Results
74-09-03: 74-09-03 AVCO LYCOMING: Amendment 39-1823. Applies to all Avco Lycoming T5309C, T5311A and T5311B turboshaft engines. Compliance required, unless already accomplished, prior to the accumulation of 100 hours in service after the effective date of this AD. To prevent possible compressor disc or impeller assembly failures leading to partial or complete loss of engine power, remove and replace the second, third, fourth, and fifth stage compressor rotor discs and centrifugal impeller assemblies in accordance with the table below. COMPONENT - 2nd Stage Compressor Rotor Disc; REMOVE P/N - 1-100-239-01; INSTALL P/N - 1- 100-239-04 or later FAA approved P/N COMPONENT - 3rd Stage Compressor Rotor Disc; REMOVE P/N - 1-100-242-01 or 1-100-242-06; INSTALL P/N - 1-100-242-09 or later FAA approved P/N COMPONENT- 4th Stage Compressor Rotor Disc; REMOVE P/N - 1-100-244-01 or 1-100-244-02; or 1-100-244-04 or 1-100-244-06; INSTALL P/N - 1-100-244-08 or later FAA approved P/N COMPONENT- 5th Stage Compressor Rotor Disc; REMOVE P/N - 1-100-417-01 or 1-100-417-02; INSTALL P/N - 1-100-417-05 or later FAA approved P/N COMPONENT - Centrifugal Impeller Assembly; REMOVE P/N - 1-100-440-04 or 1-100-440-07; INSTALL P/N - 1-100-440-07; Rev. B or later FAA approved P/N Upon submission of substantiating data through an FAA Maintenance Inspector, the Chief, Engineering and Manufacturing Branch, FAA, New England Region, may adjust the compliance time. NOTE: (Avco Lycoming Service Bulletin Number 0033 pertains to this subject.) This amendment becomes effective May 2, 1974.
2012-06-24: We are adopting a new airworthiness directive (AD) for Sikorsky Aircraft Corporation (Sikorsky) Model S-92A helicopters. This AD was prompted by the discovery of tail rotor blade assemblies (blades) manufactured with mislocated aluminum wire mesh, leaving portions of the graphite torque tube (spar) region unprotected from a lightning strike. The actions are intended to detect mislocated blade wire mesh and to prevent spar delamination, loss of the blade tip cap during a lightning strike, blade imbalance, loss of a blade, and subsequent loss of control of the helicopter.
2012-06-10: We are adopting a new airworthiness directive (AD) for certain Airbus Model A330-200, A330-300, A340-500, and A340-600 series airplanes. This AD requires a detailed inspection for cracked and missing nuts, and replacement of cracked or missing nuts with new nuts having the same part number. This AD was prompted by reports of cracked nuts detected during production. We are issuing this AD to detect and correct cracked or missing nuts, and replace all affected nuts in multiple locations (including fuel tank areas) that could result in reduced structural integrity of the airplane.
2012-06-23: We are superseding an existing airworthiness directive (AD) for all Rolls-Royce plc (RR) RB211-Trent 875-17, RB211-Trent 877-17, RB211-Trent 884-17, RB211-Trent 884B-17, RB211-Trent 892-17, RB211- Trent 892B-17, and RB211-Trent 895-17 turbofan engines. That AD currently requires initial and repetitive ultrasonic inspections (UIs) of certain low-pressure (LP) compressor blades identified by serial number (S/N). This AD requires the same actions but expands the population of blades. This AD was prompted by RR concluding that additional blades affected must be inspected. We are issuing this AD to prevent LP compressor blades from failing due to blade root cracks, which could lead to uncontained engine failure and damage to the airplane.
59-12-03: 59-12-03 VICKERS: Applies to All Viscount 745D and 810 Series Aircraft. Compliance required by October 31, 1959. Two cases have occurred of the Graviner fire extinguisher cartridge types A216 and A217 failing to operate at altitudes exceeding 20,000 feet. The failures were due to a combination of altitude and temperature affecting the gunpowder charge. To preclude such failures the Graviner Manufacturing Company has issued Modification AU 393 introducing improved firing units type A716 (replacing type A216) and type A717 (replacing A217). The new units have a modified bridge wire arrangement and may be identified by a blue plastic band around the neck of the cartridge. The British Air Registration Board considers the embodiment of this modification mandatory. (Graviner Manufacturing Company Modification No. AU 393 and Vickers-Armstrongs PTL205 and Modification D.2926 (700 Series) and PTL 73 and Modification FG.1695 (800/810 Series) covers this subject.)
