Special Conditions: The Boeing Company, Leonardo S.p.a. Model AW139 Helicopter; Use of New Hovering Out of Ground Effect Utility Power on the Model AW139 Helicopter, 52854-52856 [2022-18722]
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Federal Register / Vol. 87, No. 167 / Tuesday, August 30, 2022 / Rules and Regulations
16. Minimum Value Option
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(c) * * *
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16(b)(1) .....................................
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§ 457.149
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500 cartons × $2 = value of sold production ($6 price received minus $4.25 allowable costs =
$1.75. The $2.00 minimum value option price is greater than $1.75).
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[Amended]
[Amended]
9. In § 457.167, in the ‘‘Pecan Revenue
Crop Insurance Provisions’’, in section
4, in paragraph (b), remove the words
‘‘Web site’’ and add ‘‘website’’ in its
place.
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§ 457.173
[Amended]
10. In § 457.173, in the ‘‘Florida
Avocado Crop Insurance Provisions’’, in
section 8, in paragraph (a)(3)(i), remove
the words ‘‘varieties of’’ and add
‘‘varieties and mid varieties of’’ in their
place.
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§ 457.175
[Amended]
11. In § 457.175, in the ‘‘California
Avocado Crop Provisions’’, in section
11, in paragraph (b)(2), remove ‘‘11(c)’’
and add ‘‘11(c))’’ in its place.
■
Marcia Bunger,
Manager, Federal Crop Insurance
Corporation.
[FR Doc. 2022–18595 Filed 8–29–22; 8:45 am]
BILLING CODE 3410–08–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 29
khammond on DSKJM1Z7X2PROD with RULES
[Docket No. FAA–2022–0183; Special
Conditions No. 29–056–SC]
Special Conditions: The Boeing
Company, Leonardo S.p.a. Model
AW139 Helicopter; Use of New
Hovering Out of Ground Effect Utility
Power on the Model AW139 Helicopter
Federal Aviation
Administration (FAA), DOT.
ACTION: Final special conditions.
AGENCY:
VerDate Sep<11>2014
15:56 Aug 29, 2022
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These special conditions are
issued for the Leonardo S.p.a.
(Leonardo) Model AW139 helicopter.
This helicopter as modified by The
Boeing Company (Boeing) will have a
novel or unusual design feature when
compared to the state of technology
envisioned in the airworthiness
standards for helicopters. This design
feature incorporates a 2.5-minute all
engines operating (AEO) power
restricted for use at helicopter operating
speeds below 60 knots indicated
airspeed (KIAS), and hovering out of
ground effect (HOGE). This power is
referred to as 2.5-minute HOGE utility
power (HUP), or 2.5-minute HUP. The
2.5-minute HUP is greater than the
transmission power limitations
associated with takeoff and AEO. 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 September 29, 2022.
FOR FURTHER INFORMATION CONTACT:
Dorina Mihail, Propulsion and Energy
Section, AIR–624, Technical Innovation
Policy Branch, Policy and Innovation
Division, Aircraft Certification Service,
Federal Aviation Administration, 1200
District Avenue, Burlington, MA 01803;
telephone 781–238–7153; fax 781–238–
7199; email Dorina.Mihail@faa.gov.
SUPPLEMENTARY INFORMATION:
SUMMARY:
8. Amend § 457.149 in the ‘‘Table
Grape Crop Provisions’’ by:
■ a. In section 3, in paragraph (b),
removing the phrase ‘‘have same
percentage relationship’’ and adding
‘‘have the same percentage relationship’’
in its place; and
■ b. In section 11, in paragraph (c),
removing the words ‘‘meet
requirements’’ and adding ‘‘meet the
requirements’’ in their place.
■
§ 457.167
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Background
On September 18, 2020, Boeing
applied for a supplemental type
certificate for performance envelope
expansion of the Leonardo Model
AW139 helicopter. The AW139
helicopter as changed, is a medium
twin-engine 14 CFR part 29 transport
category B helicopter with a 15,521
pounds (7040 Kg) maximum takeoff
weight and a maximum seating capacity
of nine passengers and two crew. This
helicopter takeoff and landing altitude
is 10,000 feet density altitude (Hd), and
the forward flight altitude is 11,000 feet
Hd. This helicopter has the capability
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1,000
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for Category II instrument landing
system (ILS) approaches. The Model
AW139 helicopter as changed will be
equipped with two PT6C–67C1 engines.
