spaschal on DSK3GDR082PROD with CFR

Federal Aviation Administration, DOT

Pt. 43, App. E

(1) All units - for poor condition and insecurity of attachment.
(2) Shock absorbing devices - for improper
oleo fluid level.
(3) Linkages, trusses, and members - for
undue or excessive wear fatigue, and distortion.
(4) Retracting and locking mechanism - for
improper operation.
(5) Hydraulic lines - for leakage.
(6) Electrical system - for chafing and improper operation of switches.
(7) Wheels - for cracks, defects, and condition of bearings.
(8) Tires - for wear and cuts.
(9) Brakes - for improper adjustment.
(10) Floats and skis - for insecure attachment and obvious or apparent defects.
(f) Each person performing an annual or
100-hour inspection shall inspect (where applicable) all components of the wing and center section assembly for poor general condition, fabric or skin deterioration, distortion,
evidence of failure, and insecurity of attachment.
(g) Each person performing an annual or
100-hour inspection shall inspect (where applicable) all components and systems that
make up the complete empennage assembly
for poor general condition, fabric or skin deterioration, distortion, evidence of failure,
insecure attachment, improper component
installation, and improper component operation.
(h) Each person performing an annual or
100-hour inspection shall inspect (where applicable) the following components of the
propeller group:
(1) Propeller assembly - for cracks, nicks,
binds, and oil leakage.
(2) Bolts - for improper torquing and lack
of safetying.
(3) Anti-icing devices - for improper operations and obvious defects.
(4) Control mechanisms - for improper operation, insecure mounting, and restricted
travel.
(i) Each person performing an annual or
100-hour inspection shall inspect (where applicable) the following components of the
radio group:
(1) Radio and electronic equipment - for
improper installation and insecure mounting.
(2) Wiring and conduits - for improper routing, insecure mounting, and obvious defects.
(3) Bonding and shielding - for improper installation and poor condition.
(4) Antenna including trailing antenna - for
poor condition, insecure mounting, and improper operation.
(j) Each person performing an annual or
100-hour inspection shall inspect (where applicable) each installed miscellaneous item
that is not otherwise covered by this listing
for improper installation and improper operation.

APPENDIX E TO PART 43 - ALTIMETER
SYSTEM TEST AND INSPECTION
Each person performing the altimeter system tests and inspections required by Section 91.411
of this chapter must comply with the following:
(a) Static pressure system:
(1) Ensure freedom from entrapped moisture and restrictions.
(2) Perform a proof test to demonstrate the
integrity of the static pressure system in a
manner acceptable to the Administrator. For
airplanes certificated under part 25 of this
chapter, determine that leakage is within
the tolerances established by Section 25.1325.
(3) Determine that the static port heater,
if installed, is operative.
(4) Ensure that no alterations or deformations of the airframe surface have been made
that would affect the relationship between
air pressure in the static pressure system
and true ambient static air pressure for any
flight condition.
(b) Altimeter:
(1) Test by an appropriately rated repair
facility in accordance with the following
subparagraphs. Unless otherwise specified,
each test for performance may be conducted
with the instrument subjected to vibration.
When tests are conducted with the temperature substantially different from ambient
temperature of approximately 25 degrees C.,
allowance shall be made for the variation
from the specified condition.
(i) Scale error. With the barometric pressure scale at 29.92 inches of mercury, the altimeter shall be subjected successively to
pressures corresponding to the altitude specified in Table I up to the maximum normally
expected operating altitude of the airplane
in which the altimeter is to be installed. The
reduction in pressure shall be made at a rate
not in excess of 20,000 feet per minute to
within approximately 2,000 feet of the test
point. The test point shall be approached at
a rate compatible with the test equipment.
The altimeter shall be kept at the pressure
corresponding to each test point for at least
1 minute, but not more than 10 minutes, before a reading is taken. The error at all test
points must not exceed the tolerances specified in Table I.
(ii) Hysteresis. The hysteresis test shall
begin not more than 15 minutes after the altimeter-s initial exposure to the pressure
corresponding to the upper limit of the scale
error test prescribed in subparagraph (i); and
while the altimeter is at this pressure, the
hysteresis test shall commence. Pressure
shall be increased at a rate simulating a descent in altitude at the rate of 5,000 to 20,000
feet per minute until within 3,000 feet of the
first test point (50 percent of maximum altitude). The test point shall then be approached at a rate of approximately 3,000
feet per minute. The altimeter shall be kept

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