Rudder

This document, P5284, outlines specifications for preimpregnated glass fabric with epoxy resin for use in manufacturing graphite-epoxy and boron-epoxy composite parts, referencing FMS-2005. It details different types of fabric by roll size (e.g., P5284-1, P5284-3, P5284-5, P5284-7, P5284-9) and specifies packaging and labeling requirements for material samples, emphasizing identification with the source roll. The document mandates that samples be heat-sealed in a bag and shipped in a separate container, clearly marked "PRECUT SAMPLE." It also reserves General Dynamics' right to conduct additional acceptance testing if necessary. Furthermore, it restricts procurement to sources listed in FMS-2005 and requires compliance with environmental regulations. A destruction notice is included to prevent disclosure of contents. This document serves as a guideline for material procurement and quality control within a government contract context, likely an RFP or federal grant for aerospace or defense manufacturing.

This government document, likely a technical specification or part of an RFP from General Dynamics, details the requirements for two types of modified two-part epoxy adhesives: FMS-3008 and FMS-3068. It outlines revisions to notes and application procedures, emphasizing compliance with FMS-3068 forms I and II for qualification and acceptance. The document specifies that both adhesives must meet FPS-1012 application standards and highlights the use of non-metallic fillers for FMS-3008. Crucially, it mandates that all procurement by contractors, subcontractors, suppliers, and co-producers must use sources listed in FQML-3068 to ensure environmental regulatory compliance. The document also includes a warning about export control and destruction notice for sensitive information. Approved in April 1976, this file underscores stringent material and procurement guidelines within federal contracts.

This document, P5026, outlines the requirements for retaining compounds and primers for fasteners and bearings, particularly within the context of Lockheed Martin contracts. It details specifications for various grades and types of compounds (e.g., L-S-22473, MIL-S-46163) and primers, intended for use in temperature ranges from -65°F to 300°F. The document includes warnings regarding export control restrictions and mandates adherence to DoD security procedures. It provides tables listing different dash numbers for retaining compounds, their colors, maximum gap tolerances, and fixture times, as well as primer descriptions. The document emphasizes the importance of using approved sources and complying with environmental regulations. Procurement of these materials must follow specified ordering forms and identification standards, with supplemental numbers used for material callouts only. This technical specification ensures the proper selection and application of retaining compounds and primers for critical aerospace components.

The NDTS-1502 N document, issued by Lockheed Martin Aeronautics on October 4, 2021, outlines detailed instructions for the conductivity testing of aluminum alloys, serving as a critical supplement to NDTS 1500 and NDTS 1501. This document is essential for verifying heat treatment conditions in federal, state, and local aerospace manufacturing and maintenance. It specifies approved equipment, conductivity standards traceable to NIST, and crucial equipment cautions regarding temperature variations. The document also details process limitations for various materials and shapes, such as curved surfaces, thin materials, and castings, often recommending hardness testing as an alternative. It emphasizes personnel certification, subcontractor approval, and precise procedures for standardization and testing. Acceptance and rejection criteria are provided in tables based on alloy type and temper, with specific notes for stress corrosion cracking resistance in 7XXX series alloys. The document also addresses handling unacceptable parts, reheat treatment, and recording test results to ensure quality and compliance in aerospace applications.

Amendment SPRHA4-25-Q-0980-0001, issued October 3, 2025, modifies Solicitation SPRHA425Q0980 to correct a Part Number for an F-16 Rudder (NSN 1560-01-077-1314) from 16T7302-806 to 16T7302-805. This amendment, originating from DLA Aviation - Ogden, addresses Foreign Military Sales (FMS) requirements and details quantity range pricing for 1 to 16+ units. It emphasizes the need for offerors to acknowledge the amendment. The solicitation includes an On-Time Delivery Improvement initiative, requiring a proposed delivery schedule. Provisions for First Article testing (Bid A) and production articles without First Article testing (Bid B) are outlined, along with inspection, acceptance, and transportation details. This modification ensures accurate product specifications and compliance within the federal procurement process.

This government Request for Quotation (RFQ) SPRHA4-25-Q-0980, issued by DLA Aviation - Ogden, seeks quotations for NSN 1560-01-077-1314, Aircraft Rudders, primarily for Foreign Military Sales (FMS) customers. The acquisition is restricted to qualified sources (Aerospace and Commercial Technologies CAGE 1XKR3) and requires range pricing for quantities from 1 to 16+ units. The RFQ emphasizes on-time delivery improvement and includes options for First Article Required and First Article NOT Required, each with specific delivery and inspection terms. Key requirements cover supply chain traceability, adherence to MIL-STD-130 and MIL-STD-129R for marking and packaging, and compliance with numerous federal acquisition regulations (FAR and DFARS clauses) related to quality assurance, payments, and various prohibitions.

The DD Form 1423-1, dated February 2001, is a Contract Data Requirements List (CDRL) used by the Department of Defense. This form is essential for federal government RFPs and contracts, outlining specific data items required from contractors. It details information such as contract line item numbers, data item titles, authority for data acquisition, contract references, requiring office, and submission schedules. The form also includes sections for distribution, remarks, and pricing information. It serves to standardize and streamline the data deliverables in government contracts, ensuring that all necessary information is formally requested, tracked, and submitted according to established guidelines. The document emphasizes the importance of accurate completion and submission to the Government Issuing Contracting Officer.

This government file outlines packaging and destruction procedures, focusing on international standards for wood packaging material (WPM) to prevent the spread of invasive species like the pinewood nematode. It details distribution limitations to DOD and U.S. DOD contractors only, with specific destruction protocols. Key instructions include wrapping items to prevent direct contact with cushioning, securing mounting blocks and other components with nails or staples conforming to ASTM F1667, and using adhesive A-A-59692, Type II, for cushioning. The document emphasizes that all WPM, including pallets, skids, and wooden boxes, must be constructed from debarked, heat-treated wood (56°C/133°F for 30 minutes). Certification by an ALSC-recognized agency is mandatory, referencing ISPM No. 15 for detailed requirements. This ensures compliance for worldwide shipments from various logistics centers.

This document, "ENGINEERING DATA REQUIREMENTS (ATTACHMENT A)," outlines the manufacturing specifications for the F-16 Rudder Assembly, Part Number 16T7302-805, with National Stock Number 1560-01-077-1314WF. Prepared by Kacey Abbott of 416 SCMS/GUEAA on November 2, 2023, the document provides instructions for manufacturing, replacing certain superseded data with updated specifications and standards. It strictly mandates that only listed sources and materials be used, requiring prior engineering approval for any substitutions or deviations from control drawings. Key instructions include using MIL-STD-130 for part marking instead of FPS-3008, and SAE AMS-QQ-A-250/4 in place of QQ-A-250/4 for materials. It also specifies that 16PR100 is not required and 16PR006 is not furnished, directing the use of IGES loft data listed on the EDL instead.

This Engineering Data List, revision 13 dated November 8, 2023, provides a comprehensive inventory of engineering data, materials, and processes related to the F-16 aircraft rudder assembly, manufactured by Lockheed Martin Corporation. The document details various components such as precipitation static dischargers, nuts, bolts, and numerous specialized materials including epoxy resins, sealants, adhesives, and graphite fiber tape. It also lists critical manufacturing processes like sealing specifications, adhesive application, laminates manufacturing, finishing specifications, and adhesive bonding. Furthermore, the list includes non-destructive testing procedures (penetrant inspection, hardness/conductivity testing, ultrasonic inspection) and various installation guidelines for bolts, nuts, rivets, and fasteners. The file also outlines specific rudder assembly components, identification plates, and related structural elements, along with data for chemical milling and hole preparation. This document serves as a crucial reference for the manufacturing, assembly, and maintenance of the F-16 rudder, ensuring adherence to specified materials and procedures.

This Statement of Work outlines comprehensive preservation, packaging, and marking requirements for government contractors, primarily focusing on Department of Defense (DoD) procurements. It mandates adherence to various military and commercial standards, including MIL-STD 2073-1 for military packaging, ASTM D3951 for commercial packaging, and MIL-STD 129 for military marking. Specific provisions address hazardous materials, classified materials, electrostatic sensitive devices, and international phytosanitary measures (ISPM 15) for wood packaging. The document details requirements for specialized shipping containers (MIL-STD-648), palletized unit loads (MIL-STD-147), and the use of Item Type Storage Codes (ITSC). It also covers procedures for handling reusable containers, reporting supply discrepancies via WebSDR, and accessing government specifications through the ASSIST website. The overarching goal is to ensure consistent, compliant, and safe packaging and shipment of materials for government activities, with an emphasis on adherence to the latest revisions of applicable standards and regulations.

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This government file, likely an engineering drawing or specification for an RFP, details the design and manufacturing requirements for a "SPAR, RUDDER" component, specifically a "VERTICAL STABILIZER." It includes precise dimensions, tolerances, and material specifications, with various views (e.g., A-A, F-F, G-G, H-H, J-J, K-K) and sections (e.g., C-C, E-E) illustrating the component from different angles. Key details cover tooling holes, hinge lines, contour data, and surface finishes, with notes on metal removal, edge treatment, and tapering. The document also contains a revision history, indicating numerous engineering change notices (ECNs) over time, and strict distribution controls due to its classification as "CRITICAL TECHNOLOGY" under U.S. export laws. It references various standards like NAS523 for rivet codes and FFS-3008 for part markings, highlighting a comprehensive approach to design, manufacturing, and regulatory compliance for an aerospace component.