The Model AW139 helicopter as
changed will have a 2.5-minute HUP for
use in HOGE that exceeds the
transmission power limitations
associated with takeoff and AEO.
Type Certification Basis
Under the provisions of 14 CFR
21.101, Boeing must show that the
Leonardo Model AW139 helicopter, as
changed, continues to meet the
applicable provisions of the regulations
listed in Type Certificate No. R00002RD,
or the applicable regulations in effect on
the date of application for the change,
except for earlier amendments as agreed
upon by the FAA. The proposed
certification basis for this supplemental
type certificate is as follows:
14 CFR 21.29 and Part 29,
Amendment 29–1 through Amendment
29–45 with 14 CFR 29.25, 29.143,
29.173, 29.175, 29.177 at Amendment
29–51, and 14 CFR 29.773 at
Amendment 29–57.
Equivalent Level of Safety Findings
issued against:
14 CFR 29.1305, as documented in the
AB139 FAA Memo, dated December 20,
2004.
If the Administrator finds that the
applicable airworthiness regulations
(e.g., 14 CFR part 29) do not contain
adequate or appropriate safety standards
for the Leonardo Model AW139
helicopter 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 Leonardo Model AW139
helicopter must comply with the noise
certification requirements of 14 CFR
part 36.
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Federal Register / Vol. 87, No. 167 / Tuesday, August 30, 2022 / Rules and Regulations
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 Feature
The Leonardo Model AW139
helicopter will incorporate a novel or
unusual design feature, which is a 2.5minute AEO power that is greater than
the transmission takeoff power
limitations associated with takeoff and
AEO. This power is restricted for use
when HOGE and at helicopter operating
speeds below 60 KIAS. The applicable
airworthiness regulations do not contain
adequate or appropriate safety standards
for this design feature.
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Discussion
The design feature will incorporate a
2.5-minute HUP that allows the pilot to
enter HOGE, operate in HOGE, and
depart from HOGE at high altitudes and
ambient atmospheric temperatures. The
use of the 2.5-minute HUP is limited to
periods of no longer than 2.5 minutes
each use, under AEO conditions, at
helicopter operating speeds below 60
KIAS and HOGE. Use of the 2.5-minute
HUP is not part of, or combined with a
takeoff operation.
Helicopter operation at the 2.5-minute
HUP will use the engine power higher
than the rated maximum continuous
power and limits but lower than the
rated takeoff power and limits and does
not exceed the 5 minute takeoff rating
for which the engines are type
certificated. Existing part 33 regulations
for the engines are adequate for the
helicopter 2.5-minute HUP.
Use of the 2.5-minute HUP exceeds
the helicopter transmission power
limitations associated with takeoff and
AEO. Existing part 29 regulations do not
recognize helicopter operation that
exceeds the transmission power
limitations associated with takeoff and
AEO. The special conditions that
address the use of the 2.5-minute HUP
on this model of helicopter, as modified
by Boeing, are as follows.
The Rotorcraft Flight Manual must
specify that the use of the 2.5-minute
HUP is limited to periods no longer than
2.5 minutes each, under AEO
conditions, at helicopter operating
speeds below 60 KIAS and HOGE.
Additionally, the Rotorcraft Flight
Manual must specify that use of the 2.5minute HUP is not part of, or combined
with, a takeoff operation.
The requirement added to § 29.49(c)
provides for the development of
helicopter performance data for 2.5minute HUP utilization.
VerDate Sep<11>2014
15:56 Aug 29, 2022
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The testing requirement added to
§ 29.923(d) consists of two applications
of 2.5-minute HUP torque and the
maximum speed per 10-hour cycle. The
10-hour cycle represents a run of 10
hours in length that is repeated 20
times, for a total of (at least) 200 hours
of endurance testing as required by
§ 29.923(a). Therefore, the testing added
to § 29.923(d) provides for 40
applications of the 2.5-minute HUP
during the 200-hour endurance test
specified in § 29.923(a). This testing is
added to § 29.923(d) ‘‘Endurance tests;
90 percent of maximum continuous
run,’’ since the 2.5-minute HUP is not
part of, or combined with, a takeoff
operation, as stated in these special
conditions and is expected to be used
during mid-mission.
The flight-test requirement added to
§ 29.1049 is intended to address the
hovering cooling provisions at the 2.5minute HUP and HOGE following
thermal stabilization at maximum
weight, mission representative power,
maximum altitude, and ambient
temperatures specified in § 29.1043(b).
