Results
90-02-22: 90-02-22 DEHAVILLAND: Amendment 39-6471. Applicability: Models DHC-2 Mk. I (including L-20A, YL-20, U-6, and U-6A), and DHC-2 Mk. II (serial numbers 1 through 1056) airplanes certificated in any category. Compliance: Required as indicated in the body of the AD. To ensure the structural integrity of the horizontal tailplane to fuselage front attachment brackets, accomplish the following: (a) Within the next 200 hours time-in-service (TIS), or prior to the accumulation of 1000 hours TIS, whichever occurs later after the effective date of this AD, unless already accomplished per the requirements of AD 54-11-01, and thereafter at intervals not to exceed 1000 hours TIS: (1) Inspect attachment brackets, part number (P/N) C2-FS-543A and P/N C2-FS-544A for cracks and distorted rivets in accordance with paragraph `A' of the "ACCOMPLISHMENT INSTRUCTIONS" in deHavilland Service Bulletin (S/B) No. 2/42, Revision C, dated February 2, 1989. (2) Prior to furtherflight replace any distorted rivets as indicated in the above S/B, paragraph "B", and any cracked brackets as indicated in paragraph "C" of the Service Bulletin. (b) At each interval not exceeding 1000 hours TIS since the last bolt replacement, replace all 1/4 inch diameter forward attachment bolts on the tailplane front attachment brackets with new bolts, P/N AN174-H12A, in accordance with S/B No. 2/42 Rev C. (c) The repetitive inspections or modifications in paragraph (a) of this AD are not required on airplanes modified in accordance with deHavilland Modification No. 2/1338, or Agriculture Modification No. 2/984, as applicable. (d) Airplanes may be flown in accordance with FAR 21.197 to a location where the requirements of this AD may be accomplished. (e) An alternate method of compliance or adjustment of the initial or repetitive compliance times, which provides an equivalent level of safety, may be used when approved by the Manager, New York Aircraft Certification Office, FAA, New England Region, 181 South Franklin Avenue, Valley Stream, New York 11581. NOTE: The request should be forwarded through an FAA Principal Maintenance Inspector, who may add comments and then send it to the Manager, New York Aircraft Certification Office. All persons affected by this directive may obtain copies of the documents referred to herein upon request to Boeing of Canada, Ltd.; deHavilland Division, Garratt Boulevard, Downsview, Ontario, Canada M3K 1Y5; Telephone (416) 633-7310; or may examine these documents at the FAA, Central Region, Office of the Assistant Chief Counsel, Room 1558, 601 East 12th Street, Kansas City, Missouri 64106. This AD supersedes AD 54-11-01. This amendment (39-6471, AD 90-02-22) becomes effective on February 13, 1990.
2021-13-11: The FAA is adopting a new airworthiness directive (AD) for certain MHI RJ Aviation ULC Model CL-600-2D15 (Regional Jet Series 705) and CL-600-2D24 (Regional Jet Series 900) airplanes. This AD was prompted by a report that the lower aft outboard supporting structure of galley 2 does not meet certification requirements for all flight and/or emergency landing loads. This AD requires modifying the floor structure between certain fuselage stations. The FAA is issuing this AD to address the unsafe condition on these products.
76-17-04: 76-17-04 ARMSTRONG WHITWORTH: Amendment 39-2701. Applies to all Model AW-650 Series 101 airplanes certificated in all categories. Compliance is required within the next 100 hours time in service after the effective date of this AD, unless already accomplished. To detect cracks in the undercut at the bottom of the main undercarriage sliding cylinder and prevent possible failure of the main landing gear, accomplish the following: (a) Inspect the undercut at the bottom of the main undercarriage sliding cylinder with magnetic particle fluid in accordance with Accomplishment Instructions 2A(1) through 2A(6) of Dowty Rotol Service Bulletin No. 32-49D, dated August 15, 1975, or an FAA-approved equivalent. (b) If a crack in the sliding cylinder is detected during the inspection required by paragraph (a) of this AD, replace the main undercarriage sliding cylinder before further flight with a serviceable part of the same part number or an FAA-approved equivalent. This amendment becomes effective on September 9, 1976.
