Results
86-18-09: 86-18-09 GROB WERKE GMBH (BURKHART GROB): Amendment 39-5410. Applies to Model G103 TWIN ASTIR gliders serial numbers 3000 through 3291, and 3000-T-1 through 3284-T-44 certificated in any category. Compliance is required as indicated unless already accomplished. To prevent failure of the rudder control rear parallel lever P/N II 103-4320.05 which could result in loss of rudder control, accomplish the following: (a) Within the next 10 hours time-in-service after the effective date of this AD, and thereafter at intervals not to exceed 10 hours time-in-service after the last inspection, until compliance with Paragraph (c) is accomplished, visually inspect the rear parallel lever in the area of the left and right boreholes, using a 10 power or greater magnifying glass, for cracks in accordance with Part 1 of the "Instructions" section of Grob Technical Information No. TM 315- 30, dated October 1, 1985. (b) If a cracked lever is found during the inspection required by Paragraph (a) of this AD, before further flight, replace the rear parallel lever with a stronger new parallel lever in accordance with part 2 of the "Instructions" section of Grob Technical Information No. TM 315- 30, dated October 1, 1985, and Grob Repair Instructions No. 315-30, dated October 1, 1985. (c) Within the next 30 hours time-in-service but no later than 60 days after the effective date of this AD, replace any rear parallel lever not replaced in accordance with Paragraph (b) of this AD, with a stronger rear parallel lever in accordance with Part 2 of the "Instructions" section of Grob Technical Information No. TM 315-30, dated October 1, 1985, and Grob Repair "Instructions" No. 315-30, dated October 1, 1985. NOTE: Stronger rear parallel lever does not have a new part number. It can be identified as it is made of stock aluminum, not a casting as the original part. Upon request, an equivalent means of compliance with the requirements of this AD may be approvedby the Manager, Brussels Aircraft Certification Office, AEU-100, Europe, Africa, and Middle East Office, FAA, c/o American Embassy, 15 Rue de la Loi B-1040 Brussels, Belgium, Telephone No. 513.38.30 ext. 2710 or the Manager, New York Aircraft Certification Office, Aircraft Certification Division, FAA, New England Region, 181 South Franklin Avenue, Room 202, Valley Stream, New York 11581, Telephone No. 516-791-6680. Upon submission of substantiating data by an owner or operator through an FAA maintenance inspector, the Manager, Brussels Aircraft Certification Office, or the Manager, New York Aircraft Certification Office, may adjust the compliance time specified in this AD. Grob Technical Information No. 315-30 dated October 1, 1985, and Grob Repair Instructions No. 315-30 dated October 1, 1985, 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 alreadyreceived these documents from the manufacturer may obtain copies upon request to Grob Systems, Inc., Aircraft Division, I-75 and Airport Drive, Bluffton, Ohio 45817. These documents also may be examined at the Office of Regional Counsel, ANE-7, FAA New England Region, 12 New England Executive Park, Burlington, Massachusetts 01803, Room 311, Rules Docket 86-ANE-36, between the hours of 8:00 am and 4:30 pm; Monday thru Friday, except Federal holidays. This amendment becomes effective on September 15, 1986.
86-21-04: 86-21-04 BRITISH AEROSPACE: Amendment 39-5419. Applies to Model BAe-146 series airplanes, with serial numbers as listed in BAe Service Bulletin 32-18, Revision 1, dated November 28, 1984, certificated in any category. Compliance is required within 60 days after the effective date of this AD. To prevent structural failure of the main landing gear, accomplish the following, unless previously accomplished: 1. Inspect and repair, if necessary, the main landing gear main fittings in accordance with BAe Service Bulletin 32-18, Revision 1, dated November 28, 1984. 2. 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. 3. 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 thisAD. All persons affected by this directive who have not already received the appropriate service bulletin from the manufacturer may obtain copies upon request to British Aerospace, Inc., Librarian, Box 17414, Dulles International Airport, Washington, D.C. 20041. This document may be examined at the 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 becomes effective October 20, 1986.
99-16-12: This amendment adopts a new airworthiness directive (AD) that applies to certain Raytheon Aircraft Company (Raytheon) Model Beech 1900D airplanes that are equipped with the electric elevator trim option. This AD requires installing electric elevator trim servo covers. This AD is the result of reports of the affected airplanes leaving the factory without electric elevator trim servo covers installed. If the covers are not installed, moisture could freeze on parts of the electric actuator. The actions specified by this AD are intended to prevent failure of the electric elevator trim and difficulty operating the manual elevator trim caused by moisture freezing on parts of the electric actuator installation, which would result in the pilot having to apply constant pressure to the control wheel during flight.
