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2011-06-02: We are adopting a new airworthiness directive (AD) for the products listed above. This AD requires installing a full authority digital engine control (FADEC) backup battery, replacing the supplement pilot's operating handbook and FAA approved airplane flight manual, and replacing the FADEC backup battery every 12 calendar months. This AD was prompted by an incident where an airplane experienced an in-flight engine shutdown caused by a momentary loss of electrical power to the FADEC. We are issuing this AD to prevent interruption of electrical power to the FADEC, which could result in an uncommanded engine shutdown. This failure could lead to a loss of engine power.
2011-09-11: We are adopting a new airworthiness directive (AD) for the products listed above. This AD requires repetitive inspections for hydraulic fluid contamination of the interior of the strut disconnect assembly; repetitive inspections for discrepancies of the interior of the strut disconnect assembly, if necessary; repetitive inspections of the exterior of the strut disconnect assembly for cracks, if necessary; and corrective action if necessary. This AD also provides an optional terminating action for the inspections. This AD was prompted by reports of system disconnect boxes that have been contaminated with hydraulic fluid and, in one incident, led to subsequent cracking of titanium parts in the system disconnect assembly. We are issuing this AD to detect and correct hydraulic fluid contamination, which can cause cracking of titanium parts in the system disconnect assembly, resulting in compromise of the engine firewall. A cracked firewall can allow fire in the engine area to enter the strut and can lead to an uncontained engine strut fire if flammable fluid is present. Cracking of the disconnect box may also reduce the effectiveness of the fire extinguishing system in the engine compartment and could contribute to an uncontained engine fire. In addition, a cracked disconnect box can leak flammable fluids into the engine core, which can initiate an engine fire, and lead to one or both fire conditions discussed above.
96-14-01: This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 747-200 "combi" and 747-300 "combi" airplanes. This action requires the installation of a new hose and fitting for the oxygen supply system. This amendment is prompted by a report indicating that a gasket seal in the oxygen hose assembly was omitted during installation. The actions specified in this AD are intended to prevent leakage of oxygen from the passenger oxygen supply lines, which could prevent an adequate flow of oxygen from reaching passengers in the event of a deployment of the passenger oxygen masks.
2011-09-10: 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: Airbus, in the frame of the Extended Service Goal (ESG) exercise, has demonstrated by post-certification analysis that, among the types of yokes in service, one component on the CF6-80C2 forward engine mounts (skinny cast yoke) does not meet the Design Service Goal (DSG) requirements. This condition, if not corrected, could result in a deterioration of the structural integrity of the forward engine mount. * * * * * The unsafe condition is possible separation of the engine from the engine mount during flight. We are issuing this AD to require actions to correct the unsafe condition on these products.
59-23-01: 59-23-01 PIAGGIO: Applies to All Models P.136-L1 and P.136-L2 Aircraft. Compliance required by December 31, 1959. In order to preclude the water rudder cables from fouling the bolt end and nuts that secure the microswitch to the water rudder retraction cylinder, a cable guard plate must be installed. The Registro Aeronautico Italiano considers compliance mandatory. (Piaggio & Co. Change Order No. 36 L-48 covers the same subject.)
96-14-02: This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 767 series airplanes, that requires a visual inspection to verify proper clearance between the number 18 fuel nozzle secondary transfer fuel tube and the pylon drain tube of the engine, and various follow-on actions. This amendment also requires the installation of clamps and associated fasteners between the environmental control system (ECS) controller tube and the pylon drain tube. This amendment is prompted by reports of chafing of the number 18 fuel nozzle secondary transfer fuel tube of the engine due to an improperly installed or loose pylon drain tube. The actions specified by this AD are intended to prevent such chafing, which could lead to subsequent fuel leakage and a possible engine fire.
