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91-18-17: 91-18-17 BOEING: Amendment 39-8020. Docket No. 90-NM-264-AD. \n\n\tApplicability: Model 757 series airplanes, as listed in Boeing Service Bulletin 757-52- 0052, Revision 1, dated June 20, 1991, certificated in any category. \n\n\tCompliance: Required within the next 90 days after the effective date of this AD, unless previously accomplished. \n\n\tTo prevent the hazard of an unexpectedly powered door opening and escape slide deployment when ground personnel open from the outside an armed passenger door with a broken disarm cable, accomplish the following: \n\n\tA.\tFor passenger doors 1, left and right, and 2, left and right: Measure the clearance between the lower end of the disarm cable and the pin in the disarm lever, in accordance with Boeing Service Bulletin 757-52-0052, Revision 1, dated June 20, 1991. \n\n\t\t1.\tIf the clearance between the end of the cable and the pin is less than 0.010 inch, prior to further flight, inspect the cable for damage or breakage. \n\n\t\t\ta.\tIf the cable is damaged or broken, prior to further flight, replace the cable in accordance with the service bulletin. \n\n\t\t\tb.\tIf the cable is not damaged or broken, grind the cable end and/or swaged ball and reinstall the cable into the door in accordance with the service bulletin. \n\n\t\t2.\tIf the clearance is 0.010 inch or more, no modification or replacement is required. \n\n\t\t3.\tFunctionally test the door in accordance with the service bulletin. \n\n\tB.\tFor passenger doors 4, left and right: Disconnect the disarm cable from the disarm lever on the door handle box, and inspect the cable for damage or breakage in accordance with the service bulletin.\n\n\t\t1.\tPrior to further flight, replace any damaged or broken cable in accordance with the service bulletin. \n\n\t\t2.\tFor any cable that is not damaged or broken, grind the cable end and/or swaged ball and reinstall the cable into the door, in accordance with the service bulletin. \n\n\t\t3.\tFunctionally test the door in accordance with the service bulletin. \n\n\tC.\tFor airplanes on which the requirements of paragraph A. or B. of this AD were accomplished prior to the effective date of this AD in accordance with Boeing Service Bulletin 757-52-0052, dated August 30, 1990, no further action is necessary. \n\n\tD.\tAn 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, Seattle Aircraft Certification Office (ACO), FAA, Transport Airplane Directorate. \n\n\tNOTE: The request should be forwarded through an FAA Principal Maintenance Inspector, who may concur or comment and then send it to the Manager, Seattle ACO. \n\n\tE.\tSpecial flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes to a base in order to comply with the requirements of this AD. \n\n\tAll persons affected by this directive who have not already received the appropriate service documents from the manufacturer may obtain copies upon request to Boeing Commercial Airplane Group, P.O. Box 3707, Seattle, Washington 98124. These documents may be examined at the FAA, Northwest Mountain Region, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, Washington. \n\n\tThis amendment (39-8020, AD 91-18-17) becomes effective on September 30, 1991.
2016-10-03: We are adopting a new airworthiness directive (AD) for Viking Air Limited Model DHC-3 airplanes that are modified with the Baron Short Take Off and Landing (STOL) kit (Supplemental Type Certificate SA94-114 or SA 00287NY). This AD results from mandatory continuing airworthiness information (MCAI) issued by the aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as a center of gravity that is too far aft contributing to a stall during takeoff and loss of control during other phases of flight. We are issuing this AD to require actions to address the unsafe condition on these products.
65-21-04: 65-21-04 HARTZELL: Amdt. 39-132 Part 39 Federal Register September 4, 1965, as amended by Amendment 39-1342. Applies to Models HC-12X20-7 and -8 Propellers Installed on but not limited to Navion, Navion A, Beech 35, Bellanca, Stinson L-5, and Stinson 108 Airplanes. Compliance required as indicated. To prevent further failures of the A-38 propeller bearing, accomplish the following (a) Unless already accomplished, within the next 100 hours' time in service after the effective date of this AD: (1) Inspect and replace as necessary each A-38 bearing in accordance with Hartzell Service Bulletin No. 82, dated April 27, 1962, revised June 2, 1965, or later FAA- approved revision. (2) Replace each A-38 bearing having a riveted cage with an A-38 bearing having a crimped cage or with an A-83B bearing having a bakelite cage in accordance with Hartzell Service Bulletin No. 82, dated April 27, 1962, revision June 2, 1965, or later FAA- approved revision. (3)Identify propellers modified in accordance with this paragraph by painting a 3/4-inch diameter white spot on the front face of the propeller piston. (b) Bearing lubrication and maintenance: (1) Grease the A-38 propeller control bearing within the next 100 hours in service after the effective date of this AD, and thereafter not to exceed 100 hours in service from the last greasing. (2) Propellers which are installed on aircraft which have not been flown for a calendar period of two months or more, but less than six months, grease the A-38 control bearing prior to further flight. (3) Propellers which are installed on aircraft which have not been flown for a calendar period of six months or more, must be removed prior to further flight. Inspect the A- 38 control bearing for rust, replace as necessary and grease in accordance with Hartzell Bulletin No. 82 Addendum No. 1 dated 27 May 1971, No. 82 revised 2 June 1965 or equivalent inspection approved by the Chief,Engineering and Manufacturing Branch, Eastern Region. Also, inspect B-119 rubber diaphragm for cracking and replace if necessary in accordance with Service Letter 48 dated 20 April 1967, or equivalent inspection approved by the Chief, Engineering and Manufacturing Branch, Eastern Region. (Hartzell Bulletins No. 82 revised 2 June 1965, No. 82 Addendum No. 1 dated 27 May 1971, Service Letter No. 48 dated 20 April 1967 and Manual 100D pertain to this subject.) Amendment 39-132 was effective October 4, 1965. This amendment 39-1342 is effective November 30, 1971.