Report 16PR070T, dated August 13, 2018, details finish codes for the F-16 Air Combat Fighter, superseding revision S. This document outlines finishing codes and combinations for F-16 aircraft, aligning with FPS-3001 requirements for engineering drawings and parts lists. Key updates include new finish codes and basic elements, revisions to military specifications, and the addition of FMS-3120 as an alternative. It provides detailed guidance on selecting finish codes based on part location, material, and surface treatment, with examples for various components like aluminum fuselage longerons and steel support brackets. The report also includes cross-reference guides for aluminum, non-CRES, and CRES alloy finish codes, along with special and additional codes for complex or unlisted finishing requirements. EMPS is noted as the official repository for the latest finish codes, ensuring consistency and compliance with aerospace finishing standards.

This government file details the engineering and manufacturing specifications for a "SPAR,RUDDER-VERTICAL STABILIZER" component, likely for an F-16 aircraft, under Lockheed Martin Aeronautics. The document, originating from contract F33657-75-C-0310, includes a comprehensive change history dating from 1975 to 2021, a parts list with specific material notes (ultrasonic inspection and heat treatment requirements), and a reference document list covering finish specifications, part marking, metal removal, interchangeability, roughness tolerance, penetrant inspection, hardness/conductivity testing, and ultrasonic inspection. The list of materials specifies SPAR components with a stock size of 4X4X85, material specification FMS-3002-T851, and finish A103, with notes referencing the inspection and heat treatment requirements. A warning regarding export control and F-16 engineering authority is also present.

This government file details the "RUDDER ASSY-AIRCRAFT" for Lockheed Martin Aeronautics, identified by contract F33657-75-C-0310 and PL 16T7302. The document serves as a comprehensive parts list with a detailed change history, spanning multiple revisions from 1976 to 2024, indicating ongoing modifications and updates to the rudder assembly. Key sections include specific notes regarding vendor items, fastener usage variations, service data for part replacements (e.g., -5 or -805 for -3, -801, -803), and references to interim designs and engineering change proposals. A critical warning highlights the export-controlled nature of the information. The file also lists numerous reference documents covering aspects such as interchangeability, finish specifications, part marking, metal removal, torque and sealant application, rivet installation, grip length variations, seal/primer installation, and rudder installation. The formal parts list outlines various rudder assembly part numbers (e.g., 16T7303-1, 16T7303-803, 16T7303-805, 16T7303-807, 16T7303-809, 16T7303-811, 16T7303-817 and 16T7309-803) with their respective effective dates and attributes, detailing component configurations. The document underscores the rigorous management and meticulous record-keeping associated with critical aircraft components within government contracts.

This government file details a Lockheed Martin Aeronautics document, PL 16T7303, titled "RUDDER-ASSY OF," with an origination contract F33657-75-C-0310 and released on 76-01-13. The document is marked as export-controlled and includes a comprehensive change history with numerous revisions dating from 2023 back to the initial release. It also contains a parts list, notes on vendor items and alternate parts, and a reference document list outlining specifications for sealing, adhesives, finishes, part marking, and installation procedures for bolts, rivets, and sealants. The formal parts list details components like cores, caps, adhesives, shims, sealants, prime coatings, fabric, plates, spars, ribs, skin assemblies, wedges, nuts, retainers, bolts, rivets, and pins, indicating required quantities and attributes for various assembly configurations.

The document, titled "RUDDER INSTALL AND REMOVAL PROCEDURES," originates from Lockheed Martin Aeronautics in Fort Worth, TX, with a CAGEC of 81755 and an origination contract number AL 16I111003. It is a technical drawing (Type 18, Distribution Code A5, Size A) detailing the procedures for rudder installation and removal. The release date is 96-06-15, with an AL/PL issue date of 24-08-02 and revision letter A. The document contains an "APPLICATION LIST" and a "FORMAL PRODUCTION - APPLICATION LIST," which reference various part numbers, nomenclatures (e.g., AEI), versions, and effective dates/periods for different configurations and next assemblies. A significant portion of the document is dedicated to "DRAWING EFFECTIVITY USAGE FLAGS," which utilize symbols (A through Z, and AA through CJ) to indicate the applicability of the drawing across various Engineering Change Proposals (ECPs) and application types (APPL), with specific 'FROM' and 'THRU' ranges for effectivity. This detailed breakdown ensures precise application of the procedures across different F-16 engineering authorities, with a warning that the content is export-controlled.

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This government file from Lockheed Fort Worth Company details the "RUDDER ASSY-AIRCRAFT" drawing, identified as AL 16T7302, under contract F33657-75-C-0310. The document, released on January 27, 1976, with an AL/PL issue date of May 11, 2011, and revision AY, outlines formal production application lists for various rudder assembly part numbers. It includes a critical warning regarding export-controlled information, designated as "STATEMENT D, DOD AND CONTRACTORS, OO-ALC/LAAE." The file meticulously lists configurations, effective dates (from and through), and next assembly numbers (16T7301) for different versions of the rudder assembly, some of which are noted as interchangeable. The extensive "Drawing Effectivity Usage Flags" section further specifies application details and date ranges for numerous symbols and versions, indicating the broad applicability and revision history of the rudder assembly across different aircraft configurations.

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This government file, originating from Lockheed Martin Aeronautics, details the specifications and manufacturing requirements for a "RIB,RUDDER-WL 211.50" component, likely for an F-16 aircraft given the "F-16 ENGRG AUTHORITY" warning. The document includes a parts list, change history, and reference documents, along with specific manufacturing notes. Key details include material specifications (e.g., AMS 4218-T6 for castings), heat treatment verification (NDTS-1500), penetrant inspection (NDTS 1101), and alternative material options for certain parts. The file also explicitly states it is "EXPORT-CONTROLLED," indicating its sensitive nature. The "Formal Parts List" and "List of Materials" sections provide detailed breakdowns of components and their associated specifications.

This government file, primarily a technical drawing or engineering specification from Lockheed Martin Aeronautics, outlines detailed revision history, manufacturing processes, and material specifications for an unspecified part, likely related to F-16 components. It includes numerous revisions with corresponding Engineering Change Notice (ECN) numbers and dates, some dating back to the 1970s and extending to 2210. Key instructions cover finishing all areas per FPS-3001, specific omissions for prime and paint in certain areas like tapered holes and boss diameters, and cleaning and bonding procedures for various components (-7, -15, -17, -23, -27). The document also details curing processes, material removal, edge finishing, and penetrant inspection. Critical warnings about export control, distribution restrictions (Critical Technology), and severe criminal penalties for violations highlight the sensitive nature of the technical data. It also references destruction notices to prevent disclosure. The file specifies design and manufacturing standards, material codes, and dimensional tolerances, emphasizing strict adherence to military and aerospace specifications.

The document details manufacturing specifications for "SKIN-RUDDER, ASSY OF" components, likely for an aircraft, under contract F33657-75-C-0301 by Lockheed Martin Corporation. It includes detailed diagrams, material layup sequences with ply orientations, and specific processing and quality control instructions. Key aspects cover dimensional tolerances, angular tolerances on graphite ply orientation, nondestructive inspection requirements (NDTS 5103), and various engineering change notices (ECNs) indicating revisions over time. The document also specifies conditions for using different Waterline (WL) values based on loft data blocks and outlines export control restrictions, designating the data as critical technology for DOD and DOD contractors only.

This government file, originating from Lockheed Martin Aeronautics, details the "RUDDER-ASSY OF" with contract F33657-75-C-0310 and drawing number PL 16T7303. The document, dated January 13, 1976, and last revised on August 2, 2024, includes a comprehensive change history with numerous revisions dating back to 1978. It contains a "Parts List Notes" section outlining alternate and interchangeable parts, interim designs, and specific usage instructions. A "Reference Document List" provides a compilation of specifications for sealing, adhesives, finishes, part marking, metal removal, forming, electrical bonding, torque, sealants, bolt/rivet installation, grip length variations, and lines data reporting. The "Formal Parts List" enumerates various components, including cores, caps, adhesives, shims, sealants, primes, fabric, plates, spars, ribs, skin assemblies, wedges, nuts, retainers, bolts, and rivets, along with their quantities and applicable notes, some of which are export-controlled. The file emphasizes detailed documentation for manufacturing and assembly processes.

The document is a technical file from Lockheed Fort Worth Company, specifically a

This government file from Lockheed Martin Aeronautics details the "RIB,ROOT-RUDDER" component, identified by drawing number PL 16T7305 and originating from contract F33657-75-C-0310. The document, released on 1975-12-16 with an AL/PL issue date of 2022-08-10, includes a comprehensive change history with numerous revisions dating back to 1975. A critical warning states the document is export-controlled and under the F-16 Engineering Authority. It outlines parts list notes, including material inspection requirements per MIL-I-8950 (NDTS 5101) and heat treat verification per NDTS 1500. Service data indicates that -23 can replace several older part numbers. The file also lists reference documents such as FPS-3001 for finish specifications and NDTS 5101 for ultrasonic inspection. The "List of Materials" section details various RIB dash numbers (-7, -13, -15, -19, -21, -23) with a stock size of 6x12x33 and material specification FMS-3002-T851, each requiring adherence to notes A and B related to inspection and heat treatment.

