Special Conditions: Bombardier Inc. Model BD-700-2A12 and Model BD-700-2A13 Airplanes; Autobrake System Structural Loads, 24652-24654 [2018-11506]

Download as PDF 24652 Federal Register / Vol. 83, No. 104 / Wednesday, May 30, 2018 / Rules and Regulations economic impact a rule may have on a substantial number of small entities (primarily those under $100 million in assets). The severance provision imposes no new requirements on credit unions. Instead, it provides a limited exception to an existing regulation that applies to liquidated credit unions. Accordingly, the final rule will not have a significant economic impact on a substantial number of small credit unions, and therefore, no regulatory flexibility analysis is required. Paperwork Reduction Act The Paperwork Reduction Act of 1995 (PRA) applies to rulemakings in which an agency by rule creates a new paperwork burden on regulated entities or modifies an existing burden. 44 U.S.C. 3507(d). For purposes of the PRA, a paperwork burden may take the form of either a reporting or a recordkeeping requirement, both referred to as information collections. Part 709 only concerns credit unions that have failed and imposes no information collection requirements on existing credit unions. Accordingly, there are no PRA implications. sradovich on DSK3GMQ082PROD with RULES Small Business Regulatory Enforcement Fairness Act of 1996 The Small Business Regulatory Enforcement Fairness Act of 1996 (SBREFA) provides generally for congressional review of agency rules. A reporting requirement is triggered in instances where the NCUA issues a final rule as defined by Section 551 of the Administrative Procedure Act. The NCUA does not believe this final rule is a ‘‘major rule’’ within the meaning of the relevant sections of SBREFA. The NCUA has submitted the rule to the Office of Management and Budget for its determination in that regard. Executive Order 13132 Executive Order 13132 encourages independent regulatory agencies to consider the impact of their actions on state and local interests. In adherence to fundamental federalism principles, the NCUA, an independent regulatory agency as defined in 44 U.S.C. 3502(5), voluntarily complies with the executive order. This final rule will clarify certain procedures for the NCUA’s administration of liquidated federally insured credit unions. This final rule will not have a substantial direct effect on the states, on the connection between the national government and the states, or on the distribution of power and responsibilities among the various levels of government. The Board has determined that the final rule does not constitute a policy that has federalism VerDate Sep<11>2014 19:27 May 29, 2018 Jkt 244001 implications for purposes of the executive order. The Treasury and General Government Appropriations Act, 1999—Assessment of Federal Regulations and Policies on Families The NCUA has determined that the final rule will not affect family wellbeing within the meaning of section 654 of the Treasury and General Government Appropriations Act, 1999, Public Law 105–277, 112 Stat. 2681 (1998). List of Subjects in 12 CFR Part 709 Credit unions, Involuntary liquidation. For the reasons discussed above, the NCUA Board amends 12 CFR part 709 as follows: PART 709—INVOLUNTARY LIQUIDATION OF FEDERAL CREDIT UNIONS AND ADJUDICATION OF CREDITOR CLAIMS INVOLVING FEDERALLY INSURED CREDIT UNIONS IN LIQUIDATION 1. The authority citation for part 709 is revised to read as follows: ■ Authority: 12 U.S.C. 1757, 1766, 1767, 1786(h), 1786(t), and 1787(b)(4), 1788, 1789, 1789a. 2. Revise paragraph (b)(2) of § 709.5 to read as follows: ■ § 709.5 Payout priorities in involuntary liquidation. * * * * * (b) * * * (2) Claims for wages and salaries, including vacation, severance, and sick leave pay; provided, however, that, in accordance with § 750.7 of this chapter, no claim for vacation, severance, or sick leave pay is provable unless entitlement to the benefit is provided for in the credit union employee handbook or other written credit union record, is calculable in accordance with an objective formula, and is available to all employees who meet applicable eligibility requirements, such as minimum length of service, or if such payment is required by applicable state or local law; * * * * * [FR Doc. 2018–11588 Filed 5–29–18; 8:45 am] PO 00000 Frm 00002 Fmt 4700 Sfmt 4700 Federal Aviation Administration 14 CFR Part 25 [Docket No. FAA–2018–0469; Special Conditions No. 25–727–SC] Special Conditions: Bombardier Inc. Model BD–700–2A12 and Model BD– 700–2A13 Airplanes; Autobrake System Structural Loads Federal Aviation Administration (FAA), DOT. ACTION: Final special conditions; request for comments. AGENCY: These special conditions are issued for the Bombardier Inc. Model BD–700–2A12 and Model BD–700– 2A13 airplanes. This airplane will have a novel or unusual design feature when compared to the state of technology envisioned in the airworthiness standards for transport category airplanes. This design feature is an autobrake system that allows earlier braking at landing without pedal input from the pilot. 