Results
2017-05-10: We are superseding Airworthiness Directive (AD) 2015-16-02 for all Airbus Model A330 series airplanes. AD 2015-16-02 required revising the maintenance or inspection program to incorporate certain maintenance requirements and airworthiness limitations. This new AD requires revising the maintenance or inspection program to incorporate new maintenance requirements and airworthiness limitations. This AD was prompted by a revision of the airworthiness limitations items (ALI) document, which provides new and more restrictive maintenance requirements and airworthiness limitations for airplane structures and systems. We are issuing this AD to address the unsafe condition on these products.
2017-05-09: We are adopting a new airworthiness directive (AD) for certain CFM International S.A. (CFM) CFM56-5 turbofan engines. This AD requires removal of the radial drive shaft (RDS) assembly and the RDS outer housing and their replacement with parts eligible for installation. This AD was prompted by reports of the failure of the RDS on CFM CFM56- 5B engines. We are issuing this AD to correct the unsafe condition on these products.
92-07-07: 92-07-07 EIRIAVION: Amendment 39-8203. Docket No. 91-CE-35-AD. Applicability: Models PIK-20 and PIK-20B sailplanes (all serial numbers) that are equipped with lead mass balance strips on the flaps and ailerons, certificated in any category. Compliance: Required within the next 25 hours time-in-service (TIS) after the effective date of this AD, unless already accomplished, and thereafter at intervals not to exceed 500 hours TIS. To prevent interference to the ailerons that could result in loss of control of the sailplane, accomplish the following: (a) Remove the flaps and ailerons and inspect the lead mass balance strips for cracks using a 10-power magnifying glass. NOTE 1: Particular attention should be given to the attachment rivets during the inspections specified in paragraph (a) of this AD. NOTE 2: If the sailplane is not equipped with mass balance strips on the flaps and ailerons, then no further action is required by this AD. (b) If cracking is detected in accordance with the inspections required by paragraph (a) of this AD, prior to further flight, fabricate and replace the mass balance strips in accordance with the following: (1) Utilize strips made of malleable lead (not brittle or granular) that are the same weight and dimensions. (2) Attach the strips at the same rivet holes as the cracked one and bond the lead in place with epoxy resin. (3) Keep the counter bore holes to the minimum depth in accordance with the applicable service manual. (4) Install washers to the rivets on the glass-reinforced plastic face. (5) Do not increase the diameter of any rivet. (6) Ensure that the final mass balance of each flap and aileron complies with the applicable service manual. (c) Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate the sailplane to a location where the requirements of this AD can be accomplished. (d) An alternative method of compliance or adjustment of the compliance time that provides an equivalent level of safety may be approved by the Manager, Brussels Aircraft Certification Staff, Europe, Africa, Middle East office, FAA, c/o American Embassy, 1000 Brussels, Belgium. The request should be forwarded through an FAA Maintenance Inspector, who may add comments and then send it to the Manager, Brussels Aircraft Certification Staff. (e) All persons affected by this directive may examine information that is related to this AD upon request to the FAA, Central Region, Office of the Assistant Chief Counsel, Room 1558, 601 E. 12th Street, Kansas City, Missouri 64106. (f) This amendment (39-8203, AD 92-07-07) becomes effective on April 30, 1992.
2001-20-09: This amendment adopts a new airworthiness directive (AD), applicable to all Boeing Model 727 series airplanes, that requires repetitive inspections of the bearing support fitting of the forward trunnion on the main landing gear (MLG) to detect corrosion and cracking; follow-on actions, if necessary; and repair/rework of the support fitting, or replacement with a new or repaired/reworked fitting. The actions specified by this AD are intended to prevent failure of the support fitting, which could result in collapse of the MLG during normal operations; consequent damage to the airplane structure; and injury to flight crew, passengers, or ground personnel. This action is intended to address the identified unsafe condition.
2001-20-15: This amendment adopts a new airworthiness directive (AD) that is applicable to certain McDonnell Douglas Model DC-9 series airplanes and MD-88 airplanes. This action requires an inspection to determine if a certain AC cross-tie relay is installed; replacement of a certain AC cross-tie relay with a new AC cross-tie relay; and repetitive cleaning, inspection, repair and testing of a certain AC cross-tie relay. This action is necessary to prevent AC cross-tie relay failures, which could result in internal arcing of the relay and smoke and/or fire in the cockpit and cabin. This action is intended to address the identified unsafe condition.
2017-05-08: We are adopting a new airworthiness directive (AD) for all Safran Helicopter Engines, S.A. Arriel 2B turboshaft engines. This AD requires removing any pre-modification (mod) TU 158 hydro-mechanical metering unit (HMU) and replacing with a part eligible for installation. This AD was prompted by a report of an uncommanded in- flight shutdown (IFSD) on a single-engine helicopter, caused by a low returning spring rate of the needle of the HMU. We are issuing this AD to correct the unsafe condition on these products.
