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68-04-01: 68-04-01 HAWKER SIDDELEY: Amdt. 39-742. Applies to Model Series DH.125-1A, -1A/R-522, -1A/522, -3A, -3A/R. Compliance required as indicated, unless already accomplished. To detect fuel leakage past the fuel filter de-icing system non-return valves, P/N A.W.E. 124-25, -26, -27, and fuel or methanol leakage from the fuel filter and windshield de-icing systems, accomplish the following: (a) Immediately prior to each flight after the effective date of this AD, check for signs of fuel leakage past the non-return valves, P/N A.W.E. 124-25, -26, or -27, and inspect for fuel or methanol leakage from the fuel filter and windshield de-icing systems in accordance with Hawker Siddeley Aviation Ltd., Service Bulletin No. 28-A23, Revision 2, dated July 4, 1968, or later ARB-approved revision, or FAA-approved equivalent. (b) Within the next 7 days after the effective date of this AD and thereafter at intervals not to exceed 7 days from the last serviceability test, accomplish a serviceability test of the fuel filter and windshield de-icing systems, in accordance with Hawker Siddeley Aviation Ltd., Service Bulletin No. 28-A23, Revision 2 dated July 4, 1968, or later ARB-approved revision, or FAA-approved equivalent. However, whenever an airplane has not been operated for a period in excess of 7 days, the serviceability test required during that period may be postponed until immediately prior to the first flight after such period. (c) If unserviceable non-return valves or leaks in the de-icing systems are found during the checks, inspections, or tests required by paragraphs (a) and (b) of this AD, before further flight, replace defective parts with serviceable parts of the same or approved equivalent part numbers, and continue the checks, inspections and tests required by paragraphs (a) and (b) of this AD. (d) The pre-flight checks and serviceability tests required by paragraphs (a) and (b), respectively, of this AD may be discontinued after either (1) The fuel filter and windshield fluid de-icing systems have been inspected as specified in paragraph (e) and have revealed no evidence of corrosion for a period of at least six months, and the non-return valves P/N AWE 124-25, AWE 124-26 and AWE 124-27 have been replaced by P/N AWE 124-25A, AWE 124-36 and AWE 124-37, respectively, as specified in paragraph (e); or (2) The aluminum alloy lines and components have been replaced with corrosion resistant lines and components, and non-return valves P/N AWE 124-25, AWE 124-26 and AWE 124-27 have been replaced by P/N AWE 124-25A, AWE 124-36 and AWE 124-37, respectively, as specified in paragraph (e). (e) The inspection for corrosion, the replacement of the non-return valves, and the replacement of the aluminum alloy lines and components covered in paragraph (a), must be accomplished in accordance with Hawker Siddeley Aviation Limited, Service Bulletin No. 28- A23, Revision 2, dated July 4, 1968, or later ARB approved revision or anFAA approved equivalent. Effective February 13, 1968. Revised March 27, 1969.
59-05-03: 59-05-03 FAIRCHILD: Applies to F-27 aircraft Serial Numbers 1 through 11, 14 through 23, and 27 through 35. Compliance required as indicated. A number of malfunctions of Bendix 38E09-3B, 38E09-3C and 38E09-3D deicer shutoff and regulating valves have occurred. These malfunctions have been traced to corrosion of the pilot valve assembly. New valves Bendix P/N 38E09-4E have been designed to eliminate this malfunction, however, until new valves are available, the following must be accomplished: (1) A functional performance check of the pneumatic wing deicing system must be performed prior to each flight into known or suspected icing conditions to ascertain that the pneumatic deicing system is performing satisfactorily. (2) At next inspection period, but not to exceed 100 hours, and every 100 hours thereafter remove Bendix shut-off and regulating valves, P/N 38E09-3B, 38E09-3C and 38E09- 3D, whichever type is installed, from left and right nacelles. Remove pilot valvecap, valve assembly and push rod and inspect for corrosion. Remove any signs of corrosion and apply a light coat of DC-7 Dow-Corning Compound or equivalent to valve assembly and push rod. Reinstall valves in aircraft. (3) Not later than June 1, 1959, replace valves P/N 38E09-3B, 38E09-3C and 38E09- 3D with valve P/N 38E09-4E. When this has been accomplished, the function check and inspection covered by items (1) and (2) can be discontinued. (Fairchild F-27 Service Letter F27-93 dated January 20, 1959, and Service Bulletin 30-2 dated January 20, 1959, revision 1 dated March 5, 1959, cover this same subject.) This supersedes AD 59-3-1.