This government file from Lockheed Martin Aeronautics outlines the 'SKIN-RUDDER,ASSY OF' drawing, identified as PL 16T7307, with an origination contract F33657-75-C-0310 and a CAGEC of 81755. The document, dated 75-11-11 with a PL Issue No. 096 and AL/PL Issue Date 23-09-01, includes a parts list with a warning regarding its export-controlled nature and its relation to F-16 engineering authority. It also details a comprehensive change history with numerous revisions, a list of acceptable alternate materials for various specifications (FMS 2023 Type III Form B for Form C, FMS-2023 Type V, Form A or B for Form C, and -23/-24/-5/-6 as alternates), and a reference document list for manufacturing, finish, part marking, adhesive bonding, graphite processes, penetrant inspection, and lines data reporting. The formal parts list specifies various skin assemblies, inner plies, outer plies, bonding plies, and adhesives, along with their quantities, finishes, and associated notes. The list of materials section provides detailed specifications, stock sizes, and finishes for each component, such as FMS 2023 TYIII FRC for skin components, P5362-1 for inner plies, P5284-3 for outer plies, P5284-5 and P5284-7 for bonding plies, and FMS-3011IB for adhesive.

The Lockheed Martin Aeronautics document, "BELLCRANK,RUDDER-ASSY OF," details the parts list, notes, and change history for a rudder bellcrank assembly under origination contract F33657-75-C-0310. The file, issued on 75-12-23 with a latest revision of AE on 12/15/22, includes a warning about being export-controlled and is designated for DOD and contractors with F-16 engineering authority. The parts list specifies components like bellcranks, plates, adhesive, and pins, with quantities varying by assembly type. Critical notes detail material requirements, inspection standards (MIL-I-8950, NDTS 5101), heat treatment (NDTS 1500), and material specifications (MIL-S-5059 for CRES Type 301). A comprehensive reference document list is provided, including standards for adhesives, finishes, part marking, metal removal, interchangeability, and various inspection and testing procedures. The document also provides specific effective-on dates for different part versions.

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This government file, likely an RFP or technical specification from Lockheed Martin Aeronautics, details the manufacturing and inspection requirements for a "RUDDER - WL 211.50" component, identified as part number 81755/16T 7306-11. The document outlines an investment casting process with specific tolerances for core shift, mismatch, and maximum draft. It mandates metal removal per FPS-3017, in-process welding per FPS-1032, and penetrant inspection per NDT3. The file also specifies surface finish, straightening requirements, and detailed marking instructions, including the removal of casting part numbers and stamping of finished part numbers per FPS-3008 CL2A. Crucially, it includes a warning about restricted technical data under U.S. export control laws, indicating its sensitive nature and controlled distribution to DOD and DOD contractors only. The document also provides specific instructions for using different Waterline (WL) values based on loft data blocks (01/05/10/15 vs. 25+).

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The document is a detailed manufacturing and parts list for a "FLAPERON,OUTBD-ASSY OF" from Lockheed Fort Worth Company, identified by contract F33657-75-C-0310. It includes a comprehensive change history dating from 1978 to 2015, parts list notes detailing alternative fabrication methods and material substitutions, and an extensive reference document list covering various specifications like sealing, chemical milling, finish, part marking, adhesive bonding, metal removal, roughness tolerance, etching, riveting, fastener installation, and testing procedures (e.g., heat treat, penetrant inspection). The formal parts list outlines quantities, part numbers, nomenclature, and relevant notes for components like skins, shims, compounds, adhesives, cores, covers, bushings, and rivets. The list of materials specifies stock size, material specifications (e.g., QQ-A-250/4-T851, FMS 1026), and finishes for each component, emphasizing the precise manufacturing requirements for the flaperon assembly.

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This government file, originating from Lockheed Martin Aeronautics, details the "FLAPERON,WING-ASSY OF" component with the origination contract F33657-75-C-0310. It includes a comprehensive change history dating from 1978 to 2015, indicating numerous revisions to the drawing and parts list. The document is export-controlled and falls under Statement D, DOD, and Contractors, OO-ALC Current F-16 Engineering Authority. It also provides a detailed "Parts List Notes" section outlining specific instructions for manufacturing, material alternatives, service data, and alternate designs for various components like rivets and shims. Furthermore, a "Reference Document List" specifies various standards and procedures, including sealing, adhesives, finishes, part marking, metal removal, cold-working holes, painting, dry film lubricants, marking requirements, thread compounds, anti-seize compounds, torque and sealant application, nut and rivet installation, hole preparation, seal/primer installation, hardness/conductivity testing, and eddy current testing. The formal parts list details quantities, part numbers, nomenclature, and attributes for items such as compounds, seals, channels, flap assemblies, shims, liquid shims, flaperon bonded assemblies, skins, ribs, intercostal assemblies, brackets, leading edges, washers, and rivets, often with specific notes or interchangeability/replaceability indications. This file serves as a critical technical document for the manufacture, maintenance, and modification of the flaperon assembly, highlighting the stringent requirements and detailed records kept for such aerospace components.

This government file, likely an RFP or specification document, details the requirements for "Specification Control Drawing C061" under contract AF33(657)-8260 with Lockheed. It outlines detailed specifications for self-sealing, self-locking, two-lug floating nut plates, including dimensions, materials (alloy steel, CRES, silicone rubber), finishes (cadmium plate, solid film lube, epoxy coat), and performance characteristics such as minimum float and bolt alignment. The document also includes tables with thread data and control numbers, an example callout indicating material and finish, and notes on seal material compatibility with hot mineral base oils for a temperature range of -80°F to +375°F. Furthermore, it specifies procurement requirements, strength requirements (NASM25027), and identifies suggested sources of supply with vendor CAGE codes and part numbers. The file emphasizes that any changes require approval and that procurement of certain parts became inactive after May 1979, with specific instructions for parts procured after December 1977.

This document is an engineering change notice (ECN) from Lockheed Martin Aeronautics Company, dated December 4, 2001, and printed January 3, 2002. The ECN, number 984C1, details a change to the drawing for a "RUDDER-VERTICAL STABILIZER SPAR." The reason for the change is to "MERGE RASTER MODELS AND UPDATE STATUS SHEET." The notice specifies the disposition of the drawing as "DISPOSE" for the old version and "USE" for the new version, indicating a replacement. It lists personnel responsible for checking, preparing, and supervising the change, with their respective dates. This ECN is a formal record of a design modification, ensuring proper documentation and control of engineering drawings within the company.

This government file details the "FLAPERON,OUTBD-ASSY OF" drawing for Lockheed Martin Aeronautics, originating from contract F33657-75-C-0310, released on 75-12-16, and last issued on 24-11-15. The document is export-controlled and pertains to F-16 engineering authority. It includes a comprehensive application list for various "FLAPERON BONDED" and "SKIN" parts, detailing their effective versions and application ranges, with some designated as replaceable spares. Also listed are "BUSHING" parts. The drawing is an extensive 82-sheet document, of which 10 pages are provided, focusing on the formal production application list for these aircraft components.

The document is a detailed parts list and change history for a FLAPERON,WING-ASSY manufactured by Lockheed Martin Aeronautics. It outlines the origination contract (F33657-75-C-0310) and provides a comprehensive record of revisions to the drawing and parts list, with release dates spanning from 1976 to 2015. The file also includes a section on

This Lockheed Martin document, designated as a federal government Request for Proposal (RFP), outlines the interpretation of engineering formats, general drawing requirements, and definitions of terms for various engineering and manufacturing processes. It details standards for dimensions, tolerances, manufacturing requirements, and the use of CAD data. The document also provides guidelines for symbol flag interpretation, applicable documents for standard parts and material substitutions, and the structure and content of modification drawings. Its purpose is to eliminate interpretational conflicts, standardize engineering data fields, and establish consistent drawing requirements for all Lockheed Martin Aeronautics Company engineering drawings and datasets, including those used by subcontractors and co-producers.

This government file, F33657-75-C-0310, details the specifications for flushed head Torq-Set bolts, crucial for federal procurement and manufacturing. It includes precise dimensions in inches, material specifications (AMS 6487 alloy steel), heat treatment (46-50 HRC hardness, 220,000 PSI tensile strength), and various finishes like cadmium plate and aluminum coatings. The document outlines quality control measures, including 100% magnetic particle inspection (ASTM E 1444, MIL-I-6868) and specific acceptance criteria for defects. It also provides detailed tables for tensile and shear strength, torque values, and part numbers with corresponding CAGE codes for multiple vendors. The file emphasizes strict adherence to military and industry standards (e.g., MIL-S-8879 for threads, NAS672 for finish), especially for repair and oversized bolt requirements, ensuring high-quality components for critical applications.

This government file details specifications for reduced head bolts, designated as MS33781, for federal procurement. It includes design configurations, dimensions, material requirements, and testing procedures for various bolt sizes. The document outlines specific characteristics such as Torq-Set or hex recess heads, nominal grip length, and thread type (UNJF-3A). It also provides a table with detailed measurements for different dash numbers, covering parameters like diameter, depth, and thread dimensions. The file lists approved vendors and their CAGE codes, emphasizing that procurement from these sources requires prior approval. The document serves as a crucial guide for manufacturers and contractors involved in the production and use of these specialized bolts, ensuring compliance with federal standards and aiding in the procurement process for aerospace applications.

