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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.
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.
47-32-17: 47-32-17 BELLANCA: (Was Mandatory Note 7 of AD-773-5.) Applies to Models 14- 13, 14-13-2 Serial Numbers 1060, and Up. Compliance required prior to October 15, 1947. Improper positioning of the inspection covers on the top surface of each wing at the landing gear retracting sprocket can cause malfunctioning of the gear retracting mechanism. This cover is held in place by two spring clips, and if the cover is installed with the clips running in a chordwise direction, it is possible that the ends of the clips will bear against the chain and force it off the sprocket, jamming the system. Inspect the covers on your airplane for proper installation, and paint arrows on the cover and wing surface so that the arrows point toward each other when the spring clips run spanwise. (Bellanca Service Bulletin No. 10 covers this same subject.)
91-12-07: 91-12-07 WYTWORNIA SPRZETU KOMUNEKACYJNEGO PZL-MIELEC: Amendment No. 39-7018. Docket No. 91-CE-07-AD. Applicability: Model M18 airplanes (serial numbers (S/N) 1Z013-21 through 1Z023-30), equipped with an agriculture equipment electro-hydraulic control system (Modification D73.701.00.1), certificated in any category. Compliance: Required as indicated, unless already accomplished. To prevent failure of the electro-hydraulic control system that results in loss of flap and brake control, accomplish the following: (a) For S/N 1Z013-21 through 1Z023-30 airplanes, upon the accumulation of 200 hours time-in- service (TIS) or within the next 25 hours TIS after the effective date of this AD, whichever occurs later, replace each flexible hose having part number (P/N) D73.7/21.00.0 or D73.7/24.00.0. with a new hose in accordance with the instructions in PZL-Mielec Mandatory Engineering Bulletin (MEB) No. K/02.141/90, dated April 1990. (1) If hoses are replaced with either P/N D73.7/21.00.0 or D73.7/24.00.0, replace these hoses at intervals not to exceed 200 hours TIS. (2) If hoses are replaced with P/N D73.7/26.00.0 or D73.7.25.00.0 hose, no further action is required. (b) For S/N 1Z013-21 through 1Z022-05 airplanes, upon the accumulation of 500 hours TIS or within the next 100 hours TIS after the effective date of this AD, whichever occurs later, modify the electro- hydraulic control system in accordance with the instructions in Paragraph III, 2. of PZL-Mielec MEB No. K/02.141/90, dated April 1990. (c) Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes to a location where the requirements of this AD can be accomplished. (d) An alternative method of compliance or adjustment of the initial or repetitive compliance times that provides an equivalent level of safety may be approved by the Manager, Brussels Aircraft Certification Staff, FAA, Europe, Africa, and Middle East Office, c/oAmerican Embassy, B-1000, Brussels, Belgium. The request should be forwarded through an appropriate FAA Maintenance Inspector, who may add comments and then send it to the Manager, Brussels Aircraft Certification Staff. (e) The modifications and replacements required by this AD shall be done in accordance with PZL-Mielec Mandatory Engineering Bulletin No. K/02.141/90, dated April 1990. 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 PZL-Mielec, Ludowego Wojska Polkiego 3, 39-300 Mielec, Poland. Copies may be inspected at the FAA, Central Region, Office of the Assistant Chief Counsel, Room 1558, 601 E. 12th Street, Kansas City, Missouri, or at the Office of the Federal Register, 1100 L Street, NW; Room 8401, Washington, DC. This amendment (39-7018, AD 91-12-07) becomes effective on July 5, 1991.
2022-11-05: The FAA is adopting a new airworthiness directive (AD) for certain The Boeing Company Model 777 airplanes. This AD was prompted by a report of the loss of the nuts at all four fastener locations common to the outboard flap inboard support rear spar attachment fittings, which affects the retention feature of the fasteners and leaves the fasteners susceptible to migrating out of the joint. This AD requires repetitive detailed inspections for discrepancies of the fasteners and shim of the wing rear spar at certain outboard flap supports; a detailed inspection for damage of the shim, flap support mechanism, and wing lower skin; installation of new fasteners and shims; and repair or replacement of damaged parts. The FAA is issuing this AD to address the unsafe condition on these products.
