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86-15-02: 86-15-02 AVIONS MARCEL DASSAULT - BREGUET AVIATION: Amendment 39- 5355. Applies to Model Mystere-Falcon 50 series airplanes, serial numbers 24 through 146, 148 through 158, 160, 161, and 162. Compliance is required as indicated below. To prevent engine failure due to fuel starvation, accomplish the following, unless previously accomplished: A. Within the next 21 days after the effective date of this AD, replace the actuators in the distributor blocks of the crossfeed valves and install a placard in accordance with Avion Marcel Dassault-Breguet Aviation Service Bulletin F52-28-17 (AMD-BA F50-182), dated April 4, 1986. B. 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, 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 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 bulletin from the manufacturer, may obtain copies upon request to Falcon Jet Corporation, Customer Support Department, Teterboro Airport, Teterboro, New Jersey 07608. This document 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 amendment becomes effective July 28, 1986.
2017-16-10: We are adopting a new airworthiness directive (AD) for all The Boeing Company Model 777 airplanes. This AD was prompted by reports of cracks on the underwing longerons. This AD requires repetitive inspections of the left and right side underwing longerons for any crack, and related investigative and corrective actions if necessary. We are issuing this AD to address the unsafe condition on these products.
2010-26-13: 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: Several cases of aileron terminal quadrant support brackets that were manufactured using sheet metal have been found cracked on DHC-8 Series 300 aircraft. Investigation revealed that the failure of the support bracket was due to fatigue. Failure of the aileron terminal quadrant support bracket could result in an adverse reduction of aircraft roll control. * * * * * These conditions could result in loss of control of the airplane. We are issuing this AD to require actions to correct the unsafe condition on these products.
2023-02-09: The FAA is superseding Airworthiness Directive (AD) 2007-10- 04, which applied to all McDonnell Douglas Model DC-9-81 (MD-81), DC-9- 82 (MD-82), DC-9-83 (MD-83), DC-9-87 (MD-87), and MD-88 airplanes. AD 2007-10-04 required repetitive inspections to detect cracks in the horizontal stabilizer, and related investigative and corrective actions if necessary. Since the FAA issued AD 2007-10-04, it has been determined that certain compliance times and repetitive intervals must be reduced to address the unsafe condition. This AD continues to require the actions specified in AD 2007-10-04 with revised compliance times for certain actions. The FAA is issuing this AD to address the unsafe condition on these products.
91-21-06: 91-21-06 BRITISH AEROSPACE: Amendment 39-8053. Docket No. 91-NM-122-AD. Applicability: Model BAe 146-100A series airplanes, Serial Numbers up to and including E1152; Model BAe 146-200A series airplanes, Serial Numbers up to and including E2156; and Model BAe 146-300A series airplanes, Serial Numbers up to and including E3157; certificated in any category. Compliance: Required as indicated, unless previously accomplished. To ensure engine fire extinguisher medium is discharged to proper locations in the event of an engine fire, accomplish the following: (a) Within 30 days after the effective date of this AD, perform a visual inspection to detect chafing of the extinguisher pipe and clamp assemblies between the two fire extinguisher bottles in the engine nose cowls; and ensure that adequate clearance exists between the three pipe assemblies and the adjacent equipment and structure; in accordance with the instructions in British Aerospace Inspection Service Bulletin 26-A29, Revision 2, dated January 14, 1991. (b) Prior to the installation of any nose cowl or engine/nose cowl combination on an operational airplane, perform a visual inspection to detect chafing of the extinguisher pipe and clamp assemblies between the two fire extinguisher bottles in the engine nose cowls; and ensure that adequate clearance exists between the three pipe assemblies and the adjacent equipment and structure; in accordance with the instructions in British Aerospace Inspection Service Bulletin 26-A29, Revision 2, dated January 14, 1991. (c) If any damaged extinguisher pipe and clamp assembly is identified as a result of the inspection required by paragraph (a) or (b) of this AD, prior to further flight, repair or replace the damaged assembly in accordance with instructions in British Aerospace Inspection Service Bulletin 26-A29, Revision 2, dated January 14, 1991. (d) An alternative method 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 forwarded through an FAA Principal Maintenance Inspector, who may concur or comment and then send it to the Manager, Standardization Branch, ANM-113. (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. (f) The inspection and repair or replacement requirements shall be done in accordance with British Aerospace Inspection Service Bulletin 26-A29, Revision 2, dated January 14, 1991. 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 British Aerospace, PLC, Librarian for Service Bulletins, P.O. Box 17414, Dulles International Airport, Washington, D.C. 20041-0414. Copies may be inspected at the FAA, Transport Airplane Directorate, 1601 Lind Avenue S.W., Renton, Washington; or at the Office of the Federal Register, 1100 L Street N.W., Room 8401, Washington, D.C. This amendment (39-8053, AD 91-21-06) becomes effective on November 19, 1991.
2001-26-24: This amendment adopts a new airworthiness directive (AD), applicable to McDonnell Douglas Model DC-9-10, -20, -30, -40, and -50 series airplanes; and C-9 airplanes that requires replacing the transformer ballast assembly in the pilot's console with a new, improved ballast assembly. The actions specified by this AD are intended to prevent overheating of the ballast transformers due to aging fluorescent tubes that cause a higher power demand on the ballast transformers, which could result in smoke in the cockpit. This action is intended to address the identified unsafe condition.
