Special Conditions: Gulfstream Aerospace Corporation Model GVII Series Airplane; Electro-Hydraulically Actuated Seats Equipped With Backup Power Supply, 31522-31524 [2019-14010]
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Federal Register / Vol. 84, No. 127 / Tuesday, July 2, 2019 / Proposed Rules
special nuclear material waste as
defined in regulations or orders of the
Commission;
G. The regulation of the disposal of
such other byproduct, source, or special
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should, because of the hazards or
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khammond on DSKBBV9HB2PROD with PROPOSALS
ARTICLE V
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Commission and State programs for
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programs of the State and the
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hazards of radiation and to assure that
the State’s program will continue to be
VerDate Sep<11>2014
16:06 Jul 01, 2019
Jkt 247001
compatible with the program of the
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BILLING CODE 7590–01–P
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(2) the State has not complied with one
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Pursuant to Section 274j. of the Act,
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Commission, an emergency situation
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a State program to be adequate to
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respect to the materials covered by this
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Done at [location] this [date] day of
[month], 2019.
For the Nuclear Regulatory Commission.
Kristine L. Svinicki,
Chairman.
Done at [location] this [date] day of
[month], 2019.
For the State of Vermont.
Philip B. Scott,
Governor.
[FR Doc. 2019–13453 Filed 7–1–19; 8:45 am]
ARTICLE VII
PO 00000
ARTICLE IX
This Agreement shall become
effective on [date], and shall remain in
effect unless and until such time as it is
terminated pursuant to Article VIII.
Sfmt 4702
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 25
[Docket No. FAA–2019–0470; Notice No. 25–
19–10–SC]
Special Conditions: Gulfstream
Aerospace Corporation Model GVII
Series Airplane; Electro-Hydraulically
Actuated Seats Equipped With Backup
Power Supply
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed special
conditions.
AGENCY:
This action proposes special
conditions for the Gulfstream Aerospace
Corporation (Gulfstream) Model GVII
series airplane. These airplanes, as
modified by Gulfstream, 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 electrohydraulically actuated seats equipped
with backup power supply. The
applicable airworthiness regulations do
not contain adequate or appropriate
safety standards for this design feature.
These proposed 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: Send comments on or before
August 1, 2019.
ADDRESSES: Send comments identified
by Docket No. FAA–2019–0470 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.
SUMMARY:
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Federal Register / Vol. 84, No. 127 / Tuesday, July 2, 2019 / Proposed Rules
• 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
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:
Alan Sinclair, AIR–675, Airframe and
Cabin Safety Section, Transport
Standards Branch, Policy and
Innovation Division, Aircraft
Certification Service, Federal Aviation
Administration, 2200 South 216th
Street, Des Moines, Washington 98198;
telephone and fax 206–231–3215; email
alan.sinclair@faa.gov.
SUPPLEMENTARY INFORMATION:
khammond on DSKBBV9HB2PROD with PROPOSALS
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.
VerDate Sep<11>2014
16:06 Jul 01, 2019
Jkt 247001
Background
On October 12, 2018, Gulfstream
applied for a supplemental type
certificate for electro-hydraulically
actuated seats equipped with backup
power supply in the Model GVII series
airplane. The Gulfstream Model GVII
series airplane, currently approved
under Type Certificate No. T00021AT,
is twin-engine, transport-category
airplane with seating for 19 passengers
and a maximum takeoff weight of
79,600 pounds.
Type Certification Basis
Under the provisions of title 14, Code
of Federal Regulations (14 CFR) 21.101,
Gulfstream must show that the Model
GVII series airplane, as changed,
continues to meet the applicable
provisions of the regulations listed in
Type Certificate No. T00021AT 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 Gulfstream Model GVII series
airplane 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 applicant apply
for a supplemental type certificate to
modify any other model included on the
same type certificate 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 Gulfstream Model GVII
series airplane 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 Gulfstream Model GVII series
airplane will incorporate the following
novel or unusual design features:
Hydraulically actuated components
on airplane seats, including hydraulic
reservoir, pump, actuators, and backup
power systems.
