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87-06-06: 87-06-06 LOCKHEED-CALIFORNIA COMPANY: Amendment 39-5570. Applies to Lockheed Model L-1011-385 series airplanes, certificated in any category. Compliance required as indicated, unless previously accomplished. To prevent engine separation due to broken pylon attach fittings-to-skate-angle bolts, which are cracking because of stress-corrosion, accomplish the following: A. Before accumulating a total of 15,000 hours time-in-service or within the next 3,000 hours time-in-service after the effective date of the AD, whichever occurs later, and thereafter at intervals not to exceed 3,000 hours time-in-service or 15 months, whichever occurs later, accomplish the following: 1. Inspect the pylon attach fittings-to-skate-angle bolts in accordance with the Accomplishment Instructions in Lockheed Service Bulletin 093-54-049, Revision 1, dated September 25, 1986, or later FAA approved revision. 2. If broken bolts are found, before further flight, replace each broken bolt with a new bolt in accordance with the Accomplishment Instructions in Lockheed Service Bulletin 093-54-049, Revision 1, dated September 25, 1986, or later FAA-approved revision. B. Before accumulating a total of 15,000 hours time-in-service or before January 15, 1991, whichever is later, replace all of the pylon attach fittings-to-skate-angle H-11 steel bolts with stress-corrosion resistant MP-35N bolts in accordance with the Accomplishment Instructions in Lockheed Service Bulletin 093-54-049, Revision 1, dated September 25, 1986, or later FAA- approved revision. The inspections required by paragraph A. may be discontinued after paragraph B. has been accomplished. C. Alternate means of compliance which provide an acceptable level of safety may be used when approved by the Manager, Los Angeles Aircraft Certification Office, FAA, Northwest Mountain Region. D. Special 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. All persons affected by this directive who have not already received the appropriate service documents from the manufacturer may obtain copies upon request to Lockheed-California Company, P.O. Box 551, Burbank, California 91520, Attention: Commercial Order Administration, Dept. 65-33, U-33, B-1. These documents may be examined at the FAA, Northwest Mountain Region, 17900 Pacific Highway South, Seattle, Washington, or the Los Angeles Aircraft Certification Office, 4344 Donald Douglas Drive, Long Beach, California. This Amendment becomes effective April 2, 1987.
2016-13-05: We are adopting a new airworthiness directive (AD) for all General Electric Company (GE) GE90-76B, GE90-77B, GE90-85B, GE90-90B, and GE90-94B turbofan engines. This AD was prompted by an uncontained failure of the high-pressure compressor (HPC) stage 8-10 spool, leading to an airplane fire. This AD requires eddy current inspection (ECI) or ultrasonic inspection (USI) of the HPC stage 8-10 spool and removing from service those parts that fail inspection. We are issuing this AD to prevent failure of the HPC stage 8-10 spool, uncontained rotor release, damage to the engine, and damage to the airplane.
2001-08-10: This amendment adopts a new airworthiness directive (AD) that applies to certain Aerostar Aircraft Corporation (Aerostar) Models PA-60-600, PA-60-601, PA-60-601P, PA-60-602P, and PA-60-700P airplanes. This AD requires you to replace both of the existing main landing gear lower side brace assemblies with parts of improved design. This AD is the result of several reports of cracking of the main landing gear lower side brace at the upper bolt lug discovered on preflight inspection. The actions specified by this AD are intended to correct damage or cracks in the main landing gear lower side brace at the upper bolt lug where the upper and lower side braces connect. This could result in failure of the main landing gear lower side brace. Such failure could lead to loss of control of the airplane.
2016-12-11: We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 787-8 airplanes. This AD was prompted by a report that certain center and outboard stowage bin modules were incorrectly installed. This AD requires an inspection of the center and outboard stowage bin modules for missing parts, quick release pins that are not fully engaged, and parts that are installed in incorrect locations; and corrective actions if necessary. We are issuing this AD to detect and correct incorrectly installed center and outboard stowage bin modules that might not remain intact during an emergency landing, resulting in injuries to occupants and interference with airplane evacuation.