92-11-09: 92-11-09 ROCKWELL INTERNATIONAL/COLLINS AIR TRANSPORT SYSTEMS: Amendment 39-8259. Docket No. 92-CE-30-AD. \n\n\tApplicability: TPR-720 Air Traffic Control Radar Beacon System/Mode S Transponders, part numbers (P/N) 622-7878-020, and P/N 622-7878-120, installed on, but not limited to, the following aircraft (all serial numbers), certificated in any category: \n\n\t\t\tBoeing 737-300, 747, and 767 Series Airplanes \n\n\t\t\tMcDonnell Douglas DC-10 Series Airplanes \n\n\t\t\tFokker F.28 Mark 0100 Series Airplanes \n\n\tCompliance: Required as indicated, unless already accomplished. \n\n\tTo prevent the loss of the ability to track aircraft positions by radar in high density air traffic areas that could result from transponder malfunction, accomplish the following: \n\n\t(a)\tWithin the next 6 calendar months after the effective date of this AD, accomplish either (1) or (2) below: \n\n\t\t(1)\tModify the transponder software in accordance with the instructions in Collins Service Bulletin (SB) 8, TPR-720-34-08, dated September 19, 1990. This modification converts transponder P/N 622-7878-020 and 622-7878-120 to P/N 622-7878-200 status. \n\n\tNOTE 1: Although not required by this AD, accomplishment of Collins SB 14, TPR-720-34-14, dated February 26, 1991, Revision 1, dated June 28, 1991; or Collins SB 15, TPR-720-34-15, dated February 26, 1991, Revision 1, dated June 28, 1991, is recommended after accomplishment of Collins SB 8, TPR-720-34-08. Collins SB 14, TPR-720-34-14, and SB15, TPR-720-34-15, convert transponder P/N 622-7878-200 to transponder P/N 622-7878-201 status or transponder P/N 622-7878-300 status, respectively. \n\n\t\t(2)\tModify the transponder hardware in accordance with the instructions in Collins SB C, TPR-720-34-C, dated April 28, 1992. \n\n\t(b)\tAn alternative method of compliance or adjustment of the compliance time that provides an equivalent level of safety may be approved by the Manager, Wichita Aircraft Certification Office, FAA, 1801 Airport Road, Mid-Continent Airport, Wichita, Kansas 67209. The request should be forwarded through an appropriate FAA Maintenance Inspector, who may add comments and then send it to the Manager, Wichita Aircraft Certification Office. \n\n\tNOTE 2: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Wichita Aircraft Certification Office. \n\n\t(c)\tThe modification required by this AD shall be done in accordance with Collins Service Bulletin 8, TPR-720-34-08, dated September 19, 1990; or Collins Service Bulletin C, TPR-720-34-C, dated April 28, 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 Rockwell International/Collins Air Transport Division, 400 Collins Road, NE, Cedar Rapids, Iowa 52498. 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. \n\n\t(d)\tThis amendment becomes effective on May 28, 1992.
2010-05-05: We are adopting a new airworthiness directive (AD) for the products listed above that would supersede an existing AD. 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: A review of the results of the final fuselage fatigue test identified the need for additional and revised safety-related fatigue- and environmental inspections for the fuselage. These additional tasks were introduced by Service Bulletin (SB) ATP-51-002 * * *. As it was determined that these inspections were necessary to maintain the structural integrity of the aeroplane, EASA AD 2006- 0090 [which corresponds to FAA AD 2007-15-08] was issued * * *. Since the original Issue of the SB, three revisions have been published. Revision 1 of the SB included only editorial changes. Revision 2 of the SB corrected the fuselage frame designations in Parts 50 and 50A and extended the allowable time before initial inspection. In addition, the repeat inspection interval in Part 43 of the SB was reduced. In the latest Revision 3 of the SB, the grace period for the initial inspection in Part 50 has been clarified. * * * * * The unsafe condition is fatigue cracking of certain structural elements, which could result in reduced structural integrity of the airplane and consequent rapid decompression of the airplane. This AD requires actions that are intended to address the unsafe condition described in the MCAI.
