Results
53-08-02: 53-08-02 DOUGLAS: Applies to All Model DC-6 Series Aircraft (Fuselage Numbers 1 to 213 Inclusive). \n\n\tCompliance required as indicated. \n\n\tThe following inspections and rework pertain to the center wing lower skin panel and stringers inboard of Station 60 at both sides of the two access doors (fore and aft). The accomplishment of this change is for repair of details which have failed due to fatigue and to make general reinforcement of the affected area. \n\n\t1.\tInspection. \n\n\t\t(a)\tConduct following inspection as soon as practical but not later than the next 50 hours of operation unless already accomplished and continuing thereafter at periodic intervals nearest to 500 flying hours from the time of initial inspection until permanent rework is accomplished as outlined in items (2) and (3). Using at least an 8-power magnifying glass and/or dye check method or equivalent, make inspection for cracks in the door doubler, bottom wing skin and stringers in the area of Station 52 between the front and center spars. If cracks are found in any of these details, make repairs as indicated in item 2 before next scheduled flight. \n\n\t\t(b)\tIf no cracks are found in any of the details mentioned in 1(a) install preventive reinforcements as outlined in item 3. \n\n\t2.\tRepair. \n\n\t\t(a)\tIf a crack is found in the lower skin panel at Station 52 greater than 2 1/2 inches long or if cracked stringers are found in the area of Station 52, make repair and modify the door doubler splice as per Douglas Drawing 5460214. (Refer to Kit A of Douglas Service Bulletin No. 521.) \n\n\tNOTE: This repair must be supplemented by reinforcing remaining areas of rework as outlined in part 3(c). \n\n\t\t(b)\tIf a crack is found in the skin less than 2 1/2 inches long (without stringers being cracked), in the area of Station 52, make repair as per Douglas Drawing 5460328-501. (Refer to Kit F of Douglas Service Bulletin No. 521.) \n\n\tNOTE: This repair must be supplemented by reinforcing remaining areas of rework as outlined in part 3(c). \n\n\t\t(c)\tIf a crack is found in the door doubler only in the area of Station 52, repair per Douglas Drawing 5460328-1. (Refer to Kit E of Douglas Service Bulletin No. 521.) \n\n\tNOTE: This repair must be supplemented by reinforcing remaining areas of rework as outlined in part 3(c). \n\n\t3.\tPreventive Reinforcement. \n\n\t\t(a)\tIf no cracks are found in the area of Station 52 on airplane fuselage Nos. 1-69 install reinforcements to the stringers and door doubler no later than May 1, 1953, as per Drawing 5460275-1 or Douglas Service Bulletin No. 440. (Refer to Kit B of Douglas Service Bulletin No. 521.) \n\n\t\t(b)\tIf no cracks are found in the area of Station 52 on airplane fuselage Nos. 70-213, install reinforcement to the door doubler as per Drawing 5460275-501 no later than September 1, 1953. (Refer to Kits C and D of Douglas Service Bulletin No. 521.) \n\n\t\t(c)\tIf cracks are found by inspection and repaired by reinforcements as outlinedin part 2(a), (b) or (c), these repairs must be supplemented by reinforcing the stringers and/or door doublers at all other areas outlined in 3(a) and (b). This should be accomplished no later than May 1, 1953, on airplanes having fuselage Numbers 1 through 69 and no later than September 1, 1953, or a period not to exceed 1,500 flying hours (whichever occurs first), on airplanes having fuselage numbers 70 to 213 inclusive. Airplanes incorporating local reinforcements shall be given an external inspection at periods not to exceed 35 flying hours in addition to the 500-hour inspection outlined in part 1 (a) until the complete rework has been accomplished. \n\n\t(See Douglas Service Bulletin No. 521 dated May 29, 1952, and Douglas Service Letter No. 128 dated June 27, 1952, for applicable models subject to the above-mentioned reworks.) \n\n\tThis supersedes AD 52-27-01.
2012-26-07: We are adopting a new airworthiness directive (AD) for Eurocopter France (Eurocopter) Model AS350BA helicopters with certain AERAZUR emergency flotation gear container assemblies installed. This AD requires replacing each affected emergency flotation gear container assembly (container assembly) at specified time limits based on the date of manufacture. This AD was prompted because container assemblies with an intended operating limitation of 10 years may not have been replaced because the limit is no longer recorded in the Maintenance Program. The actions of this AD are intended to prevent failure of the emergency container assembly because of age and subsequent damage to the helicopter and injury to the occupants after an emergency water landing.
2004-13-15: This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 747-400 and -400D series airplanes, that requires an inspection to detect missing fasteners in the section 42 skin and internal doubler at the cutout for the ground exhaust valve of the electrical equipment; modification and rework of the doubler; repetitive inspections of the skin for cracks; and corrective actions if necessary; as applicable. This action is necessary to detect and correct fatigue cracks in the section 42 skin at the cutout for the ground exhaust valve of the electrical equipment, which could result in rapid decompression of the airplane. This action is intended to address the identified unsafe condition.
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.