78-02-02: 78-02-02 HUGHES HELICOPTERS: Amendment 39-3127. Applies to Model 269 Series helicopters, certificated in all categories including Model TH-55A. Compliance is required as indicated, unless already accomplished. To prevent failure of the tail rotor control pedals, accomplish the following: (a) Within the next 100 hours time in service from the effective date of this AD, unless already accomplished, and thereafter at intervals not to exceed 100 hours time in service perform the following: (1) On all models visually inspect the pilots' pedal arms P/N 269A7336 for cracks and corrosion in accordance with service information notice (SIN) N-121.1, Part I, Paragraph (b). (i) If visual inspection reveals evidence of incipient cracks, further inspect with dye penetrant and if confirmed replace with a serviceable pedal arm P/N 269A7336 before further flight. (ii) If corrosion is found, remove the corrosion in accordance with SIN N-121.1 before further flight.(iii) After corrosion removal of (1)(ii) above, inspect the wall thickness of the pedal arm in the areas of corrosion removal. If the wall thickness in the cylindrical section is less than .10 inches replace the pedal arm P/N 269A7336 with a serviceable pedal arm before further flight. If the corrosion removal on the pedal arm above the cylindrical section exceeds .005 inches in depth replace the pedal arm P/N 269A7336 with a serviceable pedal arm before further flight. (2) On Models 269A, A-1, and TH-55A, visually inspect the copilots' pedal arms P/N 269A7336 in accordance with paragraph (a)(1) above. (3) On Models 269B and C, remove the copilots' pedal arms P/N 269A7330 from the pedal sockets P/N 269A9973 or P/N 269A7334 and visually inspect for cracks and corrosion in accordance with SIN N-121.1, Part I, Paragraph (d). (i) If visual inspection reveals evidence of incipient cracks, further inspect with dye penetrant in accordance with SIN N-121.1 and ifconfirmed replace with a serviceable part or parts before further flight. (ii) If corrosion is found, remove the corrosion in accordance with SIN N121.1 before further flight. (iii) After corrosion removal of (3)(ii) above, inspect the wall thickness in the areas of corrosion removal. If the wall thickness of the pedal arm is less than .13 inches replace the pedal arm P/N 269A7330 before further flight. If the wall thickness of the socket is less than .10 inches replace the socket P/N 269A9973 or P/N 269A7334 before further flight. (b) Within the next 100 hours time in service, from the effective date of this AD unless already accomplished, and thereafter at intervals not to exceed 100 hours time in service, torque the pedal arm and/or socket bushing nuts to the limits specified by SIN N-121.1. (c) On the 269B and 269C helicopters only, within the next 100 hours time in service, from the effective date of this AD unless already accomplished, measure the copilots' pedal arm wall thickness above the quick release pin hole. If the wall thickness is less than 0.130 inches replace the pedal arm P/N 269A7330 before further flight. (d) On all Models except 269C, within the next 100 hours time in service, from the effective date of this AD unless already accomplished, rework the pilots' and copilots' left hand pedal arm and or sockets in accordance with SIN N-121.1 Part II. (e) Hughes service information notice (SIN) N-121.1, dated October 3, 1977, or later FAA approved revisions shall be used for compliance where indicated in this AD except for alternate inspection and rework methods approved under Paragraph (f). (f) Equivalent inspections, and reworks may be approved by Chief, Aircraft Engineering Division, FAA Western Region, Los Angeles, California. This amendment becomes effective January 24, 1978.
