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Composite Swing-Arm EMI/RFI Strain Relief

Composite Swing-Arm EMI/RFI Strain Relief. 319-064 Composite Swing-Arm Strain-Relief. Light Weight - Corrosion Free - Three-in-One. Straight, 45 and 90 Degrees Integrated EMI/RFI Shield Sock Inspection Window Self-Locking Coupling Nut Optional Composite Braid (319-065)

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Composite Swing-Arm EMI/RFI Strain Relief

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  1. Composite Swing-Arm EMI/RFI Strain Relief

  2. 319-064 Composite Swing-Arm Strain-Relief • Light Weight - Corrosion Free - Three-in-One • Straight, 45 and 90 Degrees • Integrated EMI/RFI Shield Sock • Inspection Window • Self-Locking Coupling Nut • Optional Composite Braid (319-065) • Brown or Black Material • Electroless Nickel Shield Termination and Interface • No-Braid Version (627-122) • Available Backshell Holding Tool

  3. Composite Ultem 2300 (PEI)Reinforced with Glass • Non Corrosive • 2000+ Hours Salt Spray • Light Weight • 40% Lighter than Aluminum • 80% Lighter than SST • Vibration Dampening • Superior Mechanical Properties • Injection Mold Components for Connectors & Accessories • AIR4567, Type I, Grades A&B, Class 2 • General Duty -65 to -175 Deg C

  4. Performance Testing of Glenair Material 515

  5. Origin of the Swing-Arm: The F-22 Composite Braid Sock Strain Relief • 440-088 and 440-089 Series Shield Sock Parts • Were Developed for the F-22 to Accelerate EMI Shield Termination Assembly Times and Reduce the Weight of Interconnect Cabling

  6. F-22 Shield Sock Performance Testing(Test Report No. 08-0204 Available from Factory Upon Request) • Outstanding Mechanical, Environmental and EMI Performance • Electrical Resistance per AS85049, para 3.5.2 / 4.6.3 • Vibration per AS85049 para 3.5.4 / 4.6.5.3 • Half Sine Shock per AS85049 para 3.5.5 / 4.6.6.2 • Transfer Impedance and Shielding Effectiveness Test Report 2004-1 Available From Factory Upon Request

  7. EMI Shield Termination Procedure • (1) Select Straight, 45 or 90 Degree Angle; (2) Insert Wire Bundle; (3) Mark Support Ring Location; (4) Apply Optional Tape Wrap; (5) Slide Cable Shielding Over Support Ring and Trim to Fit.

  8. EMI Shield Termination Procedure • (6) Evenly Space Shield Pigtails, if any, Around Support Ring; • (7) Slide Backshell Shield Sock Over Support Ring; • (8) Trim and Fold Braid in Place; • (9) Install Band; • (10) Wrap Assembly Area with High Temperature Tape

  9. EMI Shield Termination Procedure • (11) Secure Loose Areas of Shield Sock with Ties or Lacing; • (12) Tighten Backshell to Connector with 600-091 Series Backshell Holding Tool and Torque to 40 to 120 Lbs. (See Catalog Torque Chart). • (13) Tighten Strain-Relief Saddle Bars to Correct Torque: 5.2 lbs Max for #4 Fastener and 10 lbs Max for #6 Fastener. • (14) Use Only Genuine Glenair Tools and Replacement Parts

  10. The Swing-Arm Advantage Operates in a similar manner to the F-22 Shield Sock, but offers three-in-one straight, 45° and 90° design for SKU reduction

  11. Proven Performance Applications The Swing-Arm is perfectly suited for new connector accessory design-ins for the next generation of manned and unmanned aircraft • Approved for use at: • Lockheed Martin • Boeing • Bell Helicopter • Northrop Grumman • Bombardier • Embraer

  12. Swing-Arm Qualification Testing Summary Results

  13. Swing-Arm Qualification Testing Summary Results

  14. For More Information • Please see the April 2007 Issue of QwikConnect • Complete Product Overview • EMI Shield Assembly Instructions • Application References • How to Order and Part Number Development • Same-Day Inventory Listing • Qualification Test Report • Available in Hard Copy or at www.glenair.com

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