91-05-04: 91-05-04 BOEING: Amendment 39-6907. Docket No. 90-NM-153-AD. \n\n\tApplicability: Model 747-400 series airplanes, listed in Boeing Service Bulletin 747-26- 2138, Revision 1, dated March 1, 1990, and Boeing Service Bulletin 747-26-2141, Revision 1, dated July 12, 1990, certificated in any category. \n\n\tCompliance: Required within the next 12 months after the effective date of this AD, unless previously accomplished. \n\n\tTo preclude cross connection of fire extinguishing wiring during maintenance, accomplish the following: \n\n\tA.\tFor airplanes identified in Boeing Service Bulletin 747-26-2138, Revision 1, dated March 1, 1990: Modify the engine fire extinguishing system in accordance with that service bulletin. \n\n\tB.\tFor airplanes identified in Boeing Service Bulletin 747-26-2141, Revision 1, dated July 12, 1990: Modify the fire control module in accordance with that service bulletin. \n\n\tC.\tAn alternate means of compliance or adjustment of the compliance time, which provides an acceptable level of safety, may be used when approved by the Manager, Seattle Aircraft Certification Office (ACO), FAA, Transport Airplane Directorate. \n\n\tNOTE: The request should be submitted directly to the Manager, Seattle ACO, and a copy sent to the cognizant FAA Principal Inspector (PI). The PI will then forward comments or concurrence to the Seattle ACO. \n\n\tD.\tSpecial flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes to a base in order to comply with the requirements of this AD. \n\n\tAll persons affected by this directive who have not already received the appropriate service documents from the manufacturer may obtain copies upon request to Boeing Commercial Airplane Group, P.O. Box 3707, Seattle, Washington 98124. These documents may be examined at the FAA, Northwest Mountain Region, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, Washington. \n\n\tThis amendment (39-6907, AD 91-05-04) becomes effective on March 25, 1991.
98-06-05: This amendment adopts a new airworthiness directive (AD) that applies to Industrie Aeronautiche e Meccaniche (I.A.M.) Model Piaggio P-180 airplanes that are equipped with a Rockwell Collins APS-65 autopilot system that incorporates an APC-65A autopilot computer. This AD requires incorporating airplane flight manual (AFM) and pilot s operating handbook (POH) supplements that include revised autopilot emergency disengagement procedures. This AD is the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for Italy. The actions specified by this AD are intended to prevent pilot difficulty in disengaging the autopilot during flight, which could result in the pilot s lack of proper attention to critical flight tasks due to the increased pilot workload with possible consequent loss of airplane controllability.
2021-15-52: The FAA is adopting a new airworthiness directive (AD) for various restricted category helicopters originally manufactured by Bell Textron Inc. This AD was prompted by a fatal accident in which an outboard main rotor hub strap pin (pin) sheared off during flight, resulting in the main rotor blade and the main rotor head detaching from the helicopter. This AD requires removing certain pins from service and prohibits installing those pins on any helicopter. The FAA previously sent an emergency AD to all known U.S. owners and operators of these restricted category helicopters and is now issuing this AD to address the unsafe condition on these products.
2011-15-09: We are adopting a new airworthiness directive (AD) for the products listed above that would [[Page 42034]] supersede an existing AD. This AD results from mandatory continuing airworthiness information (MCAI) originated 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: Two cases of the main landing gear (MLG) alternate extension system (AES) cam mechanism failure were found during line checks. The cam mechanism operates the cable to open the MLG door and releases the MLG uplock in sequence. In the case where it is necessary to deploy the MLG using the AES, the failure of the MLG AES cam mechanism on one side will lead to an unsafe asymmetrical landing configuration. * * * * * The unsafe condition is possible loss of control during landing. This AD requires actions that are intended to address the unsafe condition described in the MCAI.
