Results
90-19-12: 90-19-12 MCDONNELL DOUGLAS: Amendment 39-6735. Docket No. 90-NM-170-AD. \n\n\tApplicability: McDonnell Douglas Model DC-10 series airplanes, manufacturer's fuselage numbers 1 through 379, certificated in any category. \n\n\tCompliance: Required as indicated. To prevent inadvertent opening of a cargo door in flight, a condition which could result in loss of pressurization and control of the aircraft, accomplish the following: \n\n\tA.\tExcept as provided in paragraph B. of this AD, within 30 calendar days after the effective date of this AD, unless previously accomplished within the last 60 days, remove sealant in accordance with Figure 1, Step 2, and perform the torque test on the cargo door latch spool fitting attach bolts, in accordance with the Accomplishment Instructions for Group 1, Phase 1, of McDonnell Douglas DC-10 Service Bulletin 52-183, Revision 2, dated April 15, 1981 (hereafter referred to as the Service Bulletin). \n\n\tNOTE: The requirements of this AD are applicableto Model DC-10 series airplanes, manufacturers's fuselage numbers 1 through 379, regardless of the effectivity as specified in the McDonnell Douglas Service Bulletin. \n\n\t\t1.\tIf a bolt breaks, prior to further flight, replace it with a new bolt and seal in accordance with Figure 1 of the Service Bulletin. \n\n\t\t2.\tIf a bolt passes the torque test, prior to further flight, retorque the bolt and seal in accordance with the Accomplishment Instructions for Group 1, Phase 1, of the Service Bulletin. \n\n\tB.\tThe test required by paragraph A. of this AD is not required for Inconel bolts, part numbers RA21026-7, 77711-7, and 3D0031-7 (grip lengths as applicable per location as specified in Figure 1, sheets 3 and 4, of the Service Bulletin). \n\n\tC.\tSpecial flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes unpressurized to a base for the accomplishment of the requirements of this AD. \n\n\tD.\tAn 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, Los Angeles Aircraft Certification Office (ACO), FAA, Transport Airplane Directorate. \n\n\tNOTE: The request should be submitted directly to the Manager, Los Angeles ACO, and a copy sent to the cognizant FAA Principal Inspector (PI). The PI will then forward comments or concurrence to the Los Angeles ACO. \n\n\tAll persons affected by this directive who have not already received the appropriate service information from the manufacturer may obtain copies upon request to McDonnell Douglas Corporation, P. O. Box 1771, Long Beach, California 90846-0001, Attention: Business Unit Manager, Technical Publications, C1-HDR (54-60). These documents may be examined at the FAA, Northwest Mountain Region, Transport Airplane Directorate, 1601 Lind Avenue S.W., Renton, Washington, or the Los Angeles Aircraft Certification Office, 3229 East Spring Street, Long Beach, California. \n\n\tThis amendment (39-6735, AD 90-19-12) becomes effective on October 1, 1990.
87-04-08: 87-04-08 MCDONNELL DOUGLAS: Amendment 39-5537. Applies to McDonnell Douglas Model DC-9-80 (MD-80) series airplanes, certificated in any category, equipped with Pratt and Whitney (P&W) JT8D-209, -217, or -217A engines, listed in P&W Service Bulletin (S/B) 5618, dated November 26, 1985. Compliance required as indicated, unless previously accomplished. \n\n\tTo prevent 5th stage compressor blade failure from flutter and the possibility of engine power loss, accomplish the following within 30 calendar days after the effective date of this airworthiness directive: \n\n\tA.\tRevise the McDonnell Douglas DC-9-80 FAA approved Airplane Flight Manual (AFM) Report MDC-J8480 (English) or MDC-J8480M (Metric) to add the following: \n\n\tSECTION 1 - LIMITATIONS \n\n\t\t1.\tThe engine and airplane performance limitations presented in the AFM Report MDC-J8480, Appendix 10, FAA-approved November 26, 1986, or later FAA-approved revisions, must be observed. \n\n\t\t2.\tThe Engine Pressure Ratio (EPR) Indicating System for each engine must have the pointer, digital counter, and maximum limit chevron operative prior to takeoff. \n\n\tNOTE: The McDonnell Douglas DC-9 Master Minimum Equipment List (MMEL) Revision No. 21, dated November 1, 1984, and subsequent revisions, Page 77-1, Item 77-1, Engine Pressure Ratio Indicating System (with Pointer AND Digital Counter) (Series 80) and Maximum Limit Chevrons (Series 80) is affected by the above AFM Limitations, which take precedence over the MMEL. \n\n\tB.\tTerminating action for this AD is the installation of the modified blades P/N 804505 in accordance with P&W Service Bulletin (S/B) 5618, dated November 26, 1985, or later FAA-approved revisions, or other equivalent FAA-approved 5th stage blades. \n\n\tC.\tA copy of this AD inserted in the FAA approved AFM may be considered as an acceptable means of compliance with the required AFM revisions. \n\n\tD.\tSpecial flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes toa base in order to comply with the requirements of this AD. \n\n\tE.\tAlternate 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. \n\n\tAll persons affected by this directive who have not already received the appropriate service documents from the manufacturer may obtain copies upon request to McDonnell Douglas Corporation, 3855 Lakewood Boulevard, Long Beach, California 90846, Attention: Director, Publications and Training, C1-750 (54-60). These documents may be examined at FAA, Northwest Mountain Region, 17900 Pacific Highway South, Seattle, Washington, or at 4344 Donald Douglas Drive, Long Beach, California 90808. \n\n\tThis amendment becomes effective March 9, 1987.
