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98-03-02: This amendment adopts a new airworthiness directive (AD), applicable to certain Bombardier Model CL-600-1A11 and CL-600-2A12 series airplanes, that requires replacement of the anti-noise filter on the standby and auxiliary power unit (APU) fuel pump assemblies with a new filter. 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 electrical arcing between the internal wiring and casing of the anti-noise filter on the standby and APU fuel pump assemblies, and consequent increased risk of fuel tank explosion or fire.
98-02-07: This amendment adopts a new airworthiness directive (AD) that is applicable to Hartzell Propeller Inc. Model HC-E4A-3(A,I) propellers. This action requires replacing propeller blade counterweight clamp bolts with improved bolts. This amendment is prompted by reports of a manufacturing defect in the counterweight clamp bolts that resulted in the blade counterweight separating and causing damage to the propeller. The actions specified in this AD are intended to prevent counterweight clamp bolt failure, which can result in propeller blade counterweight separation and damage to the propeller and aircraft.
2011-20-05: This amendment adopts a new airworthiness directive (AD) for the Eurocopter Model EC225LP helicopters. This AD requires inspecting the dome fairing support for a crack at the dome fairing attachment point. If a crack is found, this AD requires replacing the dome fairing support and the associated coning stop support assembly before further flight. If no crack is found, this AD requires repetitive inspections and retorquing the screws at specified intervals. This AD is prompted by the discovery of two fatigue cracks in the dome fairing attachment on the dome fairing support. This condition, if not corrected, could lead to the loss of the dome fairing in flight, causing damage to the helicopter and injury to people on the ground.
86-05-03: 86-05-03 DeHAVILLAND AIRCRAFT OF CANADA, LTD.: Amendment 39-5247. Applies to Model DHC-8-101 airplanes, serial numbers 1 through 24, certificated in any category. To assure structural integrity of the elevator and spring tab, accomplish the following within the next 200 flight hours or 30 days after the effective date of this AD, whichever comes first, unless already accomplished: A. For airplanes, serial numbers 1 through 14, accomplish Modification No. 8/0478 to the elevator mass balance weights as described in deHavilland Aircraft of Canada, Ltd., Service Bulletin No. A8-55-4, dated January 15, 1986. B. For airplanes, serial numbers 15 through 24, the limitation imposed by telegraphic AD T85-26-52, issued January 3, 1986, may be removed from the Airplane Flight Manual when Modification No. 8/0468 to the spring tab and elevator mass balance weights, as described in deHavilland Aircraft of Canada, Ltd., Service Bulletin No. A8-55-3, dated January 3, 1986, has been incorporated. C. Alternate means of compliance which provide 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 documents from the manufacturer may obtain copies upon request to deHavilland Aircraft of Canada, Ltd., Garrett Boulevard, Downsview, Ontario M3K 1Y5, Canada. These documents may be examined at the FAA, Northwest Mountain Region, 17900 Pacific Highway South, Seattle, Washington, or the Seattle Aircraft Certification Office, 9010 East Marginal Way South, Seattle, Washington. This supersedes telegraphic AD T85-26-52, dated January 3, 1986. This amendment becomes effective March 24, 1986.
87-08-06: 87-08-06 LOCKHEED-CALIFORNIA COMPANY: Amendment 39-5594. Applies to Lockheed Model L-1011-385 series airplanes, equipped with Dynamic Controls Corporation oxygen initiator sequence timer switch(es), P/N's 11035-2/-3, certificated in any category. Compliance required as indicated, unless previously accomplished. To prevent malfunction of the passenger oxygen system due to dormant shorted electromagnetic interference filter capacitors in the oxygen initiator sequencer timer switch(es), accomplish the following: A. Within 12 months after the effective date of this airworthiness directive (AD), modify P/N's 11035-2 and -3 oxygen initiator sequencer timer switches in accordance with Part II of the Accomplishment Instructions of Lockheed Service Bulletin 093-35-041, Revision 3, dated November 6, 1986, or later revisions approved by the Manager, Los Angeles Aircraft Certification Office, FAA, Northwest Mountain Region. B. Alternate means of compliance which provide an acceptable level of safety may be used when approved by the Manager, Los Angeles Aircraft Certification Office, FAA, Northwest Mountain Region. C. 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 information from the manufacturer may obtain copies upon request to Lockheed-California Company, P.O. Box 551, Burbank, California 91520, Attention: Commercial Order Administration, Dept. 65-33, U-33, B-1. These documents may be examined at the FAA, Northwest Mountain Region, 17900 Pacific Highway South, Seattle, Washington, or the Los Angeles Aircraft Certification Office, 4344 Donald Douglas Drive, Long Beach, California. This Amendment becomes effective May 5, 1987.
2011-21-06: We are superseding an existing airworthiness directive (AD) that applies to 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: * * * BAE Systems (Operations) Ltd has issued Revision 33 of the AMM [airplane maintenance manual] to amend Chapter 05-10-10 by adding one new Structurally Significant Item (SSI) and increasing the repeat inspection period on another SSI. Failure to comply with this revision constitutes an unsafe condition. * * * * * The unsafe condition is failure of certain structurally significant items, including the main landing gear and the nose landing gear, which could result in reduced structural integrity of the airplane; and fuel vapor ignition sources, which could result in a fuel tank explosion and consequent loss of the airplane. We are issuing this AD to require actions to correct the unsafe condition on these products.
