Results
2017-08-05: We are superseding Airworthiness Directive (AD) 2016-13-05 for all General Electric Company (GE) GE90-76B, GE90-77B, GE90-85B, GE90- 90B, and GE90-94B turbofan engines. AD 2016-13-05 required eddy current inspection (ECI) of the high-pressure compressor (HPC) stage 8-10 spool at each shop visit for all affected engines and ECI or ultrasonic inspection (USI) for certain affected engines. This new AD requires initial and repetitive on-wing USIs of the HPC stage 8-10 spool for certain engines prior to shop visit and ECI of all affected engines at each shop visit. This AD was prompted by analysis that the risk of the failure of an HPC stage 8-10 spool was excessive without repetitive USI prior to shop visit. We are issuing this AD to correct the unsafe condition on these products.
84-26-02: 84-26-02 INDUCTION AIR FILTERS: Amendment 39-4966. Applies to all paper induction air filters used in small airplanes. Compliance: Required as indicated, unless already accomplished. To prevent possible engine power loss or stoppage caused by engine ingestion of fragments of a deteriorated induction air filter, accomplish the following: Within the next one hundred hours time-in-service after the effective date of this AD or prior to the accumulation of 500 hours time-in-service on the filter, whichever occurs later, and thereafter at intervals not exceeding 500 hours time-in-service on the filter: (a) Replace the air filter with a new filter that is FAA approved for the airplane installation. (b) Within 100 hours time-in-service replace any filter on which the time-in-service cannot be determined utilizing the airplane maintenance records for this determination. NOTE: This AD does not alter current maintenance procedures which require inspection of paper induction air filters at 100 hours time-in-service and annual inspections and replacement as necessary based on filter condition. This amendment becomes effective January 29, 1985.
64-04-06: 64-04-06 PRATT READ: Amdt. 685 Part 507 Federal Register February 12, 1964. Applies to All Model PR-G1 Gliders. Compliance required as indicated. Due to a deteriorating condition of the wood structure supporting the aft elevator bellcrank, resulting in loss of elevator control, accomplish the following within 25 hours' time in service after the effective date of this AD unless already accomplished within the last 75 hours' time in service, and at intervals thereafter not to exceed 100 hours' time in service from the last inspection, or one year, whichever occurs first. (a) Remove the stabilizer and elevators and any other obstructing structure necessary to gain access to the aft internal fuselage area (tail cone section). (b) With the use of a light and mirror, visually inspect for deterioration both the front and rear side of the wood bulkhead in the vicinity of its support of the aft elevator bellcrank. (c) If indications of deterioration of the wood structureare found, repair that bulkhead in accordance with an FAA approved repair before further flight, or replace with a part having the same part number, or an FAA approved equivalent before further flight. NOTE: After installation of a new or repaired bulkhead, it should be ascertained that the elevator is functioning properly throughout the entire range. This directive effective March 13, 1964.
2017-07-01: We are adopting a new airworthiness directive (AD) for certain M7 Aerospace LLC Models SA226-T, SA226-AT, SA226-T(B), SA226-TC, SA227- AC (C-26A), SA227-AT, SA227-BC (C-26A), SA227-CC, SA227-DC (C-26B), and SA227-TT airplanes. This AD was prompted by detachment of the power lever linkage to the TPE331 engine propeller pitch control. This AD requires repetitively inspecting the propeller pitch control for proper torque, with corrections as necessary until required replacement or rework of the PPC assembly to have a threaded hole in the splined end of the shouldered shaft and installation of a secondary retention device is done. We are issuing this AD to correct the unsafe condition on these products.