92-10-12: 92-10-12 BEECH AIRCRAFT CORPORATION: Amendment 39-8246. Docket No. 91-CE-96-AD. Supersedes AD 91-18-11; Amendment 39-8014. Applicability: The following model and serial number airplanes, certificated in any category: Model Serial Numbers 200 and B200 BB-2 and BB-6 through BB-1404 200C and B200C BL-1 through BL-72 and BL-124 through BL-137 200CT and B200CT BN-1 through BN-4 200T and B200T BT-1 through BT-33 A100-1 (U-21J) BB-3, BB-4, and BB-5 A200 (C-12A) BC-1 through BC-75 A200 (C-12C) BD-1 through BD-30 A200C (UC-12B) BJ-1 through BJ-66 A200CT (C-12D) BP-1, BP-22, and BP-24 through BP-51 A200CT (FWC-12D) BP-7 through BP-11 A200CT (RC-12D) GR-1 through GR-13 A200CT (C-12F) BP-52 through BP-71 A200CT (RC-12G) FC-1, FC-2, and FC-3 A200CT (RC-12H) GR-14 through GR-19 B200C (C-12F) BL-73 through BL-112 and BL-118 through BL-123 B200C (UC-12F) BU-1 through BU-10 B200C (RC-12F) BU-11 and BU-12 B200C (UC-12M) FC-1, FC-2, and FC-3 B200C (RC-12M) BV-11 and BV-12 Compliance: Required within the next 50 hours time-in-service after the effective date of this AD, unless already accomplished (superseded AD 91-18-11). To prevent separation of the aft cowling doors, which could result in occupant injury if decompression or structural damage occurs, accomplish the following: (a) Inspect and modify the aft engine cowling doors of both engine nacelles in accordance with the ACCOMPLISHMENT INSTRUCTIONS section of Beech Mandatory Service Bulletin (SB) No. 2416, Revision I, dated December 1991. (b) If the aft engine cowling doors of both nacelles have been inspected and modified in accordance with the original issue of Beech SB No. 2416, dated July 1991, (as required by superseded AD 91-18-11), then no further action is required by this AD. NOTE 1: The configuration of certain early model airplanes made compliance with the original issue of Beech SB No. 2416 impossible as required by superseded AD 91-18-11. Service (SVR) 025 was approved as an alternative method of compliance for portions of superseded AD 91-18-11 on some of the affected early model airplanes. (c) Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate the airplane to a location where the requirements of this AD can be accomplished. (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, Wichita Aircraft Certification Office, FAA, 1801 Airport Road, Mid-Continent Airport, Wichita, Kansas 67209. The request should be forwarded through an appropriate FAA Maintenance Inspector, who may add comments and then send it to the Manager, Wichita Aircraft Certification Office. NOTE 2: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Wichita Aircraft Certification Office. (e) The inspections and modifications required by this AD shall be done in accordance with Beech Mandatory Service Bulletin No. 2416, Revision I, dated December 1991. This incorporation by reference was approved by the Director of the Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR Part 51. Copies may be obtained from the Beech Aircraft Corporation, P.O. Box 85, Wichita, Kansas 67201-0085. Copies may be inspected at the FAA, Central Region, Office of the Assistant Chief Counsel, Room 1558, 601 E. 12th Street, Kansas City, Missouri, or at the Office of the Federal Register, 1100 L Street, NW; Room 8401, Washington, DC. (f) This amendment (39-8246) supersedes AD 91-18-11, Amendment 39-8014. (g) This amendment (39-8246) becomes effective on June 12, 1992.
2004-07-23: This amendment adopts a new airworthiness directive (AD), applicable to certain Saab Model SAAB SF340A and SAAB 340B series airplanes, that requires replacement of certain assistor springs and bearings with certain new assistor springs and bearings. This action is necessary to prevent possible collapse of a main landing gear upon landing and consequent reduced controllability of the airplane. This action is intended to address the identified unsafe condition.
