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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]]
66-28-04: 66-28-04 LOCKHEED: Amdt. 39-310 Part 39 Federal Register November 15, 1966. Applies to Models 188A and 188C Series Airplanes with Steering Housing, P/N 800905-1, with 4,000 or More Landings. Compliance required as indicated. (a) For airplanes that have not been inspected in accordance with (d) within the last 200 landings before the effective date of this AD, comply with (d) within the next 300 landings after the last inspection before the effective date of this AD, and thereafter at intervals not to exceed 100 landings from the last inspection. (b) For airplanes that have been inspected in accordance with (d) within the last 200 landings before the effective date of this AD, comply with (d) within the next 100 landings after the effective date of this AD, and thereafter at intervals not to exceed 100 landings from the last inspection. (c) Within the next 500 landings after November 18, 1965, unless already accomplished within the last 700 landings before November 19, 1965, comply with (e), and thereafter at intervals not to exceed 1,200 landings from the last inspection. (d) Visually inspect steering housing, P/N 800905-1, for hydraulic oil leaks. If a leak is indicated, inspect steering housing, P/N 800905-1, before further flight in accordance with (e). (e) Inspect the 4 1/8-12 UNS-3A screw threaded portion of the bosses on both sides of the steering housing, P/N 800905-1, for cracks using the dye penetrant procedure outlined in Lockheed Alert Service Bulletin 88/SB-576B or an equivalent approved by the Chief, Aircraft Engineering Division, FAA Western Region. Gain access to the screw threads by accomplishing the instructions of Sections 2.A through 2.D of Lockheed Alert Service Bulletin 88/SB-576, Revision 1. (f) Replace any cracked steering housings detected during the inspection specified in (e) before further flight in accordance with the instructions of Sections 2.G through 2.K of Lockheed Alert Service Bulletin 88/SB-576, Revision 1, with a new steering housing, P/N 800905- 1, or with a new improved steering housing, P/N 800905-101. (g) If a housing, P/N 800905-1, is replaced with a new housing of the same part number or had been replaced prior to the effective date of this AD, inspect in accordance with (d) within 4,100 landings following replacement and thereafter at intervals not to exceed 100 landings from the last inspection, and inspect in accordance with (e) within 4,500 landings following replacement and thereafter at intervals not to exceed 1,200 landings from the last inspection. (h) For the purpose of compliance with this AD, subject to acceptance by the assigned FAA maintenance inspector, the number of landings may be determined by dividing the airplane's hours' time in service since the installation of the steering housing, by the operator's fleet average time from takeoff to landing for the airplane type. (i) Upon request of the operator, an FAA maintenance inspector, subject to prior approval of the Chief, Aircraft Engineering Division, FAA Western Region, may adjust the repetitive inspection intervals specified in this AD to permit compliance at an established inspection period of the operator if the request contains substantiating data to justify the increase for such operator. This supersedes AD 65-26-04. This directive effective November 25, 1966.
58-07-01: 58-07-01 HARTZELL: Applies to All HC-12X20, HC-13X20, HC-82X and HC-83X Series Propellers. Compliance required at the next propeller overhaul. To minimize the possibility of fatigue failure of the split rings used to retain the blades in the hub, replace all unmarked split rings with new split rings marked with the letter "N". The new production rings have a higher safety factor. Recent failures involving the old type split rings have been covered in airworthiness directives concerned with the particular propeller model or hub-blade combination involved. (Hartzell Service Bulletin No. 58 covers this same subject.)
68-26-06: 68-26-06 BEECH: Amdt. 39-702 as amended by Amendment 39-712, 39-1040 and 39- 1469 is further amended by Amendment 39-1776. Applies to Models 95-55, 95-A55, B95A, D95A, E95, 95-B55, 95-B55A, 95-B55B, 95- C55, 95-C55A, D55 and D55A Airplanes. NOTE: Amendment 39-1776, effective February 5, 1974, removed the Model 95 and B95 airplanes from the applicability block of this AD. Placard and Flight Manual revisions previously required to be installed in these model airplanes by this AD may be removed. Compliance required as indicated unless already accomplished. To prevent engine power loss accomplish the following: (A) Effective immediately, turning type takeoffs or a takeoff immediately following a fast taxi turn is prohibited. (B) Within 10 hours' time in service after the effective date of this airworthiness directive, either install a permanent type placard on the lower portion of the pilot's shock mounted instrument panel utilizing a minimum of 1/8 inchhigh letters or at any equivalent location approved by the FAA with the following wording: "TAKE OFF AND LAND ON MAIN TANKS ONLY. TURNING TYPE TAKEOFFS OR TAKEOFFS IMMEDIATELY FOLLOWING FAST TAXI TURNS PROHIBITED. REFER TO FAA FLIGHT MANUAL FOR OTHER FUEL SYSTEM LIMITATIONS." and revise the Airplane Flight Manual to include Beech Part No. 130776 AFM Supplement dated November 27, 1968 with the exception that the portion a. and b. under "For Ground Operation" is to be deleted. (C) Airplanes in which fuel cells have been installed in both wings in accordance with Beech Service Instructions 0459-281 (Beech Kit Nos. 35-9009-1S, 35-9009-2S, 35-9009-3S or 35-9009-4S) or 365-281, Rev. 1 (Beech Kits 35-9009S or 35-9009-5S), or later revisions, or which have fuel reservoirs installed in both wings per Beech Kit 35-9012 or a fuel reservoir in one wing and a baffled cell in the other, are exempt from compliance with this AD. When either of these installations has been accomplished, the placard and the revisions to the Airplane Flight Manual required by Paragraph B of the AD may be removed. The limitations for baffled cells in Airplane Flight Manual Supplement, P/N 96-590011-7 dated February 11, 1972, or later revision, are applicable to installation of either baffled cells or fuel reservoirs. NOTE: The operator may make and install the above placard. 3/16 inch high letters must be used if the placard is installed at a location other than the pilot's shock mounted instrument panel. Amendment 39-702 became effective January 1, 1969. Amendment 39-712 became effective January 27, 1969. Amendment 39-1040 became effective July 24, 1970. Amendment 39-1469 became effective June 28, 1972. This amendment 39-1776 becomes effective February 5, 1974.
