Special Conditions: Safran Helicopter Engines, S.A., Arrano 1A Turboshaft Engine Model; 30-Minute All Engines Operating Power Rating, 52041-52043 [2020-18614]

Download as PDF Federal Register / Vol. 85, No. 164 / Monday, August 24, 2020 / Rules and Regulations c. In paragraphs (b) and (e), remove the word ‘‘such’’ each time it appears and add the word ‘‘the’’ in its place. ■ Richard Fordyce, Administrator, Farm Service Agency. Robert Stephenson, Executive Vice President, Commodity Credit Corporation. [FR Doc. 2020–18148 Filed 8–19–20; 4:15 pm] BILLING CODE 3410–05–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 33 [Docket No FAA–2020–0816; Special Conditions No. 33–20–01–SC] Special Conditions: Safran Helicopter Engines, S.A., Arrano 1A Turboshaft Engine Model; 30-Minute All Engines Operating Power Rating Federal Aviation Administration (FAA), DOT. ACTION: Final special conditions; request for comments. AGENCY: These special conditions are issued for the Safran Helicopter Engines, S.A. (Safran Helicopter Engines), Arrano 1A turboshaft engine model. This engine model will have a novel or unusual design feature when compared to the state of technology envisioned in the airworthiness standards for aircraft engines. This design feature is a 30-minute All Engines Operating (AEO) power rating. 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: This action is effective on Safran Helicopter Engines on August 24, 2020. Send comments on or before October 8, 2020. ADDRESSES: Send comments identified by docket number FAA–2020–0816 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. • 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. jbell on DSKJLSW7X2PROD with RULES SUMMARY: VerDate Sep<11>2014 15:48 Aug 21, 2020 Jkt 250001 • 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://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 the 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: Tara Fitzgerald, FAA, AIR–6A2, Engine and Propeller Standards Branch, Aircraft Certification Service, 1200 District Avenue, Burlington, Massachusetts, 01803–5213; telephone (781) 238–7130; facsimile (781) 238–7199; email tara.fitzgerald@faa.gov. SUPPLEMENTARY INFORMATION: The FAA has determined, in accordance with 5 U.S. Code 553(b)(3)(B) and 553(d)(3), that notice and opportunity for prior public comment are unnecessary because substantially identical special conditions have been previously subject to the public comment process in several prior instances such that the FAA is satisfied that new comments are unlikely. For the same reason, the FAA finds that good cause exists for adopting these special conditions upon issuance. The FAA is requesting comments to allow interested persons to submit views that may not have been submitted in response to the prior opportunities for comment. Company and model No. 33–021–SC 1 Frm 00017 No. 33–010–SC 2 No. 33–009–SC 3 1 82 2 76 3 76 Company and model Pratt and Whitney Canada, Inc. PT6C–67E Turboshaft Engine. Pratt and Whitney Canada Corp. PW210S Turboshaft Engine. FR 60854, December 26, 2017. FR 56097, September 12, 2011. FR 40594, July 11, 2011. Comments Invited The FAA invites 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. The FAA will consider all comments received by the closing date for comments. The FAA may change these special conditions based on the comments received. Background On August 30, 2019, Safran Helicopter Engines applied for a type certificate for the Arrano 1A turboshaft engine model. The Arrano 1A turboshaft engine model has an annular inlet integrating inlet guide vanes, a twostage centrifugal compressor driven by a single-stage high pressure turbine, a reverse flow combustion chamber and a single-stage low pressure turbine (power turbine) driving a reduction gearbox located at the front of the engine and an exhaust pipe. The Arrano 1A turboshaft engine model will incorporate a novel or unusual design feature, which is a 30minute AEO power rating. Regulations pertaining to a 30-minute AEO power rating have not been incorporated into part 33. These special conditions provide the requirements for the 30minute AEO power rating for the Arrano 1A turboshaft engine model. Safran Helicopter Engines has requested this 30-minute AEO power rating to support helicopter search and rescue missions that require hover operations at high power. The use of the 30-minute AEO power rating will require special conditions to address the use of this 30minute AEO power rating and its effects on the Arrano 1A engine model. Type Certification Basis Special conditions number PO 00000 Special conditions number 52041 Light Helicopter Turbine Engine Company CTS800–4AT Turboshaft Engine. Fmt 4700 Sfmt 4700 Under the provisions of title 14, Code of Federal Regulations (14 CFR) 21.17, Safran Helicopter Engines must show that the Arrano 1A turboshaft engine model meets the applicable provisions of 14 CFR part 33, dated February 1, E:\FR\FM\24AUR1.SGM 24AUR1 52042 Federal Register / Vol. 85, No. 164 / Monday, August 24, 2020 / Rules and Regulations 1965, as amended by amendments 33– 1 through 33–34. If the Administrator finds that the applicable airworthiness regulations (e.g., 14 CFR part 33) do not contain adequate or appropriate safety standards for the Safran Helicopter Engines, Arrano 1A turboshaft engine model because of a novel or unusual design feature, special conditions are prescribed under the provisions of § 21.16. Special conditions are initially applicable to the model for which they are issued. Should the type certificate for that model be amended later to include any other model that incorporates the same novel or unusual design feature, these special conditions would also apply to the other model under § 21.101. 