[Federal Register Volume 65, Number 155 (Thursday, August 10, 2000)]
[Rules and Regulations]
[Pages 48887-48888]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 00-20272]



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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 33

[Docket No. NE122; Special Conditions No. 33-003-SC]


Special Conditions: General Electric Aircraft Engines Model CT7-
6E and CT7-8 Turboshaft Engines

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final special conditions; request for comments.

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SUMMARY: These special conditions are issued for General Electric 
Aircraft Engines (GEAE) models CT7-6E and CT7-8 turboshaft engines. 
These engines will have a novel or unusual rated 30-minute power that 
makes the issue of these special conditions necessary. The existing 
airworthiness regulations do not contain adequate or appropriate safety 
standards for this design feature. These special conditions contain the 
additional safety standards the Administrator considers to establish a 
level of safety equivalent to that established by existing 
airworthiness standards. The rated 30-minute power provides necessary 
increased rotorcraft hover time to enable operators to better perform 
critical, life-saving search and rescue missions. For this reason and 
because a delay would not be in the public interest, the FAA has 
determined that good cause exists for adopting these special conditions 
immediately upon publication.

DATES: The effective date of these special conditions is August 10, 
2000. Comments must be received on or before September 11, 2000.

ADDRESSES: Comments on these special conditions may be mailed in 
duplicate to: Federal Aviation Administration, Office of the Regional 
Counsel, Attention: Docket NE122; 12 New England Executive Park, 
Burlington, Massachusetts 01803-5299, or delivered in duplicate to the 
Office of the Regional Counsel at the above address. Comments must be 
marked: Docket No. NE122. Comments may be inspected in the Docket 
weekdays, except for Federal holidays, between 8 a.m. and 4:30 p.m.

FOR FURTHER INFORMATION CONTACT: Mr. Chung Hsieh, Engine and Propeller 
Standards Staff, ANE-110, Engine and Propeller Directorate, Aircraft 
Certification Service, FAA, New England Region, 12 New England 
Executive Park, Burlington, Massachusetts 01803-5229; (781) 238-7115; 
Fax (781) 238-7199. If you have access to the Internet, you may also 
obtain further information by writing to the following Internet 
address: ``[email protected]''.

SUPPLEMENTARY INFORMATION:

Comments Invited

    The FAA has determined that good cause exists for making these 
special conditions effective upon issuance; however, interested persons 
are invited to submit such written data, views, or arguments as they 
may desire. Communications should identify the docket number and 
special conditions number, and be submitted in duplicate to the address 
specified above, or, if you have access to the internet, you may make a 
submission to the following Internet address: ``[email protected]''. 
All communications received on or before the closing date for comments 
will be considered by the Administrator. These special conditions may 
be changed in light of the comments received. All comments submitted 
will be available in the docket for examination by interested persons, 
both before and after the closing date for comments. A report 
summarizing each substantive public contact with FAA personnel 
concerning this rulemaking will be filed in the docket. Persons wishing 
the FAA to acknowledge receipt of their comments submitted in response 
to this request must submit with those comments a self-addressed, 
stamped postcard on which the following statement is made: ``Comments 
to Docket No. NE122.'' The postcard will be date-stamped and returned 
to the commenter.

Background

    On August 12, 1996, GEAE applied for an amendment to Type 
Certificate No. E8NE to include new models CT7-6 and CT7-8 turboshaft 
engines. These models, derivatives of the CT7-6 series turboshaft 
engine, will include new rated 30-second and 2-minute one-engine-
inoperative (OEI) power. On March 10, 2000, GEAE requested an 
additional rated 30-minute power for models CT7-6E and CT7-8 turboshaft 
engines. This rating is intended for use after takeoff, for up to 30 
minutes at any time between takeoff and landing during any flight when 
performing search and rescue missions. These engine models will be 
rated at 30-second OEI, 2-minute OEI, 30-minute OEI, 30-minute, 
takeoff, and maximum continuous ratings. The existing requirements do 
not contain a definition for a rated 30-minute power, and do not 
contain adequate or appropriate safety standards of this new and 
unusual engine rating.
    The rated 30-minute power is the approved brake horsepower 
developed under static conditions at specified altitudes and 
temperatures within the operating limitations established under 14 CFR 
part 33 for periods of use no longer than 30 minutes each. This rating 
power would provide for rotorcraft hovering operations at a power level 
greater than maximum continuous power. The certification requirements 
have been defined around the worst case scenario of unrestricted 
periods of use up to 30 minutes each in one flight. Therefore, the 
total accumulated time for endurance testing of 30-minute periods at 
rated 30-minute power must be 25 hours for certification. However, 
because the CT7-6E and -8 engine models have a rated 30-minute OEI at 
higher power and engine limitations than rated 30-minute power, the 
test run time of 12.5 hours under 33.87(c) may be credited to satisfy 
one half of the required running time for rated 30-minute power. The 
additional endurance test runs required for these engine models would 
therefore be 25 periods of test at rated 30-minute power for 30 minutes 
each.