90-08-10: 90-08-10 FAIRCHILD INDUSTRIES, INC.: Amendment 39-6573. Docket No. 89-NM-265-AD. Applicability: All Model F-27 and FH-227 series airplanes, certificated in any category. Compliance: Required as indicated, unless previously accomplished. To prevent reduced structural capability of the wing due to undetected fatigue cracks, accomplish the following: A. Within 25 hours time-in-service after August 21, 1989 (the effective date of AD 89-15-01, Amendment 39-6292), perform a dye penetrant inspection for cracks in the wing outer panel upper surface stringer splice fitting, in accordance with Fairchild Industries Service Bulletin F27-51-8, dated April 22, 1974, [reference paragraph 2A(6)(e), page 5; and Figure 14, page 24] or Fairchild Industries Service Bulletin FH227-51-4, dated January 17, 1979 [reference paragraph 2A(6)(e), page 5; and Figure 14, page 23], as appropriate, and Maryland Air Industries Alert Service Letters F27-681 and FH227-57-6, both dated June 29, 1989, as appropriate. B. If cracks are found in the wing outer panel upper surface stringer splice fittings, prior to further flight, accomplish the following: 1. If cracks found are less than or equal to .100 inch on the Model F-27 series airplanes, or less than or equal to .075 inch on the Model FH-227 series airplanes, perform the blending operation in accordance with Maryland Air Industries Drawing No. D27-7723, dated July 27, 1989. Perform a dye penetrant inspection after the blending operation to ensure that all damaged material has been removed. Pay particular attention to the maximum torque value and gaps as shown on Maryland Industries Drawing D27-7723, dated July 27, 1989. 2. If cracks found are more than .100 inch on the Model F-27 series airplanes, or more than .075 inch on the Model FH-227 series airplanes, replace aluminum fittings with new steel fittings, in accordance with Maryland Air Industrie Drawing No. 27-133008, dated July 28, 1989. NOTE: For thoseairplanes that have removed and replaced the wing outer panel upper surface stringer splice fittings, with serviceable parts, in accordance with AD 89-15-01, Amendment 39-6292, accomplish the requirements of paragraph C., below. Included in this group of airplanes are those that were granted an alternate means of compliance to the requirement of replacement with serviceable parts. C. Within one year time-in-service after the effective date of this AD, replace all aluminum fittings part number (P/N) 27-133008-21 with a new steel fitting, P/N 27-133008-23, in accordance with Maryland Air Industries Drawing No. 27-133008, dated July 28, 1989. D. 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, New York Aircraft Certification Office, ANE-170, FAA, New England Region. NOTE: The request should be forwarded through an FAA Principal Maintenance Inspector (PMI), who willeither concur or comment and then send it to the Manager, New York Aircraft Certification Office, ANE-170, FAA, New England Region. E. 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. All persons affected by this directive who have not already received the appropriate service documents from the manufacturer may obtain copies upon request to Maryland Air Industries, Inc., Hagerstown, Maryland 21740. These documents may be examined at the FAA, Northwest Mountain Region, Transport Airplane Directorate, 17900 Pacific Highway South, Seattle, Washington, or at the New York Aircraft Certification Office, FAA, New England Region, 181 South Franklin Avenue, Valley Stream, New York. Airworthiness Directive 90-08-10 supersedes AD 89-15-01, Amendment 39-6292. This amendment (39-6573, AD 90-08-10) becomes effective on May 14, 1990.
91-15-03: 91-15-03 GENERAL ELECTRIC COMPANY: Amendment 39-7066. Docket No. 91-ANE- 25. Applicability: General Electric Company (GE) CF6-6 series turbofan engines installed on, but not limited to, McDonnell Douglas DC10-10 aircraft. Compliance: Required as indicated, unless previously accomplished. To prevent an uncontained engine failure and damage to the aircraft, accomplish the following: (a) Remove from service stage 1 fan disks identified by serial number (S/N) in Group A, Figure 3 of GE CF6-6 Service Bulletin (SB) 72-962, Revision 3, dated May 22, 1991, within the next 10 cycles in service (CIS) after the effective date of this AD and replace with a serviceable part. (b) Eddy current inspect in accordance with GE CF6-6 SB 72-962, Revision 3, dated May 22, 1991, the bore forward corner of stage 1 fan disks identified by S/N in Group B, Figure 3 of GE CF6-6 SB 72-962, Revision 3, dated May 22, 1991, as follows: (1) For disks which on the effective date of this AD have not received an eddy current inspection in accordance with the Accomplishment Instructions of GE CF6-6 SB 72-962, Revision 3, dated May 22, 1991, inspect in accordance with the following schedule: (i) Within the next 100 CIS after the effective date of this AD, for disks which on the effective date of this AD have accumulated 1,250 CIS or greater since accomplishing the immersion ultrasonic inspection in accordance with the Accomplishment Instructions, paragraph 2.B. of GE CF6-6 SB 72-962, Revision 3, dated May 22, 1991. (ii) Within the next 100 CIS after the effective date of this AD or prior to accumulating 1,250 CIS since the immersion ultrasonic inspection, whichever comes later, for disks which on the effective date of this AD have accumulated less than 1,250 CIS since accomplishing the immersion ultrasonic inspection in accordance with the Accomplishment Instructions, paragraph 2.B. of GE SB 72-962, Revision 3, dated May 22, 1991. (2) For disks which on the effective date of this AD, have received an eddy current inspection in accordance with the Accomplishment Instructions of GE CF6-6 SB 72-962, Revision 3, dated May 22, 1991, inspect in accordance with the following schedule: (i) Within the next 100 CIS after the effective date of this AD for those disks which on the effective date of this AD have accumulated 1,500 CIS or greater since accomplishing the immersion ultrasonic inspection in accordance with the Accomplishment Instructions, paragraph 2.B. of GE CF6-6 SB 72-962, Revision 3, dated May 22, 1991. (ii) Within the next 100 CIS after the effective date of this AD or prior to accumulating 1,500 CIS since accomplishing the immersion ultrasonic inspection, in accordance with the Accomplishment Instructions, paragraph 2.B of GE CF6-6 SB 72-962, Revision 3, dated May 22, 1991, whichever occurs later, for those disks which on the effective date of this AD have accumulated less than 1,500 CIS since accomplishing the immersion ultrasonic inspection in accordance with the Accomplishment Instructions, paragraph 2.B. of GE CF6-6 SB 72-962, Revision 3, dated May 22, 1991. (c) Thereafter, eddy current inspect the bore forward corner of stage 1 fan disks which meet the acceptance criteria of paragraph 2.A.