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92-23-02: 92-23-02 MCDONNELL DOUGLAS: Amendment 39-8402. Docket No. 92-NM-92-AD. \n\n\tApplicability: Model MD-11 series airplanes; operating in an all-passenger configuration, or in any combination of passenger and main deck cargo configurations; certificated in any category. \n\n\tCompliance: Required as indicated, unless accomplished previously. \n\n\tNOTE: Model MD-11 series airplanes that are operated as freighters may continue to use the unmodified slides at door number 1. However, should any of these airplanes be converted to an all-passenger configuration, or any combination of passenger and main deck cargo configurations, the requirements of this AD must be accomplished. \n\n\tTo prevent buckling of the evacuation slides/rafts and poor visibility during night lighting conditions, which could delay or impede the evacuation of passengers during an emergency, accomplish the following: \n\n\t(a)\tFor Model MD-11 series airplanes with interior passenger seating configurations not exceeding306, and the number of passenger seats in the zone between doors 3 and 4 not exceeding 165: Within 12 months after the effective date of this AD, replace existing evacuation slides/rafts with modified slides/rafts, part numbers 60289-115 or -117; 60290-115; 60291-115; and 60291-116; in accordance with the Accomplishment Instructions of McDonnell Douglas Service Bulletin 25-87, dated January 23, 1992; and McDonnell Douglas Service Bulletin 25-116, Revision 1, dated May 15, 1992. \n\n\t(b)\tFor Model MD-11 series airplanes with interior passenger seating configurations from 307 to 381, inclusive, and the number of passenger seats in the zone between doors 3 and 4 not exceeding 165: Within 6 months after the effective date of this AD, replace existing evacuation slides/rafts with modified slides/rafts, part numbers 60289-115 or -117; 60290-115; 60291-115; and 60291-116; in accordance with the Accomplishment Instructions of McDonnell Douglas Service Bulletin 25-116, Revision 1, dated May 15, 1992. \n\n\t(c)\tFor Model MD-11 series airplanes with interior passenger seating configurations not exceeding 381, and more than 165 passenger seats in the zone between doors 3 and 4: Within 3 months after the effective date of this AD, replace existing evacuation slides/rafts with modified slides/rafts, part numbers 60289-115 or -117; 60290-115; 60291-115; and 60291-116; in accordance with the Accomplishment Instructions of McDonnell Douglas Service Bulletin 25-87, dated January 23, 1992; and McDonnell Douglas Service Bulletin 25-116, Revision 1, dated May 15, 1992. \n\n\t(d)\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, Los Angeles ACO.NOTE: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Los Angeles 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 replacement shall be done in accordance with McDonnell Douglas Service Bulletin 25-87, dated January 23, 1992; and McDonnell Douglas Service Bulletin 25-116, Revision 1, dated May 15, 1992. 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 McDonnell Douglas Corporation, P.O. Box 1771, Long Beach, California 90846-0001, 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 the FAA, Los Angeles Aircraft Certification Office (ACO), 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(g)\tThis amendment becomes effective on November 25, 1992.
