Special Conditions: Airbus Model A330 Series Airplanes; Seats With Inertia Locking Devices, 24701-24703 [2019-11071]
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24701
Rules and Regulations
Federal Register
Vol. 84, No. 103
Wednesday, May 29, 2019
This section of the FEDERAL REGISTER
contains regulatory documents having general
applicability and legal effect, most of which
are keyed to and codified in the Code of
Federal Regulations, which is published under
50 titles pursuant to 44 U.S.C. 1510.
employees-of-the-national-mediationboard.
The Code of Federal Regulations is sold by
the Superintendent of Documents.
This rule is not a significant rule for
purposes of Executive Order 12866 and
has not been reviewed by the Office of
Management and Budget.
NATIONAL MEDIATION BOARD
[Docket No. C–7188]
RIN 3209–AA47
Supplemental Standards of Ethical
Conduct for Employees of the National
Mediation Board
National Mediation Board.
Final rule.
AGENCY:
The National Mediation
Board (NMB or Board), with the
concurrence of the U.S. Office of
Government Ethics (OGE), is issuing a
final rule for employees of the NMB that
supplements the executive branch-wide
Standards of Ethical Conduct
(Standards) issued by OGE. The
supplemental regulation requires NMB
employees to obtain approval before
engaging in outside employment.
DATES: This final rule is effective May
29, 2019.
FOR FURTHER INFORMATION CONTACT:
Mary Johnson, General Counsel,
National Mediation Board, 202–692–
5050, infoline@nmb.gov.
SUPPLEMENTARY INFORMATION:
khammond on DSKBBV9HB2PROD with RULES
As required by the Regulatory
Flexibility Act, the NMB certifies that
these regulatory changes will not have
a significant impact on small business
entities. This rule will not have any
significant impact on the quality of the
human environment under the National
Environmental Policy Act.
Paperwork Reduction Act
SUMMARY:
The NMB has determined that the
Paperwork Reduction Act does not
apply because this regulation does not
contain any information collection
requirements that require the approval
of the Office of Management and
Budget.
List of Subjects in 5 CFR Part 10101
Conflicts of interests, Government
employees.
Dated: May 1, 2019.
By direction of the Board.
Mary Johnson,
General Counsel, National Mediation Board.
Emory A. Rounds, III,
Director, U.S. Office of Government Ethics.
I. Background
Chapter CI—National Mediation Board
On November 1, 2018, the NMB, with
OGE’s concurrence, published an
interim final rule in the Federal
Register, 83 FR 54861, adopting agencyspecific supplemental regulations
requiring NMB employees to obtain
approval before engaging in outside
employment. The interim final rule
provided a 60 day comment period,
which ended on December 31, 2018.
The NMB did not receive any
comments. The rationale for the interim
final rule, which the NMB is now
adopting as final, is explained in the
preamble at: https://
www.federalregister.gov/documents/
2018/11/01/2018-23548/supplementalstandards-of-ethical-conduct-for-
PART 10101—SUPPLEMENTAL
STANDARDS OF ETHICAL CONDUCT
FOR EMPLOYEES OF THE NATIONAL
MEDIATION BOARD
VerDate Sep<11>2014
16:21 May 28, 2019
Jkt 247001
Accordingly, the interim rule adding
5 CFR chapter CI, consisting of part
10101, which was published at 83 FR
54861 on November 1, 2018, is adopted
as final without change.
■
[FR Doc. 2019–11163 Filed 5–28–19; 8:45 am]
BILLING CODE 7550–01–P
PO 00000
Federal Aviation Administration
14 CFR Part 25
Executive Order 12866
Regulatory Flexibility Act
5 CFR Chapter CI
ACTION:
II. Matters of Regulatory Procedure
DEPARTMENT OF TRANSPORTATION
[Docket No. FAA–2019–0235; Special
Conditions No. 25–747–SC]
Special Conditions: Airbus Model A330
Series Airplanes; Seats With Inertia
Locking Devices
Federal Aviation
Administration (FAA), DOT.
ACTION: Final special conditions.
AGENCY:
These special conditions are
issued for the Airbus Model A330 series
airplane. 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. 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: Effective May 29, 2019.
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:
SUMMARY:
Background
On February 13, 2019, Airbus applied
for a change to Type Certificate No.
A46NM for seats with inertia locking
devices in Model A330 series airplanes.
