Results
2001-14-07: This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 747 series airplanes, that requires repetitive high frequency eddy current inspections to find cracking of the bulkhead frame support at body station 2598 under the hinge support fittings of the horizontal stabilizer, and repair if cracking is found. These actions are necessary to find and fix fatigue cracking in the frame support, which could result in inability of the structure to carry horizontal stabilizer flight loads and reduced controllability of the horizontal stabilizer. This action is intended to address the identified unsafe condition.
78-16-05: 78-16-05 PRATT & WHITNEY AIRCRAFT: Amendment 39-3274. Applies to all Pratt & Whitney Aircraft JT9D turbofan engines not incorporating an annular strainer element, in accordance with Pratt & Whitney Service Bulletin 4860 dated March 16, 1978, or later FAA approved revision, in the No. 4 bearing compartment. Compliance is required as indicated. To preclude failures of sixth stage turbine disks due to a plugged No. 4 bearing compartment oil scavenge tube, inspect the inside of the No. 4 bearing compartment sump for coke in accordance with the provisions of Pratt & Whitney Alert Service Bulletin No. 4826, dated October 17, 1977, or later FAA approved revision, in accordance with the following schedule: Engines with No. 4 bearing compartments having more than 6000 hours time in service since new or the last cleaning per ASB 4826: 1. Must have a daily visual tailpipe check for oil leakage from the No. 4 bearing compartment. If leakage is noted, the compartment must be inspected prior to further flight. The daily visual check may be discontinued after accomplishing the compartment inspection noted below. A flight crewmember may perform the daily check. NOTE: For the purpose of this AD, compliance with the daily visual check may be shown by recording accomplishment in accordance with FAR 121.380 or by amending the manual required by FAR 121.133 to include the check. 2. Must have the compartment inspected within the next 1500 hours time in service after the effective date of this AD, unless already accomplished, and every 5000 hours time in service thereafter. Engines having unacceptable coke formation in the forward portion of the No. 4 compartment sump area, as defined in Figure 2 of ASB 4826, must have the sump and compartment oil scavenge tube cleaned in accordance with the JT9D Engine Manual, P/N 646028, Section 72-53-00, prior to further flight. Upon request of the operator, an equivalent method of compliance with the requirements of this AD may be approved by the Chief, Engineering and Manufacturing Branch, Federal Aviation Administration, New England Region. Upon request of the operator, an FAA maintenance inspector, subject to prior approval of the Chief, Engineering and Manufacturing Branch, New England Region, may adjust the initial inspection interval specified in this AD to permit compliance at an established inspection period of the operator if the request contains substantiating data to justify the increase for that operator. 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 Pratt & Whitney Aircraft, Division of United Technologies Corporation, 400 Main Street, East Hartford, Connecticut 06108. These documents may also be examined at the Federal Aviation Administration, New England Region, 12 New England Executive Park, Burlington, Massachusetts, 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 FAA, New England Region Headquarters, Burlington, Massachusetts. This amendment becomes effective September 12, 1978.
2016-22-10: We are adopting a new airworthiness directive (AD) for certain Turbomeca S.A. Arriel 1, 1A, 1A1, 1A2, 1B, 1B2, 1C, 1C1, 1C2, 1D, 1D1, 1E, 1E2, 1K1, 1S, and 1S1 turboshaft engines. This AD requires removing the centrifugal impeller and replacing with a part eligible for installation. This AD was prompted by an anomaly that occurred during the grinding operation required by modification TU376, which increases the clearance between the rear curvic coupling of the centrifugal impeller and the fuel injection manifold. We are issuing this AD to prevent failure of the centrifugal impeller, uncontained centrifugal impeller release, damage to the engine, and damage to the helicopter.