(2)(c) of the Accomplishment Instructions of GE CF6-6 SB 72-962, Revision 3, dated May 22, 1991, at intervals not to exceed 500 CIS since last eddy current inspection. (d) Remove from service prior to further flight and replace with a serviceable part, disks inspected in accordance with paragraphs (b) and (c) of this AD, which do not meet the acceptance criteria of paragraph 2.A.(2)(c) of the Accomplishment Instructions of GE CF6-6 SB 72-962, Revision 3, dated May 22, 1991. (e) Remove from service and replace with a serviceable part all Group B stage 1 fan disks at the next shop visit but no later than 2,500 CIS since immersion ultrasonic inspection in accordance with the AccomplishmentInstructions, paragraph 2.B. of GE CF6-6 SB 72-962, Revision 3, dated May 22, 1991, or June 30, 1992, whichever occurs first. (f) Immersion ultrasonic inspect in accordance with the Accomplishment Instructions, paragraph 2.B. of GE CF6-6 SB 72-962, Revision 3, dated May 22, 1991, at the next engine shop visit or no later than December 31, 1991, whichever occurs first, stage 1 fan disks identified by S/N in Group C, Figure 3 of GE SB 72-962, Revision 3, dated May 22, 1991. (g) For the purpose of this AD, "shop visit" is defined as the induction of the engine into the shop for any reason. (h) Stage 1 fan disks that have been inspected to the Immersion Ultrasonic Inspection of CF6-6 Commercial Engine Service Memorandum (CESM) No. 98, have been found serviceable and comply with the immersion ultrasonic requirements of this AD. (i) Remove from service prior to further flight those disks inspected in accordance with paragraph (f) of this AD which do not meet the acceptance criteria of paragraph 2.B. of the Accomplishment Instructions of GE CF6-6 SB 72-962, Revision 3, dated May 22, 1991. (j) Aircraft may be ferried in accordance with the provisions of FAR 21.197 and 21.199 to a base where the AD can be accomplished. (k) Upon submission of substantiating data by an owner or operator through an FAA Inspector, (maintenance, avionics, or operations, as appropriate) an alternate method of compliance with the requirements of this AD or adjustments to the compliance schedules specified in this AD may be approved by the Manager, Engine Certification Office, Engine and Propeller Directorate, Aircraft Certification Service, FAA, 12 New England Executive Park, Burlington, Massachusetts 01803-5299. The inspections and removal of fan disks shall be done in accordance with the following General Electric service documents: Document No. Page No. Issue Date CF6-6 S/B 72-962 1 and 13 Rev. 3 May 22, 1991 2 thru 4 Rev. 2 Feb. 8, 19918, 12, and 14 6, 9, 10 Rev. 1 Dec. 20, 1990 5, 7, and 11 original July 2, 1990 Total Pages: 14 CF6-6 CESM No. 98 1 thru 3 Rev. 2 Oct. 5, 1989 Total Pages: 3 This incorporation was approved by the Director of the Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR Part 51. All persons affected by this directive who have not already received the appropriate service information from the manufacturer may obtain copies upon request to General Electric Company, Technical Publications Department, 1 Neumann Way, Cincinnati, Ohio 45215. This information may be examined at the FAA, New England Region, Office of the Assistant Chief Counsel, Room 311, 12 New England Executive Park, Burlington, Massachusetts, or at the Office of the Federal Register, 1100 L Street, NW, Room 8401, Washington, D.C. This amendment (39-7066, AD 91-15-03) becomes effective on August 5, 1991.
95-20-01 R1: This document publishes in the Federal Register an amendment adopting Airworthiness Directive (AD) 95-20-01 R1, which was sent previously to all known U.S. owners and operators of certain Beech Aircraft Corporation (Beech) Models 65 and L-23F (military conversion) airplanes. This AD requires fabricating and installing a placard that specifies not to operate the airplane with the cabin door removed, and incorporating a copy of the AD into the Limitations Section of the Airplane Flight Manual (AFM). A recent accident of one of the affected airplanes that was operating with the cabin door removed prompted the existing AD. The actions specified by this AD are intended to prevent the possibility of a reduction in stability, controllability, or airplane climb performance during operation, particularly in single-engine operations at high gross weights. Comments for inclusion in the Rules Docket must be received on or before December 27, 1995.
2011-09-17: We are adopting a new airworthiness directive (AD) for the products listed above that supersedes an existing AD. 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: * * * * * The revision 01 of Airbus A340 ALS [Airworthiness Limitations section] Part 3 introduces more restrictive maintenance requirements and/or airworthiness limitations. Failure to comply with this revision constitutes an unsafe condition. * * * * * The unsafe condition is a safety-significant latent failure that would, in combination with one or more other specific failures or events, result in a hazardous or catastrophic failure condition. This AD requires actions that are intended to address the unsafe condition described in the MCAI.