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98-18-25: This amendment adopts a new airworthiness directive (AD), applicable to certain Fokker Model F28 Mark 1000, 2000, 3000, and 4000 series airplanes, that requires replacement of certain hinges on the forward, center, and aft cargo doors with improved hinges. This amendment is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified by this AD are intended to prevent failure of the cargo door hinges caused by stress corrosion or fatigue cracks, which could result in decompression of the airplane, and possible in-flight separation of the cargo door.
98-18-12: This amendment adopts a new airworthiness directive (AD) that is applicable to certain Textron Lycoming fuel injected reciprocating engines with certain Crane/Lear Romec "AN" rotary fuel pumps installed. This action requires initial and repetitive torque check inspections of pump relief valve attaching screws. In addition, if the torque remains within acceptable values after two inspections, the repetitive torque check inspections may be terminated. This amendment is prompted by reports of inflight engine fires caused by leaking rotary fuel pumps. The actions specified in this AD are intended to prevent rotary fuel pump leaks, which could result in an engine failure, engine fire, and damage to or loss of the aircraft.
70-03-04 R1: 70-03-04 R1 CESSNA: Amendment 39-933 as amended by Amendment 39-5564. Applies to the following serial numbered Models T310P, T310Q, 320D, 320E and 320F airplanes equipped with Teledyne Continental Model TSIO-520B engines, and to the following serial numbered Models 401, 401A, 401B, 402, 402A and 402B airplanes equipped with Teledyne Continental Model TSIO-520E engines: MODEL SERIAL NUMBER T310P T310P0001 thru T310P0240 T310Q T310Q0001 thru T310Q0291 320D 320D0001 thru 320D0130 320E 320E0001 thru 320E0110 320F 320F0001 thru 320F0045 401 4010001 thru 4010322 401A 401A0001 thru 401A0132 401B 401B0001 thru 401B0121 402 4020001 thru 4020322 402A 402A0001 thru 402A0129 402B 402B0001 thru 402B0122 Compliance: Within 25 hours time-in-service (TIS) after the effective date of this AD on airplanes with turbosupercharger turbine housings having 400 hours or more TIS, or at or before 425 hours TIS on turbosupercharger turbine housings having less than 400 hours TIS and thereafter at intervals not to exceed 100 hours TIS, unless already accomplished. To detect incipient failure of turbosupercharger turbine housings installed in the above airplanes, accomplish the following: (a) Remove the engine top cowling and the turbosupercharger turbine insulation blanket and visually inspect the complete surface of the turbine housing of the TCM turbosupercharger assembly P/N 632729 (AID P/N 406610) for cracks, bulges and burnt areas. Remove and reinstall the turbosupercharger insulation blanket in accordance with applicable Cessna Service Manuals. (b) If cracks, bulges or burnt areas are found during the inspection required by paragraph (a) of this AD, prior to further flight, replace the defective part with an airworthy part. (c) Replacement of the turbosupercharger turbine insulation blanket with stainless steel heat shields in accordance with Cessna Multi-engine Service Letter ME72-4, dated March 24, 1972, will terminate further time interval repetitive inspections required by this AD. However, the inspection cited in paragraph (a) above and any necessary corrective action in paragraph (b) above must be completed at the time of the heat shield installation. (d) Any equivalent method of compliance with this AD, if used, must be approved by the Manager, Wichita Aircraft Certification Office, FAA, 1801 Airport Road, Room 100, Wichita, Kansas 67209. All persons affected by this directive may obtain copies of the document(s) referred to herein upon request to Cessna Aircraft Company, Customer Services, P.O. Box 1521, Wichita, Kansas 67201; or may examine the document(s) referred to herein at the FAA, Rules Docket, Office of the Regional Counsel, Room 1558, 601 East 12th Street, Kansas City, Missouri 64106. NOTE 1: Cessna Multi-engine Service Letter No. ME70-3, dated January 9, 1970, ME70-3 Supplement I, dated February 9, 1970, and ME72-4, dated March 24, 1972, relate to this subject.NOTE 2: Time-in-service on turbosupercharger turbine housings may be determined from the engine maintenance records. This amendment revises AD 70-03-04, Amendment 39-933. This amendment becomes effective March 28, 1987.
