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88-02-02: 88-02-02 GLASER-DIRKS FLUGZEUGBAU GmbH: Amendment 39-5814. Applies to Model DG-400 motor gliders, work numbers 4-1 thru 4-188, certificated in any category. Compliance is required as indicated unless already accomplished. To prevent damage to the drive pinion gears on the spindle motor that operates the engine extension/retraction mechanism, which could result in the inability to obtain power in flight, accomplish the following: (a) Within the next 10 hours' time in service after the effective date of this AD accomplish the following in accordance with the procedures specified in Glaser-Dirks Technical Note TN 826/18; dated March 10, 1987: (1) Replace pages in the aircraft handbook Flight and Maintenance Manuals in accordance with Procedure 1. (2) Check the engine extension time in accordance with Procedures 2 and 3. If this extension time exceeds 13 seconds: Within 25 hours time in service after the effective date of this AD, or 90 days, whichever comes first, replace the gas strut with Type 10-02-250-600/1200-N in accordance with Procedure 3 (procedures described on Page 41 of the Maintenance Manual). If extension time is 13 seconds or less, proceed to paragraph (b). NOTE: Replacement of pages in the aircraft handbook Flight and Maintenance Manuals and the check of the engine extension time may be accomplished by the pilot. (b) Within 25 hours time in service after the effective date of this AD, or 90 days, whichever comes first, modify the spindle drive in accordance with Procedure 4 of Glaser-Dirks Technical Note TN 826/18 (detailed procedures are described in Glaser-Dirks Service Instruction 1/10/86 dated March 10, 1987). This action must be accomplished regardless of whether the gas strut requires replacement. (c) Aircraft may be ferried in accordance with FAR Section 21.197 and Section 21.199 to a base where the AD can be accomplished. (d) Upon request, an equivalent means of compliance with the requirementsof this AD may be approved by the Manager, Brussels Aircraft Certification Office, Europe, Africa, and Middle East Office, Federal Aviation Administration, c/o American Embassy, 15 Rue de la Loi B-1040, Brussels, Belgium; telephone 513.38.30 ext. 2710, or the Manager, New York Aircraft Certification Office, Federal Aviation Administration, New England Region, 181 S. Franklin Avenue, Room 202, Valley Stream, New York 11581; telephone (516) 791-6690. (e) 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. Glaser-Dirks Technical Note TN 826/18, and Service Instruction 1/10/86, each dated March 10, 1987, 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 havenot already received these documents from the manufacturer may obtain copies upon request to Glaser-Dirks Flugzeugbau GmbH, Im Schollongarton 19-20, D-7520 Bruchsal 4, Federal Republic of Germany. These documents may also be examined at the Office of the Regional Counsel, Rules Docket No. 87-ANE-33, Room 311, Federal Aviation Administration, New England Region, 12 New England Executive Park, Burlington, Massachusetts 01803, between the hours of 8:00 a.m. and 4:30 p.m., Monday through Friday, except federal holidays. This amendment becomes effective on January 22, 1988.
2022-18-04: The FAA is adopting a new airworthiness directive (AD) for certain General Electric Company (GE) GEnx-1B model turbofan engines. This AD was prompted by several reports of fuel leaks caused by high cycle fatigue (HCF) cracks found at the braze joints on fuel manifolds, and the subsequent manufacturer redesign of the high-pressure turbine (HPT) fuel hose variable stator vane (VSV) manifold, VSV fuel hose manifold, low-pressure turbine (LPT) fuel hose variable bleed valve (VBV) manifold, and VBV fuel hose manifold. This AD requires removal and replacement of the fuel hydraulic lines. The FAA is issuing this AD to address the unsafe condition on these products.
2014-08-08: We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 737-200, -200C, -300, -400, and -500 series airplanes. This AD was prompted by reports of cracking found in the skin at the lower aft corner of the forward entry doorway on airplanes that do not have an airstair door cutout. This AD requires repetitive inspections for cracking in the lower corners of the forward entry doorway on airplanes that do not have an airstair door cutout, and repair if necessary. We are issuing this AD to detect and correct cracking in the lower corners of the forward entry doorway, which could lead to crack progression and consequent rapid decompression of the airplane.