This government file, likely an old engineering drawing from Lockheed Martin Aeronautics, details various components of a "PRECIPITATION STATIC DISCHARGER" with associated retainers and their dimensions. The document includes multiple sheets illustrating different configurations and mating parts, such as "DISCHARGER" and "RETAINER" assemblies. It also lists suggested sources of supply, including Granger Associates, Dayton-Granger Inc., Chelton Electrostatics Ltd., and Chelton Inc., along with specific part numbers and CAGE codes. Crucially, the notes indicate that these parts are inactive for new design after April 1969 and inactive for procurement after various dates, with the latest being March 1994, due to reasons like improved parts or non-compliance with the drawing. This suggests the document is a historical record of aircraft components that are no longer actively produced or used in new designs, highlighting past procurement restrictions and product evolution.

This Lockheed Martin specification (FMS-1023K, superseding FMS-1023J and FMS-1023H) details the minimum performance requirements for epoxy resin preimpregnated woven glass fabric (prepreg) for high-temperature aircraft applications, specifically for F-16 components. The document outlines material classifications (Class I, Types A, B, C), general requirements for manufacturers, repackagers, and distributors, and specifies material characteristics such as volatile content, solids content, tack, flow, and cure. It also defines material properties like hardness, resin content, and mechanical and electrical properties with detailed test methods and quality assurance provisions. Amendments to the document extended the material's shelf life from 6 to 12 months and revised the acceptable thickness range for mechanical testing. The specification emphasizes rigorous testing, quality control, packaging, and identification to ensure the material's suitability and compliance for its intended use, with Lockheed Martin retaining final authority on interpretation and conflict resolution.

This document, FMS-1097A, specifies requirements for a modified epoxy, high-strength, peel adhesive (Form IV) used in aerospace applications by Convair Aerospace Division of General Dynamics. The adhesive must meet MIL-A-132 standards with additional outlined requirements, including specific physical qualities like uniform consistency, weight loss limits, and viscosity ranges, as well as mechanical properties such as peel strength and lap shear strength. The specification details various tests, including qualification and quality conformance tests, to ensure the adhesive meets these standards, covering aspects like thermal aging, fluid immersion, and salt spray exposure. It also outlines procedures for specimen preparation, testing configurations, and manufacturer responsibilities for quality control. Packaging and labeling requirements are also defined to ensure proper storage and identification of the adhesive. The document emphasizes adherence to export control laws for technical data dissemination.

This government file, titled "Interpretation of Engineering Formats," from Lockheed Fort Worth Company (Contract F33657-75-C-0310), is a comprehensive document detailing a "Parts List" and "Change History" for various aircraft components and assemblies. It outlines numerous revisions and engineering change notices (ECNs) dating from 1978 to 2011. The file includes a formal parts list that enumerates components like multiplexers, remote interface units (RIUs), flight control panels, and electrical components. It also lists various F-16 aircraft models for countries such as Israel, Denmark, Jordan, Chile, Pakistan, Poland, Egypt, Morocco, UAE, Oman, and Greece, along with general aircraft parts like canopies, wing tip launchers, seats, emergency power units, weapon pylons, fuel pylons, repair panels, and numerous structural components. The document is marked "EXPORT-CONTROLLED" and includes notes on associated drawings and type version codes.

The “FORT WORTH QUALIFIED MATERIAL LIST FOR FMS-1097” (FQML-1097-4) issued by General Dynamics, Fort Worth Division on August 29, 1991, identifies approved materials for use with their FMS-1097 specification, “ADHESIVE - MODIFIED EPOXY, HIGH PEEL STRENGTH.” This document, a resource under DoD Regulation Number 5400.7-R, is not subject to the Freedom of Information Act. It supersedes FQML-1097-3 and specifies that future orders for these materials must come from currently approved sources. The list includes products from HYSOI Division, Dexter Corporation, specifically EA 9601 (in various forms) and ADX-322Y, along with specific adhesive primer materials qualified to FMS-1097 Form I or III. Requirements for qualification and requalification are effective immediately, with changes in this revision indicated by an asterisk.

The FMS-1044J specification, dated March 7, 2012, outlines minimum performance requirements for a modified polysulfide sealant used in aircraft integral fuel tanks, cabin pressure sealing, aerodynamic smoothing, and as a general-purpose sealant. This document, superseding FMS-1044H, details classifications (Type V for F-16/F-111 aircraft, with discontinued Types I-IV), classes (A, B, C based on viscosity), application times, and forms (bulk, pre-weighed kits, or premixed and frozen cartridges). It specifies material characteristics, properties, and quality assurance provisions, including qualification, acceptance, and verification tests. The specification covers various environmental resistances, strength retention, and repairability. Changes from FMS-1044H include corrected military document numbers, deleted thermal extrusion and microorganism resistance tests, and updated language for environmental health and safety. The document also provides guidelines for panel preparation, jet reference fluid usage, and specimen preparation, ensuring compliance and quality for aerospace applications.

This government file, F33657-75-C-0310, details the specifications for self-locking nuts, including design, material, testing, and supplier information. The document outlines dimensions, thread specifications (AS887B, UNJF-3B), and material requirements (AISI 8740 alloy steel or equivalent, AMS6322, heat-treated to 38-46 Rockwell C). Key requirements include 100% magnetic particle inspection (MIL-I-6868 or ASTM E 1444), application of dry film lubricant to threads (AS8879) prior to lock torque (MIL-N-8985), and ensuring parts are free from cracks, burrs, and other defects affecting serviceability. Preservation and packaging must protect against corrosion and physical damage. The nuts are intended for shear applications with specific bolts (C7984, C7521, C7985). The file also provides a list of suggested vendors and their CAGE codes, emphasizing that these are suggestions and not restrictive unless formally approved by engineering. This document serves as a comprehensive guide for procurement and quality control of these specialized locking nuts for Lockheed Martin and its subcontractors.

This document, FMS-3002A, outlines the requirements for 2124 aluminum alloy plate (1.500 to 6 inches thick) in the T851 temper, for use by General Dynamics, Fort Worth Division. It details specifications for chemical composition, mechanical properties, and extensive quality assurance provisions including 100% ultrasonic inspection and tensile testing by approved vendors. The document also includes procedures for qualifying production methods and vendor testing equipment. Revisions from Amendment No. 2, dated October 23, 1990, updated applicable documents to include F-16 and A-12 program specifications (16PR711 and 86PR0616), clarified acceptable ultrasonic inspection standards (MIL-I-8950 or MIL-STD-2154), and specified that artificial aging can occur before or after ultrasonic inspection. The plate material is intended for parts designed for temperatures above which 7000 series aluminum alloys are normally used, offering better short transverse stress corrosion resistance.

The Lockheed Martin FMS-3011G specification, dated September 10, 2001, details the requirements for a high shear strength, intermediate peel strength, modified epoxy adhesive (Forms 1A and 1B) and its corrosion-inhibiting primer (Form II) for aircraft structures. This adhesive system is designed for a maximum service temperature of 300°F and covers aspects from manufacturing responsibility, storage, and material characteristics (e.g., cure cycles, tack bonding, fuel tightness) to extensive quality assurance provisions. The document outlines rigorous qualification and acceptance testing, including flatwise tension, flexural sandwich beam, double overlap shear, and durability tests. It also specifies packaging, identification, and shipping temperatures for both adhesive and primer, with strict cold storage receiving protocols. The FMS-3011G supersedes previous revisions (FMS-3011F and Amendment 1 to FMS-3011E), incorporating updates to applicable documents, environmental health and safety policies, and minor dimension corrections.

This document, FMS-3018G, outlines the general requirements for adhesives and primers used in aircraft structures, superseding FMS-3018F. It details manufacturer and distributor responsibilities, emphasizing quality control, storage conditions, and "out time" limits for materials. The specification includes extensive material characteristics like weight loss, filleting, fluid tightness, shrinkage, and cure cycles. It specifies packaging, identification, and shipping temperatures for both adhesive and primer forms. Crucially, the document outlines rigorous qualification and acceptance testing procedures, including environmental durability tests, to ensure materials meet performance standards for various applications, such as fiberglass-to-titanium and fiberglass-to-aluminum bonding. It also references numerous related specifications and test methods, highlighting the comprehensive quality assurance required for these aerospace-grade materials.

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The FMS-3019E specification, dated April 28, 2003, outlines the performance requirements for a heat-expandable epoxy adhesive film used in core splices and bonded assembly shear ties within Lockheed Martin Aeronautics Company—Fort Worth (LM Aero). This document supersedes FMS-3019D and details material characteristics such as areal weight (0.18 to 0.25 lbs/sq ft), initial uncured thickness (0.050 ± 0.010 inches), and expansion of 1.5 to 3.0 times its initial thickness after curing. The adhesive is suitable for use between -65°F and its cure temperature (295-350°F), with specific cure cycles defined. The specification also covers quality assurance provisions, including qualification and acceptance tests for manufacturers, repackagers, and purchasers, as well as detailed test methods for spliced sandwich beams, areal weight, and thickness change. Packaging, identification, shipping, and cold storage requirements are also stipulated, alongside environmental, health, and safety guidelines. The document emphasizes traceability and LM Aero's sole right to interpret the specification.

The Lockheed Martin FPS-3026F specification, dated October 26, 1999, outlines the process and quality control requirements for fabricating F-16 glass-reinforced thermosetting plastic parts. This document, superseding FPS-3026E, details procedures for material inspection, manufacturing, and quality assurance. Key aspects include structural and surface smoothness classifications, strict control over material storage, handling, and work-life limits, and precise fabrication and cure procedures. The specification also mandates Design Verification Test Parts (DVTP) and test tabs for quality validation, outlining requirements for outside suppliers and procedures for addressing nonconforming parts. It emphasizes compliance with federal, military, and LMTAS specifications, highlighting the need for controlled environments and equipment calibration to ensure the safety and performance of F-16 components.

