[Federal Register Volume 84, Number 211 (Thursday, October 31, 2019)]
[Rules and Regulations]
[Pages 58313-58315]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2019-23798]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 25

[Docket No. FAA-2019-0814; Special Conditions No. 25-759-SC]


Special Conditions: Airbus Model A340 Series Airplanes; Seats 
With Inertia Locking Devices

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 Model A340 
series airplanes. These airplanes 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 seats with inertia locking devices (ILD). 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 on October 31, 2019. Send 
comments on or before December 16, 2019.

ADDRESSES: Send comments identified by Docket No. FAA-2019-0814 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 can find and read the electronic form of all 
comments received into any FAA docket, including the name of the

[[Page 58314]]

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: Shannon Lennon, Cabin and Airframe 
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 206-231-3209; email Shannon.Lennon@faa.gov.

SUPPLEMENTARY INFORMATION: The substance of these special conditions 
has been subject to the notice and comment period in several prior 
instances and has been derived without substantive change from those 
previously issued. It is unlikely that prior public comment would 
result in a significant change from the substance contained herein. 
Therefore, the FAA has determined that prior public notice and comment 
are unnecessary, and finds that, for the same reason, good cause exists 
for adopting these special conditions upon publication in the Federal 
Register.

Comments Invited

    The FAA invites 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.
    The FAA will consider all comments received by the closing date for 
comments. The FAA may change these special conditions based on the 
comments received.

Background

    On December 19, 2017, Airbus applied for a change to Type 
Certificate No. A43NM for seats with ILD in the Model A340 series 
airplanes. The Airbus Model A340 series airplane is a four-engine, 
transport category airplane with a maximum takeoff weight of 824,528 
pounds and seating for 440 passengers.

Type Certification Basis

    Under the provisions of title 14, Code of Federal Regulations (14 
CFR) 21.101, Airbus must show that the Airbus Model A340 series 
airplanes, as changed, continue to meet the applicable provisions of 
the regulations listed in Type Certificate No. A43NM, 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 (e.g., 14 CFR part 25) do not contain adequate or 
appropriate safety standards for the Airbus Model A340 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, 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 Airbus Model A340 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.
    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 Airbus Model A340 series airplanes will incorporate the 
following novel or unusual design features:
    Seats with inertia locking devices.

Discussion

    Airbus will install, in Model A340 series airplanes, Thompson Aero 
Seating Ltd. first-class passenger seats that can be translated in the 
fore and aft direction by an electrically powered motor (actuator) that 
is attached to the seat primary structure. Under typical service-
loading conditions, the motor internal brake is able to translate the 
seat and hold the seat in the translated position. However, under the 
inertial loads of emergency-landing loading conditions specified in 14 
CFR 25.562, the motor internal brake may not be able to maintain the 
seat in the required position. The ILD is an ``active'' device intended 
to control seat movement (i.e., a system that mechanically deploys 
during an impact event) to lock the gears of the motor assembly in 
place. The ILD mechanism is activated by the higher inertial load 
factors that could occur during an emergency-landing event. Each seat 
place incorporates two ILDs, one on either side of the seat pan. Only 
one ILD is required to hold an occupied seat in position during worst-
case dynamic loading specified in Sec.  25.562.
    The ILD will self-activate only in the event of a predetermined 
airplane loading condition such as that occurring during crash or 
emergency landing, and will prevent excessive seat forward translation. 
A minimum level of protection must be provided if the seat-locking 
device does not deploy.
    The normal means of satisfying the structural and occupant 
protection requirements of Sec.  25.562 result in a non-quantified, but 
nominally predictable, progressive structural deformation or reduction 
of injury severity for impact conditions less than the maximum 
specified by the rule. A seat using ILD technology, however, may 
involve a step change in protection for impacts below and above that at 
which the ILD activates and deploys to retain the seat pan in place. 
This could result in structural deformation or occupant injury output 
being higher at an intermediate impact condition than that resulting 
from the maximum impact condition. It is acceptable for such step-
change characteristics to exist, provided the resulting output does not 
exceed the maximum allowable criteria at any condition at which the ILD 
does or does not deploy, up to the maximum severity pulse specified by 
the requirements.
    The ideal triangular maximum severity pulse is defined in Advisory 
Circular (AC) 25.562-1B. For the evaluation and testing of less-severe 
pulses for purposes of assessing the effectiveness of the ILD 
deployment setting, a similar triangular pulse should be used with 
acceleration, rise time, and velocity change scaled accordingly. The 
magnitude of the required pulse should not deviate below the ideal 
pulse by more than 0.5g until 1.33 t1 is reached, where 
t1 represents the time interval between 0 and t1 
on the referenced pulse shape as shown in AC 25.562-1B. This is an 
acceptable method of compliance to the test requirements of the special 
conditions.
    Conditions 1 through 5 address ensuring that the ILD activates when 
intended, to provide the necessary