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 Bombardier on May 30, 2018. Send comments on or before July 16, 2018. ADDRESSES: Send comments identified by Docket No. FAA–2018–0469 using any of the following methods: • Federal eRegulations Portal: Go to https://www.regulations.gov/ and follow the online instructions for sending your comments electronically. • 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. • Hand Delivery or 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 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. • Fax: Fax comments to Docket Operations at 202–493–2251. Privacy: The FAA will post all comments it receives, without change, to https://www.regulations.gov/, including any personal information the commenter provides. Using the search function of the docket website, anyone SUMMARY: By the National Credit Union Administration Board, on May 24, 2018. Gerard Poliquin, Secretary of the Board. BILLING CODE 7535–01–P DEPARTMENT OF TRANSPORTATION E:\FR\FM\30MYR1.SGM 30MYR1 Federal Register / Vol. 83, No. 104 / Wednesday, May 30, 2018 / Rules and Regulations can find 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). Docket: Background documents or comments received may be read at https://www.regulations.gov/ at any time. Follow the online instructions for accessing the docket or go to Docket Operations in Room W12–140 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: Mark Freisthler, Airframe & Cabin Safety Section, AIR–675, Transport Standards Branch, Policy and Innovation Division, Aircraft Certification Service, Federal Aviation Administration, 2200 South 216th Street, Des Moines, Washington 98198; telephone and fax 206–231–3207; email Mark.Freisthler@faa.gov. SUPPLEMENTARY INFORMATION: The FAA has determined that notice of, and opportunity for prior public comment on, these special conditions is impracticable because these procedures would significantly delay issuance of the design approval and thus delivery of the affected airplanes. In addition, the substance of these special conditions has been published in the Federal Register for public comment in several prior instances with no substantive comments received. The FAA, therefore, finds it unnecessary to delay the effective date and finds that good cause exists for making these special conditions effective upon publication in the Federal Register. sradovich on DSK3GMQ082PROD with RULES Comments Invited 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 may change these special conditions based on the comments we receive. Background On May 30, 2012, Bombardier Inc. (Bombardier) applied for an amendment to Type Certificate No. T00003NY to include new Model BD–700–2A12 and VerDate Sep<11>2014 19:27 May 29, 2018 Jkt 244001 Model BD–700–2A13 airplanes. These airplanes, which are derivatives of the BD–700 series airplanes currently approved under Type Certificate No. T00003NY, are marketed as the Bombardier Global 7000 and Global 8000, respectively. These airplanes are twin engine, transport category, executive interior business jets with a maximum certified passenger capacity of 19. The maximum takeoff weight for the Model BD–700–2A12 and Model BD–700–2A13 is 106,250 pounds and 104,800 pounds, respectively. Type Certification Basis Under the provisions of title 14, Code of Federal Regulations (14 CFR) 21.101, Bombardier must show that the Model BD–700–2A12 and Model BD–700– 2A13 airplanes meet the applicable provisions of the regulations listed in Type Certificate No. T00003NY, or the applicable regulations in effect on the date of application for the change, except for earlier amendments as agreed upon by the FAA. 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 Bombardier Model BD–700– 2A12 and Model BD–700–2A13 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, or should any other model already included on the same type certificate be modified to incorporate the same novel or unusual design feature, these special conditions would also apply to the other model under § 21.101. In addition to the applicable airworthiness regulations and special conditions, the Bombardier Model BD– 700–2A12 and Model BD–700–2A13 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. 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 § 21.101. Novel or Unusual Design Features The Bombardier Model BD–700–2A12 and Model BD–700–2A13 airplanes will PO 00000 Frm 00003 Fmt 4700 Sfmt 4700 24653 incorporate the following novel or unusual design feature: The autobrake system on the Bombardier Model BD–700–2A12 and Model BD–700–2A13 airplanes is a pilot-selectable function that allows earlier braking at landing without pedal input from the pilot. When the pilot arms the autobrake system before landing, the system automatically commands braking when the main wheels touch down. This might cause a high nose gear sink rate, and potentially higher gear and airframe loads than would occur with a traditional braking system. Discussion These special conditions define a landing pitchover condition that accounts for the effects of the autobrake system. The special conditions define the airplane configuration, speeds, and other parameters necessary to develop airframe and nose gear loads for this condition. The special conditions require that the airplane be designed to support the resulting limit and ultimate loads as defined in § 25.305, ‘‘Strength and deformation.’’ 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. Applicability As discussed above, these special conditions are applicable to the Bombardier Inc. Model BD–700–2A12 and Model BD–700–2A13 airplanes. Should Bombardier apply at a later date for a change to the type certificate to include another model incorporating the same novel or unusual design feature, these special conditions would apply to that model as well. Conclusion This action affects only a certain novel or unusual design feature on Bombardier Model BD–700–2A12 and Model BD–700–2A13 airplanes. It is not a rule of general applicability. List of Subjects in 14 CFR Part 25 Aircraft, Aviation safety, Reporting and recordkeeping requirements. Authority Citation The authority citation for these special conditions is as follows: Authority: 49 U.S.C. 106(f), 106(g), 40113, 44701, 44702, 44704. The Special Conditions Accordingly, pursuant to the authority delegated to me by