The flight-test continues with cycling in
and out of the HUP mode, in a manner
representative of the intended use of the
2.5-minute HUP, per the instructions
specified in the Rotorcraft Flight
Manual. The repeated successive HUP
applications and time duration between
HUP cycles result in the most critical
condition for the cooling provisions
required by § 29.1041(a) and
§ 29.1041(b). The flight-test continues
with departing the hover and
transitioning to a maximum continuous
power climb at the best rate of climb
speed. Climb is continued for 5 minutes
after the highest temperatures are
observed or until the service ceiling is
reached.
The requirements added to § 29.1305
are means for the pilot to identify when
the 2.5-minute HUP level is achieved,
when the event begins, and when the
time interval expires. These means will
assist the pilot in managing the 2.5minute HUP short time duration in a
pilot high-workload environment.
The requirements added to § 29.1521
are similar to the powerplant limitations
for takeoff operations in § 29.1521(b),
modified to reflect the 2.5-minute HUP.
The requirement added to
§ 29.1587(b)(8) will require publishing
the performance data developed under
paragraph (b) of these special conditions
in the Rotorcraft Flight Manual. These
data must be clearly referenced to the
appropriate hover charts and specify
that they are not to be used for take-off
or landing determinations.
These special conditions contain the
additional safety standards that the
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52855
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. 29–22–01–SC
for the Leonardo Model AW139
helicopter, which was published in the
Federal Register on May 3, 2022 (87 FR
26143). The FAA did not receive any
comments.
Applicability
As discussed above, these special
conditions are applicable to the
Leonardo Model AW139 helicopter.
Should Boeing apply at a later date for
a supplemental type certificate to
modify any other model included on
Type Certificate No. R00002RD, to
incorporate 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 the
Leonardo Model AW139 helicopter. It is
not a rule of general applicability and
affects only the applicant who applied
to the FAA for approval of this feature
on the helicopter.
List of Subjects in 14 CFR Part 29
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 the Leonardo
S.p.a. Model AW139 helicopter, as
modified by The Boeing Company.
(a) The Rotorcraft Flight Manual must
state the following:
(1) Use of the 2.5-minute Hovering
Out of Ground Effect (HOGE) Utility
Power (2.5-minute HUP) is limited to a
period no longer than 2.5 minutes each,
under all engine operating (AEO)
conditions, at helicopter operating
speeds below 60 knots indicated
airspeed (KIAS) and HOGE.
(2) Use of the 2.5-minute HUP is not
part of, or combined with, a takeoff
operation.
(b) In addition to the requirements of
§ 29.49(c), the out-of-ground effect hover
performance must be determined over
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Federal Register / Vol. 87, No. 167 / Tuesday, August 30, 2022 / Rules and Regulations
the ranges of weight, altitude, and
temperatures for which certification is
requested with the 2.5-minute HUP.
(c) In addition to the requirements of
§ 29.923(d) when performing the
endurance test, the 2.5 minute all
engines operating must be performed
using two applications of 2.5-minute
HUP torque and the maximum speed for
use with 2.5-minute HUP torque, per 10hour cycle.
(d) In addition to the requirements of
§ 29.1049, the hovering cooling
provisions at the 2.5-minute HUP must
be shown as follows—
(1) Conduct a thermal stabilization at
maximum weight, mission
representative power, maximum
altitude, and ambient temperatures
specified in § 29.1043(b); following
stabilization, increase power to the 2.5minute HUP and HOGE for a duration
of 2.5 minutes (150 seconds).
(2) Cycle in and out the HUP mode in
a manner representative of the intended
use of the 2.5-minute HUP, and per the
instructions specified in the Rotorcraft
Flight Manual, if any. The HUP cycles
should account for repeated successive
HUP applications and time duration
between HUP cycles resulting in the
most critical condition for the cooling
provisions required by § 29.1041(a) and
§ 29.1041(b).
(3) Following the tests in paragraphs
(d)(1) and (d)(2) of these special
conditions, depart the hover and
transition to a maximum continuous
power climb at the best rate of climb
speed. Continue the climb until 5
minutes after the highest temperatures
are observed or until the service ceiling
is reached.
(e) In addition to the requirements of
§ 29.1305, the pilot must have the
means to identify the 2.5-minute HUP
time limit associated with its use as
follows—
(1) When the power level is achieved,
(2) when the event begins, and
(3) when the time interval expires.