91-18-18: 91-18-18 MCDONNELL DOUGLAS: Amendment 39-8021. Docket No. 91-NM-175-AD. \n\n\tApplicability: Model DC-9-10, -20, -30, -40, -50, and C-9 (Military) series airplanes, certificated in any category. \n\n\tCompliance: Required as indicated, unless previously accomplished. \n\n\tTo prevent rapid decompression of the pressurized fuselage, accomplish the following: \n\n\t(a)\tFor airplanes that have accumulated 55,000 landings or more as of the effective date of this AD, within 15 calendar days after the effective date of this AD, and thereafter at intervals not to exceed 1,500 landings, perform high frequency eddy current (HFEC) inspections to detect cracks of the fuselage left-hand skin panel at longeron 22L, between stations 160 and 200, in accordance with McDonnell Douglas Alert Service Bulletin A53-251, dated August 9, 1991. \n\n\t(b)\tFor airplanes that have accumulated less than 55,000 landings as of the effective date of this AD, within 45 calendar days after the effective date of this AD, or prior to the accumulation of 40,000 landings, whichever occurs later, and thereafter at intervals not to exceed 1,500 landings, perform high frequency eddy current (HFEC) inspections to detect cracks of the fuselage left-hand skin panel at longeron 22L, between stations 160 and 200, in accordance with McDonnell Douglas Alert Service Bulletin A53-251, dated August 9, 1991. \n\n\t(c)\tIf the fuselage skin attachments are obscured from exterior coatings of paint, prior to the accomplishment of the high frequency eddy current (HFEC) inspections required by paragraph (a) or (b) of this AD, chemically remove the obscuring coatings of paint. \n\n\t(d)\tIf cracks are found as a result of the inspections required by paragraph (a) or (b) of this AD, before further flight, repair in a manner approved by the Manager of the Los Angeles Aircraft Certification Office (ACO). \n\n\t(e)\tWithin 10 calendar days after the accomplishment of the initial inspections required by paragraph (a) or (b) of thisAD, submit a report of both positive and negative findings of the initial inspection to the Manager of the Los Angeles Aircraft Certification Office (ACO), FAA, Transport Airplane Directorate, at 3229 East Spring Street, Long Beach, California 90806-2425, or Fax to (213) 988-5210. The information collection requirements contained in this regulation have been approved by the Office of Management and Budget (OMB) under the provisions of the Paperwork Reduction Act of 1980 (P.L. 96-511) and have been assigned OMB Control Number 2120-0056. \n\n\t(f)\tIf other cracks, as specified in McDonnell Douglas Alert Service Bulletin A53-251, dated August 9, 1991, are found on any adjacent longerons or fuselage skin panels as a result of any other inspection of those areas, within 10 calendar days after those inspections, report all positive findings to the Manager of the Los Angeles ACO. The information collection requirements contained in this regulation have been approved by the Office of Management and Budget (OMB) under the provisions of the Paperwork Reduction Act of 1980 (P.L. 96-511) and have been assigned OMB Control Number 2120-0056. \n\n\t(g)\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, Los Angeles Aircraft Certification Office (ACO), FAA, Transport Airplane Directorate. \n\n\tNOTE: The request should be forwarded through an FAA Principal Maintenance Inspector, who may concur or comment and then send it to the Manager, Los Angeles ACO. \n\n\t(h)\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\t(i)\tThe inspection requirements shall be done in accordance with McDonnell Douglas Alert Service Bulletin A53-251, dated August 9, 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 McDonnell Douglas Corporation, P. O. Box 1771, Long Beach, California 90846-0001, Attention: Business Unit Manager, Technical Publications, C1-HDR (54-60). Copies may be inspected at the FAA, Northwest Mountain Region, Transport Airplane Directorate, 1601 Lind Avenue S.W., Renton, Washington, or at the Los Angeles Aircraft Certification Office, 3229 East Spring Street, Long Beach, California, or at the Office of the Federal Register, 1100 L Street N.W., Room 8401, Washington, D.C. \n\n\tThis amendment (39-8021, AD 91-18-18) becomes effective on August 21, 1991.
