What you will study
Find the actual member
Follow skin, frames, stringers and bulkheads; locate FS 84.00/347.75 boundaries and the six-rivet flat-web/zee-stiffener connection. Keep partial rework and side-specific kit identity explicit.
Interpret the measured damage
Compare controlled bonded-panel reference zones with a known competing drain-tube response. Evaluate depth, affected area and required spacing under the actual material/access branch.
Preserve the joint configuration
Distinguish early tension and later lower-forward shear joints, upper soft aluminum washers and installed spar-bridge expansion/clamp-up hardware.
Verify post-repair restoration
Use directional elevator, rudder and aircraft-specific aileron moment bands; distinguish stabilizer fit, installation torque, nonrotation checks and control restoration.
Learning outcomes
- Locate the pressure vessel and distinguish primary load-carrying structure from secondary fairings.
- Plan an inspection around actual floorline, bulkhead, opening and attachment locations.
- Locate the six-rivet flat-web inspection area and use side, stringer number and actual repair status.
- Locate the aft drainage paths and preserve protection at wing joints and fuel-bay interfaces.
- Use known reference zones and distinguish a suspected separation from a drain-tube sound change.
- Apply depth, affected area and spacing criteria to named secondary skins and keep the wing-upper exception separate.
- Read the actual joint configuration and keep tension, shear and expansion-bolt records separate.
- Calculate balance moment with explicit nose/tail direction, correct tare and the actual surface/model range.
- Interpret the actual horizontal/vertical stabilizer gap and fastener checks without mixing their joints.
- Connect each disturbed structural boundary to its measured recheck and required restoration.
Aircraft and course applicability
Original training based on supplied 101-590010-19 Chapters 51, 53, 55 and 57. Includes named structural inspections, moisture paths, bounded secondary-skin damage measurements, wing-joint configuration and post-repair control-surface balance. Model, serial, repair and kit branches remain explicit. It does not provide new repair design, strength substantiation, a complete SIRM/airworthiness-limitation inspection program, specialized absorber tuning or aircraft release authority. Chapter LEPs: 51/55 January 1, 2019; 53/57 November 1, 2024; individual task dates vary. Current online currency has not been verified.
WWAOG provides independent training. Online completion records knowledge and simulation achievement; it does not replace observed practical qualification, employer authorization or applicable licensing. Use current aircraft-effective maintenance instructions for physical work.