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 § 21.17(a)(2). jbell on DSKJLSW7X2PROD with RULES Novel or Unusual Design Features The Arrano 1A turboshaft engine model will incorporate a novel or unusual design feature, which is a 30minute AEO power rating. This rating will be used to support helicopter search and rescue missions that require hover operations at high power. Discussion The type certification basis for the Arrano 1A turboshaft engine model does not contain adequate airworthiness standards for a 30-minute AEO power rating. Therefore, special conditions are necessary to provide additional safety standards for rating definition, instructions for continued airworthiness (ICA), and endurance testing. The 30-minute AEO power rating is generally intended to be used for hovering at increased power for search and rescue missions at power levels higher than the maximum continuous rating, up to rated takeoff power. These special conditions address the effects on the engine during the use of the 30minute AEO power for up to 30 minutes. The 30-minute AEO power rating time limitation applies to each instance the 30-minute AEO power rating is used. There is no limit to the number of times the 30-minute AEO power rating can be used during any one flight and there is no cumulative time limitation. In accordance with § 33.4, the applicant must prepare ICAs. Those ICAs must include instructions to address the unknown usage of the 30minute AEO power rating and its effect on engine deterioration for the Arrano VerDate Sep<11>2014 15:48 Aug 21, 2020 Jkt 250001 1A turboshaft engine model. Safran Helicopter Engines must assess the usage and publish ICAs with airworthiness limitations section limits in accordance with the usage to prevent excessive engine deterioration. Because the Arrano 1A turboshaft engine model has a continuous one engine inoperative (OEI) rating and associated limitations equal to or higher than the 30-minute AEO rating, the test time performed at the continuous OEI rating may be credited toward the 25 hours of operation endurance test requirement set forth in these SCs. However, test times spent at other rating elements of the § 33.87 endurance test, such as takeoff or other OEI ratings (that may be equal to or higher), may not be counted toward the required 25 hours endurance test set forth in these SCs. Therefore, special conditions are issued under the provisions of 14 CFR 11.19, 21.16, and 21.17. Safran Helicopter Engines must demonstrate compliance to the safety standards specified in the special conditions. 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. Applicability As discussed above, these special conditions are applicable to the Safran Helicopter Engines, Arrano 1A turboshaft engine model. Should Safran Helicopter Engines apply at a later date for a change to the type certificate to include another model incorporating the same novel or unusual design feature, these special conditions would apply to that model as well. Conclusion This action affects only certain novel or unusual design features on the Arrano 1A turboshaft engine model. It is not a rule of general applicability. List of Subjects in 14 CFR Part 33 Aircraft, Engines, Aviation Safety, Reporting and recordkeeping requirements. Authority Citation The authority citation for these special conditions is as follows: Authority: 49 U.S.C. 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 Safran PO 00000 Frm 00018 Fmt 4700 Sfmt 4700 Helicopter Engines, Arrano 1A turboshaft engine model. In addition to the general definitions in § 1.1, the following definition applies to these special conditions: ‘‘Rated 30minute All Engines Operating (AEO) power’’ means the approved brake horsepower developed under static conditions at the specified altitude and temperature, and within the operating limitations under part 33, and limited in use to periods not exceeding 30 minutes. In addition to the airworthiness standards in 14 CFR part 33, the following special conditions apply: (a) Section 33.1, Applicability, and Section 33.3, General. As applicable, all documentation, testing and analysis required to comply with the part 33 type certification basis must account for the 30-minute AEO rating, limits, and usage. (b) Section 33.4, Instructions for Continued