The document describes the proposed layout of the On Instrument Wavefront Sensor (OIWFS) components that will be mounted inside the GMT Instrument Feed System (GMTIFS) on the Giant Magellan Telescope (GMT). The OIWFS includes channels for the deformable mirror, truth path, tip/tilt sensing, integrated optic segment piston sensing, and focus sensing. All optics will be mounted on a single optical bench inside GMTIFS and maintained at a temperature of 70K. The layout must fit all components in a tight space around the deformable mirror and withstand stresses from cooling from 300K to 70K without degrading image quality or sensor performance.
Caterpillar Cat CS-531C Vibratory Compactor (Prefix 9RN) Service Repair Manua...oi9rsiik1m5
This document provides instructions for removing and installing inlet and exhaust valves, valve guides, and valve seat inserts on a Caterpillar 3116 engine. The procedures describe using various specialty tools to compress valve springs, extract components from the cylinder head, and properly seat new parts. Technicians are directed to other documents for specifications on reusable parts and salvage guidelines. The document is from a Caterpillar service manual and aims to correctly guide maintenance and overhaul of engine components.
Caterpillar Cat CS-531C Vibratory Compactor (Prefix 9RN) Service Repair Manua...youyong9098
This document provides instructions for removing and installing inlet and exhaust valves, valve guides, and valve seat inserts on a Caterpillar 3116 engine. The procedures describe using various specialty tools to compress valve springs, extract components from the cylinder head, and properly seat new parts. Technicians are directed to other documents for specifications on reusable parts and salvage guidelines. The document is from a Caterpillar service manual and aims to correctly guide maintenance and overhaul of engine components.
Caterpillar Cat CS-531C Vibratory Compactor (Prefix 9RN) Service Repair Manua...pengdi0699527652
This document provides instructions for removing and installing inlet and exhaust valve seat inserts on a CS-531C vibratory compactor with a 3116 engine. It outlines the required tools and steps to remove the valve guides from the cylinder head, which must be done before removing the valve seat inserts. The procedure describes using a valve seat extractor tool to remove the inserts and notes to keep all parts clean to prevent contamination. Reinstallation involves tapping the new inserts into position in the cylinder head.
Caterpillar Cat CS-531C Vibratory Compactor (Prefix 9RN) Service Repair Manua...mikeme1900
This document provides instructions for removing and installing inlet and exhaust valves, valve guides, and valve seat inserts on a Caterpillar 3116 engine. The procedures describe using various specialty tools to compress valve springs, extract components from the cylinder head, and properly seat new parts. Technicians are directed to other documents for specifications on reusable parts and salvage guidelines. The document is from a Caterpillar service manual and aims to correctly guide maintenance and overhaul of engine components.
Caterpillar Cat CS-531C Vibratory Compactor (Prefix 9RN) Service Repair Manua...qiaolin7012
This document provides instructions for removing and installing inlet and exhaust valves, valve guides, and valve seat inserts on a Caterpillar 3116 engine. The procedures describe using various specialty tools to compress valve springs, extract components from the cylinder head, and properly seat new parts. Technicians are directed to other documents for specifications on reusable parts and salvage guidelines. The document is from a Caterpillar service manual and aims to correctly guide maintenance and overhaul of engine components.
Caterpillar Cat CS-531C Vibratory Compactor (Prefix 9RN) Service Repair Manua...ivsp76367868
This document provides instructions for removing and installing inlet and exhaust valves, valve guides, and valve seat inserts on a Caterpillar 3116 engine. The procedures describe using various specialty tools to compress valve springs, extract components from the cylinder head, and properly seat new parts. Technicians are directed to other documents for specifications on reusable parts and salvage guidelines. The document is from a Caterpillar service manual and aims to correctly guide maintenance and overhaul of engine components.
Caterpillar Cat CS-531C Vibratory Compactor (Prefix 9RN) Service Repair Manua...qrw192677
This document provides instructions for removing and installing inlet and exhaust valves, valve guides, and valve seat inserts on a Caterpillar 3116 engine. The procedures describe using various specialty tools to compress valve springs, extract components from the cylinder head, and properly seat new parts. Technicians are directed to other documents for specifications on reusable parts and salvage guidelines. The steps are illustrated with diagrams and photographs for clarity.
The document describes the proposed layout of the On Instrument Wavefront Sensor (OIWFS) components that will be mounted inside the GMT Instrument Feed System (GMTIFS) on the Giant Magellan Telescope (GMT). The OIWFS includes channels for the deformable mirror, truth path, tip/tilt sensing, integrated optic segment piston sensing, and focus sensing. All optics will be mounted on a single optical bench inside GMTIFS and maintained at a temperature of 70K. The layout must fit all components in a tight space around the deformable mirror and withstand stresses from cooling from 300K to 70K without degrading image quality or sensor performance.
Caterpillar Cat CS-531C Vibratory Compactor (Prefix 9RN) Service Repair Manua...oi9rsiik1m5
This document provides instructions for removing and installing inlet and exhaust valves, valve guides, and valve seat inserts on a Caterpillar 3116 engine. The procedures describe using various specialty tools to compress valve springs, extract components from the cylinder head, and properly seat new parts. Technicians are directed to other documents for specifications on reusable parts and salvage guidelines. The document is from a Caterpillar service manual and aims to correctly guide maintenance and overhaul of engine components.
Caterpillar Cat CS-531C Vibratory Compactor (Prefix 9RN) Service Repair Manua...youyong9098
This document provides instructions for removing and installing inlet and exhaust valves, valve guides, and valve seat inserts on a Caterpillar 3116 engine. The procedures describe using various specialty tools to compress valve springs, extract components from the cylinder head, and properly seat new parts. Technicians are directed to other documents for specifications on reusable parts and salvage guidelines. The document is from a Caterpillar service manual and aims to correctly guide maintenance and overhaul of engine components.
Caterpillar Cat CS-531C Vibratory Compactor (Prefix 9RN) Service Repair Manua...pengdi0699527652
This document provides instructions for removing and installing inlet and exhaust valve seat inserts on a CS-531C vibratory compactor with a 3116 engine. It outlines the required tools and steps to remove the valve guides from the cylinder head, which must be done before removing the valve seat inserts. The procedure describes using a valve seat extractor tool to remove the inserts and notes to keep all parts clean to prevent contamination. Reinstallation involves tapping the new inserts into position in the cylinder head.
Caterpillar Cat CS-531C Vibratory Compactor (Prefix 9RN) Service Repair Manua...mikeme1900
This document provides instructions for removing and installing inlet and exhaust valves, valve guides, and valve seat inserts on a Caterpillar 3116 engine. The procedures describe using various specialty tools to compress valve springs, extract components from the cylinder head, and properly seat new parts. Technicians are directed to other documents for specifications on reusable parts and salvage guidelines. The document is from a Caterpillar service manual and aims to correctly guide maintenance and overhaul of engine components.
Caterpillar Cat CS-531C Vibratory Compactor (Prefix 9RN) Service Repair Manua...qiaolin7012
This document provides instructions for removing and installing inlet and exhaust valves, valve guides, and valve seat inserts on a Caterpillar 3116 engine. The procedures describe using various specialty tools to compress valve springs, extract components from the cylinder head, and properly seat new parts. Technicians are directed to other documents for specifications on reusable parts and salvage guidelines. The document is from a Caterpillar service manual and aims to correctly guide maintenance and overhaul of engine components.
Caterpillar Cat CS-531C Vibratory Compactor (Prefix 9RN) Service Repair Manua...ivsp76367868
This document provides instructions for removing and installing inlet and exhaust valves, valve guides, and valve seat inserts on a Caterpillar 3116 engine. The procedures describe using various specialty tools to compress valve springs, extract components from the cylinder head, and properly seat new parts. Technicians are directed to other documents for specifications on reusable parts and salvage guidelines. The document is from a Caterpillar service manual and aims to correctly guide maintenance and overhaul of engine components.
Caterpillar Cat CS-531C Vibratory Compactor (Prefix 9RN) Service Repair Manua...qrw192677
This document provides instructions for removing and installing inlet and exhaust valves, valve guides, and valve seat inserts on a Caterpillar 3116 engine. The procedures describe using various specialty tools to compress valve springs, extract components from the cylinder head, and properly seat new parts. Technicians are directed to other documents for specifications on reusable parts and salvage guidelines. The steps are illustrated with diagrams and photographs for clarity.
Caterpillar Cat CS-531C Vibratory Compactor (Prefix 9RN) Service Repair Manua...yongpan22957
This document provides instructions for removing and installing inlet and exhaust valves, valve guides, and valve seat inserts on a Caterpillar 3116 engine. The procedures describe using various specialty tools to compress valve springs, extract components from the cylinder head, and properly seat new parts. Technicians are directed to other documents for specifications on reusable parts and salvage guidelines. The document is from a Caterpillar service manual and aims to correctly guide maintenance and overhaul of engine components.
This document outlines procedures for ultrasonic testing using manual ultrasonic methods. It describes qualifications for technicians, responsibilities, calibration of equipment, test procedures, evaluation of indications, reporting requirements, and acceptance criteria. The procedures are intended to inspect base metal and fusion welded butt joints in ferritic steel. Attachments provide details on equipment performance checks, probe characteristics checks, and construction of distance amplitude correction curves. Technique sheets and report formats are listed in the documents section.
This document provides information about electric motors manufactured by FFD, including:
- Single and three phase motors are available in frame sizes 56 to 315 with power outputs from 0.06kW to 200kW.
- Details are given on the construction of the motors, including the housing, end shields, rotor, terminal boxes, fans, cooling, and protection levels.
- Standards that the motors are manufactured according to are listed.
- Performance data is provided for three phase motors in a table including rated speed, power output, efficiency, torque, sound levels, weight and more.
Caterpillar Cat CP-563D, CS-563D Vibratory Compactors (Prefix 2RZ) Service Re...8fisiodkdmm3e
This document provides instructions for removing and installing inlet and exhaust valve guides on CP-563D and CS-563D vibratory compactors powered by 3116 engines. The removal procedure involves using a valve guide driver tool to remove the guides from the cylinder head. The installation procedure involves positioning the guides and using a driver tool and collar to fully install the guides until the collar contacts the cylinder head. Precautions are listed to keep parts clean and refer to other documents for part reuse guidelines.
Caterpillar Cat CP-563D Vibratory Compactors (Prefix 2RZ) Service Repair Manu...jnnfnjsdnnd
This document provides instructions for removing and installing inlet and exhaust valve guides on CP-563D and CS-563D vibratory compactors powered by 3116 engines. The removal procedure involves using a valve guide driver tool to remove the guides from the cylinder head. The installation procedure involves positioning the guides and using a driver tool and collar to fully install the guides until the collar contacts the cylinder head. Precautions are listed to keep parts clean and refer to other documents for part reuse guidelines.