The Model A330 series airplane is a
twin-engine, transport-category airplane
with a maximum takeoff weight of
533,518 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 Model A330
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29MYR1
24702
Federal Register / Vol. 84, No. 103 / Wednesday, May 29, 2019 / Rules and Regulations
series airplanes, as changed, continue to
meet the applicable provisions of the
regulations listed in Type Certificate No.
A46NM, 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 Airbus Model A330 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, 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, Airbus Model A330 series
airplanes must comply with the fuelvent and exhaust-emission requirements
of 14 CFR part 34, and the noisecertification 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.
khammond on DSKBBV9HB2PROD with RULES
Novel or Unusual Design Features
Airbus Model A330 series airplanes
will incorporate the following novel or
unusual design features:
Seats with inertia locking devices
(ILD).
Discussion
Airbus will install, in Model A330
series airplanes, Thompson Aero
Seating Ltd. 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
VerDate Sep<11>2014
16:21 May 28, 2019
Jkt 247001
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 worstcase dynamic loading specified in
§ 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 seatlocking device does not deploy.
The normal means of satisfying the
structural and occupant protection
requirements of § 25.562 result in a nonquantified, 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 stepchange 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) 25.561–1B. 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 25.561–1B.
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
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
PO 00000
Frm 00002
Fmt 4700
Sfmt 4700
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.
Discussion of Comments
The FAA issued Notice of Proposed
Special Conditions No. 25–19–02–SC
for the Airbus Model A330 series
airplane. This document was published
in the Federal Register on April 16,
2019 (84 FR 15531). No comments were
received, and the special conditions are
adopted as proposed.
Applicability
As discussed above, these special
conditions are applicable to Airbus
Model A330 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 one 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
A330 series airplanes.
In addition to the requirements of
§ 25.562, passenger seats incorporating
inertia locking devices (ILD)s 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
§ 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
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29MYR1
khammond on DSKBBV9HB2PROD with RULES
Federal Register / Vol. 84, No. 103 / Wednesday, May 29, 2019 / Rules and Regulations
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
§ 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 § 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 § 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 ninety-five
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.
VerDate Sep<11>2014
16:21 May 28, 2019
Jkt 247001
Issued in Des Moines, Washington, on May
22, 2019.
Victor Wicklund,
Manager, Transport Standards Branch, Policy
and Innovation Division, Aircraft
Certification Service.
[FR Doc. 2019–11071 Filed 5–28–19; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2018–0726; Product
Identifier 2017–SW–097–AD; Amendment
39–19638; AD 2019–09–04]
RIN 2120–AA64
Airworthiness Directives; Leonardo
S.p.A. (Type Certificate Previously
Held by Finmeccanica S.p.A.,
AgustaWestland S.p.A) Helicopters
We are adopting a new
airworthiness directive (AD) for certain
Leonardo S.p.A. (Type Certificate
previously held by Finmeccanica S.p.A.,
AgustaWestland S.p.A.) Model
AW109SP helicopters. This AD requires
inspecting and altering the rescue hoist.
This AD was prompted by a report of a
damaged hoist cable that detached after
load application. The actions of this AD
are intended to address an unsafe
condition on these products.
DATES: This AD is effective July 3, 2019.
The Director of the Federal Register
approved the incorporation by reference
of a certain document listed in this AD
as of July 3, 2019.
ADDRESSES: For service information
identified in this final rule, contact
Leonardo S.p.A. Helicopters, Matteo
Ragazzi, Head of Airworthiness, Viale
G.Agusta 520, 21017 C.Costa di
Samarate (Va) Italy; telephone +39–
0331–711756; fax +39–0331–229046; or
at https://www.leonardocompany.com/
en/home. You may review the
referenced service information at the
FAA, Office of the Regional Counsel,
Southwest Region, 10101 Hillwood
Pkwy., Room 6N–321, Fort Worth, TX
76177. It is also available on the internet
at https://www.regulations.gov by
searching for and locating Docket No.
FAA–2018–0726.
Examining the AD Docket
You may examine the AD docket on
the internet at https://
www.regulations.gov by searching for
Fmt 4700
Sfmt 4700
FOR FURTHER INFORMATION CONTACT:
David Hatfield, Aviation Safety
Engineer, Safety Management Section,
Rotorcraft Standards Branch, FAA,
10101 Hillwood Pkwy., Fort Worth, TX
76177; telephone (817) 222–5110; email
david.hatfield@faa.gov.