PO 00000
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31523
Discussion
Hydraulically actuated components
and backup power systems on airplane
seats are considered novel or unusual by
the FAA. Therefore, we developed
special conditions that contain the
additional standards that the
Administrator considers necessary to
establish a level of safety equivalent to
that established by the existing
airworthiness standards.
The FAA has considered the
installation of seats with these features
to have four primary safety concerns:
1. Reliability of the backup power
supply;
2. Safety hazards to the occupants
from the hydraulically actuated
components of the seat;
3. Structural integrity of the hydraulic
components; and
4. Flammability.
Emergency exits must be accessible to
the passengers, and the effectiveness of
evacuation must be maintained. Typical
airplane seats can be positioned
manually to the lateral (track) and
directional (swivel) taxi, takeoff, and
landing (TT&L) position by mechanical
means, so that the seats can be
positioned accordingly in the event of a
loss of cabin power. For this electrohydraulically operated seat design, in
lieu of a manual means to re-position
the hydraulically operated seat features
(backrest, seat pan, and leg-rest
deployment) for TT&L, a backup power
supply (BPS) temporarily powers the
hydraulic system in the event of loss of
cabin power. The BPS is deployed, and
intended only for use, in the event of a
loss of cabin power. If the seats are
installed in the path of the emergency
over-wing exits, failure to return the seat
to a TT&L position may have an adverse
effect on evacuation. Substantiation of
14 CFR 25.809(b) and 25.813(c)(2)(ii)
must be shown with the seats in their
most adverse positions.
It must be shown that the
hydraulically actuated components of
the seat pose no safety hazard to the
occupants or airplane. This includes
injuries caused by crushing of airplane
occupants who are between the
hydraulically actuated components and
any part of the passenger cabin when
seat features (e.g., leg rest or backrest)
are actuated. Additionally, the risk of
loss of function of a control or proximity
switch, resulting in the pump motor
commanded to remain pumping after
the hydraulic actuator(s) have reached
their minimum or maximum limit, must
not cause the overloaded motor to
overheat, a condition that could result
in fire.
The FAA has also considered the
emergency-landing dynamic conditions
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Federal Register / Vol. 84, No. 127 / Tuesday, July 2, 2019 / Proposed Rules
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for the installation of electrohydraulically actuated seats. The
applicant must show that the hydraulic
system (actuators, reservoir, lines, etc.)
remains intact and free from leakage
under the conditions specified in
§ 25.562. Testing of each seat’s
hydraulic system per § 25.1435(c) may
be conducted off of the airplane.
Flammability of hydraulic fluid used
in the seat-movement mechanism must
be considered. If the fluid is flammable,
it could contribute to a post-crash or inflight fire. Any failure modes that would
result in release of the flammable
hydraulic fluid during a post-crash or
in-flight fire, causing such fluid to
materially increase an existing fire, must
be examined. Examples of this could be
flex lines burning through and releasing
the flammable hydraulic fluid, or the
fluid reservoir could be heated in a fire,
resulting in a boiling-liquid, expandingvapor explosion. The potential for
spontaneous ignition of the fluid
coming into contact with hot surfaces or
other ignition sources should also be
addressed. The applicant should
examine any possible failure mode in
which the flammable hydraulic fluid
could be absorbed into materials, such
as the seat foam and fabric, carpeting,
etc. The applicant must show that any
fluid-soaked seat parts remain selfextinguishing. The applicant must also
show that flammability of dry residue,
which may be present from a slow leak
or fluid seepage, does not degrade the
flammability characteristics of any
materials the fluid contacts, to a level
below the requirements specified in
§ 25.853.
These proposed 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 proposed
special conditions are applicable to the
Gulfstream Model GVII series airplane.
Should Gulfstream apply at a later date
for a supplemental type certificate to
modify any other model included on
Type Certificate No. T00021AT to
incorporate the same novel or unusual
design feature, these special conditions
would apply to that model as well.
Conclusion
This action affects only certain novel
or unusual design features on one model
series of airplane. It is not a rule of
general applicability and affects only
the applicant who applied to the FAA
for approval of these features on the
airplane.