89-23-15: 89-23-15 BOEING OF CANADA, LTD., DE HAVILLAND DIVISION: Amendment 39- 6384. Docket No. 89-NM-80-AD. Applicability: Model DHC-8-100 series airplanes, Serial Numbers 1 through 91, certificated in any category. Compliance: Required within the next 400 hours time-in-service after the effective date of this AD, unless previously accomplished. To prevent unwanted propeller feathering due to inadvertent activation of the alternate feather switches, accomplish the following: A. Modify the alternate feather system, in accordance with the Accomplishment Instructions of Boeing of Canada, Ltd., de Havilland Division, Service Bulletin No. 8-61-10, Revision A, dated August 5, 1988. B. 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, New York Aircraft Certification Office, FAA, New England Region. NOTE: 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, New York Aircraft Certification Office. C. 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 Boeing of Canada, Ltd., de Havilland Division, Garratt Boulevard, Downsview, Ontario M3K 1Y5, Canada. These documents may be examined at the FAA, Northwest Mountain Region, Transport Airplane Directorate, 17900 Pacific Highway South, Seattle, Washington, or New York Aircraft Certification Office, Engine and Propeller Directorate, Aircraft Certification Service, FAA, 181 South Franklin Avenue, Room 202, Valley Stream, New York 11581. This amendment (39-6384, AD 89-23-15) becomes effective on December 11, 1989.
99-19-19: This amendment adopts a new airworthiness directive (AD), applicable to certain Fokker Model F27 Mark 100, 200, 300, 400, 500, 600, and 700 series airplanes and Model F27 Mark 050 series airplanes, that requires revising the Airplane Flight Manual (AFM) to include requirements for activation of the airframe pneumatic deicing boots. This amendment is prompted by reports of inflight incidents and an accident that occurred in icing conditions where the airframe pneumatic deicing boots were not activated. The actions specified by this AD are intended to ensure that flightcrews activate the pneumatic wing and tail deicing boots at the first signs of ice accumulation. This action will prevent reduced controllability of the aircraft due to adverse aerodynamic effects of ice adhering to the airplane prior to the first deicing cycle.
82-18-09: 82-18-09 AIRCRAFT TANK SERVICE, INC.: Amendment 39-4449. Applies to Lockheed Model 1329 series airplanes, Avions Marcel Dassault Model Fan Jet Falcon series airplanes, and British Aerospace (Aircraft Group) Model DH-125 series airplanes which have been modified in accordance with STC SA2603WE, SA3221WE, SA3324WE, SA1851WE, or SA3382WE, certificated in all categories. Compliance required as indicated, unless already accomplished. To prevent possible engine fuel starvation, accomplish the following: A. Within the next 30 calendar days after the effective date of this AD, or before the accumulation of two years calendar time since the installation of tygothane tubing, whichever occurs later, inspect to determine the condition of the tygothane components in accordance with the appropriate service bulletin listed in the table below. 1. If there is cracking or brittleness, discontinue use of the single point refueling system and within 90 calendar days after the inspection, remove tygothane tubing systems components and replace with like serviceable components in accordance with Part III of the appropriate service bulletin. The appropriate service bulletin for each type airplane is shown below. Model STC No. Aircraft Tank Service, Inc. Service Bulletin Fan Jet Falcon SA1851WE A28-01 Rev. 1 dated January 21, 1982 DH-125 SA3382WE A28-02 Rev. 1 dated February 5, 1982 1329 SA2603WE A28-04 Rev. 1 dated January 29, 1982, or A28-05 Rev. 1 dated February 5, 1982 (see Service Bulletin effectivity) 1329 SA3221WE A28-05 Rev. 1 dated February 5, 1982 1329 SA3324WE A28-05 Rev. 1 dated February 5, 1982 2. If there is no cracking or brittleness but a chocolate brown color noted, continue operation and repeat inspection at six months from initial inspection and replace tygothane components per appropriate service bulletin within one year from initial inspection. 