This government file outlines the General Dynamics FPS-1003M specification, superseding FPS-1003L, detailing materials and methods for sealing pressurized and non-fuel areas in F-16 and F-111 aircraft. The specification covers faying surface sealing, filleting, fastener installation, void/mismatch sealing, aerodynamic smoothing, and transparency sealing, emphasizing corrosion protection and weather sealing. It details preparation for sealing, sealant materials, application procedures, and curing processes, including specific requirements for various surfaces and fasteners. The document also addresses reprocessing of imperfections, quality assurance, and environmental health and safety. Key updates in the M revision include clarifications on material usage, processing steps, and updated safety verbiage, ensuring alignment with industry standards and internal procedures.

The FPS-3001H specification, superseding FPS-3001G, outlines detailed procedures for corrosion protection of F-16 Air Combat Fighter aircraft surfaces and components. Issued by Aeronautics Company – Fort Worth, this document covers cleaning, surface treatment, and application of finishes and protective coatings. Key changes include updating military specifications, removing environmentally restricted solvents, and adding new documents for organic finishes, passivation, and touch-up procedures. It clarifies material approval processes, defines protective system thicknesses, and details exterior and interior finish requirements for various alloys and composites. The specification emphasizes adherence to high-grade aircraft manufacturing practices, material inspection, and the resolution of conflicts with other specifications by LM Aero F-16 Materials and Processes Engineering. The document ensures comprehensive corrosion prevention and control for the F-16 program.

The Lockheed Martin Process Specification FPS-2021E, dated September 21, 2004, outlines procedures for manufacturing laminates using FMS-2023 Graphite-Epoxy material. This supersedes FPS-2021D and applies to specific F-16 parts, primarily for test panel fabrication, with FPS-3032 used for new production designs. The document details requirements for part fabricators, material control, lay-up processes, preparation for cure, and identification. It includes comprehensive instructions for basic and post-cure cycles, emphasizing temperature and pressure monitoring, and outlines quality assurance provisions such as documentation, thickness, visual, dimensional, and nondestructive inspections. Changes from the previous version include updates to material references, clarification of responsibilities, and revised process parameters for improved realism and conformity to F-16 specification formats. The specification also addresses environmental health and safety, nonconformance, and business definitions.

This document, FPS-1051D, outlines the requirements for chemical milling of metals, a process involving controlled metal removal. It supersedes FPS-1051C and details major technical changes, including updating references from QCS-170 to QCS-001 and changing "Lockheed Fort Worth Company" to "Lockheed Martin Aero." The specification clarifies temper conditions for aluminum alloys in chemical milling, defines the transition zone for chemically milled pockets, and revises rejection criteria. It covers scope, applicable documents, requirements for qualification, equipment, engineering drawings, material, processing operations, and quality assurance provisions. Key aspects include facility and process qualification, strict controls over chemical solutions, hydrogen content analysis for titanium alloys, and environmental health and safety guidelines. The document emphasizes adherence to engineering drawings, material specifications, and regulatory compliance for all chemical milling operations.

The FPS-3017G specification outlines comprehensive procedures and limitations for metal removal, aiming to achieve metallurgically damage-free surfaces on metallic parts. It details requirements for raw stock cleanup, including the removal of mill decarburization and skin from various alloys like titanium, nickel, and aluminum. The document also covers initial cutting operations such as flame, abrasive, laser, and EDM cutting, specifying acceptable methods and necessary post-cutting material removal. Grinding, bench working, hole preparation, and deburring are addressed with specific guidelines for different materials and applications. Furthermore, the specification emphasizes surface integrity, material handling, corrosion protection, and the use of coolants. Quality assurance provisions, including part quality, surface integrity, and dimensional tolerances, are provided. The document also includes environmental health and safety considerations and scrap segregation requirements for aluminum-lithium alloys, ensuring compliance and safe practices.

The Lockheed Martin document, FPS-1012N, dated October 10, 2022, outlines processing and quality control requirements for general-purpose adhesives and provides guidelines for material and process selection in Fort Worth aeronautics applications. This supersedes FPS-1012M and earlier versions, detailing significant changes marked with a bar in the left margin. Key updates include revisions to shelf-life extension controls to prevent misuse and a re-focusing of cleaning methods to reduce hexavalent chrome usage. The document specifies general requirements for materials, control procedures for materials and parts, facilities, equipment, tooling, preparation procedures (including various cleaning methods), application procedures, and cure procedures. It also covers post-treatment, properties, qualification, quality assurance, and environmental health and safety responsibilities. This specification is crucial for ensuring the proper application and bonding of adhesives in aircraft manufacturing, adhering to strict safety and quality standards.

The provided document, DS-4701-8L, outlines the General Specification for Retaining Compound, specifically for retaining bearings, bushings, and studs, with or without primer. The document details requirements for application, preparation, and assembly of these compounds, emphasizing cleanliness and proper surface preparation. It includes sections on inspection, materials, and specific application instructions for various components, such as non-seated fasteners and studs. The specification also details quality assurance, packaging, and distribution information, indicating controlled distribution to authorized agencies and contractors. Changes include updates to various tables and references, as well as the addition of a new retaining compound, further refining the scope and application of these materials in government projects.

The FPS-3016 S specification, dated September 21, 2006, outlines the process and quality control standards for F-16 adhesive-bonded assemblies. This document supersedes FPS-3016R and details requirements for documentation, operational controls, equipment, tooling, materials, and fabrication procedures. Key changes in this revision include allowances for suppliers to use alternative overlay materials, restrictions on vacuum levels during honeycomb core splicing and cure cycles to prevent negative impacts on foam materials, and clarification of adhesive fill criteria for FMS-3019 to control air inclusions. It also adds re-test and shelf-life extension requirements for FMS-3011, addressing challenges with low-usage materials. The specification emphasizes traceability, environmental controls, and rigorous testing for quality assurance in F-16 aircraft manufacturing.

The document "FQML-3011-3: FORT WORTH QUALIFIED MATERIAL LIST FOR FMS-3011" from Lockheed Martin Tactical Aircraft Systems, dated November 19, 1999, is an updated list of approved materials for use with Specification FMS-3011, which details a high shear strength, intermediate peel strength, modified epoxy adhesive. This revision supersedes FQML-3011-2 and is effective immediately. Key changes include the deletion of Form IA and EC-3917 products, as they are no longer used in F-16 production. The document lists 3M Company as an approved source for AF-147-.11 Wt. adhesive, along with its LMTAS designation and test report dates. Notes clarify that EC-3917 primer is no longer used for F-16 aluminum bonding applications involving FMS-3011, and that AF-147 manufacturing moved in 1981. The document is approved by L. K. Austin from Systems Engineering, Materials & Processes, indicating its role in maintaining material quality and compliance for tactical aircraft systems.

The FPS-3030 E specification outlines a standardized system for split sleeve cold working of holes in heat-treated aluminum to enhance fatigue performance. It details application scope, tooling requirements, and manufacturing limits for holes up to 1.0 inch in diameter, creating a 3-5% expansion. The document explicitly restricts its use for certain Aluminum-Lithium alloys (FMS-4097) but permits it for others (FMS-3103) when specified. Key requirements cover engineering drawings, hole preparation, tool selection, the cold working process, and quality assurance, including verification and qualification criteria for tools and personnel. This revision supersedes FPS-3030 D, incorporating changes such as updated tooling references, requirements for backing plates in thin structures, and clarified cleaning procedures.

The "FORT WORTH QUALIFIED MATERIAL LIST" (FQML-3096), dated March 11, 1991, from General Dynamics, Fort Worth Division, identifies approved materials for specific applications. This document, superseding previous FQMLs, focuses on modified epoxy adhesive (asbestos-filled) for composite and composite-to-metal applications. It stipulates that future procurement orders must be from currently approved sources, though products from sources listed in earlier issues may be used to completion. The revision notes changes and lists CIBA GEIGY R-398 as an approved product, qualified under FMS-3096, with a test report from GENERAL DYNAMICS. Primers qualified to FMS-3018 for Form II are acceptable for use with the FMS-3096 adhesive. The document also clarifies its status as Technical Data, not a public record under the Freedom of Information Act.

The “Fort Worth Qualified Producers List for FPS-3030” (FQPL-3030-4) is a restricted document from Lockheed Martin Aeronautics Company, superseding FQPL-3030-3. Dated March 7, 2022, this list identifies approved producers for

The “FORT WORTH QUALIFIED PRODUCTS LIST FOR FPS-3024” document, FQPL-3024-15, issued by Lockheed Martin Aeronautical Systems on May 25, 2022, outlines approved equipment and materials for electrical bonding requirements for the F-16 Air Combat Fighter, superseding FQPL-3024-14. This critical technology document has restricted distribution to the DoD and United States DoD contractors due to export control regulations. The list specifies various milli-ohmmeters, such as the Tegam 720A, Amptec Research 720A, and Megger DLRO series, approved for verifying electrical bonds. It also includes Volt-Ohm meters, specifically the Simpson Model 260, for bonds with allowed resistances of 0.5 and 0.2 Ohm. Additionally, the document lists approved materials like the Berol Rapidesign Klenzo 533T eraser and the C-17203 tooling system for surface preparation for electrical bonding. The revision primarily adds the Tegam 720A meter to the approved list.

