Results
89-15-02: 89-15-02 BOEING: Amendment 39-6260. \n\tApplicability: Model 747 series airplanes, as listed in Boeing Service Bulletin 747-27- 2228, Revision 1, dated October 26, 1984, certificated in any category. \n\n\tCompliance: Required within the next 18 months following the effective date of this AD, unless previously accomplished. \n\n\tTo prevent rejected takeoffs as a result of false takeoff warnings, accomplish the following: \n\n\tA.\tReplace the stabilizer limit switch assembly mounting brackets, in accordance with Boeing Service Bulletin 747-27-2228, Revision 1, dated October 26, 1984. \n\n\t\tB.\tAn 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, Seattle Aircraft Certification Office, FAA, Northwest Mountain Region. \n\n\tNOTE: The request should be forwarded through an FAA Principal Maintenance Inspector (PMI), who will either concur or comment and then send it to the Manager, Seattle Aircraft Certification Office. \n\n\tC.\tSpecial 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. \n\n\tAll persons affected by this directive who have not already received the appropriate service documents from the manufacturer may obtain copies upon request to Boeing Commercial Airplanes, P.O. Box 3707, Seattle, Washington 98124. These documents may be examined at the FAA, Northwest Mountain Region, Transport Airplane Directorate, 17900 Pacific Highway South, Seattle, Washington, or Seattle Aircraft Certification Office, 9010 East Marginal Way South, Seattle, Washington. \n\n\tThis amendment (39-6260, AD 89-15-02) becomes effective on August 14, 1989.
2015-25-03: We are superseding Airworthiness Directive (AD) 2013-23-03, which applies to certain The Boeing Company Model 747-100, 747-100B, 747-100B SUD, 747-200B, 747-200C, 747-200F, 747-300, 747-400, 747-400D, 747-400F, and 747SR series airplanes. AD 2013-23-03 required a detailed inspection of certain attach fittings for a cylindrical defect, and replacement if necessary. For certain airplanes, this new AD requires new inspections of the inboard actuator attach fittings for machining defects, and overhaul or replacement if necessary. This new AD also limits the compliance time for doing the replacement for certain other airplanes. This AD was prompted by a report that a machining defect was also found on some of the actuator assemblies inspected during manufacture. This defect could lead to fatigue cracking and subsequent fracture. We are issuing this AD to detect and correct defective inboard actuator attach fittings which, combined with loss of the outboard actuator load path, couldresult in uncontrolled retraction of the outboard flap, damage to flight control systems, and consequent reduced controllability of the airplane.
54-20-02: 54-20-02 SIKORSKY: Applies to All Model S-55 Helicopters. Compliance required as indicated. In order that cracks in the fore and aft transmission support assemblies (S14-20-2503) may be detected, these assemblies should be inspected daily, without removing the support assemblies from the helicopter, in accordance with the following procedure: 1. Remove the paint, grease and foreign matter from all welds and from the areas of the tubes within 3 inches of a weld on both upper and lower ends. 2. Inspect for cracks all areas of the tubes within 2 inches of a weld and all welds visually, and, where possible, with the assistance of a 5- to 7-power glass. 3. Assemblies found with a crack should be replaced immediately. 4. Protect the exposed areas of metal with any suitable corrosion preventive. The manufacturer is presently investigating the reasons for the occurrence of such cracks and a permanent repair is expected in the near future which, when incorporated, will make these daily inspections unnecessary. These inspections are in addition to those required by AD 54-16- 01. (Revision C to Sikorsky Information Circular No. 1435-383 covers this same subject.) When transmission support, S14-20-4603, is installed in place of support S14-20-2503, the above inspection may be performed at every intermediate inspection rather than on a daily basis. (Sikorsky Service Information Circular No. 1420-548, dated December 3, 1954, covers the installation instructions.)
2003-16-03: This amendment supersedes an existing airworthiness directive (AD) that applies to Turbomeca Arriel 1A, 1 A1, 1 A2, 1 B, 1 C, 1 C1, 1 C2, 1 D, and 1 D1 turboshaft engines. That AD currently requires repetitive checks for engine rubbing noise during gas generator rundown following engine shutdown, and for free rotation of the gas generator by rotating the compressor manually after the last flight of the day. In addition, the AD 95-11-01 requires installation of modification TU 202 or TU 197 as terminating action to the repetitive checks. This amendment adds additional engine models to the applicability section, eliminates the installation of modification TU 197 as a terminating action to the repetitive checks, requires additional inspections for engines that have modification TU 197 installed, and requires the replacement of modifications TU 76 and TU 197 with modification TU 202, as a terminating action to the repetitive checks and inspections. This amendment is prompted by areport of an in-flight engine shutdown on an engine that had modification TU 197 installed, and the need to update the modification standard on certain engine models. We are issuing this AD to prevent engine failure due to rubbing of the 2nd stage turbine disk on the 2nd stage turbine nozzle guide vanes, which could result in complete engine failure and damage to the helicopter.