Caterpillar Cat CP-563D, CS-563D Vibratory Compactors (Prefix 2RZ) Service Re...8fusejkdmd9i
This document provides instructions for removing and installing inlet and exhaust valve guides on CP-563D and CS-563D vibratory compactors powered by 3116 engines. The removal procedure involves using a valve guide driver tool to remove the guides from the cylinder head. The installation procedure involves positioning the guides and using a driver tool and collar to fully install the guides until the collar contacts the cylinder head. Proper cleaning and lubrication of parts is emphasized.
Caterpillar Cat CP-563D, CS-563D Vibratory Compactors (Prefix 2RZ) Service Re...9fikslkddmd8u
This document provides instructions for removing and installing inlet and exhaust valve guides on CP-563D and CS-563D vibratory compactors powered by 3116 engines. The removal procedure involves using a valve guide driver tool to remove the guides from the cylinder head. The installation procedure involves positioning the guides and using a driver tool and collar to fully install the guides until the collar contacts the cylinder head. Precautions are listed to keep parts clean and refer to other documents for part reuse guidelines.
Caterpillar Cat CP-563D, CS-563D Vibratory Compactors (Prefix 2RZ) Service Re...9fiisekodkdmd
This document provides instructions for removing and installing inlet and exhaust valve seat inserts on CP-563D and CS-563D vibratory compactors powered by a 3116 engine. The removal procedure involves using a valve seat extractor tool to expand below the edge of the valve seat insert in order to remove it from the cylinder head. The installation procedure refers to lubricating and tapping the valve seat insert into position in the cylinder head.
Caterpillar Cat CP-563D, CS-563D Vibratory Compactors (Prefix 2RZ) Service Re...ufjsekdm8id
This document provides instructions for removing and installing inlet and exhaust valve seat inserts on CP-563D and CS-563D vibratory compactors powered by a 3116 engine. The removal procedure involves using a valve seat extractor tool to expand below the edge of the valve seat insert in order to remove it from the cylinder head. The installation procedure refers to ensuring parts are clean and checking guidelines for determining if valve seats can be reused.
Caterpillar Cat CS-563D Vibratory Compactors (Prefix 2RZ) Service Repair Manu...ujkfdkkmsmd
This document provides instructions for removing and installing inlet and exhaust valve seat inserts on CP-563D and CS-563D vibratory compactors powered by a 3116 engine. The removal procedure involves using a valve seat extractor tool to expand below the edge of the valve seat insert in order to remove it from the cylinder head. The installation procedure refers to ensuring parts are clean and checking guidelines for determining if valve seats can be reused.
Caterpillar Cat CP-563D Vibratory Compactors (Prefix 2RZ) Service Repair Manu...ujkfdkkmsmd
This document provides instructions for removing and installing inlet and exhaust valve seat inserts on CP-563D and CS-563D vibratory compactors powered by a 3116 engine. The removal procedure involves using a valve seat extractor tool to expand below the edge of the valve seat insert in order to remove it from the cylinder head. The installation procedure refers to ensuring parts are clean and checking guidelines for determining if valve seats can be reused.
Caterpillar Cat CS-563D Vibratory Compactors (Prefix 2RZ) Service Repair Manu...jnnfnjsdnnd
This document provides instructions for removing and installing inlet and exhaust valve seat inserts on CP-563D and CS-563D vibratory compactors powered by a 3116 engine. The removal procedure uses a valve seat extractor tool to expand below the edge of the valve seat insert to allow its removal from the cylinder head. The installation procedure does not provide details, but refers the technician to other documents for specifications on the reusability of valve seat components. The summary is intended only to convey the main topic and purpose of the document in 3 sentences or less.
Caterpillar Cat CS-563D Vibratory Compactors (Prefix 2RZ) Service Repair Manu...hdjsjndndnd
This document provides instructions for removing and installing inlet and exhaust valve seat inserts on CP-563D and CS-563D vibratory compactors powered by a 3116 engine. The removal procedure uses a valve seat extractor tool to expand below the edge of the valve seat insert to allow its removal from the cylinder head. The installation procedure does not provide details, but refers the technician to other documents for specifications on the reusability of valve seat components. The summary is intended only to convey the main topic and purpose of the document in 3 sentences or less.
Caterpillar Cat CP-563D Vibratory Compactors (Prefix 2RZ) Service Repair Manu...hdjsjndndnd
This document provides instructions for removing and installing inlet and exhaust valve guides on CP-563D and CS-563D vibratory compactors powered by 3116 engines. The removal procedure involves using a valve guide driver tool to remove the guides from the cylinder head. The installation procedure involves positioning the guides and using a driver tool and collar to fully install the guides until the collar contacts the cylinder head. Precautions are listed to keep parts clean and refer to other documents for part reuse guidelines.
Caterpillar cat 323 f excavator (prefix rgp) service repair manual (rgp00001 ...jfdskekdmme
This document provides instructions for removing and installing electronic unit injectors on a C4.4 engine. The removal procedure involves draining fuel, removing fuel lines and electrical connections, and prying the injector from the cylinder head. Special tools are required. The installation procedure specifies cleaning components, installing new seals, and calibrating injector codes if replacements are used. Precautions are outlined for working on the fuel system to prevent contamination.
Caterpillar cat 323 f ln excavator (prefix rgp) service repair manual (rgp000...fjjskekdmme
This document provides instructions for removing and installing electronic unit injectors on a C4.4 engine. The removal process involves draining fuel, removing fuel lines and electrical connections, and prying the injector from the cylinder head. Installation requires cleaning components, applying new seals and bolts, and calibrating the injector code in the electronic control module. Tools including sockets, pry bars, caps, and torque wrenches are required. Precautions are listed to contain fluids, ensure cleanliness, and only have authorized personnel perform fuel system work.
Mitsubishi ac servos melservo j4 solutions vertical form, fill & seal-die...Dien Ha The
Khoa Học - Kỹ Thuật & Giải Trí: http://phongvan.org
Tài Liệu Khoa Học Kỹ Thuật: http://tailieukythuat.info
Thiết bị Điện Công Nghiệp - Điện Hạ Thế: http://dienhathe.org
Mitsubishi ac servos melservo j4 solutions vertical form, fill & sealDien Ha The
Mitsubishi ,
Catalog Thiết Bị Điện Mitsubishi , Catalog Thiết Bị Điện
Catalog Phụ Kiện Mitsubishi , Catalog Phụ Kiện,
Catalog Mitsubishi , Catalog,
https://www.dienhathe.com,
Chi tiết các sản phẩm khác của Mitsubishi tại https://dienhathe.com
Xem thêm các Catalog khác của Mitsubishi tại https://dienhathe.info
Để nhận báo giá sản phẩm Mitsubishi vui lòng gọi: 0907.764.966
Paut based techniques developed for power industries and refinery in taiwan ...Yung how Wu
Although conventional ultrasonic method is still widely used elsewhere, PAUT technique is applied increasingly for improving the ISI of utility, refinery and as well the emerging wind power in Taiwan. PAUT together with scanner is one of the major advantages to precede conventional UT by enhancing the defect characterization or inspection speed. In this study, special scanners were designed and employed with PAUT for the inspection of composite blades, bolts of wind turbine and anchor bolts of nuclear RPV skirt. Results showed that delamination of composite and fatigue crack of bolt may be detected and sized in more confidence and convenience for in-situ inspections. Moreover, PAUT was also used to characterize carefully the inner crack of pressure vessel for FFS assessment. Crack was found in safe margin and hence remained to operate. In conclusions, PAUT together with manipulator designed for specific purpose may facilitate the applications of PAUT technique widely in ISI of various industrial sectors.
Toyota 5 fbc20 battery forklift service repair manualfhsjejkdmem
This document provides an overview of service procedures for the Toyota Battery Forklift 5FBC13-30 Series. It contains information on vehicle models, frame numbers, how to read the manual, terminology, abbreviations, operational tips, and the circuit tester. The manual covers exterior views, recommended lubricants and capacities, lubrication charts, periodic maintenance schedules, and the periodic replacement of parts and lubricants. Technicians should use this manual for providing quick and correct servicing of the corresponding forklift models.
Electric vehicle and photovoltaic advanced roles in enhancing the financial p...IJECEIAES
Climate change's impact on the planet forced the United Nations and governments to promote green energies and electric transportation. The deployments of photovoltaic (PV) and electric vehicle (EV) systems gained stronger momentum due to their numerous advantages over fossil fuel types. The advantages go beyond sustainability to reach financial support and stability. The work in this paper introduces the hybrid system between PV and EV to support industrial and commercial plants. This paper covers the theoretical framework of the proposed hybrid system including the required equation to complete the cost analysis when PV and EV are present. In addition, the proposed design diagram which sets the priorities and requirements of the system is presented. The proposed approach allows setup to advance their power stability, especially during power outages. The presented information supports researchers and plant owners to complete the necessary analysis while promoting the deployment of clean energy. The result of a case study that represents a dairy milk farmer supports the theoretical works and highlights its advanced benefits to existing plants. The short return on investment of the proposed approach supports the paper's novelty approach for the sustainable electrical system. In addition, the proposed system allows for an isolated power setup without the need for a transmission line which enhances the safety of the electrical network
Caterpillar Cat CS-531C Vibratory Compactor (Prefix 9RN) Service Repair Manua...yongpan22957
This document provides instructions for removing and installing inlet and exhaust valves, valve guides, and valve seat inserts on a Caterpillar 3116 engine. The procedures describe using various specialty tools to compress valve springs, extract components from the cylinder head, and properly seat new parts. Technicians are directed to other documents for specifications on reusable parts and salvage guidelines. The document is from a Caterpillar service manual and aims to correctly guide maintenance and overhaul of engine components.
This document outlines procedures for ultrasonic testing using manual ultrasonic methods. It describes qualifications for technicians, responsibilities, calibration of equipment, test procedures, evaluation of indications, reporting requirements, and acceptance criteria. The procedures are intended to inspect base metal and fusion welded butt joints in ferritic steel. Attachments provide details on equipment performance checks, probe characteristics checks, and construction of distance amplitude correction curves. Technique sheets and report formats are listed in the documents section.
This document provides information about electric motors manufactured by FFD, including:
- Single and three phase motors are available in frame sizes 56 to 315 with power outputs from 0.06kW to 200kW.
