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fault isolation manualTroubleshooting may involve avionic LRU changes, however, it does not involve multiple avionic LRU changes in pursuit of a system fault, unless the changes are made in accordance with a published approved fault isolation maintenance procedure (e.g. Troubleshooting Manual, Fault Isolation Manual procedure). Customer’s claim includes all applicable documentation of such tests with the returned Boeing Product, including but not limited to: Central Maintenance Computer ( CMC), Flight Maintenance Computer System, (FMCS), Fault Isolation Manual (FIM), Engine Indicating and Crew Alerting System (EICAS) or Built In Test Equipment (BITE) messages. All rights reserved. View our Terms of Service and Privacy Policy. For instance, instead of spending time searching manually or electronically through the Fault Isolation Manual to troubleshoot the problem and then through the Airplane Maintenance Manual (AMM) for repair information, maintenance personnel can click on 2D airplane system diagrams to retrieve line-replaceable-unit information, including maintenance procedures, troubleshooting information, parts data, wiring diagrams, maintenance tips, in-service activity reports, and service letters. It also enables retrieval of part information directly from the airplane Illustrated Parts Catalog (IPC). Repair information is structured to standardize record contents and format. This enables operators and maintenance organizations to: Incidents can be plotted graphically to show exactly which part of the airframe was affected. Clicking on an incident brings up detailed information about it. The graphical user interface streamlines access to information across all documentation. And the intuitive user interface and common look and feel minimize user learning curves. FIM stands for Fault Isolation Manual (also Functional Independence Measure and 308 more ) Rating: 5 Votes: 5 What is the abbreviation for Fault Isolation Manual.http://sewonfd.com/userData/board/adt1616-manual.xml
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This information should not be considered complete, up to date, and is not intended to be used in place of a visit, consultation, or advice of a legal, medical, or any other professional. I ordered up the part and checked effective in the ipc reference 27-09-01. I decided to use chapter 20 of the wiring diagram to change the rrcm and performed the fim task 27-21-00. The test passed and the message on the EICAS disappeared. I signed the logbook; inspected and found right-hand rudder ratio change module failed fault ball; removed and replaced per maintenance manual operations checked good. I failed to read this maintenance manual reference and see that the operations check was an rii item. The test was completed as described in the maintenance manual; but no one else besides the pilots witnessed the operations check to sign an rii. I feel a note should be put I the bfim to direct the mechanic performing the task if he changes the rrcm due to a fault with the rrcm to follow the maintenance manual and give the maintenance manual reference. Because he had changed the ratio change module box and had not actually broken into; the rigging or any part of the rudder cable or trim system; an rii was not required. Reporter stated he still feels some reference to a maintenance manual chapter should be included in the bfim; in case an rii is required; especially for flight control systems.I followed the Fault Isolation Manual and found the right-hand Rudder Ratio Change Module had failed. I ordered up the part and checked effective in the IPC reference 27-09-01. I decided to use Chapter 20 of the Wiring diagram to change the RRCM and performed the FIM task 27-21-00. The test passed and the message on the EICAS disappeared. I signed the logbook; inspected and found Right-hand Rudder Ratio Change Module Failed fault ball; removed and replaced per maintenance manual operations checked good. I failed to read this maintenance manual reference and see that the operations check was an RII item. The test was completed as described in the maintenance manual; but no one else besides the pilots witnessed the operations check to sign an RII. I feel a note should be put I the BFIM to direct the Mechanic performing the task if he changes the RRCM due to a fault with the RRCM to follow the maintenance manual and give the maintenance manual reference. Because he had changed the Ratio Change Module box and had not actually broken into; the rigging or any part of the rudder cable or trim system; an RII was not required. Reporter stated he still feels some reference to a maintenance manual chapter should be included in the BFIM; in case an RII is required; especially for flight control systems. See NASA's ASRS site for official report. It only takes a minute to sign up. I want to know if aircraft engineers are mandated to close or rectify a defect by only following the fault isolation manual (FIM). Can an engineer instead use his knowledge and experience of the systems to isolate the problem and resolve the defect? Hypothetical, or actual situation. If actual, and if properly diagnosed, I don't see a problem. I could be wrong, but I don't think technicians are bound to using checklists in the way aircrew are. Now if they didn't use a reference and missed something, that's a totally different issue. If such information is not included contact OEM. Please be sure to answer the question. Provide details and share your research. Making statements based on opinion; back them up with references or personal experience. Use MathJax to format equations. MathJax reference. To learn more, see our tips on writing great answers. Browse other questions tagged aircraft-maintenance dash-8 or ask your own question. There are multiple approaches.There are two approaches.This may be intrusive, and could interfere with normal operation briefly.Operational failure will eventually occur when an item is used in its normal mode of operation if there is no intervention. The procedures associated with periodic maintenance are generally called a Periodic Maintenance System (PMS).This relies on invasive procedures that renders a system inoperable for a brief period while users run manual diagnostic or preventative procedures. The following are a few examples.There is a random chance that the system or item will not function when required. Reliability declines as the time passes, and probability of failure increases until action is taken.Average reliability improves as the time between maintenance actions