Aircraft-logs.com

Results
86-23-04: 86-23-04 FOKKER B.V.: Amendment 39-5459. Applies to Model F27 airplanes; serial numbers 10105 to 10648 inclusive, 10654, 10658, 10659, 10660, 10662 to 10667 inclusive, 10669, 10672 and 10678; certificated in any category. To ensure structural integrity of the elevator trim tab, accomplish the following, unless already accomplished: A. Within 60 days after the effective date of this AD, conduct a one-time visual inspection of the elevator trim tab in accordance with Fokker Service Bulletin F27/55-59, Revision 1, dated October 15, 1985. B. If incorrect rivets are installed, repair the tab before further flight in accordance with the above service bulletin. C. An alternate means of compliance or adjustment of compliance time, which provides an acceptable level of safety, may be used when approved by the Manager, Standardization Branch, ANM-113, FAA, Northwest Mountain Region. D. Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes to a base for the accomplishment of inspections and/or modifications required by this AD. All persons affected by this directive who have not already received the appropriate service document from the manufacturer may obtain copies upon request to the Manager of Maintenance and Engineering, Fokker B.V., Product Support, P.O. Box 7600, 11172J Schiphol Oost, the Netherlands. This document may be examined at the FAA, Northwest Mountain Region, 17900 Pacific Highway South, Seattle, Washington, or at the Seattle Aircraft Certification Office, 9010 East Marginal Way South, Seattle, Washington. This amendment becomes effective December 10, 1986.
93-01-25: 93-01-25 AIRBUS INDUSTRIE: Amendment 39-8479. Docket 92-NM-243-AD. Applicability: Model A320 series airplanes, manufacturer's serial numbers 002 through 180, inclusive; 183 through 194, inclusive; 196 through 315, inclusive; 317 through 321, inclusive; 323 through 325, inclusive; and 328 through 334, inclusive; certificated in any category. Compliance: Required as indicated, unless accomplished previously. To prevent fuel leakage onto the engine and the potential for an engine fire, accomplish the following: (a) Within 500 hours time-in-service after the effective date of this AD, perform a torque check of the connection on the fuel return line at rib 9 in accordance with Airbus Industrie All Operator Telex (AOT) 28-04, Revision 1, dated September 9, 1992. (1) If the red witness marks are incorrectly aligned, prior to further flight, accomplish paragraphs (a)(1)(i) and (a)(1)(ii) of this AD in accordance with the AOT. (i) Tighten the connection totorque values between 478 and 522 inch-pounds. (ii) Remove the existing witness marks and remark with an indelible marker pen. (2) If the red witness marks are correctly aligned, this AD does not require retorquing or remarking. (b) Within 500 hours time-in-service after the effective date of this AD, perform a leak check of the sealant in pylon zone "A", in accordance with All Operator Telex (AOT) 28-04, Revision 1, dated September 9, 1992. (1) If any leak is found or if the water level drops while conducting the leak check, prior to further flight, replace the sealant in accordance with the AOT. (2) If no leak is found and if the water level does not drop while conducting the leak check, this AD does not require replacement of the sealant. (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, Standardization Branch, ANM-113, FAA, Transport Airplane Directorate. Operators shall submit their requests through an appropriate FAA Principal Maintenance Inspector, who may add comments and then send it to the Manager, Standardization Branch. NOTE: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Standardization Branch. (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 checks, torquing, marking, and replacement shall be done in accordance with Airbus Industrie All Operator Telex 28-04, Revision 1, dated September 9, 1992. 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 Airbus Industrie, Airbus Support Division, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France. Copies may be inspected atthe FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC. (f) This amendment becomes effective on February 10, 1993.
85-01-05: 85-01-05 BRITISH AEROSPACE: Amendment 39-5047. Applies to Model 125 800A series airplanes with manufacturer serial numbers 258003 through 258020, certificated in all categories. To detect the lack of engine fire protection caused by improper wiring which would result in the wrong fire bottle operating, accomplish the following, unless previously accomplished: (A). Within ten (10) hours time in service after the effective date of this AD, inspect and rewire, if necessary, the electrical circuits of the engines' fire protection system, in accordance with the accomplishment instructions of British Aerospace 125 Service Bulletin 26-A25(253028), dated December 20, 1984. (B). Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes to a base for the accomplishment of inspections required by this AD. (C). Alternate inspections, modifications, or other actions which provide an acceptable level of safety may be used when approved by the Manager, Seattle Aircraft Certification Office, FAA, Northwest Mountain Region. All persons affected by this directive who have not already received these documents from their manufacturer may obtain copies upon request to British Aerospace, Inc., Librarian, Box 12414, Dulles International Airport, Washington, D.C. 20041. This amendment becomes effective May 13, 1985, and was effective earlier to those recipients of AD 85-01-05 dated January 15, 1985, distributed by priority letter.
