[Federal Register Volume 79, Number 250 (Wednesday, December 31, 2014)]
[Rules and Regulations]
[Pages 78694-78696]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2014-30562]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 29

[Docket No. FAA-2014-1090; Special Conditions No. 29-037-SC]


Special Conditions: Airbus Helicopters Deutschland GmbH Model 
MBB-BK117D-2 Helicopters; Use of 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 the Airbus Helicopters 
Deutschland GmbH Model MBB-BK117 D-2 helicopter. This model helicopter 
will have the novel or unusual design feature of a 30-minute power 
rating, generally intended to be used for hovering at increased power 
for search and rescue missions. The applicable airworthiness 
regulations do not contain adequate or appropriate safety standards for 
this design feature. These special conditions contain 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: This action is effective on Airbus Helicopters Deutschland GmbH 
Model MBB-BK117D-2 Helicopters on December 19, 2014.
    We must receive your comments by March 2, 2015.

ADDRESSES: Send comments identified by docket number FAA-2014-1090 
using any of the following methods:
    [ssquf] Federal eRegulations Portal: Go to http://www.regulations.gov and follow the online instructions for sending your 
comments electronically.
    [ssquf] Mail: Send comments to Docket Operations, M-30, U.S. 
Department of Transportation (DOT), 1200 New Jersey Avenue SE., Room 
W12-140, West Building Ground Floor, Washington, DC 20590-0001.
    [ssquf] Hand Delivery of Courier: Take comments to Docket 
Operations in Room W12-140 of the West Building Ground Floor at 1200 
New Jersey Avenue SE., Washington, DC, between 8 a.m., and 5 p.m., 
Monday through Friday, except Federal holidays.
    [ssquf] Fax: Fax comments to Docket Operations at 202-493-2251.
    Privacy: The FAA will post all comments it receives, without 
change, to http://regulations.gov, including any personal information 
the commenter provides. Using the search function of the docket Web 
site, anyone can find

[[Page 78695]]

and read the electronic form of all comments received into any FAA 
docket, including the name of the individual sending the comment (or 
signing the comment for an association, business, labor union, etc.). 
DOT's complete Privacy Act Statement can be found in the Federal 
Register published on April 11, 2000 (65 FR 19477-19478), as well as at 
http://DocketsInfo.dot.gov.
    Docket: You can read the background documents or comments received 
at http://www.regulations.gov. Follow the online instructions for 
accessing the docket or go to the Docket Operations in Room @12-140 of 
the West Building Ground Floor at 1200 New Jersey Avenue SE., 
Washington, DC, between 9 a.m., and 5 p.m., Monday through Friday, 
except Federal holidays.

FOR FURTHER INFORMATION CONTACT: Rao Edupuganti, Rotorcraft Standards 
Staff, ASW-111, Rotorcraft Directorate, Aircraft Certification Service, 
2601 Meacham Blvd., Fort Worth, Texas 76137; telephone (817) 222-4389; 
email <a href="/cdn-cgi/l/email-protection#3a485b55145f5e4f4a5b5d5b544e537a5c5b5b145d554c"><span class="__cf_email__" data-cfemail="95e7f4fabbf0f1e0e5f4f2f4fbe1fcd5f3f4f4bbf2fae3">[email protected]</span></a>.

SUPPLEMENTARY INFORMATION:

Reason for No Prior Notice and Comment Before Adoption

    The FAA has determined that notice and opportunity for public 
comment are impractical and contrary to the public interest because the 
issuance of a design approval would significantly delay delivery of the 
affected aircraft. Therefore, we find that good cause exists for making 
these special conditions effective upon issuance.

Comments Invited

    While we did not precede this with a notice of proposed special 
conditions, we invite interested people to take part in this rulemaking 
by sending written comments, data, or views. The most helpful comments 
reference a specific portion of the special conditions, explain the 
reason for any recommended change, and include supporting data.
    We will consider all comments we receive by the closing date for 
comments. We will consider comments filed late if it is possible to do 
so without incurring expense or delay. We may change these special 
conditions based on the comments we receive.

