Results
96-22-16: This amendment adopts a new airworthiness directive (AD) that applies to certain HB Aircraft Industries AG HB-23 2400 Hobbyliner/Scanliner sailplanes. This action requires inspecting the rudder bearing support bracket for cracks, replacing the bracket if cracked, and modifying the bracket with a third bolt, if no cracks are found. Cracks found in the rudder bearing support brackets prompted this action. The actions specified by this AD are intended to prevent cracks in the rudder bearing support bracket, which could cause loss of control of the rudder and possible loss of the sailplane.
96-22-13: This amendment adopts a new airworthiness directive (AD) that applies to Pilatus Aircraft Ltd. (Pilatus), Model PC-6 airplanes. This action requires inspecting for loose or sheared rivets in the hinge brackets on the horizontal stabilizer and inspecting for incorrect spacing tolerance of the hinge brackets. If the rivets are found loose or sheared, the AD requires replacing the rivets and also re-positioning the hinge brackets, if found incorrectly spaced. Several reports of rivets shearing on the hinge brackets prompted this action. The actions specified by this AD are intended to prevent structural failure of the hinge bracket on the horizontal stabilizer, which could result in partial or complete loss of control of the horizontal stabilizer and loss of control of the airplane.
92-27-11 R1: 92-27-11 R1 MCDONNELL DOUGLAS: Amendment 39-8491. Docket 93-NM-07-AD. Revises AD 92-27-11, Amendment 39-8446. \n\n\tApplicability: McDonnell Douglas Model MD-11 and MD-11F series airplanes; as listed in McDonnell Douglas MD-11 Alert Service Bulletin A76-3, dated November 17, 1992; certificated in any category. \n\n\tCompliance: Required as indicated, unless accomplished previously. \n\n\tTo prevent inhibited operation of the engine emergency fire extinguisher system, accomplish the following: \n\n\t(a)\tWithin 30 days after the effective date of this AD, perform a functional inspection for proper actuation of the fire bottle switch, and a visual inspection of the fire shutoff handle cover assembly to verify whether a minimum clearance of 0.030 inch (0.76 mm) exists between the fire shutoff handles, cover assembly, and rub strips in the flight compartment, in accordance with the Accomplishment Instructions of McDonnell Douglas MD-11 Alert Service Bulletin A76-3, dated November 17, 1992. \n\n\t\t(1)\tIf any fire bottle switch actuates (audible click), and if any handle clearance is found to be 0.030 inch (0.76 mm) or greater, no further action is necessary; or \n\n\t\t(2)\tIf any fire bottle switch does not actuate (click is not audible), and/or any handle clearance is not found to be 0.030 inch (0.76 mm) or greater, prior to further flight, trim the cover assembly handle cutout and rub strips to achieve a clearance of 0.030 inch (0.76 mm) or greater, and repeat the functional inspection requirements for proper switch actuation in accordance with paragraph (a) of this AD. \n\n\t(b)\tAn 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, Los Angeles Aircraft Certification Office (ACO), 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, LosAngeles ACO. \n\n\tNOTE: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Manager, Los Angeles ACO. \n\n\t(c)\tSpecial 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. \n\n\t(d)\tThe functional inspection and trim shall be done in accordance with McDonnell Douglas MD-11 Alert Service Bulletin A76-3, dated November 17, 1992. This incorporation by reference was approved previously by the Director of the Federal Register, in accordance with 5 U.S.C. 552(a) and 1 CFR Part 51, as of January 13, 1993 (57 FR 61791, December 29, 1992). Copies may be obtained from McDonnell Douglas Corporation, P.O. Box 1771, Long Beach, California 90846-1771, Attention: Business Unit Manager, Technical Publications - Technical Administrative Support, C1-L5B. Copies may be inspected at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; or at FAA, Transport Airplane Directorate, Los Angeles Aircraft Certification Office, 3229 East Spring Street, Long Beach, California; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC. \n\n\t(e)\tThis amendment becomes effective on February 8, 1993.
2021-13-10: The FAA is adopting a new airworthiness directive (AD) for certain The Boeing Company Model 777 airplanes. This AD was prompted by reports indicating that during investigation of a fuel leak, fatigue cracking was found on the forward inboard side of the fuel tank access door cutouts on the left and right lower wing skin. The cause of the cracking is attributed to corrosion damage. This AD requires repetitive inspections for any existing repair of the wing lower skin fuel tank and dry bay access door cutouts on the left and right lower wing skin, and applicable on-condition actions. The FAA is issuing this AD to address the unsafe condition on these products.
96-22-10: This amendment adopts a new airworthiness directive (AD), applicable to all McDonnell Douglas DC-9 and DC-9-80 series airplanes, and Model MD-88 airplanes, that requires repetitive leak checks of the lavatory drain system and repair, if necessary; provides for the option of revising the FAA-approved maintenance program to include a schedule of leak checks; requires the installation of a cap on the flush/fill line; and requires replacement or modification of the vent system piping. This amendment is prompted by continuing reports of damage to engines and airframes, separation of engines from airplanes, and damage to property on the ground, caused by "blue ice" that forms from leaking lavatory drain systems on transport category airplanes and subsequently dislodges from the airplane fuselage. The actions specified by this AD are intended to prevent such damage associated with the problems of "blue ice."