Type Certification Basis

    Under 14 CFR 21.101, GEAE must show that the models CT7-6E and CT7-
8 turboshaft engines meet the requirements of the applicable 
regulations in effect on the date of the application, or the applicable 
provisions of the regulations incorporated by reference in Type 
Certificate No. E8NE. The regulations incorporated by reference in the 
type certificate are commonly referred to as the ``original type 
certification basis''. Since models CT7-6E and CT7-8 engines are 
derivatives of the model CT7-6 series turboshaft engine, the 
regulations incorporated by reference of the engine in Type Certificate 
No. E8NE are part 33, effective February 1, 1965, as amended by 
Amendments 33-1 through 33-5; Sec. 33.87, Amendment 12; and Special 
Conditions Number 33-76-NE-2, Docket No. 16921 (issued October 31, 
1978). However, GEAE has elected to demonstrate compliance of later 
amendments of part 33 for the engines. The certification basis for 
models CT7-6E and CT7-8 turboshaft engines will be part 33, effective 
February 1, 1965, as amended by Amendments 33-1 through 33-19; and 
Special Conditions No. 33-002-SC, Docket No. NE121, published on May 
28, 1999 (64 FR 28900).
    The Administrator finds that the applicable airworthiness 
regulations in part 33, as amended, do not contain adequate or 
appropriate safety standards for the new rated 30-minute power for 
engine models CT7-6E and CT7-8

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turboshaft engines. Because it is a novel or unusual engine rating 
feature, special conditions are prescribed under the provisions of 14 
CFR 21.16.
    Special conditions, as appropriate, are issued in accordance with 
14 CFR 11.49 after public notice, as required by Secs. 11.28 and 
11.29(b), and became part of the type certification basis in accordance 
with 14 CFR 21.101(b)(2).

Novel or Unusual Design Features

    The GEAE engine models CT7-6E and CT7-8 turboshaft engines will 
incorporate the following novel or unusual design feature: Rated 30-
minute power. The power available for rotocrafts hovering to perform 
search and rescue missions is limited to the maximum continuous rating 
power under the current part 33 requirements. The proposed rated 30-
minute power would provide a higher power level than currently 
available for use up to 30 minutes at any time between takeoff and 
landing during any flight. This new rating will enhance rotorcraft 
safety through the availability of increased power for hovering 
operations calling for greater than maximum continuous power.

Applicability

    As discussed above, these special conditions are applicable to the 
GEAE models CT7-6E and CT7-8 turboshaft engines. Should GEAE apply at a 
later date for a change to the type certificate to include another 
model incorporating the same novel or unusual design feature, the 
special conditions would apply to that model as well under the 
provisions of 14 CFR 21.101(a)(1).

Conclusion

    This action affects only certain novel or unusual design features 
on GEAE models CT7-6E and CT7-8 turboshaft engines. It is not a rule of 
general applicability, and it affects only the applicant who applied to 
the FAA for approval of these features on the engines.

List of Subjects in 14 CFR Part 33

    Air transportation, Aircraft, Aviation safety, Safety.

    The authority citations for these special conditions is as follows:

    Authority: 49 U.S.C. 106(g), 40113, 44701-44702, 44704.

The Special Conditions

    Accordingly, the Federal Aviation Administration (FAA) proposes the 
following special conditions as part of the type certification basis 
for the GEAE models CT7-6E and CT7-8 turboshaft engines:


Sec. 33.4  Instructions for Continued Airworthiness (ICA).

    (a) In addition to the requirements of Sec. 33.4, the Instructions 
for Continued Airworthiness (ICA) procedures must:
    (1) Ensure that the engine deterioration in service will not exceed 
the level shown in certification using the rated 30-minute power.
    (2) Be included in the airworthiness limitations section of the 
ICA.


Sec. 33.7  Engine Ratings and Operating Limitations.

    (b) In addition to the ratings provided in Sec. 33.7, a rated 30-
minute power is available, which shall be defined as the approved brake 
horsepower developed under static conditions at specified altitudes and 
temperatures within the operating limitations established under part 33 
of this chapter, and limited in use to periods of not over 30 minutes 
each.


Sec. 33.87  Endurance Test.

    (c) The test requirements of Sec. 33.87(a), (c), and (f), except 
that the first 35 minutes of the two hour test required by paragraph 
(c)(3) must be run at rated maximum continuous power for 5 minutes and 
then at rated 30-minute power for 30 minutes, in each of the 25 six-
hour endurance test sequences.

    Issued in Burlington, Massachusetts on August 2, 2000.
David A. Downey,
Assistant Manager, Engine and Propeller Directorate, Aircraft 
Certification Service.
[FR Doc. 00-20272 Filed 8-9-00; 8:45 am]
BILLING CODE 4910-13-M