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86-23-03: 86-23-03 PRATT & WHITNEY: Amendment 39-5455. Applies to Pratt & Whitney (PW) JT9D-7R4D, D1, E, and E1 turbofan engines. Compliance is required as indicated, unless already accomplished. To prevent failure of the second stage high pressure turbine rotor (HPTR) airseal that can cause an uncontained engine failure, accomplish the following: (a) Remove from service, HPTR airseal Part Number (P/N) 5001413-01 or 798916 and replace with HPTR airseal P/N 803673 or 803674, respectively, or rework HPTR airseal P/N 5001413-01 or 798916 in accordance with PW Alert Service Bulletin (ASB) JT9D-7R4-72-318, dated October 25, 1986, or FAA approved equivalent, per the following schedule: (1) JT9D-7R4D1 and JT9D-7R4E1 series engines: (i) Within 400 cycles in service (CIS) after the effective date of this AD, for HPTR airseals with greater than 800 CIS since new on the effective date of this AD. (ii) Within 400 CIS after the effective date of this AD, or 800 CIS since new, whichever occurs later, for HPTR airseals with 800 CIS since new or less on the effective date of this AD. (2) JT9D-7R4D and JT9D-7R4E series engines: (i) Within 900 CIS after the effective date of this AD, for HPTR airseals with greater than 1,600 CIS since new on the effective date of this AD. (ii) Within 900 CIS after the effective date of this AD, or 1,600 CIS since new, whichever occurs later, for HPTR airseals with 1,600 CIS since new or less on the effective date of this AD. (b) Remove first stage high pressure turbine cooling (HPTC) airduct assembly, P/N 796123, 796975, or 796746, and replace with HPTC airduct assembly, P/N 804146, 804145, or 804148, respectively, or rework HPTC airduct assembly, P/N 796123, 796975, or 796746, in accordance with PW ASB JT9D-7R4-72-318, dated October 25, 1986, or FAA approved equivalent, concurrent with accomplishing paragraph (a) above. (c) Modify the first stage turbine rotor assembly, P/N 792041, 792931,795121, or 801821, by removing two units each of bolt, P/N 746130; washer, P/N 151178; and nut, P/N 341859; and redistributing the remaining units in accordance with PW ASB JT9D-7R4-72-318, dated October 25, 1986, or FAA approved equivalent, concurrent with accomplishing paragraph (a) above. Aircraft may be ferried in accordance with the provisions of FAR 21.197 and 21.199 to a base where the AD can be accomplished. Upon request, an equivalent means of compliance with the requirements of this AD may be approved by the Manager, Engine Certification Office, Aircraft Certification Division, Federal Aviation Administration, New England Region, 12 New England Executive Park, Burlington, Massachusetts 01803. Upon submission of substantiating data by an owner or operator through an FAA maintenance inspector, the Manager, Engine Certification Office, may adjust the compliance times specified in this AD. Pratt & Whitney ASB JT9D-7R4-72-318, dated October 25, 1986, identifiedand described in this document, is 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 this document from the manufacturer may obtain copies upon request to Pratt & Whitney, Commercial Products Division, 400 Main Street, East Hartford, Connecticut 06108. This document also may be examined at the Office of the Regional Counsel, Federal Aviation Administration, 12 New England Executive Park, Burlington, Massachusetts 01803, Room 311, Rules Docket Number 86-ANE-42, between the hours of 8:00 a.m. and 4:30 p.m., Monday through Friday, except Federal holidays. This amendment becomes effective on December 8, 1986.
98-04-15: This amendment adopts a new airworthiness directive (AD), applicable to AlliedSignal Inc., (formerly Garrett Engine Division, Garrett Turbine Engine Company and AiResearch Manufacturing Company of Arizona) TPE331 series turboprop and TSE331 turboshaft engines, that requires replacement or radiographic inspection, and replacement, if necessary, of certain third stage turbine stators with serviceable parts. This amendment is prompted by a report of an outer band weld that cracked subsequent to a radiographic inspection required by a previous AD. The actions specified by this AD are intended to prevent third stage turbine wheel separation due to thermal fatigue cracking and shifting of the third stage turbine stator, which could contact the third stage turbine wheel and result in an uncontained engine failure and damage to the aircraft.