90-24-07: 90-24-07 MCDONNELL DOUGLAS HELICOPTER COMPANY (MDHC): Amendment 39-6784. Docket Number 90-ASW-10. Applicability: All MDHC Model 369D, 369E, and 369F/FF series helicopters certificated in any category. \n\n\tCompliance: Required as indicated, unless previously accomplished. \n\n\tTo prevent possible failure of the main rotor transmission drive assembly, which could result in loss of control of the helicopter, accomplish the following: \n\n\t(a)\tWithin the next 300 hours' time in service after the effective date of the AD or at the next annual inspection or the next time the transmission is removed, whichever occurs first, after the main rotor transmission is removed inspect the MS21250-04036 bolts which retain the debris cover, P/N 369D25174. Remove any bolts with the head inscription shown as unacceptable in Figure 1, and replace with MS21250-04038 bolts, which have a length of 2.887 plus/minus 0.010 inch. \n\n\tNOTE: MDHC Service Information Notice (SIN) DN-166.1, EN-57.1, and SINFN-45.1, dated March 14, 1990, or later revisions pertain to this subject. \n\n\t(b)\tInspect the thread protrusion of all bolts. Remove any bolt which does not protrude through the H14-4 nut for a length equivalent to two full threads (0.071 inch minimum), including the chamfer. Replace removed bolts with MS21250-04038 bolts. Torque the bolts to 50-70 inch pounds. Verify that the bolts protrude through the nut for a length equivalent to two full threads (0.071 inch minimum), including the chamfer. If more than four threads protrude through the nut, add AN960C416L or AN960C416 washers under the nut as required. Remove and reinstall parts in accordance with the manufacturer's instructions. \n\n\t(c)\tApply a white dot to the main transmission data plate to indicate that the transmission has been inspected and reworked in accordance with the manufacturer's instructions, and record compliance with this AD in the rotorcraft log book. \n\n\t(d)\tIn accordance with FAR Sections 21.197 and21.199, flight is permitted to a base where the requirements of this AD may be accomplished. \n\n\t(e)\tAn alternate method of compliance or adjustment of the compliance time which provides an equivalent level of safety, may be used when approved by the Manager, Los Angeles Aircraft Certification Office, ANM-100L, FAA, Northwest Mountain Region, 3229 East Spring Street, Long Beach, California 90806-2425. \n\n\tThis amendment (39-6784, AD 90-24-07) becomes effective on December 10, 1990. \n\n\n\n\t\t\tFigure 1. Inspection/Definition of Bolt Heads.
2011-14-08: We are adopting a new airworthiness directive (AD) for the products listed above, except for those that are currently affected by similar action through any of five ADs applicable to Boeing products. This AD requires an inspection/records check to determine the manufacturer and part number of the oxygen mask assemblies installed, an inspection to determine the manufacturing date and modification status if certain oxygen mask assemblies are installed, and corrective action for certain oxygen mask assemblies. This AD was prompted by a report that several oxygen mask assemblies with broken in-line flow indicators were found following a mask deployment. We are issuing this AD to prevent the in-line flow indicators of the oxygen mask assembly from fracturing and separating, which could inhibit oxygen flow to the masks. This condition could consequently result in occupants developing hypoxia following a depressurization event.
2021-15-14: The FAA is adopting a new airworthiness directive (AD) for various restricted category helicopters, originally manufactured by Bell Textron Inc. (Bell). This AD was prompted by multiple events involving failure of the tail boom attach structure including the bolts. This AD requires revising the existing Rotorcraft Flight Manual (RFM) for your helicopter to incorporate pre-flight checks; removing paint and sealant, and cleaning; repetitive inspections of structural components that attach the tail boom to the fuselage; and depending on the outcome of the inspections, repairing or replacing components, or re-bonding the structure. The FAA is issuing this AD to address the unsafe condition on these products.
