Front View	Back View

The test panel was fabricated with 0.040 inch thick 2024-T3 sheet aluminum. Panel was in a hot water quench material for 55 days for which approximately 0.008 inch depth of intergranular corrosion attack would occur.

2. Large 0.07 Inch Thickness Aluminum Panel (AANC Test Specimen Library Number 111)

This actual aircraft aluminum panel 0.07 inch thick shows areas of pillowing and corrosion around the middle section of the panel. Scanner tests were performed at the 8 inch square section indicated.

3. Tear Strap Disbond Calibration Samples (AANC Test Specimen Library Numbers 183 through 185)

Aluminum sheets 2024-T3. Dimensions are in inches. Top sheet is 0.040 inch, 0.050 inch, 0.070 inch. Bottom sheet is 0.070 inch.

4. Boron/Epoxy Composite Repair Patches (AANC Test Specimen Library Number 152)

Boron epoxy doubler ultrasonic reference standard showing 2 ply, 4 ply, 6 ply and 8 ply sections on a curved Aluminum skin. Teflon implants (0.005 inch thick x 0.5 inch diameter disks) are placed at the bond line and at interfaces between the plies. Pull tabs (0.5 inch wide x 0.75 inch long) were place at the bond line at the left and right edges of each ply. The area of the four plies is 9 inches wide and 12 inches high.

Octagonal shaped boron epoxy patch applied to the skin of the B737 airplane aft of the wing on the left side of the airplane.

5. B737 Airplane Locations (AANC Test Specimen Library Number 100)

The full scale B737 aircraft was received by AANC on October 9, 1992. The aircraft is being used as a commercial transport aircraft test specimen that provides a means to assess human factors issues, accessibility issues, and hangar environment for evaluating NDI inspection requirements.

Aircraft Model: 737-222
Date of Manufacture: July 1968
Airframe Total Hours: 38,342
Airframe Total Cycles: 46,358