Boeing 737 Structur Repair Manual [Unlimited EBook]

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Some features of WorldCat will not be available.By continuing to use the site, you are agreeing to OCLC’s placement of cookies on your device. Find out more here. However, formatting rules can vary widely between applications and fields of interest or study. The specific requirements or preferences of your reviewing publisher, classroom teacher, institution or organization should be applied. Please enter recipient e-mail address(es). Please re-enter recipient e-mail address(es). Please enter your name. Please enter the subject. Please enter the message. Publisher: Seattle, Wash.: Boeing Proprietary, 2000.Please select Ok if you would like to proceed with this request anyway. All rights reserved. You can easily create a free account. Boeing 737 Structural Repair Manual1. 2015-03-16 structural repair manual boeing 737 download. These Manuals is incorporated inthe standard formatting and it can be read through the platform. Did you searching for 737ng Structural Repair Manual?boeing 737 structural repair manual 200.Students willdescribe engineering Supplemental Composite Structure DamageAssessment and Repair Manual for the Next. He assisted Boeing with repair requirements forthe composite components. Approximately 5.5 metres (or 18 feet) ofcabin covering and structure was detached from On 28 April 1988, aBoeing 737-200, being operated by Aloha Airlines experienced Thepassenger oxygen manual tee handle was not actuated. The Boeing Company, Crystal Mountain, Inc,Grassroots political organization Maintenance Docs include StructuralRepair Manual, Service Bulletins, Airplane Flight Manual, AircraftCurrently supporting the 737 MAX Nacelle structures. Maintenance. Structural Repair and Alpha-Jet, Breguet Atlantic or BellUH-1D Helicopter (all manuals).Boeing 737-800. installed using the Boeing Model 737 structural repair manual (SRM)repairs identified in Part 3, Permanent Repair, of Paragraph 3.B.,Work Instructions,.

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Great value for the price! Privacy Policy. The engineering drawing for the composite repairs was integrated into the SRM. The NDT procedure for bonded composite doublers (ultrasonic resonance technique) was also included in the Boeing NDT Standard Practices Manual. Finally, a set of training classes are being developed to safely integrate composite doubler technology into the commercial maintenance depots. The classes will cover all aspects of design, analysis, installation, quality control and in-service inspection. View chapter Purchase book Read full chapter URL: Nondestructive Inspection and Repair: Because Things Do Not Always Go As Planned F.C. Campbell, in Manufacturing Processes for Advanced Composites, 2004 13.7 Repair All repairs of composite or bonded assemblies should be conducted per the specific instructions outlined in the Structural Repair Manual (SRM) or Technical Order (TO) for the aircraft. If the damage exceeds the limits specified in the manual, it is imperative that a qualified stress engineer approves the repair procedure. All personnel conducting structural repairs should be trained and certified in the repair procedure. The instructions in the repair manual must be followed to the letter. A repair that is done incorrectly can often result in a second more extensive and complicated repair. Repairs can be categorized as fill, injection, bolted or bonded repairs. Simple fill repairs ( Fig. 17 ) are conducted with paste adhesives to repair non-structural damage such as minor scratches, gouges, nicks and dings. Injection repairs use low-viscosity adhesives that are injected into composite delaminations or adhesive unbonds. Bolted repairs are usually done on thick highly loaded composite laminates while bonded repairs are often required for thin skin honeycomb assemblies. Like NDI, the literature on composite repair is quite extensive. An excellent in-depth treatment of repair technology can be found in Ref. 6. Fig. 17.