86-02-02: 86-02-02 BOEING: Amendment 39-5201. Applies to Model 757 airplanes listed in Boeing Service Bulletin Number 757-25-0047, Revision 1, certificated in any category. To prevent the overloading of the main deck floor as the result of a sudden decompression, accomplish the following within 120 days after the effective date of this AD, unless already accomplished: \n\n\tA.\tInspect and, if necessary, rework and reinstall the cargo compartment blowout panel assemblies in accordance with Paragraph III of Boeing Service Bulletin 757-25-0047, Revision 1, or later FAA-approved revision. \n\n\tB.\tAlternate means of compliance which provide an acceptable level of safety may be used when approved by the Manager, Seattle Aircraft Certification Office, FAA, Northwest Mountain Region. \n\n\tC.\tSpecial 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. \n\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. These documents may be examined at the FAA, Northwest Mountain Region, 17900 Pacific Highway South, Seattle, Washington, or the Seattle Aircraft Certification Office, 9010 East Marginal Way South, Seattle, Washington. \n\n\tThis amendment becomes effective February 3, 1986.
56-15-02: 56-15-02 BELL: Applies to All Model 47 Series Helicopters Having the 47-150-184-1 or 47-150-184-3 Swashplate Control Ring Installed, Except the Following: Model 47G, Serial Numbers 1378, 1524, 1529 Through 1533 and 1687 and Subsequent. Model 47G2, Serial Numbers 1467, 1469 Through 1471, 1478, 1479, 1481, 1483, 1484, 1487 Through 1499 and 1500 and Subsequent. Model 47H1, Serial Numbers 1347, 1348, 1361, 1366 and Subsequent. Compliance required as indicated. Cracking of the control ring horns in the area of the control horn ears has been found. It is necessary that the following action for the 47-150-184-1 and 47-150-184-3 swashplate control ring, lateral, fore and aft control horns be taken as soon as possible but not later than August 15, 1956: Disconnect the control rods from the swashplate control ring horns and using a 10-power magnifying glass inspect the area around the control horn ears for evidence of cracks. If cracks are found, remove the swashplate and replace immediately. If no cracks are found, remove the sharp edge from the top of the fore and aft control horn between the ears and file a 0.062 inch radius in each corner of the fore and after control horn between the ears before replacing. (Bell Mandatory Service Bulletin No. 108, dated May 1, 1956 covers this same subject.)
2003-03-16: This amendment adopts a new airworthiness directive (AD) that is applicable to certain Airbus Model A330-223, -321, -322, and -323 series airplanes equipped with Pratt & Whitney Model PW4164, PW4168, or PW4168A engines. This action requires modification of the primary structure of the engine pylons, and replacement of the thrust reverser locking actuators with new, improved locking actuators. This action is necessary to prevent reduced structural integrity of the primary structure of the engine pylons, and uncommanded deployment of the thrust reversers, which could result in reduced controllability of the airplane. This action is intended to address the identified unsafe condition.
69-10-01: 69-10-01 NORTH AMERICAN ROCKWELL: Amendment 39-764. Applies to NA- 265 Series aircraft equipped with main landing gear pistons P/N 174447 (LH), 174448 (RH), 174981 (LH), 174982 (RH), 2573965 (LH), 2573966 (RH), 1127L011-1 (lH), or 1127L011-2 (RH) with serial numbers which have not been altered by the addition of the letter "L", "R", or "T" in accordance with the instructions contained in Los Angeles Division of North American Rockwell Corporation Sabreliner Field Service Bulletin No. 69-2, dated March 31, 1969, or later revision approved by the Chief, Aircraft Engineering Division, FAA, Western Region. Compliance required as indicated, unless already accomplished. To prevent failure of the main landing gear pistons, accomplish the following: PART I (a) Part I of this AD applies to landing gear pistons, P/N 174981 (LH) (Serial Nos. S-132A, S-145, S-148, S-153, S-158, S-162, S-169, and S-172) and 174982 (RH) (Serial Nos. S- 144, S-149, S-154, S-157, S-159, S-161, S-164, S-165, S-166, and S-168). (b) Within 15 hours time in service after the effective date of this AD, accomplish the following: (1) Rework and inspect the lower inside diameter of the piston in accordance with instructions contained in the above mentioned service bulletin No. 69-2, dated March 31, 1969, or later revision approved by the Chief, Aircraft Engineering Division, FAA Western Region; or (2) Replace main landing gear pistons with parts which have been identified in accordance with Service Bulletin 69-2 with the letter "L", "R", or "T" following the serial number on the lower outboard side of the piston, or with another approved piston. PART II (a) Part II of this AD applies to all affected landing gear pistons not listed in Part I above. (b) Within the next 300 hours time in service after the effective date of this AD accomplish the following: (1) Inspect the lower inside diameter of the piston and rework as necessary in accordance with instructions contained in the above mentioned Service Bulletin No. 69-2, dated March 31, 1969, or later revision approved by the Chief, Aircraft Engineering Division, FAA Western Region; or (2) Replace each main landing gear piston with a piston which has been identified in accordance with Service Bulletin No. 69-2 with the letter "L", "R", or "T" following the serial number on the lower outboard side of the piston or with another approved piston. This amendment becomes effective May 9, 1969.