Results
99-07-10: This amendment adopts a new airworthiness directive (AD) that applies to all Industrie Aeronautiche e Meccaniche (I.A.M.) Model Piaggio P-180 airplanes. This AD requires inspecting the upper and lower engine nacelle inner panels for any loose or partially detached inner film, and removing any loose or partially detached inner film. This AD is the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for Italy. The actions specified by this AD are intended to prevent the accumulation of loose particles on the engine inlet screen caused by film delamination, which could result in reduced engine power and possible loss of airplane control.
60-18-02: 60-18-02 VICKERS: Amdt. 197 Part 507 Federal Register August 24, 1960. Applies To All 745D and 810 Series Aircraft. Compliance required as indicated. Conduct inspections of the brake accumulator systems as specified in Vickers Preliminary Technical Leaflet (PTL) 222 (700 Series) and PTL 87 (800/810 Series) within the next 300 hours' time in service and at subsequent periodic intervals of 800 hours' time in service. These inspections are not mandatory when filters, Dunlop ACM 18308 or equivalent, are installed in accordance with Vickers Modification Bulletins D.2994 (700 Series) and FG.1796 (800/810 Series). This amendment shall become effective 30 days after date of its publication in the Federal Register.
99-07-05: This amendment adopts a new airworthiness directive (AD), applicable to all Lockheed Model L-1011-385 series airplanes, that requires repetitive external visual inspections and internal borescope inspections to detect discrepancies of the elevator assembly; and either repair or repair/modification of certain identified discrepancies. This amendment is prompted by a report of fretting at the diagonal truss to web joint of the elevator and cracking in the cap fillet radius adjacent to the joint, apparently due to loose fasteners as a result of local vibration. The actions specified by this AD are intended to detect and correct such fretting and cracking, which could result in reduced structural integrity of the elevator and consequent flutter instability if coupled with other structural failures.
71-08-03: 71-08-03 BELL: Amdt. 39-1190 as amended by Amendment 39-1330. Applies to Model 206A-1 helicopters, serial numbers 39998 through 40994 and to all Model 206A helicopters equipped with Particle Separator Kit, Self Purging, P/N 206-706-201-1, or P/N 206-706-200-1, certificated in all categories. Compliance required before further flight in snow, but no later than 25 hours time in service after the effective date of this airworthiness directive, unless already accomplished. 1. To prevent power interruption caused by ingestion into the engine of snow or ice which may have accumulated in the engine inlet during flight, crew notification of a limitation against flight into snow must be accomplished as follows: a. Install a permanent type placard in full view of the pilot as near as possible to the basic limitations placard, worded as follows: "FLIGHT INTO FALLING OR BLOWING SNOW IS NOT PERMITTED" b. If approved placards are unavailable, the owner or operator maymake and use a placard containing the above words. Letters must be at least 1/8 inch in height. 2. Alternatively, upon accomplishment of modifications listed below, the placard required by paragraph 1. may be removed and flight operations may be conducted in falling or blowing snow for periods not in excess of ninety minutes, provided flight visibility due to snow is not less than one-half mile. a. For the Model 206A-1, S/N 39998 through 40994, install Particle Separator Assembly, P/N 206-062-819-5 in accordance with Bell Helicopter Company Drawing 206-062-800-5. Incorporate revised pages A, 7, 13, 15 and 20, approved and dated October 26, 1971, into the Model 206A-1 Flight Manual, approved and dated May 5, 1969. b. For Model 206A helicopters equipped with Particle Separator Kit, Self Purging, P/N 206-706-201-1 or P/N 206-706-200-1, modify and/or replace particle separator system components as indicated in applicable sections of Bell Service Instruction No. 206-89, revised October 25, 1971, or later FAA approved revision. Incorporate revised pages A, B, and D, approved and dated October 18, 1971, into the Model 206A Flight Manual, approved and dated October 20, 1966, or later FAA approved reissues. Incorporate revised pages 1, 2, and 5, approved and dated October 18, 1971, into the Model 206A Flight Manual Supplement titled "Snow Particle Separator - Engine Air Induction System," approved and dated July 23, 1970. Alternate means of compliance or equivalent replacement parts may be acceptable if approved by the Chief, Engineering and Manufacturing Branch, Flight Standards Division, Southwest Region, Federal Aviation Administration, Fort Worth, Texas. Amendment 39-1190 became effective April 12, 1971. This amendment 39-1330 becomes effective November 18, 1971.
2013-15-10: We are superseding airworthiness directive (AD) 2012-10-12 for all RR RB211-Trent 553-61, 553A2-61, 556-61, 556A2-61, 556B-61, 556B2- 61, 560-61, 560A2-61, 768-60, 772-60, 772B-60, 875-17, 877-17, 884-17, 884B-17, 892-17, 892B-17, and 895-17 turbofan engines. AD 2012-10-12 required inspecting the intermediate-pressure (IP) compressor rotor shaft rear balance land for cracks. We are issuing this AD to require inspections of the IP compressor rotor shaft, as required by AD 2012- 10-12, to add on-wing [[Page 54150]] inspections for the Trent 500 engines, and to add on-wing and in-shop inspections for the Trent 900 engines. This AD was prompted by detection of a crack in a Trent 500 IP compressor rotor shaft rear balance land during a shop visit. Further engineering evaluation, done by RR, concluded that the cracking may also exist in Trent 900 engines. We are issuing this AD to detect cracking on the IP compressor rotor shaft rear balance land, which could lead to uncontained engine failure and damage to the airplane.
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.