91-15-10: 91-15-10 SOCATA Groupe AEROSPATIALE: Amendment 39-7074. Docket No. 91-CE-56-AD. Applicability: Models TB9 and TB10 airplanes (serial numbers 1 through 1217); and Models TB20 and TB21 airplanes (serial numbers 1 through 1030), certificated in any category. Compliance: Required within the next 25 hours time-in-service after the effective date of this AD, unless already accomplished. NOTE: The compliance time referenced in this AD takes precedence over that in the referenced service bulletin. To prevent adverse airplane handling qualities and possible loss of control of the airplane, accomplish the following: (a) Inspect the horizontal stabilizer balance weight attachment nuts for proper installation in accordance with the instructions in Parts 1) and 2) of SOCATA Groupe AEROSPATIALE Imperative Service Bulletin No. 57, dated January 1991. (1) If the horizontal stabilizer balance weight attachment nuts are not loose and are properly installed, accomplish the requirements in Part 3) of SOCATA Groupe AEROSPATIALE Imperative Service Bulletin No. 57, dated January 1991, and return the airplane to service. (2) If the horizontal stabilizer balance weight attachment nuts are loose or are improperly installed, prior to further flight, remove, inspect, modify and reinstall the horizontal stabilizer balance weight in accordance with the criteria and instructions in Part 4) of SOCATA Groupe AEROSPATIALE Imperative Service Bulletin No. 57, dated January 1991. (b) An alternative method of compliance or adjustment of the compliance time that provides an equivalent level of safety may be approved by the Manager, Brussels Aircraft Certification Office, FAA, Europe, Africa, and Middle East Office, c/o American Embassy, B-1000, Brussels, Belgium. The request should be forwarded through an appropriate FAA Maintenance Inspector, who may add comments and then send it to the Manager, Brussels Aircraft Certification Office. (c) The inspection and possible modification required by this AD shall be done in accordance with SOCATA Groupe AEROSPATIALE Imperative Service Bulletin No. 57, dated January 1991. This incorporation by reference was previously approved by the Director of the Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR Part 51, as of June 20, 1991, at 56 FR 2433 (May 30, 1991). Copies may be obtained from SOCATA Groupe AEROSPATIALE, Socata Product Support, Aeroport Tarbes-Ossun-Lourdes, B P 930, 65009 Tarbes Cedex, France; or the Product Support Manager, U.S.; AEROSPATIALE, 2701 Forum Drive, Grand Prairie, Texas. Copies may be inspected at the FAA, Central Region, Office of the Assistant Chief Counsel, Room 1558, 601 E. 12th Street, Kansas City, Missouri, or at the Office of the Federal Register, 1100 L Street, NW, Room 8401, Washington, DC. Airworthiness Directive 91-15-10 supersedes AD 91-12-19, Amendment 39-6988. The amendment (39-7074, AD 91-15-10) becomes effective on August 10, 1991.
2011-14-06: We are superseding an existing airworthiness directive (AD) [[Page 42025]] 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: * * * * * The issue 10 of Airbus A318/A319/A320/A321 ALI [Airworthiness Limitation Items] Document and issue 2 of Airbus A319 Corporate Jet ALI Document introduce more restrictive maintenance requirements/ airworthiness limitations. Failure to comply with this issue 10 constitutes an unsafe condition. * * * * * The unsafe condition is fatigue cracking, accidental damage, or corrosion in principal structural elements and possible failure of certain life limited parts, which could result in reduced structural integrity of the airplane. We are issuing this AD to require actions to correct the unsafe condition on these products.
