Results
2000-16-10: This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model DC-10-10, -15, -30, -30F (KC-10A military), and -40 series airplanes, and Model MD-10-10F and MD-10-30F series airplanes that requires performing repetitive ultrasonic inspections of the attaching bolts on the inboard and outboard support on the inboard and outboard flap assembly to detect failed bolts, or verifying the torque of the attaching bolts on the inboard support on the outboard flap; and follow-on actions. This AD also requires replacing all bolts with bolts made from Inconel, which constitutes terminating action for the repetitive inspection requirements. This amendment is prompted by an in-flight loss of the inboard flap assembly on an airplane during approach for landing. The actions specified by this AD are intended to prevent in-flight loss of inboard and outboard flap assemblies due to failure of H-11 attaching bolts, which could result in reduced controllability of the airplane.
2005-03-07: This amendment adopts a new airworthiness directive (AD) for Bell Helicopter Textron Canada (Bell) Model 407 helicopters that requires creating a component history card or equivalent record for each crosstube assembly, converting accumulated run-on landings to an accumulated Retirement Index Number (RIN) count, and establishing a maximum accumulated RIN for certain crosstube assemblies. This amendment is prompted by fatigue testing, analysis, and evaluation by the manufacturer that determined that run-on landings impose a high stress on landing gear or crosstubes and may cause cracking in the area above the skid tube saddle. The actions specified by this AD are intended to prevent fatigue failure in a crosstube assembly due to excessive stress during run-on landings and subsequent loss of control of the helicopter.
2023-08-08: The FAA is adopting a new airworthiness directive (AD) for all Airbus SAS Model A330-201, -202, -203, -301, -302, and -303 airplanes. This AD was prompted by reports of corrosion and cracks found on engine inlet attach fittings. This AD requires an inspection to determine whether affected engine inlet attach fittings are installed, and replacement of those affected engine inlet attach fittings or replacement with and inlet cowl having no affected engine inlet attach fittings, as specified in a European Union Aviation Safety Agency (EASA) AD, which is incorporated by reference. This AD also prohibits the installation of affected parts. The FAA is issuing this AD to address the unsafe condition on these products.
96-04-07: This amendment adopts a new airworthiness directive (AD) that is applicable to certain Airbus Model A310 and A300-600 series airplanes. This amendment requires repetitive inspections to detect distortion and/or cracks on the attachment brackets of the backrest recline control locks of certain seats. It also provides for an optional modification which, if accomplished, terminates the repetitive inspections. This amendment is prompted by a report of failure of the bracket of the backrest recline control lock on a seat due to fatigue-related cracking. The actions specified by this AD are intended to prevent fatigue-related cracking and/or distortion, which could result in failure of the seat backrest attach fitting, and the subsequent uncommanded 50 angle recline of the pilot or co-pilot seat; this situation could lead to the temporary inability of the pilots to control the airplane.
2000-16-11: This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A330 and A340 series airplanes, that requires repetitive inspections to check for backlash of the spherical bearing of the active aileron servo-controls, and follow-on corrective actions, if necessary. This amendment also provides optional terminating action for the repetitive inspections. This action is necessary to detect and correct excess backlash of the spherical bearing of the active aileron servo-controls, which could result in failure of the active aileron servo-controls and consequent reduced controllability of the airplane. This action is intended to address the identified unsafe condition.
2005-03-05: The FAA is revising an existing airworthiness directive (AD), which applies to certain McDonnell Douglas Model MD-90-30 airplanes. This AD requires a one-time general visual inspection to detect wire chafing damage and to determine adequate clearance between the disconnect panel structure and the wires above the aft left lavatory; and corrective actions, if necessary. This new AD revises the applicability of the existing AD. This AD is prompted by the determination that certain airplanes unaffected by the existing AD are subject to the unsafe condition, and certain other airplanes should be removed from the applicability. We are issuing this AD to prevent damage to certain wires due to contact between the wires and the adjacent structure, which could result in electrical arcing and consequent smoke and fire in the cabin.