92-08-12: 92-08-12 BOEING: Amendment 39-8223. Docket No. 91-NM-95-AD.\n\n\tApplicability: Model 747-400 series airplanes, up to and including line position 839, certificated in any category.\n\n\tCompliance: Required within the next 24 months after the effective date of this AD, unless accomplished previously.\n\n\tTo preclude cross connection of cargo compartment and engine fire protection wiring and plumbing during maintenance, accomplish the following:\n\n\t(a)\tFor airplanes identified in Boeing Service Bulletin 747-26-2143, Revision 1, dated August 15, 1991: Modify the cargo compartment fire extinguishing system plumbing and wiring in accordance with that service bulletin.\n\n\t(b)\tFor airplanes identified in Boeing Service Bulletin 747-26-2164, dated February 14, 1991: Modify the engine fire control module in accordance with that service bulletin.\n\n\t(c)\tFor airplanes identified in Boeing Service Bulletin 747-26-2168, dated March 28, 1991: Modify the cargo compartment smoke detectionsystem wiring in accordance with that service bulletin.\n\n\t(d)\tAn 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, Seattle Aircraft Certification Office (ACO), FAA, Transport Airplane Directorate. The request shall be forwarded through an FAA Principal Maintenance Inspector, who may concur or comment and then send it to the Manager, Seattle ACO.\n\n\t(e)\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(f)\tThe modifications shall be done in accordance with Boeing Service Bulletin 747-26-2164, dated February 14, 1991; Boeing Service Bulletin 747-26-2168, dated March 28, 1991; and Boeing Service Bulletin 747-26-2143, Revision 1, dated August 15, 1991, which includes the following list of effective pages:\n \n \tPage Number\tRevision Level\tDate\n\t1, 3-8, 18-20, 33, 45-50,\t1\tAugust 15, 1991\n\t54, 61-62, 64-87\n\n\t2, 9-17, 21-32, 34-44,\t(original)\tDecember 20, \t51-53, 55-60, 63\t\t1990\n\t\n\nThis 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 Boeing Commercial Airplane Group, P.O. Box 3707, Seattle, Washington 98124. Copies may be inspected at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, Washington; or at the Office of the Federal Register, 1100 L Street NW., Room 8401, Washington, DC.\n\n\t(g)\tThis amendment becomes effective on May 29, 1992.
98-15-21: This amendment supersedes an existing airworthiness directive (AD), applicable to certain Boeing Model 747-100 series airplanes, that currently requires repetitive inspections to detect cracking of the wing front spar web above engine numbers 2 and 3, and to detect cracked or broken fasteners in the web; and repair, if necessary. That AD also provides an optional terminating action for the repetitive inspections. This amendment requires various improved inspections. This amendment is prompted by a report indicating that the existing inspections do not adequately detect vertical cracks. The actions specified by this AD are intended to prevent fuel leakage onto an engine and a resultant fire due to cracked or broken fasteners in the wing front spar.
82-18-51: 82-18-51 MCDONNELL DOUGLAS: Amendment 39-4499. Applies to McDonnell Douglas Model DC-8-70 series airplanes with P/N 3505154-18-1 series Airesearch engine starters installed, certificated in all categories. Compliance required within 20 flight hours after receipt of this AD, and at intervals not to exceed 20 flight hours thereafter. \n\n\tTo detect starter output shaft bearing distress, accomplish the following, unless already accomplished: \n\n\tA)\tRemove the magnetic portion (knurled knob, bayonet type, quick disconnect) of each starter drain plug and check for the presence of metallic particles. The following action shall be taken when the degree of contamination has been determined: \n\n\t\t1)\tA plug that is clean or having light fuzz is normal and acceptable. Clean plug as necessary, reinstall, and continue starter operation. \n\n\t\t2)\tIf light metal particle accumulation is observed on the magnetic portion of the plug, drain the starter oil and observe color and odor of the oil. \n\n\t\t\ta)\tIf the oil is transparent, reservice the starter with clean oil, clean the drain plug, reinstall, and continue starter operation. If metal is again observed at any subsequent inspection, replace the starter with a serviceable unit. \n\n\t\t\tb)\tIf the oil is black, or has a burnt smell, replace the starter with a serviceable unit. \n\n\t\t3)\tIf metal accumulation in excess of that defined in 2), above, is observed on the magnetic portion of the drain plug, replace the starter with a serviceable unit. \n\n\tB)\tWhen a P/N 3505154-19-1 series or subsequent approved P/N starter is installed, inspection per this AD is terminated. \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 repairs required for the purposes of this AD when approved by the Manager, Los Angeles Aircraft Certification Office, FAA, Northwest Mountain Region. \n\n\tD)\tAlternate means of compliance which providean equivalent level of safety may be used when approved by the Manager, Los Angeles Aircraft Certification Office, FAA, Northwest Mountain Region. \n\n\tThis amendment becomes effective November 23, 1982, and was effective earlier to those recipients of Telegraphic AD T82-18-51 dated August 31, 1982.