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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:
Issued in Des Moines, Washington, on June
21, 2019.
Christopher R. Parker,
Acting Manager, Transport Standards
Branch, Policy and Innovation Division,
Aircraft Certification Service.
[FR Doc. 2019–14010 Filed 7–1–19; 8:45 am]
Authority: 49 U.S.C. 106(f), 106(g), 40113,
44701, 44702, 44704.
BILLING CODE 4910–13–P
The Proposed Special Conditions
Accordingly, the Federal Aviation
Administration (FAA) proposes the
following special conditions as part of
the type certification basis for Model
GVII series airplanes modified by
Gulfstream Aerospace Corporation.
1. It must be shown that the
probability of failure of the backup
power supply to return seat components
to the required taxi, takeoff, and landing
position is no greater than 10¥5 per
flight hour.
2. It must be shown that the
hydraulically actuated components of
the seat pose no safety hazard to the
occupants. Hazards to be considered,
per the latest revision of Advisory
Circular 25.1309–1, at a minimum are:
a. Injuries caused by crushing of
airplane occupants who are between the
hydraulically actuated components and
any part of the passenger cabin when
the leg rest or backrest is actuated.
b. The risk of loss of function of a
control or proximity switch resulting in
the pump motor being commanded to
stay on after the hydraulic actuator(s)
have reached their minimum or
maximum limit, creating potential for
motor overheating or fire.
c. The potential for a significant
contribution to a fire in the event fluid
comes into contact with hot surfaces or
other ignition sources, and the potential
for release of toxic or flammable vapors
and gasses.
3. It must be shown that the hydraulic
system (actuators, reservoir, lines, etc.)
remains intact and free from leakage
under the conditions specified in
§ 25.562. Testing of each seat’s
hydraulic system per § 25.1435(c) may
be conducted off of the airplane.
4. Section 25.863 requires
consideration of any effects the
hydraulic fluid, including the fluid as a
dry residue, could have on combustible
or absorbing materials. The
characteristics of such flammable fluid
in these conditions must be tested to the
requirements of § 25.853(a) and (c), or
the materials must be shielded in a
manner that prevents contact by the
fluid. However, as an alternative to such
testing or shielding, the applicant may
provide, in accordance with § 25.863(c),
a quick-acting means that alerts the
crew that hydraulic fluid has leaked.
DEPARTMENT OF TRANSPORTATION
PO 00000
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Fmt 4702
Sfmt 4702
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2019–0520; Product
Identifier 2019–NM–046–AD]
RIN 2120–AA64
Airworthiness Directives; Saab AB,
Saab Aeronautics (Formerly Known as
Saab AB, Saab Aerosystems)
Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
The FAA proposes to adopt a
new airworthiness directive (AD) for
certain Saab AB, Saab Aeronautics
Model SAAB 2000 airplanes. This
proposed AD was prompted by reports
of loose and irregular fasteners at the
forward end of the nacelle upper
longeron, where the bulkhead frame and
struts are attached to the engine
mounting structure (EMS). This
proposed AD would require
modification of the EMS and structural
attachments. The FAA is proposing this
AD to address the unsafe condition on
these products.
DATES: The FAA must receive comments
on this proposed AD by August 16,
2019.
SUMMARY:
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: Deliver to Mail
address above between 9 a.m. and 5
p.m., Monday through Friday, except
Federal holidays.
For service information identified in
this NPRM, contact Saab AB, Saab
Aeronautics, SE–581 88, Linko¨ping,
Sweden; phone: +46 13 18 5591; fax:
ADDRESSES:
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]]>Agencies
[Federal Register Volume 84, Number 127 (Tuesday, July 2, 2019)]
[Proposed Rules]
[Pages 31522-31524]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2019-14010]
=======================================================================
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 25
[Docket No. FAA-2019-0470; Notice No. 25-19-10-SC]
Special Conditions: Gulfstream Aerospace Corporation Model GVII
Series Airplane; Electro-Hydraulically Actuated Seats Equipped With
Backup Power Supply
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Notice of proposed special conditions.
