AEROSPATIALE: Amendment 39-7064. Docket No. 91-NM-123-AD. Applicability: Model ATR42-200 and -300 series airplanes, serial numbers 003 to 208, 213, 214, 218, 221, 225, 226, and 228; and Model ATR72-100 and -200 series airplanes, serial numbers 126 to 189, 195, 198, and 210; certificated in any category. Compliance: Required as indicated, unless previously accomplished. To prevent failure of the rudder pedal connection rod and subsequent reduced controllability of the airplane, accomplish the following: (a) Within 10 days after the effective date of this AD, perform a visual inspection of the rudder pedal connection rod (captain side) to determine the rod vendor, in accordance with Aerospatiale Service Bulletin ATR42-27-0052 (for Model ATR42 series airplanes), Revision 1, dated April 4, 1991; or Aerospatiale Service Bulletin ATR72-27-1015 (for Model ATR72 series airplanes), Revision 1, dated April 4, 1991; as applicable. (1) If the rod is manufactured by TAC, no further action is required. (2) If the rod is manufactured by SARMA, vendor P/N 14132B, prior to further flight, replace the rod with a TAC rod; or a SARMA rod, vendor P/N 14132-C; in accordance with the applicable service bulletin. (b) As of the effective date of this AD, no SARMA rudder pedal connection rod, P/N 14132B, shall be installed on any airplane. (c) An alternative method of compliance or adjustment of the compliance time, which provides an acceptable level of safety, may be used when approved by the Manager, Standardization Branch, ANM-113, FAA, Transport Airplane Directorate. NOTE: The request should be forwarded through an FAA Principal Maintenance Inspector, who may concur or comment and then send it to the Manager, Standardization Branch, ANM-113. (d) Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes to a base in order to comply with the requirements of this AD. (e) The inspection and replacement requirements shall be done in accordance with Aerospatiale Service Bulletin ATR42-27-0052 (for Model ATR42 series airplanes), Revision 1, dated April 4, 1991; or Aerospatiale Service Bulletin ATR72-27-1015 (for Model ATR72 series airplanes), Revision 1, dated April 4, 1991; which include the following list of affected pages: Service Bulletin Page Number Revision Level Date 1, 3, 4, 7 1 April 4, 1991 ATR42-27-0052 2, 5-6, 8 through 17 (Original) March 7, 1991 1, 2, 5 1 April 4, 1991 ATR72-27-1015 3, 4, 6 through 15 (Original) March 7, 1991 This incorporation by reference was approved by the Director of the Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR Part 51. Copies may be obtained from Aerospatiale, 316 Route de Bayonne, 31060 Toulouse, Cedex 03, France. Copies may be inspected at the FAA, Transport Airplane Directorate, Renton, Washington; or at the Office of the Federal Register, 1100 L Street N.W., Room 8401, Washington, D.C. This amendment (39-7064, AD 91-15-01) becomes effective on July 17, 1991.
2013-09-01: We are superseding an existing airworthiness directive (AD) for certain The Boeing Company Model 737-200, -200C, -300, -400, and - 500 series airplanes. That AD currently requires a one-time mid- frequency eddy current (MFEC) inspection, a low-frequency eddy current (LFEC) inspection, and a detailed inspection for damage or cracking of stringer S-4L and S-4R lap joints and stringer clips between body station (BS) 540 and BS 727, and follow-on inspections and repair if necessary. This new AD instead requires repetitive external eddy current inspections for cracking of certain fuselage crown lap joints, and corrective actions if necessary; internal eddy current and detailed inspections for cracking of certain fuselage crown lap joints, and repair if necessary; and detailed inspections of certain stringer clips, and replacement with new stringer clips if necessary. This AD also adds airplanes to the applicability. This AD was prompted by reports of cracking of the lap joint lowerrow. We are issuing this AD to detect and correct cracking of the fuselage lap joints, which could result in sudden decompression of the airplane.
