Results
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.
2023-14-11: The FAA is adopting a new airworthiness directive (AD) for certain Bombardier, Inc., Model BD-100-1A10 airplanes. This AD was prompted by reports of unexpected pitch upset upon autopilot disconnect. This AD requires revising the Non-Normal Procedures section of the existing airplane flight manual (AFM) associated with Auto Flight. The FAA is issuing this AD to address the unsafe condition on these products.
2023-15-01: The FAA is adopting a new airworthiness directive (AD) for all Pratt & Whitney Canada Corp. (P&WC) Model PW307D engines. This AD is prompted by a root cause analysis of an event involving an uncontained failure of a high-pressure turbine (HPT) 1st-stage disk, on an International Aero Engines AG (IAE) Model V2533-A5 engine, that resulted in high-energy debris penetrating the engine cowling and an aborted takeoff. This AD requires removing certain HPT 2nd-stage disks from service and also prohibits installation of certain HPT 2nd-stage disks on any affected engine. The FAA is issuing this AD to address the unsafe condition on these products.
60-03-10: 60-03-10 WRIGHT: Amdt. 90 Part 507 Federal Register January 26, 1960. Applies to All TC18DA and TC18EA Series Engines. Compliance required at first engine overhaul after February 1, 1960, but not later than October 1, 1960. To prevent inadvertent loss of oil from the power recovery turbine fluid couplings, the PRT oil control valve must incorporate a WAD P/N 147825 valve body, or subsequently released part. This valve body incorporates three flats to provide a permanent oil bypass to insure an adequate supply of turbine coupling oil in the event of a regulator spring failure. (WAD Service Bulletins Nos. TC18-390 and TC18E-210 cover this same subject and furnish instructions for the rework of the superseded valve bodies to the P/N 147825 configuration.) This supersedes and cancels item No. (8) of AD 58-13-05.
97-04-12: This amendment adopts a new airworthiness directive (AD) that is applicable to certain Pratt & Whitney Canada (PWC) PT6 series turboprop engines. This action requires a one-time visual inspection of compressor bleed-off valves (BOVs) to determine if an affected supplier's code number is on the cover; and, if so, this AD requires the removal of the bleed valve cover assembly from the compressor bleed valve housing assembly and inspection of the cotter pin and the guide shaft pin. If the cotter pin or guide shaft pin is not acceptable, this AD requires modifying the compressor BOV or replacing it with a serviceable part. This amendment is prompted by reports of two malfunctions of compressor BOVs that resulted in inflight engine power reduction. The actions specified in this AD are intended to prevent engine power reduction due to malfunction of the compressor BOV, which could result in a forced landing and loss of the aircraft.
2005-02-03: The FAA is superseding an existing airworthiness directive (AD) for Pratt & Whitney (PW) JT8D-209, -217, -217A, -217C, and -219 series turbofan engines. That AD currently requires torque inspection of the 3rd stage and 4th stage low pressure turbine (LPT) blades for shroud notch wear and replacement of the blade if wear limits are exceeded. This AD continues to require those torque inspections at shorter inspection intervals of the refurbished 3rd stage and 4th stage LPT blades, but the same or longer inspection intervals of the new 3rd stage and 4th stage LPT blades, for shroud notch wear and replacement of the blade if wear limits are exceeded. This AD also requires replacing LPT-to-exhaust case bolts and nuts with bolts and nuts made of Tinidur material. This AD results from reports of 194 blade fractures since 1991, with 37 of those blade fractures resulting in LPT case separation, and three reports of uncontained 3rd stage and 4th stage LPT blade failures with cowl penetration. We are issuing this AD to prevent an uncontained blade failure that could result in damage to the airplane.
2023-12-22: The FAA is adopting a new airworthiness directive (AD) for all BAE Systems (Operations) Limited Model 4101 airplanes. This AD was prompted by in-service cracking of the passenger door edge member, seal carrier, and inner skin, adjacent to the roller guide bracket. This AD requires a one-time inspection of the external visible surface of the inner skin, door edge member, and seal carrier adjacent to the roller bracket attachment brackets; and the inner skin, door edge member, and seal carrier at the roller bracket attachment bore, and repair if necessary. The FAA is issuing this AD to address the unsafe condition on these products.