92-27-21: 92-27-21 BELL HELICOPTER TEXTRON, INC. (BHTI): Amendment 39-8575. Docket Number 92-ASW-45. Applicability: Model 205A-1 and 205B series helicopters, with increased diameter tail rotor drive shaft (drive shaft), P/N 204-040-620-011, installed, certificated in any category. Compliance: Required as indicated, unless accomplished previously. To prevent failure of the drive shaft, loss of tail rotor control, and subsequent loss of control of the helicopter, accomplish the following: (a) Within 25 hours' time-in-service after the effective date of this AD: (1) Conduct a one-time inspection of the helicopter and the drive shaft in accordance with paragraphs 1 through 4 of the Accomplishment Instructions of BHTI Alert Service Bulletin (ASB) 205-92-49, dated October 5, 1992, for BHTI Model 205A-1 helicopters, and ASB 205B-92-13, dated October 5, 1992, for BHTI Model 205B helicopters. (2) Reassemble the tail rotor drive shaft assembly in accordance with paragraph 5 of the pertinent ASB to ensure a minimum of 0.50 inch clearance is obtained between the tail rotor drive shaft tunnel (drive shaft tunnel) and the drive shaft. (b) Each time the starter generator is installed after maintenance, ensure a minimum of 0.50 inch clearance is maintained between the drive shaft tunnel and the drive shaft. Adjust the position of the drive shaft tunnel in accordance with paragraph 5 of the pertinent ASB to obtain proper clearance. (c) Remove unairworthy parts found during the inspection required in paragraph (a) and replace with airworthy parts before further flight. (d) An alternative method of compliance or adjustment of the compliance time, which provides an acceptable level of safety, may be used when approved by the Manager, Rotorcraft Certification Office, FAA, Rotorcraft Directorate, Fort Worth, Texas 76193-0170. Operators shall submit their requests through an FAA Principal Maintenance Inspector, who may concur or comment and then send it to the Manager, Rotorcraft Certification Office. NOTE: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Rotorcraft Certification Office. (e) Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate the helicopter to a location where the requirements of this AD can be accomplished. (f) The inspection, removal, and replacement, if necessary, and reassembly shall be done in accordance with the applicable BHTI ASB 205-92-49 or 205B-92-13, both dated October 5, 1992. 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 Bell Helicopter Textron, Inc., P.O. Box 482, Fort Worth, Texas 76101. Copies may be inspected at the FAA, Office of the Assistant Chief Counsel, 4400 Blue Mound Road, bldg. 3B, room 158, Fort Worth, Texas; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC. (g) This amendment becomes effective on July 7, 1993, to all persons except those persons to whom it was made immediately effective by Priority Letter AD 92-27-21, issued January 7, 1993, which contained the requirements of this amendment.
2022-12-01: The FAA is adopting a new airworthiness directive (AD) for certain Bombardier, Inc., Model BD-700-1A10 and BD-700-1A11 airplanes. This AD was prompted by reports of oxygen leaks caused by cracked, brittle, or broken oxygen hoses that were found during scheduled maintenance tests of the airplane oxygen system. This AD requires an inspection of the oxygen hose assembly to determine if an affected part number is installed, and replacement of affected oxygen hoses. For certain airplanes, this AD allows repetitive testing of the oxygen system until affected hoses are replaced. This AD also prohibits installation of an affected oxygen hose. The FAA is issuing this AD to address the unsafe condition on these products.
99-06-16: This amendment adopts a new airworthiness directive (AD), applicable to CFM International CFM56-5 series turbofan engines, that reduces the low cycle fatigue (LCF) retirement lives for certain high pressure turbine rotor (HPTR) front air seals, and provides a drawdown schedule for those affected parts with reduced LCF retirement lives. This amendment is prompted by results of a refined life analysis performed by the manufacturer that revealed minimum calculated LCF lives significantly lower than the published LCF retirement lives. The actions specified by this AD are intended to prevent a LCF failure of the HPTR front air seal, which could result in an uncontained engine failure and damage to the aircraft.
