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2000-14-08: This document adopts a new airworthiness directive (AD) that applies to all The New Piper Aircraft, Inc. (Piper) PA-42 series airplanes that are equipped with pneumatic deicing boots. This AD requires you to revise the Airplane Flight Manual (AFM) to include requirements for activation of the airframe pneumatic deicing boots. This AD is the result of reports of in-flight incidents and an accident (on airplanes other than the affected Piper airplanes) that occurred in icing conditions where the airframe pneumatic deicing boots were not activated. The Piper PA-42 series airplanes have a similar type design (as it relates to airframe pneumatic deice boots) to the incident and accident airplanes. The actions specified by this AD are intended to assure that flight crews activate the pneumatic wing and tail deicing boots at the first signs of ice accumulation. This action will prevent reduced controllability of the aircraft due to adverse aerodynamic effects of ice adhering tothe airplane prior to the first deicing cycle.
67-12-04: 67-12-04 FAIRCHILD-HILLER: Amdt. 39-391 Part 39 Federal Register April 8, 1967. Applies to Models F-27 Series and FH-227 Series Airplanes. Compliance required as indicated. To detect cracks in the rudder horn assembly, accomplish the following: (a) Within the next 50 hours' time in service after the effective date of this AD, unless already accomplished within the last 450 hours' time in service, and thereafter at intervals not to exceed 500 hours' time in service from the last inspection, comply with (b). (b) Visually inspect the rudder horn assembly, P/N 27-243018-11, for cracks, using a glass of at least 10-power, or use an equivalent inspection approved by an FAA maintenance inspector. If a crack is found comply with (c) before further flight. (c) Replace a cracked part with a part of the same part number that has been inspected in accordance with (b), or use an equivalent part approved by the Chief, Engineering and Manufacturing Branch, FAA Eastern Region. (d) The repetitive inspection required by (a) may be discontinued when a modification, approved by the Chief, Engineering and Manufacturing Branch, FAA Eastern Region is incorporated. (e) Upon request of the operator, an FAA maintenance inspector, subject to prior approval of the Chief, Engineering and Manufacturing Branch, FAA Eastern Region, may adjust the initial compliance time and the repetitive inspection interval specified in this AD if the request contains substantiating data to justify the increase for that operator. This directive effective April 8, 1967.
2000-14-06: This amendment supersedes an existing airworthiness directive (AD), applicable to certain Boeing Model 747 series airplanes, that currently requires a one-time inspection to determine the part number of the fuel shutoff spar valve for the outboard engines. That AD also requires replacement of certain valves with new valves, or modification of the spar valve body assembly, and various follow-on actions. This amendment adds new requirements to accomplish those actions on additional airplanes; and requires a one- time inspection of the maintenance records of certain airplanes to determine if the fuel shutoff spar valve for the outboard engines has ever been replaced, and various follow-on actions. This amendment is prompted by reports indicating that, due to high fuel pressure, certain fuel system components of the outboard engines have failed. The actions specified by this AD are intended to prevent such high fuel pressure, which could result in failure of the fuel systemcomponents; this situation could result in fuel leakage, and, consequently, lead to an engine fire.
2013-16-19: We are adopting a new airworthiness directive (AD) for Eurocopter France (Eurocopter) Model EC120B and EC130B4 helicopters with a certain emergency flotation gear (float) installed. This AD requires inspecting the float for chafing of the fabric covering and adding protectors to the float installation to prevent contact between the float and the protruding [[Page 52408]] sections of the installation. This AD was prompted by a report of a float that would not inflate during overhaul because one of the float compartments was punctured due to chafing. The actions of this AD are intended to prevent failure of float and subsequent loss of control of the helicopter during an emergency water landing.
2013-16-18: We are adopting a new airworthiness directive (AD) for certain Airbus Model A320-214, -232 and -233 airplanes; and Model A321-211, - 213, and -231 airplanes. This AD was prompted by a report of a missing fastener between certain stringers of the fuselage frame that connects the frame to a tee. This AD requires an inspection for a missing fastener, and a rototest inspection and a modification or repair of the fuselage frame at the affected area if necessary. We are issuing this AD to detect and correct cracking in the fuselage that could result in reduced structural integrity of the airplane.
69-16-05: 69-16-05 ALLISON: Amdt. 39-829. Applies to Model 250-C18 engines installed in Bell Model 206A Helicopters. Compliance: Required as indicated. To detect incipient engine failure, accomplish the following: A) Effective immediately upon receipt of this Airworthiness Directive, inspect the lower gear box and the oil outlet magnetic plugs on a daily basis as described in Allison Commercial Service Letter 250 CSL No. 6, dated January 12, 1967. This inspection shall be performed at time intervals not to exceed five (5) hours' time in service. B) On or before November 3, 1969, install a visual magnetic plug indicator as described in Bell Service Letter 206A-129, dated August 11, 1969, or later FAA approved revision or an equivalent installation approved by Chief, Engineering & Manufacturing Branch, FAA, Central Region. C) When the installation described in Paragraph B of this Airworthiness Directive has been accomplished, the inspections required by Paragraph A of this Airworthiness Directive will no longer be required. Effective August 13, 1969, revised August 30, 1969.
2000-13-07: This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A330 and A340 series airplanes. This AD requires repetitive detailed visual and ultrasonic inspections of the main landing gear (MLG) to detect fatigue cracks, and repair if necessary; replacement of certain nose landing gear (NLG) handwheel controllers and certain placards with new placards; installation of steering angle recording software; and corrective action for exceeding certain steering angles. This AD also requires an AFM revision to limit the nose wheel steering angle for pushback and towing and to limit the nose wheel steering for powered turns. 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 MLG failure due to fatigue cracking, which could result in reduced structural capability of the airplane and collapse of the MLG.