The Lockheed Fort Worth Company Specification FPS-3032E, dated November 19, 1993, outlines the process for manufacturing F-16 aircraft parts, including skins, spars, ribs for vertical and horizontal stabilizer leading edge assemblies, rudder skins, and repair patches, as well as test tab laminates (P653). This revised specification, superseding FPS-3032D, details requirements for materials, facilities, equipment, tooling, and fabrication procedures, covering aspects from material control and handling to cure cycles and quality assurance. Key updates include increased flexibility by removing the word "inspection" and incorporating supplier values for thickness measurements. The document also provides specific instructions for bonding and post-cure processing, emphasizing quality control, nondestructive evaluation, and destructive testing to ensure compliance with federal and military standards under contract F33657-88-C-0037.

The FQPL-3026-13 document, effective April 5, 2022, is a Fort Worth Qualified Processor List for Lockheed Martin Aero Specification FPS-3026, which details the process and quality control of F-16 Glass Reinforced Plastic Parts. This revision corrects errors in Elbit Systems – Cyclone Ltd. part listings. The list identifies approved processors and co-producers for various F-16 components, including their part numbers and production status (Active or Inactive). Key approved processors include IAI-Production Division, Elbit Systems – Cyclone Ltd., LM Aero – Fort Worth, Texas, and Kanfit Ltd. The document notes recent qualification efforts completed in March 2022 for Kanfit Ltd. and requalification for Elbit Systems – Cyclone Ltd., with reports available in the historical files of FPS-3026.

The FQPL-3032-3 document, effective March 22, 2022, is a Qualified Material List for Lockheed Martin Aeronautics Fort Worth Specification FPS-3032, detailing approved manufacturers for F-16 aircraft parts. It supersedes FQPL-3032-2 and lists processors for parts such as skins, spars, and ribs for vertical and horizontal stabilizer leading edge assemblies, rudder assemblies, and repair patches. Key updates in this revision include the completion of Elbit Systems – Cyclone Ltd's re-qualification in March 2022, changing their production status to “Active” for listed parts, and the change of LM Aero's production status to “Active.” The document also lists inactive processors and specifies approved gloves for use by processors, highlighting regulatory compliance and quality assurance in aerospace manufacturing.

The document FQML-3018-19, issued by Lockheed Martin Aeronautics Company – Fort Worth on February 11, 2016, is a Qualified Materials List for FMS-3018. This supersedes FQML-3018-18 and is intended for use with Lockheed Martin specification FMS-3018, which details "Structural Adhesive, Intermediate Cure Temperature, Metal-to-Metal and Composite Applications." The list approves specific products for procurement, noting changes in this revision, particularly the approval of Cytec – Solvay Group materials for production applications. It lists approved manufacturers like Cytec-Solvay Group and Henkel Technologies, along with their product designations, LM Aero designations, and test report dates. The document also includes important notes regarding company transitions (Cytec's acquisition of J. D. Lincoln), manufacturing location changes for specific products, re-qualification details, and the removal of Ciba-Geigy products due to acquisition by Hexcel Corporation, requiring retesting for F-16 use. This document is restricted to the DoD and United States DoD contractors due to critical technology information.

The General Dynamics Specification FPS-3024D (superseding FPS-3024B) details electrical bonding requirements for the F-16 Air Combat Fighter. This document outlines procedures for electrical bonding and grounding, replacing previous military standards. It specifies preparation methods for various metallic surfaces, assembly instructions, and verification processes for electrical bonds, including resistance measurements and special case verifications for equipment racks and LRUs. The specification also addresses touch-up, sealing, and interpretation of engineering drawing call-outs, emphasizing the evolution of these call-outs over the F-16 program's lifespan. The latest revision, FPS-3024H (superseding FPS-3024G), includes updates for clarification, removal of chemical deoxidation allowances, and refinements to drawing interpretations and figures.

The FPS-3018B specification, dated March 23, 1993, and superseding FPS-3018A, outlines procedures and requirements for forming, straightening, and swaging aluminum parts and tubing. This document is crucial for federal, state, and local RFPs, setting standards for material condition, cleaning, lubricants, and multi-stage forming of various aluminum alloys like 2024, 6061, 6013, and 7075. Key revisions in FPS-3018B include updated group names, references to industry specifications like AMS 2750 for temperature control and AMS 2770 for heat treatment, and revised paragraphs for clarification and practicality. The specification details forming after solution heat treatment, straight-line bends, stretch forming, joggles, dimpling, beading, beaded holes, straightening after artificial aging, hot forming, and high-energy forming processes. It also addresses thinning, tolerance measurement, penetrant inspection, and heat treatment. Quality assurance provisions cover tensile testing, penetrant inspection, and temper verification, ensuring adherence to specified standards. The document includes several figures and tables to provide visual and tabular guidance for various forming operations and material properties.

The “Fort Worth Qualified Materials List for FMS-3019” document, dated December 21, 2006, supersedes FQML-3019-6 and is to be used with Lockheed Martin Aeronautics Company Fort Worth Specification FMS-3019. This list details approved adhesive film compound primary splice materials for honeycomb core materials. It specifies that products from previously listed sources may be used to depletion, but future orders must be from currently approved sources. The revision documents a name and location change for a supplier from Sovereign Engineered Adhesives in Akron, Ohio, to Henkel Technology in Bay Point, California, noting no change in formulation. The document lists approved products from 3M (St. Paul, MN and Tillory, France) and Henkel Technologies (Bay Point, CA), along with their respective approval dates and relevant notes regarding qualification and equivalency testing. The release of this material is subject to Freedom of Information Act restrictions.

The document FQML-3002-14 from Lockheed Martin Aeronautics – Fort Worth, dated April 23, 2019, is a Qualified Material List for FMS-3002, concerning Aluminum Alloy 2124 Plate (1.500 – 6.00 inches in thickness). It supersedes FQML-3002-13 and is restricted to DoD and U.S. DoD contractors due to critical technology. The revision FQML-3002-14 is divided into two sections: Section I outlines 16PR092 Materials Substitution industry specification certification requirements for using AMS-4101 as a substitute for FMS-3002 plate, and Section II lists approved manufacturers, their test laboratories, and qualified production methods. Key changes include updated manufacturer names due to industry mergers and the addition of AMS-4101 certification requirements for Al 2124-T851 plate as a material substitution. The document specifies that AMS-4101 plate must be from FMS-3002 FQML-approved suppliers, undergo 100% ultrasonic inspection, and meet AMS-4101 minimum tensile values. Tables I and II detail approved laboratories and production methods, respectively, along with associated test reports and qualified plate thicknesses.

The FQPL NDTS-1101-28 document, dated February 13, 2023, is a Fort Worth Qualified Processors List for penetrant inspection of aircraft parts, superseding FQPL NDTS-1101-27. It authorizes distribution to the DoD and U.S. DoD contractors only due to critical technology and export restrictions. The list is incomplete without NDTS-1101, which outlines the penetrant demonstration program required for processors to qualify for Zone 1A, 1B, and/or 1C parts. Changes in this revision include adding Lockheed Martin Aeronautics Greenville Operations, revising and deleting outdated vendors, removing vendors with changed penetrant materials, adding new materials for Morrell Electro Plating and NDE Inc., adding Fine Quality Metal Finishing, updating Aaxon Labs and NDE PCIR reports, and modifying zone approvals for AAA Plating and Inspection and NDE. Processors are qualified for both fracture critical and non-fracture critical parts using documented penetrant materials. Re-qualification is necessary for changes in materials or inspection processes. A separate list, Table 2, details processors qualified for non-fracture critical parts using pre-penetrant etch per LMA-PG001.

The FQPL-3016-29 document, issued by Lockheed Martin Aeronautics Company– Fort Worth on June 27, 2023, is the Fort Worth Qualified Processors List for FPS-3016. This list identifies approved processors and co-producers for F-16 adhesive bonded assemblies, to be used with Lockheed Martin Aeronautics Specification FPS-3016. It supersedes FQPL-3016-28 and includes updates to the status of IAI for the 16E130 antenna. The document details various international and domestic processors, their parts, production status (active or inactive), and applicable process specifications. Additionally, it provides a list of gloves approved for use by the listed processors, including details on manufacturers, product numbers, descriptions, and approval dates, with specific notes regarding deviations and qualifications for certain processors and glove types. The document emphasizes distribution restrictions due to critical technology and export control regulations.

The Lockheed Fort Worth Company issued FQML-P5026-2 on February 23, 1994, a Qualified Material List for P5026 Retaining Compound, intended for use with Threaded Bearing Parts. This document approves specific products from manufacturers like Loctite Corp. and Hernon Mfg Inc. for procurement. The list details various primers and compounds, including their designations and approval dates. The document also contains warnings regarding technical data export controls and dissemination restrictions under DoD directives. It outlines procedures for destruction and controlled release of information, emphasizing compliance with national industrial security programs. This list ensures that only approved materials are used, maintaining quality and adherence to federal regulations.