- Details are given on the construction of the motors, including the housing, end shields, rotor, terminal boxes, fans, cooling, and protection levels.
- Standards that the motors are manufactured according to are listed.
- Performance data is provided for three phase motors in a table including rated speed, power output, efficiency, torque, sound levels, weight and more.
Caterpillar Cat CP-563D, CS-563D Vibratory Compactors (Prefix 2RZ) Service Re...8fisiodkdmm3e
This document provides instructions for removing and installing inlet and exhaust valve guides on CP-563D and CS-563D vibratory compactors powered by 3116 engines. The removal procedure involves using a valve guide driver tool to remove the guides from the cylinder head. The installation procedure involves positioning the guides and using a driver tool and collar to fully install the guides until the collar contacts the cylinder head. Precautions are listed to keep parts clean and refer to other documents for part reuse guidelines.
Caterpillar Cat CP-563D Vibratory Compactors (Prefix 2RZ) Service Repair Manu...jnnfnjsdnnd
This document provides instructions for removing and installing inlet and exhaust valve guides on CP-563D and CS-563D vibratory compactors powered by 3116 engines. The removal procedure involves using a valve guide driver tool to remove the guides from the cylinder head. The installation procedure involves positioning the guides and using a driver tool and collar to fully install the guides until the collar contacts the cylinder head. Precautions are listed to keep parts clean and refer to other documents for part reuse guidelines.
Caterpillar Cat CP-563D, CS-563D Vibratory Compactors (Prefix 2RZ) Service Re...8fusejkdmd9i
This document provides instructions for removing and installing inlet and exhaust valve guides on CP-563D and CS-563D vibratory compactors powered by 3116 engines. The removal procedure involves using a valve guide driver tool to remove the guides from the cylinder head. The installation procedure involves positioning the guides and using a driver tool and collar to fully install the guides until the collar contacts the cylinder head. Proper cleaning and lubrication of parts is emphasized.
Caterpillar Cat CP-563D, CS-563D Vibratory Compactors (Prefix 2RZ) Service Re...9fikslkddmd8u
This document provides instructions for removing and installing inlet and exhaust valve guides on CP-563D and CS-563D vibratory compactors powered by 3116 engines. The removal procedure involves using a valve guide driver tool to remove the guides from the cylinder head. The installation procedure involves positioning the guides and using a driver tool and collar to fully install the guides until the collar contacts the cylinder head. Precautions are listed to keep parts clean and refer to other documents for part reuse guidelines.
Caterpillar Cat CP-563D, CS-563D Vibratory Compactors (Prefix 2RZ) Service Re...9fiisekodkdmd
This document provides instructions for removing and installing inlet and exhaust valve seat inserts on CP-563D and CS-563D vibratory compactors powered by a 3116 engine. The removal procedure involves using a valve seat extractor tool to expand below the edge of the valve seat insert in order to remove it from the cylinder head. The installation procedure refers to lubricating and tapping the valve seat insert into position in the cylinder head.
Caterpillar Cat CP-563D, CS-563D Vibratory Compactors (Prefix 2RZ) Service Re...ufjsekdm8id
This document provides instructions for removing and installing inlet and exhaust valve seat inserts on CP-563D and CS-563D vibratory compactors powered by a 3116 engine. The removal procedure involves using a valve seat extractor tool to expand below the edge of the valve seat insert in order to remove it from the cylinder head. The installation procedure refers to ensuring parts are clean and checking guidelines for determining if valve seats can be reused.
Caterpillar Cat CS-563D Vibratory Compactors (Prefix 2RZ) Service Repair Manu...ujkfdkkmsmd
This document provides instructions for removing and installing inlet and exhaust valve seat inserts on CP-563D and CS-563D vibratory compactors powered by a 3116 engine. The removal procedure involves using a valve seat extractor tool to expand below the edge of the valve seat insert in order to remove it from the cylinder head. The installation procedure refers to ensuring parts are clean and checking guidelines for determining if valve seats can be reused.
Caterpillar Cat CP-563D Vibratory Compactors (Prefix 2RZ) Service Repair Manu...ujkfdkkmsmd
This document provides instructions for removing and installing inlet and exhaust valve seat inserts on CP-563D and CS-563D vibratory compactors powered by a 3116 engine. The removal procedure involves using a valve seat extractor tool to expand below the edge of the valve seat insert in order to remove it from the cylinder head. The installation procedure refers to ensuring parts are clean and checking guidelines for determining if valve seats can be reused.
Caterpillar Cat CS-563D Vibratory Compactors (Prefix 2RZ) Service Repair Manu...jnnfnjsdnnd
This document provides instructions for removing and installing inlet and exhaust valve seat inserts on CP-563D and CS-563D vibratory compactors powered by a 3116 engine. The removal procedure uses a valve seat extractor tool to expand below the edge of the valve seat insert to allow its removal from the cylinder head. The installation procedure does not provide details, but refers the technician to other documents for specifications on the reusability of valve seat components. The summary is intended only to convey the main topic and purpose of the document in 3 sentences or less.
Caterpillar Cat CS-563D Vibratory Compactors (Prefix 2RZ) Service Repair Manu...hdjsjndndnd
This document provides instructions for removing and installing inlet and exhaust valve seat inserts on CP-563D and CS-563D vibratory compactors powered by a 3116 engine. The removal procedure uses a valve seat extractor tool to expand below the edge of the valve seat insert to allow its removal from the cylinder head. The installation procedure does not provide details, but refers the technician to other documents for specifications on the reusability of valve seat components. The summary is intended only to convey the main topic and purpose of the document in 3 sentences or less.
Caterpillar Cat CP-563D Vibratory Compactors (Prefix 2RZ) Service Repair Manu...hdjsjndndnd
This document provides instructions for removing and installing inlet and exhaust valve guides on CP-563D and CS-563D vibratory compactors powered by 3116 engines. The removal procedure involves using a valve guide driver tool to remove the guides from the cylinder head. The installation procedure involves positioning the guides and using a driver tool and collar to fully install the guides until the collar contacts the cylinder head. Precautions are listed to keep parts clean and refer to other documents for part reuse guidelines.
Caterpillar cat 323 f excavator (prefix rgp) service repair manual (rgp00001 ...jfdskekdmme
This document provides instructions for removing and installing electronic unit injectors on a C4.4 engine. The removal procedure involves draining fuel, removing fuel lines and electrical connections, and prying the injector from the cylinder head. Special tools are required. The installation procedure specifies cleaning components, installing new seals, and calibrating injector codes if replacements are used. Precautions are outlined for working on the fuel system to prevent contamination.
Caterpillar cat 323 f ln excavator (prefix rgp) service repair manual (rgp000...fjjskekdmme
This document provides instructions for removing and installing electronic unit injectors on a C4.4 engine. The removal process involves draining fuel, removing fuel lines and electrical connections, and prying the injector from the cylinder head. Installation requires cleaning components, applying new seals and bolts, and calibrating the injector code in the electronic control module. Tools including sockets, pry bars, caps, and torque wrenches are required. Precautions are listed to contain fluids, ensure cleanliness, and only have authorized personnel perform fuel system work.
Mitsubishi ac servos melservo j4 solutions vertical form, fill & seal-die...Dien Ha The
Khoa Học - Kỹ Thuật & Giải Trí: http://phongvan.org
Tài Liệu Khoa Học Kỹ Thuật: http://tailieukythuat.info
Thiết bị Điện Công Nghiệp - Điện Hạ Thế: http://dienhathe.org
Mitsubishi ac servos melservo j4 solutions vertical form, fill & sealDien Ha The
Mitsubishi ,
Catalog Thiết Bị Điện Mitsubishi , Catalog Thiết Bị Điện
Catalog Phụ Kiện Mitsubishi , Catalog Phụ Kiện,
Catalog Mitsubishi , Catalog,
https://www.dienhathe.com,
Chi tiết các sản phẩm khác của Mitsubishi tại https://dienhathe.com
Xem thêm các Catalog khác của Mitsubishi tại https://dienhathe.info
Để nhận báo giá sản phẩm Mitsubishi vui lòng gọi: 0907.764.966
Paut based techniques developed for power industries and refinery in taiwan ...Yung how Wu
Although conventional ultrasonic method is still widely used elsewhere, PAUT technique is applied increasingly for improving the ISI of utility, refinery and as well the emerging wind power in Taiwan. PAUT together with scanner is one of the major advantages to precede conventional UT by enhancing the defect characterization or inspection speed. In this study, special scanners were designed and employed with PAUT for the inspection of composite blades, bolts of wind turbine and anchor bolts of nuclear RPV skirt. Results showed that delamination of composite and fatigue crack of bolt may be detected and sized in more confidence and convenience for in-situ inspections. Moreover, PAUT was also used to characterize carefully the inner crack of pressure vessel for FFS assessment. Crack was found in safe margin and hence remained to operate. In conclusions, PAUT together with manipulator designed for specific purpose may facilitate the applications of PAUT technique widely in ISI of various industrial sectors.
Toyota 5 fbc20 battery forklift service repair manualfhsjejkdmem
This document provides an overview of service procedures for the Toyota Battery Forklift 5FBC13-30 Series. It contains information on vehicle models, frame numbers, how to read the manual, terminology, abbreviations, operational tips, and the circuit tester. The manual covers exterior views, recommended lubricants and capacities, lubrication charts, periodic maintenance schedules, and the periodic replacement of parts and lubricants. Technicians should use this manual for providing quick and correct servicing of the corresponding forklift models.
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1. CFMI-TP-NT.11 NOVEMBER 30, 1980
REVISED NOVEMBER 30, 2011
NON-DESTRUCTIVE
TEST MANUAL
PART 7-BORESCOPE INSPECTION
2.
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5. CONTENTS
Part 7
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PART 7 - BORESCOPE INSPECTION
TABLE OF CONTENTS
Section Page
72-00-00 Borescope Inspection ....................................... 1
R 72-21-00 Borescope Inspection of Low Pressure Compressor ............ 1
72-31-00 Borescope Inspection of High Pressure Compressor ........... 1
72-42-00 Borescope Inspection of Combustion Section ................. l
72-51-00 Borescope Inspection of High Pressure Turbine Nozzle ....... l
72-52-00 Borescope Inspection of High Pressure Turbine Blades ....... l
72-54-00 Borescope Inspection of Low Pressure Turbine ............... 1
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BORESCOPE INSPECTION
1. General.
A. This procedure describes the type of borescope equipment found to be
acceptable for inspection of the CFM56 turbofan engine.