93-09-13: 93-09-13 DE HAVILLAND, INC.: Amendment 39-8579. Docket 92-NM-232-AD. Applicability: Model DHC-8-100 and -300 series airplanes on which Modification 8/1970 has not been accomplished; certificated in any category. Compliance: Required as indicated, unless accomplished previously. To prevent loss of conductivity, which could lead to overheat damage to wiring or connectors, accomplish the following: (a) Within 60 days after the effective date of this AD, replace aluminum washers installed at the bus bar connections with steel washers, in accordance with de Havilland Alert Service Bulletin S.B. A8-24-44, dated October 23, 1992. (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, New York Aircraft Certification Office (ACO), FAA, Engine and Propeller Directorate. Operators shall submit their requests through an appropriate FAA Principal Maintenance Inspector, who may add comments and then send it to the Manager, New York ACO. NOTE: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the New York ACO. (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 shall be done in accordance with de Havilland Alert Service Bulletin S.B. A8-24-44, dated October 23, 1992. 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 de Havilland, Inc., Garratt Boulevard, Downsview, Ontario M3K 1Y5, Canada. Copies may be inspected at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; or at the FAA, Engine and Propeller Directorate, New York Aircraft Certification Office, 181 South Franklin Avenue, Room 202, Valley Stream, New York; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC. (e) This amendment becomes effective on June 17, 1993.
2014-03-16: We are adopting a new airworthiness directive (AD) for all Rolls-Royce Deutschland Ltd & Co. KG (RRD) Tay 620-15, 650-15, and 651- 54 turbofan engines. This AD requires replacement of low-pressure compressor (LPC) fan blades. This AD was prompted by the discovery that the LPC fan blades leading edges erode in service and create an unacceptable blade flutter margin. We are issuing this AD to prevent LPC fan blade failure, damage to the engine, and damage to the airplane.
99-19-33: This amendment adopts a new airworthiness directive (AD) that applies to all LET Aeronautical Works (LET) Model L-13 "Blanik" sailplanes. This AD requires painting (using a contrasting color, i.e., red paint) the left hand elevator drive mechanism in order to not have the elevator drive bellcrank inadvertently installed backwards. This AD is the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for the Czech Republic. The actions specified by this AD are intended to prevent the elevator drive bellcrank from being installed backwards, which could result in an incorrect rigging of the elevator flight control with potential reduced or loss of control of the sailplane.
2014-02-01: We are superseding Airworthiness Directive (AD) 2011-03- [[Page 7383]] 13 for certain Bombardier, Inc. Model CL-600-2C10 (Regional Jet Series 700, 701, & 702) airplanes, Model CL-600-2D15 (Regional Jet Series 705) airplanes, and Model CL-600-2D24 (Regional Jet Series 900) airplanes. AD 2011-03-13 required repetitive inspections of the rudder travel limiter (RTL) return springs and primary actuator, and corrective actions if necessary. This new AD requires replacing certain RTL return springs, including doing related investigative and corrective actions, if necessary; which is terminating action for the repetitive inspections. This new AD also revises the applicability. This AD was prompted by reports of failure of the RTL return spring. We are issuing this AD to prevent failure of the RTL, which would permit an increase of rudder authority beyond normal structural limits and consequently affect the controllability of the airplane.
2014-01-04: We are adopting a new airworthiness directive (AD) for all Bae Systems (Operations) Limited Model BAe 146 series airplanes and Model Avro 146-RJ series airplanes. This AD was prompted by reports of excess solder deposited during overhaul on the frangible plug of a fire extinguisher, which prevented the release of the extinguishant. This AD requires a one-time inspection of certain engine and auxiliary power unit (APU) fire extinguishers to determine if the fire extinguishers are affected by excessive solder and corrective actions if necessary. We are issuing this AD to prevent the failure of a fire extinguisher to discharge, which reduces the ability of the fire protection system to extinguish fires in the engine or APU fire zones, possibly resulting in damage to the airplane and injury to the passengers.
99-19-21: This amendment adopts a new airworthiness directive (AD), applicable to certain Saab Model SAAB SF340A and SAAB 340B series airplanes, that requires repetitive inspections to detect cracking around certain fastener holes and adjacent areas of the front spar of the horizontal stabilizers; and corrective actions, if necessary. This amendment also requires repetitive x-ray inspections, cold working of certain fastener holes of the front spar of the horizontal stabilizers, and follow-on actions; and installation of new fasteners, which constitutes terminating action for the repetitive inspections required by this AD. This amendment is prompted by the issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified by this AD are intended to prevent failure of the front spar due to fatigue cracking around certain fastener holes of the front spar of the horizontal stabilizers, which could result in reduced structural integrity of the airplane.
48-05-04: 48-05-04 CESSNA: Applies to 120 and 140 Aircraft. Compliance required by April 1, 1948. "This airplane is to be operated in accordance with the flight limitations of the Operations Manual." This refers to the various Airplane Flight Manuals which are required equipment for landplane, skiplane, and seaplane as listed in Aircraft Specification A-768, item 403 and Note 9, which must be carried in the aircraft at all times. Airplane Flight Manuals may be obtained from Cessna dealers and the Cessna Aircraft Co., Wichita, Kansas. (Cessna Service Letters Nos. 32 and 40 dated February 10 and May 6, 1947, respectively, cover this same subject.)