2010-18-52: This document publishes in the Federal Register an amendment adopting Emergency Airworthiness Directive (AD) 2010-18-52 which was sent previously to all known owners and operators of MD Helicopters, Inc. (MDHI) Model MD900 helicopters by individual letters. This AD requires visually inspecting the main rotor hub (hub) for a crack. If a crack is found, this AD requires, before further flight, replacing the unairworthy hub with an airworthy hub. Additionally, if a cracked hub is found, this AD requires reporting the finding to the Los Angeles Aircraft Certification Office within 10 days of finding the crack. This AD is prompted by two reports of cracks detected in the hub in the area near the flex beam bolt hole locations during maintenance on two MDHI Model MD900 helicopters. The actions specified by this AD are intended to detect a crack in the hub and prevent failure of the hub and subsequent loss of control of the helicopter.
47-10-30: 47-10-30 LOCKHEED: (Was Mandatory Note 33 of AD-763-3.) Applies to Model 49 Serials 2047 Up to and Including 2075 and to Serials Prior to 2047 Which Have Had 68092 Surge Box Flapper Valves Replaced by 285750 Valves in Accordance With Lockheed SI-15, Dated June 18, 1946. Compliance required prior to April 1, 1947. Replace fuel tank surge box flapper valves, LAC P/N 285750, with new type valve, LAC P/N 285750-600. (LAC Service Instructions 49/SI-15, revised August 10, 1946, and 49/SI-15A, revised August 3, 1946, or subsequent, cover this same subject.)
2001-14-11: This amendment adopts a new airworthiness directive (AD), applicable to all Boeing Model 747-100 and -200 series airplanes modified by Supplemental Type Certificate SA8622SW, that requires deactivation of the in-flight entertainment (IFE) system. This action is necessary to ensure that the flight crew is able to remove power from the IFE system when necessary. Inability to remove power from the IFE system during a non-normal or emergency situation could result in inability to control smoke or fumes in the airplane flight deck or cabin. This action is intended to address the identified unsafe condition.
2016-22-01: We are adopting a new airworthiness directive (AD) for Schempp-Hirth Flugzeugbau GmbH Models Discus-2a, Discus-2b, Discus-2c, Discus 2cT, Ventus-2a, and Ventus-2b gliders. 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 insufficient overlap of the airbrake panels. We are issuing this AD to correct the unsafe condition on these products.
2001-14-15: This amendment adopts a new airworthiness directive (AD), applicable to all Boeing Model 747-400 series airplanes modified by Supplemental Type Certificate (STC) SA8843SW, that requires modifying the passenger entertainment system (PES) installed by that STC and revising the Airplane Flight Manual. This action is necessary to ensure that the flight crew is able to remove electrical power from the PES when necessary and is advised of appropriate procedures for such action. Inability to remove power from the PES during a non-normal or emergency situation could result in inability to control smoke or fumes in the airplane flight deck or cabin. This action is intended to address the identified unsafe condition.
50-38-02: 50-38-02 BELL: (a) Applies to All Models 47B, 47B-S, 47B3, 47B3-S, 47D and 47D-S; (b) Applies to Model 47D1, Serial Numbers 145 Through 164, 174 Through 183. Compliance required before November 15, 1950. Service difficulties have been experienced involving fan bearing failure due to improper adjustment of the cooling fan belt. This allows the cooling fan to move forward and jam the cyclic controls. To prevent such failures, fan belt tension should be properly adjusted. In addition, a fan shaft washer should be incorporated to prevent the fan from jamming the cyclic control in case bearing failure does occur. (Bell Service Bulletin No. 61 dated July 20, 1950, covers this subject for models under (a). Bell Service Bulletin No. 72 dated August 4, 1950, covers this subject for models under (b).)
2022-25-11: The FAA is adopting a new airworthiness directive (AD) for all Airbus SAS Model A310 series airplanes. This AD was prompted by a determination that new or more restrictive maintenance requirements and airworthiness tasks are necessary. This AD requires revising the existing maintenance or inspection program, as applicable, to incorporate new or more restrictive airworthiness tasks, as specified in a European Union Aviation Safety Agency (EASA) AD, which is incorporated by reference. The FAA is issuing this AD to address the unsafe condition on these products.