2015-26-07: We are adopting a new airworthiness directive (AD) for all The Boeing Company Model 767-200, -300, and -300F series airplanes. This AD was prompted by a finding that certain barrel nuts installed at the vertical fin may be subject to stress corrosion and cracking. This AD requires either repetitive inspections of vertical fin barrel nuts for corrosion or a magnetic check to identify certain barrel nuts, and corrective actions if necessary. We are issuing this AD to detect and correct corroded and loose barrel nuts that attach the vertical fin to body section 48; this condition could result in reduced structural integrity of the vertical fin attachment joint, loss of the vertical fin, and consequent loss of controllability of the airplane.
89-08-02: 89-08-02 GROB WERKE GMBH & COMPANY KG (BURKHART GROB): Amendment 39-6174. Applicability: Models G103 TWIN II and G103 A TWIN II ACRO (serial numbers 3501 through 3878, and 33879 through 34078) gliders. Compliance: As indicated in the body of the AD. To preclude failure of the flight control systems, accomplish the following: (a) Within the next 10 hours time-in-service after the effective date of this AD, inspect the control systems for weld cracks in accordance with the instructions contained in Grob Service Bulletin (S/B) TM315-37, dated July 22, 1988. (b) If weld cracks are found per the inspection specified in paragraph (a) of this AD, prior to further flight repair the cracks and modify the glider in accordance with the instructions in the above referenced S/B. (c) If weld cracks are not found per the inspection specified in paragraph (a) of this AD, within the next 100 hours time-in-service after the effective date of this AD, modify the gliderin accordance with the instructions in the above referenced S/B. (d) An equivalent means of compliance with this AD may be used if approved by the Manager, Brussels Aircraft Certification Staff, AEU-100, FAA, c/o American Embassy, 15 Rue de la Loi B1040, Brussels, Belgium. All persons affected by this directive may obtain copies of the documents referred to herein upon request to Grob Systems, Incorporated, Aircraft Division, I-75 and Airport Drive, Bluffton, Ohio 45817; 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 (39-6174, AD 89-08-02) becomes effective on April 27, 1989.
88-12-09: 88-12-09 BOEING HELICOPTER COMPANY (BOEING VERTOL; VERTOL) AND KAWASAKI HEAVY INDUSTRIES, LTD: Amendment 39-5919. Applies to Boeing Helicopter Company Model 107-II and Kawasaki Model KV107- IIA helicopters, certificated in any category (Airworthiness Docket 88-ASW-10). Compliance is required as indicated, unless already accomplished. To prevent possible hazards in flight associated with a cracked aft main rotor shaft slider guide, Part Number (P/N) 107R3574-1, accomplish the following: (a) Within the next 10 hours time in service from the effective date of this AD, or before the accumulation of 1,200 hours time in service, whichever comes later, perform a dye penetrant inspection of the two forward lug areas of the aft main rotor shaft slider guide for cracks in accordance with paragraph 2, "Accomplishment Instructions," Boeing Helicopter Co., Service Bulletin No. 107-370R1, dated September 21, 1987. (b) After the initial inspection of paragraph (a), repeat the dye penetrant inspection at intervals not to exceed 50 hours time in service from the last inspection. (c) Remove cracked slider guides from service and replace with a serviceable part prior to further flight. (d) Upon submission of substantiating data by an owner or operator through an FAA maintenance inspector, the Manager, New York Aircraft Certification Office, FAA, New England Region, may adjust the compliance times specified in this AD. (e) An alternate method of compliance which provides an equivalent level of safety may be used when approved by the Manager, New York Aircraft Certification Office, 181 South Franklin Avenue, Valley Stream, New York 11581. (f) In accordance with FAR sections 21.197, and 21.199, flight is permitted to a base where the requirements of this AD may be accomplished. The procedures shall be done in accordance with paragraph 2, "Accomplishment Instructions," Boeing Helicopter Co., Service Bulletin No. 107-370R1, dated September 21, 1987. This incorporation by reference was approved by the Director of the Federal Register in Accordance with 5 U.S.C. 552(a) and 1 CFR Part 51. Copies may be obtained from Boeing Helicopter Company, Boeing Center, P.O. Box 16858, Philadelphia, Pennsylvania 19141. These documents may be examined at the Office of the Regional Counsel, FAA, Southwest Region, 4400 Blue Mound Road, Fort Worth, Texas, or the Office of the Federal Register, 1100 L Street, N.W., Room 8401, Washington, D.C. This amendment, 39-5919, becomes effective June 2, 1988.