Document ID: FAA-2018-0469-0001
Agency: faa
Document Type: Rule
Title: Special Conditions: Bombardier Inc. Model BD 700 2A12 and Model BD 700 2A13 Airplanes; Autobrake System Structural Loads
Posted Date: 2018-05-30T04:00Z

[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]

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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.

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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 http://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 http://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 
http://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