Typical Composite Repairs View chapter Purchase book Read full chapter URL: Repairing composites F. Collombet,. R. Thevenin, in Advances in Composites Manufacturing and Process Design, 2015 10.1 Introduction “In-field” repair of composite primary principal structures is a very strategic issue for the aeronautical industry. Obviously, whatever the material (metallic or composite), the Structural Repair Manual (SRM) does not cover all repairs. A view of A340-541 after a tail strike (MSN 608) of Emirate Company for Flight EK-407 is shown in Figure 10.1 (left) with no injuries and no fatalities. The incident occurred on March 20, 2009. Even if a structural repair had been defined and validated by Airbus experts, Emirate Company decided to replace all damaged parts. A view of B787-8 after a fire under the crown in front of the vertical tail fin of an Ethiopian Airlines aircraft in Heathrow Airport (UK) is shown in Figure 10.1 (right) with no injuries and no fatalities. These two costs do not include grounding costs, which are really huge. Everything needs to be controlled and approved by certification authorities. The requirements must be accepted worldwide by companies and certified by airworthiness authorities, which include the US Federal Aviation Administration (FAA) as well as the European Aviation Safety Agency (EASA). Obviously, the development and production of unitary complex primary composite structure as quickly as possible is a great challenge. Composite solutions need to be considered with real “industrial” variabilities and with a continuous link between all scales (from microscale to structure scale). A definition of the state of the field is mandatory for “in-field” repairs of composite primary principal structures. View chapter Purchase book Read full chapter URL: Repair of damaged aerospace composite structures E. Archer, A. McIlhagger, in Polymer Composites in the Aerospace Industry, 2015 14.

6 Conclusion and future trends Regarding the current composite airframes, Boeing claim their rapid composite repair technique for the 787 offers temporary repair capability to get an airplane flying again quickly, despite minor damage that might ground an aluminium airplane. Looking to the future, EADS Innovation has been working on automation that might eventually carry out an entire repair cycle encompassing damage detection, surface preparation, repair patch creation, patch application and finally quality assurance checking. Meanwhile, the German Aerospace Research Centre DLR has been investigating the automation of resin-infused repairs. The aim is to develop scarf repair capability including damage removal by computer-controlled milling, impregnation of a dry preform laid into an excised site, and subsequent cure. DLR claims the method is particularly appropriate for curved areas, reducing complexity and avoiding the need to produce special tooling. Laser specialists cleanLASER and SLCR, also in Germany, are separately working on systems to prepare repair sites. Looking beyond state of the art, research on structural health monitors using techniques such as embedded fibre optic strain sensing and self-healing composites using microvascular systems of repair networks have been demonstrated. Whatever the future holds, the approach for the composite structure design teams needs to be based upon input and knowledge gained from a working relationship established with the airline maintenance personnel. This can be accomplished through repair workshops, or inquiries, involving airline and OEM customer support personnel, engineering personnel and involvement with the Commercial Aircraft Composite Repair Committee (CACRC). CACRC meets twice per year, under the auspices of the SAE International, alternating between Europe and North America. The remit is to address issues experienced by aircraft operators when maintaining composite components on commercial aircraft.