B. The borescope is a precision monocular periscope instrument especially
designed for the inspection of the inside of turbofan engines through
small diameter access holes. The borescope provides a system of
visually inspecting and taking photographs of selected areas inside the
engine. A television camera and viewing screen may be used instead of
visual examination through the monocular viewer and a television tape
recorder may be used in lieu of the photographic method of making a
record. The CFM56 engine has been designed with a substantial number of
access holes for viewing critical areas inside the engine.
C. This procedure includes instructions for checking the resolution of
borescopes and fiberscopes.
2. Safety.
The following WARNINGS apply to using borescope equipment.
WARNING: DO NOT EXPOSE YOUR EYES TO THE FULL INTENSITY OF THE XENON OR
GAS ARC LIGHT SOURCE.
WARNING: ALL ELECTRICAL EQUIPMENT USED IN INSPECTION SHALL BE PROPERLY
GROUNDED.
WARNING: ALL STANDS AND GROUND EQUIPMENT SHALL HAVE SAFETY LOCKS AND
RAILINGS. DO NOT IMPROVISE WITH LADDERS AND BOARDS.
3. Tools, Equipment and Materials.
NOTE: Equivalent substitutes may be used instead of the following items.
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A. Tools and Equipment.
(1) Special Tools.
Tool No. Description
856A1084G02, Cart, Stator Actuator
G03 or G04
856A1142P03 or P04 Motor, Drive-Core Engine
Rotation (CFM56-2)
856A1310G01 Kit, Borescope Guide - HP
Turbine
856A1351P01 Guide Tube, HPT Shroud
856A1320P04, P05, P06 Borescope Set, Rigid
P07
856A1321P05, P06 Fiberscope Set
856A1324P01 (ALT) Borescope, Videoprobe -
Flexible
856A1322P02, P04, P08, Borescope, Light Source Set
P09, P11
856A1323G01 Borescope Resolution Monitor
856A1488P01 or P02 Motor Drive - Core Engine
Rotation (CFM56-5)
856A2002P01, P02, P03 Motor Drive - Core Engine
or P04 Rotation (CFM56-3)
856A1815G04, G05, G06 Motor Drive-Core Engine
Rotation (CFM56-7B)
NOTE: Other borescope systems using either fiber light or distal
lamps for illumination and a rigid lens optical path may be
considered acceptable for inspection of the CFM56 turbofan
engine if they meet the design specifications of CFMI
Specification M50TF3276-S1.
R
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(2) Standard Tools.
Description Manufacturer
35 mm Camera Local Purchase
Video Monitor Local Purchase
B. Rigid Borescope Set, 856A1320, and Light Source Set, 856A1322. See
figure 1.
(1) This borescope set consists of the following:
(a) Light source - 110 VAC 60 Hz, 220 VAC 50 Hz, or 110 VAC 400
Hz.
(b) Four rigid probes. See figure 2.
(c) Two fiber light bundles.
(d) Long right angle extension.
(e) 40-60 degree eyepiece extension.
(f) Magnification adapter - 2:1 magnification at 2 in. (50,8 mm).
(g) 35 mm camera adapter.
(h) Television camera adapter.
NOTE: The 35 mm camera and television camera adapters are
optional equipment and may be obtained from the
borescope vendor.
(2) Preparation for use.
(a) The rigid borescope set, except for the light source, is
stored in a carrying case and must be assembled prior to use.
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CAUTION: BEFORE CONNECTING THE POWER SUPPLY TO A 110 VAC 60 HZ
POWER SOURCE, BE SURE THE ON-OFF SWITCH IS IN THE OFF
POSITION AND LIGHT INTENSITY CONTROL IS SET TO MINIMUM.
ENSURE PROJECTOR AND POWER SUPPLY ARE PROPERLY GROUNDED.
(b) Select desired probe. Connect the fiber bundle to the probe
and to the light projector. Connect the light projector
electrical cable to a grounded power source.
(c) When the magnification adapter is required, attach the adapter
to the eyepiece at the selected probe. When used with probe 1
the probe must be focused prior to attaching the magnification
adapter.
(d) If photographic record is desired, attach the 35 mm camera on
the optional adapter. Attach the camera and adapter to the
eyepiece of the selected probe.
(e) When using the optional television camera adapter, attach the
C-mount to the TV camera adapter and connect the camera
assembly (vidicon and low light intensifier) to the C-mount.
Connect the TV camera electrical cable to the camera and
camera control unit. Attach the TV camera adapter to the
eyepiece of the probe.
(f) Attach the offset eyepiece to the probe eyepiece as required
if viewing access is limited.
(3) Operating information for the use of the rigid borescope set is as
follows:
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(a) Probe 1 is primarily used for defect assessment of the
combustion chamber and high pressure turbine (HPT) nozzle.
This probe contains a variable focus adjustment in the form of
a knurled ring between the eyepiece and the fiber light bundle
disconnect fitting. This is the high magnification probe and
can be used to define or access most defects in the combustion
chamber or HPT nozzle. For photo recording purposes a visually
sharp focus should be obtained prior to coupling of the camera
and adapter to the borescope. Fine adjustments may then be
accomplished through adjustment of the camera adapter. This
probe will require more exposure time than the other probes
due to increased focal length and therefore less light
transmission. The depth of field and field of view are
decreased because of the magnification provided in the probe
optics.
(b) Probe 2 is a general purpose 90 degree probe and is primarily
used for general inspection of the engine. Probe 2 can be used
in all borescope ports of the engine.
(c) Probe 3 is a fore-oblique angle probe primarily required for
the high pressure compressor (HPC) blade platforms and
airfoils.
(d) Probe 4 is a retro-angle probe primarily required for blade
tips and other liner surfaces and shrouds.
(e) Probes 2, 3 and 4 can have fixed or adjustable focus lenses.
1 For close-up inspection, less than 0.25 in. (6,4 mm) away
from the probe optics window, the magnification adapter
should be utilized. The magnification adapter provides
variable focus as well as magnification. The magnification
of 2 to 1 is only obtained at 2.0 in. (50,8 mm) from optics
to object distance. The magnification factor decreases for
object distances greater than 2.0 in. (50,8 mm); object to
optic spacing.
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2 For objects less than 2.0 in. (50,8 mm) from the probe lens
window, adjust the magnification adapter to bring the
object clearly into focus. Only fine adjustments are
required on the camera adapter. Use of the magnification
adapter for photo recording will require more exposure time
for a given probe, than photos taken without its use. The
magnification adapter is not recommended for use with probe
1 during photo recording.
(f) Light projection provides the light source for the fiber
bundle probes. Place the power unit switch to ON. The red
indicator light should glow. Adjust the intensity of the light
source to provide the required illumination after the probe is
inserted into the engine port.
(g) Two light sources are built into the power unit. The 150-watt
lamp is used for visual inspection of objects close to the
distal end of the probe. The 1000-watt high intensity lamp is
used for photography as well as visual inspection of
combustors and HPT nozzle vanes.
NOTE: The photo arc light circuit contains a thermal delay
cutout that prevents the light from being turned ON if
light projector is too hot.
C. Fiberscope Set, 856A1321 and Borescope Guide Tube, 856A1310. See figure
3.
(1) The flexible fiber optic system has an articulated distal tip. The
light for viewing is conducted from the projector to the probe
through an integrally attached fiber light bundle. The distal end
can be angulated over a range of 180 degrees of arc vertically at
the bending point. The system contains the following features.
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(a) Optical system specifications.
1 Distal focusing - adjustment at eyepiece.
2 Depth of field - 6 mm to 100 mm.
3 Angle of view - 90 degrees.
4 Diopter adjustment - minus 6D to plus 4D.
5 Magnification - 1:1 at 25 mm.
6 Objective focal distance - 2.13 mm.
7 Lens speed - f 2.8.
8 Image bundle size - 1.7 mm square.
9 Single fiber image guide - 17 microns.
10 Illumination - inherent light guide with 5 feet extension.
(b) Distal tip specifications.
1 Size - 6 mm dia x 20 mm long.
2 Side view - 90 degrees to centerline of probe.
(c) Bending section (articulated tip) specifications.
1 Angulation controllable at eyepiece 180° (90° up - 90°
down).
2 Minimum bend radius - one in. (25,4 mm).
3 Length of bending section - 50 mm.
(d) Flexible cable-probe specifications.
1 Working length - 70 in. (1800 mm).
2 Outside diameter over working length - 6 mm.
3 Covering on cable - stainless steel braid.
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4 Temperature range - 0°F to 200°F (- 18°C to 93°C)
continuous operation.
5 Light source - the fiberscope integral light bundle will
attach to the Light Source Set, 856A1322.
(2) Preparation for use.
CAUTION: MOST FLEXIBLE FIBER OPTICAL SYSTEMS MAY BE DAMAGED QUITE
EASILY IN VERY COLD WEATHER. FORCED BENDING OR WARMING
CAN DAMAGE THE FIBER BUNDLE. SLOWLY AND GENTLY
ARTICULATE TIP IN COLD WEATHER. AFTER EXPOSURE TO
EXTREME COLD, WARM INSTRUMENT TO ROOM TEMPERATURE VERY
GRADUALLY.
(a) Connect the fiber light bundle from probe to light projector.
Connect light projector to power source. Be sure that the
power supply and power outlet is grounded.
(b) Install optional 35 mm camera adapter or TV camera adapter as
required.
(c) Turn light projector ON.
(3) Care and use of flexible fiberscope.
The fiberscope (flexible borescope) is a precision optical
instrument utilizing bunches of finely spun glass fibers to carry
light and images. Although guarded by a stainless steel sheath for
protection, reasonable care must be used to prevent damage and
assure long service life.
(a) Read the instruction manual completely before using.
(b) Check the scope for damage before using. A slightly damaged
scope, such as partial loss of tip control can result in
getting the scope hung up and finally resulting in severe
damage.
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(c) Although they are safer than ones with distal tip bulbs,
scopes are not explosion proof. They ~ should not be used
where highly volatile gases or explosive dust could reach the
hot projection lamp of the external light source.
(d) Do not subject the scope to intense X-ray or gamma radiation.
Glass fibers are not nonbrowning and will turn yellow, amber,
or brown if exposed to radiation.
(e) When cleaning the scope, use lens tissue only on glass
surfaces. Scopes should be kept clean at all times.
(f) Avoid extreme temperatures. Use between 0°F to 200°F (- 18°C
to 93°C). Do not insert into a hot engine; heat will cause
bubbling of epoxy at the tip. This will cause loss of focus
and damage to the lens sheath seals. Low temperatures will
make the sheath brittle and tend to crack.
(g) Hold tip or adjacent hardware when removing scope to prevent
dropping to floor which will avoid hard shocks.