87-02-08: 87-02-08 BEECH: Amendment 39-5568. Applies to the following serial-numbered airplanes certificated in any category: MODEL SERIAL NUMBERS A23-19, 19A, M19A and B19 MB-1 thru MB-520 B19 Sport 150 MB-521 thru MB-905 23, A23, A23A, B23, C23 M-1 thru M-1361 C23 Sundowner 180 M-1362 thru M-2156, M-2158 thru M- 2392 A23-24, A24 MA-1 thru MA-368 A24R MC-2 thru MC-95 A24R, B24R, C24R Sierra 200 MC-96 thru MC-795 Compliance: Required prior to further flight on all airplanes and each 100 hours time-in- service (TIS) thereafter for normal and utility category airplanes, and each 25 hours TIS thereafter for acrobatic category airplanes, unless already accomplished. To preclude failure of the fasteners securing the stabilator hinge assemblies and subsequent loss of pitch control, accomplish the following: (a) Visually inspect the fasteners securing the stabilator hinge assemblies to the fuselage for looseness or failure in accordance with the "ACCOMPLISHMENT INSTRUCTIONS" in Beech Service Bulletin No. 2182, issued February 1987. (b) If any fasteners are found loose or failed when conducting the inspections required in paragraph (a) above, prior to further flight, replace all fasteners securing both the right and left hinge assemblies to the fuselage in accordance with the above-referenced service bulletin. (c) Airplanes may be flown in accordance with FAR 21.197 to a location where this AD may be accomplished. (d) An equivalent method of compliance with this AD may be used when approved by the Manager, Wichita Aircraft Certification Office, Federal Aviation Administration (FAA), Central Region, 1801 Airport Road, Room 100, Mid-Continent Airport, Wichita, Kansas 67209. All persons affected by this directive may obtain copies of the document(s) referred to herein upon request to Beech Aircraft Corporation, Commercial Service Department, P.O. Box 85, Wichita, Kansas 67201; or may examine the document(s) referred to herein at the FAA, Office of the Regional Counsel, Room 1558, 601 East 12th Street, Kansas City, Missouri 64106. This amendment becomes effective on March 4, 1987, to all persons except those to whom it has already been made effective by priority letter from the FAA dated January 27, 1987, and is identified as AD 87-02-08.
2022-05-07: The FAA is adopting a new airworthiness directive (AD) for all Airbus SAS Model A350-941 and -1041 airplanes. This AD was prompted by a report that in the event of a specific discrete wire failure, the landing gear extension and retraction system (LGERS) may not be able to complete landing gear retraction when commanded by moving the landing gear lever to the UP position. This AD requires revising the operator's existing FAA-approved minimum equipment list (MEL) for the LGERS, as specified in a European Union Aviation Safety Agency (EASA) AD, which is incorporated by reference. The FAA is issuing this AD to address the unsafe condition on these products.
2022-03-21: The FAA is adopting a new airworthiness directive (AD) for certain The Boeing Company Model 787-8, 787-9, and 787-10 airplanes. This AD was prompted by significant changes, including new or more restrictive requirements, made to the airworthiness limitations (AWLs) related to fuel tank ignition prevention and the nitrogen generation system. This AD requires revising the existing maintenance or inspection program, as applicable, to incorporate new or more restrictive airworthiness limitations. The FAA is issuing this AD to address the unsafe condition on these products.
