Results
87-16-12: 87-16-12 BRITISH AEROSPACE: Amendment 39-5706. Applies to Model BAe-146 airplanes, as listed in British Aerospace BAe-146 Service Bulletin 27-58, Revision 1, dated November 14, 1986, certificated in any category. Compliance is required as indicated, unless previously accomplished. To prevent an unannunciated failure of the stall identification system, accomplish the following: A. Within 14 days or prior to the accumulation of 125 landings, whichever occurs first after the effective date of this AD, inspect the electro/pneumatic solenoid valve to identify the serial number and modification state in accordance with BAe-146 Service Bulletin 27-58, Revision 1, November 14, 1986. If the valve is identified as suspect, accomplish either of the following: 1. Prior to further flight, replace the affected valve with a modified valve identified in accordance with the service bulletin; or 2. Prior to further flight, and thereafter at intervals not to exceed 14 daysor 125 landings, whichever occurs first, functionally test the suspect valve in accordance with the Accomplishment Instructions of the service bulletin. a. Valves found defective must be removed prior to further flight and replaced with modified valves or a serviceable suspect valve. b. The serviceability of suspect replacement valves must be determined by performing the above mentioned functional test upon installation. B. Replacement of suspect valves with modified valves identified in accordance with BAe-146 Service Bulletin 27-58, Revision 1, dated November 14, 1986, constitutes terminating action for the requirements of this AD. C. An 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, Standardization Branch, ANM-113, FAA, Northwest Mountain Region. D. Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operateairplanes to a base for the accomplishment of the modification required by this AD. All persons affected by this directive who have not already received the appropriate service information from the manufacturer, may obtain copies upon request to British Aerospace, Librarian for Service Bulletins, P.O. Box 17414, Dulles International Airport, Washington, D.C. 20041. This information may be examined at FAA, Northwest Mountain Region, 17900 Pacific Highway South, Seattle, Washington, or the Seattle Aircraft Certification Office, 9010 East Marginal Way South, Seattle, Washington. This amendment, 39-5706, becomes effective August 31, 1987.
86-01-04: 86-01-04 HUGHES HELICOPTERS, INC. (Hughes Helicopters): Amendment 39-5187. Applies to Model 369 series helicopters including military Models YOH-6A and OH-6A, certificated in any category, equipped with tail rotor blades Part Numbers (P/N) 369A1613-3,- 7, -501, and -503, Serial Numbers (S/N) 6928 and prior; P/N's 369D21613-11, -41, and -51, S/N's 5144 and prior; P/N 369D21606, S/N's 0077 and prior; P/N 369D21615, S/N's 0480 and prior; and P/N's 421-088-BSC and -3, all serial numbers. Compliance is required within the next 100 hours time in service after the effective date of this AD, unless already accomplished. To prevent the loss of a tail rotor blade tip cap in flight and subsequent loss of tail rotor control, accomplish the following: (a) Remove, inspect, and modify blades in accordance with paragraphs a through g, Part I "PROCEDURE" section of Hughes Service Information Notices (SIN) DN-132.1, EN-21.1, FN-9.1, HN-199.1 dated May 1, 1985, or SIN's DN-129, EN-18,and HN-195 dated August 27, 1984. (b) An alternate method of compliance which provides an equivalent level of safety may be used when approved by the Manager of the Western Aircraft Certification Office, Hawthorne, California. (c) Special flight permits may be issued in accordance with FAR Sections 21.197 and 21.199 to ferry aircraft to a maintenance base in order to comply with the requirements of this AD. 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 McDonnell Douglas Helicopter Company, Centinela Avenue and Teale Street, Culver City, California 90230. These documents also may be examined at the FAA, Southwest Region, Room 158, Building 3B, 4400 Blue Mound Road, Fort Worth, Texas 76106, or at the Western Aircraft Certification Office, 15000 Aviation Boulevard, Hawthorne, California 90250. This amendment supersedes Amendment 39-4940 (49 FR 43046; October 26, 1984), AD 84-18-08. This amendment becomes effective February 14, 1986.