2022-09-06: The FAA is superseding Airworthiness Directive (AD) 2021-13- 06, which applied to certain Airbus SAS Model A350-941 and -1041 airplanes. AD 2021-13-06 required revising the existing maintenance or inspection program, as applicable, to incorporate new or more restrictive airworthiness limitations. Since the FAA issued AD 2021-13- 06, the FAA has determined that new or more restrictive airworthiness limitations are necessary. This AD continues to require the actions in AD 2021-13-06 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, which is incorporated by reference. The FAA is issuing this AD to address the unsafe condition on these products.
98-23-03: This amendment adopts a new airworthiness directive (AD), applicable to Eurocopter France Model SA 330F, G, and J helicopters, that requires removing and replacing each tail rotor electrical bonding braid (bonding braid). This amendment is prompted by an in-service report of the failure of a bonding braid. The actions specified by this AD are intended to prevent failure of a bonding braid due to fatigue, resulting impact with the tail rotor blades, and subsequent loss of control of the helicopter.
93-08-16: 93-08-16 PRATT & WHITNEY: Amendment 39-8564. Docket 92-ANE-06. Supersedes AD 90-20-11, Amendment 39-6682. Applicability: Pratt & Whitney PW4050, PW4052, PW4056, PW4060, and PW4060A model turbofan engines equipped with electronic engine control (EEC) Part Numbers 50D437, 50D821, 50D823, 51D011, and 51D012, installed on but not limited to Boeing 747 and 767 aircraft. Compliance: Required within 30 calendar days after the effective date of this airworthiness directive (AD), unless accomplished previously. To prevent a high pressure compressor (HPC) failure caused by excessive blade tip to airseal interference, which can result in total loss of engine thrust, accomplish the following: (a) Incorporate the requirements of Boeing Commercial Airplanes Alert Service Bulletin (ASB) 747-73A2055, dated June 8, 1990, on PW4000 powered Boeing 747-400 aircraft, so that the minimum inflight rotational speed (rpm) of the low pressure rotor is limited to Approach Idle rpm. (b) Incorporate the requirements of Boeing Commercial Airplanes ASB 767-73A0033, dated June 5, 1990, on PW4000 powered Boeing 767-200/-300 aircraft, so that the minimum inflight rotational speed of the low pressure rotor inflight is limited to Approach Idle rpm. (c) 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. The request should be forwarded through an appropriate 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. (d) 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. (e) The modification shall be done in accordance with the following Boeing service documents: Document No. Pages Revision Date ASB 747-73A2055 1-10 Original June 8, 1990 Total pages: 10 ASB 767-73A0033 1-12 Original June 5, 1990 Total pages: 12 This incorporation by reference was approved previously by the Director of the Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR part 51 as of October 1, 1990 (55 FR 37316, September 11, 1990). Copies may be obtained from Boeing Commercial Airplanes, Post Office Box 3707, Seattle, WA 98124-2207. Copies may be inspected at the FAA, New England Region, Office of the Assistant Chief Counsel, 12 New England Executive Park, Burlington, MA; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC. (f) This amendment becomes effective on July 12, 1993.
2013-09-02: We are superseding two existing airworthiness directives (AD) that apply to certain The Boeing Company Model 737-100, -200, -200C, - 300, -400, and -500 series airplanes. Those ADs, for certain airplanes, currently require repetitive inspections of the flap track of the wing outboard flap, and corrective actions if necessary; and eventual rework of the flap track assembly and rear spar attachments. For certain airplanes, this new AD adds repetitive inspections, scheduled overhauls, correct alignment during installation, and repetitive maintenance of the flap track, and corrective actions if necessary. This new AD also adds airplanes to the applicability. This AD was prompted by reports that the work sequence and procedures used during installation of replacement tracks could cause loose or cracked tracks. We are issuing this AD to detect and correct cracking and damage in the flap track, which could cause loss of the outboard trailing edge flap and consequent reduced controllability of the airplane.