(h) Use control knob to maneuver bending section of tip. Never
bend or twist tip by hand; damage will result.
(i) Do not force the control knob. Use the knob to guide the tip
through curves, using tip touch to insert and also to remove
or reposition the fiber probe. Do not merely push through
guide tubes nor yank out when removing.
(j) Return angle control knob to neutral position before
withdrawing scope from engine or guide tube.
(k) Bending section is flexible in one plane only. This plane must
be oriented to the curves in the guide tube. The plane can be
established by the articulation control. Do not bend in a 90
degree plane to the tip articulation plane.
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(l) Do not insert the scope too far into the engine. If engine
rotor is rotated the tip might be cut.
(m) Use plastic guide tube, 856A1310, to guide flexible fiber
scope when inspecting the leading edge of the HPT blades.
(n) When storing the scope, use care when closing the protective
case. If the fiber bundles are closed within the case edges,
damage will result. Never leave scope laying on floor where it
might be stepped on or run over.
4. Procedure Before Borescope Inspection.
A. Support Equipment.
Inspection of the HP rotor blades (compressor and turbine) requires
rotation of the core engine rotor a complete 360 degrees for each stage
of blades to be inspected. This can be done manually or with the aid of
a pneumatically powered motor. A special pad is provided for this
purpose.
(1) Manual rotation.
The core engine rotor is actuated by means of a drive adapter with
a long breaker bar installed into the drive pad.
(2) Pneumatic rotation.
The pneumatic turning device provides smooth even speed turning of
the core rotor. This is an advantage to the inspector viewing the
blades. Reversible control as well as speed control are provided
and the need for an additional mechanic to turn the rotor is
eliminated. A 360 degree protractor is integral with the device.
The pneumatic pressure required is satisfied by a shop or line air
supply.
(3) Installation and operation.
The installation and operation of the MOTOR, DRIVE CORE ENGINE
ROTATION are given in the maintenance manual relative to each
engine model:
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Engine Tool number
CFM56-2/A/B/C 856A1142
CFM56-3 856A2002
CFM56-5/A/B/C 856A1488
CFM56-7B 856A1815
B. Zero CFM56-7B Index Position.
The zero index position is the referenced position for borescope
inspection. Thus, you can put the No. 1 blade in position before you
turn each stage of blades.
(1) Low pressure rotor zero index position. See figure 4.
(a) Locate No. 1 fan blade which is identified by a circular hole
in the spinner rear cone adjacent to the No. 1 blade.
(b) Align the leading edge of the No. 1 fan blade with the T12
temperature sensor located in the fan frame at 1: 30 o'clock,
aft looking forward.
(c) The low pressure rotor is now in the zero referenced position
for inspection.
(2) Core rotor zero index position. See figure 5.
(a) Prepare for borescope inspection.
(b) Remove the borescope port ( S4) plug between the 4 and 5
o'clock position on the compressor case.
(c) Put the rigid borescope probe with the 90° right angle viewer
and a 60° field of vision in the borescope port, and lock aft
to the stage 4 blade platform.
(d) While you lock in the borescope, turn the core engine rotor
clockwise (forward looking aft).
(e) Turn the rotor until you can see the locking lug of the first
blade slot.
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(f) Continue to turn the rotor until you see the second locking
lug. The second locking lug is 2 blades past the first locking
lug.
(g) Align the leading edge of the first blade past the second
locking lug with the leading edge of the nearest stage 4 vane.
This is the zero index point and blade number 1 for inspection
of all stages of the compressor rotor.
5. Inspection Techniques.
A. Description.
(1) The CFM56 booster has one borescope port in the stage 3 (a second
port is provided in stage 4 for CFM56-5B/5C only) for inspection.
The core rotor blade airfoils and root/platform are completely
inspectable from the gas path aspect. Borescope inspection ports
are located in each HPC stator assembly. The low pressure turbine
(LPT) has borescope inspection ports in all stator stages. The HPT
blade leading edges are inspected using the fiberscope via the
igniter ports. The relative closeness of the borescope inspection
ports to the rotor blades results in high magnification viewing
using any of the specified probes (CFMI Specification M50TF3276-
S1).
(2) The primary probe recommended for CFM56 inspection is probe 2, wide
angle fixed field, 90 degree angle of view with 60 to 65 degree
field of view. The magnification of this probe is 1 x 1 at 2 in.
(25,4 x 25,4 at 51 mm). Therefore, objects viewed closer than 2
in. (51 mm) from the distal lens are magnified. Those objects
viewed further away than 2 in. (51 mm) are decreased in image
size, relative to actual dimensions of the object. The
magnification is variable relative to blade position due to the
changing viewing distances as a rotor is turned and the blade
passes the relatively fixed borescope. The probe is turned or
rotated to view the passing blade.
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Along with the varying magnification, the angle of incidence of
the illumination beam changes as the blades pass the fixed viewing
port positions. These views are further varied by probe immersions
into the engine (radially), thus producing/providing a third
variable, the aspect of the object.
(3) Use a borescope probes 2, 3 or 4 change the angle of views as well
as the incidence angle of light beam relative to optic angle of
view. The magnification factor of probes 2, 3 or 4 does not
change, it is 1 x 1 at 2 in. (25,4 x 25,4 at 51 mm).
NOTE: The above factors or variables should be utilized to the
inspectors advantage when attempting to assess suspected
deterioration or defects, e.g.; scratches, cracks, contour
changes, impact results, dents, dirt smears, surface finish
changes, and coloration variables.
(4) Another helpful technique in establishing the type of defect is
through varying the borescope light intensity. Flooding a scratch,
crack, or dirt streak to attempt to establish what the mark or
line really is, gives the inspector the aid of depth. Cracks that
are open do not usually disappear with low to high light levels.
Dirt/carbon/water streaks do not show the depth or shadow
characteristics that cracks exhibit. It should also be noted that
arc light sources such as the GE Marc 300/16 high intensity light
(300 watt) versus the 150 watt quartz iodide or any incandescent
light source tends to give a difference in image color when viewed
through the borescope. The 300 watt arc light gives the closest to
true or actual color of any light source.
(5) In contrast, the nonarc or incandescent light sources give a copper
or bronze hue/coloration to the internal engine parts. Use of the
various probes and variable positioning of the borescope relative
to the suspect defects usually results in defining the suspected
defect, e.g.; a crack or dirt line or water mark, a sharp nick or
smooth dent, loss of metal or coloration change, etc. Having
established the defect or suspected problem, the assessment of the
magnitude of the defect now becomes the challenge.
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B. Resolution Check of Borescope and Fiberscope Using Borescope Resolution
Monitor, 856A1323.
NOTE: If the person performing the testing has corrected vision, then
the appropriate eyewear (eyeglasses, contact lenses, etc.)
should be worn.
(1) Test rigid borescope as follows. See figures 6 and 7.
(a) Turn on lightsource and allow a minimum of 3 minutes warm up
for lamp to reach its' maximum operating range.
CAUTION: NEVER LOOK DIRECTLY INTO THE LIGHT BUNDLE OUTPUT.
(b) Insert male end of light bundle into lightsource. Glance at
female end to assure that adequate light is passing through.
(c) Connect female end of light bundle to male connector on
Borescope Resolution Monitor, 856A1323.
(d) Turn intensity of lightsource to maximum.
(e) Check Borescope Resolution Monitor to assure that resolution
target is illuminated.
(f) Insert borescope into clamping device located on arm of the
Borescope Resolution Monitor, with objective window of
borescope facing resolution target.
CAUTION: DO NOT OVERTIGHTEN THE CLAMPING DEVICE. OVERTIGHTENING
COULD RESULT IN DAMAGE TO THE BORESCOPE. HAND TIGHTENING
IS SUFFICIENT.
(g) Hand tighten borescope in place.
(h) In order to ensure that borescope is positioned correctly, lay
Borescope Resolution Monitor on a flat surface making sure
that the arm with the clamping device is also resting on a
flat surface. The objective window on borescope should be in
line with black pivot bolt of arm.
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(i) Align borescope so resolution target is centered in field of
view. If you peer through borescope and only part of
resolution target is illuminated in your field of view, (i.e.
half of field of view resembles a half moon) borescope is not
serviceable for engine inspection.
NOTE: The resolution target is divided into group numbers and
element numbers. There are 7 groups , with 6 elements to
each group. Group 0, element 1 is located at the lower
right of the target, its' 6 lines are quite visible to
your eye. Group 1 is located on the far right side of
the target and appears smaller than group 0. Group 2 is
located in the center left side of the target, while
group 3 is located in the center right side of the
target. Each group diminishes in size.
(j) For borescopes with a magnification of 1:1 at 2 in. (51 mm),
the 6 individual lines (3 horizontal, 3 vertical) of group 3,
element 4 (11.3 lines per millimeter of resolution) should be
distinguishable. Otherwise, borescope is not serviceable for
engine inspection. See figure 7, sheet 1.
(k) For borescopes with a magnification of 1:1 at 7 in. (178 mm),
the 6 individual lines (3 horizontal, 3 vertical) of group 5,
element 2 (36.0 lines per millimeter of resolution) should be
distinguishable. Otherwise, the borescope is not serviceable
for engine inspection. See figure 7, sheet 2.
NOTE: It may be necessary to adjust the light intensity or the
scope position in order to obtain the best view.
However, if the forementioned group/element cannot be
seen, the scope or light bundle or light source is not
serviceable for engine inspection.
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(2) Test fiberscope as follows. See figures 6 and 7.
(a) Turn lightsource on and allow a minimum of 3 minutes warm up
for lamp to reach its' maximum operating range.
WARNING: NEVER LOOK DIRECTLY INTO THE LIGHT BUNDLE OUTPUT. THIS
COULD RESULT IN INJURY TO PERSONNEL.
(b) Insert male end of light bundle into lightsource. Glance at
female end to assure that adequate light is passing through.
(c) Connect female end of light bundle to male connector on
Borescope Resolution Monitor, 856A1323.
(d) Turn intensity of lightsource to maximum.
(e) Check Borescope Resolution Monitor to assure that resolution
target is illuminated.
(f) Insert fiberscope into clamping device located on arm of the
Borescope Resolution Monitor.
(g) Align objective window of fiberscope with resolution target.
CAUTION: DO NOT OVERTIGHTEN THE CLAMPING DEVICE. OVERTIGHTENING
COULD RESULT IN DAMAGE TO THE FIBERSCOPE. HAND
TIGHTENING IS SUFFICIENT.
(h) Hand tighten fiberscope in place.
