[Federal Register: December 24, 2003 (Volume 68, Number 247)]
[Rules and Regulations]
[Page 74469-74471]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr24de03-3]
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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
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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 chung.hsieh@faa.gov.
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
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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