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T85-21-51: T85-21-51 BOEING: Telegram issued October 25, 1985. Applicable to Boeing 767 series airplanes certificated in any category. \n\n\tTo prevent loss of certain critical airframe self-locking nuts accomplish the following unless previously accomplished: \n\n\tA.\tWithin 35 landings or 10 days after the effective date of this AD whichever occurs first inspect the horizontal elevator self-locking nuts in accordance with Boeing Alert Service Bulletin 767-27A0064 dated 10/25/85 or later FAA-approved revision. Self-locking nuts found to be insecure in accordance with the criteria specified in the service bulletin must be replaced before further flight with serviceable self-locking nuts. \n\n\tB.\tWithin 50 landings or 20 days after the effective date of this AD whichever occurs first, inspect the inboard aft trailing edge flap self-locking nuts and the outboard wing spoiler actuator self-locking nuts in accordance with Boeing Alert Service Bulletin 767-27A0064 dated 10/25/85 or later FAA-approved revision. Self-locking nuts found to be insecure in accordance with the criteria specified in the service bulletin must be replaced before further flight with serviceable self-locking nuts. \n\n\tC.\tAlternate means of compliance which provide an acceptable level of safety may be used when approved by the Manager, Seattle Aircraft Certification Office, FAA, Northwest Mountain Region. \n\n\tThe Boeing service bulletin specified in this directive may be obtained upon request to the Boeing Company, P.O. Box 3707, Seattle, Washington 98124. \n\n\tThis airworthiness directive becomes effective upon receipt.
64-06-07: 64-06-07 VERTOL: Amdt. 697 Part 507 Federal Register March 7, 1964. Applies to All Model 107-II Helicopters. Compliance required within 25 hours' time in service after the effective date of this AD. To prevent recurrence of a serious lurching condition which has been encountered on this model helicopter, modify each stability augmentation system to derive a.c. power from its respective generator instead of the essential bus, as follows: Remove the present a.c. electrical circuit wiring from terminals A3 and B3 of the a.c. instrument relay and from the "B" phase of the a.c. bus. Connect terminals A3 and B3 of the instrument relay to the terminal T2 of the a.c. feeder relay No. 1 and a.c. feeder relay No. 2 respectively. (Vertol 107-II Service Bulletin No. 107-118 dated December 6, 1963, covers the same subject.) This directive effective March 7, 1964.
2019-16-11: The FAA is superseding Airworthiness Directive (AD) 2018-20- 06, which applied to certain Airbus SAS Model A300 F4-600R series airplanes. AD 2018-20-06 required repetitive high frequency eddy current (HFEC) inspections of the aft lower deck cargo door (LDCD) frame forks; a one-time check of the LDCD clearances; a one-time detailed visual inspection of hooks, eccentric bushes, and x-stops; and corrective actions if necessary. This AD retains the actions of AD 2018-20-06 and requires new compliance times, depending on frame fork configuration. This AD was prompted by a report of two adjacent frame forks that were found cracked on the aft LDCD of two airplanes during scheduled maintenance, and a determination that certain compliance times need to be revised. The FAA is issuing this AD to address the unsafe condition on these products.
91-21-11: 91-21-11 MCDONNELL DOUGLAS: Amendment 39-8058. Docket No. 91-NM-202-AD.\n\n\tApplicability: Model DC-9-81, -82, -83, and -87 series airplanes (MD-81, -82, -83, and -87); and Model MD-88 airplanes; certificated in any category.\n\n\tCompliance: Required as indicated, unless previously accomplished within the last 45 days.\n\n\tTo prevent inadvertent retraction of the slats during flight, accomplish the following:\n\n\t(a)\tPrior to the accumulation of 10,000 total landings or within 30 days after the effective date of this AD, whichever occurs later, perform a visual or eddy current inspection to detect cracks of the slat drive mechanism brackets, part numbers 5938886-(any configuration) and 5938887-(any configuration), in accordance with the instructions in McDonnell Douglas MD-80 Alert Service Bulletin A27-322, dated August 22, 1991 (hereinafter referred to as "A27-322").\n\n\t(b)\tIf no crack is found as a result of the inspections required by paragraph (a) of this AD, repeat the inspections at the following intervals:\n\n\t\t(1)\tIf the immediately preceding inspection was accomplished using visual means, conduct the next inspection within 1,000 landings.\n\n\t\t(2)\tIf the immediately preceding inspection was accomplished using eddy current means, conduct the next inspection within 3,000 landings.\n\n\t(c)\tIf a crack is found as a result of the inspections required by paragraph (a) or (b) this AD, prior to further flight, remove and replace the slat drive mechanism with a new part, part numbers 5938887-(any configuration) and 5938886-(any configuration), in accordance with A27-322.\n\n\t(d)\tAfter replacement is accomplished in accordance with the provisions of paragraph (c) of this AD, prior to the accumulation of 10,000 additional landings, conduct inspections in accordance with A27-322, and reinspect or replace in accordance with the provisions of paragraph (b) and (c) of this AD.\n\n\t(e)\tSpecial flight permits may be issued in accordance with FAR 21.197 and 21.199 tooperate airplanes to a base in order to comply with the inspection requirements of this AD.\n\n\t(f)\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 forwarded through an FAA Principal Maintenance Inspector (PMI), who may concur or comment and then send it to the Manager, Los Angeles ACO.\n\n\t(g)\tThe inspection and replacement requirements shall be done in accordance with McDonnell Douglas MD-80 Alert Service Bulletin A27-322, dated August 22, 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, Technical Publications-Technical Administrative Support, C1-L5B, 3855 Lakewood Boulevard, Long Beach, California 90846. 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 (39-8058, AD 91-21-11) becomes effective on October 30, 1991.