61-18-02: 61-18-02 BRANTLY: Amdt. 327 Part 507 Federal Register August 24, 1961. Applies to All Model B-2 Helicopters prior to Serial No. 112. Compliance required within the next 25 hours' time in service after effective date of this directive unless already accomplished. Investigation of a recent Model B-2 helicopter accident indicated evidence of limited tail rotor control. Accordingly, in order to provide directional control over a wider main rotor r.p.m. range, the following modification and rerigging of the tail rotor is required: (a) Modify the rudder control arm P/N B2-284-1 as follows. (1) Disconnect the vertical rudder rod P/N B2-251-5 at its top end by removing the AN 3-10A bolt. (2) Drill a 1/16-inch diameter hole and then enlarge to 0.187-inch diameter 1/2 inch inboard (center to center) from the existing hole in the rudder control arm P/N B2-284-1. Deburr edges. (3) Cut off the end of the rudder control arm P/N B2-284-1 with the old 0.187-inch hole 0.344-inch outboard from the centerline of the new 0.187-inch hole (0.250-inch edge distance from new hole) and perpendicular to the longitudinal axes of the rudder control arm. Break all sharp edges. (4) Rerig the tail rotor in accordance with the manufacturer's instructions, Service Bulletin No. 15. (Brantly Service Bulletin No. 15 dated June 23, 1961, covers this subject.) This directive effective August 29, 1961.
83-25-01: 83-25-01 SHORT BROTHERS LIMITED: Amendment 39-4783. Applies to all Models of the SD3-30 airplane, certificated in all categories, with the serial numbers specified below. To prevent a potential fuel fire hazard, accomplish the following within the next 60 days after the effective date of this AD, unless already accomplished. A. For aircraft serial numbers SH3002 to SH3091 inclusive, modify the fuel vapor exhaust ducting in accordance with paragraph 2, Accomplishment Instructions, of Shorts Service Bulletin No. SD3-53-47, Revision 3, dated June 23, 1983. B. For aircraft serial numbers SH3002 to SH3089 inclusive, replace the existing flexible vapor proof shrouds covering fuel lines in the passenger compartment in accordance with paragraph 2, Accomplishment Instructions of Shorts Service Bulletin No. SD3-28-17, Revision 2, dated June 23, 1983. NOTE: The actions of paragraph A., above, must be accomplished before performing the requirements of paragraph B. C. For aircraft with serial numbers specified in paragraph 1, Planning Information, of Shorts Service Bulletin No. SD3-28-16, Revision 3, dated June 23, 1983, inspect, replace components if necessary, and pressure check the fuel lines as required in accordance with paragraph 2, Accomplishment Instructions, of the service bulletin. NOTE: The actions of paragraphs A. and B., above, must be accomplished before performing the requirements of paragraph C. D. Alternate means of compliance which provide an equivalent level of safety may be used when approved by the Manager, Seattle Aircraft Certification Office, FAA, Northwest Mountain Region. E. 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 inspections and/or modifications required by this AD. F. This AD supersedes Amendment 39-4677 (48 FR 31631, July 11, 1983), AD 83- 13-07. This amendment becomes effective January 8, 1984.
2017-05-12: We are adopting a new airworthiness directive (AD) for certain Airbus Model A318-112 airplanes, A319-111, -112, -115, -132, and -133 airplanes, A320-214, -232, and -233 airplanes, and A321-211, -212, - 213, -231, and -232 airplanes. This AD was prompted by a quality control review on the final assembly line, which determined that aluminum alloy with inadequate heat treatment had been delivered and used on several structural parts. This AD requires a one-time eddy current conductivity measurement of certain cabin, cargo compartment, and frame structural parts to determine if aluminum alloy with inadequate heat treatment was used, and replacement if necessary. We are issuing this AD to address the unsafe condition on these products.