88-24-16: 88-24-16 CESSNA: Amendment 39-6078. Applies to Model S550 series airplanes, Serial Numbers (S/N) S550-0001 through S550-0039, and S550-0041 through S550-0120, except the lavatory vanities on S550-0100 through S550-0120; and Model 650 series airplanes, S/N 650-0001 through 650-0126, except the lavatory vanities on S/N 650-0087 and 650-0105 through 650-0126; certificated in any category. Compliance required as indicated, unless previously accomplished. To preclude wiring failure, which can result in cabin smoke and/or fire, accomplish the following: A. For Cessna Model S550 series airplanes: Before next activation of the airplane's electrical power, disconnect the electrical power to the interior cabinetry in accordance with the accomplishment instructions of Cessna Alert Service Bulletin SBAS550-25-16, dated February 3, 1987. 1. Electrical wiring may be reconnected following modification of the interior cabinetry wiring and electrical components described in,and in accordance with, Cessna Service Letter SLS550-25-02, Revision 4, dated October 21, 1988. B. For Cessna Model 650 series airplanes: Before next activation of the airplane's electrical power, disconnect the electrical power to the interior cabinetry in accordance with the accomplishment instructions of Cessna Alert Service Bulletin SBA650-25-12, dated February 3, 1987. 1. Electrical wiring may be reconnected following modification of the interior cabinetry wiring and electrical components described in, and in accordance with, Cessna Service Letter SL650-25-02, Revision 4, dated October 21, 1988. 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, Wichita Aircraft Certification Office, FAA, Central Region. NOTE: The request for alternate means of compliance should be forwarded through an FAA Principal Maintenance Inspector (PMI), who may add any comments and then send it to the Manager, Wichita Aircraft Certification Office. 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 information from the manufacturer may obtain copies upon request to Cessna Aircraft Company, P.O. Box 7706, Wichita, Kansas 67277. This information may be examined at FAA, Northwest Mountain Region, 17900 Pacific Highway South, Seattle, Washington, or FAA, Central Region, Wichita Aircraft Certification Office, 1801 Airport Road, Room 100, Mid-Continent Airport, Wichita, Kansas. This amendment supersedes AD 87-03-15, Amendment 39-5647, effective July 6, 1987, as to all persons except those to whom it was made immediately effective by Priority Letter AD, 87-03-15 issued February 6, 1987. This amendment, 39-6078, becomes effective December 12, 1988.
2002-21-01: This amendment supersedes an existing airworthiness directive (AD), that is applicable to Britax Sell GmbH & Co. OHG water boilers, coffee makers, and beverage makers. That AD currently requires inspecting the wiring for indications of overheating or electrical arcing, and if indications are found, replacing the wiring. This amendment requires replacing the wiring on those water boilers, coffee makers, and beverage makers whether or not they show indications of overheating or electrical arcing. This amendment is prompted by revisions to the manufacturer's service bulletin that were not incorporated in the proposed rule. The actions specified by this AD are intended to prevent a fire in the galley compartment due to inadequate crimping of the electrical terminal contact pins, which could result in smoke in the cockpit and cabin and loss of control of the airplane. \n\nDATES: Effective November 27, 2002. The incorporation by reference of certain publications listed in the regulations is approved by the Director of the Federal Register as of November 27, 2002. The incorporation by reference of certain other publications, as listed in the regulations, was approved previously by the Director of the Federal Register as of June 15, 2002 (66 FR 29467; May 31, 2001).
2002-21-15: This amendment adopts a new airworthiness directive (AD), that is applicable to Honeywell International Inc. (formerly AlliedSignal Inc., Garrett Engine Division, Garrett Turbine Engine Company, and AiResearch Manufacturing Company of Arizona) TPE331 series turboprop and TSE331-3U series turboshaft engines. This amendment requires replacing second stage turbine stator assemblies, part numbers (P/N's) 894528-1, -2, -3, -5, -6, -10, and -11, with serviceable turbine stator assemblies. This amendment is prompted by reports of six uncontained separations of the second stage turbine wheels associated with obstructed internal cooling holes or passage in the vanes of the second stage turbine stator which may result in contact and rub into the turbine rotor. The actions specified by this AD are intended to prevent uncontained turbine rotor separation and damage to the aircraft.
