Special Conditions: Bombardier Aerospace Inc., Models BD-500-1A10 and BD-500-1A11 Series Airplanes; Autobraking System Loads, 7370-7371 [2014-02613]

Download as PDF 7370 Federal Register / Vol. 79, No. 26 / Friday, February 7, 2014 / Rules and Regulations K. Review Under Executive Order 13211 Executive Order 13211, ‘‘Actions Concerning Regulations That Significantly Affect Energy Supply, Distribution, or Use,’’ 66 FR 28355 (May 22, 2001), requires Federal agencies to prepare and submit to OMB, a Statement of Energy Effects for any significant energy action. A ‘‘significant energy action’’ is defined as any action by an agency that promulgated or is expected to lead to promulgation of a final rule, and that: (1) Is a significant regulatory action under Executive Order 12866, or any successor order; and (2) is likely to have a significant adverse effect on the supply, distribution, or use of energy; or (3) is designated by the Administrator of OIRA as a significant energy action. For any significant energy action, the agency must give a detailed statement of any adverse effects on energy supply, distribution, or use if the regulation is implemented, and of reasonable alternatives to the action and their expected benefits on energy supply, distribution, and use. Today’s regulatory action is not a significant regulatory action under Executive Order 12866. Moreover, it would not have a significant adverse effect on the supply, distribution, or use of energy, nor has it been designated as a significant energy action by the Administrator of OIRA. Therefore, it is not a significant energy action, and, accordingly, DOE has not prepared a Statement of Energy Effects. mstockstill on DSK4VPTVN1PROD with RULES Jkt 232001 As required by 5 U.S.C. 801, DOE will report to Congress on the promulgation of today’s rule before its effective date. The report will state that it has been determined that the rule is not a ‘‘major rule’’ as defined by 5 U.S.C. 804(2). IV. Approval of the Office of the Secretary The Secretary of Energy has approved publication of this final rule. List of Subjects in 10 CFR Part 430 Administrative practice and procedure, Confidential business information, Energy conservation, Household appliances, Imports, Incorporation by reference, Intergovernmental relations, Small businesses. Issued in Washington, DC, on January 29, 2014. Kathleen B. Hogan, Deputy Assistant Secretary for Energy Efficiency, Energy Efficiency and Renewable Energy. For the reasons stated in the preamble, DOE amends part 430 of Chapter II of Title 10, Code of Federal Regulations as set forth below: PART 430—ENERGY CONSERVATION PROGRAM FOR CONSUMER PRODUCTS determined according to paragraph 5.2 of appendix X to this subpart. * * * * * Appendix X to Subpart B of Part 430— [Removed] 4. Appendix X to subpart B of part 430 is removed. ■ Appendix X1 to Subpart B of Part 430— [Redesignated as Appendix X] 5. Appendix X1 to subpart B of part 430 is redesignated as appendix X. ■ 6. Redesignated appendix X to subpart B of part 430 is amended by revising the Note after the heading to read as follows: ■ Appendix X to Subpart B of Part 430– Uniform Test Method for Measuring the Energy Consumption of Dehumidifiers Note: After August 6, 2014, any representations made with respect to the energy use or efficiency of dehumidifiers must be made in accordance with the results of testing pursuant to this appendix. After this date, if a manufacturer elects to make representations with regard to standby mode and off mode energy consumption, then testing must also include the provisions of this appendix related to standby mode and off mode energy consumption. * * * * * [FR Doc. 2014–02355 Filed 2–6–14; 8:45 am] BILLING CODE 6450–01–P DEPARTMENT OF TRANSPORTATION 1. The authority citation for part 430 continues to read as follows: Federal Aviation Administration Authority: 42 U.S.C. 6291–6309; 28 U.S.C. 2461 note. Under section 301 of the Department of Energy Organization Act (Pub. L. 95– 91; 42 U.S.C. 7101), DOE must comply with section 32 of the Federal Energy Administration Act of 1974, as amended by the Federal Energy Administration Authorization Act of 1977. (15 U.S.C. 788; FEAA) Section 32 essentially provides in relevant part that, where a proposed rule authorizes or requires use of commercial standards, the notice of proposed rulemaking must inform the public of the use and background of such standards. In addition, section 32(c) requires DOE to consult with the Attorney General and the Chairman of the Federal Trade Commission (FTC) concerning the impact of the commercial or industry standards on competition. DOE required the use of a commercial standard (DH–1–2008) in the October 2012 final rule. This rule requires earlier use of the October 2012 test procedures in this rulemaking, but does not require the use of a commercial 16:20 Feb 06, 2014 M. Congressional Notification 14 CFR Part 25 § 430.3 [Docket No. FAA–2013–0942; Special Conditions No. 25–515–SC] ■ L. Review Under Section 32 of the Federal Energy Administration Act of 1974 VerDate Mar<15>2010 standard, so these requirements do not apply. [Amended] 2. Section 430.3 is amended by removing ‘‘X1’’ from paragraphs (h)(1) and (o)(4) and adding ‘‘X’’ in its place. ■ 3. Section 430.23 is amended by revising paragraph (z) to read as follows: ■ Special Conditions: Bombardier Aerospace Inc., Models BD–500–1A10 and BD–500–1A11 Series Airplanes; Autobraking System Loads § 430.23 Test procedures for the measurement of energy and water consumption. Federal Aviation Administration (FAA), DOT. ACTION: Final special conditions. * SUMMARY: * * * * (z) Dehumidifiers. (1) When measuring the energy factor for dehumidifiers (see the note at the beginning of appendix X to this subpart), expressed in liters per kilowatt hour (L/kWh), energy factor shall be measured in accordance with section 4.1 of appendix X to this subpart. (2) When measuring the integrated energy factor for dehumidifiers (see the note at the beginning of appendix X to this subpart), expressed in L/kWh, integrated energy factor shall be PO 00000 Frm 00006 Fmt 4700 Sfmt 4700 AGENCY: These special conditions are issued for the Bombardier Aerospace Inc. Models BD–500–1A10 and BD– 500–1A11 series airplanes. These airplanes will have novel or unusual design features associated with the autobraking system for use during landing. 