[Federal Register Volume 68, Number 247 (Wednesday, December 24, 2003)]
[Rules and Regulations]
[Pages 74469-74471]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 03-31734]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 33

[Docket No. NE126; Special Conditions No. 33-005-SC]


Special Conditions: General Electric Aircraft Engines, Model CT7-
8A, -8A5, -8B, -8B5, -8E, -8E5, -8F, and -8F5 Engines

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final special conditions; request for comments.

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SUMMARY: The FAA is issuing special conditions for the General Electric 
Aircraft Engines (GEAE) models CT7-8A, CT7-8A5, CT7-8B, CT7-8B5, CT7-
8E, CT7-8E5, CT7-8F, CT7-8F5, engines. On August 2, 2000, the FAA 
issued Special Conditions (SC) No. 33-003-SC for the GEAE CT7-6e, and 
CT7-8, turboshaft engines. The CT7-8A, CT7-8A5, CT7-8B, CT7-8B5, CT7-
8E, CT7-8E5, CT7-8F, CT7-8F5 engines will have a novel or unusual rated 
30-minute power, and rated continuous one engine inoperative (OEI) 
power. The

[[Page 74470]]

applicable airworthiness regulations do not contain adequate or 
appropriate safety standards for this design feature. This document 
contains the additional safety standards that the Administrator 
considers necessary to establish a level of safety equivalent to that 
established by the existing airworthiness standards.

DATES: The effective date of these special conditions is December 31, 
2003. The FAA must receive comments on or before January 31, 2004.

ADDRESSES: Mail or deliver comments on these special conditions to: 
Federal Aviation Administration, Office of the Assistant Chief Counsel, 
Attention: Rules Docket NE126. You must identify the docket number 
NE126 at the beginning of your comments, and you should submit two 
copies of your comments. You may review the public docket containing 
comments to these special conditions in person at the Office of the 
Regional Counsel between 8 a.m. and 4:30 p.m., Monday through Friday, 
except Federal holidays.

FOR FURTHER INFORMATION CONTACT: Chung Hsieh, FAA, Engine and Propeller 
Standards Staff, Engine and Propeller Directorate, Aircraft 
Certification Service, ANE-110, 12 New England Executive Park, 
Burlington, Massachusetts, 01803-5229; telephone (781) 238-7115; fax 
(781) 238-7199; e-mail [email protected].

SUPPLEMENTARY INFORMATION: The FAA has determined that notice and 
opportunity for prior public comment hereon are impracticable because 
these procedures would significantly delay the issuance of the design 
approval, and, as a result delay the delivery of aircraft with these 
engines installed. In addition, the substance of these special 
conditions has been subject to the public comment process on a prior 
occasion with no substantive comments received. The FAA, therefore, 
finds that good cause exists for making these special conditions 
effective upon issuance.

Comments Invited

    The FAA has determined that good cause exists for making these 
special conditions effective December 31, 2003; however, the FAA 
invites interested parties to submit comments on the special 
conditions. Comments should identify the Rules Docket and special 
conditions number and be submitted in duplicate to the address 
specified above. The FAA will consider all comments received by the 
closing date. These special conditions may be changed in light of the 
comments received. All comments submitted will be available in the 
Rules 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 proposal 
will be filed in the docket. Commenters wishing the FAA to acknowledge 
receipt of their comments submitted in response to this notice must 
include a self-addressed, stamped postcard on which the following 
statement is made: ``Comments to Docket No. NE126.'' The postcard will 
be date-stamped and returned to the commenter.

Background

    On March 12, 2003, General Electric Aircraft Engines (GEAE) applied 
for an amendment to Type Certificate No. E8NE to include the new model 
CT7-8A turboshaft engine. The application was subsequently amended to 
include the CT7-8A5, CT7-8B, CT7-8B5, CT7-8E, CT7-8E5, CT7-8F, and CT7-
8F5 engines. These engine models, which are derivatives of the CT7-8 
currently approved under Type Certificate (TC) No. E8NE, will have the 
same engine rating structure as the CT7-8 model except that they will 
include rated continuous one engine inoperative (OEI) power instead of 
rated 30-minute OEI power. These engine models will be rated at 30-
second OEI, 2-minute OEI, continuous OEI, 30-minute, takeoff, and 
maximum continuous ratings. The requirements in the existing 
regulations do not contain adequate or appropriate safety standards of 
this new and unusual engine rating structure.
    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 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 for each period, must be 25 hours for 
certification. However, when the CT7-8A, CT7-8A5, CT7-8B, CT7-8B5, CT7-
8E, CT7-8E5, CT7-8F, or CT7-8F5 engine models have a rated continuous 
OEI power equal to or higher than rated 30-minute power, the test run 
time of 25 hours under Sec.  33.87(d) may be credited to satisfy the 
required running time of 25 hours at rated 30-minute power.

