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91-03-09: 91-03-09 BOEING: Amendment 39-6874. Docket No. 90-NM-189-AD. \n\n\tApplicability: Boeing Model 727 series airplanes, as listed in Service Bulletin 727-25- 0271, dated April 19, 1990, certificated in any category. \n\n\tCompliance: Required as indicated, unless previously accomplished. \n\n\tTo prevent a fire hazard associated with unrestrained loose items in life raft stowage compartments falling onto hot passenger service unit lights, accomplish the following: \n\n\tA.\tWithin the next 30 days after the effective date of this AD, install a placard on each affected life raft compartment, stating: "LIFE RAFT STOWAGE ONLY" \n\n\tB.\tThe life raft compartment may be used for stowage and the placard required by paragraph A. of this AD may be removed if or when the life raft compartment is modified in accordance with Boeing Service Bulletin 727-25-0271, dated April 19, 1990. \n\n\tC.\tAn alternate means of compliance or adjustment of the compliance time, which provides an acceptable level ofsafety, may be used when approved by the Manager, Seattle Aircraft Certification Office (ACO), FAA, Transport Airplane Directorate. \n\n\tNOTE: The request should be submitted directly to the Manager, Seattle ACO, and a copy sent to the cognizant FAA Principal Inspector (PI). The PI will then forward comments or concurrence to the Seattle ACO. \n\n\tD.\tSpecial 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. \n\n\tAll persons affected by this directive who have not already received the appropriate service documents from the manufacturer may obtain copies upon request to Boeing Commercial Airplane Group, P.O. Box 3707, Seattle, Washington 98124. These documents may be examined at the FAA, Northwest Mountain Region, Transport Airplane Directorate, 1601 Lind Avenue S.W., Renton, Washington. \n\n\tThis amendment (39-6874, AD 91-03-09) becomes effective on March 4, 1991.
90-19-07: 90-19-07 AIRBUS INDUSTRIE: Amendment 39-6731. Docket No. 90-NM-93-AD. Applicability: Model A310-200 series airplanes, up to and including serial number 264, certificated in any category. Compliance: Required as indicated, unless previously accomplished. To prevent reduced structural capability of the wings, accomplish the following: A. Prior to the accumulation of 12,000 landings, or within 1,500 landings after the effective date of this AD, whichever occurs later, and thereafter at intervals not to exceed 12,000 landings, perform an X-ray inspection of Stringers 6, 7, 8, and 9 run-outs inboard and outboard of Rib 14, in accordance with Airbus Industrie Service Bulletin A310-57-2038, dated November 6, 1989. B. If cracks are found, repair prior to further flight in accordance with a procedure approved by the Manager, Standardization Branch, ANM-113, FAA, Northwest Mountain Region. C. 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, Standardization Branch, ANM-113, FAA, Transport Airplane Directorate. NOTE: The request should be submitted directly to the Manager, Standardization Branch, ANM-113, and a copy sent to the cognizant FAA Principal Inspector (PI). The PI will then forward comments or concurrence 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. All persons affected by this directive who have not already received the appropriate service documents from the manufacturer may obtain copies upon request to Airbus Industrie, Airbus Support Division, Avenue Didier Daurat, 31700 Blagnac, France. These documents may be examined at the FAA, Northwest Mountain Region, Transport Airplane Directorate, 1601 Lind Avenue S.W., Renton, Washington. This amendment (39-6731, AD 90-19-07) becomes effective October 23, 1990.
77-08-08: 77-08-08 GENERAL ELECTRIC: Amendment 39-2878 as amended by Amendment 39-3690. Applies to General Electric Models CF6-50A, CF6-50C, CF6-50C1, CF6-50D, CF6-50E, CF6-50E1, and CF6-50H engines that do not incorporate steel high pressure compressor rotors and cases, and are installed in aircraft certificated in all categories. Engines with serial numbers 517451, 517452, 517472 thru 517475, 517502, and subsequent 517 prefixed numbers; and 455907 thru 455912, 455920, and subsequent 455 prefixed numbers were manufactured with steel compressor rotors and cases. Earlier engines may be converted to the steel configuration in accordance with General Electric Service Bulletins (CF6-50/45) 72-547, 72-549, 72-550, and 72-551. Compliance required by January 31, 1978, unless previously accomplished. To prevent possible burn through of fuel or oil tubes located below the compressor section, accomplish the following in accordance with General Electric Service Bulletin (CF6-50) 72-447 datedDecember 30, 1976, or subsequent FAA Approved revisions thereto: (a) Replace the Fuel Manifold, Part Number 9008M43G01, 9008M43G02 or 9008M43G03, with Part Number 9200M17G01, 9200M17G02 or 9200M17G03. (b) Replace the Lube Supply, Part Number 9043M25G02, with Part Number 9200M11G01. (c) Replace the "B" Sump Scavenge Aft, Part Number 9068M88G01 or 9194M18G01, with Part Number 9200M10G01. (d) Replace the "B" Sump Scavenge Forward, Part Number 9005M64G01, with Part Number 9191M72G01. (e) Replace the "C" Sump Scavenge, Part Number 9054M44G01, with Part Number 9200M15G03. (f) Replace the "D" Sump Scavenge, Part Number 9055M93G01, with Part Number 9200M16G02. Equivalent modifications may be approved by the Chief, Engineering and Manufacturing Branch, FAA Great Lakes Region. Amendment 39-2878 became effective April 29, 1977. This Amendment 39-3690 becomes effective February 14, 1980.