2004-07-13: The FAA is adopting a new airworthiness directive (AD) for General Electric Company (GE) CF6-80C2 series turbofan engines. This AD requires replacing certain high pressure turbine (HPT) stage 1 disks at or before reaching a new reduced life cycle limit. This AD is prompted by an updated low-cycle-fatigue (LCF) analysis of the HPT stage 1 disk. We are issuing this AD to prevent LCF cracking and failure of the HPT stage 1 disk due to exceeding the life limit, which could result in an uncontained engine failure and damage to the airplane.
76-16-02: 76-16-02 AIRBORNE MANUFACTURING COMPANY: Amendment 39-2685. Applies to Models 113A, 200CC, 200CW, 220CC, 220CW, 221CC, 222CW engine driven pumps. Compliance is required within the next 25 hours time in service, or by next annual inspection, whichever occurs first, after the effective date of this AD, unless already accomplished. To prevent loss of vacuum pressure with the accompanying loss of directional or attitude gyro function accomplish the following: Remove from service and replace with another serviceable approved vacuum pump all Airborne engine driven vacuum pumps manufactured prior to 1966 for which the model and serial numbers are listed below: Model Year Serial Numbers 113A 1960 1D1 thru 12D1199 inclusive 1961 1E1 thru 12E2288 inclusive 1962 1F1 thru 12F3411 inclusive 1963 1G1 thru 12G4230 inclusive 1964 1H1 thru 12H1688 inclusive 1965 1J1 thru 12J210 inclusive 200CC, 200CW 1963 5G43 thru 12G903 inclusive 1964 1H1 thru 12H5623 inclusive 1965 1J1 thru 12J9397 inclusive 220CC, 220CW 1964 2H1 thru 12H680 inclusive 1965 1J1 thru 4J393 inclusive 221CC, 222CW 1965 3J1 thru 12J371 inclusive Airborne Manufacturing Company Service Letter No. 16, dated January 29, 1976, also pertains to this subject. This amendment becomes effective August 11, 1976.
2021-15-06: The FAA is adopting a new airworthiness directive (AD) for certain Bell Helicopter Textron Canada Limited (now Bell Textron Canada Limited) Model 206A, 206B, 206L, 206L-1, 206L-3, and 206L-4 helicopters. This AD was prompted by a report that a certain tail rotor disc assembly, sold as an alternate part, does not conform to the approved configuration. This AD requires determining if an affected part is installed (by doing a maintenance records check or inspection), and if an affected part is found, replacement with a non-affected part. The FAA is issuing this AD to address the unsafe condition on these products.
91-06-09: 91-06-09 GLASFLUGEL: Amendment 39-6920. Docket No. 90-CE-37-AD. Applicability: Models H301 Libelle, H301B Libelle, Standard Libelle, Standard Libelle 201, Standard Libelle 201B, Standard Libelle 203, Kestrel 604, and BS-1 Gliders (all serial numbers), certificated in any category. Compliance: Required as indicated after the effective date of this AD, unless already accomplished. To prevent failures in the rudder control system, accomplish the following: (a) Within the next 25 hours time-in-service (TIS) after the effective date of this AD, unless already accomplished, replace all DIN specification 055, 6 by 7 inch rudder cables with a diameter of 2.55 mm (.098 in.) having a hemp core, with a 7 by 7, 3/32 inch cable, manufactured in accordance with MIL-W-83420D or MIL-W-1511A, with cable connections constructed in accordance with Actions 2 of Hansjorg Streifeneder Technical Note Nos. 201-26, 301-33, 401- 20, 501-4, all dated March 15, 1987. NOTE: The replacement cables may have been installed pursuant to superseded AD 71- 16-06, Amendment 39-1253, or superseded AD 88-07-05, Amendment 39-5865. (b) Within the next 100 hours TIS after the replacement of the cables required in paragraph (a) of this AD or within the next 100 hours after the effective date of this AD, whichever is applicable, and thereafter at intervals not to exceed 100 hours TIS, visually inspect the rudder cables for wear, fraying, corrosion, twisting or other damage. If damaged cables are found, prior to further flight, replace the damaged cables with cables and connections as specified in paragraph (a) of