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 E:\FR\FM\07FER1.SGM 07FER1 Federal Register / Vol. 79, No. 26 / Friday, February 7, 2014 / Rules and Regulations equivalent to that established by the existing airworthiness standards. DATES: Effective Date: March 10, 2014. FOR FURTHER INFORMATION CONTACT: Mark Freisthler, FAA, Airframe and Cabin Safety Branch, ANM–115 Transport Airplane Directorate, Aircraft Certification Service, 1601 Lind Avenue SW., Renton, Washington 98057–3356; telephone 425–227–1119; facsimile 425–227–1232. SUPPLEMENTARY INFORMATION: mstockstill on DSK4VPTVN1PROD with RULES Background On December 10, 2009, Bombardier Inc. applied for a type certificate for their new Models BD–500–1A10 and BD–500–1A1 series airplanes (hereafter collectively referred to as ‘‘C-series’’). The C-series airplanes are swept-wing monoplanes with an aluminum alloy fuselage sized for 5-abreast seating. Passenger capacity is designated as 110 for the Model BD–500–1A10 and 125 for the Model BD–500–1A11. Maximum takeoff weight is 131,000 pounds for the Model BD–500–1A10 and 144,000 pounds for the Model BD–500–1A11. Type Certification Basis Under the provisions of Title 14, Code of Federal Regulations (14 CFR) 21.17, Bombardier Inc. must show that the Cseries airplanes meet the applicable provisions of part 25, as amended by Amendment 25–1 through 25–129. If the Administrator finds that the applicable airworthiness regulations (i.e., 14 CFR part 25) do not contain adequate or appropriate safety standards for the C-series airplanes because of a novel or unusual design feature, special conditions are prescribed under the provisions of § 21.16. 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, the special conditions would also apply to the other model under § 21.101. In addition to the applicable airworthiness regulations and special conditions, the C-series airplanes must comply with the fuel vent and exhaust emission requirements of 14 CFR part 34 and the noise certification requirements of 14 CFR part 36, and the FAA must issue a finding of regulatory adequacy under section 611 of Public Law 92–574, the ‘‘Noise Control Act of 1972.’’ The FAA issues special conditions, as defined in 14 CFR 11.19, in accordance with § 11.38, and they become part of the type certification basis under § 21.17(a)(2). VerDate Mar<15>2010 16:20 Feb 06, 2014 Jkt 232001 Novel or Unusual Design Features The C-series airplanes will incorporate the following novel or unusual design features: The C-series airplanes will have an autobrake system. This is a pilot-selectable function that allows earlier maximum braking at landing without pilot pedal input. When the autobrake system is armed before landing, it automatically commands maximum braking at main wheels touchdown. Normal procedures remain unchanged and call for manual braking after nose wheel touchdown. Discussion Section 25.493 addresses braked roll loads but does not contain a specific ‘‘pitchover’’ requirement addressing the loading on the nose gear, the nose gear surrounding structure, and the forward fuselage. Moreover, § 25.493 specifies airplane attitudes in accordance with figure 6 of appendix A to part 25, which are level landing attitudes. For airplanes with traditional braking systems, the current ground load requirements are considered adequate for the design of the nose gear and airframe structure. However, the C-Series airplane autobrake system, which could apply maximum braking at the main wheels with the airplane in a tail-down attitude well before the nose touches down, will cause a high nose gear sink rate and potentially higher gear and airframe loads. Part 25 does not contain adequate requirements to address the potentially higher structural loads that could result from this type of braking system. In addition, the effects on fatigue covered by § 25.571 also need to be considered. Therefore, FAA has determined that additional airworthiness standards are needed for the certification of this unusual design feature. These special conditions propose airworthiness standards for the certification of the Cseries airplanes with an autobrake system. Discussion of Comments Notice of proposed special conditions No. FAA–2013–0942 for the Bombardier C-series airplanes was published in the Federal Register on November 12, 2013 (78 FR 67321). No comments were received, and the special conditions are adopted as proposed. Applicability As discussed above, these special conditions are applicable to the Models BD–500–1A10 and BD–500–1A11 series airplanes. Should Bombardier Inc. apply at a later date for a change to the type certificate to include another model incorporating the same novel or unusual PO 00000 Frm 00007 Fmt 4700 Sfmt 9990 7371 design feature, the special conditions would apply to that model as well. Conclusion This action affects only certain novel or unusual design features on one series of airplanes. It is not a rule of general applicability. List of Subjects in 14 CFR Part 25 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 Bombardier Inc. Models BD–500–1A10 and BD–500– 1A11 series airplanes. Autobraking System Loads. A landing pitchover condition must be addressed that takes into account the effect of the autobrake system. The airplane is assumed to be at the design maximum landing weight, or at the maximum weight allowed with the autobrake system on. The airplane is assumed to land in a tail-down attitude at the speeds defined by § 25.481. Following main gear contact, the airplane is assumed to rotate about the main gear wheels at the highest pitch rate generated by the autobrake system. This is considered a limit load condition from which ultimate loads must also be determined. Loads must be determined for a critical fuel and payload distribution and centers of gravity. Nose gear loads, as well as airframe loads, must be determined. The airplane must support these loads as described in § 25.305. In addition to the above airworthiness standards, fatigue loads must also be determined and applied in accordance to § 25.571. Issued in Renton, Washington, on January 31, 2014. John P. Piccola, Jr., Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2014–02613 Filed 2–6–14; 8:45 am] BILLING CODE 4910–13–P E:\FR\FM\07FER1.SGM 07FER1