91-03-01: 91-03-01 BOEING HELICOPTERS (BOEING VERTOL HELICOPTER CO.): Amendment 39-6862. Docket No. 90-ASW-47-AD. Applicability: All Model 234 series helicopter, with serial numbers (S/N) MJ001, MJ002, MJ003, MJ005, MJ006, MJ016, MJ017, MJ022, MJ023, MM819, MM820, and MM821, certificated in any category. Compliance: Required as indicated, unless previously accomplished. To prevent failure of a rotor blade damper elastomeric rod end, which could result in the rotor blade striking the helicopter during start up or shut down, accomplish the following: (a) Within the next 10 hours' time in service after the effective date of this AD inspect all rod ends, part number (P/N) 234RS202-1 and -2, with more than 350 hours' time in service, unless accomplished within the last 40 hours' time in service. Thereafter, inspect these rod ends at intervals not to exceed 25 hours' time in service from the last inspection. Conduct these inspections using eddy current inspection methodsapproved by the FAA. NOTE: The Accomplishment Instructions of paragraphs 3.B and C of Boeing Helicopters Service Bulletin 234-62-1031, dated September 26, 1990, provide an FAA approved calibration and inspection procedure for eddy current inspection of the rod ends. (b) Conduct an FAA approved eddy current inspection of any used spare serviceable rod end, P/N 234RS202-1 or -2, with more than 350 hours' time in service prior to installation and return to service, and thereafter at intervals not to exceed 25 hours' time in service from the last inspection. (c) If a crack is found, replace the cracked rod end with a serviceable rod end prior to further flight. (d) Helicopters may be ferried in accordance with the provisions of FAR Sections 21.197 and 21.199 to a base where the requirements of the AD can be accomplished. (e) Alternate inspections, modification, other actions, or adjustment of the compliance times, which provides an equivalent level of safety maybe used when approved by the Manager, New York Aircraft Certification Office, FAA, 181 South Franklin Avenue, Room 202, Valley Stream, New York. This amendment (39-6862, AD 91-03-01) becomes effective on February 14, 1991.
2000-16-02: This amendment supersedes an existing airworthiness directive (AD), applicable to Pratt & Whitney PW4164, PW4168, and PW4168A series turbofan engines. The current AD requires initial and repetitive torque checks for loose or broken bolts used to secure the engine to the airplane made from INCO 718 material (front pylon mount bolts). The current AD also requires the replacement of the bolts, if necessary, with new bolts, and establishes a new cyclic life limit for the front pylon mount bolt. This amendment adds requirements for initial and repetitive torque checks of front pylon mount bolts made from a new material, MP159, and initial and repetitive visual inspections of the primary mount thrust load path. This amendment is prompted by the use of front pylon mount bolts made from MP159 material and fatigue testing that shows that the forward engine mount bearing housings have insufficient fatigue life expectancy. The actions specified by this AD are intended to prevent frontpylon mount bolt and primary mount thrust load path failure, which could result in an engine separating from the airplane.
2005-03-03: The FAA is superseding an existing airworthiness directive (AD), which applies to all Boeing Model 767-200, -300, and -300F series airplanes. That AD currently requires examination of maintenance records to determine if Titanine JC5A (also known as Desoto 823E508) corrosion inhibiting compound ("C.I.C.") was ever used; inspection for cracks or corrosion and corrective action, if applicable; repetitive inspections and C.I.C. applications; and modification of the aft trunnion area of the outer cylinder, which terminates the need for the repetitive inspections and C.I.C. applications. This new AD also requires, for certain other airplanes, repetitive inspections for cracks or corrosion, corrective action if necessary, and repetitive C.I.C. applications. This AD is prompted by a report that JC5A was used on more airplanes during production than previously identified. We are issuing this AD to prevent severe corrosion in the main landing gear (MLG) outer cylinder at the aft trunnion, which could develop into stress corrosion cracking and consequent collapse of the MLG.
96-16-05: This amendment adopts a new airworthiness directive (AD), applicable to certain Fokker Model F28 Mark 1000, 2000, 3000, and 4000 series airplanes, and Model F28 Mark 0100 series airplanes, that requires repetitive pre-load adjustments of the main landing gear (MLG) downlock-actuator. This AD also provides optional terminating action for the repetitive adjustments. This amendment is prompted by a report that, upon landing, the MLG of an airplane collapsed as a result of the lock toggle-links being pulled out of the over-center position by the downlock-actuator, which was due to the relative movement of the upper and lower side-stay members. The actions specified by this AD are intended to prevent collapse of the MLG, which could adversely affect the controllability of the airplane during landing.
2000-15-20: This amendment adopts a new airworthiness directive (AD) for Agusta S.p.A. (Agusta) Model A109A and A109A II helicopters. This AD requires radiographic inspections of the internal surface of each main rotor blade spar (spar) for corrosion. This AD is prompted by the discovery of corrosion on the internal surfaces of the spar in the area adjacent to the main rotor blade inertia balance weights. The actions specified by this AD are intended to prevent failure of a main rotor blade due to corrosion on the internal surface of the spar and subsequent loss of control of the helicopter.