92-21-06: 92-21-06 GARRETT ENGINE DIVISION, A DIVISION OF THE ALLIED SIGNAL AEROSPACE COMPANY: Amendment 39-8386. Applicability: Garrett Engine Division Model TFE731-2, -3, -3A, -3AR, and -3R turbofan engines assembled with Part Number (P/N) 3072068-X, 3072544-X, 3073015-X, or 3073115-X low pressure turbine (LPT) rotor disks identified by serial number listed in Allied-Signal Aerospace Company, Garrett Engine Division, Alert Service Bulletin (ASB) No. TFE731-A72-3474, dated April 3, 1992, installed on but not limited to Avions Marcel Dassault Falcon 10, 50, and 100, AiResearch Aviation Company 731 Jetstar, Lockheed 1329-25 (Jetstar II), Israel Aircraft Industries Ltd. 1124 Series (Westwind) and 1125 Westwind Astra, British Aerospace DH/HS/BH 125 Series, Learjet 31 (M31), 35, 36, and 55 Series, and Sabreliner NA265-65 (Sabreliner 65 and 65A Series) aircraft. Compliance: Required as indicated, unless accomplished previously. To prevent an uncontained engine failure, accomplish the following: (a) Remove affected third stage LPT rotor disks in accordance with the Accomplishment Instructions of Allied-Signal Aerospace Company, Garrett Engine Division, ASB No. TFE731-A72-3474, dated April 3, 1992, at the next access to the turbine rotor assembly or before accumulating 100 hours time in service after the effective date of this AD, whichever occurs first, and replace with a serviceable disk. (b) For the purpose of this AD, access to the turbine assembly is defined as whenever the low pressure turbine module is separated from the engine. (c) An alternative method of compliance or adjustment of the compliance time that provides an acceptable level of safety may be used if approved by the Manager, Los Angeles Aircraft Certification Office, FAA, Transport Airplane Directorate. The request should be forwarded through an appropriate FAA Principal Maintenance Inspector, who may add comments and then send it to the Manager, Los Angeles Aircraft Certification Office. NOTE: Information concerning the existence of approved alternative methods of compliance with this airworthiness directive, if any, may be obtained from the Los Angeles Aircraft Certification Office. (d) Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate the airplane to a location where the requirements of this AD can be accomplished. (e) The removal and replacement of the LPT rotor disk shall be done in accordance with the following Allied-Signal Aerospace Company, Garrett Engine Division, Alert Service Bulletin: Document No. Page No. Date No. TFE731-A72-3474 Total pages: 8 1-8 April 3, 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 Garrett General Aviation Services Division, Distribution Center, 1944 East Sky Harbor Circle, Phoenix, Arizona 85034, telephone (602) 365-2548. This information may be examined at the FAA, New England Region, Office of the Assistant Chief Counsel, 12 New England Executive Park, Burlington, Massachusetts; or at the Office of the Federal Register, 800 North Capitol Street NW., Suite 700, Washington, DC. (f) This amendment becomes effective on November 27, 1992.