Agencies

[Federal Register Volume 79, Number 26 (Friday, February 7, 2014)]
[Rules and Regulations]
[Pages 7370-7371]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2014-02613]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 25

[Docket No. FAA-2013-0942; Special Conditions No. 25-515-SC]


Special Conditions: Bombardier Aerospace Inc., Models BD-500-1A10 
and BD-500-1A11 Series Airplanes; Autobraking System Loads

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final special conditions.

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SUMMARY: These special conditions are issued for the Bombardier 
Aerospace Inc. Models BD-500-1A10 and BD-500-1A11 series airplanes. 
These airplanes will have novel or unusual design features associated 
with the autobraking system for use during landing. 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

[[Page 7371]]

equivalent to that established by the existing airworthiness standards.

DATES: Effective Date: March 10, 2014.

FOR FURTHER INFORMATION CONTACT: Mark Freisthler, FAA, Airframe and 
Cabin Safety Branch, ANM-115 Transport Airplane Directorate, Aircraft 
Certification Service, 1601 Lind Avenue SW., Renton, Washington 98057-
3356; telephone 425-227-1119; facsimile 425-227-1232.

SUPPLEMENTARY INFORMATION:

Background

    On December 10, 2009, Bombardier Inc. applied for a type 
certificate for their new Models BD-500-1A10 and BD-500-1A1 series 
airplanes (hereafter collectively referred to as ``C-series''). The C-
series airplanes are swept-wing monoplanes with an aluminum alloy 
fuselage sized for 5-abreast seating. Passenger capacity is designated 
as 110 for the Model BD-500-1A10 and 125 for the Model BD-500-1A11. 
Maximum takeoff weight is 131,000 pounds for the Model BD-500-1A10 and 
144,000 pounds for the Model BD-500-1A11.