99-06-07: This amendment adopts a new airworthiness directive (AD), applicable to all Short Brothers Model SD3-60 and SD3-60 SHERPA series airplanes, that requires repetitive inspections to detect corrosion and/or wear of the top and bottom shear decks of the left and right stub wings in the area of the forward pintle pin of the main landing gear (MLG), and repair, if necessary. 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 detect and correct corrosion and/or wear of the top and bottom shear decks of the left and right stub wings in the area of the forward pintle pin of the MLG, which could result in failure of the MLG to extend or retract.
2013-17-05: We are adopting a new airworthiness directive (AD) for certain Bombardier, Inc. Model CL-600-2C10 (Regional Jet Series 700, 701, & 702) airplanes, Model CL-600-2D15 (Regional Jet Series 705) airplanes, Model CL-600-2D24 (Regional Jet Series 900) airplanes, and Model CL- 600-2E25 (Regional Jet Series 1000) airplanes. This AD was prompted by reports of erratic pitch movement and oscillatory behaviors of the elevator control system. This AD requires repetitive replacement of the bellcrank supports on the inner rear spar of the horizontal stabilizer with new, improved bellcrank supports. We are issuing this AD to prevent erratic pitch movement and transient accelerations, which could result in a significant pitch upset, and injuries to passengers and flightcrew.
99-06-05: This amendment adopts a new airworthiness directive (AD) that applies to certain Pilatus Aircraft Ltd. (Pilatus) Models PC-12 and PC-12/45 airplanes. This AD requires removing the "Alternate Flap System" from the airplane flight controls and inserting a temporary revision that specifies this change in SECTION 2 - LIMITATIONS of the PC-12 Pilot's Operating Handbook. This AD is the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for Switzerland. The actions specified by this AD are intended to preclude improper use of the "Alternate Flap System", which could result in flap asymmetry with consequent reduced or loss of control of the airplane.
83-02-51: 83-02-51 BELL HELICOPTER TEXTRON, INC: Amendment 39-4842. Applies to Bell Helicopter Textron Models 222 and 222B helicopters certified in all categories equipped with main rotor controls walking beam assembly Part Numbers 222-010-415-5 and -9. Note that the -5 assembly contains a -7 detail beam and the -9 assembly contains a -11 detail beam. Beam assemblies may be identified in the area of their serial numbers by their detail numbers instead of their assembly numbers. The -7 and -11 details are included in this AD. (Airworthiness Docket No. 83-ASW-6.) Compliance is required as indicated (unless already accomplished). To prevent failure of the walking beam, accomplish the following: (a) Before further flight, remove and inspect walking beam assemblies Serial Numbers VN07-1O7 through VN07-140, VN06-057, VN06-060, VN06-061, VNO6-065, VN06- 069, VN06-089 through VN06-092, VN06-095, VN06-096, VNO6-100, EA-004, and EA-008 as follows: (1) Remove all grease fittings from the walking beam. (2) Using a magnifying glass of at least 10-power magnification and a bright light, inspect each one of the threaded holes from which the grease fittings were removed for evidence of corrosion, trapped foreign material, or thread indentations caused by foreign material having been trapped between the grease fittings and the threads. Of special interest is the presence of shot-peening residue. This residue will have the appearance of small round balls similar to shotgun pellets. These balls may be as small as 0.012 inch in diameter and are difficult to see unless a magnifying glass and bright light are used. (3) If any of the above defects are present, remove the part from service and replace it with a serviceable part. (4) If no defects are found, reinstall the grease fittings with wet zinc chromate primer on the threads. (b) Before further flight and prior to the first flight of each day, conduct the following inspections of all walking beam assembly Part Numbers 222-010-415-5 and -9, regardless of serial number, with emphasis on the area around the grease fittings in the portion of the beams through which the drive links are attached by