75-03-01: 75-03-01 BOEING: Amendment 39-2074 as amended by Amendment 39-2421 and 39-3502 is further amended by Amendment 39-3737. Applies to all Boeing Model 707-300, -300B, - 300C, and -400 series airplanes listed in Boeing Service Bulletin No. 3157, Revision 4, or later FAA approved revisions upon the accumulation of the following number of landings since new: \n\nModels\n707-300, -400\t13,000 or more landings \n707-300B\t8,000 or more landings\n707-300C\t8,000 or more landings \n\n\tCompliance required as indicated. \n\tTo detect cracks in the upper wing skin splice plate at W.S. 360, accomplish the following: \n\tA.\tWithin the next 50 landings, unless accomplished within the last 350 landings, and at intervals thereafter not to exceed 400 landings, inspect the upper wing splice plate at station 360 in accordance with (1), (2), or (3) below. Special attention should be focused in the area of stringer 11 as it is in the high stressed area of the splice plate. If cracks are found, repair priorto further flight in accordance with paragraph B below. \n\t\t(1)\tX-Ray inspect per Boeing Service Bulletin No. 3157, Revision 3 and visually inspect the splice plate by removing the aerodynamic sealant between the wing skins from front to rear spar. This inspection method is acceptable for only two successive inspections after the effective date of this amendment. \n\t\t(2)\tLow frequency eddy current inspect as specified in Boeing Service Bulletin No. 3157, Revision 7, or inspections approved by the Chief, Engineering and Manufacturing Branch, FAA Northwest Region. \n\t\t(3)\tInspect in a manner approved by the Chief, Engineering and Manufacturing Branch, FAA Northwest Region. \n\tB.\tIf cracks are found, repair prior to further flight in accordance with Boeing Service Bulletin No. 2510, Revision 3, or later FAA approved revisions, or in a manner approved by the Chief, Engineering and Manufacturing Branch, FAA Northwest Region. The repetitive inspections of paragraph A. must be accomplishedin areas not covered by repairs per Part VII of Boeing Service Bulletin No. 2510, Revision 3, or later FAA approved revisions. \n\tC.\tThe inspections required by this AD may be terminated when the following is accomplished: \n\t\t(1)\tSplice plate, skin and rib cap fastener holes are oversized to remove fatigue material per Part IV of Boeing Service Bulletin No. 2510, Revision 3, or later FAA approved revisions, and complete external doublers are installed in accordance with Part VIII of Boeing Service Bulletin No. 2510, Revision 3, or later FAA approved revisions, or \n\t\t(2)\tOther modifications are made in a manner approved by the Chief, Engineering and Manufacturing Branch, FAA Northwest Region. \n\tD.\tFor the purpose of complying with this AD, subject to acceptance by the assigned FAA maintenance inspector, the number of landings may be determined by dividing each airplane's hours' time in service by the operator's fleet average time from takeoff to landing for the airplane type. \n\tE.\tUpon request of the operator, an FAA maintenance inspector, subject to prior approval of the Chief, Engineering and Manufacturing Branch, FAA Northwest 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 change for that operator. \n\tThe 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). \n\tAll persons affected by this directive who have not already received these documents from the manufacturer may obtain copies upon request to Boeing Commercial Airplane Company, P.O. Box 3707, Seattle, Washington 98124. The documents may be examined at FAA Northwest Region, 9010 East Marginal Way South, Seattle, Washington. \n\tThis supersedes Amendment 39-1829 (39 F.R. 15027), AD 74-09-07, as amended by Amendment 39-2002. \n\tAmendment39-2074 became effective January 27, 1975. \n\tAmendment 39-3421 became effective December 4, 1975. \n\tAmendment 39-3502 became effective July 3, 1979. \n\tThis Amendment 39-3737 becomes effective April 17, 1980.
2013-15-21: We are superseding airworthiness directive (AD) 2004-13-06 for certain Airbus Model A319 and A320 series airplanes. AD 2004-13-06 required repetitive detailed inspections to detect cracks in the keel beam side panels, and repair if necessary. This new AD requires repetitive eddy current inspections for cracking in the keel beam side panels, and corrective actions if necessary. This AD was prompted by reports of cracks on the side panels of the keel beams. We are issuing this AD to detect and correct fatigue cracks on the side panels of the keel beams, which could result in reduced structural integrity of the airplane.
75-09-01: 75-09-01 LOCKHEED-CALIFORNIA COMPANY: Amendment 39-2172. Applies to L-1011-385-1-193L airplanes, Serial Nos. 1064, 1079, 1114, 1120, and 1125, certificated in all categories. After receipt of this AD, occupancy of the under floor lounge is prohibited until the conformity of the under floor lower lounge floor boards and the related applicable components is verified to establish adherence to the configuration defined by FAA Sealed Drawing List L-1011- 385-1, No. 385-1, supplement entitled, "FAA List for Model L Peculiars" and "Model L Peculiars Drawing List Addendum", dated May 10, 1974, or FAA-approved equivalent configuration. The conformity inspection shall be accomplished by the Chief, Aircraft Engineering Division, FAA Western Region, or his authorized representative. This amendment becomes effective April 21, 1975, for all persons except those to whom it was made effective by telegram, dated March 18, 1975.