2005-03-02: This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 737-300, -400, and -500 series airplanes; and Model 757-200 and -200CB series airplanes, that requires inspection of the applicable body station frames for open body station frames and related investigative/corrective actions; and installation of lanyard hook brackets and lanyard assemblies under the air conditioning overhead ducts, as applicable. This action is necessary to prevent loosened or disconnected overhead ducts from causing ceiling panels to drop below the minimum height of the evacuation zone for the passenger cabin, which could result in inadequate height for safe exit in the event of an emergency evacuation. This action is intended to address the identified unsafe condition.
2014-23-08: We are superseding Airworthiness Directive (AD) 2012-06-19 for certain Airbus Model A330-201, -202, -203, -223, -243, -301, -302, - 303, -321, -322, -323, -341, -342, and -343 airplanes; and Model A340- 200 and -300 series airplanes. AD 2012-06-19 required repetitive inspections of the main fitting and sliding tube of the nose landing gear (NLG) for defects, damage, and cracks; and corrective actions if necessary. This new AD requires an inspection of the part number and serial number of the NLG main fitting and NLG sliding tube; for affected parts, this new AD requires a magnetic particle inspection (MPI) for cracks, and flap peening and replacement if necessary. This new AD also requires, for certain parts, additional inspections for damage and cracking. This new AD also adds airplanes to the applicability. This AD was prompted by reports of a cracked main fitting and sliding tube during NLG overhaul. We are issuing this AD to detect and correct cracks, defects, or damage ofthe main fitting or sliding tube, which could result in consequent NLG collapse.
97-06-06: This amendment supersedes AD 92-27-10, which currently requires inspecting the pilot and copilot chairs to ensure that the locking pins will fully engage in the seat tracks on certain Raytheon Aircraft Company (Raytheon) 90, 99, 100, 200, and 1900 series airplanes (formerly referred to as Beech 90, 99, 100, 200, and 1900 series airplanes), and modifying any chair where the locking pin fails to fully engage or is misaligned. AD 92-27-10 resulted from reports of pilot and copilot chair locking pin malfunctions. Since issuance of that AD, the Federal Aviation Administration (FAA) has determined that additional airplanes should be subject to the pilot and copilot chair locking pin inspection and possible modification, and that the inspection should be accomplished in accordance with revised procedures. This AD retains the inspection and possible modification requirements of AD 92-27-10; incorporates additional airplanes into the applicability over that included in AD 92-27-10;and requires the inspection in accordance with revised service information. The actions specified by this AD are intended to prevent inadvertent movement of the pilot or copilot chair, which could result in loss of control of the airplane if it occurs during a critical flight maneuver.
2005-03-04: The FAA adopts a new airworthiness directive (AD) for all Pacific Aerospace Corporation, Ltd. (Pacific Aerospace) Model 750XL airplanes. This AD requires you to replace any type TLP-D or TLED rivets on the aileron pushrod ends and elevator control pushrod ends. This AD results from mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for New Zealand. We are issuing this AD to replace the above identified rivets on the aileron pushrod ends and elevator control pushrod ends, which, if not replaced, could result in loose mechanical elements in the control systems. This could lead to control anomalies and loss of airplane control.
76-10-09: 76-10-09 BEECH: Amendment 39-2616. Applies to Models B19 (Serial Numbers MB-732 through MB-788), C23 (Serial Numbers M-1600 thru M-1769) and B24R (Serial Numbers MC-305 thru MC-398) airplanes equipped with mechanical flaps. Compliance: Required as indicated, unless already accomplished. To prevent unscheduled retraction of wing flaps, within the next 50 hours' time in service after the effective date of this AD, accomplish the following: A. Pursuant to the procedures and instructions outlined in Beechcraft Service Instructions No. 0831-161 or later approved revisions: (1) Using a flashlight and mirror, visually inspect the inside of the flap torque tube to determine if Beech P/N 169-524024-9 flap cable block is attached to the torque tube with rivets or with screws and nuts. (2) If the flap cable block is attached to the torque tube with the screws and nuts identified in Paragraph (3) below, no further action is required. (3) If a flap cable blockis attached to the torque tube with rivets, drill out the three rivets (one at a time in accordance with the aforementioned service instructions) and replace with three each MS24694S58 screws, AN960-10 washers and MS21042L3 locknuts or Beech P/N 130909N29 locknuts. B. Any equivalent method of compliance with this AD must be approved by the Chief, Engineering and Manufacturing Branch, FAA, Central Region. This amendment becomes effective May 28, 1976.