79-23-04: 79-23-04 GENERAL ELECTRIC COMPANY: Amendment 39-3610. Applies to all General Electric CT58 turboshaft engines which are presently in use or have been used in repetitive heavy-lift operation. Compliance required as indicated, unless already accomplished. To prevent low cycle fatigue initiated failure, revise the total recorded operating cycles of all life-limited rotating components, on the effective date of this AD, and remove these components from service in accordance with the multiplying factors and retirement lives contained in General Electric Alert Service Bulletin CT58 (A72- 162) CEB-258, dated July 9, 1979. Later FAA approved revisions or equivalent means may be approved by the Chief, Engineering and Manufacturing Branch, New England Region. Hourly limits are not affected by this AD. Components with revised total recorded operating cycles in excess of the limits or within 600 cycles or 100 hours of the limits in Tables I, II, or III of General Electric Alert Service Bulletin CT58 (A72-162) CEB-258, on the effective date of this AD, must be removed from service prior to the accumulation of 600 additional cycles or 100 hours, whichever comes first. NOTE: Repetitive heavy-lift operations are considered to be those operations during which a lift-carry-drop cycle is repeated more than 10 times per hour without landing. This activity is typical of logging operations and may also include some construction or utility operations. 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 General Electric Company, 1000 Western Avenue, Lynn, Massachusetts, 01910. 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 upon publication in the Federal Register.
2013-24-17: We are adopting a new airworthiness directive (AD) for General Electric Company (GE) GE90-110B1 and GE90-115B turbofan engines with certain high pressure compressor (HPC) rotor stage 2-5 spools installed. This AD requires removing these spools from service at times determined by a drawdown plan. This AD was prompted by reports of cracks in HPC rotor stage 2-5 spool aft spacer arms. We are issuing this AD to prevent failure of a critical life-limited rotating engine part, which could result in an uncontained engine failure and damage to the airplane.
98-15-18 R1: We are revising Airworthiness Directive (AD) 98-15-18 that applies to certain Maule Aerospace Technology, Inc. Models M-4, M-5, M- 6, M-7, MT-7, MX-7, MXT-7, and M-8 airplanes that are equipped with rear wing lift struts, part number (P/N) 2079E, and/or front wing lift struts, P/N 2080E. AD 98-15-18 required repetitively inspecting certain wing lift struts for internal corrosion and replacing of any wing lift strut where corrosion was found. Since we issued AD 98-15-18, we were informed by the manufacturer that Model MXT-7-420 airplanes are no longer in existence, are no longer type certificated, and should be removed from the Applicability section. We were also informed that paragraph (b) in AD 98-15-18 had been misinterpreted and caused confusion. This AD removes Model MXT-7-420 airplanes from the Applicability section and clarifies the intent of the language in paragraph (b) of AD 98-15-18. This AD also retains all other requirements of AD 98-15-18. We are issuing this AD to correct the unsafe condition on these products.
2006-03-06: This amendment adopts a new airworthiness directive (AD), applicable to all Empresa Brasileira de Aeronautica S.A. (EMBRAER) Model EMB-135 airplanes, and EMB-145, -145ER, -145MR, -145LR, -145XR, - 145MP, and -145EP airplanes. This AD requires inspecting the pilot's and co-pilot's seat tracks for proper locking of the seats, and adjusting or replacing the seat tracks if necessary. This AD also requires replacement of the seat locking pin on certain SICMA-brand seats. The actions specified by this AD are intended to prevent uncommanded movement of the pilot's or co-pilot's seat, which could interfere with the operation of the airplane and consequent temporary loss of airplane control. This action is intended to address the identified unsafe condition.
95-24-07: This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A320-111, -211, and -231 series airplanes, that requires modification of the aileron support frame of the wings. This amendment is prompted by reports indicating that tensile cracks have been found at a certain mounting hinge of the aileron support frame during full scale fatigue testing of the test article due to fatigue-related stress. The actions specified by this AD are intended to prevent such fatigue-related cracking, which could result in loss of the aileron control surface and the inability of the pilot to control rolling moments of the airplane.
99-16-13: This amendment supersedes an existing airworthiness directive (AD), applicable to MDHI Model MD-900 helicopters, that currently requires applying specified serial numbers and establishing life limits for certain parts. This amendment is prompted by additional analysis that supports an increase in the life limit of certain parts. The actions specified by this AD are intended to increase the life limits for various parts.
2013-24-15: We are superseding Airworthiness Directive (AD) 2007-11-08 for all The Boeing Company Model 727 airplanes. AD 2007-11-08 required repetitive inspections of the in-tank fuel boost pump wiring, installation of sleeving over the in-tank fuel boost pump wires, repetitive inspections of a certain electrical wire, sleeve, and conduit, and applicable investigative and corrective actions; and repetitive engine fuel suction feed operational tests. This new AD also requires replacement of the wire bundles for the wing and center fuel boost pumps, installation of convoluted liners, and related investigative and corrective actions if necessary. This new AD also requires replacement of the fuel quantity indicating system (FQIS) wires, a low-frequency eddy current inspection for cracking, and repair if necessary. This new AD also requires revising the maintenance program to incorporate changes to the airworthiness limitations section. This AD was prompted by a report of damage found to thesleeve, jacket, and insulation on an electrical wire during a repetitive inspection. We are issuing this AD to prevent chafing of the fuel boost pump electrical wiring and leakage of fuel into the conduit, and to prevent electrical arcing between the wiring and the surrounding conduit, which could result in arc-through of the conduit, and consequent fire or explosion of the fuel tank.