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99-07-04: This amendment adopts a new airworthiness directive (AD), applicable to Williams International, L.L.C. FJ44-1A turbofan engines, that requires removing the high pressure turbine (HPT) disk from service prior to accumulating a reduced cyclic life limit of 1,900 cycles since new (CSN) and replacing with a serviceable disk. As an option, the HPT nozzle can be modified, thereby increasing the HPT disk cyclic life limit from the new reduced cyclic life limit. This amendment is prompted by a revised life analysis conducted by the manufacturer after the failure of a similarly designed HPT disk. The actions specified by this AD are intended to prevent HPT disk rim failure, which could result in an uncontained engine failure and damage to the aircraft.
91-24-07: 91-24-07 AIR CRUISERS CO.: Amendment 39-8093. Docket No. 90-ANE-36. Applicability: Air Cruisers Co., TSO-C69 Emergency Evacuation Slide Systems P/N D31005-( ), Serial Numbers 0001 through 0870, and P/N D30543-( ), Serial Numbers 0001 through 0067, installed on, but not limited to British Aerospace Model BAe-146 series airplanes. Compliance: Required within the next 3 months after the effective date of this AD, unless already accomplished. To prevent the possibility of the emergency evacuation slide from inflating improperly which could result in hindrance of the emergency evacuation of the airplane, accomplish the following. (a) Replace the inflation cable, and reidentify the emergency evacuation slide in accordance with paragraph 2, of the Accomplishment Instructions of Air Cruisers Co., Service Bulletin (SB) 201-25-13, dated September 17, 1990. (b) Upon submission of substantiating data by an owner or operator through an FAA Inspector (maintenance, operations or avionics, as appropriate), an alternate method of compliance with the requirements of this AD or adjustments to the compliance time specified in this AD may be approved by the Manager, New York Aircraft Certification Office, ANE-170, Engine & Propeller Directorate, Aircraft Certification Service, FAA, 181 South Franklin Avenue, Valley Stream, New York. (c) 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. (d) The modification procedure shall be done in accordance with the following Air Cruisers Co. Service Bulletin: DOCUMENT NO. PAGE NO. ISSUE/REVISION DATE 201-25-13 1-6 Issue 9/17/90 Total Pages: 6 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 Air Cruisers Co., P.O. Box 180, Belmar, New Jersey 07719-0810. A copy may be inspected at the FAA, New England Region, Office of the Assistant Chief Counsel, 12 New England Executive Park, Room 311, Burlington, Massachusetts, or at the Office of the Federal Register, 1100 L Street, NW, Room 8401, Washington, DC. This amendment (39-8093, AD 91-24-07) becomes effective on February 10, 1992.
71-07-02: 71-07-02 LOCKHEED AIRCRAFT CORPORATION: Amdt. 39-1181. Applies to Lockheed Models 49, 149, 649, 749, 1049, and 1649 series airplanes certificated in all categories. Compliance required prior to the first flight after May 3, 1971 unless already accomplished. To provide for an acceptable obstacle clearance profile when computing the takeoff flight path, accomplish the following: (a) Revise the airplane flight manuals by adding to the airplane flight manuals listed in this subparagraph the following note to the lower right hand portion of the specified page and adjacent to that portion showing the ground time. "NOTE: To obtain correct ground time, multiply ground time by 1.42." Lockheed Model Lockheed Report No. Page Identification 49-46 5817 Section II, Page 17, Figure 14 Appendix I, Part 2, Page 78, Figure 11 149-46 5817 Appendix V, Page 21, Figure 13 49-46 Appendix VI, Page 6, Figure 6 Appendix VI, Page 14, Figure 14 649-79 6028 Section II, Page 2-21, Figure 20 649A-79 Appendix 1, Part 1, Page I-24, Figure 17 749-79 Appendix 1, Part 2, Page I-50, Figure 45 749A-79 Appendix III, Page III-12, Figure 11 Appendix V, Page V-12, Figure 11 749-79 6028 Appendix III, Supplement A, Page IIIA-12, Figure 11 749A-79 1049-54 7787 Appendix II, Page II-17, Figure II-14 1049C-55 9154 Supplement A, Section III, Part 2, Page A-32.1, Figure A-25 1049E-55 Supplement A, Section III, Part 3, Page A-54.1, Figure A-47 Supplement A, Section III, Part 4, Page A-77, Figure A- 70 1049C 9153 Supplement A, Section III, Part 2, Page A-35, Figure A- 29, Sheet 2 1049E Supplement