bolts part number 20-057-9-95D. Remove cracked parts from service before further flight and replace with serviceable parts. (c) Within 10 hours time in service following the effective date of this AD, and each 25 hours thereafter, conduct a dye penetrant inspection of a 2-inch diameter area around the grease fittings described in paragraph (b) above. The area shall be prepared for penetrant inspection by thorough cleaning using Stoddard solvent or equivalent. Do not use methyl-ethyl- ketone (MEK) or paint stripper. Remove cracked parts from service before further flight and replace with serviceable parts. NOTE: Bell Alert Service Bulletin (ASB) 222-83-18 is an equivalent means of compliance with paragraph (b) of this AD. The inspections required in paragraph (b) maybe performed with the parts installed on the helicopter. Any other equivalent means of compliance with this AD must be approved by the Manager, Helicopter Certification Branch, Federal Aviation Administration, Southwest Region. (d) The helicopter may be flown to a repair base for the above inspections under the provisions of FAR 21.197. This amendment becomes effective May 15, 1984, as to all persons except those to whom it was made immediately effective by telegraphic AD T83-O2-51 issued January 21, 1983, which contained this amendment.
73-23-06: 73-23-06 BEECH: Amdt. 39-1745. Applies to all Models A23-19, 19A, M19A and B19 (S/Ns MB-1 thru MB-557); and all Models 23, B23, and C23 (S/Ns M-1 thru M-554, M-1095 thru M-1415, M-1419, M-1423, M-1439 and M-1447) airplanes, having the vernier-type throttle control. Compliance: Required as indicated, unless already accomplished. To prevent throttle control actuating cable failure and loss of proper adjustment of the throttle control system, within 100 hours' time in service after the effective date of this AD, accomplish the following: A) Inspect the throttle control cable in accordance with the following procedures: 1. Remove the engine cowling, disconnect the throttle control cable from the carburetor throttle arm, and remove the carburetor from the engine. 2. Move the throttle control through its full travel several times and check by feel for binding or roughness. 3. Lock the cockpit throttle control in the full forward position and apply approximately 50 lbs. pressure at the throttle cable rod end in a direction to force the control cable back into the housing. While this pressure is applied, mark the throttle control cable at the end of the housing. 4. Apply a pulling force of approximately 50 lbs. to the cable rod end and while this force is applied place another mark on the throttle control cable at the end of the housing. 5. If the throttle lock gives under either loading condition specified in Paragraphs A(3) and A(4) or if binding or roughness is evident during operation of the throttle control or if the distance between the marks made on the control cable in accordance with Paragraphs A(3) and A(4) is .25 inch or more, prior to further flight, replace the throttle control assembly with an airworthy assembly. B) Replace the carburetor throttle shaft and stop arm assembly and throttle lever with either Marvel Schebler P/Ns 13-1521 and 12-B57 respectively and Marvel Schebler P/N 81- 311 nut if a MarvelSchebler Model MA-3-SPA carburetor is installed on the engine or Marvel Schebler P/Ns 13-1526 and 12-B56 respectively and Marvel Schebler P/N 81-311 nut if a Marvel Schebler Model HA-6 carburetor is installed on the engine. NOTE: The Marvel Schebler carburetor modifications should be accomplished in accordance with instructions contained in the current Marvel Schebler Overhaul Manual. C) Reinstall the carburetor and rig the throttle control cable to the throttle arm leaving a 1/16 inch cushion in the full throttle position as shown in Section 3 of Beechcraft Models 19, 23, and 24 Series Shop Manual, tighten Marvel Schebler P/N 81-311 nut to 25/60 in. lbs. torque and safety with a cotter pin. D) Any equivalent methods of compliance with this AD must be approved by the Chief, Engineering and Manufacturing Branch, FAA, Central Region. Beechcraft Service Instructions No. 0589-159 or later FAA-approved revisions covers this subject. This amendment becomes effectiveNovember 19, 1973.