Delegates are drawn from airlines, OEMs, regulatory authorities, material suppliers and maintenance and repair organisations. View chapter Purchase book Read full chapter URL: Repair of metallic airframe components using fibre-reinforced polymer (FRP) composites A.A. Baker, in Rehabilitation of Metallic Civil Infrastructure Using Fiber Reinforced Polymer (FRP) Composites, 2014 2.1 Introduction Airframe structures must be repaired or replaced when service damage results, or has the potential to result, in the residual strength being reduced below an acceptable level for flight safety. The most prevalent forms of service damage in aging metallic airframe components are cracks and corrosion. The availability of efficient, rapid and cost-effective means of making repairs is a very important economic requirement for both military and civil aircraft. Repairs to significant damage generally involve the attachment of a reinforcing metallic patch or doubler over the damaged region. The aim is to restore mechanical properties to the original design specifications, including: residual strength, stiffness, fatigue resistance and damage tolerance. 1 The method of attaching the repair patch prescribed in the Structural Repair Manual (SRM) for the aircraft uses bolts or rivets. Figure 2.1a is a schematic of a typical mechanically fastened repair, for example to a wing skin. Although these SRM repair procedures are generally effective, they can have limited fatigue lives, especially for repairs to relatively thick, highly loaded primary structure; they are also damaging in that they require a large number of extra fastener holes. The purpose of this chapter is to show that application of a fibre composite patch by structural adhesive bonding over the defective region, as illustrated in Fig. 2.1b, can provide a far more efficient and cost-effective repair as well as being much less damaging, fatigue prone and intrusive to the structure.
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This chapter discusses the repair of metallic aircraft structure with adhesively bonded fibre-reinforced composites, mainly from an Australian perspective. Details are then provided on the technology for applying the reinforcing patches to the structure, especially the critical issue of surface treatment for durable adhesive bonding. The design of patch repairs is then discussed, mainly from the perspective of estimation of stress intensity in the patched crack, including some experimental confirmation of an analytical model. The future challenge in the certification of bonded repairs for flight-critical applications is discussed, and a proposal is made on how to meet this challenge. This is based on the testing of representative joints to obtain material allowables for the patch system and the use of proof testing or structural-health monitoring to validate the through-life integrity of the applied patch. Finally, two applications, one USAF and the other Australian, are briefly described followed by a conclusion on limitations and lessons learned. There are types of damage that can be anticipated, so that the repair of this damage can be studied in advance. Manual and other Instructions for Continued Airworthiness (such as Manufacturer Structural Repair Manual ) are provided by the TCH for the aircraft operators and contain useful information for the development and approval of repairs. When these data are explicitly identified and approved, they may be used by the operators without further approval to cope with anticipated in-service problems arising from normal usage provided that they are used strictly for the purpose for which they have been developed. This chapter lists the scope of bonded repairs and reinforcements—some applications are listed in the appendix. Important materials, processes and design issues are presented, based on Australian approaches.

Finally, key issues are addressed with the focus on adhesive bond structural integrity for through-life management of repairs. Structural modifications to airframe structures are frequently made either to repair regions damaged by fatigue cracking or to extend fatigue life by reducing stresses in prospective regions of cracking. With traditional repairs a metallic patch or doubler is attached to the parent structure using bolts or rivets after removal of the cracked region. The aim is to restore mechanical properties, including: residual strength, stiffness, fatigue resistance and damage tolerance to an acceptable level. When repairing cracks, the method for attaching the repair patch generally prescribed in the aircraft's structural repair manual (SRM) uses bolts or rivets. Fig. 1 A shows a schematic of a typical mechanically fastened repair recommended, for example, for a wing skin suffering fatigue cracks. Prior to application of the reinforcement the defect—typically a crack—is removed to leave round or elliptical shaped smooth-edged cut-out. Fig. 1. Comparison between (A) mechanically fastened and (B) bonded repairs. Well designed and correctly implemented these SRM repair procedures are effective in the short term, however, they may have limited fatigue life due to the development of high stresses at the new fastener holes. Some problems associated with mechanical repairs are listed in Fig. 1 A include the danger of inadvertent damage to the internal structure, wiring and hydraulic lines. An alternative approach is to apply the repair patch over the defective region using structural adhesive bonding as illustrated in Fig. 1 B. This approach is far more efficient in transferring loads from the parent structure into the patch or reinforcement, and does not cause damage to the parent structure because there is no requirement for fastener holes.

This approach does not require removal of the crack; this is an important advantage because in many cases removal of the crack is difficult or not feasible. To demonstrate the advantages of using bonded repairs for crack repair, fatigue tests were performed on patched edge-notched 2024 T3 aluminium alloy panels, shown inset with details in Fig. 2 A and B. The total thickness of the aluminium patches, on both sides, was equal to the thickness of the metal. The plotted points show crack growth. Therefore, inspection techniques (NDI) using eddy currents can be used to detect crack growth—as shown by the plotted points in Fig. 2. Fig. 2 A shows that the mechanically attached metallic patch provides poor reinforcing efficiency since there is only a very slight reduction in crack growth rate. Also, as seen in Fig. 2, once the crack emerges from under the patch it grows very rapidly. The metallic patch can appear to be effective in some cases if the crack arrests temporarily in a fastener hole. In this chapter the scope of bonded repairs and reinforcements, with examples of applications, is first discussed very briefly. Then key materials and process and design issues are discussed, focusing on Australian approaches. Finally, the discussion focuses on the key issue of how to access adhesive bond structural integrity, especially in relation to the through-life management of repairs. View chapter Purchase book Read full chapter URL: Polymer Matrix Composites: Applications John Tomblin. Cindy Ashforth, in Comprehensive Composite Materials II, 2018 3.9.4 Conclusions and Recommendations 3.9.4.1 Critical Bonded Repair Processing Parameters Critical processing parameters were identified from this research work. CACRC standards cannot be used as a sole document to repair a composite part. The CACRC standards can however be used along with an SRM or other part specific repair document. 3.9.4.