this AD. (c) An alternative method of compliance or adjustment of the initial or repetitive compliance times that provides an equivalent level of safety may be approved by the Manager, Brussels Aircraft Certification Office, Europe, Africa, and Middle East Office, FAA, c/o American Embassy 15 Rue de la Loi, B-1000 Brussels, Belgium. The request should be forwarded through an appropriate FAA Maintenance Inspector, who may add comments and then send it to the Manager, Brussels Aircraft Certification Office. (d) All persons affected by this directive may obtain copies of the documents referred to herein upon request to Hansjorg Streifeneder, Glasflaser Flugzeug Service GmbH, Hofener Weg, D-7431 Grabenstetten, Federal Republic of Germany; or may examine these documents at the FAA, Central Region, Office of the Assistant Chief Counsel, Room 1558, 601 E. 12th Street, Kansas City, Missouri 64106. Airworthiness Directive 91-06-09 supersedes AD 71-16-06, Amendment 39-1253, and AD 88-07-05, Amendment 39-5865. This amendment (39-6920, AD 91-06-09) becomes effective on April 8, 1991.
2021-15-03: The FAA is adopting a new airworthiness directive (AD) for certain Gulfstream Aerospace Corporation (Gulfstream) Model GVII-G500 airplanes. This AD results from flap yoke fittings with design features that cause decreased fatigue life. This AD requires replacing the flap inboard and outboard yoke fitting assemblies and establishing a 20,000 flight cycle life limit for the fittings. The FAA is issuing this AD to address the unsafe condition on these products.
77-07-06: 77-07-06 BEECH: Amendment 39-2863. Applies to Models C90 (Serial Numbers LJ- 640 thru LJ-716), and E90 (Serial Numbers LW-120 thru LW-220, LW-222 and LW-223) airplanes. To assure adequate clearance between the left hand rudder cable and the electrical components on the relay panel located under the left hand cockpit floorboard, accomplish the following: A) Prior to further flight inspect the left hand rudder control cable under the left hand cockpit floorboard in accordance with Steps 1 through 4 of Beechcraft Service Instructions 0896, or later approved revisions, to determine that at least 3/4 inch clearance exists between the rudder control cable and all electrical components located on the relay panel. B) If the inspection required by Paragraph A shows that the clearance is less than 3/8 inch, prior to further flight: 1. If possible, relocate the relay panel to provide at least 3/4 inch clearance, or if the relay panel cannot be relocated to provide at least 3/4 inch clearance, modify the panel in accordance with Steps 6 through 13 of Beechcraft Service Instructions 0896, or later approved revisions, and 2. Inspect the rudder cable to determine if it has been damaged by coming in contact with the electrical components. If the cable has been damaged, install a new cable, Beech P/N 50-524438-17, or an equivalent cable fabricated in accordance with acceptable FAA standards (AC 43.13-1A). C) If the inspection required by Paragraph A shows that the clearance is between 3/8 and 3/4 inches, within 25 hours' time in service after the effective date of this AD, accomplish the requirements of Paragraphs B(1) and B(2). D) If the inspection required by Paragraph A shows that the clearance is 3/4 inch or more, make an entry in the aircraft's maintenance records indicating that this AD has been accomplished and the airplane may be returned to service. E) Airplanes may be flown in accordance with FAR 21.197 to a location where the needed electrical system modification or rudder cable replacement required by this AD may be accomplished. Prior to authorizing a flight under FAR 21.197, the FAA District Office involved should contact the Chief, Engineering and Manufacturing Branch, FAA, Central Region, for appropriate operating limitations. F) 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 April 11, 1977, to all persons except those to whom it has already been made effective by air mail letter from the Federal Aviation Administration dated March 14, 1977.
