[Federal Register Volume 67, Number 209 (Tuesday, October 29, 2002)]
[Rules and Regulations]
[Pages 65871-65872]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 02-27378]



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  Federal Register / Vol. 67, No. 209 / Tuesday, October 29, 2002 / 
Rules and Regulations  

[[Page 65871]]



DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Parts 21 and 29

[Docket No. SW011; Special Conditions No. 29-011-SC]


Special Conditions: Sikorsky Aircraft Corporation Model S-92A 
Helicopter; Use of a Dual-Engine 30-Minute Power Rating

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final special conditions; request for comments.

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SUMMARY: These special conditions are issued for Sikorsky Aircraft 
Corporation (Sikorsky) Model S-92A helicopters. The S-92A helicopters 
will have an unusual feature associated with the use of a dual-engine 
30-minute power rating. The applicable airworthiness regulations do not 
contain adequate or appropriate safety standards for use of this power 
rating. These special conditions contain the additional safety 
standards that the Administrator considers necessary to ensure that 
critical functions of systems will be maintained during use of this 
rating.

DATES: The effective date of these special conditions is October 16, 
2002. Comments must be received on or before December 30, 2002.

ADDRESSES: Comments on these special conditions should be mailed in 
duplicate to: Federal Aviation Administration (FAA), Office of the 
Regional Counsel, Attention: Rules Docket No. SW011, 2601 Meacham 
Blvd., Room 663, Fort Worth, Texas 76137; or delivered in duplicate to 
the Office of the Regional Counsel at the above address. Comments must 
be marked Docket No. SW011. Comments may be inspected in the Rules 
Docket weekdays, except Federal holidays, between 8:30 a.m. and 4:00 
p.m. The Rules Docket for special conditions is maintained at the 
Federal Aviation Administration, Rotorcraft Directorate, 2601 Meacham 
Blvd., Room 448, Fort Worth, Texas 76137.

FOR FURTHER INFORMATION CONTACT: Ed Cuevas, FAA, Rotorcraft 
Directorate, Rotorcraft Standards, Fort Worth, Texas 76193-0110, 
telephone (817) 222-5355, fax (817) 222-5961.

SUPPLEMENTARY INFORMATION: The FAA has determined that notice and 
opportunity for prior public comment hereon are impracticable because 
these procedures would significantly delay issuance of the approval 
design and thus delivery of the affected helicopter. The FAA therefore 
finds that good cause exists for making these special conditions 
effective upon issuance.

Comments Invited

    The FAA invites interested persons to participate in this 
rulemaking by submitting written comments, views, or data. 
Communications should identify the regulatory docket and be submitted 
in duplicate to the address specified above. We will consider all 
comments we receive on or before the closing date for comments. We may 
change these special conditions in light of the comments we receive. 
All comments received 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 rulemaking will be filed in the 
docket. If you want the FAA to acknowledge receipt of your comments on 
this proposal, include a self-addressed, stamped postcard on which the 
docket number appears. We will stamp the date on the postcard and mail 
it back to you.

Background

    For the Model S-92A helicopter, Sikorsky Aircraft Corporation has 
applied for use of a dual-engine 30-minute power rating in addition to 
a maximum continuous power rating. The Sikorsky Model S-92A is a 
transport category A and B rotorcraft, powered by two General Electric 
CT7-8 engines certificated with a dual-engine 30-minute power rating 
greater than the maximum continuous power rating. The S-92A with the 
CT7-8 engine installation will have 30-Second One-Engine-Inoperative 
(OEI), 2-Minute OEI, Continuous OEI, 30-Minute, Takeoff, and Maximum 
Continuous power ratings.
    This unusual dual-engine power capability must be limited to use 
for hovering operations only for periods not to exceed 30 minutes at 
any time after takeoff, to allow the rotorcraft to fly extended hover 
maneuvers while performing search and rescue missions. However, this 
rating is also suitable for other missions that require increased 
rotorcraft hovering capability and duration, beyond those that the 
maximum continuous engine rating allows.
    The S-92A has the same engine torque and rotor speed limits for use 
of aircraft 30-minute power or maximum continuous power ratings. As a 
result, the FAA has determined that compliance with the structural and 
drive system requirements of 14 CFR part 29 (part 29) has not been 
affected by the 30-minute rating application.
    The applicable airworthiness requirements do not contain a 30-
minute power rating definition and do not contain adequate or 
appropriate safety standards for the type certification of this unusual 
engine rating. Due to increased engine N1 (gas turbine 
speed) and T4.5 (power turbine inlet temperature) limits for 
this new rating, as compared to the existing continuous rating, 
airworthiness requirements must be specified for powerplant cooling and 
operational limitations for this novel or unusual design feature.