NOTE: Due to the nature of the fiberscope, it may be necessary
to use a free hand to assure that the tip of the
objective window remains centered on the resolution
target.
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(i) Check fiberscope with objective window aligned and centered in
field of view. If only part of target is illuminated in field
of view (i.e. half of field of view resembles a half-moon),
fiberscope is defective and is not serviceable for engine
inspection.
NOTE: The resolution target is divided into group numbers and
elements numbers. There are 7 groups, with 6 elements to
each group. Group 0, element 1 is located at the lower
right of the target, its' 6 lines are quite visible to
your eye. Group 1 is located on the far side of the
target and appears to be smaller than group 0. Group 2
is located in the center left side of the target, while
group 3 is located in the center right side of the
target. Each group diminishes in size.
(j) For fiberscopes with 90° direction of view, the 6 individual
lines (3 horizontal, 3 vertical) of group 1, element 4 (2.83
lines per millimeter of resolution) should be distinguishable.
Otherwise, the fiberscope is not serviceable for engine
inspection. See figure 7, sheet 1.
NOTE: It may be necessary to adjust the light intensity or the
scope position in order to obtain the best view.
However, if the forementioned group/element cannot be
seen, the scope or light bundle or light source is not
serviceable for engine inspection.
C. Procedure.
(1) If Polaroid camera equipment and optional camera adapters are
available, it is relatively easy to effect a comparative
measurement.
(a) Position the rotor to obtain the best view of the defect,
relative to assessment of the maintenance manual limit, e.g.;
leading edge impact, tip (distortion) curl, leading edge or
trailing edge distortion, etc. Usually normal (at right angle)
to the defect and centered in the field of view.
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(b) Obtain a Polaroid photo of the defect.
(c) Using a full scale cross section of the engine, for reference,
locate a scale (machinist 6 in. scale marked in 0.010 in.
increments) in the relative axial and circumferential position
outside the HPC case, withdraw the borescope probe with camera
attached.
(d) Hold the borescope probe aligned with the centerline (same
position, axial, angle of look, and circumferential
orientation as the defect photo was obtained) of the borescope
port and obtain a photo of the measurement scale.
(e) By comparative measurement, apply the magnified scale
increments from the photo of the scale to the photo of the
actual defect. These 2 photos should be at the same relative
magnification.
(2) If photographic equipment is not available, the comparative
assessment becomes more difficult; however, the following
procedure has been used successfully.
(a) Position the rotor at the optimum rotation angle to view the
defect.
(b) Use a sample blade (if available) and mark a similar or
depiction of the blade defect. Place this blade in the
relative position of the installed defective blade on the
outside of the engine.
(c) Withdraw the borescope, retaining the axial circumferential
orientation and lock angle relationship and visually assess
the comparison of the actual to marked defect (from the
installed blade to the external sample).
(d) Re-mark or correct the depiction until satisfied that the 2
images compare.
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(e) Measure the marked defect.
NOTE: A straight edge scale can also be used if no blade
samples are available to the inspector.
(3) Borescope temperature limitations.
(a) Figure 8 provides engine cool-down information relative to the
various borescope port locations for use in determining
elapsed time required prior to engine inspection of arrival
aircraft.
(b) The information is either calculated or recorded from test
engine data runs. It is not recommended that (fiber light type
or fiber optic/light flexible) fiberscope inspections be
accomplished at temperatures above 150°F (65,6°C).
CAUTION: REFER TO AIRCRAFT OPERATION MANUAL FOR STARTER DUTY
CYCLE LIMITATIONS PRIOR TO MOTORING OF ENGINE.
(c) To increase the engine cool-down rate after shutdown, motor
engine for a maximum of 2 minutes by utilizing the engine
starter and by carefully adhering to starter duty cycle
limitations. This will reduce the hot section area temperature
sufficiently to allow fiber optics method of inspection at
that time.
NOTE: If engine starter motoring is used it is further
recommended that engine hot section inspections be
accomplished within 20 minutes after the motoring cycles
are completed. Local temperature rise (due to engine
temperature soak-back) may cause local temperatures
sufficient to damage the fiber optic type borescopes.
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Engine Temperature for Borescope Inspection after Engine Shutdown
Following Normal Flight Cycle
Figure 8
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BORESCOPE INSPECTION OF LOW PRESSURE COMPRESSOR
1. Requirements.
A. On Condition Maintenance.
Borescope inspection of the booster section may be required for visual
assessment check as part of the on condition engine maintenance plan.
B. Special Inspection.
Other borescope inspection checks will be required resulting from
engine problems, trend symptoms, or troubleshooting/fault isolation.
The CFM56 Maintenance Manual will call out the engine sections required
to be inspected.
2. Procedure.
The borescope inspection of the booster section is given in the
Maintenance Manual or Aircraft Maintenance Manual relative to each engine
model.
ENGINE REFERENCE
CFM56-2 72-21-00, Fan and Booster Inspection/Check
CFM56-3 TASK 72-00-00-216-008-C00
CFM56-5A TASK 72-21-00-290-001
CFM56-5B TASK 72-21-00-290-003
CFM56-5C TASK 72-21-00-290-801
CFM56-7B TASK 72-00-00-200-803-F00
3. Inspection Criteria.
A. General.
Whenever borescope inspection of the fan rotor is required, the
following defects must be observed and assessed as to the applicable
hardware limits for serviceability. It is recommended that in-limit
defect conditions be documented for determination of subsequent
deterioration rates.
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(1) On Condition (Scheduled Inspection).
(a) Cracks or tears.
(b) Nicks and scratches.
(c) Dents.
(d) Erosion.
(e) Tip curl.
(f) Pits.
(g) Distortion leading or trailing edges.
(h) Missing metal.
(2) Special Inspections.
Specific defects accompany some of the special check requirements.
The following listing relates the special checks to those
additional defects which are prevalent in engines having
experienced a problem requiring special checks.
(a) Fan stall.
(b) Foreign object damage (FOD) and suspected bird injection.
(c) High fan vibs.
4. Documentation of Defects.
A. General.
(1) It is recommended that a record of the inspection be maintained for
each borescope inspection conducted. Sample forms are provided
which include borescope inspection record forms and maps for each
rotor stage. The maps are provided so that any damage within
serviceable limits can be recorded pictorially by blade number and
position on the blade.
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The propagation of the damage can then be pictorially illustrated
during subsequent inspections. The rotor blade maps are oriented
about the zero reference for inspection continuity. The inspection
records and maps will remain with the engine folder until the
damaged parts are repaired or replaced.
(2) Record inspection on inspection record. See figure 1.
B. Mapping Defects.
(1) Record individual blade damage on booster blade maps. See figure 2.
(2) Record damage detected on appropriate fan/booster rotor blade map.
See figures 3 through 7. The blade numbering relative to angular
position applies only when the booster is indexed as defined in
section 72-00-00.
NOTE: When defect/damage maps are used, accomplish the mapping at
the inspection site. Do not rely on memory of the defect to
allow the mapping to be done in an office after the
inspection. Details are lost relative to percent of chord
or span, magnitude of defect, surrounding condition, etc.
C. Photo Recording of Damage.
Whenever photos are made of a defect, a record of the photo should be
made immediately on the spot. If the photo is not recorded relative to
engine serial number, stage, port direction of view, and date, the
correlation of the hardware damage and the photo will be extremely
difficult. Note directly on polaroid photos and record relative to
sequence of photos on 35 mm or negative film.
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R CFM56-2 Stage 2 Booster Rotor Map of Damaged Blades
R Figure 4 (Sheet 1 of 6)
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R CFM56-3 Stage 2 Booster Rotor Map of Damaged Blades
R Figure 4 (Sheet 2 of 6)
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R CFM56-5A Stage 2 Booster Rotor Map of Damaged Blades
R Figure 4 (Sheet 3 of 6)
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R CFM56-5B Stage 2 Booster Rotor Map of Damaged Blades
R Figure 4 (Sheet 4 of 6)
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R CFM56-5C Stage 2 Booster Rotor Map of Damaged Blades
R Figure 4 (Sheet 5 of 6)
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R CFM56-7B Stage 2 Booster Rotor Map of Damaged Blades
R Figure 4 (Sheet 6 of 6)
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R CFM56-2 Stage 3 Booster Rotor Map of Damaged Blades
R Figure 5 (Sheet 1 of 6)
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R CFM56-3 Stage 3 Booster Rotor Map of Damaged Blades
R Figure 5 (Sheet 2 of 6)
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R CFM56-5A Stage 3 Booster Rotor Map of Damaged Blades
R Figure 5 (Sheet 3 of 6)
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R CFM56-5B Stage 3 Booster Rotor Map of Damaged Blades
R Figure 5 (Sheet 4 of 6)
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R CFM56-5C Stage 3 Booster Rotor Map of Damaged Blades
R Figure 5 (Sheet 5 of 6)
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R CFM56-7B Stage 3 Booster Rotor Map of Damaged Blades
R Figure 5 (Sheet 6 of 6)
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R CFM56-2 Stage 4 Booster Rotor Map of Damaged Blades
R Figure 6 (Sheet 1 of 6)
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R CFM56-3 Stage 4 Booster Rotor Map of Damaged Blades
R Figure 6 (Sheet 2 of 6)
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R CFM56-5A Stage 4 Booster Rotor Map of Damaged Blades
R Figure 6 (Sheet 3 of 6)
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R CFM56-5B Stage 4 Booster Rotor Map of Damaged Blades
R Figure 6 (Sheet 4 of 6)
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R CFM56-5C Stage 4 Booster Rotor Map of Damaged Blades
R Figure 6 (Sheet 5 of 6)
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R CFM56-7B Stage 4 Booster Rotor Map of Damaged Blades
R Figure 6 (Sheet 6 of 6)
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R CFM56-5B Stage 5 Booster Rotor Map of Damaged Blades
Figure 7 (Sheet 1 of 2)
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R CFM56-5C Stage 5 Booster Rotor Map of Damaged Blades
Figure 7 (Sheet 2 of 2)
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BORESCOPE INSPECTION OF HIGH PRESSURE COMPRESSOR
1. Requirements.
A. On Condition Maintenance.
Borescope inspection of high pressure compressor (HPC) section may be
required for a visual assessment check as part of the on condition
engine maintenance.
B. Special Inspection.
Other borescope inspection checks will be required resulting from
engine problems, trend symptoms, or troubleshooting/fault isolation.
The CFM56 Maintenance Manual will call out the engine sections required
to be inspected.
2. Procedure.
The borescope inspection of high pressure compressor is given in the
Maintenance Manual or Aircraft Maintenance Manual relative to each engine
model.