93-13-07: 93-13-07 MCDONNELL DOUGLAS: Amendment 39-8620. Docket 92-NM-246-AD. \n\n\tApplicability: Model DC-9-10, -20, -30, -40, and -50 series airplanes, Model DC-9-81 and -82 series airplanes, and Model C-9 (Military) airplanes; as listed in McDonnell Douglas DC-9 Service Bulletin 53-179, dated January 18, 1985, as amended by Service Bulletin Change Notification 53-179 CN1, dated February 28, 1985, and Service Bulletin Change Notification 53-179 CN2, dated May 30, 1985; certificated in any category. \n\n\tCompliance: Required as indicated, unless accomplished previously. \n\n\tTo prevent freezing of water on the control cables, which could restrict the movement of the cables and result in reduced controllability of the airplane, accomplish the following: \n\n\t(a)\tWithin 24 months after the effective date of this AD, install a water drain system in the slant pressure panel in accordance with McDonnell Douglas DC-9 Service Bulletin 53-179, dated January 18, 1985, as amended by Service BulletinChange Notification 53-179 CN1, dated February 28, 1985, and Service Bulletin Change Notification 53-179 CN2, dated May 30, 1985. \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 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 installation shall be done in accordance with McDonnell Douglas DC-9 Service Bulletin 53-179, dated January 18, 1985; and Service Bulletin Change Notification 53-179 CN1, dated February 28, 1985, and Service Bulletin Change Notification 53-179 CN2, dated May 30, 1985, for McDonnell Douglas DC-9 Service Bulletin 53-179, dated January 18, 1985. 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 90801-1771, 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 the FAA, Transport Airplane Directorate, 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(e)\tThis amendment becomes effectiveon August 18, 1993.
96-11-07: This amendment adopts a new airworthiness directive (AD), applicable to certain Learjet Model 31 and 35A airplanes, that requires replacement of two segments of 16 American Wire Gauge (AWG) wire with 8 AWG wire at the connector that is connected to the auxiliary cabin heater relay box. This amendment is prompted by a report that two segments of the 16 AWG wire in the auxiliary cabin heater that were spliced during production do not provide adequate current-carrying capacity. The actions specified by this AD are intended to prevent electrical arcing and a subsequent fire hazard that could result from wiring with inadequate current-carrying capacity.
92-27-07: 92-27-07 MCDONNELL DOUGLAS: Amendment 39-8441. Docket No. 92-NM-86-AD.\n\n\tApplicability: Model DC-9-10, -20, -30, -40, and -50 series airplanes; Model DC-9-81, -82, -83, and -87 series airplanes; Model MD-88 airplanes; and C-9 (Military) airplanes; as listed in McDonnell Douglas DC-9 Alert Service Bulletin A27-325, Revision 1, dated February 3, 1992; certificated in any category.\n\n\tCompliance: Required as indicated, unless accomplished previously.\n\n\tTo prevent loss of rudder pedals control and reduction of braking capability, accomplish the following:\n\n\t(a)\tPrior to the accumulation of 15,000 landings or within 270 days after the effective date of this AD, whichever occurs later, conduct a visual and eddy current inspection to detect cracks of the rudder pedals adjuster hub assembly, part number 4616066, in accordance with McDonnell Douglas DC-9 Alert Service Bulletin A27-325, Revision 1, dated February 3, 1992.\n\n\t(b)\tIf no cracks are detected as a result of the inspections required by paragraph (a) of this AD, repeat the inspections at intervals not to exceed 3,500 landings.\n\n\t(c)\tIf cracks are detected as a result of the inspections required by paragraph (a) or (b) of this AD, prior to further flight, replace the rudder pedals adjuster hub assembly, part number 4616066, with a new assembly having the same part number, in accordance with McDonnell Douglas DC-9 Alert Service Bulletin A27-325, Revision 1, dated February 3, 1992. Thereafter, conduct visual and eddy current inspections of the replacement rudder pedals adjuster hub assembly in accordance with paragraph (a) and (b) of this AD.\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.\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(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 inspections and replacement shall be done in accordance with McDonnell Douglas DC-9 Alert Service Bulletin A27-325, Revision 1, dated February 3, 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 90846-1771, 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 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(g)\tThis amendment becomes effective on January 22, 1993.