98-02-51: This document publishes in the Federal Register an amendment adopting Airworthiness Directive (AD) 98-02-51 that was sent previously to all known U.S. owners and operators of Boeing Model 737-300, -400, and -500 series airplanes by individual telegrams. This AD requires a one-time general visual inspection to detect any missing fasteners on the top and bottom of the leading edge skin where it attaches to the front spar of the horizontal stabilizer. This AD also requires a one-time detailed visual inspection to detect any loose or missing fasteners of the attachment of the elevator hinge plates to the horizontal stabilizer rear spar fittings. If a loose or missing fastener is detected, this AD requires installation of a new or serviceable fastener. This action is prompted by reports of loose or missing fasteners of the leading edge structure and elevator attachment fitting of the right-hand horizontal stabilizer. The actions specified by this AD are intended to preventreduced structural integrity of the horizontal stabilizer due to loose or missing fasteners.
47-47-07: 47-47-07 BEECH: (Was Mandatory Note 1 of AD-777-1.) Applies to Model 35 Serial Numbers D1 to D491, Inclusive. Compliance required prior to next annual inspection. Replace the engine identification plate containing either E-165-4 or E-165-4A model designation with an identification plate, furnished by the engine manufacturer, having E-185-1 stamped in the engine designation block. The engine model designation, E-165-4 or E-165-4A, stamped on the airplane's identification plate should be permanently deleted through the use of a sharp-pointed instrument. (Beech Service Bulletin No. 35-3 covers this same subject.)
2022-05-08: The FAA is adopting a new airworthiness directive (AD) for certain General Electric Company (GE) CF34-10E model turbofan engines. This AD was prompted by a manufacturer investigation that revealed Teflon material in the A-sump oil strainer (strainer assembly) screen after several reports of in-flight shutdowns (IFSDs) and unscheduled engine removals (UERs). This AD requires initial and repetitive visual inspections of the strainer assembly screen. As a terminating action to the initial and repetitive visual inspections, this AD requires the replacement of the stationary oil seal at the No. 1 forward bearing. The FAA is issuing this AD to address the unsafe condition on these products.
51-27-01: 51-27-01 BELL: Applies to All Model 47 Helicopters Incorporating Engine Mount Assembly P/N 47-612-111-1 or -5. Compliance required as indicated. 1. Compliance required daily after first 300-hour inspection. (a) Remove paint from welds in tube cluster at mount housing at both sides of mount assembly. Use solvent to remove paint. (b) With the engine mount under load, either by operating the engine with maximum collective pitch without becoming airborne, or by placing equivalent pilot and passenger weights in the seat and hoisting helicopter until wheels are clear of ground (or any equivalent loading means), inspect the outboard surface of welds with at least a 10-power magnifying glass and the inboard surfaces of welds with an inspection mirror (use magnifying if available). Give particular attention to forward tube in left cluster (from top of mount to housing) and aft tube in right cluster. Oil appearing on surface of weld or tube after cleaning is evidenceof a crack and must be examined carefully. Replace mount if crack is found. (c) Clean welds in upper forward tube (under collective pitch disc bracket) with a cloth. Carefully inspect welds under disc bracket for cracks using a flashlight and mirror. Give particular attention to weld which joins diagonal tube (right side) to forward tube. Replace mount immediately if a crack is found in these areas. Apply grease or other corrosion preventive on areas where paint has been removed. 2. Compliance required at each 600 hours of engine mount service. Replace engine mount assembly after 600 hours of operation have been accumulated. (Bell Service Bulletin No. 74, revised February 2, 1953, covers this same subject.) This supersedes AD 51-23-02.
98-04-42: This amendment adopts a new airworthiness directive (AD), applicable to all Grumman Model TS-2A series airplanes, that requires revising the Airplane Flight Manual (AFM) to modify the limitation that prohibits positioning the power levers below the flight idle stop during flight, and to add a statement of the consequences of such positioning of the power levers. This amendment is prompted by incidents and accidents involving airplanes equipped with turboprop engines in which the ground propeller beta range was used improperly during flight. The actions specified by this AD are intended to prevent loss of airplane controllability, or engine overspeed and consequent loss of engine power, caused by the power levers being positioned below the flight idle stop when the airplane is in flight.