Results
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.
83-18-02: 83-18-02 McDONNELL DOUGLAS: Amendment 39-4718. Applies to CFM-56 powered McDonnell Douglas Model DC-8-70 series airplanes, with P/N 9984M90G20 fuel injectors installed on one or more engines, certificated in all categories. Compliance required as indicated, unless previously accomplished: \n\n\tA.\tTo prevent possible engine flameouts while using JP4 or Jet B fuel accomplish the following within seven calendar days after the effective date of this AD: \n\n\t\t1.\tRevise the limitations section of the FAA approved Airplane Flight Manual (AFM) to read: "Aircraft being operated with any amount of JP4 or Jet B fuel and equipped with one or more engines incorporating General Electric P/N 9984M90G20 injectors will require that the ignition override switch be placed in the ALL ENGINES position, on one or both systems, prior to and during descent through landing." \n\n\t\t2.\tInstall a placard in the cockpit, in clear view of the pilots, which reads: "With any amount of JP4 or Jet B fuel - Use ignition override prior to and during descent through landing." \n\n\tB.\tA copy of this AD inserted in the FAA approved Airplane Flight Manual is considered as an acceptable means of compliance with the required AFM revisions. \n\n\tC.\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\tD.\tAlternate means of compliance which provide an equivalent level of safety may be used when approved by the Manager, Los Angeles Aircraft Certification Office, FAA, Northwest Mountain Region. \n\n\tNOTE: Replacement of all P/N 9984M90G20 injectors on an aircraft with approved replacement injectors, removes that aircraft from the applicability of this AD, and permits removal at the AFM revision and placard required by paragraph A., above. \n\n\tThis amendment becomes effective September 8, 1983.
97-05-07: This amendment supersedes an existing airworthiness directive (AD), applicable to certain Lockheed Model 382 series airplanes, that currently requires a revision to the Airplane Flight Manual to require takeoff operation in accordance with revised performance data. That AD also requires installation of certain valve housings for the propeller governor on the outboard engines. This amendment revises the applicability of the existing AD to remove certain airplanes. This amendment also revises references to a certain replacement part number of a valve housing. The actions specified by this AD are intended to ensure that the airplane maintains adequate thrust decay characteristics in the event of critical engine failure during takeoff.
2005-02-06: The FAA is adopting a new airworthiness directive (AD) for certain McDonnell Douglas Model MD-11 and MD-11F airplanes equipped with Pratt & Whitney PW4000 series engines. This AD requires, for each engine, replacing, with a tube assembly, the existing hose assembly that connects the oil pressure transmitter to the main oil circuit. This AD is prompted by a report indicating that, for each engine, the existing hose assembly does not meet zero-flow fireproof capability requirements. We are issuing this AD to prevent, if there is an engine fire, failure of the oil pressure indicator and the low-oil pressure warning, which could result in an unannounced shutdown of that engine; and oil leakage, which may feed the engine fire.
2023-13-13: The FAA is adopting a new airworthiness directive (AD) for all Airbus SAS Model A350-941 and -1041 airplanes. This AD was prompted by reports of a non-full life clearance in the low-pressure hydraulic pipes of the nose landing gear return line, due to two quality escapes. This AD requires replacing the affected aluminum pipes with titanium pipes, 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.
79-13-06: 79-13-06 DORNIER GmbH: Amendment 39-3489. Applies to Model Do 28 D-2 Skyservant airplanes, serial numbers 4050 and 4301 through 4307, certificated in all categories. Compliance required as indicated, unless already accomplished. To detect and eliminate corrosion and chafing of the engine fire extinguishing system pipelines, accomplish the following in accordance with Dornier Service Bulletin No. 2062-2828, dated April 1, 1977, or an FAA-approved equivalent: (a) Within the next 25 hours time in service after the effective date of this AD, inspect the engine fire extinghishing system for corrosion, accumulation of water, and pipeline chafing. (b) If corrosion or water accumulation is found during the inspection required by paragraph (a), before further flight, except as provided in paragraph (d) of this AD, modify the system by - (1) Installing a pipeline seal; (2) Incorporating pipeline water drainage holes; (3) Installing a drain valve; and(4) Replacing corrosion-prone pipelines with stainless steel pipelines between the engine fire extinghisher bottle and frame 6020. (c) If pipeline chafing is found during the inspection required by paragraph (a), before further flight, except as provided in paragraph (d), modify the system by - (1) Incorporating anti-abrasive protection; and (2) Installing a pipeline securing clamp. (d) Airplanes may be flown in accordance with FAR 21.197 and 21.199 to a base where the modifications required by paragraphs (b) and (c) of this can be performed. This amendment becomes effective July 11, 1979.
2005-02-07: The FAA is adopting a new airworthiness directive (AD) for certain EMBRAER Model EMB-135BJ series airplanes. This AD requires modifying the electrical wiring for the "stick pusher" system. This AD is prompted by a report that the stick pushers are not being inhibited when the AP/PUSH/TRIM switches are activated, which can result in reduced controllability of the airplane if there is a system malfunction. We are issuing this AD to prevent reduced controllability of the airplane if the stick pusher system malfunctions.