67-29-05: 67-29-05 SIKORSKY AIRCRAFT: Amdt. 39-501 Part 39 Federal Register November 1, 1967. Applies to type S61 Helicopters. Compliance required as indicated. To prevent fatigue failures of the Rotary Wing Hub Horizontal Hinge Pins, P/N S6100-23020 and P/N S6110-23320, accomplish the following: (a) Within the next 10 hours' time in service after the effective date of this AD, unless already accomplished, inspect the horizontal hinge pins in accordance with Sikorsky Service Bulletin No. 61B10-4 dated August 21, 1967 or later revisions approved by the Chief, Engineering and Manufacturing Branch, Federal Aviation Administration, Eastern Region. Equivalent inspections may be approved by an FAA maintenance inspector. (1) If a machining defect is found on the interior surface of the cylindrical part of the pin or on the inner surface of the part of the pin where the damper is attached (sections 1 or 3 of the pin as defined in the Sikorsky Service Bulletin) remove the hingepin from service prior to further flight. (2) If a machining defect is found on the interior surface of the tapered part of hinge pin (section 2 of the pins is defined in the Sikorsky Service Bulletin) inspect the external surface of this tapered section using a magnifying glass (2 power minimum). If a crack is found replace the hinge pin prior to further flight. (3) If a defect is found on the interior surface of the tapered part of the hinge pin (section 2 of the pin is defined in the Sikorsky Service Bulletin) and no crack is detected on the external surface of this section: (i) Perform a daily visual inspection of the external surface of section 2 using a magnifying glass (2 power minimum). If a crack is found remove the hinge pin from service before further flight. (ii) The hinge pin must be removed from service within the next 50 hours' time in service. This amendment effective October 30, 1967.
92-22-06: 92-22-06 MCDONNELL DOUGLAS: Amendment 39-8392. Docket No. 92-NM-160-AD. \n\n\tApplicability: Model MD-11 airplanes, Model DC-10 series airplanes, and Model KC-10 (military) airplanes; certificated in any category. \n\n\tCompliance: Required as indicated, unless accomplished previously. \n\n\tTo prevent fuel from being dumped below the minimum allowable level, which could lead to an all-engine-out condition, accomplish the following: \n\n\t(a)\tFor Model MD-11 airplanes: Within 15 days after the effective date of this AD, accomplish the requirements of paragraphs (a)(1) and (a)(2) of this AD: \n\n\t\t(1)\tRevise the Limitations Section of the FAA-approved Airplane Flight Manual (AFM) to include the following statement. This may be accomplished by inserting a copy of this AD in the AFM. \n\n\t\t"FUEL DUMP\n\n\t\t\t Careful monitoring of the fuel system status and consequences is required during \tdumping operations when electrical malfunctions are present." \n\n\t\t(2)\tRevise the Procedures Section of the FAA-approved AFM to include the following statement. This may be accomplished by inserting a copy of this AD in the AFM. \n\n\t\t"FUEL DUMP \n\n\t\t\tDUMP Switch.................................................. On \n\n\t\t\tNote: The fuel dump is designed to automatically terminate at approximately 40,000 lbs. \ttotal; however, when the Bus DC 2 OFF alert is displayed, the automatic termination feature will be inoperative." \n\n\t(b)\tFor Model DC-10 series airplanes and Model KC-10 (military) airplanes: Within 15 days after the effective date of this AD, accomplish the requirements of paragraphs (b)(1) and (b)(2) of this AD: \n\n\t\t(1)\tRevise the Limitations Section of the FAA-approved AFM to include the following statement. This may be accomplished by inserting a copy of this AD in the AFM. \n\n\t\t"FUEL DUMP \n\n\t\t\tCareful monitoring of the fuel quantity is required during dumping operations when electrical malfunctions are present." \n\n\t\t(2)\tRevise the Procedures Section of theFAA-approved AFM to include the following statement. This may be accomplished by inserting a copy of this AD in the AFM. \n\n\t\t\t"FUEL QTY Indicators...................................... MONITOR \n\n\t\t\t--- \t The fuel dump is designed to automatically terminate at approximately 40,000 lbs. total; however, if the DC BUS 2 OFF light is illuminated, the automatic termination feature will be inoperative." \n\n\t(c)\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 Los Angeles ACO. \n\n\t(d)\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(e)\tThis amendment becomes effective on November 3, 1992.