93-11-03: 93-11-03 TELEDYNE CONTINENTAL MOTORS: Amendment 39-8600. Docket 93-ANE-32. Applicability: Teledyne Continental Motors (TCM) Models O-200A, O-300A, O-300C, and O-300D reciprocating engines with the following serial numbers: New O-200A: 256005 through 256009, 256011 and 256012; Rebuilt O-200A: 281313-R, 281316-R, 281319-R through 281323-R, 281325-R through 281327-R, 281329-R, 281331-R, 281335-R, 281338-R, 281340-R, 281342-R, 281344-R, 281345-R, 281347-R, 281350-R, 281354-R, 281356-R, 281358-R, 281359-R, 281364-R, 281367-R, 281372-R through 281375-R, 281385-R, 281389-R, 281394-R, 281398-R, 281405-R, 281407-R, 281409-R, 281410-R, 281416-R, 281419-R through 281423-R, 281427-R, 281428-R, 281433-R, 281435-R, 281436-R, 281438-R, 281440-R, 281444-R through 281446-R, 281457-R, 281459-R through 281461-R, 281463-R, 281464-R, 281472-R, 281476-R, 281479-R, 281494-R, 285002-R, and 285005-R; Factory Overhauled O-200A: 242663-H, 252848-H, 254252-H, 255170-H, 255210-H, and 255984-H; Rebuilt O-300A: 16107D-R and 16108D-R; Rebuilt O-300C: 230815-R; Rebuilt O-300D: 25356-R, 25363-R, 25622D-R, 29680-R, 29723-R, 35774-R, 35977-R, and 35978-R; Factory Overhauled O-300D: 27903-H, 29712-H, and 29899-H. These engines are installed on but not limited to: Aeronca Models 15AC and S15AC; American Champion (Bellanca) Models 7ECA and 402; Cessna 150, 170, and 172 series; Maule Models Bee Dee M-4, M-4, M-4C, M-4S, and M-4T; and Taylorcraft Model F-19 aircraft. Compliance: Required prior to further flight, unless accomplished previously. To prevent engine failure from an incorrect connecting rod, accomplish the following: (a) For engines that have less than 100 hours time in service (TIS), or unknown TIS, on the effective date of the AD since new, rebuild, or factory overhaul, accomplish the following: (1) With the engine cold, remove the engine cowling, ground both magnetos, and remove the top spark plugs. (2) Taking each cylinder in turn: (i) Position each piston at about 60 degrees before top dead center. (ii) Insert a small brass rod into the spark plug bore until contact with the top of the piston is achieved. (iii) Holding the brass rod against the top of the piston, move the propeller back and forth about 30 degrees in a rocking motion to move the crankshaft. (iv) By observing the brass rod move, ascertain that piston movement responds immediately and synchronously to connecting rod/crankshaft movement; that is, the brass rod must move immediately upon moving the crankshaft. (v) While checking for synchronous movement between the piston and the crankshaft, there must be no audible indication of differential movement between the piston and the connecting rod/crankshaft. (3) If for any cylinder, piston movement does not respond immediately and synchronously to crankshaft movement, or if there is an audible indication of differential movement between the piston and the connecting rod/crankshaft, replace the connecting rod with the correct serviceable part for that model engine, and inspect for serviceability, and replace as necessary, other applicable engine parts. (b) For engines that have 100 hours or more TIS on the effective date of this AD, since new, rebuild, or factory overhaul, no inspection is required. (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, Atlanta Aircraft Certification Office. The request should be forwarded through an appropriate FAA Maintenance Inspector, who may add comments and then send it to the Manager, Atlanta Aircraft Certification Office. NOTE: Information concerning the existence of approved alternative methods of compliance with this airworthiness directive, if any, may be obtained from the Atlanta Aircraft Certification Office. (d) This amendment becomes effective July 13, 1993, to all persons except those persons to whom itwas made immediately effective by priority letter AD 93-11-03, issued June 1, 1993, which contained the requirements of this amendment.
91-05-13: 91-05-13 BOEING OF CANADA, LTD., DE HAVILLAND DIVISION: Amendment 39- 6910. Docket No. 90-NM-243-AD. Applicability: de Havilland Model DHC-7 series airplanes, Serial Numbers 3 through 36, inclusive, certificated in any category. Compliance: Required as indicated, unless previously accomplished. To prevent possible malfunction of the wing flight spoilers, accomplish the following: A. Within 180 days after the effective date of this AD, replace the outboard (Modification Nos. 7/1927 and 7/1951) and inboard (Modification Nos. 7/1928 and 7/1952), right and left wing flight spoilers spigot fittings, in accordance with the Accomplishment Instructions in de Havilland Service Bulletins 7-27-25, Revision B, and 7-27-26, Revision B, both dated January 28, 1983. 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, New York Aircraft Certification Office (ACO), ANE-170, FAA, New England Region. NOTE: The request should be submitted directly to the Manager, New York ACO, ANE-170, and a copy sent to the cognizant FAA Principal Inspector (PI). The PI will then forward comments or concurrence to the Manager, New York ACO, ANE-170. 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 documents from the manufacturer may obtain copies upon request to Boeing of Canada, Ltd., de Havilland Division, Garratt Boulevard, Downsview, Ontario M3K 1YK, Canada. These documents may be examined at the FAA, Northwest Mountain Region, Transport Airplane Directorate, 1601 Lind Avenue S.W., Renton, Washington; or at the FAA, New England Region, New York Aircraft Certification Office, 181 South Franklin Avenue, Valley Stream, New York. Thisamendment (39-6910, AD 91-05-13) becomes effective on March 29, 1991.
95-12-22: This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A340 series airplanes. This action requires installation of a reinforcement modification on the structure of the left- and right-hand cowls of the thrust reversers. This amendment is prompted by the results of a full-scale fatigue test, conducted by the manufacturer, which indicated that fatigue cracks can occur between the 3 and 9 o'clock thrust reverser beams and the forward frame/"J"-ring. The actions specified in this AD are intended to prevent loss of the use of the thrust reversers as a result of the problems associated with fatigue cracking in their cowling structure.