C3-14992. Special Conditions: Boeing Model 777 Series Airplanes; Revision to Special Conditions 25-ANM-84

[Federal Register Volume 68, Number 120 (Monday, June 23, 2003)]
[Corrections]
[Pages 37205-37206]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: C3-14992]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 25

[Docket No. NM81; Notice No. 25-03-04-SC]


Special Conditions: Boeing Model 777 Series Airplanes; Revision 
to Special Conditions 25-ANM-84

Correction

    In proposed rule document 03-14992 beginning on page 35335 in the 
issue of Friday, June 13, 2003 make the following correction:
    On page 35344, starting in the first column, paragraphs (e)(6) and 
(e)(7) should be presented in italics as set forth below:

PART 25--[CORRECTED]

    (6) Engine Demonstration Test. One engine of each type to be 
certificated with the airplane must complete 3000 equivalent airplane 
operational cycles. The engine must be configured with a complete 
airplane nacelle package for this demonstration, including engine-
mounted equipment except for any configuration differences necessary to 
accommodate test instrumentation and test stand interfaces with the 
engine nacelle package. At completion of the engine demonstration test, 
the engine and airplane nacelle test hardware must undergo a complete 
teardown inspection. This inspection must be conducted in a manner to 
identify abnormal conditions that could become potential sources of 
engine inflight shutdown. An analysis of any abnormal conditions found 
must consider the possible consequences of similar occurrences in 
service to determine if they may become sources of engine inflight 
shutdowns, power loss, or inability to control engine thrust. Any 
potential sources of engine inflight shutdown identified must be 
corrected in accordance with paragraph (g)(2).
    (7) Airplane Demonstration Test. In addition to the function and 
reliability testing required by 14 CFR 21.35(b)(2), for each engine 
type to be certificated with the airplane, one or more airplanes must 
complete flight testing which demonstrates that the aircraft, its 
components, and equipment, are capable of and function properly during 
long range operations and airplane diversions, including engine-
inoperative diversions.
    (i) The flight conditions must expose the airplane to 
representative operational variations based on the airplane's system 
and equipment design and the intended use of the airplane including:
    (A) Engine inoperative maximum length diversions to demonstrate the 
airplane and propulsion system's capability to safely conduct a 
diversion.
    (B) Non-normal conditions to demonstrate the airplane's capability 
to safely divert under worst case probable system failure conditions.
    (C) Simulated airline operations including normal cruise altitudes, 
step climbs, and maximum expected flight durations out of and into a 
variety of departure and arrival airports.
    (D) Diversions to worldwide airports representative of those 
intended as operational alternates.
    (E) Repeated exposure to humid and inclement weather on the ground 
followed by long-range operation at normal cruise altitude.
    (ii) The flight testing must validate expected airplane flying 
qualities and performance considering engine failure, electrical power 
losses, etc. The testing must demonstrate the adequacy of remaining 
airplane systems and performance and flightcrew ability to deal with an 
emergency considering remaining flight deck information following 
expected failure conditions.
    (iii) The engine-inoperative diversions must be evenly distributed 
among the number of engines in the applicant's flight test program.

[[Page 37206]]

    (iv) The test airplane(s) must be operated and maintained using the 
recommended operations and maintenance manual procedures during the 
airplane demonstration test.
    (v) At completion of the airplane demonstration test, the test 
engines and engine-mounted equipment must undergo a complete external 
on-wing visual inspection. The engines must also undergo a complete 
internal visual inspection. These inspections must be conducted in a 
manner to identify abnormal conditions that could become potential 
sources of engine inflight shutdowns. An analysis of any abnormal 
conditions found must consider the possible consequences of similar 
occurrences in service to determine if they may become sources of 
engine inflight shutdowns. Any potential sources of engine inflight 
shutdown that are identified must be corrected in accordance with 
paragraph (g)(2).

[FR Doc. C3-14992 Filed 6-20-03; 8:45 am]
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