Background and Discussion

    On December 21, 2009, Airbus Helicopters Deutschland GmbH applied 
to amend Type Certificate No. H13EU to include the new Model MBB-BK117 
D-2. The MBB-BK117 D-2, which is a derivative of the MBB-BK117 C-2 
currently approved under Type Certificate No. H13EU, is a Transport 
Category, 14 CFR part 29, twin engine conventional helicopter designed 
for civil operations. It is certificated with Category A performance 
and for day and night operation under visual and instrument flight 
rules. It is powered by two Turbomeca Arriel 2E engines with dual 
channel Full Authority Digital Engine Control systems and has four main 
rotor blades and a maximum gross weight of 8,046 pounds. It has an 
integrated modular avionics suite with three 6x8 inch multi-function 
displays termed the Common Integrated Global Avionics for Light 
Helicopters.
    Airbus Helicopters Deutschland GmbH proposes that the model MBB-
BK117 D-2 use a novel and unusual design feature, which is a 30-minute 
power rating, identified in the Turbomeca Arriel 2E Engine Special 
Conditions No. 33-009-SC. 14 CFR 1.1 defines ``rated takeoff power'' as 
limited in use to no more than 5 minutes for takeoff operation. Thus, 
the use of takeoff power for 30 minutes will require special 
airworthiness standards, known as special conditions, to address the 
use of this 30-minute power rating and its effects on the rotorcraft. 
These special conditions will add requirements to the existing 
airworthiness standards in 14 CFR 29.1049 (Hover cooling test 
procedures), Sec.  29.1305 (Powerplant instruments), and Sec.  29.1521 
(Powerplant limitations).
    The following is a summary of the final special conditions:
    In addition to the requirements of Sec.  29.1049 (Hover cooling 
test procedures), the aircraft cooling effects due to use of the 30-
minute power rating versus the Takeoff (5-minute) rating must be 
accounted for in the testing.
    In addition to the requirements of Sec.  29.1305, Powerplant 
Instruments, since this new 30-minute power rating has a 30-minute time 
limit associated with its use, the pilot must have the means to 
identify:
    <bullet> When the rated engine power level is achieved,
    <bullet> When the event begins, and
    <bullet> When the time interval expires.
    In addition to the requirements of Sec.  29.1521, Powerplant 
Limitations, a new 30-minute rating must be limited to no more than 30 
minutes per use. This new rating will allow use of power above maximum 
continuous power (MCP) for 30 minutes.
    Furthermore, the Model MBB-BK117 D-2 rotorcraft flight manual must 
include limitations on use of the 30-minute power rating to state that 
continuous use above MCP up to takeoff power is limited to 30 minutes.

Type Certification Basis

    Under 14 CFR 21.101, Airbus Helicopters Deutschland GmbH must show 
that the MBB-BK117 D-2 model helicopter meets the applicable provisions 
of the regulations incorporated by reference in Type Certificate No. 
H13EU or the applicable regulations in effect on the date of 
application for the change to the type certificate. The regulations 
incorporated by reference in the type certificate are commonly referred 
to as the ``original type certification basis.'' The regulations 
incorporated by reference in Type Certificate No. H13EU are as follows:

1. 14 CFR 21.29 and 14 CFR 29 effective February 1, 1965 plus 
Amendments 29-1 through 29-40 for the new or changed parts with respect 
to the MBB-BK117 C-2 identified in the document ETYC 1183/09-MHa, 
supplemented with requirements from other amendments listed below.
2. 14 CFR 29 requirements with amendment through 29-51 for: 29.25, 
29.59, 29.62, 29.67, 29.77, 29.81, 29.85, 29.143, 29.173, 29.175, 
29.177, 29.351, 29.397, 29.562, 29.602, 29.865, 29.923, 29.1317, 
29.1323, 29.1329, 29.1351, 29.1359, 29.1457, 29.1459, 29.1521, 29.1587, 
B29.5, B29.7
3. Equivalent Level Of Safety:
    (a) 14 CFR 29.807 (a)(4) Emergency exits
    (b) 14CFR 29.1305, 29.1351(b)(6), 29.1435(a)(3) Part Time Display 
of Vehicle Parameters
    (c) 14 CFR 29.1545(b)(4), 29.1549(b) Airspeed & Powerplant 
indication green marking
4. Environmental Standards:
    (a) 14 CFR 36 Appendix H at amendment 36-25
5. The main differences between the MBB-BK117 C-2 and the MBB-BK117 D-2 
are as follows:
    (a) Installation of Turbomeca Arriel 2E engines with FADEC control
    (b) New tail section including composite structure and fanned tail 
rotor (FENESTRON) with composite blades
    (c) New cockpit indication system using integrated modular 
avionics.
    (d) Auto Flight System as a standard configuration of the MBB-BK117 
D-2
    (e) Main gearbox modifications to support 30 minute run-dry 
capability
    (f) Maximum take-off weight increased to 3650 kg