99-19-38: This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A310 series airplanes, that requires repetitive high frequency eddy current inspections to detect fatigue cracking at the hole in the lower web of the inner and outer attachment fittings of the number 3 wing spoilers; and corrective actions, if necessary. This amendment also provides for an optional modification, which terminates the repetitive inspections. 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 detect and correct fatigue cracking and eventual failure of the attachment fittings of the number 3 wing spoilers.
99-27-05: This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 767-200, -300, and -300F series airplanes, that requires replacement of the hydraulic reducer fitting in the return port of the alternate brake selector valve with a new restrictor fitting. This amendment is prompted by a report indicating that a brake housing had fractured due to high loads associated with brake vibration during landing gear retraction, which allowed the torque rod to swing free. The actions specified by this AD are intended to prevent failure of the brake housing in the torque rod region, which could reduce the braking capability of the airplane and/or prevent the extension of a main landing gear by any method.
99-25-10: This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A319, A320, and A321 series airplanes, that requires a one-time inspection of the forward engine mount assembly of the left and right engines to verify that the part number on each assembly is correct; re-identification of the forward engine mount assembly; and follow-on actions, if necessary. 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 structural failure of the secondary load path of the forward engine mount, which, if combined with failure of the primary load path, could result in separation of the engine from the airplane.
98-22-14: This amendment adopts a new airworthiness directive (AD) that applies to Rolladen Schneider Flugzeugbau GmbH (Rolladen Schneider) Models LS 3-A, LS 4, and LS 4a sailplanes. This AD requires repetitively inspecting the forward elevator mounting bracket on the vertical tail fin for looseness, and, if any loose bracket is found, modifying the area and installing a new forward elevator mounting bracket. This AD is the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for Germany. The actions specified by this AD are intended to detect and correct loose forward elevator mounting brackets, which could result in these brackets separating from the sailplane with consequent loss of control of the sailplane.
99-27-09: This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A300 B4-203 series airplanes. This action requires repetitive inspections of the attachment bolts of the brake bar on the main landing gear (MLG) to detect missing or damaged bolts, and replacement with new bolts, if necessary. This amendment is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified in this AD are intended to prevent detachment of the brake bar from the MLG strut, which could result in failure of the main landing gear to extend.
99-24-08: This amendment supersedes an existing airworthiness directive (AD), applicable to all Boeing Model 737-100, - 200, -300, -400, and -500 series airplanes, that currently requires, for certain airplanes, repetitive replacements of the airplane battery with a new or reconditioned battery and replacement of the battery charger with a new or serviceable battery charger; performing repetitive tests to determine the condition of a certain diode of the Generator Control Units (GCU); and corrective actions, if necessary. This amendment adds, for certain other airplanes, a requirement for repetitive replacements of the airplane battery with a new or reconditioned battery, and clarifies a diode test requirement. This amendment is prompted by an incident during which all electrical power was lost due to a combination of a weak or depleted battery and the failure of a certain diode of the GCU. The actions specified in this AD are intended to prevent failure of all electrically powered airplane systems, which could result in the inability to continue safe flight and landing.
97-07-01: This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A330 and A340 series airplanes. This action requires the deactivation of the avionics ground refrigeration unit (GRU) of the air conditioning system until a modification of avionics ventilation circuit and the GRU is accomplished. This amendment is prompted by reports of water accumulation found in the Air Data/Inertial Reference Unit (ADIRU) trays of the avionics rack; the accumulation is the result of operation of the GRU in high ambient humidity. The actions specified in this AD are intended to prevent water accumulating in this area, which could result in the failure of the ADIRU and consequent loss of air data and navigational information to the flightcrew.