80-15-51: 80-15-51 PRATT & WHITNEY AIRCRAFT: Amendment 39-3898. Applies to JT8D-1, -1A, -1B, -5, -7, -7A, -7B, -9, -9A, -11, -15, -17, -17R, -209, and -209A model turbofan engines. Compliance is required as indicated. To prevent uncontained failure of engine rear compressor front hubs, accomplish the following: Inspect, in accordance with the following schedule, unless already accomplished, all eighth stage rear compressor front hubs, P/Ns 690908, 701308, 717608, 717708, and 738308, which contain balance cuts, for cracks in accordance with the ultrasonic or fluorescent magnetic particle procedures contained in Pratt & Whitney Aircraft Alert Service Bulletin ASB 5154, Revision No. 1, dated July 16, 1980, or later revision approved by the Chief, Engineering and Manufacturing Branch, FAA, New England Region: ENGINE MODEL HUB TOTAL CYCLES AS OF JULY 21, 1980 INSPECTION REQUIRED JT8D-1, -1A, -1B, -5, -7, -7A, and -7B A) Less than 13,000. A) Before accumulation of 15,000 cycles. B) Within the next 2,000 than 15,000. B) 13,000 or more and less cycles. C) 15,000 or more. C) Before accumulation of 17,000 cycles or within the next 500 cycles, whichever is later. JT8D-9, -9A, -11, -15, -209, and -209A A) Less than 10,000. A) Before accumulation of 12,000 cycles. B) 10,000 or more and less than 12,000. B) Within the next 2,000 cycles. C) 12,000 or more and less than 14,000. C) Before accumulation of 14,000 cycles or within the next 500 cycles, whichever is later. D) 14,000 or more and less than 15,000. D) Within the next 500 cycles. E) 15,000 or more and less than 16,000. E) Within the next 300 cycles. F) 16,000 or more. F) Within the next 200 cycles. JT8D-17 and -17R A) Less than 11,000. A) Before accumulation of 12,000 cycles. B) 11,000 or more and less than 12,000. B) Within the next 1,000 cycles. C) 12,000 or more and less than 13,000. C) Before accumulation of 13,000 cycles or within the next 500 cycles, whichever is later. D) 13,000 or more and less than 13,500. D) Within the next 500 cycles. E) 13,500 or more and less than 14,000. E) Before accumulation of 14,000 cycles or within the next 100 cycles, whichever is later. F) 14,000 or more. F) Within the next 100 cycles, unless already accomplished. All models Inspect thereafter at intervals not to exceed 6,000 cycles in service since last inspection. (NOTE: Established life limits are not to be exceeded.) Remove from service, before further flight, any rear compressor front hub having a crack indication. Report defects found to Chief, Engineering and Manufacturing Branch, FAA, New England Region, 12 New England Executive Park, Burlington, Massachusetts 01803, within 5 days of the inspection. (Reporting approved by the Office of Management and Budget under OMB No. 04-R0174.) Airplanes may be ferried in accordance with the provisions of FAR 21.197 to a base where the AD can be accomplished. Upon request of the operator an equivalent means of compliance with the requirements of this AD may be approved by the Chief, Engineering and Manufacturing Branch, FAA, New England Region. 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 Pratt & Whitney Aircraft, East Hartford, Connecticut 06108. These documents may also be examined at FAA, New England Region, 12 New England Executive Park, Burlington, Massachusetts 01803, and at FAA Headquarters, 800 Independence Avenue, S.W., Washington, D.C. A historical file on this AD is maintained by the FAA at its headquarters in Washington, D.C., and at the FAA, New England Region Headquarters, Burlington, Massachusetts. This AD supersedes AD T80-14-51 issued July 3, 1980. This Amendment 39-3898 becomes effective August 21, 1980, as to all persons except those persons to whom it was made immediately effective by the telegram of July 16, 1980.