3 Bonded Repair Variability Research work showed variability in the repair residual strength results between depots and mechanics and underscored that repair technician experience alone is not a predictor of repair performance and that some of the process deviations may have been avoided with more stringent quality control oversight. 3.9.4.4 Repair Process Development, Substantiation, and Knowledge Transfer (Records Keeping) Results of the study also demonstrate the importance of repair process development, substantiation and proper execution. Process substantiation should include understanding of the critical process steps and parameters affecting the repair performance and the consequences of bad process implementation. The use of adequate processes specific to the materials used is key to the structural integrity of the repaired part. Caution should be exercised when applying results from one material system to the next. This should be used to demonstrate that the substrate will yield durable bonds in service, and must be conducted in the most aggressive environments the structure will be subjected to. Knowledge transfer in the form of training, validated repair instructions and repair records and documentation is an integral part in ensuring repair process repeatability, stability and thus structural integrity of the repaired component. Process documentation is necessary to ensure strict adherence to the process. QA oversight is strongly advocated. 3.9.4.5 Repair Curing Process Simulation The simulation of cure process for bonded repairs can be used for process development, to understand the evolution of cure as well as the development of residual stresses. For large repair areas on complex structures with multiple components, this can be used to identify the optimal layout for heat blankets and thermocouples. 3.9.4.

6 Workforce Education and Training The study demonstrates the importance of workforce education and training for the proper execution of bonded repairs to composite substrates. Part specific training of the composite repair workforce, taking into account the process learning curve, is strongly advocated. At this point, due to the potential for understrength bonded repairs, and limitations in inspection methods, repair sizes should be limited such that the repair failure will not cause the aircraft to lose its capability for continued safe flight and landing. View chapter Purchase book Read full chapter URL: Surface Treatment and Repair Bonding Andrew N. Rider,. James J. Mazza, in Aircraft Sustainment and Repair, 2018 1.4 Standards and Environments for Adhesive Bonding The facilities, environment, conditions, skills and techniques available for adhesive bonding vary widely. However, it must be emphasised that the quality and long-term performance of an adhesive bond relies on attention to standards and the skill of the technician, together with controls over processes and procedures for all bonding situations. 1.4.1 Bond Integrity and Standards Adhesively bonded components are manufactured, and bonded repairs are conducted, without the benefit of a comprehensive set of effective nondestructive process control tests or techniques to fully assess the through-life integrity of the bonded product. Standard nondestructive inspection (NDI) techniques may be able to detect physical defects leading to voids or airgaps in bondlines, but they cannot detect weak bonds or bonds that may potentially weaken in service. In the meantime, the quality and integrity of the bonded component will rely on a fully qualified bonding procedure, together with the assurance that the process was carried out correctly. Facilities located adjacent to operational airbases or in industrial environments need to have concern for the effect of hydrocarbon contamination.

