(a) The Altimeter system and altitude reporting equipment tests and inspections must be conducted by - (1) the manufacturer of the airplane, or helicopter, on which the tests and    

 inspections are to be performed; (2) a certificated repair station properly equipped to perform those functions and 
holding –

(i)   an instrument rating, Class I;

(ii)    a limited instrument rating appropriate to the make and model of appliance 
                                         to be tested;

(iii) a limited rating appropriate to the test to be performed;

(iv)   an airframe rating appropriate to the airplane, or helicopter, to be tested; or
 (3) any “E” licence AME (for aircraft with an MCTOW 5700 Kg or less) or an “E” licence 

         AME trained on the type of aircraft with an MCTOW greater than 5700kg.

(b) Altimeter and altitude reporting equipment approved under Technical Standard Orders are considered to be tested and inspected as of the date of their manufacture. (c) Each person performing the altimeter system tests and inspections required by schedule 10 shall comply with the following:
 

I.   Static pressure system -

(1) ensure freedom from entrapped moisture and restrictions.

(2) determine that leakage is within the tolerances established in the aircraft certification  rule.

(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. 

II.   Altimeter -

(5) 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 at this pressure for at least 5 minutes, but not more than 15 minutes, before the test reading is taken. After the reading has been taken, the pressure shall be increased further, in the same manner as before, until the pressure corresponding to the second test point (40 percent of maximum altitude) is reached. The altimeter shall be kept at this pressure for at least 1 minute, but not more than 10 minutes, before the test reading is taken. After the reading has been taken, the pressure shall be increased further, in the same manner as before, until atmospheric pressure is reached. The reading of the altimeter at either of the two test points shall not differ by more than the tolerance specified in Table II from the reading of the altimeter for the corresponding altitude recorded during the scale error test prescribed in paragraph (b)(i).
　
中國航空網 www.k6050.com
航空翻譯 www.aviation.cn
本文鏈接地址：飛機持續適航 CONTINUING AIRWORTHINESS OF AIRCRAFT(19)