Discussion
SUMMARY:
Frm 00003
and locating Docket No. FAA–2018–
0726; or in person at Docket Operations
between 9 a.m. and 5 p.m., Monday
through Friday, except Federal holidays.
The AD docket contains this final rule,
the European Aviation Safety Agency
(EASA) AD, any incorporated-byreference service information, the
regulatory evaluation, any comments
received, and other information. The
street address for Docket Operations
(phone: 800–647–5527) is U.S.
Department of Transportation, Docket
Operations, M–30, West Building
Ground Floor, Room W12–140, 1200
New Jersey Avenue SE, Washington, DC
20590.
SUPPLEMENTARY INFORMATION:
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
AGENCY:
PO 00000
24703
We issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 by adding an AD that would
apply to certain Leonardo S.p.A.
(formerly Finmeccanica S.p.A,
AgustaWestland S.p.A.) Model
AW109SP helicopters. The NPRM
published in the Federal Register on
August 21, 2018 (83 FR 42230). The
NPRM was prompted by a report of a
damaged hoist cable that detached after
load application. The NPRM proposed
to require inspecting and altering the
rescue hoist.
We are issuing this AD to address
chafing of a rescue hoist cable. This
condition could result in detachment of
an external load and subsequent injury
to persons being lifted.
EASA, which is the Technical Agent
for the Member States of the European
Union, has issued AD No. 2017–0025,
dated February 14, 2017, to correct an
unsafe condition for certain Leonardo
S.p.A. (formerly Finmeccanica S.p.A.
and AgustaWestland S.p.A.) Model
AW109SP helicopters. EASA advises
that a hoist cable became snagged
behind a hoist handle assembly nut and
broke during a dummy load application.
EASA further advises that this condition
could result in detachment of an
external load, and subsequent personal
injury or injury to persons on the
ground. To address this unsafe
condition, the EASA AD requires
inspecting the hoist cable, modifying
the rescue hoist handle, and amending
the rescue hoist pre-flight inspection
described in the rotorcraft flight manual.
E:\FR\FM\29MYR1.SGM
29MYR1
]]>Agencies
[Federal Register Volume 84, Number 103 (Wednesday, May 29, 2019)]
[Rules and Regulations]
[Pages 24701-24703]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2019-11071]
=======================================================================
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 25
[Docket No. FAA-2019-0235; Special Conditions No. 25-747-SC]
Special Conditions: Airbus Model A330 Series Airplanes; Seats
With Inertia Locking Devices
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final special conditions.
-----------------------------------------------------------------------
SUMMARY: These special conditions are issued for the Airbus Model A330
series airplane. 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. 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: Effective May 29, 2019.
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 [email protected].
SUPPLEMENTARY INFORMATION:
Background
On February 13, 2019, Airbus applied for a change to Type
Certificate No. A46NM for seats with inertia locking devices in Model
A330 series airplanes. The Model A330 series airplane is a twin-engine,
transport-category airplane with a maximum takeoff weight of 533,518
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 Model A330
[[Page 24702]]
series airplanes, as changed, continue to meet the applicable
provisions of the regulations listed in Type Certificate No. A46NM, 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 Airbus Model A330 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, Airbus Model A330 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
Airbus Model A330 series airplanes will incorporate the following
novel or unusual design features:
Seats with inertia locking devices (ILD).
Discussion
Airbus will install, in Model A330 series airplanes, Thompson Aero
Seating Ltd. 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) 25.561-1B. 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 25.561-1B. 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 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.
Discussion of Comments
The FAA issued Notice of Proposed Special Conditions No. 25-19-02-
SC for the Airbus Model A330 series airplane. This document was
published in the Federal Register on April 16, 2019 (84 FR 15531). No
comments were received, and the special conditions are adopted as
proposed.
Applicability
As discussed above, these special conditions are applicable to
Airbus Model A330 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 one 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 A330 series airplanes.
In addition to the requirements of Sec. 25.562, passenger seats
incorporating inertia locking devices (ILD)s 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
[[Page 24703]]
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
ninety-five 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 May 22, 2019.
Victor Wicklund,
Manager, Transport Standards Branch, Policy and Innovation Division,
Aircraft Certification Service.
[FR Doc. 2019-11071 Filed 5-28-19; 8:45 am]
BILLING CODE 4910-13-P