90-26-04: 90-26-04 BOEING: Amendment 39-6830. Docket No. 90-NM-135-AD. \n\n\tApplicability: Model 747 series airplanes, line numbers 1 through 39, certificated in any category. \n\n\tCompliance: Required within the next 4,500 hours time-in-service after the effective date of this AD, unless previously accomplished. \n\n\tTo prevent the loss of the airplane primary flight controls due to loss of hydraulic fluid from all four hydraulic systems, accomplish the following: \n\n\tA.\tModify the hydraulic lines in the elevator control system in accordance with Section III of the Accomplishment Instructions, Steps G through H, of Boeing Alert Service Bulletin 747-29A2063, Revision 5, dated June 7, 1990. \n\n\tB.\tAn 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, Seattle Aircraft Certification Office (ACO), FAA, Transport Airplane Directorate. \n\n\tNOTE: The request should be submitted directly to the Manager, Seattle ACO, and a copy sent to the cognizant FAA Principal Inspector (PI). The PI will then forward comments or concurrence to the Seattle ACO. \n\n\tC.\tSpecial 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. \n\n\tAll persons affected by this directive who have not already received the appropriate service documents from the manufacturer may obtain copies upon request to Boeing Commercial Airplane Group, P.O. Box 3707, Seattle, Washington 98124. These documents may be examined at the FAA, Northwest Mountain Region, Transport Airplane Directorate, 1601 Lind Avenue S.W., Renton, Washington. \n\n\tThis amendment (39-6830, AD 90-26-04) becomes effective on January 15, 1991.
2012-26-03: We are adopting a new airworthiness directive (AD) for certain Airbus Model A330-202, -203, -223, -243, -302, -323, -342, and -343 airplanes; and Model A340-313 airplanes. This AD was prompted by reports that a specific batch of cargo doors might have deviations in quality related to door structure, such as irregular bore holes, improper application of sealant and paint, or uncleanliness. This AD requires inspecting to identify the part and serial numbers of the forward and aft cargo doors, and replacing the affected cargo doors. We are issuing this AD to prevent the degraded structural capability of the cargo door, a primary structure, from leading to failure of the door, which could lead to a breach through the door or the door detaching from the airplane, resulting in potential rapid decompression.
2010-11-10: We are adopting a new airworthiness directive (AD) for the products listed above. This AD results from mandatory continuing airworthiness information (MCAI) issued 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: Investigation of an uncommanded in-flight shutdown (IFSD) revealed that a third stage turbine wheel rupture was not contained by the turbine casings. The released portion consisted of a turbine blade together with the rim piece immediately below the blade. The rim piece was bounded by two adjacent axial slots and a fatigue crack that had developed between the holes in which the slots terminate. The slots and holes, which are closed by riveted plugs, were introduced by modification AB 173 in order to improve the vibration characteristics of the turbine wheel. Modification AB 208 brings an improvement to modification AB 173 by changing only the riveting detail. SN 283 72 0805 provides instructions for re-boring the holes at overhaul or repair in order to improve their surface condition. A manufacturing process modification has been introduced to improve the surface condition of these holes in third stage turbine wheels. Wheels subject to the improved manufacturing process have S/Ns outside the range specified in Table 1. Although there is only one known event, and although it resulted only in an uncommanded IFSD, with no damage to the aircraft, the possibility exists that additional events may occur, potentially involving damage to the aircraft. We are issuing this AD to prevent uncontained failures of the third stage turbine wheel, which could result in damage to the helicopter.
98-15-20: This amendment adopts a new airworthiness directive (AD) that applies to all Glaser-Dirks Flugzeugbau GmbH (Glaser-Dirks) Model DG-500M gliders. This AD requires inspecting the center of gravity (C.G.) tow release cable pulley for correct positioning, and replacing the C.G. tow release cable pulley with one made of aluminum either immediately or eventually depending on the results of the inspection. This AD is the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for Germany. The actions specified by this AD are intended to prevent the C.G. tow release cable from coming off the pulley because of incorrect positioning, which could result in the pilot being unable to release from tow operations.
98-15-19: This amendment adopts a new airworthiness directive (AD) that applies to certain Aeromot-Industria Mecanico Metalurgica Ltda. (Aeromot) Model AMT-200 powered gliders. This AD requires replacing certain flexible hoses in the engine oil system with flexible hoses with a larger internal diameter. This AD is the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for Brazil. The actions specified by this AD are intended to prevent inefficiency of the engine lubricating system because of ineffective flexible hoses, which could result in an in-flight engine shutdown with consequent loss of powered glider controllability.