These indications must be clear and
unambiguous to the pilot and must not
cause pilot confusion. The use of these
indications must be evaluated in
operationally relevant scenarios in
accordance with § 29.1523 for crew
workload.
(f) In addition to the requirements of
§ 29.1521, the use of the 2.5-minute
HUP must be limited by the following:
(1) The maximum rotational speed,
which may not be greater than—
(i) The maximum value determined
by the rotor design; or
(ii) The maximum value demonstrated
during the type tests;
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15:56 Aug 29, 2022
Jkt 256001
(2) The maximum allowable turbine
inlet or turbine outlet gas temperature
(for turbine engines);
(3) The maximum allowable power or
torque for each engine, considering the
power input limitations of the
transmission with all engines operating;
(4) The maximum allowable power or
torque for each engine considering the
power input limitations of the
transmission with one engine
inoperative;
(5) The time limit for the use of the
power corresponding to the limitations
established in paragraphs (f)(1) through
(f)(4) of these special conditions; and
(6) The maximum allowable engine
and transmission oil temperatures, if the
time limit established in paragraph (f)(5)
of these special conditions exceeds 2
minutes.
(7) Use of 2.5-minute HUP is limited
to HOGE only.
(g) In addition to the requirements of
§ 29.1587(b)(8), the Rotorcraft Flight
Manual must contain the out-of-ground
effect hover performance determined
under paragraph (b) of these special
conditions, and the maximum safe wind
demonstrated under the ambient
conditions for the data presented. In
addition, the Rotorcraft Flight Manual
must include the maximum weight for
each altitude and temperature condition
at which the rotorcraft can safely hover
out-of-ground-effect in winds not less
than 17 knots from all azimuths. These
data must be clearly referenced to the
appropriate hover charts and specify
that they are not to be used for take-off
or landing determinations.
Issued in Kansas City, Missouri, on August
25, 2022.
Patrick R. Mullen,
Manager, Technical Innovation Policy
Branch, Policy and Innovation Division,
Aircraft Certification Service.
[FR Doc. 2022–18722 Filed 8–29–22; 8:45 am]
BILLING CODE 4910–13–P
ENVIRONMENTAL PROTECTION
AGENCY
40 CFR Part 52
[EPA–HQ–OAR–2022–0320; FRL–9731–01–
OAR]
Finding of Failure To Submit Regional
Haze State Implementation Plans for
the Second Planning Period
Environmental Protection
Agency (EPA).
ACTION: Final action.
AGENCY:
The Environmental Protection
Agency (EPA) is taking final action
SUMMARY:
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finding that 15 states have failed to
submit State Implementation Plans
(SIPs) to satisfy the visibility protection
requirements of the Clean Air Act
(CAA), as described in implementing
regulations, for the regional haze second
planning period. These findings of
failure to submit establish a 2-year
deadline for the EPA to promulgate
Federal Implementation Plans (FIPs) to
address these requirements for a given
state unless, prior to the EPA
promulgating a FIP, the state submits,
and the EPA approves, a SIP that meets
these requirements.
DATES: Effective date of this action is
September 29, 2022.
FOR FURTHER INFORMATION CONTACT:
General questions concerning this
document should be addressed to Mr.
Joseph Stein, Office of Air Quality
Planning and Standards, Air Quality
Policy Division, Mail Code C539–04,
109 TW Alexander Drive, Research
Triangle Park, NC 27711; telephone
number: (919) 541–0195; email address:
stein.joseph@epa.gov.
SUPPLEMENTARY INFORMATION:
I. General Information
A. Notice and Comment Under the
Administrative Procedures Act (APA)
Section 553 of the APA, 5 U.S.C.
553(b)(3)(B), provides that, when an
agency for good cause finds that notice
and public procedure are impracticable,
unnecessary, or contrary to the public
interest, the agency may issue a rule
without providing notice and an
opportunity for public comment. The
EPA has determined that there is good
cause for making this final agency
action without prior proposal and
opportunity for comment because no
significant EPA judgment is involved in
making a finding of failure to submit
SIPs, or elements of SIPs, required by
the CAA, where states have made no
submissions or incomplete submissions,
to meet the requirement. Thus, notice
and public procedure are unnecessary.
The EPA finds that this constitutes good
cause under 5 U.S.C. 553(b)(3)(B).
B. How can I get copies of this document
and other related information?