58-23-02: 58-23-02 DOUGLAS: Applies to All Model DC-6 Series Aircraft Prior to Fuselage Number 221, Except Number 214. \n\n\tCompliance required as indicated. \n\n\tNumerous cases have been reported wherein cracks have occurred in the vertical stabilizer front spar fittings, P/N 3344473, at Station 1033 bulkhead. Unless already accomplished, the following inspection must be made on all DC-6 Series airplanes indicated above which have in excess of 10,000 hours total flight time: \n\n\t1.\tWithin the next 25 hours flying time, inspect the above fittings for cracks occurring through the stabilizer attachment bolt holes and boss of the fitting and which propagate into either or both longitudinal flanges of the part. Cracks in one leg only should not exceed 3 1/2 inches in length. Cracks in both legs should not exceed 2 inches each. Cracks shall not be less than 3/4 inch from the edge of the leg and their length should be measured from the face of the counter bore on the lower side of the stabilizer attach bolt hole. \n\n\t2.\tIf cracks do not exceed the above limits, the parts may be continued in service for a maximum of 150 hours of flying time before replacement with the new part P/N 3406332, provided they are: (1) Stop drilled using a No. 10 drill and, (2) they are inspected at periods not to exceed 25 hours of flying time. \n\n\t3.\tFittings having cracks in excess of the above limits or cracks which extend across the leg of the fitting, must be replaced with new part, P/N 3406332, prior to next flight. \n\n\t4.\tFittings found to have no cracks at the time of inspection, per 1. must be accorded a repetitive inspection at each block overhaul period or at periods not to exceed 3,500 hours, until new fitting, P/N 3406332, is installed. \n\n\t(Douglas Alert Service Bulletin No. A-796, dated August 15, 1958, and Service Bulletin No. 796, dated September 2, 1958, cover this same subject.)
2009-04-13: 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: The application of most recent 3D FEM modeling has resulted in the need to reconsider the disc lives as currently shown in the Time Limits Manual. The current Post Certification Life Statement for the low pressure (LP) compressor (fan) disc assembly revises the Declared Safe Cyclic Life (DSCL) from 33,000 flight cycles to 25,000 flight cycles for both the BR715 LP (fan) disc assembly Part No. (P/ N) BRH10048 and BR715 LP compressor (fan) disc assembly P/N BRH19253, when installed in the BR700-715A1-30 engine model and operated against the Hawaiian Flight Mission. We are issuing this AD to prevent uncontained failure of the LP compressor (fan) disc assembly and damage to the airplane.
71-03-02: 71-03-02 BOEING: Amdt. 39-1151. Applies to Model 707 and 720 series airplanes listed in Boeing Service Bulletin 3003, Revision 2, dated January 15, 1971, or later FAA approved revisions. \n\tCompliance required as indicated after the effective date of this AD. \n\tTo assure elevator aft quadrant integrity, accomplish the following inspections and rework or the equivalent inspections and rework approved by the Chief, Aircraft Engineering Division, FAA Western Region. \n\n\t(a)\tWithin the next 15 hours' time in service unless already accomplished per Telegraphic Alert Service Bulletin 3003 dated October 16, 1970, or AD 70-22-08, perform a close visual inspection of the elevator aft control quadrant hub aft flange face and central web area for corrosion and cracks per Part I of Boeing Service Bulletin 3003, Revision 2, dated January 15, 1971, or later FAA approved revisions. If cracks are found, replace quadrant per paragraph (d). \n\t(b)\tWithin the next 750 hours' time in service unlessalready accomplished, inspect the aft flange face and central web of the elevator aft quadrant for corrosion and cracks per Parts I and II of Boeing Service Bulletin 3003, Revision 2, or later FAA approved revisions. Accomplish a micrometer check of the quadrant torque tube diameter for ovalness in both the "x" and "y" axes as shown in Fig. 1 of Boeing Service Bulletin 3003, Revision 2, or later FAA approved revisions. \n\t\t(1)\tIf the torque tube is either round or oval within limits per Part II of Boeing Service Bulletin 3003, Revision 2, or later FAA approved revisions, perform periodic close visual inspections at intervals not to exceed 750 hours' time in service. On or before 1500 hours' time