86-19-13: 86-19-13 AVCO LYCOMING: Amendment 39-5374. Applies to Avco Lycoming model T5508D turboshaft engines. Compliance is required as indicated, unless already accomplished. To prevent failure of the first stage turbine disk that can cause an uncontained engine failure, accomplish the following: (a) Visual and fluorescent penetrant inspect the first turbine rotor assembly, Part Number (P/N) 2-120- 030-43, within the next 50 hours time in service after the effective date of this AD, in accordance with the Accomplishment Instructions contained in Avco Lycoming Service Bulletin (SB) 5508-0031, Revision 1, dated August 19, 1986, or FAA approved equivalent. (b) Remove and replace with new parts, bolts P/N 2-100-079-05 and their associated locking plates P/N 2-100-078-01, when accomplishing the inspections of Paragraph (a) above, in accordance with the Accomplishment Instructions contained in Avco Lycoming SB 5508-0031, Revision 1, dated August 19, 1986, or FAA approved equivalent.(c) Remove from service and replace with a serviceable part, prior to further flight, all first turbine disks that exhibit fretting on the disk to shaft mating face and/or a crack indication during inspection. (d) Report the following information in writing for each inspection within 30 days of the inspection to the Manager, Engine Certification Office, Aircraft Certification Division, Federal Aviation Administration, New England Region, 12 New England Executive Park, Burlington, Massachusetts 01803, (Telex Number 949301 FAANE BURL) (Reporting approved by the Office of Management and Budget (OMB) under OBM Number 2120-0056): (1) Engine serial number (2) Inspection date (3) Disk part number and serial number (4) Disk total time and cycles (5) Disk time and cycles since last installation (6) Breakaway up torque for bolts, P/N 2-100-079-05 (7) Any evidence of oil leakage and/or fire in the Number 2 bearing area (8) Disk disposition (crack indication or, no crack indication, fretting or, no fretting, thread marks inside the boltholes or not) NOTE: For the purpose of this AD fretting is defined as metal removal below the original machined surface that is exemplified by a pitting pattern. Aircraft may be ferried in accordance with the provisions of FAR 21.197 and 21.199 to a base where the AD can be accomplished. Upon request, an equivalent means of compliance with the requirements of this AD may be approved by the Manager, Engine Certification Office, Aircraft Certification Division, New England Region, 12 New England Executive Park, Burlington, Massachusetts 01803. Upon submission of substantiating data by an owner or operator through an FAA maintenance inspector, the Manager, Engine Certification Office, Aircraft Certification Division, Federal Aviation Administration, New England Region, may adjust the compliance times specified in this AD. Avco Lycoming SB 5508-0031, Revision 1, dated August 19, 1986, identified and described in this document, is 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 this document from the manufacturer may obtain copies upon request to Avco Lycoming, 550 South Main Street, Stratford, Connecticut 06497. This document also may be examined at the Office of the Regional Counsel, Rules Docket Number 86-ANE-31, Federal Aviation Administration, New England Region, 12 New England Executive Park, Burlington, Massachusetts 01803, Rules Docket Number 86-ANE-31, Room 311, between the hours of 8:00 a.m. and 4:30 p.m., Monday through Friday, except Federal holidays. This amendment becomes effective on October 6, 1986.
2000-22-22: This amendment adopts a new airworthiness directive (AD), applicable to certain Raytheon Model Hawker 800XP and Hawker 800 (U-125A) series airplanes, that requires inspection of the wire bundle to relay `KT' on panel `JA' for correct routing, adequate clearance from the fuel cross-feed valve operating lever, and the presence of chafing; this amendment also requires corrective action, if necessary. The actions specified by this AD are intended to detect and correct chafing of the wire bundle exiting panel `JA' due to insufficient clearance from the fuel cross-feed valve operating lever. Such chafing of the wire bundle could result in a fire in the area of the fuel system in a confined space. This action is intended to address the identified unsafe condition.
63-24-01: 63-24-01 CURTISS-WRIGHT: Amdt. 647 Part 507 Federal Register November 26, 1963. Applies to All Models C634S-C400 through -C499 and C634S-C500 through -C599 Series Propellers Equipped With P/N 142080-1 Brake Assemblies. (These Propellers May Be Found Installed On Such Aircraft as Lockheed 749 and 1049.) Compliance required within 100 hours' time in service after the effective date of this AD. There have been failures of P/N 142080-1, threaded-type brake assemblies, causing the propellers to malfunction. To correct this unsafe condition, the following shall be accomplished: Replace P/N 142080-1 brake assemblies with P/N's 149252-1, 152908-2, or 161462-2 brake assemblies. (Curtiss Service Bulletins Nos. C-14 and C-32 and Parts Bulletins C-52, C-67, C-80 and C-90 cover this same subject.) This directive effective December 27, 1963.