2010-22-02: We are adopting a new airworthiness directive (AD) for the products listed above. This AD results from mandatory continuing airworthiness information (MCAI) originated by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as: Seven cases of on-ground hydraulic accumulator screw cap/end cap failure have been experienced on CL-600-2B19 aeroplanes, resulting in the loss of the associated hydraulic system and high-energy impact damage to adjacent systems and structure. * * * * * * * * A detailed analysis of the calculated line of trajectory of a failed screw cap/end cap for each of the accumulators has been conducted, resulting in the identification of several areas where systems and/or structural components could potentially be damaged. Although all of the failures to date have occurred on the ground, an in-flight failure affecting such components could potentially have an adverse effect on the controllability of the aeroplane. * * * * * This AD requires actions that are intended to address the unsafe condition described in the MCAI.
2016-13-04: We are adopting a new airworthiness directive (AD) for certain BRP-Powertrain GmbH & Co KG Rotax 912 F2, 912 F3, 912 F4, 912 S2, 912 S3, 912 S4, 914 F2, 914 F3, and 914 F4 reciprocating engines. This AD requires re-identification of the engine model and concurrent modification of the aircraft to indicate the maximum coolant temperature limit. This AD was prompted by a design change introduced by the manufacturer that relocated the engine cylinder head temperature sensor to a different location and converted it to a coolant temperature sensor. We are issuing this AD to prevent exceeding engine coolant temperature limits, which could result in loss of engine coolant, damage to the engine, and loss of control of the airplane.
2016-12-14: We are adopting a new airworthiness directive (AD) for all Embraer S.A. Model ERJ 170 airplanes; and all 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 reports of cracks in certain engine low-stage bleed check valves. This AD requires replacing the air management system (AMS) controller operation program of the AMS controller processor boards, and replacing the current low-stage bleed check valve and associated seals. We are issuing this AD to prevent failure of the low-stage bleed check valve; simultaneous failures of both low-stage bleed check valves could result in a dual engine in- flight shutdown.
74-22-04: 74-22-04 TELEDYNE CONTINENTAL MOTORS: Amendment 39-1998. Applies to TCM Model 6-285- B engines with engine serial numbers 700000 through 700095. Compliance required within the next 25 hours time in service after the effective date of this AD unless already accomplished. Inspect the crankcase main bearing oil supply passages in accordance with procedures outlined in Teledyne Continental Service Bulletin M74-21. After compliance with this bulletin, if it is determined that an oil passage has been omitted the engine must be removed from service. This amendment becomes effective October 28, 1974.
97-02-12: 97-02-12 ROLLS-ROYCE PLC: Amendment 39-9897. Docket 96-ANE-09. Applicability: Rolls-Royce plc. (R-R) Models RB211-535E4 and -535E4-B turbofan engines installed on Boeing 757-200 series aircraft. Note 1: This airworthiness directive (AD) applies to each engine identified in the preceding applicability provision, regardless of whether it has been modified, altered, or repaired in the area subject to the requirements of this AD. For engines that have been modified, altered, or repaired so that the performance of the requirements of this AD is affected, the owner/operator must request approval for an alternative method of compliance in accordance with paragraph (c) of this AD. The request should include an assessment of the effect of the modification, alteration, or repair on the unsafe condition addressed by this AD; and, if the unsafe condition has not been eliminated, the request should include specific proposed actions to address it. Compliance: Required as indicated, unless accomplished previously. To prevent compressor stall and subsequent engine rundown on one or both engines, accomplish the following: (a) No later than 9 calendar months after the effective date of this AD, install a fuel flow governor (FFG) that incorporates a revised minimum compressor discharge P4 stop setting, in accordance with R-R Mandatory Service Bulletin (SB) No. RB.211-73-B869, Revision 1, dated May 24, 1996. (b) Installation of improved FFGs on both engines for each Boeing 757 aircraft in accordance with paragraph (a) of this AD constitutes terminating action to the requirements of AD 96-04-11. (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, Engine Certification Office. The request should be forwarded through an appropriate FAA Principal Maintenance Inspector, who may add comments and then send it to the Manager, Engine Certification Office. Note 2: Information concerning the existence of approved alternative methods of compliance with this airworthiness directive, if any, may be obtained from the Engine Certification Office. (d) Special flight permits may be issued in accordance with sections 21.197 and 21.199 of the Federal Aviation Regulations (14 CFR 21.197 and 21.199) to operate the aircraft to a location where the requirements of this AD can be accomplished. (e) The actions required by this AD shall be done in accordance with the following R-R Mandatory SB: Document No Pages Revision Date RB.211-73-B869 1-4 1 May 24, 1996 5-9 Original February 12, 1996 Supplement 1 Original February 12, 1996 Total Pages: 10. 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 Rolls-Royce plc, P.O. Box 31, Moor Lane, Derby, DE248BJ, United Kingdom; telephone 1332-249428, fax 1332-249423. Copies may be inspected at the FAA, New England Region, Office of the Assistant Chief Counsel, 12 New England Executive Park, Burlington, MA; or at the Office of the Federal Register, 800 North Capitol Street NW., suite 700, Washington, DC. (f) This amendment becomes effective on April 4, 1997.