82-23-07: 82-23-07 RATIER-FIGEAC FH.146: Amendment 39-4490. Applies to Ratier-Figeac propeller Model FH.146. Compliance required within the next 100 hours of operation after the effective date of this AD unless already accomplished. To preclude the possibility of propeller blade failure, accomplish the following: (a) In accordance with Ratier-Figeac Service Bulletin No. 61-142 dated June 1, 1982, or an equivalent method approved by the Manager, Aircraft Certification Division, Federal Aviation Administration, New England Region: 1. Measure electrical resistance at end of disconnected wires of slip ring assembly. 2. Measure electrical resistance of insulation between wires and each propeller blade. (b) Remove propellers with measurements outside the limits of Bulletin No. 61-142 from service prior to further flight. This airworthiness directive becomes effective November 15, 1982.
55-23-02: 55-23-02 LOCKHEED: Applies to Models 1049C, D, E, and G, Serial Numbers 4163 Through 4166, 4520 Through 4581, 4583 Through 4605, 4608 Through 4615, and 4620. Compliance required as indicated. 1. Inspect the outer wing main beam web between wing Stations 510 and 668 left and right for cracks as soon as practical and repeat at 125-hour intervals until reinforcement in accordance with paragraph 2 is accomplished. If cracks are found repair immediately in accordance with Lockheed Repair Manual, Report 8882, and continue 125-hour inspections until reinforcement per paragraph 2 is accomplished. Inspection for fuel stains alone as an indication of a crack is not sufficient because of the presence of fuel sealant on the forward side of the web. 2. To be accomplished as soon as possible, but not later than next scheduled progressive overhaul time, and in no case later than December 1, 1956, whichever occurs first: Reinforce the main beam web, left and right, between wing Stations510 and 668. This shall be accomplished by the addition of three extruded 75S-T6 stiffeners, (LS2186 or LS6097) or equivalent between each of the original stiffeners. The LS347-3 stiffeners added previously in accordance with AD 54-24-02 on some of these aircraft may be retained. In these cases, one new (LS2186 or LS6097 or equivalent) stiffener must be added between each of these and the original stiffeners in this area. (Lockheed Service Bulletin No. 1049/SB-2753 also covers this subject.)
2014-21-06: We are adopting a new airworthiness directive (AD) for certain Beechcraft Corporation (Type Certificate Previously Held by Hawker Beechcraft Corporation; Raytheon Aircraft Company; Beech Aircraft Corporation) Model 400, 400A, 400T, and MU-300 airplanes. This AD was prompted by a report of a failure of the Acme nut threads in a pitch trim actuator (PTA). This AD requires an inspection to determine if PTAs having a certain serial number and part number are installed, and replacement if they are installed. This AD also requires repetitive replacements of PTAs with new PTAs or certain overhauled PTAs. We are issuing this AD to prevent failure of the Acme nut threads in the PTA, which could lead to loss of control of pitch trim and reduced controllability of the airplane.
2000-13-05: This amendment adopts a new airworthiness directive (AD) that is applicable to Rolls-Royce plc. (RR) RB211 Trent 768-60, Trent 772-60, and Trent 772B-60 turbofan engines. This action requires initial and repetitive ultrasonic inspections for cracks in fan blade dovetail roots, and if necessary, replacement with serviceable parts. This amendment is prompted by reports of fan blade failures due to dovetail root cracks in factory engine. The actions specified in this AD are intended to prevent possible multiple fan blade failures, which could result in an uncontained engine failure and damage to the airplane.
2014-21-02: We are adopting a new airworthiness directive (AD) for Pacific Aerospace Limited Model FU24-954 and FU24A-954 airplanes. This AD results from mandatory continuing airworthiness information (MCAI) issued 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 cracking of the control column at the wiring access hole, which could lead to loss of control. We are issuing this AD to require actions to address the unsafe condition on these products.