2021-13-16: The FAA is adopting a new airworthiness directive (AD) for certain General Electric Company (GE) GEnx-2B67, GEnx-2B67/P, and GEnx- 2B67B model turbofan engines. This AD was prompted by a report of a crack in the lower fuel manifold causing fuel leakage. This AD requires an ultrasonic inspection (USI) or a fluorescent penetrant inspection (FPI) of the lower fuel manifold. Depending on the results of the USI or FPI, this AD requires replacement of the lower fuel manifold with a part eligible for installation. The FAA is issuing this AD to address the unsafe condition on these products.
2004-07-01: This amendment adopts a new airworthiness directive (AD) that is applicable to certain Bombardier Model CL-600-2C10 (Regional Jet Series 700 & 701) and CL-600-2D24 (Regional Jet Series 900) series airplanes. This action requires revising the airplane flight manual to advise the flightcrew to monitor the fuel quantity in the center fuel tank throughout the flight. This action also requires repetitive tests to detect a fuel leak between the wing fuel tanks and the center fuel tank; and further related investigative and corrective actions, if necessary. For certain airplanes, this AD also requires installation of flexible hoses and brackets in the fuel feed system. This action is necessary to detect and correct cracking in the primary fuel ejector. Cracking in the primary fuel ejector could cause fuel leakage into the center fuel tank, which could result in engine shutdown during flight. This action is intended to address the identified unsafe condition.
2021-14-19: The FAA is adopting a new airworthiness directive (AD) for certain International Aero Engines AG (IAE) V2500 model turbofan engines. This AD was prompted by a review of investigative findings from an event involving an uncontained failure of a high-pressure turbine (HPT) 1st-stage disk that resulted in high-energy debris penetrating the engine cowling. This AD requires performance of an ultrasonic inspection (USI) of the HPT 1st-stage disk and HPT 2nd-stage disk and, depending on the results of the inspections, replacement of the HPT 1st-stage disk or HPT 2nd-stage disk with a part eligible for installation. The FAA is issuing this AD to address the unsafe condition on these products.
91-08-07: 91-08-07 TEXTRON LYCOMING: Amendment 39-6962. Docket No. 91-ANE-08. Applicability: TIO-360 Series engines with serial numbers up to L-215-64A inclusive; TIO-540 Series engines with serial numbers up to L-9245-61/61A inclusive, except TIO-540-AE2A engines for which the requirements of AD 89-15-10 are met; LTIO-540 Series engines with serial numbers up to L-2911-68A inclusive; TIGO-541 Series engines with serial numbers up to L-780-62 inclusive; all TIO-541 Series engines; and all TIVO-540 Series engines. Also applies to overhauled and remanufactured engines of these models shipped from the factory prior to November 15, 1990, and to any Textron Lycoming engine that has been modified to use a turbocharger and that has the fuel pump vent vented to the induction system. Compliance: Required within the next 15 hours in service for paragraph (a) and within the next 50 hours in service for paragraph (b), after the effective date of this AD, unless already accomplished. To prevent engine power loss and possible loss of the aircraft, accomplish the following: (a) Perform a fuel leak check at the fuel pump vent hose fitting as follows: (1) Disconnect the fuel pump vent hose at the engine fuel pump. Then proceed to turn on the aircraft boost pump and visually inspect for any fuel draining out from the engine pump vent port. (2) Prior to further flight, remove and replace with a serviceable pump, engine fuel pumps which exhibit leakage. Repeat the leak check following pump replacement to verify no fuel is passing through the fuel pump vent port. (3) Reconnect the fuel pump vent hose at the engine fuel pump. (b) Inspect and replace if necessary, the fuel pump vent restrictor fitting as follows: (1) Remove fitting from the pump vent port and measure the orifice opening using an appropriate size wire gauge or drill bit. The orifice diameter must be within .014-.020 inch and the fitting must have the code letter "R" impression stamped on a flat surface. (2) Prior to further flight, replace any restrictor fitting that has an orifice diameter out of limits, or if no restrictor orifice exists. Install