in service, initiate the dye penetrant or eddy current and torque check inspection program per Part III of Boeing Service Bulletin 3003, Revision 2, or later FAA approved revisions. The quadrant assembly may be retained in service under dye penetrant or eddy current inspection surveillance atintervals not to exceed 1500 hours' time in service until it is either replaced or overhauled per (c). \n\t\t(2)\tIf the torque tube exceeds the limits of ovalness specified in Part II of Boeing Service Bulletin 3003, Revision 2, or later FAA approved revisions, conduct a dye penetrant or eddy current inspection and torque check per Part IV of Boeing Service Bulletin 3003, Revision 2, or later FAA approved revisions prior to further flight. \n\t\t(3)\tIf, after performing the inspection and torque check per (2) above, the torque tube diameter difference is less than .004, the quadrant assembly may be retained in service under dye penetrant or eddy current inspection surveillance at intervals not to exceed 1500 hours' time in service until it is either replaced per (d) or overhauled per (c). \n\t\t(4)\tIf, after completing the inspection and torque check per (2) above, the torque tube dimensional difference is still greater than .004, replace the quadrant assembly per (d). \n\t(c)\tOn or before 12,000 hours' time in service unless already accomplished, overhaul or replace the quadrant assembly per Part V of Boeing Service Bulletin 3003, Revision 2, or later FAA approved revisions. \n\t(d)\tIf, as a result of any of the foregoing inspections, the quadrant assembly shows signs of cracks, or the torque tube ovalness is beyond limits after the torque check, replace the quadrant assembly prior to further flight with either an "Existing" quadrant assembly reworked in accordance with Part V of Boeing Service Bulletin 3003, Revision 2, or later FAA approved revisions, or by an "Equivalent" new quadrant assembly as identified in table II of Boeing Service Bulletin 3003, Revision 2, or later FAA approved revisions. \n\t(e)\tThe inspections required by this AD may be discontinued upon replacement of the aft quadrant assembly by an "Existing" quadrant assembly reworked in accordance with Part V of the Boeing Service Bulletin 3003, Revision 2, or later FAA approved revisions, or by an "Equivalent" new quadrant assembly as identified in table II of Boeing Service Bulletin 3003, Revision 2, or later FAA approved revisions. \n\tThis amendment supersedes Amendment 39-1101, 35 F.R. 16791, AD 70-22-08. \n\tThis amendment becomes effective February 13, 1971.
2009-18-08: The FAA is adopting a new airworthiness directive (AD) for certain Airbus Model A330-200 and -300 series airplanes, Model A340-200 and -300 series airplanes, and Model A340-541 and -642 airplanes. This AD requires replacing certain Thales Avionics pitot probes with certain other pitot probes. This AD results from reports of airspeed indication discrepancies while flying at high altitudes in inclement weather conditions. We are issuing this AD to prevent airspeed discrepancies, which could lead to disconnection of the autopilot and/or auto-thrust functions, and reversion to flight control alternate law and consequent increased pilot workload. Depending on the prevailing airplane altitude and weather, this condition, if not corrected, could result in reduced control of the airplane.
2009-03-01: We are adopting a new airworthiness directive (AD) for certain Learjet Model 55, 55B, and 55C airplanes. This AD requires inspecting the installation of the forward light assembly in the aft lavatory to determine the location of the terminal connector; inspecting for damage of the light assembly terminals, wires, and oxygen lines; inspecting to determine if the cable nipple is installed over the light assembly terminal; and doing corrective actions if necessary. This AD also requires installing a clamp to the forward side of the frame to maintain a positive distance between the light assembly and oxygen line. This AD results from a report of a cabin fire in the left-hand upper cabin fuselage above the aft cabin window at frame 23. We are issuing this AD to detect and correct improper installation of the lavatory light assembly, which could result in contact between the electrical terminals of the light assembly and an adjacent oxygen supply line, and consequent short circuit or fire hazard.