The EPA has established a docket for
this action under Docket ID No. EPA–
HQ–OAR–2022–0320. All documents in
the docket are listed and publicly
available at https://www.regulations.gov.
Publicly available docket materials are
also available in hard copy at the Air
and Radiation Docket and Information
Center, EPA/DC, William Jefferson
Clinton West Building, Room 3334,
1301 Constitution Avenue NW,
Washington, DC. Out of an abundance
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]]>Agencies
[Federal Register Volume 87, Number 167 (Tuesday, August 30, 2022)]
[Rules and Regulations]
[Pages 52854-52856]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2022-18722]
=======================================================================
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 29
[Docket No. FAA-2022-0183; Special Conditions No. 29-056-SC]
Special Conditions: The Boeing Company, Leonardo S.p.a. Model
AW139 Helicopter; Use of New Hovering Out of Ground Effect Utility
Power on the Model AW139 Helicopter
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final special conditions.
-----------------------------------------------------------------------
SUMMARY: These special conditions are issued for the Leonardo S.p.a.
(Leonardo) Model AW139 helicopter. This helicopter as modified by The
Boeing Company (Boeing) will have a novel or unusual design feature
when compared to the state of technology envisioned in the
airworthiness standards for helicopters. This design feature
incorporates a 2.5-minute all engines operating (AEO) power restricted
for use at helicopter operating speeds below 60 knots indicated
airspeed (KIAS), and hovering out of ground effect (HOGE). This power
is referred to as 2.5-minute HOGE utility power (HUP), or 2.5-minute
HUP. The 2.5-minute HUP is greater than the transmission power
limitations associated with takeoff and AEO. 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 September 29, 2022.
FOR FURTHER INFORMATION CONTACT: Dorina Mihail, Propulsion and Energy
Section, AIR-624, Technical Innovation Policy Branch, Policy and
Innovation Division, Aircraft Certification Service, Federal Aviation
Administration, 1200 District Avenue, Burlington, MA 01803; telephone
781-238-7153; fax 781-238-7199; email [email protected].
SUPPLEMENTARY INFORMATION:
Background
On September 18, 2020, Boeing applied for a supplemental type
certificate for performance envelope expansion of the Leonardo Model
AW139 helicopter. The AW139 helicopter as changed, is a medium twin-
engine 14 CFR part 29 transport category B helicopter with a 15,521
pounds (7040 Kg) maximum takeoff weight and a maximum seating capacity
of nine passengers and two crew. This helicopter takeoff and landing
altitude is 10,000 feet density altitude (Hd), and the forward flight
altitude is 11,000 feet Hd. This helicopter has the capability for
Category II instrument landing system (ILS) approaches. The Model AW139
helicopter as changed will be equipped with two PT6C-67C1 engines. The
Model AW139 helicopter as changed will have a 2.5-minute HUP for use in
HOGE that exceeds the transmission power limitations associated with
takeoff and AEO.
Type Certification Basis
Under the provisions of 14 CFR 21.101, Boeing must show that the
Leonardo Model AW139 helicopter, as changed, continues to meet the
applicable provisions of the regulations listed in Type Certificate No.
R00002RD, or the applicable regulations in effect on the date of
application for the change, except for earlier amendments as agreed
upon by the FAA. The proposed certification basis for this supplemental
type certificate is as follows:
14 CFR 21.29 and Part 29, Amendment 29-1 through Amendment 29-45
with 14 CFR 29.25, 29.143, 29.173, 29.175, 29.177 at Amendment 29-51,
and 14 CFR 29.773 at Amendment 29-57.
Equivalent Level of Safety Findings issued against:
14 CFR 29.1305, as documented in the AB139 FAA Memo, dated December
20, 2004.
If the Administrator finds that the applicable airworthiness
regulations (e.g., 14 CFR part 29) do not contain adequate or
appropriate safety standards for the Leonardo Model AW139 helicopter
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 Leonardo Model AW139 helicopter must comply with the
noise certification requirements of 14 CFR part 36.
[[Page 52855]]
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 Feature
The Leonardo Model AW139 helicopter will incorporate a novel or
unusual design feature, which is a 2.5-minute AEO power that is greater
than the transmission takeoff power limitations associated with takeoff
and AEO. This power is restricted for use when HOGE and at helicopter
operating speeds below 60 KIAS. The applicable airworthiness
regulations do not contain adequate or appropriate safety standards for
this design feature.