77-26-03: 77-26-03 MCCAULEY PROPELLERS: Amendment 39-1301 as amended by Amendment 39-3232. Applies to the following three bladed constant speed Model D3A34C401 and D3A34C402 propellers installed on but not limited to the Cessna Model TU206G, T207A, and T210M aircraft: Affected Propeller Serial Numbers 765815 765820 765821 765822 765823 765824 765828 766622 766624 766625 766626 766627 766638 766639 766640 766641 766642 766643 766644 767451 767452 767453 767454 767455 767456 767457 767458 767471 767472 767473 767474 767475 767476 767477 767479 767480 767481 767661 767662 767663 767664 767665 767666 767667 767668 767678 767679 767680 767682 767683 767684 767776 767777 767778 767799 767800 767801 767802 767803 767804 767805 767806 767822 767823 767824 767825 767826 767827 767828 767829 767830 767831 767832 767833 767834 767835 767837 767838 767839 767879 767880 768190 768191 768192 768193768194 768195 768196 768197 768199 768202 768254 768335 768336 768337 768338 768339 768340 768341 768342 768343 768344 768345 768346 768347 768348 768349 768350 768351 768352 768353 768354 768560 768888 768889 768890 768891 768892 768893 768970 768971 769002 769007 769008 769009 769092 769093 769094 769209 769210 769211 769212 769214 769215 769216 769217 769229 769230 769264 769265 769266 769267 769269 769288 769289 769291 769292 769449 769450 769451 769452 769453 769454 769455 769456 769457 769459 769460 769548 769549 769550 769551 769552 769553 769555 769556 769557 770212 770213 770214 770216 770217 770218 770219 770220 770221 770222 770223 770224 770225 770226 770390 770391 770392 770394 770489 770490 770491 770492 770583 770584 770585 770608 770609 770610 770611 770612 770613 770614 770615 770623 770624 770625 770626 770627 770628 770629 770630 770631 770632 770633 770634 770635 770636 770637 770638 770639 770640 770641 770642 770721 770722 770723 770724 770725 770864 770865 770866 770867 770868 770869 770870 770871 770872 770873 770874 770875 770876 770877 770878 770879 770880 770881 770882 770883 770884 770885 771659 771660 771661 771662 771663 771664 771665 771676 771677 771679 771680 771681 771682 771683 771684 771685 771813 771844 771845 771846 771987 771988 772004 772005 772006 772007 772008 772010 772011 772012 772013 772014 772015 772017 772041 772042 772204 772205 772206 772207 772208 772209 772210 772250 772251 772252 772253 772254 772255 772256 772257 772506 772507 772509 772510 772518 772519 772520 772521 772683 772694 772696 772698 772699 772700 772701 772702 772703 772704 772705 772731 772732 772733 772735 772865 772866 772940 772941 772942 772943 772945 772946 772974772975 772977 772981 772983 772984 773011 773093 773094 773095 773096 773097 773098 773101 773192 773193 773195 773196 773197 773198 773199 773200 773201 773202 773205 773207 773342 773343 773533 773709 773775 773780 773783 773785 773787 773918 773924 NOTE: Serial numbers are stamped on the side of the propeller hub. These propellers are equipped with Model 90DFA-() blades (usually - 10 cutoff). Compliance required before further flight, except that the airplane may be flown in accordance with FAR 21.197 to a Federal Aviation Administration Certificated Propeller Repair Station. To prevent possible blade pitch control failures, accomplish the following: (a) Replace blade actuating pin screws, P/N A-1635-104 (cadmium plated), with new screws, P/N A-1635-108 (black oxide) in accordance with McCauley Service Bulletin No. 129, dated October 7, 1977, and Service Manual No. 761001, or later Federal Aviation Administration approved revisions. (b) Replacement of the above parts must be accomplished by a Federal Aviation Administration Certificated Propeller Repair Station, since it is considered a major repair. (c) When the affected propellers are approved for return to service, compliance with this airworthiness directive shall be noted in the Aircraft's Records. (Cessna Service Letter SE-77-37 dated October 10, 1977, also pertains to this subject.) The manufacturer's specifications and procedures identified in this directive are incorporated herein and made part hereof pursuant to 5 U.S.C. 552(a)(1). All persons affected by the directive who have not already received these documents from the manufacturer, may obtain copies upon request to McCauley Accessory Division, Cessna Aircraft Company, Box 7, Roosevelt Station, Dayton, Ohio 45417. These documents may also be examined at the Great Lakes Regional Office, 2300 East Devon Avenue, Des Plaines, Illinois 60018, and at FAA Headquarters, 800Independence Avenue, S.W., Washington, D.C. 20591. A historical file on this airworthiness directive which includes incorporated material in full is maintained by the FAA at its Headquarters in Washington, D.C., and the Great Lakes Region. Amendment 39-3159 became effective December 28, 1977. This amendment 39-3233 becomes effective on June 7, 1978.
2017-05-02: We are adopting a new airworthiness directive (AD) for certain Airbus Model A318-112 airplanes; Model A319-111, -112, -115, -132, and -133 airplanes; Model A320-214, -232, and -233 airplanes; and Model A321-211, -212, -213, -231, and -232 airplanes. This AD was prompted by a quality control review on the final assembly line, which determined that the wrong aluminum alloy was used to manufacture several structural parts. This AD requires a one-time eddy current conductivity measurement of certain cabin and cargo compartment structural parts to determine if an incorrect aluminum alloy was used, and replacement if necessary. We are issuing this AD to address the unsafe condition on these products.
2001-20-11: This amendment supersedes an existing airworthiness directive (AD), applicable to certain Boeing Model 757 series airplanes, that currently requires repetitive freeplay checks of the elevator, and replacement of worn elevator power control actuator (PCA) reaction link rod-end bearings and the PCA rod-end bearing, if necessary. That AD also provides for an optional terminating action for the repetitive checks. This amendment removes the optional terminating action provided by the existing AD, expands the applicability of the existing AD to include additional airplanes, and requires repetitive freeplay checks of the elevator at a revised repeat interval and repetitive lubrication of bearings of the elevator actuator load loop and hinge line. The actions specified by this AD are intended to prevent unacceptable airframe vibration during flight, which could lead to excessive wear of bearings of the elevator PCA load loop and hinge line and result in reduced controllability of theairplane. This action is intended to address the identified unsafe condition.