97-04-19: This amendment adopts a new airworthiness directive (AD), applicable to certain Saab Model SAAB 2000 series airplanes, that requires a visual inspection to determine if rudder disconnection has occurred, and replacement of the disconnect unit with a new disconnect unit, if necessary. This amendment is prompted by reports that, due to the existing design, the disconnect unit of the rudder disconnect system inadvertently opened on some airplanes. The actions specified by this AD are intended to prevent the disconnect unit from opening inadvertently, which could lead to inadequate rudder control, if the engine fails during take-off or go-around and if the airplane is at low speed.
2005-02-05: The FAA is superseding an existing airworthiness directive (AD) for Rolls-Royce (RR) plc RB211-535E4-37, RB211-535E4-B-37, and RB211-535E4-B-75 series turbofan engines. That AD currently requires initial and repetitive ultrasonic inspections of installed LPC fan blade roots on-wing and during overhaul using a surface wave ultrasonic probe, and relubrication, according to accumulated life cycles. That AD also adds the application of Metco 58 blade root coating as an optional terminating action. This AD requires the same actions, but changes the reference to Mandatory Service Bulletin (MSB) No. RB.211-72-C879 from Revision 3 to Revision 4. This AD results from RR issuing MSB No. RB.211-72-C879, Revision 4, which contains revised Accomplishment Instructions and consumable materials list. We are issuing this AD to detect cracks in low pressure compressor (LPC) fan blade roots, which if not detected, could lead to uncontained multiple fan blade failure, and damage to the airplane.
80-14-10: 80-14-10 BRITTEN-NORMAN (BEMBRIDGE) LTD.: Amendment 39-3828. Applies to Model BN-2A Mark III Series Trislander airplanes, certificated in all categories. Compliance is required as indicated unless already accomplished. To detect corrosion and to prevent loss of the rudder mass balance arm brackets which could cause hazardous rudder flutter, accomplish the following: (a) Within the next 25 hours time in service after the effective date of this AD or prior to 2 years since new, whichever occurs later, visually inspect for corrosion the support brackets of the mass balance arms at the top, and on each side, of the rudder in accordance with paragraph "ACTION," of Britten-Norman Service Bulletin BN-2/SB.116, dated June 5, 1978 (hereinafter referred to as the service bulletin), or an FAA-approved equivalent. (b) If corrosion is found as a result of the inspection required by paragraph (a) of this AD, before further flight, except that the aircraft may be flown in accordance with FAR 21.197 and FAR 21.199 to a base where the work can be performed, accomplish either of the following: (1) Perform the permanent repair as specified in "Rectification - Part 1" of the service bulletin or an FAA-approved equivalent, and thereafter reinspect for corrosion in accordance with paragraph (a) of this AD, at intervals not to exceed 3 years from the date of the repair; or (2) Perform the temporary repair as specified in "Rectification - Part 2" of the service bulletin or an FAA-approved equivalent, and thereafter continue to perform the inspection required by paragraph (a) of this AD, at intervals not to exceed 2 months from the date of the repair, for a maximum of 1 year at which time the permanent repair and inspection required by paragraph (b)(1) of this AD must be accomplished. (c) If no external corrosion is found as a result of the inspection required by paragraph (a) of this AD, the mass balance arm support brackets may continue in servicefor a period not to exceed 6 months from the date of the initial inspection, provided that the visual inspection required by paragraph (a) of this AD is repeated at intervals not to exceed 2 months or 200 hours time in service from the last inspection, whichever occurs first, after which the permanent or temporary repairs and inspections of paragraph (b)(1) or (b)(2) must be accomplished. (d) Prior to the installation of rudders held in stock as spares, accomplish the inspection and repair as necessary in accordance with paragraphs (a) and (b)(1) of this AD. (e) For purposes of this AD, an FAA-approved equivalent must be approved by the Chief, Aircraft Certification Staff, Federal Aviation Administration, Europe, Africa, and Middle East Office, c/o American Embassy, Brussels, Belgium, Telephone: 513.38.30. This amendment becomes effective July 14, 1980.