65-24-02: 65-24-02\tBOEING: Amdt. 39-146 Part 39 Federal Register September 30, 1965. Applies to Models 707 and 720 Series Airplanes. \n\n\tCompliance required within the next 1,800 hours' time in service after the effective date of this AD unless already accomplished.\n \n\tTo prevent further false indications of thrust reverser operation as a result of malfunction of the thrust reverser indicating light switch and switch wiring, accomplish the following: \n\n\t(a)\tOn airplanes equipped with JT3D turbofan engines, modify as follows: \n\n\t\t(1)\tOn airplanes modified in accordance with Boeing Service Bulletin No. 1896, dated November 1963, replace each aft thrust reverser indicating light switch with sealed switch, P/N 2HT13, in accordance with Boeing Service Bulletin No. 1896, or an equivalent. \n\n\t\t(2)\tOn airplanes not modified in accordance with Boeing Service Bulletin No. 1896, replace each aft thrust reverser indicating light switch with sealed switch, P/N 2HT13, in accordance with Boeing Service Bulletin No. 1884, dated January 1964, or an equivalent. \n\n\t\t(3)\tInterchange the electrical leads on the forward and aft thrust reverser indicating light switches in accordance with Boeing Service Bulletin No. 2170, dated May 1965, or an equivalent. \n\n\t(b)\tOn airplanes equipped with JT3C or JT4A turbojet engines, modify the thrust reverser indicating light switch wiring by interchanging the electrical leads in accordance with Boeing Service Bulletin No. 2170 or an equivalent. \n\n\t(c)\tApproval of any equivalent shall be processed through the Aircraft Engineering Division, FAA Western Region. \n\n\tThis directive effective October 29, 1965.
88-20-02: 88-20-02 MCDONNELL DOUGLAS: Amendment 39-6025. Applies to Model DC-9-80 (MD-80) series airplanes and Model MD-88 airplanes, certificated in any category, equipped with Janitrol P/N 14J93-350 clamps manufactured after March 1, 1988, including, but not limited to the following airplane factory serial numbers: \n\n\n49462\t\n49584\t\n49658 \n49463\t\t\n49585\n49661 \n49464\t\n49586\t\n49667 \n49509\t\n49592\t\n49668 \n49559\t\n49593\t\n49669 \n49560\t\n49604\t\n49670 \n49561\n49605\t\n49671 \n49562\t\n49617\t\n49672 \n49563\t\n49619\t\n49701 \n49564\t\n49620\n49702 \n49565\t\n49621\t\n49703 \n49566\t\n49622\t\n49704 \n49571\n49623\n49705 \n49572\t\n49624\t\n49707 \n49573\t\t\n49625\n49711 \n49577\t\t\n49644\n49712 \n49578\n49645\t\n49389 \n49579\t \n49646\n\n49583\t\n49657 \n\n\t\n\tNOTE: Additionally, airplanes other than those listed above are affected by this AD, if suspect clamps were installed on engine eighth or thirteenth stage pneumatic manifold end caps as replacement parts. \n\n\tCompliance required as indicated, unless previously accomplished. \n\n\tTo prevent uncontained separation of engine pneumatic manifold end caps, accomplish the following: \n\n\tA.\tWithin 25 days after the effective date of this AD, inspect both engines' eighth and thirteenth stage pneumatic manifold end cap clamps, Janitrol P/N 14J93-350, for identification markings, and accomplish the following: \n\n\tNOTE: Refer to McDonnell Douglas DC-9 Master Illustrated Parts Catalog 36-10-00, Figure 1A, Item 105, for locations of clamps. \n\n\t\t1.\tClamps with the number "5T400" and a date stamp, or the number "89513", appearing next to Janitrol P/N 14J93-350 are acceptable, and no further action is necessary. \n\n\t\t2.\tClamps with the number "63367" appearing next to Janitrol P/N 14J93-350 must be removed prior to further flight, and replaced with airworthy clamps. \n\n\t\t3.