Type Certification Basis

    Under the provisions of Title 14, Code of Federal Regulations (14 
CFR) 21.17, Bombardier Inc. must show that the C-series airplanes meet 
the applicable provisions of part 25, as amended by Amendment 25-1 
through 25-129.
    If the Administrator finds that the applicable airworthiness 
regulations (i.e., 14 CFR part 25) do not contain adequate or 
appropriate safety standards for the C-series airplanes because of a 
novel or unusual design feature, special conditions are prescribed 
under the provisions of Sec.  21.16.
    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, the special conditions would also apply to the 
other model under Sec.  21.101.
    In addition to the applicable airworthiness regulations and special 
conditions, the C-series airplanes must comply with the fuel vent and 
exhaust emission requirements of 14 CFR part 34 and the noise 
certification requirements of 14 CFR part 36, and the FAA must issue a 
finding of regulatory adequacy under section 611 of Public Law 92-574, 
the ``Noise Control Act of 1972.''
    The FAA issues special conditions, as defined in 14 CFR 11.19, in 
accordance with Sec.  11.38, and they become part of the type 
certification basis under Sec.  21.17(a)(2).

Novel or Unusual Design Features

    The C-series airplanes will incorporate the following novel or 
unusual design features: The C-series airplanes will have an autobrake 
system. This is a pilot-selectable function that allows earlier maximum 
braking at landing without pilot pedal input. When the autobrake system 
is armed before landing, it automatically commands maximum braking at 
main wheels touchdown. Normal procedures remain unchanged and call for 
manual braking after nose wheel touchdown.

Discussion

    Section 25.493 addresses braked roll loads but does not contain a 
specific ``pitchover'' requirement addressing the loading on the nose 
gear, the nose gear surrounding structure, and the forward fuselage. 
Moreover, Sec.  25.493 specifies airplane attitudes in accordance with 
figure 6 of appendix A to part 25, which are level landing attitudes. 
For airplanes with traditional braking systems, the current ground load 
requirements are considered adequate for the design of the nose gear 
and airframe structure. However, the C-Series airplane autobrake 
system, which could apply maximum braking at the main wheels with the 
airplane in a tail-down attitude well before the nose touches down, 
will cause a high nose gear sink rate and potentially higher gear and 
airframe loads.
    Part 25 does not contain adequate requirements to address the 
potentially higher structural loads that could result from this type of 
braking system. In addition, the effects on fatigue covered by Sec.  
25.571 also need to be considered. Therefore, FAA has determined that 
additional airworthiness standards are needed for the certification of 
this unusual design feature. These special conditions propose 
airworthiness standards for the certification of the C-series airplanes 
with an autobrake system.

Discussion of Comments

    Notice of proposed special conditions No. FAA-2013-0942 for the 
Bombardier C-series airplanes was published in the Federal Register on 
November 12, 2013 (78 FR 67321). No comments were received, and the 
special conditions are adopted as proposed.

Applicability

    As discussed above, these special conditions are applicable to the 
Models BD-500-1A10 and BD-500-1A11 series airplanes. Should Bombardier 
Inc. 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.

Conclusion

    This action affects only certain novel or unusual design features 
on one series of airplanes. It is not a rule of general applicability.

List of Subjects in 14 CFR Part 25

    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 Bombardier Inc. Models BD-500-1A10 and 
BD-500-1A11 series airplanes.
    Autobraking System Loads. A landing pitchover condition must be 
addressed that takes into account the effect of the autobrake system. 
The airplane is assumed to be at the design maximum landing weight, or 
at the maximum weight allowed with the autobrake system on. The 
airplane is assumed to land in a tail-down attitude at the speeds 
defined by Sec.  25.481. Following main gear contact, the airplane is 
assumed to rotate about the main gear wheels at the highest pitch rate 
generated by the autobrake system. This is considered a limit load 
condition from which ultimate loads must also be determined. Loads must 
be determined for a critical fuel and payload distribution and centers 
of gravity. Nose gear loads, as well as airframe loads, must be 
determined. The airplane must support these loads as described in Sec.  
25.305.
    In addition to the above airworthiness standards, fatigue loads 
must also be determined and applied in accordance to Sec.  25.571.

    Issued in Renton, Washington, on January 31, 2014.
John P. Piccola, Jr.,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2014-02613 Filed 2-6-14; 8:45 am]
BILLING CODE 4910-13-P

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