A, Section III, Part 3, Page A-57, Figure A- 51, Sheet 2 Supplement B, Section III, Part 2, Page B-37, Figure B- 29, Sheet 2 Supplement B, Section III, Part 3, Page B-59, Figure B- 51, Sheet 2 1049C 9153 Supplement B, Section III, Part 4, Page B-83, Figure B- 74, Sheet 2 1049E Supplement C, Section III, Part 3, Page C-35, Figure C- 29, Sheet 2 Supplement C, Section III, Part 4, Page C-56A, Figure C-52, Sheet 2 Supplement E, Section III, Part 2, Page E-31, Figure E- 24, Sheet 2 Supplement E, Section III, Part 3, Page E-57, Figure E- 48, Sheet 2 1049G-82 10051 Section IV, Part II, Page 4-38, Figure 4-34 Section IV, Part II, Page A4-38, Figure 4-34 Section IV, Part III, Page 4-59, Figure 4-54 Section IV, Part III, Page A4-59, Figure 4-54 DA-1 Supplement, Part 2, Page 33, Figure 29 DA-1 Supplement, Part 3, Page 54, Figure 50 1049G-82 10052 Section IV, Part II, Page 4-39, Figure 4-34 Section IV, Part II, Page A4-39, Figure 4-34 Section IV, Part II, Page B4-39, Figure 4-34 Section IV, Part II, Page C4-39, Figure 4-34 Section IV, Part III, Page 4-61, Figure 4-55 Section IV, Part III, Page A4-61, Figure 4-55 DA-1 Supplement, Section III, Part 2, Page 33, Figure 29 DA-1 Supplement, Section III, Part 3, Page 54, Figure 50 DA-3 Supplement, Section III, Part 2, Page 31, Figure 27 DA-3 Supplement, Section III, Part 3, Page 52, Figure 48 1049D 11020 Section IV, Part 2, Page A4-39, Figure 4-35 1049H Section IV, Part 2, Page B4-39, Figure 4-35 Section IV, Part 2, Page C4-39, Figure 4-35 Section IV, Part 2, Page D4-39, Figure 4-35 Section IV, Part 2, Page E4-39, Figure 4-35 Section IV, Part 2, Page F4-39, Figure 4-35 Section IV, Part 3, Page A4-61, Figure 4-56 Section IV, Part 3, Page B4-61, Figure 4-56 Section IV, Part 3, Page C4-61, Figure 4-56 DA-1 Supplement, Section III, Part 2, Page A33, Figure 29 DA-1 Supplement, Section III, Part 3, Page A54, Figure 50 DA-1 Supplement, Section III, Part 2, Page 33, Figure 29 1049D 11020 DA-1 Supplement, Section III, Part 3, Page 54, Figure 50 1049H DA-3 Supplement, Section III, Part 2, Page 31, Figure 27 DA-3 Supplement, Section III, Part 2, Page A31, Figure 27 DA-3 Supplement,Section III, Part 2, Page B31, Figure 27 DA-3 Supplement, Section III, Part 3, Page 52, Figure 48 DA-3 Supplement, Section III, Part 3, Page A52, Figure 48 DA-3 Supplement, Section III, Part 3, Page B52, Figure 48 1649A-98 11560 Section IV, Part 2, Page 4-31, Figure 4-23, Sheet 1 Section IV, Part 2, Page B4-31, Figure 4-23, Sheet 1 Section IV, Part 3, Page 4-52, Figure 4-43 Appendix II, Page II-29, Figure II-26 (b) For the airplane flight manuals listed in this subparagraph there is a note in the top central portion of the page stating: "These lines and this grid are used only in the determination of airplane height and distance at end of 2 minute period." Add to this note the following: CORRECTION: At the end of 2 minute period, correct the airplane height by subtracting 100 feet and the airplane distance by subtracting 3000 feet. Lockheed Model Lockheed Report No. Page Identification 1049C 9153 Section III, Supplement D,Part 2, Page D-39, Figure D-34, Sheet 2 1049E Section III, Supplement D, Part 3, Page D-61, Figure D-55, Sheet 2 (c) Reference this Airworthiness Directive in the airplane flight manual at the time of accomplishment. This amendment becomes effective April 3, 1971.
98-13-35 R1: This amendment corrects information in an existing airworthiness directive (AD), applicable to certain McDonnell Douglas Model DC-9 and DC-9-80 series airplanes, Model MD-88 airplanes, and C-9 (military) series airplanes, that currently requires repetitive high frequency eddy current inspections of certain areas of the fuselage to detect cracks of the skin and/or longeron, and various follow-on actions. That AD also requires installation of a preventative modification, which terminates the repetitive inspections. The actions specified in that AD are intended to prevent fatigue cracks, which could result in loss of the structural integrity of the fuselage and, consequently, lead to rapid depressurization of the airplane. This amendment corrects the requirements of the current AD by indicating the specific area in which the subject inspection must be conducted. This amendment is prompted by communication received from the manufacturer that the current requirements of the ADare different than the service information referenced as the appropriate service information in the current AD.