90-06-18 R1: 90-06-18 R1 BOEING: Amendment 39-6541 as corrected by Amendment 39-6706. Docket No. 89-NM-105-AD. \n\n\tApplicability: Model 747 series airplanes, Groups 1, 2, and 3 as listed in Boeing Service Bulletin 747-32-2190, Revision 4, dated October 26, 1989, certificated in any category. \n\n\tCompliance: Required as indicated, unless previously accomplished. \n\n\tTo prevent landing gear collapse during landing due to corrosion and fatigue cracks, accomplish the following: \n\n\tA.\tInspect as follows: \n\n\t\t1.\tWithin the next 120 days after the effective date of this AD, perform a visual inspection, or a visual plus eddy current inspection, of the wing landing gear at the trunnion, for cracks and corrosion, in accordance with Boeing Service Bulletin 747-32-2190, Revision 4, dated October 26, 1989. \n\n\t\t2.\tIf no cracks or corrosion are found, repeat inspection described in paragraph A.1. of this AD at intervals not to exceed 6 months if the visual inspection option was selected for the previous inspection, or at intervals not to exceed 18 months if visual and eddy current inspection option was selected for the previous inspection. \n\n\t\t3.\tExcept as provided by paragraph A.4. below, if cracks or corrosion are found, prior to further flight, remove and rework or replace cracked/corroded parts in accordance with Boeing Service Bulletin 747-32-2190, Revision 4, dated October 26, 1989. \n\n\t\t4.\tIf only corrosion is found, as an alternative to paragraph A.3. of this AD, accomplish the terminating action described in Boeing Service Bulletin 747-32-2190, Revision 4, dated October 26, 1989, within 12 months after detection of corrosion, but no later than 36 months after the effective date of this AD; and high frequency eddy current inspect the wing landing gear trunnion at intervals not to exceed 6 months, until the terminating action is accomplished. \n\n\tB.\tModification in accordance with Boeing Service Bulletin 747-32-2190, Revision 4, dated October 26, 1989, constitutes terminating action for the reinspection requirements of paragraph A. above. \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, Seattle Aircraft Certification Office, FAA, Northwest Mountain Region. \n\n\tNOTE: The request should be forwarded through an FAA Principal Maintenance Inspector (PMI), who will either concur or comment, and then send it to the Manager, Seattle Aircraft Certification Office. \n\n\tD.\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 Airplanes, P.O. Box 3707, Seattle, Washington 98124. This information may be examined at the FAA, Northwest Mountain Region, Transport Airplane Directorate, 1601 Lind Avenue S.W., 5th Floor, Renton, Washington, or the Seattle Aircraft Certification Office, 1601 Lind Avenue S.W., 2nd Floor, Renton, Washington.\n \n\tAirworthiness Directive 90-06-18 R1 revises AD 90-06-18, Amendment 39-6541. \n\tThe effective date for the requirements of this AD remains April 23, 1990, as specified in Amendment AD 90-06-18, Amendment 39-6541. \n\n\tThis Amendment (39-6706, AD 90-06-18 R1) is effective on August 17, 1990.
2019-14-08: The FAA is superseding Airworthiness Directive (AD) 2016-07- 22, which applied to all Airbus SAS Model A300 B4-600, B4-600R, and F4- 600R series airplanes, and Model A300 C4-605R Variant F airplanes (collectively called Model A300-600 series airplanes); and Model A310 series airplanes. AD 2016-07-22 required modifying the electrical routing installation at the right-hand (RH) and left-hand (LH) wings to achieve a minimum distance between wiring bundles and surrounding structures. This new AD retains the requirements of AD 2016-07-22 and, for certain airplanes, adds a requirement to further modify the electrical installations in both wings, as specified in a European Aviation Safety Agency (EASA) AD, which is incorporated by reference. This AD was prompted by reports of missing installation information for certain airplanes. The FAA is issuing this AD to address the unsafe condition on these products.
94-04-05: This amendment adopts a new airworthiness directive (AD) that is applicable to certain Airbus Industrie Models A300, A310, and A300-600 series airplanes. This action requires repetitive deployment tests of the ram air turbine (RAT) and checks of the adjustment of the locking rod. This amendment is prompted by reports of failure of the RAT to rotate when necessary, due to maladjustment of the locking rod. The actions specified in this AD are intended to ensure the availability of the RAT in case of need.