Discussion
The design feature will incorporate a 2.5-minute HUP that allows
the pilot to enter HOGE, operate in HOGE, and depart from HOGE at high
altitudes and ambient atmospheric temperatures. The use of the 2.5-
minute HUP is limited to periods of no longer than 2.5 minutes each
use, under AEO conditions, at helicopter operating speeds below 60 KIAS
and HOGE. Use of the 2.5-minute HUP is not part of, or combined with a
takeoff operation.
Helicopter operation at the 2.5-minute HUP will use the engine
power higher than the rated maximum continuous power and limits but
lower than the rated takeoff power and limits and does not exceed the 5
minute takeoff rating for which the engines are type certificated.
Existing part 33 regulations for the engines are adequate for the
helicopter 2.5-minute HUP.
Use of the 2.5-minute HUP exceeds the helicopter transmission power
limitations associated with takeoff and AEO. Existing part 29
regulations do not recognize helicopter operation that exceeds the
transmission power limitations associated with takeoff and AEO. The
special conditions that address the use of the 2.5-minute HUP on this
model of helicopter, as modified by Boeing, are as follows.
The Rotorcraft Flight Manual must specify that the use of the 2.5-
minute HUP is limited to periods no longer than 2.5 minutes each, under
AEO conditions, at helicopter operating speeds below 60 KIAS and HOGE.
Additionally, the Rotorcraft Flight Manual must specify that use of the
2.5-minute HUP is not part of, or combined with, a takeoff operation.
The requirement added to Sec. 29.49(c) provides for the
development of helicopter performance data for 2.5-minute HUP
utilization.
The testing requirement added to Sec. 29.923(d) consists of two
applications of 2.5-minute HUP torque and the maximum speed per 10-hour
cycle. The 10-hour cycle represents a run of 10 hours in length that is
repeated 20 times, for a total of (at least) 200 hours of endurance
testing as required by Sec. 29.923(a). Therefore, the testing added to
Sec. 29.923(d) provides for 40 applications of the 2.5-minute HUP
during the 200-hour endurance test specified in Sec. 29.923(a). This
testing is added to Sec. 29.923(d) ``Endurance tests; 90 percent of
maximum continuous run,'' since the 2.5-minute HUP is not part of, or
combined with, a takeoff operation, as stated in these special
conditions and is expected to be used during mid-mission.
The flight-test requirement added to Sec. 29.1049 is intended to
address the hovering cooling provisions at the 2.5-minute HUP and HOGE
following thermal stabilization at maximum weight, mission
representative power, maximum altitude, and ambient temperatures
specified in Sec. 29.1043(b). The flight-test continues with cycling
in and out of the HUP mode, in a manner representative of the intended
use of the 2.5-minute HUP, per the instructions specified in the
Rotorcraft Flight Manual. The repeated successive HUP applications and
time duration between HUP cycles result in the most critical condition
for the cooling provisions required by Sec. 29.1041(a) and Sec.
29.1041(b). The flight-test continues with departing the hover and
transitioning to a maximum continuous power climb at the best rate of
climb speed. Climb is continued for 5 minutes after the highest
temperatures are observed or until the service ceiling is reached.
The requirements added to Sec. 29.1305 are means for the pilot to
identify when the 2.5-minute HUP level is achieved, when the event
begins, and when the time interval expires. These means will assist the
pilot in managing the 2.5-minute HUP short time duration in a pilot
high-workload environment.
The requirements added to Sec. 29.1521 are similar to the
powerplant limitations for takeoff operations in Sec. 29.1521(b),
modified to reflect the 2.5-minute HUP.
The requirement added to Sec. 29.1587(b)(8) will require
publishing the performance data developed under paragraph (b) of these
special conditions in the Rotorcraft Flight Manual. These data must be
clearly referenced to the appropriate hover charts and specify that
they are not to be used for take-off or landing determinations.
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. 29-22-01-
SC for the Leonardo Model AW139 helicopter, which was published in the
Federal Register on May 3, 2022 (87 FR 26143). The FAA did not receive
any comments.
Applicability
As discussed above, these special conditions are applicable to the
Leonardo Model AW139 helicopter. Should Boeing apply at a later date
for a supplemental type certificate to modify any other model included
on Type Certificate No. R00002RD, to incorporate 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 the Leonardo Model AW139 helicopter. It is not a rule of general
applicability and affects only the applicant who applied to the FAA for
approval of this feature on the helicopter.