is reduced.There are two methods.This usually requires the following.Satellites intended to operate in geosynchronous orbit must incorporate active recovery that prevents total failure when one or more parts fail.This could be a part inside an item, or it could be the whole item. This decision is made based on which is less expensive to replace. If you replace your own disk drive and install your own operating system, then it is less expensive to purchase the disk drive. If you need technical help then it is less expensive to replace the whole computer.This applies to situations where failure of one component causes the entire item to fail. The type of calculation is similar to a series electronic circuit.The type of calculation is similar to a parallel electronic circuit.Thermal shock caused by heating and cooling can induce failure when power is cycled on and off. Most mechanical switches are built to operate 10,000 cycles before failure, which is about 30 years for a cycle rate of 1 action per day.Down time is the time while the system is unavailable for normal use, and this consist of the time while periodic maintenance is being performed and the amount of time while the system is faulted.This is a useful measurement for items that incorporate automatic recovery or condition based maintenance.The following is an example of the kind of values that could be used for estimating the mechanical portion of the recovery time associated with replacing a failed circuit card.Military systems and large commercial systems share reliability constraints.These reconfigure systems without human intervention after combat damage and normal failure.This effect grows worse as size grows.If Mean Time To Repair (MTTR) is 3 days, then the system will never work.By using this site, you agree to the Terms of Use and Privacy Policy. By continuing to use this website, you are agreeing to our cookies policy. Call us on This allow you to apply quickly, track your applications and get the latest jobs straight to your inbox By registering I agree I have read and understand our Privacy Policy Click here if the page doesn't refresh By sending my CV, I agree I have read and understand the Privacy Policy Click here if the page doesn't refresh. If you continue browsing the site, you agree to the use of cookies on this website. See our User Agreement and Privacy Policy.If you continue browsing the site, you agree to the use of cookies on this website. See our Privacy Policy and User Agreement for details.If you wish to opt out, please close your SlideShare account. Learn more. You can change your ad preferences anytime. Why not share! I sent a request to ? www.HelpWriting.net ? and found a writer within a few minutes. Because I had to move house and I literally didn’t have any time to sit on a computer for many hours every evening. Thankfully, the writer I chose followed my instructions to the letter. I know we can all write essays ourselves. For those in the same situation I was in, I recommend ? www.HelpWriting.net ?.Save so as not to loseSpec 2100 to produce the ATA iSpec 2200. Information Standards for Aviation MaintenanceATA Spec 100 and Spec 2100, and provides guidance forO) section of the older airplane models.Boeing’s recommended minimum equipmentEquipment List (MMEL).XX-VV-ZZ, where:Page Type Page BlockMAINTENANCE PRACTICES page block.ListNow customize the name of a clipboard to store your clips. It’s constantly improving and developing. Both file upload and download are very convenient. Services: Sync music, Manage music, Recover missing metadata, Record CDs Download MediaMonkey Now Buy MediaMonkey Gold Get Addons Never use any other conversion tool again. Find Music File Converter Mp3 Mp3 converter www.easypdfcombine.com Merge And Convert Files Into PDFs For Free With EasyPDFCombine App. For a better experience, we recommend using another browser. Learn more Facebook Email or phone Password Forgotten account? Sign Up Sign up for Facebook to get started. Sign Up It's free and anyone can join. We recommend you upgrade to a newer version of Internet Explorer or switch to a browser like Firefox or Chrome. The flight was completed without further event. Subsequent engineering assessments twice led to release to service followed by recurrence and after the fourth such release, a left engine overheat was annunciated. After flight, a hole in the engine combustor case was found and the engine was removed for repair. The Investigation attributed the delayed identification of the causal fault to inappropriate guidance in the aircraft manufacturer’s Fault Isolation Manual which was has since been amended.With the fumes continuing and all the pilots on oxygen, an “urgency” message was transmitted to ATC and the aircraft subsequently continued to Heathrow without further event for a daylight landing. None of the 163 occupants were affected by the fumes.It was noted that the 49 year-old Captain had a total of 20,000 flying hours of which 9358 hours were on type. The flying experience of the First Officer and the Relief First Officer was not documented.This had been quickly followed by cabin crew reports of fumes in both front and rear of the passenger cabin and the Relief First Officer had entered the cabin to confirm the intensity of the fumes there. Whilst the Checklist was being actioned, further reports of fumes in the cabin continued and there was no further change in their intensity on the flight deck. An uneventful autoland was completed at Heathrow and, after an external aircraft inspection by the RFFS found nothing of concern, the aircraft taxied to its gate and normal passenger disembarkation followed.After engineering work including replacement of the APU and various components in the aircraft air conditioning system, a ground run was carried out but fumes were again detected and this time, the left engine was identified as the source. After no evidence of oil was found in the left engine compressors, the left engine bleed air supply was isolated by locking the corresponding Pressure Regulating and Shut-Off Valve (PRSOV) closed and the aircraft was released to service again in accordance with the MEL.The appropriate Abnormal Checklist for this alert was followed and Company Maintenance Control consulted. Engine parameters including EGT were observed to be within the normal range and it was concluded that the warning was false and the planed flight was thereafter competed without further event. GE established that in this case, a swirler weld had broken and the loose part had eventually chafed through the fuel nozzle allowing the resultant fuel spray