Q16-49. What component of the wing flap system shifts
springs should be verified in accordance with the values
rotary motion to linear motion?
provided in the applicable MIM.
Q16-50. Moving the flap control handle to the
3. Inspect mated surfaces for excessive wear,
TAKEOFF position will move the slats to what
separation of plating, and evidence of nicks or
position?
scratches. All parts that show signs of excessive scoring,
Q16-51. The wing control system provides high lift and
pitting, or other surface irregularities should be
drag forces for takeoff and landings. What
replaced. Minor imperfections can sometimes be
other advantages does the wing control
removed with fine crocus cloth or lapping compound,
system provide?
depending on the design and tolerance specifications of
Q16-52. When is the only time a wing sweep self-test
the part.
can be performed?
4. Be sure that all passages and chambers of
Q16-53. What flight control is used to slow down the
the part under repair are clean and free from
aircraft speed by increasing the profile drag?
obstructions.
Q16-54. What type of switch is used to control the
aileron trim system?
NOTE: During the complete repair process,
cleanliness of the work area, as well as the external and
Q16-55. How does an aircraft that does not have trim
internal parts, is a prime consideration. The close
tabs achieve lateral trim?
tolerance mated surfaces within most hydraulic
Q16-56. How is longitudinal trim achieved on an
components are extremely susceptible to damage by
a i rc r a f t t h a t h a s m o v a b l e h o r i z o n t a l
contamination regardless of the manner of
stabilizers and elevators?
introduction.
Following reassembly, the component must be
MAJOR ASSEMBLY
bench tested to verify its proper performance. Usually,
REMOVAL/INSTALLATION
testing will include proof testing, leakage testing to
verify proper internal seal operation, and operational
testing.
LEARNING OBJECTIVE: Recognize the
procedures for removal and installation of
Q u a l i t y a s s u r a n c e ve r i fi c a t i o n i s r e q u i r e d
wings, stabilizers, and flight control surfaces.
throughout the repair process and at the completion of
repair. All repairs must be accomplished as specified in
the "Intermediate Maintenance" section of the
The primary flight control surfaces and some of
applicable MIM or 03 accessories manuals. Steps that
the secondary control surfaces are attached to the
wings and stabilizers of the aircraft. In many instances,
require quality assurance verification are so indicated
the wings and stabilizers are damaged beyond repair.
by appearing in italics, being underlined, or some other
When this occurs, the wings and stabilizers must be
obvious manner. Following repair, partially fill the
removed and sent to a depot-level maintenance facility
component with preservative hydraulic fluid and cap
for repair, and a replacement installed.
and/or plug to prevent contamination.
WINGS
Q16-45. What components connect the wing flaps to
Removal and installation of a wing are major
the main wing assembly?
operations that require experienced personnel and
Q16-46. What is the purpose of the relief valve located
close supervision by a senior petty officer.
in the pressure line ahead of the flap normal
You should read the airframes section of the
system selector valve?
applicable MIM carefully before attempting to remove
Q16-47. In a leading/trailing edge flap system, what is
a wing. This manual will give step-by-step instructions
the full-down deflection of the trailing edge
for wing removal and installation. It is necessary to
flap?
follow these instructions to prevent possible damage
Q16-48. What component provides the power source
caused by failure to disconnect or connect units in the
for the emergency flap system?
proper sequence.
16-49
