[Federal Register Volume 86, Number 50 (Wednesday, March 17, 2021)]
[Rules and Regulations]
[Pages 14526-14528]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2021-05263]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 27
[Docket No. FAA-2020-1011; Notice No. 27-051-SC]
Special Conditions: AgustaWestland Philadelphia Corporation,
Leonardo S.p.A. Model A119 and AW119 MKII Helicopters; Pressure
Refueling and Fueling Provisions
AGENCY: Federal Aviation Administration (FAA), DOT.
[[Page 14527]]
ACTION: Final special conditions.
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SUMMARY: These special conditions are issued for the Leonardo S.p.A.
(Leonardo) Model A119 and AW119 MKII helicopters. These helicopters as
modified by AgustaWestland Philadelphia Corporation (AWPC) 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 is the optional closed circuit refueling receiver
(CCRR). 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 April 16, 2021.
FOR FURTHER INFORMATION CONTACT: Rao Edupuganti, Dynamic Systems
Section, AIR-627, Policy and Innovation Division, Aircraft
Certification Service, 10101 Hillwood Parkway, Fort Worth, Texas 76177;
telephone (817) 222-4389.
SUPPLEMENTARY INFORMATION:
Background
On January 30, 2020, AWPC applied for a supplemental type
certificate to install an optional CCRR in the Leonardo Model A119 and
AW119 MKII helicopters. The general configuration and the principles of
construction of these helicopters will not be changed by the
modifications. These helicopters are 14 CFR part 27 normal category
helicopters powered by turboshaft engines, with a 7-passenger maximum
capacity and minimum crew of one pilot and a maximum weight of 5,997 lb
(2,720 kg) and 6,283 lb (2,850 kg), respectively. The total useable
fuel capacity of the Leonardo Model A119 and AW119 MKII helicopters is
157.0 U.S. gallons distributed within the fuel tanks. Both helicopter
models are powered by one Pratt & Whitney Canada Inc. PT6B-37A
turboshaft engine.
Part 27 does not contain requirements for pressure refueling for
normal category helicopters. Title 14 CFR 29.979, amendment 29-12,
provides these requirements for transport category helicopters.
Accordingly, these special conditions are based on Sec. 29.979 to
provide requirements for the inclusion of the optional CCRR on the
Leonardo Model A119 and AW119 MKII helicopters.
Type Certification Basis
Under the provisions of 14 CFR 21.101, AWPC must show that the
Leonardo Model A119 and AW119 MKII helicopters, as changed, continue to
meet the applicable provisions of the regulations listed in Type
Certificate No. H7EU or the applicable regulations in effect on the
date of application for the change. The regulations adopted by
reference in the type certificate are commonly referred to as the
``original type certification basis.'' The certification basis also
includes certain special conditions, exemptions, or later amended
sections of the applicable part that are not relevant to these special
conditions.
The Administrator has determined that the applicable airworthiness
regulations do not contain adequate or appropriate safety standards for
the Leonardo Model A119 and AW119 MKII helicopters because of a novel
or unusual design feature. Therefore, 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.
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 A119 and AW119 MKII helicopters will incorporate
the following novel or unusual design feature: An optional CCRR system
that allows for pressure refueling.
Discussion
AWPC proposed to install an optional CCRR system that includes
provisions for pressure refueling during ground operations with the
engine running and the rotors turning. The design proposed by AWPC
allows for both closed-circuit pressure and normal gravity refueling
and fueling. In this design, the ground crew will be able to perform
closed-circuit pressure refueling by pulling the receiver into place
using the provided lanyard tool after the fuel filler cap is opened.
When gravity fueling is desired, a latch is depressed using the same
lanyard tool. Depressing the latch causes the receiver to swing open to
accommodate any nozzle up to three inches in diameter. The CCRR system
is currently certified on the Leonardo Model AW139 transport category
helicopter. Relative to the Model AW139 installation, the Model A119
and AW119 MKII installations will be clocked 25 degrees counter-
clockwise, and the receptacle flange will be offset approximately two
inches outboard of the fuselage profile due to packaging constraints.