The Fort Worth Qualified Products List (FQPL-1012-1) for FPS-1012, issued on February 16, 2016, outlines approved products for use with Lockheed Martin Aeronautics Specification FPS-1012, "Application and Bonding with General Purpose Adhesive." This initial release documents sources for non-chromated adhesion promoters and clarifies that Pasa-Jell, previously in FPS-1012, remains for clarity. Key changes include adding glass beads as an option for bondline control materials and incorporating source information for LMA materials, which are typically found in EMAP. The FQPL lists qualified bond preparation materials from manufacturers like 3M and PPG Industries, specifying their product names, FPS-1012 usage, and qualification dates. This document ensures the use of approved products for future orders, enhancing clarity and standardization in material procurement for aeronautics applications.

The FQML-1044-43 document, issued by Aeronautics Company – Fort Worth on July 20, 2022, is a Qualified Material List for FMS-1044, which specifies integral fuel tank and general usage sealant. This revision supersedes FQML-1044-42 and details approved manufacturers and repackagers for various classes of FMS-1044 Type V sealants. Key updates include the addition of Royal Repackaging Facility – Ball Ground, GA, as a qualified repackager and the removal of Sealants Europe SAS due to facility closure. Approved manufacturers listed are PPG Aerospace (Mojave, CA), Royal Adhesives & Sealants (Wilmington, CA), 3M Aerospace (Springfield, MO), and Flamemaster Corporation (Sun Valley, CA). Repackagers include PPG Aerospace Application Support Centers and Dyna-Seal (Sun Valley, CA), in addition to the newly added Royal Repackaging Facility. The document provides specific product designations, LM Aero designations, test report numbers, and approval dates for each source, along with notes detailing qualification conditions and changes.

The Lockheed Martin Aeronautics Company's document FQML-1023-26, dated May 14, 2003, is a Fort Worth Qualified Material List for FMS-1023, superseding FQML-1023-25. This list, used with LM Aero Specification FMS-1023 (EPOXY RESIN PREIMPREGNATED MATERIALS FOR HIGH TEMPERATURE APPLICATIONS), identifies approved materials for procurement. Key changes in this revision include the removal of a limited procurement constraint. CYTEC Engineered Materials Inc. is an approved manufacturer, with their product CYCOM 9000-1/7781 designated for FMS-1023 Class I, Types A, B, and C Glass Fabric Style 181. A note clarifies a change in a constituent material used in CYTEC's resin formulation, effective from Batch 2217507. The document is approved by R.V. Wolff of F-16 Materials and Processes and includes a contract number F33657-88-C-0037.

The Lockheed Fort Worth Company's FQPL-3017-10 document, issued November 29, 1995, is a Qualified Processors List for FPS-3017, detailing approved companies and procedures for limiting metal removal after laser cutting. This revision supersedes previous versions and is effective immediately. It outlines specific material removal requirements and restrictions for laser-cut surfaces, particularly for aluminum. Enginetics Corporation, with procedure PE0008, Revision B, is approved to remove 0.003 inches of material from all surfaces after laser cutting, applicable only to aluminum. Manufacturing Development, Inc., using procedure MDI-3000, is approved for the same material removal thickness, but exclusively for 2024-0 aluminum. The document was prepared and approved by S. B. Kiehl, Chief of Structural and Environmental Materials and Processes. This list ensures adherence to quality control and processing standards for aerospace manufacturing.

The P5055 Qualified Material List, dated August 27, 1997, is a Lockheed Martin Tactical Aircraft Systems document detailing approved materials for procurement. This list is effective immediately upon issue and supersedes previous versions, with earlier listed products usable until depletion. New items are indicated by a vertical bar in the left margin. The document specifies approved manufacturers and repackagers for various materials, including Fabric, Glass, Finished, Tape, Yarn, and Roving, with their respective designations and dates of approval. Notes clarify terms like "article" and "width" and provide manufacturer designations. The document includes distribution statements restricting its release under DoD regulations and an export warning regarding compliance with the Arms Export Control Act and Export Administration Act. It also provides a destruction notice to prevent reconstruction of its contents.

This document outlines detailed engineering and manufacturing specifications for chemically milled parts, likely related to a Lockheed contract (AF33(657)-8260). It provides precise tolerances for chemical milling operations, covering surface roughness, fillet radii, corner radii, and critical dimensions like land widths and pocket thicknesses. The document specifies different tolerances for various programs, including F-111, and defines acceptable conditions for etched areas, land features, and metal removal processes. It also addresses the "rippled effect" and "ridge" adjacent to etch steps, providing guidelines for their mitigation or acceptance. The overall purpose is to standardize the quality and dimensional accuracy of chemically milled components, ensuring consistency and compliance with stringent engineering requirements.

This government file outlines a standard procedure for fastener grip variation in structural assembly, applicable when specifically called out on engineering drawings. It details permissible fastener length adjustments, allowing for variations of up to two lengths shorter or longer without engineering approval, provided proper installation requirements are met. The document also specifies conditions for installing washers, especially to minimize dissimilar metal corrosion, and lists compatible washer types for various surfaces. It provides guidelines for pin-collar fasteners, including the use of "GO/NO-GO" gages, and addresses the application of the standard to removable nutplates. Criteria for determining acceptable fastener length, including visual inspection and measurement of thread protrusion, are presented with supporting figures and tables. The file concludes with purchasing guidelines for fasteners, emphasizing the need for both normal and extra grip lengths to account for losses and scrap.

This government file outlines the standard procedures for the installation of flush head taper shank bolts, specifically the M057 series, in various structural components, including steel, aluminum, and titanium. The document details acceptable conditions for holes, emphasizing drilling, reaming, and alignment requirements. It provides comprehensive tables for bolt dimensions, protrusion limits, torque values, and acceptable inspection conditions, including surface finish and hole roundness. The file also specifies repair procedures for oversized holes, outlining the use of larger diameter bolts. Special attention is given to sealant application, wrenching methods, bolt thread protrusion checks, and bolt removal. This document is critical for ensuring the proper and safe installation of these specialized fasteners in F-111 aircraft structures, highlighting adherence to engineering drawings and quality control throughout the process.

The document appears to be a highly technical government file, likely a blueprint or schematic for an engineering or construction project. It contains numerous codes, part numbers, and technical annotations, such as "E0EL191," "33N3~3338," and "8300178." The presence of terms like "AdOJ SIH.L," "SDNIMYIJO," and "lJV81NOJ" suggests a reference or contract document related to drawings. The file includes specific measurements and revisions, indicated by "Z T," "CB," and various numerical sequences. It emphasizes strict adherence to procedures with "ONLY FOR REFERENCE" and "NOT FOR REPRODUCTION" notes. The repetitive use of "39NIH," which may be "HINGE" or a similar component, points to a focus on specific hardware or structural elements. Overall, the document serves as a detailed technical record for a project, prioritizing precision and compliance.

The Lockheed Martin Aeronautics document M100, Revision AU, outlines detailed standards for rivet installation in F-111, F-16, and FS-X aircraft. It covers general notes, rivet spacing, edge distance, hole sizes, head dimensions, and flush head rivet installation. The document specifies criteria for solid and blind rivets, including engineering minimums, inspection minimums, and tolerances for various dimensions. It also addresses rework procedures for discrepant holes, sealing of rivets in fuel tank areas, and quality requirements such as crack-free surface diameters and acceptable imperfections. The standards are crucial for ensuring structural integrity and aerodynamic smoothness, with specific tolerances for flush rivet heads on external surfaces and guidelines for reprocessing rivet installations. The document concludes with a defect standard illustrating unacceptable rivet installations.

This government file details the installation procedures, tools, and requirements for blind elliptical head nuts, specifically focusing on hole preparation, countersinking, and nut installation. The document outlines essential notes for countersink tools, including recommended materials for different metals, and provides tables with precise dimensions, tool callouts, and installation force requirements. It also covers procedures for selecting appropriate tools based on hole size and material thickness, proper mandrel-to-anvil settings, and post-installation checks for flushness and diameter. Furthermore, the file addresses repair procedures using oversize parts and specifies installation requirements for these components, ensuring structural integrity and adherence to engineering standards.

The provided government file, likely an RFP or grant-related document, outlines detailed specifications for various components and processes, focusing on precision and compliance. It includes technical drawings, measurements, and references to specific standards (e.g., "NJ3", "805t71 IS"). Key elements involve component numbering, material specifications (e.g., "33Y", "7J"), and detailed instructions for various parts, indicating a project with stringent technical requirements. The document also mentions quality control measures, such as "03SY3BY 2113" and "N011O17008d38," highlighting a strong emphasis on accuracy and adherence to established guidelines. Overall, the file details a project requiring careful execution and strict compliance with given parameters.

This government file, M016, outlines comprehensive torque values and sealant application procedures for threaded fasteners used in engineering drawings, particularly relevant for federal government RFPs. It details specific torque requirements for various fastener types, sizes, and applications (e.g., fuel vs. non-fuel areas, electrical components), referencing multiple tables (I, II, III, IV, V, VI, VII) and figures (W, X, Y, Z) for lubrication and sealant methods. The document emphasizes adherence to minimum and nominal torque values, proper lubrication, and disposal of over-torqued components. It also provides guidance on torque codes, fastener replacement, and specific procedures for self-locking nuts and small-diameter fasteners, ensuring compliance and safety in critical assemblies for both production and maintenance. The standard has undergone revisions, with some tables becoming inactive for new designs after specific dates.