List of Subjects in 14 CFR Part 29
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 the Leonardo S.p.a. Model AW139
helicopter, as modified by The Boeing Company.
(a) The Rotorcraft Flight Manual must state the following:
(1) Use of the 2.5-minute Hovering Out of Ground Effect (HOGE)
Utility Power (2.5-minute HUP) is limited to a period no longer than
2.5 minutes each, under all engine operating (AEO) conditions, at
helicopter operating speeds below 60 knots indicated airspeed (KIAS)
and HOGE.
(2) Use of the 2.5-minute HUP is not part of, or combined with, a
takeoff operation.
(b) In addition to the requirements of Sec. 29.49(c), the out-of-
ground effect hover performance must be determined over
[[Page 52856]]
the ranges of weight, altitude, and temperatures for which
certification is requested with the 2.5-minute HUP.
(c) In addition to the requirements of Sec. 29.923(d) when
performing the endurance test, the 2.5 minute all engines operating
must be performed using two applications of 2.5-minute HUP torque and
the maximum speed for use with 2.5-minute HUP torque, per 10-hour
cycle.
(d) In addition to the requirements of Sec. 29.1049, the hovering
cooling provisions at the 2.5-minute HUP must be shown as follows--
(1) Conduct a thermal stabilization at maximum weight, mission
representative power, maximum altitude, and ambient temperatures
specified in Sec. 29.1043(b); following stabilization, increase power
to the 2.5-minute HUP and HOGE for a duration of 2.5 minutes (150
seconds).
(2) Cycle in and out the HUP mode in a manner representative of the
intended use of the 2.5-minute HUP, and per the instructions specified
in the Rotorcraft Flight Manual, if any. The HUP cycles should account
for repeated successive HUP applications and time duration between HUP
cycles resulting in the most critical condition for the cooling
provisions required by Sec. 29.1041(a) and Sec. 29.1041(b).
(3) Following the tests in paragraphs (d)(1) and (d)(2) of these
special conditions, depart the hover and transition to a maximum
continuous power climb at the best rate of climb speed. Continue the
climb until 5 minutes after the highest temperatures are observed or
until the service ceiling is reached.
(e) In addition to the requirements of Sec. 29.1305, the pilot
must have the means to identify the 2.5-minute HUP time limit
associated with its use as follows--
(1) When the power level is achieved,
(2) when the event begins, and
(3) when the time interval expires.
These indications must be clear and unambiguous to the pilot and
must not cause pilot confusion. The use of these indications must be
evaluated in operationally relevant scenarios in accordance with Sec.
29.1523 for crew workload.
(f) In addition to the requirements of Sec. 29.1521, the use of
the 2.5-minute HUP must be limited by the following:
(1) The maximum rotational speed, which may not be greater than--
(i) The maximum value determined by the rotor design; or
(ii) The maximum value demonstrated during the type tests;
(2) The maximum allowable turbine inlet or turbine outlet gas
temperature (for turbine engines);
(3) The maximum allowable power or torque for each engine,
considering the power input limitations of the transmission with all
engines operating;
(4) The maximum allowable power or torque for each engine
considering the power input limitations of the transmission with one
engine inoperative;
(5) The time limit for the use of the power corresponding to the
limitations established in paragraphs (f)(1) through (f)(4) of these
special conditions; and
(6) The maximum allowable engine and transmission oil temperatures,
if the time limit established in paragraph (f)(5) of these special
conditions exceeds 2 minutes.
(7) Use of 2.5-minute HUP is limited to HOGE only.
(g) In addition to the requirements of Sec. 29.1587(b)(8), the
Rotorcraft Flight Manual must contain the out-of-ground effect hover
performance determined under paragraph (b) of these special conditions,
and the maximum safe wind demonstrated under the ambient conditions for
the data presented. In addition, the Rotorcraft Flight Manual must
include the maximum weight for each altitude and temperature condition
at which the rotorcraft can safely hover out-of-ground-effect in winds
not less than 17 knots from all azimuths. These data must be clearly
referenced to the appropriate hover charts and specify that they are
not to be used for take-off or landing determinations.
Issued in Kansas City, Missouri, on August 25, 2022.
Patrick R. Mullen,
Manager, Technical Innovation Policy Branch, Policy and Innovation
Division, Aircraft Certification Service.
[FR Doc. 2022-18722 Filed 8-29-22; 8:45 am]
BILLING CODE 4910-13-P
