Results
96-24-07: This amendment adopts a new airworthiness directive (AD) that applies to certain HOAC Austria Model DV-20 Katana airplanes. This action requires replacing the muffler with one of improved design, installing a heat shield around the exhaust system endpipe, and adjusting the airplane weight and balance. This AD results from reports of cracks in the welding joint that connects the exhaust system endpipe to the muffler on three of the affected airplanes. The actions specified by this AD are intended to prevent separation of the exhaust system endpipe from the muffler because of cracks in the welding that connects these parts, which could result in heat damage to the electrical system and engine controls.
79-19-02: 79-19-02 MCDONNELL DOUGLAS: Amendment 39-3555. Applies to certain Model DC-9 series airplanes, certificated in all categories, including Military Type C-9A, C-9B and VC-9C, serial numbers corresponding to fuselage numbers 1 through 839 as identified in McDonnell Douglas Service Bulletin 55-28, Revision 4, dated May 18, 1979. \n\n\tCompliance required within the next 3400 hours' time-in-service unless already accomplished within the past 200 hours' time-in-service, and thereafter at intervals not to exceed 3600 hours' time-in-service, on all airplanes with over 5000 hours' time-in-service as of, and after, February 13, 1978. Accomplishment of superseded AD 78-01-12 may be credited as accomplishment of this AD until the effective date of this AD. \n\n\t(a)\tPerform an X-ray inspection of the elevator spars, P/N 9918450-1 or -501 in accordance with instructions contained in paragraph 2 of McDonnell Douglas DC-9 Service Bulletin 55-28, Revision 4, dated May 18, 1979. \n\n\t(b)\tCracked parts found during any of the inspections of paragraph (a) which do not exceed the crack limits and McDonnell Douglas DC-9 Service Bulletin 55-28, Revision 4, dated May 18, 1979 may be continued in service. However, in addition to the 3600 hour repetitive general inspection requirements of paragraph (a), the area 12 inches inboard and outboard of all cracks must be X-ray or dye penetrant inspected at intervals not to exceed the following: \n\n\t\t(1)\tLength of longest crack up to 2 inches - 800 hours' time-in-service. \n\n\t\t(2)\tLength of longest crack between 2 and 4 inches - 400 hours' time-in-service. \n\n\t(c)\tIf cracks are found during any reinspections of paragraphs (a) or (b) which exceed the crack limits of McDonnell Douglas DC-9 Service Bulletin 55-28, Revision 4, dated May 18, 1979, the cracked spar must be repaired or replaced before further flight. If the cracked spar is repaired per McDonnell Douglas Service Sketch 27378, the inspection procedures in paragraph (a) of this AD must be accomplished within 1800 hours' time-in-service after the repair and at intervals of 1800 hours' time-in-service thereafter. \n\n\t(d)\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 required by this AD. \n\n\t(e)\tIf the original 7075-T651 spars (P/N 9918450-1 or -501) are replaced with 7075-T7351 spars (P/N 9918450-503), the inspection requirements of this AD will not apply to that airplane. \n\n\t(f)\tAlternative inspections, modifications or other actions which provide an equivalent level of safety may be used when approved by the Chief, Aircraft Engineering Division, FAA Western Region. \n\n\t(g)\tUpon request of operator, an FAA maintenance inspector, subject to prior approval of the Chief, Aircraft Engineering Division, FAA Western Region may adjust the initial and repetitive inspection intervals specified in this AD to permit compliance at an established inspection period of the operator if the request contains substantiating data to justify the increase for that operator. \n\n\tThis supersedes AD 78-01-12, Amendment 39-3119. \n\n\tThis amendment becomes effective September 13, 1979.
2011-16-06: We are adopting a new airworthiness directive (AD) for the products listed above. This AD requires a general visual inspection for cracks and holes of the main equipment center (MEC) drip shields, and repairs if necessary; installation of a fiberglass reinforcing overcoat; and, for certain airplanes, installation of stiffening panels to the MEC drip shields. This AD was prompted by a report of a loss of bus control unit number 1 and generator control units numbers 1 and 2 while the airplane was on the ground, and multiple operator reports of cracked \n\n((Page 47428)) \n\nMEC drip shields. We are issuing this AD to prevent water penetration into the MEC, which could result in the loss of flight critical systems.
95-26-15 R1: This amendment revises an existing airworthiness directive (AD), applicable to various transport category airplanes equipped with Allied Signal Commercial Avionics Systems CAS-81 TCAS, that currently requires a revision to the Airplane Flight Manual (AFM) to provide the flightcrew with procedures to cycle power to the TCAS processor via the circuit breaker or power bus, and to perform a TCAS functional test to verify proper operation of the TCAS. That AD was prompted by reports of failure of the audio output of the CAS-81 TCAS. The actions specified by that AD are intended to ensure that the flightcrew is advised of the potential hazard associated with failure of the audio output of the CAS-81 TCAS, and of the procedures necessary to address it. This amendment adds a revision of the AFM requirements that provides an alternative method of compliance with the currently required AFM revision; and provides for a modification to the TCAS processor, which, if accomplished, terminates the requirements of the AD.
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.