Results
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Required within the next 50 hours time-in-service after the effective date of this AD, unless already accomplished (superseded AD 91-18-11).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inspected and modified in accordance with the original issue of Beech SB No. 2416, dated July 1991, (as required by superseded AD 91-18-11), then no further action is required by this AD.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of certain early model airplanes made compliance with the original issue of Beech SB No. 2416 impossible as required by superseded AD 91-18-11. Service (SVR) 025 was approved as an alternative method of compliance for portions of superseded AD 91-18-11 on some of the affected early model airplanes.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.