93-23-03: 93-23-03 MCDONNELL DOUGLAS: Amendment 39-8737. Docket 93-NM-39-AD. \n\n\tApplicability: Model DC-9 and Model DC-9-80 series airplanes; equipped with BFGoodrich evacuation slides, as listed in BFGoodrich Service Bulletin 4A3106/4A3153-25-258, dated March 29, 1993, having regulator part number 4A3106-1, -2, or 4A3153; certificated in any category. \n\n\tCompliance: Required as indicated, unless accomplished previously. \n\n\tTo prevent delayed inflation of the evacuation slide, which could delay or impede the evacuation of passengers during an emergency, accomplish the following: \n\n\t(a)\tWithin 12 months after the effective date of this AD, modify BFGoodrich evacuation slides having regulator part number (P/N) 4A3106-1, -2, or 4A3153, installed on forward entry/service, aft service, and tailcone exit doors, in accordance with BFGoodrich Service Bulletin 4A3106/4A3153-25-258, dated March 29, 1993. \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, Los Angeles 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 modification shall be done in accordance with BFGoodrich Service Bulletin 4A3106/4A3153-25-258, dated March 29, 1993. 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 BFGoodrich, Aircraft Evacuation Systems, 3414 South 5th Street, Phoenix, Arizona 85040. Copies may be inspected at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; or at the 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 December 22, 1993.
62-08-05: 62-08-05\tBOEING: Amdt. 422 Part 507 Federal Register April 17, 1962. Applies to All 707 and 720 Series Aircraft. \n\n\tAs a result of a recent incident involving loss of the electrical system and accumulation of dense smoke in the cockpit and cabin, the following is required: \n\n\t(a)\tUnless already accomplished in accordance with recommendations contained in the telegram dated March 23, 1962, issued by Boeing Aircraft Company, within the next 25 hours' time in service, inspect electrical components and wiring within the J6 electrical panel to determine that: \n\n\t\t(1)\tLugs and braided leads are tightly secured to the contractor studs; \n\n\t\t(2)\tBraid jumpers are adequately separated from adjacent jumpers to prevent contact; \n\n\t\t(3)\tThere is no evidence of overheating in wiring and braided leads; and \n\n\t\t(4)\tThere is no evidence of capacitor leaks, swelling or overheating. \n\n\t(b)\tIf any of the foregoing items require corrective action, repair in accordance with acceptable maintenance practices. \n\n\tThis directive effective upon publication in the Federal Register for all persons except those to whom it was made effective immediately by telegram dated March 30, 1962.
91-23-14: 91-23-14 MCDONNELL DOUGLAS: Amendment 39-8083. Docket No. 91-NM-89-AD. \n\n\tApplicability: Model DC-10-10, -10F, -15, -30, -30F, -40, -40F, and KC-10A (Military) series airplanes, certificated in any category. \n\n\tCompliance: Required as indicated, unless previously accomplished. \n\n\tTo prevent an unobserved indication that the hydraulic system number 3 shutoff valve has closed, accomplish the following: \n\n\t(a)\tWithin 6 months after the effective date of this AD, modify the Master Caution Warning System by installing a wire in accordance with paragraph 2, Accomplishment Instructions, of McDonnell Douglas DC-10 Service Bulletin 29-132, Revision 1, dated August 26, 1991. \n\n\t(b)\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, Los Angeles Aircraft Certification Office (ACO), FAA, Transport Airplane Directorate. \n\n\tNOTE: The request should be forwarded through an FAA Principal Avionics Inspector, who may concur or comment and then send it to 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 airplanes to a base in order to comply with the requirements of this AD. \n\n\t(d)\tThe modification requirements shall be done in accordance with McDonnell Douglas DC-10 Service Bulletin 29-132, Revision 1, dated August 26, 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 McDonnell Douglas Corporation, P.O. Box 1771, Long Beach, California, 90801, ATTN: Group Leader, MD-11/DC-10 and DC-8/-8, Service Change Operations, Mail Code 73-30. This information may be examined at the FAA, Northwest Mountain Region, Transport Airplane Directorate, 1601 Lind Avenue S.W., Renton, Washington, or at the Los Angeles Aircraft Certification Office, 3229 East Spring Street,Long Beach, California; or at the Office of the Federal Register, 1100 L Street N.W., Room 8401, Washington, D.C. \n\n\tThis amendment (39-8083, AD 91-23-14) becomes effective on January 9, 1992.