-----------------------------------------------------------------------
SUMMARY: This action proposes special conditions for the Gulfstream
Aerospace Corporation (Gulfstream) Model GVII series airplane. These
airplanes, as modified by Gulfstream, 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 electro-hydraulically actuated seats equipped with
backup power supply. The applicable airworthiness regulations do not
contain adequate or appropriate safety standards for this design
feature. These proposed 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: Send comments on or before August 1, 2019.
ADDRESSES: Send comments identified by Docket No. FAA-2019-0470 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.
[[Page 31523]]
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 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: Alan Sinclair, AIR-675, Airframe and
Cabin Safety Section, Transport Standards Branch, Policy and Innovation
Division, Aircraft Certification Service, Federal Aviation
Administration, 2200 South 216th Street, Des Moines, Washington 98198;
telephone and fax 206-231-3215; email [email protected].
SUPPLEMENTARY INFORMATION:
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 October 12, 2018, Gulfstream applied for a supplemental type
certificate for electro-hydraulically actuated seats equipped with
backup power supply in the Model GVII series airplane. The Gulfstream
Model GVII series airplane, currently approved under Type Certificate
No. T00021AT, is twin-engine, transport-category airplane with seating
for 19 passengers and a maximum takeoff weight of 79,600 pounds.
Type Certification Basis
Under the provisions of title 14, Code of Federal Regulations (14
CFR) 21.101, Gulfstream must show that the Model GVII series airplane,
as changed, continues to meet the applicable provisions of the
regulations listed in Type Certificate No. T00021AT 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 Gulfstream Model GVII series
airplane 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 applicant apply for a supplemental type
certificate to modify any other model included on the same type
certificate 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 Gulfstream Model GVII series airplane 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 Gulfstream Model GVII series airplane will incorporate the
following novel or unusual design features:
Hydraulically actuated components on airplane seats, including
hydraulic reservoir, pump, actuators, and backup power systems.
Discussion
Hydraulically actuated components and backup power systems on
airplane seats are considered novel or unusual by the FAA. Therefore,
we developed special conditions that contain the additional standards
that the Administrator considers necessary to establish a level of
safety equivalent to that established by the existing airworthiness
standards.
The FAA has considered the installation of seats with these
features to have four primary safety concerns:
1. Reliability of the backup power supply;
2. Safety hazards to the occupants from the hydraulically actuated
components of the seat;
3. Structural integrity of the hydraulic components; and
4. Flammability.
Emergency exits must be accessible to the passengers, and the
effectiveness of evacuation must be maintained. Typical airplane seats
can be positioned manually to the lateral (track) and directional
(swivel) taxi, takeoff, and landing (TT&L) position by mechanical
means, so that the seats can be positioned accordingly in the event of
a loss of cabin power. For this electro-hydraulically operated seat
design, in lieu of a manual means to re-position the hydraulically
operated seat features (backrest, seat pan, and leg-rest deployment)
for TT&L, a backup power supply (BPS) temporarily powers the hydraulic
system in the event of loss of cabin power. The BPS is deployed, and
intended only for use, in the event of a loss of cabin power. If the
seats are installed in the path of the emergency over-wing exits,
failure to return the seat to a TT&L position may have an adverse
effect on evacuation. Substantiation of 14 CFR 25.809(b) and
25.813(c)(2)(ii) must be shown with the seats in their most adverse
positions.
It must be shown that the hydraulically actuated components of the
seat pose no safety hazard to the occupants or airplane. This includes
injuries caused by crushing of airplane occupants who are between the
hydraulically actuated components and any part of the passenger cabin
when seat features (e.g., leg rest or backrest) are actuated.
Additionally, the risk of loss of function of a control or proximity
switch, resulting in the pump motor commanded to remain pumping after
the hydraulic actuator(s) have reached their minimum or maximum limit,
must not cause the overloaded motor to overheat, a condition that could
result in fire.