ENGINE REFERENCE
CFM56-2 72-31-00, Maintenance Practices
CFM56-3 TASK 72-00-00-216-049-C00
CFM56-5A TASK 72-31-00-290-001
CFM56-5B TASK 72-31-00-290-002
CFM56-5C TASK 72-31-00-290-801
CFM56-7B TASK 72-00-00-200-804
3. Inspection Criteria.
A. General.
Whenever borescope inspection of the HPC is required, the following
defects must be observed and assessed as to the applicable hardware
limits for serviceability. It is recommended that in limit defect
conditions be documented for determination of subsequent deterioration
rates.
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(1) on condition (Scheduled Inspection).
(a) Cracks.
(b) Nicks or scratches.
(c) Dents.
(d) Erosion.
(e) Tip curl.
(f) Pits.
(g) Distortion of leading or trailing edge.
(h) Missing metal.
(i) Dirt.
(2) Special inspections.
Specific defects accompany some of the special check requirements.
The following listing relates the special checks to those
additional defects which are prevalent in engines having
experienced a problem requiring the special check.
(a) Core stall.
(b) Oil fumes detected in cabin air.
(c) Foreign object damage (FOD).
(d) High core vibration.
4. Documentation of Defects.
A. General.
(1) It is recommended that a record of the inspection be maintained for
each borescope inspection conducted. Sample forms are provided
which include borescope inspection record forms and maps for each
rotor stage of the compressor. The maps are provided so that any
damage within serviceable limits can be recorded pictorially by
blade number and position on the blade.
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The propagation of the damage can then be pictorially illustrated
during subsequent inspection. The rotor blade maps are oriented
about the zero reference for inspection continuity. The inspection
records and maps will remain with the engine folder until the
damaged parts are repaired or replaced.
(2) Record inspection on inspection record. See figure 1.
B. Mapping Defects.
(1) Record individual blade damage on HPC blade map. See figure 2.
(2) Record damage detected on the appropriate compressor rotor stage
maps. See figures 3 through 11. The blade numbering relative to
angular position applies only when the high pressure rotor is
indexed as defined in section 72-00-00.
NOTE: When defect/damage maps are used, accomplish the mapping at
the inspection site. Do not rely on memory of the defect to
allow the mapping to be done in an office after the
inspection. Details are lost relative to percent of chord
or span, magnitude of defect, surrounding condition, etc.
C. Photo Recording of Damage.
Whenever photos are made of a defect, a record of the photo should be
made immediately on the spot. If the photo is not recorded relative to
engine serial number, stage, port direction of view, and date, the
correlation of the hardware damage and the photo will be extremely
difficult. Note directly on polaroid photos and record relative to
sequence of photos on 35 mm or negative film.
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BORESCOPE INSPECTION OF COMBUSTION SECTION
1. Requirements.
A. On Condition.
Borescope inspection of the combustion section may be required for a
visual assessment check as part of the on condition engine maintenance
plan.
B. Special Inspections.
Other borescope inspection checks will be required resulting from
engine problems, trend symptoms, or troubleshooting/fault isolation.
The CFM56 Maintenance Manual will call out the engine sections required
to be inspected.
2. Procedure.
The borescope inspection of combustion chamber is given in the Maintenance
Manual or Aircraft Maintenance Manual relative to each engine model.
ENGINE REFERENCE
CFM56-2 72-42-00, Maintenance Practices
CFM56-3 TASK 72-00-00-216-023-C00
CFM56-5A TASK 72-42-00-290-001
CFM56-5B TASK 72-42-00-290-041
CFM56-5C TASK 72-42-00-290-802
CFM56-7B TASK 72-00-00-200-805-F00 (SAC)
TASK 72-00-00-200-816-F00 (DAC)
3. Inspection Criteria.
A. General.
Whenever borescope inspection of the combustion section is required,
the following defects must be observed and assessed as to the
applicable hardware limits for serviceability.
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B. On Condition (Scheduled Maintenance).
(1) Discoloration.
(a) Normal aging of the combustion chamber components will show a
wide range of color changes. Use of arc Xenon or incandescent
light sources for borescope illumination will result in viewed
coloration differences. The closest color to true daylight
viewing is gained from the use of a Marc 300/16 type hi-
intensity lamp light projector. This light is close to white
light.
(b) Use of incandescent filament lamps tend to project a yellowish
color on the viewed hardware. Incandescent lamps usually do
not have sufficient light levels to view the distant areas of
the combustion chamber liners.
(c) Use of the Xenon arc lamp with the distal light type
borescopes tend to cast a bluish coloration on the viewed
hardware. Carbon streaks have been misinterpreted as cracks
and carbon deposits have bean misinterpreted as holes or burn
through.
(2) Inner liner.
The aft panel of the inner liner is susceptable to distortion and
cracking, the first evidence of this is discoloration in a round
spot approximately 1.0 in. (25 mm) dia., which is followed by
distortion and cracking. This usually occurs uniformly around the
aft liner in approximately 20 places.
C. Special Inspections.
(1) Overtemperature operation.
(a) High exhaust gas temperature (EGT) increase in EGT trend.
(b) Overtemperature during takeoff or cruise.
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(2) Impact damage observed on high pressure turbine (HPT) rotor blades.
Inspect the combustion chamber in accordance with the standard
condition check. Limits and area all apply as in an on condition
check.
4. Documentation of Defects.
A. General.
(1) It is recommended that a record of the inspection be maintained for
each borescope inspection conducted. Sample forms are provided
which include borescope inspection record forms and maps for the
combustion section. The maps are provided so that any damage
within serviceable limits can be recorded pictorially for location
of damaged area. The propagation of the damage can then be
pictorially illustrated during subsequent inspections. The
inspection records and maps will remain with the engine folder
until the damaged parts are repaired or replaced.
(2) Record inspection on single annular combustion chamber (SAC)
inspection record. See figure 1.
(3) Record inspection on dual annular combustion chamber (DAC)
inspection record. See figure 2.
B. Mapping Defects.
(1) Record damage on maps.
- SAC : see figures 3 through 8.
- DAC : see figures 9 through 15.
NOTE: When defect/damage maps are used, accomplish the mapping at
the inspection site. Do not rely on memory of the defect to
allow the mapping to be done in an office after the
inspection. Details are lost relative to magnitude of
defect, surrounding condition, etc.
R
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C. Photo Recording of Damage.
Whenever photos are made of a defect, a record of the photo should be
made immediately on the spot. If the photo is not recorded relative to
engine serial number, stage, port direction of view, and date, the
correlation of the hardware damage and the photo will be extremely
difficult. Note directly on polaroid photos and record relative to
sequence of photos on 35 mm or negative film.
101. 72-51-00
Part 7
Page 1
May 31/99
BORESCOPE INSPECTION OF HIGH PRESSURE TURBINE NOZZLE ASSEMBLY
1. Requirements.
A. On Condition.
Borescope inspection of the high pressure turbine (HPT) may be required
for a visual assessment check as part of the on condition engine
maintenance plan.
B. Special Inspections.
Other borescope inspection checks will be required resulting from
engine problems trend symptoms, or troubleshooting/fault isolation. The
CFM56 Maintenance Manual will call out the engine sections required to
be inspected.
2. Procedure.
The borescope inspection of high pressure turbine nozzle assembly is given
in the Maintenance Manual or Aircraft Maintenance Manual relative to each
engine model.
ENGINE REFERENCE
CFM56-2 72-51-00, Maintenance Practices
CFM56-3 TASK 72-00-00-216-023-C00
CFM56-5A TASK 72-51-00-290-002
CFM56-5B TASK 72-51-00-290-004
CFM56-5C TASK 72-51-00-290-801
CFM56-7B TASK 72-00-00-200-806-F00
3. Inspection Criteria.
A. General.
Whenever borescope inspection of the HPT nozzle assembly is required,
observed defects must be assessed as to the applicable hardware limits
for serviceability.
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B. On Condition (Scheduled Maintenance).
(1) Discoloration.
(2) Leading edge damage.
(a) Cracks.
(b) Burns.
(c) Blocked cooling air passages.
(3) Airfoil concave surface.
Cracks.
(4) Airfoil convex surface.
Cracks.
(5) Airfoil trailing edge.
(a) Cracks.
(b) Buckling and bowing.
(c) Burns.
(6) Other airfoil areas/defects.
(a) Burns.
(b) Nicks, scores, scratches, or dents.
(7) Inner and outer bands.
(a) Burns.
(b) Cracks.
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C. Special Inspections.
The on condition checks pertains to all special inspection requirements
regarding hardware limits and inspection procedures.
(1) Overtemperature operation.
(2) Engine stall.
(3) Exhaust gas temperature (EGT) trend step increase.
4. Documentation of Defects.
A. General.
(1) It is recommended that a record of each inspection be maintained
for each borescope inspection conducted. Sample forms and a map of
the HPT nozzle assembly is provided so that any damage within (or
out) of serviceable limits can be recorded. A record of the vane
by clock location as well as magnitude can be sketched on the map.
This information is useful in establishing deterioration data from
subsequent inspection or watch checks. These records should
accompany the HPT nozzle (module or engine) to the repair facility
for correlation of inspection depiction versus actual hardware
condition.
(2) Record inspection on inspection record. See figure 1.
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May 31/99
B. Mapping Defects.
(1) Record damage detected on the HPT nozzle vane map.
See figures 2 and 3.
NOTE: When defect/damage maps are used, accomplish the mapping at
the inspection site. Do not rely on memory of the defect to
allow the mapping to be done in an office after the
inspection. Details are lost relative to percent of chord
or span, magnitude of defect, surrounding condition, etc.
C. Photo Recording of Damage.
(1) Photos of the HPT nozzle vanes require time exposures unless
extremely fast ASA film is used. It is recommended that the probe
(rigid optic fiber light borescope) be used for photo recording.
This probe has the greatest fiber light transmission capability.
(2) Care should be taken to center the light beam on the vane leading
edge in question, eliminating as much glare or reflective lighting
from the inner combustion liner. Too much immersion of the probe
will show liner high-lighting and tend to wash out the HPT nozzle
vane photo detail.
NOTE: Whenever photos are made of a defect, a record of the photo
should be made immediately on the spot. If the photo is not
recorded relative to engine serial number, stage, port
direction of view, and date, the correlation of the hardware
damage and the photo will be extremely difficult. Note
directly on polaroid photos and record relative to sequence
of photos on 35 mm or negative film.