The mechanical components and functional aspects of the Model A119 and
AW119 MKII CCRR installations are unchanged from the previously
certified AW139 installation.
The part 27 airworthiness regulations in the type certification
basis do not contain appropriate safety standards for this design
feature. However, part 29 regulations contain appropriate airworthiness
standards; therefore, these special conditions are necessary. They are
derived from 14 CFR 29.979, ``Pressure refueling and fueling provisions
below fuel level.''
Section 29.979, amendment 29-12, effective February 1, 1977,
includes standards for pressure refueling and fueling provisions below
fuel level on transport category helicopters. This regulation is
intended to prevent hazards to ground crew, flight crew, and occupants
by reducing the probability of exposure to hazardous quantities of fuel
due to spillage. This regulation also ensures the pressure refueling/
defueling system is designed to prevent overfilling the fuel tank and
to withstand an ultimate load overpressure event without failure.
Section 29.979(a) requires that each fueling connection below the
fuel level in each tank have means to prevent the escape of hazardous
quantities of fuel from that tank in case of malfunction of the fuel
entry valve. The only refueling connection on the Leonardo Model A119
and AW119 MKII helicopters is located above the fuel level of the
single main upper, two main lower, and optional two auxiliary fuel
tanks. As the proposed modification by AWPC does not move the existing
refueling connection below the fuel line of any fuel tank, these
special conditions do not include a requirement derived from 14 CFR
29.979(a).
Section 29.979(b) requires that systems intended for pressure
refueling and fueling have a means in addition to the normal means for
limiting the tank content to prevent damage to the tank in case of
failure of the normal means.
Section 29.979(c) requires that the helicopter pressure fueling
system (not fuel tanks and fuel tank vents) withstand an ultimate load
that is 2.0 times the load arising from the maximum pressure, including
surge, likely to occur during fueling. The maximum surge pressure must
be established with any combination of
[[Page 14528]]
tank valves being either intentionally or inadvertently closed.
Section 29.979(d) requires that the helicopter defueling system
(not including fuel tanks and fuel tank vents) withstand an ultimate
load that is 2.0 times the load arising from the maximum permissible
defueling pressure (positive or negative) at the helicopter's fueling
connection. As the design proposed by AWPC does not include a defueling
capability, these special conditions do not include a requirement
derived from 14 CFR 29.979(d).
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. 27-051-SC
for the Leonardo Model A119 and AW119 MKII helicopters, which was
published in the Federal Register on November 2, 2020 (85 FR 69265). No
comments were received, and the special conditions are adopted as
proposed.
Applicability
As discussed above, these special conditions are applicable to
Leonardo Model A119 and AW119 MKII helicopters. Should AWPC apply at a
later date for a supplemental type certificate to modify any other
model included on Type Certificate No. H7EU to incorporate 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 the
Leonardo Model A119 and AW119 MKII helicopters. It is not a rule of
general applicability and affects only the applicant who applied to the
FAA for approval of this feature on these helicopters.
List of Subjects in 14 CFR Part 27
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
0
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 Leonardo S.p.A. Model A119 and AW119
MKII helicopters, as modified by AgustaWestland Philadelphia
Corporation.
The pressure refueling system must be designed and installed as
follows:
(a) For systems intended for pressure refueling, a means in
addition to the normal means for limiting the tank content must be
installed to prevent damage to the fuel tank in case of failure of the
normal means.
(b) The helicopter pressure fueling system (not fuel tanks and fuel
tank vents) must withstand an ultimate load that is 2.0 times the load
arising from maximum pressure, including surge, that is likely to occur
during fueling. The maximum surge pressure must be established with any
combination of tank valves being either intentionally or inadvertently
closed.
Issued in Fort Worth, Texas, on December 11, 2020.
Jorge Castillo,
Manager, Rotorcraft Standards Branch, AIR-680, Policy & Innovation
Division, Aircraft Certification Service.
[FR Doc. 2021-05263 Filed 3-16-21; 8:45 am]
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