96-13-12: 96-13-12 DORNIER: Amendment 39-9681. Docket 95-NM-231-AD. Applicability: Model 328-100 series airplanes having serial numbers 3005 through 3024 inclusive, certificated in any category. NOTE 1: This AD applies to each airplane identified in the preceding applicability provision, regardless of whether it has been modified, altered, or repaired in the area subject to the requirements of this AD. For airplanes that have been modified, altered, or repaired so that the performance of the requirements of this AD is affected, the owner/operator must request approval for an alternative method of compliance in accordance with paragraph (b) of this AD. The request should include an assessment of the effect of the modification, alteration, or repair on the unsafe condition addressed by this AD; and, if the unsafe condition has not been eliminated, the request should include specific proposed actions to address it. Compliance: Required as indicated, unless accomplished previously. To prevent abnormal functions of the bus power control units and the generator control units, which could result in electrical short circuits in the electrical power distribution systems and a subsequent fire, accomplish the following: (a) Within 3 months after the effective date of this AD, perform the requirements of paragraph (a)(l) and (a)(2) of this AD, in accordance with Dornier Service Bulletin SB-328-24-061, Revision 1, dated November 3, 1994. (1) Remove the generator control units 2PC and 12PC and replace them with new improved units having part number 118-000-1. And, (2) Remove bus power control unit 20PC and replace it with a new improved unit having part number 106-000-3. (b) An 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, Standardization Branch, ANM-113, 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, Standardization Branch, ANM-113. NOTE 2: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Standardization Branch, ANM-113. (c) Special flight permits may be issued in accordance with sections 21.197 and 21.199 of the Federal Aviation Regulations (14 CFR 21.197 and 21.199) to operate the airplane to a location where the requirements of this AD can be accomplished. (d) The removals and replacements shall be done in accordance with Dornier Service Bulletin SB-328-24-061, Revision 1, dated November 3, 1994, which contains the following effective pages: Page Number Revision Level Shown on Page Date Shown on Page 1,3 1 November 3, 1994 2 Original October 14, 1994 This incorporation by reference is 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 Dornier Luftfahrt GmbH, P.O. Box 1103, D-82230 Wessling, Germany. Copies may be inspected at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC. (e) This amendment becomes effective on August 2, 1996.
2023-15-02: The FAA is adopting a new airworthiness directive (AD) for certain Embraer S.A. Model ERJ 190-300 and -400 airplanes. This AD was prompted by reports of missing parts on the main landing gear (MLG) side stay upper spindle assembly. This AD requires inspection of the left-hand (LH) and right-hand (RH) MLG side stay upper spindle assembly attachments, and corrective actions if necessary, as specified in an Ag[ecirc]ncia Nacional de Avia[ccedil][atilde]o Civil (ANAC) AD, which is incorporated by reference. The FAA is issuing this AD to address the unsafe condition on these products.
62-01-01: 62-01-01 FAIRCHILD-HILLER: Amendment 383 Part 507 Federal Register January 9, 1962 as amended by Amendment 39-2102. Applies to Model F-27 Series and FH-227 Airplanes Equipped with Walter Kidde Company Chemical Drier Housings, P/N 890395 and P/N 890800- 0001. Compliance required as indicated. It has been determined that Walter Kidde Company Chemical Drier Housing, P/N 890395, is subject to cycling failure at a time limit lower than originally established by the manufacturer. Accordingly, the following shall be accomplished: Chemical Drier Housing, P/N 890395, shall be removed from service at each 2,000 hours' time in service, or 2 years, whichever occurs first. Chemical Drier Housing, P/N 890800-0001, may be installed as a replacement for P/N 890395. This replacement housing shall be removed from service at each 4,300 hours' time in service or 20,000 cycles of operation of the chemical drier (two cycles for each takeoff and landing sequence of the aircraft). All housings shall be visually inspected at each cartridge change during their service life. If cracking, distortion or corrosion is evidenced, remove the housing for a detail inspection. If cracks or distortion are found in either the housing tube or end caps, or if corrosion is found in the threaded areas, the entire unit shall be replaced prior to further flight. Any surface corrosion, other than in the threaded areas, may be removed provided the wall thickness is not reduced below the following: P/N 890395: 0.160 inch. P/N 890800-0001: 0.206 inch. After the removal of corrosion, clean the surface and apply a corrosive resistant finish. (Fairchild Aircraft and Missiles Division Service Bulletin No. 36-6, Revision 1, covers this same subject.) This supersedes AD 61-04-03. Amendment 383 was effective January 9, 1962. Revised December 29, 1966. This amendment 39-2102 is effective upon publication.