[[Page 58315]]

protection of occupants. This includes protection of a range of 
occupants under various accident conditions. Conditions 6 through 10 
address maintenance and reliability of the ILD, including any outside 
influences on the mechanism, to ensure it functions as intended.
    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 
Airbus Model A340 series airplanes. Should Airbus 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 one model 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.

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 
Administrator, the following special conditions are issued as part of 
the type certification basis for Airbus Model A340 series airplanes.
    In addition to the requirements of Sec.  25.562, passenger seats 
incorporating an inertia locking device (ILD) must meet the following:
    1. Level of Protection Provided by ILD--It must be demonstrated by 
test that the seats and attachments, when subject to the emergency-
landing dynamic conditions specified in Sec.  25.562, and with one ILD 
not deployed, do not experience structural failure that could result 
in:
    a. Separation of the seat from the airplane floor.
    b. Separation of any part of the seat that could form a hazard to 
the seat occupant or any other airplane occupant.
    c. Failure of the occupant restraint or any other condition that 
could result in the occupant separating from the seat.
    2. Protection Provided Below and Above the ILD Actuation 
Condition--If step-change effects on occupant protection exist for 
impacts below and above that at which the ILD deploys, tests must be 
performed to demonstrate that the occupant is shown to be protected at 
any condition at which the ILD does or does not deploy, up to the 
maximum severity pulse specified by Sec.  25.562. Test conditions must 
take into account any necessary tolerances for deployment.
    3. Protection Over a Range of Crash Pulse Vectors--The ILD must be 
shown to function as intended for all test vectors specified in Sec.  
25.562.
    4. Protection During Secondary Impacts--The ILD activation setting 
must be demonstrated to maximize the probability of the protection 
being available when needed, considering a secondary impact that is 
above the severity at which the device is intended to deploy up to the 
impact loading required by Sec.  25.562.
    5. Protection of Occupants other than 50th Percentile--Protection 
of occupants for a range of stature from a two-year-old child to a 95th 
percentile male must be shown.
    6. Inadvertent Operation--It must be shown that any inadvertent 
operation of the ILD does not affect the performance of the device 
during a subsequent emergency landing.
    7. Installation Protection--It must be shown that the ILD 
installation is protected from contamination and interference from 
foreign objects.
    8. Reliability--The performance of the ILD must not be altered by 
the effects of wear, manufacturing tolerances, aging or drying of 
lubricants, and corrosion.
    9. Maintenance and Functional Checks--The design, installation, and 
operation of the ILD must be such that it is possible to functionally 
check the device in place. Additionally, a functional check method and 
a maintenance check interval must be included in the seat installer's 
instructions for continued airworthiness (ICA) document.
    10. Release Function--If a means exists to release an inadvertently 
activated ILD, the release means must not introduce additional hidden 
failures that would prevent the ILD from functioning properly.

    Issued in Des Moines, Washington, on October 25, 2019.
James E. Wilborn,
Manager, Transport Standards Branch, Policy and Innovation Division, 
Aircraft Certification Service.
[FR Doc. 2019-23798 Filed 10-30-19; 8:45 am]
 BILLING CODE 4910-13-P


