857 

Federal Aviation Administration, DOT 

Pt. 43, App. E 

(1) All units—for poor condition and inse-

curity of attachment. 

(2) Shock absorbing devices—for improper 

oleo fluid level. 

(3) Linkages, trusses, and members—for 

undue or excessive wear fatigue, and distor-
tion. 

(4) Retracting and locking mechanism—for 

improper operation. 

(5) Hydraulic lines—for leakage. 
(6) Electrical system—for chafing and im-

proper operation of switches. 

(7) Wheels—for cracks, defects, and condi-

tion of bearings. 

(8) Tires—for wear and cuts. 
(9) Brakes—for improper adjustment. 
(10) Floats and skis—for insecure attach-

ment and obvious or apparent defects. 

(f) Each person performing an annual or 

100-hour inspection shall inspect (where ap-
plicable) all components of the wing and cen-
ter section assembly for poor general condi-
tion, fabric or skin deterioration, distortion, 
evidence of failure, and insecurity of attach-
ment. 

(g) Each person performing an annual or 

100-hour inspection shall inspect (where ap-
plicable) all components and systems that 
make up the complete empennage assembly 
for poor general condition, fabric or skin de-
terioration, distortion, evidence of failure, 
insecure attachment, improper component 
installation, and improper component oper-
ation. 

(h) Each person performing an annual or 

100-hour inspection shall inspect (where ap-
plicable) 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 oper-

ations and obvious defects. 

(4) Control mechanisms—for improper op-

eration, insecure mounting, and restricted 
travel. 

(i) Each person performing an annual or 

100-hour inspection shall inspect (where ap-
plicable) the following components of the 
radio group: 

(1) Radio and electronic equipment—for 

improper installation and insecure mount-
ing. 

(2) Wiring and conduits—for improper rout-

ing, insecure mounting, and obvious defects. 

(3) Bonding and shielding—for improper in-

stallation and poor condition. 

(4) Antenna including trailing antenna—for 

poor condition, insecure mounting, and im-
proper operation. 

(j) Each person performing an annual or 

100-hour inspection shall inspect (where ap-
plicable) each installed miscellaneous item 
that is not otherwise covered by this listing 
for improper installation and improper oper-
ation. 

A

PPENDIX

E 

TO

P

ART

43—A

LTIMETER

 

S

YSTEM

T

EST AND

I

NSPECTION

 

Each person performing the altimeter sys-

tem tests and inspections required by § 91.411 
of this chapter must comply with the fol-
lowing: 

(a) Static pressure system: 
(1) Ensure freedom from entrapped mois-

ture 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 § 25.1325. 

(3) Determine that the static port heater, 

if installed, is operative. 

(4) Ensure that no alterations or deforma-

tions 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 tempera-
ture 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 pres-

sure scale at 29.92 inches of mercury, the al-
timeter shall be subjected successively to 
pressures corresponding to the altitude spec-
ified 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, be-
fore a reading is taken. The error at all test 
points must not exceed the tolerances speci-
fied in Table I. 

(ii) 

Hysteresis. 

The hysteresis test shall 

begin not more than 15 minutes after the al-
timeter’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 de-
scent 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 alti-
tude). The test point shall then be ap-
proached at a rate of approximately 3,000 
feet per minute. The altimeter shall be kept 

VerDate Sep<11>2014 

12:50 Apr 30, 2019

Jkt 247046

PO 00000

Frm 00867

Fmt 8010

Sfmt 8002

Y:\SGML\247046.XXX

247046

spaschal on DSK3GDR082PROD with CFR