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Page 1
May 31/99
BORESCOPE INSPECTION OF HIGH PRESSURE TURBINE BLADES
1. Requirements.
A. On Condition.
Borescope inspection of the high pressure turbine (HPT) blades may be
required for a visual assessment check as part of the on condition
engine maintenance plan.
B. Special Inspections.
Other borescope inspection checks will be required resulting from
engine problem, trend symptoms, or troubleshooting/fault isolation. The
CFM56 Maintenance Manual will call out the engine sections required to
be inspected.
2. Procedure.
The borescope inspection of high pressure turbine blades is given in the
Maintenance Manual or Aircraft Maintenance Manual relative to each engine
model.
ENGINE REFERENCE
CFM56-2 72-52-00, Maintenance Practices
CFM56-3 TASK 72-00-00-216-026-C00
CFM56-5A TASK 72-52-00-290-001
CFM56-5B TASK 72-52-00-290-001-A
CFM56-5C TASK 72-52-00-290-801
CFM56-7B TASK 72-00-00-200-807-F00
3. Inspection Criteria.
A. General.
Whenever borescope inspections of the HPT section are required, the
following defects must be observed and assessed as to the applicable
hardware limits for serviceability. It is recommended that in-limit
defect conditions be documented for determination of subsequent
deterioration rates.
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B. On Condition (Scheduled Inspection).
(1) Trailing edge.
Cracks.
(2) Tip area.
(a) Cracks.
(b) Bent, curled, or missing pieces.
(c) Tip trailing edge wear.
(3) Blade platform.
(a) Nicks and dents.
(b) Cracks.
(4) Concave and convex airfoil surface.
(a) Cracks.
(b) Distortion.
(c) Burning.
(5) Cooling holes.
(a) Cracks.
(b) Plugging.
C. Special Inspection.
(1) General.
Specific defects accompany some of the special check requirements.
The following listing relates the special check to those typical
defects which are prevalent in engine having experienced those
problems requiring the special check. In all cases, the general on
condition check should be accomplished. This section merely
highlights those areas of distress associated with a given
problem.
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Page 3
May 31/99
(2) Core stall (N2).
(a) When an engine stall is either suspected or known to have
occurred, a borescope inspection of the HPT rotor is required;
prior to release of the engine.
(b) High pressure compressor (HPC) stalls usually drive the
exhaust gas temperature (EGT) to overlimit if the stall is
severe or sustained. This produces tip deterioration
(nibbling) on the concave or pressure face tip centered about
2/3 chord aft from the leading edge.
(c) The normal on condition check must be accomplished.
(3) Overtemperature.
(a) When certain EGT excursions are reported, a borescope
inspection of HPT rotor is required; prior to release of the
engine.
(b) The normal on condition check is required. The typical effect
of HPT overtemperature is the nibbling of the concave or
pressure face tip about 2/3 chord aft of the leading edge. In
all inspections of the HPT rotor, the on condition check and
limits apply.
(4) Metal in the tailpipe.
When metallic debris is noted in the engine tailpipe, a borescope
inspection of the HPT rotor is required; prior to release of the
engine. The standard on condition check and corresponding limits
apply.
(5) N2 overspeed, core vibs, and hard landing.
An N2 overspeed, high or changing core vibration indication or
following a reported hard landing, will require a borescope
inspection/check of the HPT rotor prior to release of the engine.
The standard on condition check and limits apply to these
conditional checks.
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May 31/99
4. Documentation of Defects.
A. General.
(1) It is recommended that a record of the inspection be maintained for
each borescope inspection conducted. Sample forms are provided
which include borescope inspection forms and maps for each rotor
stage of the HPT. The maps are provided so that any damage within
serviceable limits can be recorded pictorially by blade number and
position of blade. The propagation of the damage can then be
pictorially illustrated during subsequent inspections. The HPT
rotor blade maps are oriented about the zero reference for
inspection continuity. The inspection records and maps will remain
with the engine folder until damaged part(s) are repaired or
replaced.
(2) Record inspection on inspection record. See figure 1.
B. Mapping Defects.
(1) Record individual blade damage on HPT blade map. See figure 2.
(2) Record damage detected on the appropriate high pressure turbine
rotor maps. See figure 3. The blade numbering relative to angular
position applies only when the high pressure rotor is indexed as
defined in section 72-00-00.
NOTE: When defect/damage maps are used, accomplish the mapping at
the inspection site. Do not rely on memory of the defect to
allow the mapping to be done in an office after the
inspection. Details are lost relative to percent of chord
or span, magnitude of defect, surrounding condition, etc.
112. 72-52-00
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Page 5
May 31/99
C. Photo Recording of Damage.
Whenever photos are made of a defect, a record of the photo should be
made immediately on the spot. If the photo is not recorded relative to
engine serial number, stage, port direction of view, and date, the
correlation of the hardware damage and the photo will be extremely
difficult. Note directly on polaroid photos and record relative to
sequence of photos on 35 mm or negative film.
120. 72-52-00
Part 7
Page 13
Nov 30/11
R CFM56-7B Not 7BE With Single Annular Combustion
HPT Rotor Map of Damaged Blades
R Figure 3 (Sheet 4 of 6)
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R CFM56-7BE With Single Annular Combustion
R HPT Rotor Map of Damaged Blades
R Figure 3 (Sheet 5 of 6)
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Nov 30/11
CFM56-7B With Dual Annular Combustion
HPT Rotor Map of Damaged Blades
R Figure 3 (Sheet 6 of 6)
123. 72-54-00
Part 7
Page 1
May 31/99
BORESCOPE INSPECTION OF LOW PRESSURE TURBINE
1. Requirements.
A. On Condition.
Borescope inspection of low pressure turbine (LPT) may be required for
a visual assessment check as part of the on condition engine
maintenance plan.
B. Special Inspections.
Other borescope inspection checks will be required resulting from
engine problems, trend symptoms, or troubleshooting/fault isolation.
The CFM56 Maintenance Manual will call out the engine sections required
to be inspected.
2. Procedure.
The borescope inspection of low pressure turbine is given in the
Maintenance Manual or Aircraft Maintenance Manual relative to each engine
model.
ENGINE REFERENCE
CFM56-2 72-54-00, Inspection/Check
CFM56-3 TASK 72-00-00-216-045-C00
CFM56-5A TASK 72-54-00-290-001
CFM56-5B TASK 72-54-00-290-005
CFM56-5C TASK 72-54-00-290-801
CFM56-7B TASK 72-00-00-200-808-F00
3. Inspection Criteria.
A. General.
Whenever borescope inspections of the LPT section are required, the
following defects must be observed and assessed as to the applicable
hardware limits for serviceability. It is recommended that in limit
conditions be documented for determination of subsequent deterioration
rates.
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B. On Condition (Scheduled Inspection).
(1) Cracks in LPT rotor blades.
(a) Using the fiber light type rigid optic borescope probe 2 (wide
angle scope) inspect the total airfoil, platform, and tip
shrouds for evidence of cracks. For tip shroud condition, the
retrograde or probe 4 is recommended. Use of the magnification
adapter is recommended for final assessment of possible or
suspect cracks in the blade tip shrouds.
(b) Cracks shall exhibit depth and under magnified assessment
shall show edge material definition. Care must be used to
distinguish cracks from smears, carbon streaks, etc.
(2) Nicks and dents.
(a) Nicks and/or dents in the leading edge, trailing edge, airfoil
surfaces (convex/concave) and/or the platforms must be
assessed. Note and record the presence of these defects
relative to the percent span and percent chord for magnitude
and location on the blade. Note also the condition of the
blade material adjacent (at extremities of defect) to the
observed defect. Note any cracking or sharpness of dents
and/or nicks.
(b) Smooth impact deformities to leading or trailing edge blade
contour should be noted/reported. Subsequent inspection should
be performed to locate the origin of such damage. For example:
inspect damage to leading edge of stages 1, 2, 3 and 4 versus
leading edge damage (impact) to stages 2, 3, and with minor
trailing edge damage to stage 1 blades, etc.
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Feb 29/96
(3) Wear.
LPT rotor blade tip shroud interlock and/or circumferential mating
face area wear has been experienced. This area is viewable using
probe 2, but if suspected wear is observed the retrograde probe 4
is recommended for final assessment.
(4) Dirt, coloration, pitting, and corrosion.
High time LPT rotor assemblies may show airfoil surface
irregularities which can be dirt accumulation, carbon buildup,
pitting of the surface from particles in the gas stream or
corrosion of the blade material. These abnormalities are very
difficult to define and to differentiate between the various
suspect defects/surface irregularities. Dirt and coloration are of
little concern, however pitting and/or corrosion of the blade
material are considered significant deterioration modes. Use of
all 3 probes as well as varying light intensities is required for
final assessment of these conditions.
C. Special Inspections.
Special defects accompany some of the special check requirements. The
following listing relates the special check to those typical defects.
In all cases, the general on condition check should be accomplished.
This section merely highlights those areas of distress associated with
a given problem.
(1) Overtemperature inspection. See figure 1.
The LPT stage 1 and stage 4 blades (stage 5 for CFM56-5C) must be
inspected.
(2) Metal in the tailpipe.
All LPT stages must be inspected.
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Feb 29/96
4. Documentation of Defects.
A. General.
(1) It is recommended that a record of the inspection be maintained for
each borescope inspection conducted. Sample forms are provided
which include borescope inspection forms and maps for each rotor
stage of the LPT. The maps are provided so that any damage within
serviceable limits can be recorded pictorially by blade number and
position of the blade. The propagation of the damage can then be
pictorially illustrated during subsequent inspections. The LPT
rotor blade maps are oriented about the zero reference for
inspection continuity. The inspection records and maps will remain
with the engine folder until damaged part(s) are repaired or
replaced.
(2) Record inspection on inspection record. See figure 2.
B. Mapping Defects.
(1) Record individual blade damage on the LPT blade map. See figure 3.
(2) Record damage detected on the appropriate LPT rotor stage map. See
figures 4 through 8. The blade numbering relative to angular
position applies only when the low pressure rotor is indexed as
defined in section 72-00-00.
NOTE: When defect/damage maps are used, accomplish the mapping at
the inspection site. Do not rely on memory of the defect to
allow the mapping to be done in an office after the
inspection. Details are lost relative to percent of chord
or span, magnitude of defect, surrounding condition, etc.
Map the defect on the site of the inspection.
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C. Photo Recording of Damage.
Whenever photos are made of a defect, a record of the photo should be
made immediately on the spot. If the photo is not recorded relative to
engine serial number, stage, port direction of view, and date, the
correlation of the hardware damage and the photo will be extremely
difficult. Note directly on polaroid photos and record relative to
sequence of photos on 35 mm or negative film.
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