This document, likely an engineering drawing or technical specification for a government contract (e.g., RFP), outlines the detailed procedures and requirements for installing rivetless self-retaining nuts, specifically MS14200 and C7592 types. It covers hole preparation, installation methods using pneumatic compression tools, air-hydraulic puller tools, and hand-operated puller tools, and post-installation inspection procedures. The document includes tables for thread sizes, tool assemblies, grip codes, and installed flared sleeve diameters. It also specifies requirements for tool suppliers and provides examples of engineering drawing callouts for these nuts. The primary purpose is to ensure correct and standardized installation of these fasteners in accordance with Lockheed Martin Aeronautics and DOD engineering authority, emphasizing export control and proprietary information warnings.

The provided document details engineering specifications for fastener holes, particularly focusing on countersink diameters, tolerances, and fit types (clearance, transition, interference) for various applications in aircraft like the F-111 and F-16. It outlines precise measurements for flush head fasteners, specifies material requirements (titanium or steel), and provides guidelines for hole preparation and selection based on fastener shank diameter and intended use. The document also includes tables with dash numbers, basic sizes, and typical drawing callouts for different fasteners, ensuring standardization and proper installation in structural connections and other assemblies. This information is crucial for maintaining structural integrity and aerodynamic flushness in aerospace manufacturing.

The NDTS-1501 L document from Lockheed Martin Aeronautics outlines comprehensive requirements for hardness testing of metallic materials. This superseding document, dated October 4, 2021, details approved equipment, surface preparation, impression spacing, hardness scale selection, and maintenance procedures. It includes specific guidelines for Rockwell and Brinell hardness testing, daily accuracy checks, and correction factors for cylindrical parts. The document also addresses acceptance and rejection criteria, particularly for coated and plated parts. Importantly, it emphasizes that NDTS 1501 is an indivisible part of a larger set of documents (NDTS 1500 and NDTS 1502), which collectively govern nondestructive methods for verifying heat treat conditions. Distribution is restricted to the DoD and United States DoD contractors due to critical technology.

This government file, likely an engineering drawing or specification document, details tolerances and requirements for machined surfaces, particularly focusing on waviness and surface finish. It outlines conditions for acceptable machining, specifying maximum waviness, surface roughness, and machining marks. The document emphasizes the elimination of machining marks on critical surfaces and provides guidelines for various surface types, including non-machined, machined, and blended surfaces. It also addresses dimensional tolerances, misalignments, and the inspection of these characteristics. The file includes details on surface application, inspection methods, and references to relevant standards, ensuring consistency and quality in manufacturing processes. It appears to be a technical guide for precision machining and surface finishing in a government-related project.

This document outlines the application procedure for P6104 high-strength retaining compound, detailing revisions and specific steps for its use. It specifies materials such as P6104 retaining compound and P6103 primer, along with cleaning procedures using FPS-1012 and P5396 cleaner. The procedure includes cleaning surfaces, applying P6103 primer, and then P6104 retaining compound. It also defines cure time requirements, including a minimum fixture time and a full strength cure of 24 hours, with an option for accelerated cure. This standard is applicable only when specified on engineering drawings, ensuring proper application and performance of the retaining compound in relevant projects.

The document appears to be a technical drawing or schematic, likely related to a mechanical or structural component, given the presence of labels such as "39N1H 73" (possibly "HINGE"), "078", and various numerical and alphanumeric identifiers. It includes multiple views or sections, indicated by repeated elements and differing angles. The overall purpose of this government file is to detail the specifications, dimensions, and possibly the assembly of a particular part, which is common in federal RFPs for manufacturing or construction. While specific details are obscured by poor OCR quality, the structure strongly suggests an engineering or architectural blueprint, emphasizing precision and technical compliance for a government project. References to "EL19IW" and "SSLIZ" could be project or drawing numbers.

The document appears to be a technical drawing or schematic, likely related to engineering or construction, given its inclusion in a government file context. It contains numerous alphanumeric codes, measurements, and symbols that suggest detailed specifications for a system or component. Key elements include references to "PRODUCTIONS CONDITIONS," "DRAWINGS UNENSIONED," "NOTES," and various numerical sequences that could represent part numbers, dimensions, or revision dates. The overall structure indicates a formal technical document, possibly detailing a design, assembly, or installation process, typical for federal government RFPs, grants, or state/local RFPs where precise technical specifications are required.

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This Lockheed Martin Aeronautics document, M198, outlines the standard procedures for fastener installation, spacing, hole preparation, and removal in aircraft structures. It details requirements for pins, bolts, and blind fasteners, including acceptable tolerances for flushness on aerodynamic and non-aerodynamic surfaces. The document specifies hole sizes, fillet relief, and methods for removing various fastener types using specialized tools and procedures. Revisions up to AL dated September 10, 2024, are noted. This standard ensures proper fastener installation and removal, crucial for structural integrity and aerodynamic performance, and is applicable when referenced in engineering drawings.

This document outlines classifications and installation procedures for fasteners in various aircraft areas, including fuel and non-fuel zones, as well as removable panels and access covers. It details specific preparation, application of sealants and lubricants, and post-installation coating requirements to ensure corrosion protection, prevent fuel leakage, and facilitate maintenance. The classifications (M219-1 to M219-7) define procedures based on fastener location and function, emphasizing material selection, torque specifications, and protective finishes. The document ensures proper installation and long-term integrity of fasteners in diverse aircraft environments, addressing both structural and non-structural components. Each classification has specific instructions for sealant and lubricant application, cleaning, and coating, with detailed figures illustrating these processes. It provides a comprehensive guide for maintaining the aircraft's structural and functional integrity.

This government file, likely an engineering drawing or specification document, details laminated shims under contract AF331657-8260. It outlines material compositions (Aluminum, Brass, Corrosion Resistant Steel, Carbon Steel, Fiberglass, Titanium) per MIL-S-22499 and FMS-1023/FPS-3026 standards, along with nominal and maximum ply thickness for various dash numbers. The document provides examples for calling out specific shim types and thicknesses. Key notes include requirements for parts made from P103 material, acceptable lamination criteria, and detailed part requirements regarding thickness, width, length, holes, and finish. It also specifies permissible rounded edges for shims and outlines permanent marking requirements for each piece, including procurement specification and raw material details. The distribution statement restricts technical data to authorized DoD and U.S. government contractors, warning against export violations.

This document details the specifications for "IDENTIFICATION AND MODIFICATION PLATES" (P082) made from aluminum foil with a pressure-sensitive adhesive backing. These plates are to be used on aircraft for identification and modification callouts. Key specifications include material type (P5114-4 aluminum foil), dimensions in inches with specific tolerances (fractions ±1/16, decimals ±.010), and requirements for permanent and legible lettering in accordance with K933558. The document provides examples for typical lettering callouts, including part number, thickness, and control number. It also outlines distribution restrictions, designating the document as "WARNING. Export Controlled" and authorized only for DoD and DoD contractors. The document was originally approved in November 1963 and revised in November 1976.

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This government file, identified by contract F33657-75-C-0310, details specifications for Aluminum Alloy 5052 Honeycomb Core material. It outlines revisions to the material specifications, including additions and changes in type, thickness, width, and length. The document specifies manufacturing processes for core expansion, material composition (FMS-3010 process alloy), and various foil material types and sizes with corresponding thickness and weight per cell. It also provides an example of a specification callout for ordering the material, emphasizing details such as stock size, ribbon direction, and thickness. The primary purpose is to standardize the specification of honeycomb core for government contracts, ensuring consistent quality and adherence to defined technical parameters for Aluminum Alloy 5052.

The NDTS-5103E specification, issued by General Dynamics in 1992, outlines procedures and requirements for ultrasonic inspection of bonded and composite structures. This document, intended for use in federal government projects, supersedes the 1984 NDTS 5103D specification and details techniques for detecting defects such as delamination, voids, porosity, foreign material inclusions, and unbonds. It covers personnel certification, equipment, inspection reference parts, and various ultrasonic methods including through transmission, pulse echo (A-Scan, reflector plate, time of flight), ring pattern, and resonance. The specification also defines defect characteristics, signal responses, sizing methods, and detection limitations. It mandates that all personnel be certified and that Technique Data Sheets (TDSs) be approved by a UT Level III. Supplier and co-producer NDT programs must also be approved. The primary purpose is to standardize quality control and ensure structural integrity through rigorous non-destructive testing.

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This government document, labeled P5055, outlines the specifications for glass fabric, tapes, and yarns, crucial for Department of Defense (DOD) technology and contractors. The file details material properties, construction, and quality control for various glass fiber products, including thickness tolerances, weave styles, and finishes. It specifies authorized materials, packaging, shelf-life, and identification requirements, emphasizing compliance with export control acts. The document also includes detailed inspection criteria for appearance and workmanship of yarns, roving, and woven fabrics, outlining acceptable quality levels for defects. It provides guidelines for material procurement and supplemental dash numbers for part callouts, ensuring materials meet stringent engineering and purchasing standards for defense applications.

This document establishes requirements for a two-part, fast-setting epoxy adhesive, FMS-3076, for qualification and acceptance. It details two intended uses: one where environmental resistance is not a serious consideration (Type 1) and another where high humidity and other environmental conditions are crucial (Type 2). The document outlines revisions, application procedures per FPS-1012, and strict distribution controls, limiting access to US DoD and authorized contractors due to its "WARNING-Export Controlled" status. Procurement of items described must use sources listed in FML-3076 to ensure compliance with environmental regulations. This specification is essential for ensuring the correct application and quality control of the adhesive in various government contract settings.