Composite Swing-Arm EMI/RFI 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

319-064 Composite Swing-Arm Strain-Relief

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

Composite Ultem 2300 (PEI)Reinforced with Glass

515

Performance Testing of Glenair Material

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

Origin of the Swing-Arm: The F-22 Composite Braid Sock Strain Relief

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

Outstanding Mechanical, Environmental and EMI Performance

F-22 Shield Sock Performance Testing(Test Report No. 08-0204 Available from Factory Upon Request)

(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.

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

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

EMI Shield Termination Procedure

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

The Swing-Arm Advantage

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

Proven Performance Applications

Swing-Arm Qualification Testing Summary Results

Swing-Arm Qualification Testing Summary Results

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

For More Information