Rule2022-18722
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
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Published
August 30, 2022
Effective
September 29, 2022
Issuing agencies
Transportation DepartmentFederal Aviation Administration
Abstract
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.
Full Text
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<title>Federal Register, Volume 87 Issue 167 (Tuesday, August 30, 2022)</title>
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[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 [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[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.
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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 <a href="/cdn-cgi/l/email-protection#20644f52494e410e6d494841494c604641410e474f56"><span class="__cf_email__" data-cfemail="cf8ba0bda6a1aee182a6a7aea6a38fa9aeaee1a8a0b9">[email protected]</span></a>.
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
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