2014-22-02: We are adopting a new airworthiness directive (AD) for all Rolls-Royce plc (RR) Trent 1000-A, 1000-C, 1000-D, 1000-E, 1000-G, and 1000-H turbofan engines. This AD requires removing engine electronic controller (EEC) software earlier than standard MB6.15 and replacing with a software standard eligible for installation. This AD was prompted by a finding that an intermediate pressure [[Page 64505]] (IP) shaft failure may not be detected by EEC software earlier than standard MB6.15. We are issuing this AD to detect IP shaft failure and prevent IP compressor turbine burst, uncontained engine failure, and damage to the airplane.
2023-13-02: The FAA is adopting a new airworthiness directive (AD) for certain Embraer S.A. Model ERJ 170 airplanes. This AD was prompted by reports indicating that certain flight control electrical harnesses were routed incorrectly, providing inadequate separation from other electrical harness installations. This AD requires an inspection of certain flight control electrical harnesses for incorrect routing, and modifying any incorrect electrical harness installations, 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.
62-22-01: 62-22-01 CESSNA: Amdt. 494 Part 507 Federal Register October 16, 1962. Applies to All Models 150, 175, 175A, 175B, and 175C Aircraft Equipped with Continental Engines O-200-A, GO-300-A and GO-300-C Modified to Incorporate Airborne Mechanisms Model 113A5 Vacuum Pumps (Supplemental Type Certificates Nos. SA1-630 and SA1-610 Amended March 13, 1962, Issued to Airborne Mechanisms Division of Randolph Manufacturing Co.). Compliance required within the next 10 hours' time in service after the effective date of this AD. In order to prevent failure of the Airborne Mechanisms Model 113A5 vacuum pump because of improper installation, remove and reinstall the pump as follows: Mount the pump and then remove it from the engine drive pad. The coupling will remain in the engine spline and the separation will occur between the pump shaft and the coupling. The coupling must then be pressed 1/16 inch further into the engine spline. Reinstall the pump, and insure that the steel cross vanes protrude approximately 1/16 inch from the hub of the coupling. (Airborne Mechanisms Service Letter No. 4 dated May 15, 1962, entitled "Installation Interference of Model 113A5 Drive Splines" covers this same subject.) This directive effective October 31, 1962.
79-25-02 R1: 79-25-02 R1 LOCKHEED-CALIFORNIA COMPANY: Amendment 39-3629 as amended by amendment 39-4098. Applies to Lockheed-California Company L-1011-385 series airplanes certificated in all categories. To preclude possible failure of the main landing gear pistons P/N 1523009 (-109, -113, - 117, -121), perform the following: Compliance required as indicated. (a) Within the next 48 hours after the effective date of the AD, unless already accomplished, conduct a visual inspection of the main landing gear piston clevis lugs including the web area directly above the lugs. If a crack is found, the piston must be replaced prior to further revenue flight. (b) Repeat the visual inspection of paragraph (a), above, once per each day in which the aircraft is operated. NOTE: The visual inspection of paragraphs (a) and (b), above, should be conducted with the piston clevis lugs and the web area directly above the lugs thoroughly cleaned of all accumulated dirt and grease. The conductof this visual inspection is considered to constitute an interim safety action. (c) Installation and/or modification of the main landing gear uplock snubber, truck pivot pin and bushings using Kits 1630462-101, -103, -105, and -107 or alternate Kits 1630462- 109, -111, -113, and -115 per Lockheed Service Bulletin 093-32-154 Revision #2 dated January 5, 1981, constitutes terminating action for this AD. (d) Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes to a base for the accomplishment of replacements required by this AD. (e) Alternative inspections or other actions which provide an equivalent level of safety may be used when approved by the Chief, Aircraft Engineering Division, FAA Western Region. The 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). All persons affected by this directive who have not already received these documents from the manufacturer may obtain copies upon request to Lockheed-California Company, P.O. Box 551, Burbank, California 92520, Attention: Commercial Support Contracts, Department 63-11, 033, B- 1. These documents also may be examined at FAA Northwest Region, 9010 East Marginal Way South, Seattle, Washington 98108, or 15000 Aviation Boulevard, Hawthorne, California 90261, Room 6W14. Amendment 39-3629 became effective December 11, 1979. This amendment 39-4098 becomes effective May 22, 1981.
2005-02-09: This amendment adopts a new airworthiness directive (AD), applicable to all Airbus Model A319, A320, and A321 series airplanes, that requires operators to revise the Airworthiness Limitations section (ALS) of the Instructions for Continued Airworthiness to incorporate new and more restrictive service life limits for certain items, and new and more restrictive inspections to detect fatigue cracking, accidental damage, or corrosion in certain structures. The actions specified by this AD are intended to ensure the continued structural integrity of these airplanes. This action is intended to address the identified unsafe condition.