88-14-04: 88-14-04 BRITISH AEROSPACE: Amendment 39-6003. Final copy of priority letter AD issued July 8, 1988. Applies to Viscount Model 700 and 800 series airplanes, certificated in any category. Compliance is required as indicated, unless previously accomplished. To prevent structural failure of the wing, accomplish the following: A. Within 7 days after the effective date of this AD, and thereafter at intervals not to exceed 12 months, accomplish the following: 1. Visually inspect the right and left upper wing surface between Wing Stations 96 and 131 above the main (center) spar upper cap for evidence of corrosion, in accordance with British Aerospace Campaign Wire REF FSS/VIS/886135, dated June 30, 1986. Signs of corrosion include lifting of the skin, loose fasteners, and corrosion stains around the fasteners. 2. Visually inspect the underside of the upper wing skin surface between Stations 96 and 131 both front and aft sides of the main (center) spar upper cap, both right and left wings, for evidence of corrosion, in accordance with British Aerospace Campaign Wire REF FSS/VIS/886135, dated June 30, 1988. This area is accessed through the main landing gear (MLG) bay. B. If corrosion is found or suspected as a result of the inspections required by paragraph A., above, prior to further flight, remove the wing upper skin between wing stations 96 and 131 for more thorough inspection for corrosion, and repair or replace corrosion-damaged structures, if necessary, in accordance with a method approved by the Manager, Standardization Branch, ANM-113, FAA, Northwest Mountain Region. 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. NOTE: The request should be forwarded through an FAA Principal Maintenance Inspector (PMI), who may add any comments and thensend it to the Manager, Standardization Branch, ANM-113. D. 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 the modifications required by this AD. All persons affected by this directive who have not already received the appropriate service document from the manufacturer may obtain copies upon request to British Aerospace, Inc., Librarian for Service Bulletins, P.O. 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 AD was effective earlier to all recipients of Priority Letter AD 88-14-04, issued July 8, 1988. This amendment, 39-6003, becomes effective September 6, 1988.
64-09-03: 64-09-03 de HAVILLAND: Amdt. 718 Part 507 Federal Register April 22, 1964. Applies to All Model DHC-2 "Beaver" Aircraft. Compliance required as indicated. As a result of cracks and corrosion found on the aileron mass balance weight arm C2WA151 and C2WA152 or C2WA127 and C2WA128, accomplish the following inspection within 25 hours' time in service after the effective date of this AD, unless already accomplished within the last 475 hours' time in service, and thereafter within 500 hours' time in service from the last inspection. (a) Inspect the aileron mass balance weight arm on each aileron for cracks and corrosion, particularly around welds, using a dye penetrant and a 10-power magnifying glass, or an FAA-approved equivalent inspection. Prior to inspection, remove all paint (using a paint solvent which will not have a deleterious effect upon the base metal), grease and dirt from all surfaces involved. (b) If cracks or corrosion are found, replace the part witha new part of the same part number, or an equivalent, approved by the Chief, Engineering and manufacturing Branch, FAA Eastern Region, or make a repair approved by the Chief, Engineering and Manufacturing Branch, FAA Eastern Region. This is to be accomplished before further flight, except that one flight may be made in accordance with the provisions of CAR 1.76 for the purpose of obtaining these repairs. (de Havilland Engineering Bulletin Series "B", No. 17, dated November 20, 1959, available from de Havilland Aircraft of Canada, Ltd., Toronto, Canada, covers this same subject.) This directive effective May 22, 1964.
2015-26-10: We are adopting a new airworthiness directive (AD) for certain Sikorsky Aircraft Corporation (Sikorsky) Model S-76A, S-76B, and S-76C helicopters. This AD requires inspecting the main gearbox (MGB) lower housing jet bores for leaks, paint or caulk blistering, and liner protrusion. This AD was prompted by several reports of MGB low oil pressure warnings which were determined to be the result of unsecured jet bore liners that had protruded. The actions are intended to prevent failure of the MGB from loss of oil, which could result in subsequent loss of control of the helicopter. [[Page 148]]