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2016-01-05: We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 737-400 series airplanes, as modified by a certain supplemental type certificate. This AD was prompted by the discovery of a design drawing error regarding placards that identified incorrect squibs and pressure switches for certain fire extinguisher bottles. This AD requires a detailed inspection of certain cargo placards to determine if they are the correct placards and in the correct location, a detailed inspection of the harnesses to verify that they are marked and installed correctly, and corrective action if necessary. We are issuing this AD to detect and correct incorrectly installed harnesses for the cargo fire suppression system bottles, which could result in an incorrect activation sequence of the bottles, the inability to suppress a cargo fire quickly, and a possible uncontrollable fire.
88-25-10: 88-25-10 EMPRESA BRASILEIRA DE AERONAUTICA, S.A. (EMBRAER): Amendment 39-6086. Applicability: Models EMB-110P1 and EMB-110P2 (serial numbers (S/N) 110001 up to and including S/N 110466) airplanes equipped with multi position flap control switch P/N 110- 898-14, certificated in any category. Compliance: Within the next 50 hours time-in-service after the effective date of this AD, unless previously accomplished. To reduce the potential for inadvertent full flap extension that could result in loss of control of the airplane in a critical phase of flight, accomplish the following: (a) Replace the flap control switch, P/N 110-898-14, with flap control switch P/N 110-898-14, Revision S, in accordance with Part I of EMBRAER Service Bulletin (SB) 110-027-0084, dated March 23, 1988; or (b) Modify the flap control switch, P/N 110-898-14, in accordance with Part II of EMBRAER SB 110-027-0084, dated March 23, 1988, and electrically test the reassembled switch and adjust the potentiometer, if required, to resistance values specified for P/N 110-898- 14, Revision G, after the above modification in accordance with Section 2A "Adjusting the Potentiometer" as described in EMBRAER "Maintenance Manual with Illustrated Parts List", No. T.P. 27-50-00/646, dated February 15, 1985. The above modification, test and adjustment must be performed by an appropriately rated repair station. (c) Airplanes may be flown in accordance with FAR 21.197 to a location where this AD may be accomplished. (d) An equivalent means of compliance with this AD may be used if approved by the Manager, Atlanta Aircraft Certification Office, FAA, Central Region. All persons affected by this directive may obtain copies of the documents referred to herein upon request to EMBRAER, 276 S.W. 34th Street, Fort Lauderdale, Florida 33315, or may examine these documents at the FAA, Office of the Assistant Chief Counsel, Room 1558, 601 East 12th Street, Kansas City, Missouri 64106. This amendment (39-6086, AD 88-25-10) becomes effective January 5, 1989.
68-02-05: 68-02-05 MCDONNELL DOUGLAS: Amdt. 39-559. Applies to Model DC-9 Series airplanes. \n\n\tType Certificate Data Sheet No. A6WE, Revision 5, established a service life limit of 26,700 landings for the Nose Landing Gear Shock Strut Restrictor Assembly which is a component of the Nose Landing Gear Cylinder Assembly on DC-9 Series airplanes. The Nose Landing Gear Shock Strut Restrictor Assembly is available under three (3) part numbers. P/N 5958435-501 (Models DC-9-11, -12, -13, -14, -15 and -15F) and P/N 5920616-1 (Models DC-9-31, 32 and -32F) have a 3/8-inch hole near the packing groove at the upper end of the support assembly and are affected by this AD. The third part, P/N 5958435-1 (Models DC-9-11, -12, -13, -14, -15 and -15F) which has no hole, is not affected by this AD. \n\n\tAs a result of further fatigue testing, McDonnell Douglas has established a new service life limit of 8,000 landings for P/N 5958435-501 and P/N 5920616-1 due to fatigue failure in the vicinity of the hole. \n\n\tLater revisions of Type Certificate Data Sheet No. A6WE will list the new service life limit for these parts. \n\n\tTo prevent fatigue failure: \n\n\tAs of the effective date of this AD, the service life limit of P/N 5958435-501 and P/N 5920616-1 Nose Landing Gear Shock Strut Restrictor Support Assembly is 8,000 landings. \n\n\tThis amendment becomes effective on February 29, 1968.
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.