2005-02-11: The FAA adopts a new airworthiness directive (AD) for certain Gippsland Aeronautics Pty. Ltd. Model GA8 airplanes. This AD requires you to inspect the pilot and co-pilot control column wheels and aileron cable operating arm shafts for damage and, if damage is found, to repair the shafts or to replace the steel shafts with bronze shafts. We are issuing this AD to detect and correct damage of the pilot and co- pilot control wheels and aileron cable operating arm shafts. This damage could result in the aileron controls becoming stiff or locking, which could lead to loss of control of the airplane.
2023-15-04: The FAA is adopting a new airworthiness directive (AD) for all Embraer S.A. Model ERJ 190-300 and -400 airplanes. This AD was prompted by identification that, during simulations, analysis, and an in-service event of the airplane, a stall warning system activation (i.e., stick shaker) and angle of attack (AOA) limiter engagement may occur in certain vertical gust conditions with specific intensity and frequency. This AD requires revising the Limitations section of the existing airplane flight manual (AFM) to incorporate minimum operating speeds during flight at moderate or severe turbulence conditions, as specified in an Ag[ecirc]ncia Nacional de Avia[ccedil][atilde]o Civil (ANAC) AD, which is incorporated by reference. The FAA is issuing this AD to address the unsafe condition on these products.
2023-15-03: The FAA is adopting a new airworthiness directive (AD) for all Safran Helicopter Engines, S.A. (Safran) Model Arrius 2B2 engines. This AD is prompted by the manufacturer revising the airworthiness limitations section (ALS) of the existing engine maintenance manual (EMM), introducing new and more restrictive tasks and limitations for certain life-limited parts. This AD requires revising the ALS of the existing EMM or instructions for continued airworthiness (ICA) and the existing approved maintenance or inspection program, as applicable, by incorporating the actions and associated thresholds and intervals, including life limits, as specified in a European Union Aviation Safety Agency (EASA) AD, which is incorporated by reference (IBR). The FAA is issuing this AD to address the unsafe condition on these products.
79-24-04 R1: 79-24-04 R1 BOEING: Amendment 39-3617 as amended by Amendment 39-4587. Applies to all Boeing 707-100, 707-100B, 707-200, and Boeing 720, 720B series airplanes. Within the next number of landings shown in Table I, if not already accomplished within the last same number of landings, and at repeat intervals not to exceed those specified, visually inspect the horizontal stabilizer center section rear spar upper chord in accordance with page 9, paragraph IIIB, Boeing Service Bulletin 3332, Rev. 2, or in a manner approved by the Manager, Seattle Aircraft Certification Office, FAA, Northwest Mountain Region. If cracks are found, repair prior to further flight in a manner approved by the Manager, Seattle Aircraft Certification Office, FAA, Northwest Mountain Region, except that airplanes may be flown to a maintenance base for repairs or replacement in accordance with FAR 21.197.\n \n\t\t\t\t\tTABLE I \n\n\n\n720/720B\n707-100/-100B/-200\nInitial inspection interval\n125 landings\n175 landingsRepetitive inspections\n250 landings\n350 landings\n\n\tAccomplishment of the modification described in Accomplishment Instructions, Part II, of Boeing Service Bulletin 3332, Rev. 3, dated January 8, 1982, or later FAA approved revisions, constitutes terminating action for this AD. \n\tThe manufacturer's specifications and procedures identified and described in this directive are incorporated herein and made a part hereof pursuant to 5 U.S.C. 552(a)(1). \n\n\tAmendment 39-3617 became effective November 27, 1979. \n\tThis Amendment 39-4587 becomes effective April 4, 1983.
97-05-09: This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 737 series airplanes, that requires replacement of the flow restrictors of the aileron and elevator power control units (PCU's) with new flow restrictors. This amendment is prompted by a review of the design of the flight control systems on Model 737 series airplanes. The actions specified by this AD are intended to prevent reduced roll and/or pitch rate control of the airplane and consequent increased pilot workload as a result of fragments from a deteriorated flow restrictor filter screen becoming lodged in the PCU.
2005-02-10: This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 757 series airplanes, that requires repetitive detailed inspections of the support brackets and associated fasteners for the hydraulic lines located in the nacelle struts, and related investigative and corrective actions as necessary. This action also provides an optional terminating action for the repetitive inspections. This action is necessary to prevent flammable fluids from leaking into the interior compartment of the nacelle struts where ignition sources exist, which could result in the ignition of flammable fluids and an uncontained fire. This action is intended to address the identified unsafe condition.