88-14-03: 88-14-03 BOEING HELICOPTER COMPANY (BOEING VERTOL; VERTOL) AND KAWASAKI HEAVY INDUSTRIES, LTD: Amendment 39-5962. Applies to Boeing Helicopter Model 107-II and Kawasaki Model KV107-II and KV107-IIA helicopters certificated in any category. (Docket No. 88-ASW-28) Compliance is required as indicated, unless already accomplished. To prevent failure of a main rotor hub, P/N 107R2550, which could result in loss of control of the helicopter accomplish the following: (a) Within the next 10 hours' time in service (TIS) after the effective date of this AD, unless accomplished within the last 40 hours TIS, or before the accumulation of 1,200 hours TIS, whichever comes later, gain access to the forward and aft main rotor hubs, remove paint from the lower surface on both forward and aft center hubs, and conduct an inspection of the lower plate area of the forward and aft main rotor hubs for cracks as follows: (1) Conduct an eddy current inspection of the lower plate surface. (i) Direct particular attention to the transition radius between the lag lug and lower plate, (ii) Replace cracked hubs with serviceable parts. (2) If eddy current facilities are not available, conduct a dye penetrant inspection of the lower plate surface. (i) Apply dye penetrant to the lower plate surface. (ii) Allow 5 to 15 minutes of dwell time for dye penetration before removal. (iii) Remove excess penetrant. (iv) Apply the developer to the lower plate surface. (v) Allow 5 to 15 minutes of drying time for the developer. (vi) Visually inspect the developed areas for cracks (dye bleed through). (vii) Direct particular attention to the transition radius between the lag lug and lower plate. (viii) Clean surface to remove penetrant and developer from hubs. (ix) After cleaning, reinspect the transition radius using a 7X power (or greater) magnifying glass. (x) Replace cracked hubs with serviceable parts. Note: Do not paint the lower surface of the forward and aft center hubs after the inspections. Also, Boeing Helicopter Company Service Bulletin No. 107-372 pertains to this inspection. (b) Inspect, in accordance with paragraph (a), both the upper and lower plate areas of hubs which have been inverted and moved to the other head. (c) After the initial inspections of paragraphs (a) and (b), repeat the inspections at intervals not to exceed 50 hours TIS from the last inspection. (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 with this AD 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. This amendment, 39-5962, becomes effective July 5, 1988.
2013-16-23: We are adopting a new airworthiness directive (AD) for certain Rolls-Royce plc (RR) RB211-524B-02; -524B2-19; -524B3-02; -524B4-02; - 524C2-19; -524D4-19; -524D4-B-19; -524D4-39; -535C-37; -535E4-37; - 535E4-B-37, and -535E4-B-75 turbofan engines, and all RB211-524G2-19; - 524G3-19; -524H2-19; and -524H-36 turbofan engines. This AD requires a one-time inspection of the front combustion liner (FCL) metering panel to determine if it is made from N75 material and, if so, replacing it with an FCL made from C263 material. This AD was prompted by the discovery of a cracked and distorted FCL metering panel, which was made from N75 material. We are issuing this AD to prevent hot gases from burning through the engine casing, which could result in an under-cowl fire and damage to the airplane.
2010-14-10: The FAA is superseding an existing airworthiness directive (AD), which applies to certain Model 747-100, 747-200B, and -200F series airplanes. That AD currently requires inspections to detect cracking in the upper row of fasteners holes of the skin lap joints in the fuselage lower lobe, and repair if necessary. This new AD reduces the maximum interval of the post-modification inspections. This AD results from reports of fatigue cracking on modified airplanes. We are issuing this AD to detect and correct fatigue cracking in the longitudinal lap joints of the fuselage lower lobe, which could lead to the rapid decompression of the airplane and the inability of the structure to carry fail-safe loads.
99-07-02: This amendment adopts a new airworthiness directive (AD) that is applicable to Eurocopter France Model AS 332C, L, L1, and L2 helicopters and Model SA 330F, G, and J helicopters. This action requires inspecting the position and bonding of the main rotor blade (blade) leading edge stainless steel protective strips (strips) that were replaced by C.T.I. Dallas. This amendment is prompted by the discovery of a strip that was both mislocated and improperly bonded. The strip had been replaced by C.T.I. Dallas. This condition, if not corrected, could result in failure of the blade and subsequent loss of control of the helicopter.
2022-13-01: The FAA is adopting a new airworthiness directive (AD) for certain Leonardo S.p.a. Model AW169 helicopters. This AD was prompted by a report of a blockage in a fuel tank vent line. This AD requires inspecting the fuel tank vent lines, 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.
2006-13-18: The FAA is adopting a new airworthiness directive (AD) for certain transport category airplanes, identified above. This AD requires installing a bonding jumper from the boost pump volute to the fuel tank structure, and related investigative/corrective actions. This AD results from fuel system reviews conducted by the manufacturer. We are issuing this AD to prevent point-contact arcing or filament heating in the fuel tank, which, in the event of a short or ground fault inside the fuel tank, could result in a fuel tank explosion and consequent loss of the airplane.