the E:\FR\FM\30MYR1.SGM 30MYR1 24654 Federal Register / Vol. 83, No. 104 / Wednesday, May 30, 2018 / Rules and Regulations Administrator, the following special conditions are issued as part of the type certification basis for Bombardier Model BD–700–2A12 and Model BD–700– 2A13 airplanes. Autobraking System Structural 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. Issued in Des Moines, Washington, on May 23, 2018. Victor Wicklund, Manager, Transport Standards Branch, Policy and Innovation Division, Aircraft Certification Service. [FR Doc. 2018–11506 Filed 5–29–18; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2018–0492; Product Identifier 2018–NM–083–AD; Amendment 39–19303; AD 2018–11–15] RIN 2120–AA64 Airworthiness Directives; Airbus Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Final rule; request for comments. AGENCY: We are adopting a new airworthiness directive (AD) for all Airbus Model A320–271N airplanes, and Model A321–271N, –271NX, –272N and –272NX airplanes. This AD requires replacing certain full authority digital engine control (FADEC) electronic engine controllers (EECs); or installing software standard FCS4.4 and reidentifying the FADEC EECs. This AD was prompted by a report that, when sradovich on DSK3GMQ082PROD with RULES SUMMARY: VerDate Sep<11>2014 19:27 May 29, 2018 Jkt 244001 operated at low speed and high engine thrust, an engine did not restart following a fuel interruption shorter than five seconds. We are issuing this AD to address the unsafe condition on these products. DATES: This AD becomes effective May 30, 2018. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of May 30, 2018. We must receive comments on this AD by July 16, 2018. ADDRESSES: You may send comments, using the procedures found in 14 CFR 11.43 and 11.45, by any of the following methods: • Federal eRulemaking Portal: Go to https://www.regulations.gov. Follow the instructions for submitting comments. • Fax: 202–493–2251. • Mail: U.S. Department of Transportation, Docket Operations, M– 30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE, Washington, DC 20590. • Hand Delivery: U.S. Department of Transportation, Docket Operations, M– 30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE, Washington, DC, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. For service information identified in this final rule, contact Airbus, Airworthiness Office—EIAS, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 44 51; email account.airworth-eas@airbus.com; internet https://www.airbus.com. You may view this referenced service information at the FAA, Transport Standards Branch, 2200 South 216th St., Des Moines, WA. For information on the availability of this material at the FAA, call 206–231–3195. It is also available on the internet at https:// www.regulations.gov by searching for and locating Docket No. FAA–2018– 0492. Examining the AD Docket You may examine the AD docket on the internet at https:// www.regulations.gov by searching for and locating Docket No. FAA–2018– 0492; or in person at the Docket Operations office between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this AD, the regulatory evaluation, any comments received, and other information. The street address for the Docket Operations office (telephone 800–647–5527) is in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt. PO 00000 Frm 00004 Fmt 4700 Sfmt 4700 FOR FURTHER INFORMATION CONTACT: Sanjay Ralhan, Aerospace Engineer, International Section, Transport Standards Branch, FAA, 2200 South 216th St., Des Moines, WA 98198; telephone and fax 206–231–3323. SUPPLEMENTARY INFORMATION: Discussion The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Union, has issued EASA AD 2018–0110, dated May 18, 2018 (referred to after this as the Mandatory Continuing Airworthiness Information, or ‘‘the MCAI’’), to correct an unsafe condition for all Airbus Model A320–271N airplanes, and Model A321–271N, –271NX, –272N, and –272NX airplanes. The MCAI states: During certification test flights of an A320– 271N aeroplane, it has been identified that, when operated at low speed and high engine thrust, the tested engine did not re-start in case of a fuel interruption shorter than 5 seconds. Investigation revealed that this was due to the software logic implemented in the FADEC EEC of affected A320 family models. This condition, if not corrected, could prevent restart of a shut down engine while operating in high power conditions [after a single or dual in-flight engine shutdown]. To address this potentially unsafe condition, software (SW) standard FCS4.4 for the FADEC EEC has been developed, and Airbus published the SB [Airbus Service Bulletin A320–73–1128, Revision 01, dated May 17, 2018] providing modification instructions. For the reasons described above, this [EASA] AD requires modification of aeroplanes by [replacing the affected FADEC EECs or by] installation of this FADEC EEC SW [software] standard [and re-identification of the affected FADEC EECs]. You may examine the MCAI on the internet at https://www.regulations.gov by searching for and locating Docket No. FAA–2018–0492. Related Service Information Under 1 CFR Part 51 Airbus has issued Service Bulletin A320–73–1128, Revision 01, dated May 17, 2018. This service information describes procedures for replacing affected FADEC EECs and for installing software standard FCS4.4 and reidentifying affected FADEC EECs. This service information is reasonably available because the interested parties have access to it through their normal course of business or by the means identified in the ADDRESSES section. FAA’s Determination and Requirements of This AD This product has been approved by the aviation authority of another E:\FR\FM\30MYR1.SGM 30MYR1