72-01-01: 72-01-01 BELLANCA: Amendment 39-1367. Applies to following airplanes: Models Serial Numbers Affected 14-19-2 4001 thru 4105 14-19-3 4106 thru 4228 14-19-3A 4229 thru 4342 17-30 30001 thru 30262 Compliance: Required as indicated unless already accomplished. To detect leakage of flammable fluids from flexible hose assemblies in the engine compartment within 50 hour's time in service after the effective date of this AD and thereafter at intervals not to exceed 100 hours' time in service, accomplish the following: A) Visually, or by any other method approved by FAA, inspect fuel lines as follows: 1. Pressurize the fuel lines with boost pump operating in high position. When accomplishing this test, the mixture control must be in the idle cutoff position. 2. With fuel lines pressurized, examine all flexible hose exteriors in the engine compartment for evidence of fuel stains, wetness or leakage. 3. After pressure testing fuel hoses, allow sufficient time for excess fuel to drain overboard from the engine manifold before attempting an engine start. B) Visually, or by any other method approved by the FAA, inspect oil lines for evidence of wetness or leakage. C) If, as a result of the inspections required by Paragraphs A or B, fuel or oil stains, wetness or leaking is found, replace with a serviceable hose assembly. D) Inspections required by Paragraphs A and B will no longer be required when hose assemblies are replaced with assemblies identified by either a Bellanca metal identification band or a TSO-C53a Type C identification band. (This does not preclude continued inspections of this area as required by FAR 91.) NOTE: The airplane models listed above use either Aeroquip 601 series or Stratoflex 156 series flexible fluid hoses in their engine compartments. These hose assemblies are available under Bellanca 198003-x series part numbers. This amendment becomes effective December 31, 1971.
2016-11-02: We are adopting a new airworthiness directive (AD) for all 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 requires a detailed visual inspection of the upper and lower engine pylons for protruding, loose, or missing fasteners; and repair, including applicable related investigative and corrective actions, if necessary. This AD was prompted by reports of loose or [[Page 33372]] missing Hi-Lite fasteners on the upper and lower engine pylon structure common to the upper and lower pylon skin panels and engine thrust fitting. We are issuing this AD to detect and correct protruding, loose, or missing fasteners, which could result in structural failure of the engine pylons.
67-14-02: 67-14-02 BOEING: Amdt. 39-404 Part 39 Federal Register April 29, 1967. Applies to Model 727 Series Airplanes. \n\n\tCompliance required as indicated unless already accomplished. \n\n\tTo protect the aircraft structure in the event of an excessively hard landing by providing the desired separation characteristics of the main landing gear side strut, accomplish the following: \n\n\t(a)\tWithin the next 1,000 hours' time in service after the effective date of this AD replace the main landing gear side strut lower segment plugs and side strut universal fittings in accordance with the appropriate accomplishment instruction outlined in the section entitled "II". Accomplishment Instructions (PRR21974 and 22392)", of Boeing Service Bulletin No. 32-79, Revision 1, or later FAA-approved revision, or by an equivalent method approved by the Chief, Aircraft Engineering Division, FAA Western Region. \n\n\t(b)\tWithin the next 6,000 hours' time in service after the effective date of this AD incorporate the controlled groove around the outside upper end of the side strut lower segment in accordance with the appropriate accomplishment instructions outlined in the section entitled "II". Accomplishment Instructions (PRR 21974) and 22392)", of Boeing Service Bulletin No. 32-79, Revision 1, or later FAA-approved revision, or by an equivalent method approved by the Chief, Aircraft Engineering Division, FAA Western Region. \n\n\tThis directive effective May 2, 1967. \n\n\tRevised May 19, 1967.
2024-20-01: The FAA is superseding Airworthiness Directive (AD) 2023-07-13 which applied to certain Airbus SAS Model A350-941 and -1041 airplanes. AD 2023-07-13 required repetitive detailed inspections of the lower attachment studs on the AFT galley complex and, depending on findings, replacement of the lower attachment studs. This AD was prompted by a determination that additional airplanes are affected, and that all affected parts must be replaced with serviceable parts. This AD continues to require the actions in AD 2023-07-13, adds airplanes to the applicability, and requires the replacement of all affected parts; as specified in 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.
2024-20-06: The FAA is adopting a new airworthiness directive (AD) for certain Embraer S.A. Model ERJ 190-100 STD, -100 LR, -100 IGW, -200 STD, -200 LR, and -200 IGW airplanes. This AD was prompted by a manufacturing quality escape concerning certain overheat detection system (ODS) sensing elements. This AD requires inspecting the ODS sensing elements and performing applicable corrective actions, and prohibits the installation of affected parts, as specified in an Ag[ecirc]ncia Nacional de Avia[ccedil][atilde]o Civil (ANAC) AD, which is incorporated by reference. The FAA is issuing this AD to address the unsafe condition on these products.
2024-20-08: The FAA is adopting a new airworthiness directive (AD) for all Rolls-Royce Deutschland Ltd & Co KG (RRD) Model Trent XWB-97 engines. This AD was prompted by the manufacturer revising the existing engine time limits manual (TLM) to introduce new or more restrictive instructions and associated thresholds and intervals for life-limited parts. This AD requires revising the airworthiness limitations section (ALS) of the operator's existing approved engine maintenance or inspection program, as applicable, to incorporate new or more restrictive instructions and associated thresholds and intervals for life-limited parts, as specified in a European Union Aviation Safety Agency (EASA) AD, which is incorporated by reference (IBR). The FAA is issuing this AD to address the unsafe condition on these products.