Facilities in tropical locations need special consideration for the effect of heat and high humidity. Factory manufacture uses specialised facilities and staff. The facilities will include vapour degreasing or alkaline cleaning, etching tanks, anodising tanks, jigs, autoclaves and appropriate environmental controls. Adhesives will be stored in freezers, and monitoring procedures will be in place. There is a well-trained workforce with skills maintained through production volumes, and highly developed inspection procedures are available. At the other extreme, field repairs are generally conducted with relatively unsophisticated facilities, minimal surface treatments, vacuum bag or reacted force pressurisation and little or no environmental control. The requirement for environmental controls, the attention to bonding procedure detail and the need for staff training and supervision are of particular concern. If the use of training measures can be combined with regular monitoring, then any deviation in quality of repairs or bonding operations being undertaken can be identified. Depot-level repairs are conducted with facilities and staff skills that vary considerably. Some depots have almost factory-level facilities and high level of staff skill. Other depots are capable of only low-level bonded repairs and are little removed from a field repair capability. Laboratory experiments are designed to establish knowledge and principles. It is easy to overlook important detail from factory or field experience since most laboratories are held to close environmental tolerances and do not resemble the workshop environment. 1.4.3 Constraints for On-Aircraft Repairs On-aircraft repairs impose additional constraints on processes and procedures. The considerations include: accessibility of the area, limitations in the use of corrosive chemicals, adequacy of environmental controls and constraints on the tools for pressurisation and heating of the bond during cure.

Safety, health and environmental issues are more demanding for on-aircraft bonding since it is harder to control, contain and clean-up hazardous chemicals. Constraints on the use of electrical power on fuelled aircraft, or those with inadequately purged fuel tanks, can restrict the range of treatment and bonding methods available. The surrounding aircraft structure imposes constraints on the choice of surface preparation, heating arrangements and pressurisation tools. View chapter Purchase book Read full chapter URL: Polymer Matrix Composites: Applications Cindy Ashforth, Larry Ilcewicz, in Comprehensive Composite Materials II, 2018 3.1.3.3 Other MOC Publications In addition to AC 20-107B, the FAA has published numerous other MOC documents related to composites. The applicant is required to consider possible damage scenarios when evaluating accidental damage that could result in catastrophic failure. One of these damage scenarios the applicant should assess is accidental damage caused by HEWABI events. HEWABI events (e.g., impacts by service vehicles) are impacts that are spread over a large area and convey sufficient energy to cause potentially catastrophic structural damage. While the damage caused by a HEWABI event is typically readily visible in metallic structure, such damage may leave little or no external indications in composite structure. Bonded repair of critical structure must first be constrained to the sizes allowed by substantiating design data. Source documents, such as a structural repair manual, may define repair size limitations based on the limits of the substantiating design data generated by the DAH for repair purposes. This policy informs ACO engineers and designees that due to inspection limitations, bonded repair must be further limited to a maximum size whereby limit load residual strength can be demonstrated with a complete or partial failure of the bond within the repair or base structure arresting design features.

This policy is not intended for minor repairs. 3.1.3.3.3 PS-ACE100-2-18-1999 “Policy on Acceptability of Temperature Differential between Wet Glass Transition Temperature ( T gwet ) and Maximum Operating Temperature (MOT) for Epoxy Matrix Composite Structure” This policy is for general aviation aircraft, but can be applied to other products. One key topic in this policy statement relates to the glass transition temperature. The FAA sponsors research on composite materials to evaluate new technologies and ensure appropriate standards are set. FAA research is published through the William J. Hughes Technical Center Library, at. These reports often provide valuable background information that supports published guidance or training. In addition to FAA guidance, numerous industry groups publish useful documentation on best practices and some material data. The FAA is the primary funding agent and provides leadership for CMH-17. CMH-17 is a volunteer organization that creates, publishes and maintains proven, reliable engineering information and standards, subjected to thorough technical review, to support the development and use of composite materials and structures. CMH-17 provides useful guidelines for the characterization of composite materials used in structural applications with some emphasis on aerospace needs. The data documented in CMH-17 provide a statistical basis in material properties that are most useful in controlling stable materials and processes and providing basic design properties. The charter of the CACRC is to develop and improve maintenance, inspection and repair of commercial aircraft composite structure and components. They publish documents on practices such as machining of composite materials and heat application for thermosetting resin curing, as well as material specifications and training recommendations. ASTM develops and maintains test standards for composite materials. Committee D30 often meets jointly with CMH-17.