64-21-06 R2: 64-21-06 R2 BOEING VERTOL: Amendment 813 Part 507 Federal Register September 10, 1964 as amended by Amendment 39-2156 is further amended by Amendment 39-3827. Applies to Model 107-II helicopters. Compliance required as indicated. As a result of a fatigue failure in service of the rotor pitch housing, accomplish the following: (a) Unless already accomplished within the last 30 hours' time in service, before further flight, inspect the lug areas of all rotor pitch housings P/N's 107R2553-1, -2, -3, -4, -5, and -6 and blade sockets P/N's 42R1043-7 and -8 with 260 or more hours' time in service using magnetic particle inspection method or FAA approved equivalent. To accomplish the inspection, remove rotor blades and rotor hub pitch bearing assemblies. Repeat this inspection at intervals not to exceed 30 hours' time in service. (b) Inspect, using magnetic particle inspection, the lug areas of all rotor pitch housings P/N's 107R2553-1, -2, -3, -4, -5, and -6 and blade sockets P/N's 42R1043-7 and -8 with less than 260 hours' time in service in accordance with (a) prior to the accumulation of 260 hours' time in service. (c) Conduct a daily visual inspection for cracks in the lug areas of all rotor pitch housings P/N's 107R2553-1, -2, -3, -4, -5, and -6 and blade sockets P/N's 42R1043-7 and -8. This may be accomplished without disassembly from the helicopter. (d) Unless already accomplished, within the next 50 hours in service on pitch housing 107R2553-8, -10, -14, -16, with 1000 hours or more in service and within the next 100 hours in service on pitch housing 107R2553-7, -9, -13, 15, with 2000 hours or more in service install crack detector wire in accordance with Part I "Installation Procedure" of Boeing Service Bulletin No. 107-343 dated March 10, 1980, or equivalent. (1) Inspect for cracks in accordance with Part II "Inspection Procedures" of the above Bulletin, or equivalent, the lug area of pitch housings 107R2553-8, -10, -14, -16 with 1000 hours or more in service within the next 50 hours in service and thereafter at intervals not to exceed 25 hours in service, and pitch housing 107R2553-7, -9, -13, -15 with 2000 hours or more in service within the next 100 hours in service and thereafter at intervals not to exceed 50 hours in service. (2) Unless already accomplished, install crack detector wire in accordance with Part I "Installation Procedure" of the above Bulletin, or equivalent on pitch housings 107R2553-8, -10, -14, -16 with less than 1000 hours in service prior to the accumulation of 1050 hours in service, and on pitch housings 107R2553-7, -9, -13, -15 with less than 2000 hours in service prior to the accumulation of 2100 hours in service. (3) Inspect pitch housings 107R2553-8, -10, -14, -16 with less than 1000 hours in service in accordance with (1) prior to accumulation of 1050 hours in service. Inspect pitch housings 107R2553-7, -9, -13, -15 with less than 2000 hours in service in accordance with (1) prior to accumulation of 2100 hours in service. (4) Conduct a visual inspection for cracks in the lug area of blade sockets 42R1043-11, -12, -13 and -14 at intervals not to exceed 50 hours in service. This may be accomplished without disassembly from the helicopter. (e) If any cracks are found replace the part before further flight with a part found serviceable in accordance with this AD. (f) Upon request with substantiating data submitted through an FAA Maintenance Inspector, the compliance times specified in this AD may be adjusted by the Chief, Engineering and Manufacturing Branch, FAA Eastern Region. (g) Retire from service all rotor pitch housings P/N's 107R2553-7, -8, -9, -10, -13, - 14, -15, d -16 upon the accumulation of 5,000 hours' total time in service. This supersedes AD 64-06-08. Amendment 39-813 was effective September 10, 1964. Amendment 39-2156 was effective April 9, 1975. This Amendment 39-3827 is effective July 7,1980.