Agencies

[Federal Register Volume 83, Number 104 (Wednesday, May 30, 2018)]
[Rules and Regulations]
[Pages 24652-24654]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2018-11506]


=======================================================================
-----------------------------------------------------------------------

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 25

[Docket No. FAA-2018-0469; Special Conditions No. 25-727-SC]


Special Conditions: Bombardier Inc. Model BD-700-2A12 and Model 
BD-700-2A13 Airplanes; Autobrake System Structural Loads

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final special conditions; request for comments.

-----------------------------------------------------------------------

SUMMARY: These special conditions are issued for the Bombardier Inc. 
Model BD-700-2A12 and Model BD-700-2A13 airplanes. This airplane will 
have a novel or unusual design feature when compared to the state of 
technology envisioned in the airworthiness standards for transport 
category airplanes. This design feature is an autobrake system that 
allows earlier braking at landing without pedal input from the pilot. 
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 Bombardier on May 30, 2018. Send 
comments on or before July 16, 2018.

ADDRESSES: Send comments identified by Docket No. FAA-2018-0469 using 
any of the following methods:
     Federal eRegulations Portal: Go to https://www.regulations.gov/ and follow the online instructions for sending 
your comments electronically.
     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.
     Hand Delivery or 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 9 a.m. and 5 p.m., Monday 
through Friday, except Federal holidays.
     Fax: Fax comments to Docket Operations at 202-493-2251.
    Privacy: The FAA will post all comments it receives, without 
change, to https://www.regulations.gov/, including any personal 
information the commenter provides. Using the search function of the 
docket website, anyone

[[Page 24653]]

can find 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).
    Docket: Background documents or comments received may be read at 
https://www.regulations.gov/ at any time. Follow the online instructions 
for accessing the docket or go to Docket Operations in Room W12-140 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: Mark Freisthler, Airframe & Cabin 
Safety Section, AIR-675, Transport Standards Branch, Policy and 
Innovation Division, Aircraft Certification Service, Federal Aviation 
Administration, 2200 South 216th Street, Des Moines, Washington 98198; 
telephone and fax 206-231-3207; email [email protected].