\tClamps with the number "5T400" appearing next to Janitrol P/N 14J93-350, and without a date stamp, must be removed prior to further flight, and replaced with airworthy clamps. \n\n\tB.\tPrior to installation of any eighth or thirteenth stage pneumatic manifold end cap clamp, Janitrol P/N 14J93-350, perform the inspection required by paragraph A., above. Do not install any clamp having the number "63367", or the number "5T400" and no date stamp, appearing next to Janitrol P/N 14J93-350. \n\n\tC.\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, FAA, Northwest Mountain Region. \n\n\tNOTE: The request should be forwarded through an FAA Principal Maintenance Inspector (PMI), who may add any comments and then send it to the Manager, Los Angeles Aircraft Certification Office. \n\n\tThis amendment, 39-6025, becomes effective October 11, 1988.
2021-24-05: The FAA is adopting a new airworthiness directive (AD) for certain Airbus Helicopters Deutschland GmbH Model EC135P2+, EC135P3, EC135T2+, and EC135T3 helicopters. This AD was prompted by reports that certain aft and forward fitting assemblies, which are not approved for installation on certain helicopters, were installed on those helicopters as part of the outboard load system. Operators of those helicopters might not be aware of the applicable overhaul or life limits for those fitting assemblies. This AD requires inspecting the aft and forward fitting assemblies of the outboard load system to determine the part number, re-identifying the part if necessary, inspecting each affected part for damage (which may be indicated by signs of corrosion, mechanical damage, loose rivets, or cracks) and, depending on the findings, corrective actions, as specified in a European Union Aviation Safety Agency (EASA) AD, which is incorporated by reference. The FAA is issuing this AD to address the unsafe condition on these products.
91-10-08: 91-10-08 MCDONNELL DOUGLAS: Amendment 39-6990. Docket No. 90-NM-256-AD. \n\n\tApplicability: McDonnell Douglas Model DC-9-81, -82, -83, and -87 series airplanes, and MD-88 airplanes, fuselage Numbers 909 through 1825, certificated in any category. \n\n\tCompliance: Required as indicated, unless previously accomplished. \n\n\tTo eliminate a potential fire ignition source in the forward cabin ceiling panel area, accomplish the following: \n\n\tA.\tWithin 90 days after the effective date of this AD, inspect the electrical connectors located above the forward cabin ceiling panel for damage in accordance with Paragraph B. of the "Accomplishment Instructions" of McDonnell Douglas Alert Service Bulletin A33-92, dated October 22, 1990 (hereinafter referred to as "The Service Bulletin"). \n\n\t\t1.\tIf damage is found, prior to further flight, modify the connectors and wires in accordance with Paragraph B, Condition I, of the "Accomplishment Instructions" in the Service Bulletin. \n\n\t\t2.\tIf nodamage is found, reinstall the connectors and reinspect the connectors in accordance with paragraph A. of this AD at intervals not to exceed 6 months. \n\n\tB.\tWithin 2 years after the effective date of this AD, modify the connectors in accordance with Paragraph B, Condition I or Condition II, Option 2, of the Service Bulletin. Accomplishment of these modifications constitutes terminating action for the repetitive inspections required by paragraph A. of this AD. \n\n\tC.\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\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\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; ATTN: Business Unit Manager, Technical Publications C1-HCW (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 (39-6990, AD 91-10-08) becomes effective on June 11, 1991.