a new or serviceable restrictor fitting with a proper size orifice, and identified with the letter "R", using Loctite hydraulic sealant or equivalent on the pipe threads. (3) Ensure that the orientation of the reinstalled fitting is the same as the original fitting. (4) Reconnect the pump vent line. NOTE: Textron Lycoming Service Bulletin Nos. 494 and 497 and Service Instruction No. 1446 pertain to this subject. Fuel pump vent fittings supplied by Textron Lycoming with the proper size orifice are identified by the letter "R" stamped on each fitting. Engine Models TIO-541 and TIVO-540 series are not specified in the service bulletins, for these engines the engine driven pump and vent fitting were furnished by the aircraft manufacturer. (c) Aircraft may be ferried in accordance with the provisions of FederalAviation Regulations 21.197 and 21.199 to a base where the AD can be accomplished. (d) Upon submission of substantiating data by an owner or operator through an FAA Inspector (maintenance, avionics, or operations, as appropriate), an alternate method of compliance with the requirements of this AD or adjustments to the compliance schedule specified in this AD may be approved by the Manager, New York Aircraft Certification Office, Engine & Propeller Directorate, Aircraft Certification Service, FAA, New England Region, Room 202, 181 South Franklin Avenue, Valley Stream, New York 11581. All persons affected by this directive who have not already received the appropriate service information from the manufacturer may obtain copies upon request to Textron Lycoming/Subsidiary of Textron Inc., 652 Oliver Street, Williamsport, Pennsylvania 17701. This information may be examined at the FAA, New England Region, Office of the Assistant Chief Counsel, Room 311, 12 New England Executive Park, Burlington, Massachusetts. This amendment becomes effective on May 6, 1991.
2011-12-16: We are superseding an existing emergency airworthiness directive (EAD) for the specified Schweizer model helicopters that was previously sent to all known U.S. owners and operators. That EAD currently requires removing each locknut and verifying sufficient drag torque and retorquing, or if the locknut does not have sufficient drag torque, replacing the locknut with an airworthy locknut. This AD retains the existing EAD requirements but also requires within a specified time, modifying the expandable bolts and installing a cotter pin. This AD is prompted by a locknut working loose from a bolt attaching the tailboom support strut at the aft cluster fitting because the locknut installed on the expandable bolt did not have the proper threads. We are issuing this AD to modify each expandable bolt to allow adding a cotter pin to prevent the strut and driveshaft separating from the helicopter and subsequent loss of control of the helicopter.
2011-11-03: We are adopting a new airworthiness directive (AD) for the products listed above. This AD results from mandatory continuing airworthiness information (MCAI) issued by the aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as: During a production process review, a deviation in hardening of certain Part Number (P/N) 944072 washers has been detected, which exceeds the hardness of the design specification. The affected washers are part of the magneto ring flywheel hub installation and have been installed on a limited number of engines. No defective washers have been shipped as spare parts. This condition, if not corrected, could lead to cracks in the washer, loosening of the magneto flywheel hub and consequent ignition failure, possibly resulting in damage to the engine, in- flight engine shutdown and forced landing, damage to the aeroplane and injury to occupants. ThisAD requires actions that are intended to address the unsafe condition described in the MCAI.
98-04-14: This amendment adopts a new airworthiness directive (AD) that is applicable to Pratt & Whitney PW4164 and PW4168 series turbofan engines. This action requires initial and repetitive inspections for loose or broken front pylon mount bolts, replacement, if necessary, with new bolts, and establishment of a new cyclic life limit. This amendment is prompted by new flight test data that indicate higher than predicted loads. The actions specified in this AD are intended to prevent front pylon mount bolt failure, which could result in engine separation from the aircraft.