to ignite and burning through the combustion chamber case. This was the cause of the EICAS indication of Left Engine Overheat which occurred six days after the first flight when fumes had been detected. It was not possible to determine the cause of the broken weld, but no evidence could be found which indicated loose bolts or a weld deficiency had been causal. In particular, although weld repairs were permitted, no such repair had been made. The former (fuel) case required that the engine fuel nozzles should be inspected for carbon contamination which “would identify unusual combustor damage before more significant consequential damage occurs”. The latter (oil) case did not require inspection of the fuel nozzles and since the reported fumes were attributed to oil, they were not inspected. GE stated that this event was the first known occurrence of this failure on a GE90 engine. Visit our updated privacy and cookie policy to learn more. Source: Instron With each loading cycle, damage to the material accumulates. More complex fatigue tests can also produce greater insight into how fatigue damage accumulates, feeding models of exactly how performance of a component will change during its service life. This article aims to provide a brief overview of the most common types of fatigue tests and where each is commonly used. The loads applied are normally a fraction of the yield strength of the material, so tested well within the elastic limit. Multiple tests are needed to determine an S-N curve, each test (or group of tests) is performed at a different cyclic stress to determine the number of cycles until the material fails. The combined results can then be used to create the S-N curve (stress level, S, against number of cycles to failure, N). Waveform shape is one; the most common waveform is a sine wave, but it can be triangular, trapezoid or even real-life load data. The second parameter is the stress level, often expressed as a combination of mean and amplitude or maximum load and an R-ratio (the ratio of the max to min stress). The third is the test frequency, which often depends on the material and the limits of the testing system. This is normally for materials that see very high stresses through thermal expansion, and hence is common in either the power generation industry or in materials for aerospace engines.In order to achieve constant strain rate, triangular or trapezoid are the most common in LCF and very much slower than HCF, with Here we not only look at the effect of strain cycles (and hence stress) but also temperature cycles. Temperature and strain are often cycled at the same time. Typical loading patterns include triangular, trapezoid with holds, either cycling temperature in phase or out of phase with strain. TMF is a complex and very advanced fatigue testing that is critical in understanding interaction of thermal expansion with mechanically induced strain. Source: InstronThese include ensuring the transducers are calibrated and the system is tuned. Calibration of transducers such as loadcells and extensometers verifies that these measurement tools will give accurate results complying with international standards. On the other hand, tuning provides suitable control parameters for the controller according to the loadstring so that the actuator responds correctly to the control signal and you apply the loading you intend. Manual tuning is time consuming and inexperienced operators may not be able to do this consistently. Automatic tuning methods provide a much more intuitive process that will also prevent any human errors. These methods include stiffness-based tuning, which takes place well within the elastic region of the specimen, and square-wave auto tuning, which takes place in the plastic region of the material. This method uses more aggressive square-wave loading patterns that could damage the specimen. Therefore, it is common to replace specimens for the actual test. These include higher data acquisition rates to accommodate newer and better transducers and intelligent data tools that optimize what and how much data are collected. It is often the case for fatigue tests that not all cycles are required to be recorded in full. Tell me how we can improve. Please tell us why. All Sponsored Content is supplied by the advertising company. Interested in participating in our Sponsored Content section. Contact your local rep. Attendees have the opportunity to uncover new resources, experience equipment hands-on, evaluate the latest technologies and products, and connect face-to-face with industry experts. 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A fast track opposition is made by the owner of an earlier mark which is identical or similar to the opposed mark and can only be brought on grounds of complete identity or a likelihood of confusion. The decision will be made at the discretion of the Hearing Officer who can only consider doing so if the opposition does not meet the requirements for a fast track opposition, but would meet the requirements for a standard opposition. The form is only available as an e-Form on the trade mark section of the IPO website. It should be noted that a party may file the TM7a before deciding if they will lodge either a standard of fast track opposition.Therefore, you may wish to consider obtaining professional legal advice from a registered trade mark, or patent attorney, or a solicitor before you make any decision on how to proceed. The examiner will consider the amendment and tell you if it is clear enough to be accepted. If acceptable your application will proceed to registration. You must put your withdrawal request in writing. However, if you withdraw your application after an opposition is filed and the opponent has, prior to filing the opposition, given you a reasonable chance to withdraw your application then you may be liable for some limited costs. If you file an opposition without first having contacted the applicant and the applicant withdraws the application without defending it, you will not be awarded any costs and you will not recover the cost of filing the opposition. However, the Tribunal will not, as a matter of course, copy any other document. To ensure fairness and transparency of proceedings, it is imperative that any correspondence, including forms, sent to the Tribunal is copied to the other side and contain confirmation that it has been copied. If parties persistently fail to copy correspondence and documents to the other side, this will be regarded as unreasonable behavior and there may be cost implications at the conclusion of the proceedings.