3. If the tygothane components are light colored, continue toinspect in accordance with paragraph A. of this AD at intervals not to exceed six months until such time as the tygothane components are replaced in accordance with Part III of the appropriate service bulletin. B. After the effective date of this AD, if difficulty in pressure refueling or spillage out of the vent line is encountered, inspect per paragraph A. of this AD, and: 1. If the tygothane tubing has started to break up and there is evidence of tygothane particles in the tank which could cause fuel system contamination, replace the tygothane tubing prior to next flight per Part III of the appropriate Service Bulletin. 2. If cracking or embrittlement is found without evidence of loose particles, discontinue use of the single point fueling system and replace the tygothane tubing within 90 days after the inspection in accordance with Part III of the appropriate Service Bulletin. C. Special flight permits may be issued in accordance with FAR 21.197 and 21.199 tooperate aircraft to a base for the accomplishment of inspections or modifications required by this AD. D. Alternate means of compliance which provide an equivalent level of safety may be used when approved by the Chief, Western Aircraft Certification Field Office, FAA Northwest Mountain Region, Hawthorne, California. 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 proposal who have not already received these documents from the manufacturer may obtain copies upon request to Aircraft Tank Service, Inc., Product Support Engineering, P.O. Box 1307, Sun Valley, California 91352. These documents may also be examined at FAA Northwest Mountain Region, 17900 Pacific Highway South, C-68966, Seattle, Washington 98168; or Western Aircraft Certification Field Office, 15000 Aviation Boulevard, Hawthorne, California 90261. This amendment becomes effective October 4, 1982.
2014-07-09: We are adopting a new airworthiness directive (AD) for British Aerospace Regional Aircraft Jetstream Series 3101 and Jetstream Model 3201 airplanes. This AD results from mandatory continuing airworthiness information (MCAI) issued 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 inadequate instructions for inspection for corrosion on the rudder upper hinge bracket and certain internal wing and drainage paths. We are issuing this AD to require actions to address the unsafe condition on these products.
99-19-09: This amendment adopts a new airworthiness directive (AD), applicable to certain Fairchild Model F-27 and FH-227 series airplanes, that requires revising the Airplane Flight Manual (AFM) to include requirements for activation of the airframe pneumatic deicing boots. This amendment is prompted by reports of inflight incidents and an accident that occurred in icing conditions where the airframe pneumatic deicing boots were not activated. The actions specified by this AD are intended to ensure that flightcrews activate the pneumatic wing and tail deicing boots at the first signs of ice accumulation. This action will prevent reduced controllability of the aircraft due to adverse aerodynamic effects of ice adhering to the airplane prior to the first deicing cycle.
99-24-04: This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model DC-9-80 series airplanes and Model MD-88 airplanes, that requires a one-time visual inspection to determine whether self-aligning nuts are installed at certain locations of the aft pressure bulkhead tee; and corrective actions, if necessary. This amendment is prompted by reports of failures of certain Hi-Lok pin fasteners of the aft pressure bulkhead tee due to installation of non-self-aligning nuts. The actions specified by this AD are intended to prevent failure of certain Hi-Lok pin fasteners and subsequent gouging of the aft pressure bulkhead tee, which could result in fatigue cracking and reduced structural integrity of the airplane.
99-23-24: This amendment adopts a new airworthiness directive (AD), applicable to certain instrument landing system (ILS) navigation receivers manufactured by AlliedSignal. This action requires replacement of certain resistors in the ILS navigation receiver with higher ohm resistors and replacement of the nameplate on the receiver with a new nameplate. This amendment is prompted by reports of ILS navigation receivers incorrectly indicating signals from the glideslope ground station during final approach. The actions specified in this AD are intended to ensure the ILS receiver provides the flight crew with accurate glideslope data. Inaccurate glideslope data could result in an approach off the glideslope, and, consequently, a landing short of the runway or a runway overrun.