Type Certification Basis

    Under the provisions of 14 CFR 21.17, Sikorsky Aircraft Corporation 
must show that the Model S-92A helicopter meets the applicable 
provisions of the regulations as follows:
    [sbull] 14 CFR Part 29, Amendment 29-1 through Amendment 29-45, 
inclusive;
    [sbull] 14 CFR Part 29, Appendix H, Amendments 36-1 through the 
amendment effective at the time of certification; and
    [sbull] Any special conditions, exemptions, and equivalent safety 
findings deemed necessary.
    If the Administrator finds that the applicable airworthiness 
regulations for part 29 do not contain adequate or appropriate safety 
standards for the Sikorsky Model S-92A because of a novel or unusual 
design feature, special

[[Page 65872]]

conditions are prescribed under the provisions of Sec.  21.16.
    In addition to the applicable airworthiness regulations and special 
conditions, the Sikorsky Model S-92A must comply with the noise 
certification requirements of 14 CFR part 36, and the FAA must issue a 
finding of regulatory adequacy pursuant to Sec.  611 of Public Law 92-
574, the ``Noise Control Act of 1972.''
    Special conditions, as appropriate, are defined in Sec.  11.19, and 
issued in accordance with Sec.  11.38, and become part of the type 
certification basis in accordance with Sec.  21.17(a)(2).
    Special conditions are initially applicable to the model for which 
they are issued. Should the TC 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 
TC 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 Sec.  21.101(a)(1).

Novel or Unusual Design Features

    The Sikorsky Model S-92A will incorporate the following novel or 
unusual design features: A dual-engine 30-minute power rating which 
will require a special condition for hovering cooling test procedures 
and powerplant limitations.

Applicability

    As discussed above, these special conditions are applicable to the 
Sikorsky Model S-92A. Should Sikorsky Aircraft Corporation apply at a 
later date for a change to the TC 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 
Sec.  21.101(a)(1).

Conclusion

    This action affects only certain novel or unusual design features 
on one model of helicopter. It is not a rule of general applicability 
and affects only the applicant who applied to the FAA for approval of 
these features on the helicopter.
    Under standard practice, the effective date of final special 
conditions would be 30 days after the date of publication in the 
Federal Register; however, as the certification date for the Sikorsky 
Model S-92A is imminent, the FAA finds that good cause exists to make 
these special conditions effective upon issuance.

List of Subjects in 14 CFR Parts 21 and 29

    Aircraft, Air transportation, Aviation safety, Rotorcraft, Safety.

    The authority citation for these special conditions is as follows: 
42 U.S.C. 7572; 49 U.S.C. 106(g), 40105, 40113, 44701-44702, 44704, 
44709, 44711, 44713, 44715, 45303.

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 Sikorsky Model S-92A helicopters.

1. Hovering Cooling Test Procedures

    Acceptable hovering cooling provisions must be shown for the 
following conditions, which replace the requirements of Sec.  29.1049:
    (a) At the maximum weight, or at the greatest weight at which the 
rotorcraft can hover (if less), at sea level, with the power required 
to hover but not more than 30-minute power, in-ground effect with the 
maximum tailwind velocity and azimuths requested for approval, until at 
least 5 minutes after the occurrence of the highest temperature 
recorded or until the expiration of the 30-minute power application 
period, whichever occurs first; and,
    (b) With 30-minute power, maximum weight, and at the altitude 
resulting in zero rate of climb for this configuration, until at least 
5 minutes after the occurrence of the highest temperature recorded or 
until the expiration of the 30-minute power application period, 
whichever occurs first.

2. Powerplant Limitations

    In addition to the requirements of Sec.  29.1521 the limitations 
for rated 30-minute power usage must be established as follows:
Rated 30-Minute Power Operations
    The powerplant rated 30-minute power operation must be limited to 
use for periods not to exceed 30 minutes for hovering operations only 
and limited by:
    (a) The maximum rotational speed which may not be greater than
    (i) The maximum value determined by the rotor design; or
    (ii) The maximum value shown during the type tests;
    (b) The maximum allowable power turbine inlet gas temperature;
    (c) The maximum allowable engine and transmission oil temperatures.
    (d) The maximum allowable power or torque for each engine, 
considering the power input limitations of the transmission with all 
engines operating; and
    (e) The maximum allowable power or torque for each engine 
considering the power input limitations of the transmission with one-
engine-inoperative.

    Issued in Fort Worth, Texas, on October 16, 2002.
David A. Downey,
Manager, Rotorcraft Directorate, Aircraft Certification Service, ASW-
100.
[FR Doc. 02-27378 Filed 10-28-02; 8:45 am]
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