2001-26-18: This amendment adopts a new airworthiness directive (AD), applicable to certain Dornier Model 328-300 series airplanes, that requires, for certain airplanes, a one-time torque test (inspection) of the attachment bolts of the forward engine mount vibration isolators to determine if the bolts are adequately torqued, and corrective action, if necessary. For all airplanes, this amendment prohibits installation of an attachment bolt on the forward engine mount vibration isolators, unless the attachment bolt is torqued within certain limits. These actions are necessary to prevent failure of the engine mount, which could result in separation of the engine from the airplane. This action is intended to address the identified unsafe condition.
97-21-01 R1: 97-21-01 R1 MT-PROPELLER ENTWICKLUNG GMBH: Amendment 39-11206. Docket 97-ANE-36-AD. Revises AD 97-21-01, Amendment 39-10154. Applicability: MT-Propeller Entwicklung GMBH Model MTV-3-B-C/L250-21 propellers. These propellers are installed on but not limited to Sukhoi 29 aircraft. Note 1: This airworthiness directive (AD) applies to each propeller identified in the preceding applicability provision, regardless of whether it has been modified, altered, or repaired in the area subject to the requirements of this AD. For propellers that have been modified, altered, or repaired so that the performance of the requirements of this AD is affected, the owner/operator must request approval for an alternative method of compliance in accordance with paragraph (c) of this AD. The request should include an assessment of the effect of the modification, alteration, or repair on the unsafe condition addressed by this AD; and, if the unsafe condition has not been eliminated, the request should include specific proposed actions to address it. Compliance: Required as indicated, unless accomplished previously. To prevent propeller hub cracks, which could result in propeller blade separation and possible loss of control of the airplane, accomplish the following: (a) Within 50 hours time-in-service (TIS) after the effective date of this AD, accomplish the following: (1) Perform an initial dye penetrant or eddy current inspection of propeller hub, part number (P/N) B-050 or A-909-A, in accordance with paragraph (a) of MT-Propeller Entwicklung GMBH Service Bulletin (SB) No. 12C, dated March 4, 1998. The dye penetrant inspection may be done on-wing, but the eddy current inspection must be performed in an FAA-approved propeller repair station. (2) If the propeller hub is found to be cracked, prior to further flight, remove the existing propeller hub and replace with a serviceable propeller hub. (3) Rework propeller hubs, P/N B-050, by chamfering the hub bore to 0.08 inch x 45 degrees (for further information, see Detail Y of MT-Propeller Entwicklung GMBH SB No. 12C, dated March 4, 1998). Mark hubs that have been reworked in accordance with AD 97-21-01, or this revised AD, with the letters SB12C using a metal impression stamp (1/8 inch round bottom characters) above the propeller hub serial number and part number, located in the transition area between propeller blades 1 and 2 and the pitch change cylinder. (b) Thereafter, perform dye penetrant or eddy current inspections, in accordance with paragraph (a) of MT-Propeller Entwicklung GMBH SB No. 12C, dated March 4, 1998. The dye penetrant inspection may be done on-wing, but the eddy current inspection must be performed in an FAA-approved propeller repair station: (1) For propellers with hubs, P/N B-050, inspect at intervals not to exceed 50 hours TIS, or 6 months since last inspection, whichever occurs first. (2) For propellers with hubs, P/N A-909-A, inspect at intervals not to exceed 200 hours TIS, or 12 months since last inspection, whichever occurs first. (3) If the propeller hub is found to be cracked, prior to further flight, remove the existing propeller hub and replace with a serviceable propeller hub. (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, Boston Aircraft Certification Office. Operators shall submit their requests through an appropriate FAA Maintenance Inspector, who may add comments and then send it to the Manager, Boston Aircraft Certification Office. Note 2: Information concerning the existence of approved alternative methods of compliance with this airworthiness directive, if any, may be obtained from the Boston Aircraft Certification Office. (d) Special flight permits may be issued in accordance with sections 21.197 and 21.199 of the Federal Aviation Regulations (14 CFR 21.197 and 21.199) to operate the aircraft to a location where the inspection requirements of this AD can be accomplished. (e) The actions required by this AD shall be accomplished in accordance with the following MT-Propeller Entwicklung GMBH SB: Document No. Pages Date 12C 1-3 March 4, 1998 Total pages: 3. 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 MT- Propeller Entwicklung GMBH, Airport Straubing-Wallmuhle, D-94348 Atting, Germany; telephone (0 94 29) 84 33, fax (0 94 29) 84 32, Internet: "propeller@aol.com". Copies may be inspected at the FAA, New England Region, Office of the Regional Counsel, 12 New England Executive Park, Burlington, MA; or at the Office of the Federal Register, 800 North Capitol Street, NW, suite 700, Washington, DC. (f) This amendment becomes effective on August 27, 1999.
2017-16-05: We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 737-600, -700, -700C, -800, -900, and -900ER series airplanes. This AD was prompted by a report of a Krueger flap bullnose departing an airplane during taxi, which caused damage to the wing structure and thrust reverser. This AD requires a one-time detailed visual inspection for discrepancies in the Krueger flap bullnose attachment hardware, and related investigative and corrective actions, if necessary. We are issuing this AD to address the unsafe condition on these products.
2017-16-11: We are adopting a new airworthiness directive (AD) for certain models of Lycoming Engines reciprocating engines. This AD requires an inspection of connecting rods and replacement of affected connecting rod small end bushings. This AD was prompted by several reports of connecting rod failures resulting in uncontained engine failure and in- flight shutdowns (IFSDs). We are issuing this AD to address the unsafe condition on these products.