Type Certification Basis

    Under the provisions of 14 CFR Sec.  21.101, GEAE must show that 
the CT7-8A, CT7-8A5, CT7-8B, CT7-8B5, CT7-8E, CT7-8E5, CT7-8F, CT7-8F5 
turboshaft engines meet the applicable provisions of the regulations 
incorporated by reference in TC No. E8NE or the applicable regulations 
in effect on the date of application for the change to the CT7-8. The 
regulations incorporated by reference in the TC are commonly referred 
to as the ``original type certification basis.'' The regulations 
incorporated by reference in TC No. E8NE are part 33, effective 
February 1, 1965, as amended by amendments 33-1 through 33-19 and 
Special Conditions Numbers 33-002-SC and 33-003-SC.
    If the Administrator finds that the applicable airworthiness 
regulations (i.e., 14 CFR part 33) do not contain adequate or 
appropriate safety standards for the CT7-8A, CT7-8A5, CT7-8B, CT7-8B5, 
CT7-8E, CT7-8E5, CT7-8F, CT7-8F5 engines because of a novel or unusual 
design 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, as required by 14 CFR 11.28 and 11.29(b), and become part 
of the type certification basis in accordance with 14 CFR 21.101(b)(2).
    Special conditions are initially applicable to the model for which 
they are issued. Should the type certificate for that model be amended 
later to include any other model that incorporates the same novel or 
unusual design feature, or should any other model already included on 
the same type certificate be modified to incorporate the same novel or 
unusual design feature, the special conditions would also apply to the 
other model under the provisions of 14 CFR 21.101(a)(1).

Novel or Unusual Design Features

    The GEAE CT7-8A, CT7-8A5, CT7-8B, CT7-8B5, CT7-8E, CT7-8E5, CT7-8F, 
and CT7-8F5 turboshaft engines will incorporate the following novel or 
unusual design feature: rated 30-minute power. The power available for 
rotorcraft hovering to perform search and rescue or similar missions is 
limited to the maximum continuous rating power under the current part 
33 requirements. The rated 30-minute power will 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

[[Page 74471]]

power for hovering operations calling for greater than maximum 
continuous power.

Applicability

    As discussed above, these special conditions apply to the CT7-8A, 
CT7-8A5, CT7-8B, CT7-8B5, CT7-8E, CT7-8E5, CT7-8F, and CT7-8F5 
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 these models of 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 engine.
    The substance of these special conditions has been subjected to the 
notice and comment period in one prior instance and has been derived 
without substantive change from those previously issued. The FAA has 
determined that prior public notice and comment are unnecessary and 
that good cause exists for adopting these special conditions 
immediately. Therefore, these special conditions are being made 
effective December 31, 2003. The FAA is, however, requesting comments 
to allow interested parties to submit views that may not have been 
submitted in response to the prior opportunities for comment described 
above.

List of Subjects in 14 CFR Part 33

    Air transportation, Aircraft, Aviation safety, Safety.

    The authority citation for these special conditions is as follows:

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

The Special Conditions

    Accordingly, pursuant to the authority delegated to me by the 
Administrator, the following special conditions are issued as part of 
the type certification basis for GEAE model CT7-8A, CT7-8A5, CT7-8B, 
CT7-8B5, CT7-8E, CT7-8E5, CT7-8F, and CT7-8F5 turboshaft engines. The 
type certificate basis for the CT7-8A, CT7-8A5, CT7-8B, CT7-8B5, CT7-
8E, CT7-8E5, CT7-8F, and CT7-8F5 engines is part 33, effective February 
1, 1965, as amended by amendments 33-1 through 33-19 and Special 
Conditions Numbers 33-002-SC and 33-005-SC.
    (a) Section 33.4, Instructions for Continued Airworthiness (ICA). 
In addition to the requirements of Sec.  33.4, the 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.
    (b) Section 33.7, Engine Ratings and Operating Limitations. In 
addition to the ratings provided in Sec.  33.7, a rated 30-minute power 
is available. 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 part 33 
and limited in use to periods of not over 30 minutes each.
    (c) Section 33.87, Endurance Test. Unless already substantiated by 
the tests run under Sec.  33.87(d), in addition to the requirements of 
Sec.  33.87, conduct the following test:
    Rated 30-minute power: One hour and ten minutes at alternate 5-
minute periods at maximum continuous power, and 30-minute periods at 
rated 30-minute power during the 25 six-hour endurance test cycles.

    Issued in Burlington, Massachusetts, on December 17, 2003.
Peter A. White,
Acting Manager, Engine and Propeller Directorate, Aircraft 
Certification Service.
[FR Doc. 03-31734 Filed 12-23-03; 8:45 am]
BILLING CODE 4910-13-M