85-25-56 R1: 85-25-56 R1 GENERAL ELECTRIC COMPANY: Telegram issued December 20, 1985, as amended by Amendment 39-5495. Applies to General Electric Company (GE) CF6-50 and -45 series turbofan engines. Compliance is required as indicated, unless already accomplished. To prevent failure of the left hand side seventh stage low pressure turbine (LPT) cooling air manifold tube, which could result in an LPT overtemperature condition and subsequent LPT stage 1 disk rupture, accomplish the following: (a) For those engines not in compliance with the requirements of GE Service Bulletin (SB) 75-54, dated July 19, 1985, or paragraph 2.A. or 2.B. of GE SB 75-46, Revision 3, dated June 8, 1982, comply with paragraphs (1) then (2) below: (1) Accomplish the requirements of paragraphs 2.A.1. and 2.A.2. of GE SB 75-55, dated September 13, 1985, concurrently with the requirements of paragraph 2.A. of GE SB 75-54, or FAA approved equivalents, within 10 flight cycles after the effective date ofthis AD. (2) Accomplish the requirements of paragraph 2. of GE SB 75-55 or FAA approved equivalent, within 60 calendar days of complying with paragraph (1) above. (b) For engines already in compliance with the requirements of GE SB 75-54 or paragraph 2.A. or 2.B. of GE SB 75-46, accomplish the requirements of paragraph 2. of GE SB 75-55 within 60 calendar days after the effective date of this AD. (c) Replace cracked, broken or ruptured left hand side seventh stage LPT cooling air manifold tube and attachment hardware, found during accomplishment of paragraph (a) or (b) above, before further flight. (d) Inspect the left hand side seventh stage LPT cooling air manifold tubes and attachment hardware in accordance with the requirements of paragraphs 2.A., 2.B., 2.C. and 2.D.(4)(b) of GE SB 75-58, dated April 14, 1986, or FAA approved equivalent, within the next 250 flight cycles after the effective date of this AD, and thereafter, at intervals not to exceed 250 flightcycles from the last inspection. (e) Replace or tighten, in accordance with paragraph 2.D. of GE SB 75-58, left hand side seventh stage LPT cooling air system hardware found worn, loose, cracked or broken during accomplishment of paragraph (d) above, prior to further flight. 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, Federal Aviation Administration, 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, may adjust the compliance time specified in this AD. GE SB's 75-54, dated July 19, 1985; 75-46, Revision 3, dated June 8, 1982; 75-55, dated September 13, 1985; and 75-58, dated April 14, 1986, identified and described in this document, 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, from General Electric Company, 1 Neumann Way, Cincinnati, Ohio 45215. These documents also may be examined at the Office of the Regional Counsel, Federal Aviation Administration, New England Region, 12 New England Executive Park, Burlington, Massachusetts 01803, Rules Docket Number 85-ANE-44, Room 311, between the hours of 8:00 a.m. and 4:30 p.m., Monday through Friday, except Federal holidays. Paragraphs (a), (b), and (c) of this amendment become effective January 5, 1987, as to all persons except those persons to whom paragraphs (a), (b), and (c) of this amendment were made immediately effective by TAD T85-25-56, issued December 20, 1985. Paragraphs (d) and (e)of this amendment become effective January 13, 1987, as to all persons.
2016-13-12: We are adopting a new airworthiness directive (AD) for certain Rolls-Royce Deutschland Ltd & Co KG (RRD) BR700-710A1-10, -710A2-20, and -710C4-11 turbofan engines. This AD requires removing the pawl carrier pivot pins, part number (P/N) BRR17117, from service and replacing them with parts eligible for installation. This AD was prompted by a seized low-pressure turbine (LPT) fuel shut-off pawl carrier caused by corrosion of the pawl carrier pivot pin. We are issuing this AD to prevent failure of the fuel shut-off mechanism, which could result in uncontained part release, damage to the engine, and damage to the airplane.
2001-08-18: This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model DC-8 series airplanes, that requires installation of heat shrinkable tubing or application of Peel-Kote on each terminal connection of all cabin lighting switches in the forward and aft cabin electrical service panels. This action is necessary to prevent a short circuit within the cabin electrical service panel due to a foreign object being lodged between the terminals of a cabin light switch. Such a short circuit could result in overheating and damage to light circuits, and consequent smoke and fire in the main cabin of the airplane. This action is intended to address the identified unsafe condition.
