Figure 7-62.  Curing the repair. reasons, unless the part is lightly loaded, this type of repair  is usually performed at a repair facility where the part can be  inserted into the autoclave, which can result in part strength  as strong as the original part. There are several different repair methods for solid  laminates. The patch can be precured and then secondarily  bonded to the parent material. This procedure most closely  approximates the bolted repair.  [Figure 7-64]  The patch  can be made from prepreg and then co-cured at the same  time as the adhesive. The patch can also be made using a  wet layup repair. The curing cycle can also vary in length  of time, cure temperature, and cure pressure, increasing the  number of possible repair combinations.  Scarf repairs of composite laminates are performed in the  sequence of steps described below. The size and depth of damage to be repaired must be accurately  surveyed using appropriate nondestructive evaluation (NDE)  techniques. A variety of NDE techniques can be used to  Fourth, the adhesive can run to the bottom of the joint,  creating a nonuniform bond line. This can be alleviated by  approximating the scarf with a series of small steps. For these  Figure 7-63.  Post-repair inspection.  7-38 Time Temperature (°F) 250 175 100 70 Temperature (°C) 121 80 38 21 Note: Keep a minimum vacuum of 22 inches of mercury during the cure cycle. NO SCALE Ramp up Ramp down Soak Increase the temperature °F to 5 °F (0.5 °C to °C) per minute Decrease the temperature °F/minute (3 °C/minute)  maximum Below 125 °F (52 °C) release the pressure and  remove the layup and vacuum bag materials Hold for 90 to 150  minutes at 260 °F + 6 °F (126 °C + 6 °C) Repair Heat affected area Heat blanket area Step 1: Inspection and Mapping of Damage