2022-08-14: The FAA is adopting a new airworthiness directive (AD) for all The Boeing Company Model 747-8F series airplanes. This AD was prompted by reports of fuselage crown stringer cracking between station (STA) 740 and STA 1000, stringer (S)-7 to S-12. This AD requires repetitive detailed inspections for cracking of fuselage crown stringers and applicable on-condition actions. The FAA is issuing this AD to address the unsafe condition on these products.
2010-12-04: We are adopting a new airworthiness directive (AD) for the products listed above. 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: This Airworthiness Directive (AD) is prompted due to the discovery of corrosion at the bonding strap connections on the left and right lower longerons between fuselage frames 1 and 1A. The possibility of corrosion is increased because of the high electrical current flow between the tinned copper terminal lug of the bonding strap and the aluminum longeron. Such a condition, if left uncorrected, could lead to failure of the longeron and will prejudice the structural integrity of the aircraft. We are issuing this AD to require actions to correct the unsafe condition on these products.
98-19-10: This amendment adopts a new airworthiness directive (AD) that is applicable to CFM International (CFMI) CFM56-3, -3B, and -3C series turbofan engines. This action requires, on aircraft with two affected engines installed, removal of one affected engine from an aircraft, and replacement with a serviceable engine, or replacement of a suspect accessory gearbox (AGB) starter gearshaft with a serviceable gearshaft within 350 hours time in service (TIS) after the effective date of this AD, or by September 1, 1998, whichever occurs first. This action also requires, on aircraft with only one affected engine installed, removal of the affected engine from the aircraft, and replacement with a serviceable engine, or replacement of the suspect starter gearshaft with a serviceable gearshaft within 2,100 hours TIS after the effective date of this AD, or by February 1, 1999, whichever occurs first. This amendment is prompted by reports of two inflight engine shutdowns caused by an AGB starter gearshaft failure. The actions specified in this AD are intended to prevent an AGB starter gearshaft failure, which can result in an inflight engine shutdown, and on aircraft with two affected engines installed, possible dual inflight engine shutdown and forced landing.
2022-08-12: The FAA is superseding Airworthiness Directive (AD) 2020-21- 17, which applied to all The Boeing Company Model 757 airplanes. AD 2020-21-17 required repetitive inspections for skin cracking and shim migration at the upper link drag fittings, diagonal brace cracking, and fastener looseness; and applicable on-condition actions. This AD was prompted by reports of bolt rotation in the engine drag fitting joint and fastener heads and cracks found in the skin of the fastener holes, and the need to reduce the compliance time for certain groups. This AD retains the requirements of AD 2020-21-17 with reduced compliance times for certain airplane groups. The FAA is issuing this AD to address the unsafe condition on these products.
98-19-05: This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 757-200 series airplanes, that requires the application of a sealant, secondary fuel barrier, and corrosion-inhibiting compound to certain portions of the wing center section. This amendment is prompted by reports indicating that, during manufacture, the secondary fuel barrier was not applied to certain portions of the wing center section. The actions specified by this AD are intended to prevent leakage of fuel through the fasteners, sealant, or structural cracks in the center section structure, which could result in fuel or fuel vapors entering the cargo or passenger compartment of the airplane.
98-19-01: This amendment adopts a new airworthiness directive (AD) that applies to certain Stemme GmbH & Co. KG (Stemme) Model S10 sailplanes. This AD requires replacing the O-ring that is installed in the mounting part of the pitot tube (in the propeller dome) with one of improved design. This AD is the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for Germany. The actions specified by this AD are intended to prevent failure of the pitot tube O-ring caused by an ineffective design, which could result in the pitot tube falling out and the sailplane pilot losing airspeed indications.