87-06-06: 87-06-06 LOCKHEED-CALIFORNIA COMPANY: Amendment 39-5570. Applies to Lockheed Model L-1011-385 series airplanes, certificated in any category. Compliance required as indicated, unless previously accomplished. To prevent engine separation due to broken pylon attach fittings-to-skate-angle bolts, which are cracking because of stress-corrosion, accomplish the following: A. Before accumulating a total of 15,000 hours time-in-service or within the next 3,000 hours time-in-service after the effective date of the AD, whichever occurs later, and thereafter at intervals not to exceed 3,000 hours time-in-service or 15 months, whichever occurs later, accomplish the following: 1. Inspect the pylon attach fittings-to-skate-angle bolts in accordance with the Accomplishment Instructions in Lockheed Service Bulletin 093-54-049, Revision 1, dated September 25, 1986, or later FAA approved revision. 2. If broken bolts are found, before further flight, replace each broken bolt with a new bolt in accordance with the Accomplishment Instructions in Lockheed Service Bulletin 093-54-049, Revision 1, dated September 25, 1986, or later FAA-approved revision. B. Before accumulating a total of 15,000 hours time-in-service or before January 15, 1991, whichever is later, replace all of the pylon attach fittings-to-skate-angle H-11 steel bolts with stress-corrosion resistant MP-35N bolts in accordance with the Accomplishment Instructions in Lockheed Service Bulletin 093-54-049, Revision 1, dated September 25, 1986, or later FAA- approved revision. The inspections required by paragraph A. may be discontinued after paragraph B. has been accomplished. C. Alternate means of compliance which provide an acceptable level of safety may be used when approved by the Manager, Los Angeles Aircraft Certification Office, FAA, Northwest Mountain Region. D. Special 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. All persons affected by this directive who have not already received the appropriate service documents from the manufacturer may obtain copies upon request to Lockheed-California Company, P.O. Box 551, Burbank, California 91520, Attention: Commercial Order Administration, Dept. 65-33, U-33, B-1. These documents may be examined at the FAA, Northwest Mountain Region, 17900 Pacific Highway South, Seattle, Washington, or the Los Angeles Aircraft Certification Office, 4344 Donald Douglas Drive, Long Beach, California. This Amendment becomes effective April 2, 1987.
2016-13-05: We are adopting a new airworthiness directive (AD) for all General Electric Company (GE) GE90-76B, GE90-77B, GE90-85B, GE90-90B, and GE90-94B turbofan engines. This AD was prompted by an uncontained failure of the high-pressure compressor (HPC) stage 8-10 spool, leading to an airplane fire. This AD requires eddy current inspection (ECI) or ultrasonic inspection (USI) of the HPC stage 8-10 spool and removing from service those parts that fail inspection. We are issuing this AD to prevent failure of the HPC stage 8-10 spool, uncontained rotor release, damage to the engine, and damage to the airplane.
2001-08-10: This amendment adopts a new airworthiness directive (AD) that applies to certain Aerostar Aircraft Corporation (Aerostar) Models PA-60-600, PA-60-601, PA-60-601P, PA-60-602P, and PA-60-700P airplanes. This AD requires you to replace both of the existing main landing gear lower side brace assemblies with parts of improved design. This AD is the result of several reports of cracking of the main landing gear lower side brace at the upper bolt lug discovered on preflight inspection. The actions specified by this AD are intended to correct damage or cracks in the main landing gear lower side brace at the upper bolt lug where the upper and lower side braces connect. This could result in failure of the main landing gear lower side brace. Such failure could lead to loss of control of the airplane.
2016-12-11: We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 787-8 airplanes. This AD was prompted by a report that certain center and outboard stowage bin modules were incorrectly installed. This AD requires an inspection of the center and outboard stowage bin modules for missing parts, quick release pins that are not fully engaged, and parts that are installed in incorrect locations; and corrective actions if necessary. We are issuing this AD to detect and correct incorrectly installed center and outboard stowage bin modules that might not remain intact during an emergency landing, resulting in injuries to occupants and interference with airplane evacuation.
2010-22-02: We are adopting a new airworthiness directive (AD) for the products listed above. 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: Seven cases of on-ground hydraulic accumulator screw cap/end cap failure have been experienced on CL-600-2B19 aeroplanes, resulting in the loss of the associated hydraulic system and high-energy impact damage to adjacent systems and structure. * * * * * * * * A detailed analysis of the calculated line of trajectory of a failed screw cap/end cap for each of the accumulators has been conducted, resulting in the identification of several areas where systems and/or structural components could potentially be damaged. Although all of the failures to date have occurred on the ground, an in-flight failure affecting such components could potentially have an adverse effect on the controllability of the aeroplane. * * * * * This AD requires actions that are intended to address the unsafe condition described in the MCAI.