2012-07-01: We are adopting a new airworthiness directive (AD) for Agusta S.p.A. (Agusta) Model AB412 helicopters with certain tail rotor blades (blades) installed. This AD requires, before further flight, removing and replacing each affected blade with an airworthy blade. This AD is prompted by incidents where a blade tip weight separated from a blade in flight on other model helicopters with common part-numbered blades. It has been determined that this unsafe condition may also exist on the specified Agusta model helicopters. The actions specified in this AD are intended to prevent loss of the blade tip weight, loss of a blade, and subsequent loss of control of the helicopter.
74-10-04: 74-10-04 PRATT & WHITNEY: Amendment 39-1831. Applies to all Pratt & Whitney Model JT9D-3A and JT9D-7 turbofan engines. Compliance required not later than February 1, 1975. 1. To prevent the possibility of internal main gearbox fires in the event of an internal gearbox failure, rework the main gearbox in accordance with Pratt & Whitney Service Bulletin No. 4043, dated February 5, 1973, or later Federal Aviation Administration approved revisions. 2. To prevent leakage of oil around carbon face seals, replace present seal assemblies with the redesigned carbon face seal assemblies per Pratt & Whitney Service Bulletin No. 3902, dated August 8, 1972, or later Federal Aviation Administration approved revisions or Federal Aviation Administration approved equivalent. 3. Equivalent methods of compliance to the requirements of paragraph 2 above must be approved by the Chief, Engineering and Manufacturing Branch, Federal Aviation Administration, New England Region. Themanufacturer'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 the Chief Engineer, Pratt and Whitney Aircraft, Division of United Aircraft Corporation, 400 Main Street, East Hartford, Connecticut 06108. These documents may also be examined at the Office of the Regional Counsel, New England Region, FAA, 12 New England Executive Park, Burlington, Massachusetts 01803 and at FAA Headquarters, 800 Independence Avenue, S. W., Washington, D. C. A historical file on this AD which includes the incorporated material in full is maintained by the FAA at its headquarters in Washington, D. C., and at the New England Regional Office in Burlington, Massachusetts. This amendment becomes effective May 14, 1974.
98-20-35: This amendment supersedes an existing airworthiness directive (AD), applicable to all IAI, Ltd., Model 1121, 1121A, 1121B, 1123, 1124, and 1124A series airplanes, that currently requires repetitive inspections of the trim actuator of the horizontal stabilizer to verify jackscrew integrity and to detect excessive wear of the tie rod, and replacement of the actuator or tie rod, if necessary. That AD also provides for optional terminating action for the repetitive inspections. This amendment requires accomplishment of the previously optional terminating action. This amendment is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified by this AD are intended to prevent failure of the trim actuator of the horizontal stabilizer due to failure of the jackscrews, which could result in reduced controllability of the airplane. The incorporation by reference of certain publications was approved previously by the Director of the Federal Register as of April 10, 1998 (63 FR 11106, March 6, 1998).
76-02-06: 76-02-06 BELL: Amendment 39-2502. Applies to Bell Models 212, 204B, and 205A-1 helicopters certificated in all categories. Compliance required as indicated after receipt of this AD. Prior to next flight, remove the main rotor blades having the following Serial Numbers: A2-28211, A2-29920, A2-29325, A2-28198, A2-27872, A2-28195, A2-29315, A2-29919, A2- 29334, A2-29915, A2-28016, A2-27961, A2-27982, A2-27963, A2-28023, A2-28015, A2-28019, A2-27968, A2-27967, A2-28020, A2-03642, A2-03646, and A2-03643. This supersedes airmail letter dated December 24, 1975, and Amendment 39-2488 (41 F.R. 1738), AD 76-01-05. This amendment is effective February 1, 1976, and was effective upon receipt for all recipients of the letter dated January 8, 1976, which contained this amendment.
2012-05-06: We are superseding an existing airworthiness directive (AD) for all Lockheed Martin Corporation/Lockheed Martin Aeronautics Company Model L-1011-385-1, L-1011-385-1-14, and L-1011-385-1-15 airplanes. That AD currently requires implementation of a Supplemental Inspection Document (SID) program of structural inspections to detect fatigue cracking, and repair if necessary, to ensure continued airworthiness of these airplanes as they approach the manufacturer's original fatigue design life goal. This new AD adds Model L-1011-385-3 airplanes to the applicability, changes certain inspection thresholds, adds three new structurally significant details (SSDs), and removes an SSD that has been addressed by a different AD. This AD was prompted by an evaluation by the manufacturer of usage and flight data that provided additional information about certain SSDs where fatigue damage is likely to occur. We are issuing this AD to prevent fatigue cracking that could compromise the structural integrity of these airplanes.