    In addition, if the regulations incorporated by reference do not 
provide adequate standards regarding

[[Page 78696]]

the change, the applicant must comply with certain regulations in 
effect on the date of application for the change. The FAA has 
determined that the Model MBB-BK117 D-2 must also comply with the noise 
certification requirements of 14 CFR part 36; and the FAA must issue a 
finding of regulatory adequacy under Sec.  611 of Public Law 92-574, 
the ``Noise Control Act of 1972.''

Regulatory Basis for Special Conditions

    The Administrator has determined that the applicable airworthiness 
regulations (that is, 14 CFR part 29) do not contain adequate or 
appropriate safety standards for the MBB-BK117 D22 model helicopter 
because of a novel or unusual design feature. Therefore, special 
conditions are prescribed under the provisions of 14 CFR 21.16.
    The FAA issues special conditions, as defined in Sec.  11.19, in 
accordance with Sec.  11.38, and they become part of the type 
certification basis under Sec.  21.101.
    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.

Novel or Unusual Design Features

    The MBB-BK117 D-2 model helicopter will incorporate the following 
novel or unusual design feature:
    <bullet> A 30-minute power rating.

Applicability

    These special conditions are applicable to the Airbus Helicopters 
Deutschland GmbH Model MBB-BK117 D2 helicopter. Should Airbus 
Helicopters Deutschland GmbH apply at a later date for an amendment 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.

Conclusion

    This action affects only certain novel or unusual design features 
on the Airbus Helicopters Deutschland GmbH Model MBB-BK117 D-2 
helicopter. It is not a rule of general applicability.

List of Subjects in 14 CFR Part 29

    Aircraft, Aviation safety, Reporting and recordkeeping 
requirements.

    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 Airbus Helicopters Deutschland GmbH 
Model MBB-BK117 D-2 helicopters. Unless stated otherwise, all 
requirements in Sec. Sec.  29.1049, 29.1305 and 29.1521 remain 
unchanged.
    Section 29.1049 Hover cooling test procedures. In addition to the 
requirements of this section, for rotorcraft with a 30-minute power 
rating, the hovering cooling provisions at the 30-minute power rating 
must be shown--
    (a) At 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 the 30-minute power, in the ground effect in 
still air, until at least 5 minutes after the occurrence of the highest 
temperature recorded, or until the continuous time limit of the 30-
minute power rating if the highest temperature recorded is not 
stabilized before.
    (b) At 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 continuous 
time limit of the 30-minute power rating if the highest temperature 
recorded is not stabilized before.
    Section 29.1305 Powerplant instruments, at Amendment 29-40. In 
addition to the requirements of this section, a means must be provided 
to indicate to the pilot when the engine is at the 30-minute power 
level, when the event begins, and when the time interval expires.
    Section 29.1521 Powerplant limitations, at Amendment 29-41. In 
addition to the requirements of this section, use of the 30-minute 
power must be limited to no more than 30 minutes per use. The use of 
the 30-minute power must also be limited by:
    (1) The maximum rotational speed, which may not be greater than--
    (i) The maximum value determined by the rotor design; or
    (ii) The maximum value demonstrated during the type tests;
    (2) The maximum allowable turbine inlet or turbine outlet gas 
temperature (for turbine engines);
    (3) The maximum allowable power or torque for each engine, 
considering the power input limitations of the transmission with all 
engines operating;
    (4) The maximum allowable power or torque for each engine 
considering the power input limitations of the transmission with one 
engine inoperative;
    (5) The time limit for the use of the power corresponding to the 
limitations established in paragraphs (1) through (4) above; and
    (6) The maximum allowable engine and transmission oil temperatures, 
if the time limit established in paragraph (5) above exceeds 2 minutes.

    Issued in Fort Worth, Texas, on December 19, 2014.
Lance T. Gant
Acting Directorate Manager, Rotorcraft Directorate, Aircraft 
Certification Service.
[FR Doc. 2014-30562 Filed 12-30-14; 8:45 am]
BILLING CODE 4910-13-P


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