The FAA has also considered the emergency-landing dynamic
conditions
[[Page 31524]]
for the installation of electro-hydraulically actuated seats. The
applicant must show that the hydraulic system (actuators, reservoir,
lines, etc.) remains intact and free from leakage under the conditions
specified in Sec. 25.562. Testing of each seat's hydraulic system per
Sec. 25.1435(c) may be conducted off of the airplane.
Flammability of hydraulic fluid used in the seat-movement mechanism
must be considered. If the fluid is flammable, it could contribute to a
post-crash or in-flight fire. Any failure modes that would result in
release of the flammable hydraulic fluid during a post-crash or in-
flight fire, causing such fluid to materially increase an existing
fire, must be examined. Examples of this could be flex lines burning
through and releasing the flammable hydraulic fluid, or the fluid
reservoir could be heated in a fire, resulting in a boiling-liquid,
expanding-vapor explosion. The potential for spontaneous ignition of
the fluid coming into contact with hot surfaces or other ignition
sources should also be addressed. The applicant should examine any
possible failure mode in which the flammable hydraulic fluid could be
absorbed into materials, such as the seat foam and fabric, carpeting,
etc. The applicant must show that any fluid-soaked seat parts remain
self-extinguishing. The applicant must also show that flammability of
dry residue, which may be present from a slow leak or fluid seepage,
does not degrade the flammability characteristics of any materials the
fluid contacts, to a level below the requirements specified in Sec.
25.853.
These proposed 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 proposed special conditions are
applicable to the Gulfstream Model GVII series airplane. Should
Gulfstream apply at a later date for a supplemental type certificate to
modify any other model included on Type Certificate No. T00021AT to
incorporate the same novel or unusual design feature, these special
conditions would apply to that model as well.
Conclusion
This action affects only certain novel or unusual design features
on one model series of airplane. It is not a rule of general
applicability and affects only the applicant who applied to the FAA for
approval of these features on the airplane.
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 Proposed Special Conditions
Accordingly, the Federal Aviation Administration (FAA) proposes the
following special conditions as part of the type certification basis
for Model GVII series airplanes modified by Gulfstream Aerospace
Corporation.
1. It must be shown that the probability of failure of the backup
power supply to return seat components to the required taxi, takeoff,
and landing position is no greater than 10-5 per flight
hour.
2. It must be shown that the hydraulically actuated components of
the seat pose no safety hazard to the occupants. Hazards to be
considered, per the latest revision of Advisory Circular 25.1309-1, at
a minimum are:
a. Injuries caused by crushing of airplane occupants who are
between the hydraulically actuated components and any part of the
passenger cabin when the leg rest or backrest is actuated.
b. The risk of loss of function of a control or proximity switch
resulting in the pump motor being commanded to stay on after the
hydraulic actuator(s) have reached their minimum or maximum limit,
creating potential for motor overheating or fire.
c. The potential for a significant contribution to a fire in the
event fluid comes into contact with hot surfaces or other ignition
sources, and the potential for release of toxic or flammable vapors and
gasses.
3. It must be shown that the hydraulic system (actuators,
reservoir, lines, etc.) remains intact and free from leakage under the
conditions specified in Sec. 25.562. Testing of each seat's hydraulic
system per Sec. 25.1435(c) may be conducted off of the airplane.
4. Section 25.863 requires consideration of any effects the
hydraulic fluid, including the fluid as a dry residue, could have on
combustible or absorbing materials. The characteristics of such
flammable fluid in these conditions must be tested to the requirements
of Sec. 25.853(a) and (c), or the materials must be shielded in a
manner that prevents contact by the fluid. However, as an alternative
to such testing or shielding, the applicant may provide, in accordance
with Sec. 25.863(c), a quick-acting means that alerts the crew that
hydraulic fluid has leaked.
Issued in Des Moines, Washington, on June 21, 2019.
Christopher R. Parker,
Acting Manager, Transport Standards Branch, Policy and Innovation
Division, Aircraft Certification Service.
[FR Doc. 2019-14010 Filed 7-1-19; 8:45 am]
BILLING CODE 4910-13-P