SUPPLEMENTARY INFORMATION: The FAA has determined that notice of, and 
opportunity for prior public comment on, these special conditions is 
impracticable because these procedures would significantly delay 
issuance of the design approval and thus delivery of the affected 
airplanes.
    In addition, the substance of these special conditions has been 
published in the Federal Register for public comment in several prior 
instances with no substantive comments received. The FAA, therefore, 
finds it unnecessary to delay the effective date and finds that good 
cause exists for making these special conditions effective upon 
publication in the Federal Register.

Comments Invited

    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 may change these special conditions based on the comments 
we receive.

Background

    On May 30, 2012, Bombardier Inc. (Bombardier) applied for an 
amendment to Type Certificate No. T00003NY to include new Model BD-700-
2A12 and Model BD-700-2A13 airplanes. These airplanes, which are 
derivatives of the BD-700 series airplanes currently approved under 
Type Certificate No. T00003NY, are marketed as the Bombardier Global 
7000 and Global 8000, respectively. These airplanes are twin engine, 
transport category, executive interior business jets with a maximum 
certified passenger capacity of 19. The maximum takeoff weight for the 
Model BD-700-2A12 and Model BD-700-2A13 is 106,250 pounds and 104,800 
pounds, respectively.

Type Certification Basis

    Under the provisions of title 14, Code of Federal Regulations (14 
CFR) 21.101, Bombardier must show that the Model BD-700-2A12 and Model 
BD-700-2A13 airplanes meet the applicable provisions of the regulations 
listed in Type Certificate No. T00003NY, or the applicable regulations 
in effect on the date of application for the change, except for earlier 
amendments as agreed upon by the FAA.
    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 Bombardier Model BD-700-2A12 and 
Model BD-700-2A13 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, or should any other model already included on 
the same type certificate be modified to incorporate the same novel or 
unusual design feature, these special conditions would also apply to 
the other model under Sec.  21.101.
    In addition to the applicable airworthiness regulations and special 
conditions, the Bombardier Model BD-700-2A12 and Model BD-700-2A13 
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.
    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.  21.101.

Novel or Unusual Design Features

    The Bombardier Model BD-700-2A12 and Model BD-700-2A13 airplanes 
will incorporate the following novel or unusual design feature:
    The autobrake system on the Bombardier Model BD-700-2A12 and Model 
BD-700-2A13 airplanes is a pilot-selectable function that allows 
earlier braking at landing without pedal input from the pilot. When the 
pilot arms the autobrake system before landing, the system 
automatically commands braking when the main wheels touch down. This 
might cause a high nose gear sink rate, and potentially higher gear and 
airframe loads than would occur with a traditional braking system.

Discussion

    These special conditions define a landing pitchover condition that 
accounts for the effects of the autobrake system. The special 
conditions define the airplane configuration, speeds, and other 
parameters necessary to develop airframe and nose gear loads for this 
condition. The special conditions require that the airplane be designed 
to support the resulting limit and ultimate loads as defined in Sec.  
25.305, ``Strength and deformation.''
    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.

Applicability

    As discussed above, these special conditions are applicable to the 
Bombardier Inc. Model BD-700-2A12 and Model BD-700-2A13 airplanes. 
Should Bombardier apply at a later date for a change to the type 
certificate to include another model incorporating the same novel or 
unusual design feature, these special conditions would apply to that 
model as well.

Conclusion

    This action affects only a certain novel or unusual design feature 
on Bombardier Model BD-700-2A12 and Model BD-700-2A13 airplanes. It is 
not a rule of general applicability.

List of Subjects in 14 CFR Part 25

    Aircraft, Aviation safety, Reporting and recordkeeping 
requirements.

Authority Citation

    The authority citation for these special conditions is as follows:

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

The Special Conditions

    Accordingly, pursuant to the authority delegated to me by the

[[Page 24654]]

Administrator, the following special conditions are issued as part of 
the type certification basis for Bombardier Model BD-700-2A12 and Model 
BD-700-2A13 airplanes.

Autobraking System Structural 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.

    Issued in Des Moines, Washington, on May 23, 2018.
Victor Wicklund,
Manager, Transport Standards Branch, Policy and Innovation Division, 
Aircraft Certification Service.
[FR Doc. 2018-11506 Filed 5-29-18; 8:45 am]
 BILLING CODE 4910-13-P

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