Airworthiness. In addition to the requirements of § 33.4, the instructions for continued airworthiness must: (1) Include instructions to ensure that in-service engine deterioration due to the rated 30-minute AEO power usage will not exceed that assumed for establishing the engine maintenance program and all other approved ratings, including one engine inoperative (OEI), are available (within associated limits and assumed usage) for every flight. (2) Validate the adequacy of the maintenance actions required under paragraph (b)(1) of these special conditions. (3) Include in the airworthiness limitations section any mandatory inspections and serviceability limits related to the use of the 30-minute AEO power rating. (c) Section 33.7, Engine ratings and operating limitations. In addition to the ratings and operating limitations required to be established by § 33.7(a) and (c), a rated 30-minute AEO power and operating limitations must be established relating to the following: (1) Horsepower, torque, shaft speed (r.p.m.) and gas temperature. (2) The rated 30-minute AEO power and associated limitations must not exceed the rated takeoff power and associated limitations. (d) Section 33.29, Instrument connection. If dependence is placed on instrumentation needed to monitor the rating’s use, the applicant must make provision for the installation of that instrumentation, specify the provisions for instrumentation in the engine installation instructions, and declare them mandatory in the engine approval documentation. E:\FR\FM\24AUR1.SGM 24AUR1 Federal Register / Vol. 85, No. 164 / Monday, August 24, 2020 / Rules and Regulations (referred to after this as ‘‘the MCAI’’), to correct an unsafe condition for Pacific Aerospace Limited Model 750XL airplanes with wing lightning protection panels installed. To accompany the MCAI, the CAA issued Notification of Airworthiness Directive issued for New Zealand Aeronautical Products IAW ICAO Annex 8, dated December 15, 2017, which states: [Docket No. FAA–2020–0769; Product Identifier 2018–CE–033–AD; Amendment 39–21213; AD 2020–17–08] The FAA must receive comments on this AD by October 8, 2020. ADDRESSES: You may send comments 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: U.S. Department of Transportation, Docket Operations, M– 30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE, Washington, DC 20590, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. For service information identified in this AD, contact Pacific Aerospace Limited, Airport Road, Hamilton, Private Bag 3027, Hamilton 3240, New Zealand; phone: +64 7843 6144; fax: +64 843 6134; email: pacific@ aerospace.co.nz; internet: www.aerospace.co.nz. You may view this referenced service information at the FAA, Airworthiness Products Section, Operational Safety Branch, 901 Locust, Kansas City, Missouri 64106. For information on the availability of this material at the FAA, call (816) 329– 4148. It is also available on the internet at https://www.regulations.gov by searching for locating Docket No. FAA– 2020–0769. RIN 2120–AA64 Examining the AD Docket Related Service Information Under 1 CFR Part 51 The FAA reviewed Pacific Aerospace Service Bulletin PACSB/XL/092, Issue 2, dated December 15, 2017. The service information contains procedures for inspecting the electrical bonding (verification testing) on the wing lightning protection panels and repairing the electrical bonding if insufficient bonding is found during the inspection. This service information is reasonably available because the interested parties have access to it through their normal course of business or by the means identified in the ADDRESSES section. (e) Section 33.87, Endurance Test. In addition to the requirements of § 33.87(a) and (d), the overall test run must include a minimum of 25 hours of operation at rated 30-minute AEO power and limits, divided into periods of not less than 30 minutes, but not more than 60 minutes at rated 30minute AEO power, and alternate periods at maximum continuous power or less. (1) Each § 33.87(d) continuous OEI rating test period of 60 minutes duration, run at power and limits equal to or higher than the 30-minute AEO power rating, may be credited toward this requirement. Note that the test time required for the takeoff or other OEI ratings may not be counted toward the 25 hours of testing required at the 30minute AEO power rating. Issued in Burlington, Massachusetts, on August 20, 2020. Robert J. Ganley, Manager, Engine and Propeller Standards Branch, Aircraft Certification Service. [FR Doc. 2020–18614 Filed 8–20–20; 11:15 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 Airworthiness Directives; Pacific Aerospace Limited Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Final rule; request for comments AGENCY: The FAA is adopting a new airworthiness directive (AD) for Pacific Aerospace Limited Model 750XL airplanes with wing lightning protection panels installed. This AD results from mandatory continuing airworthiness information (MCAI) issued by the aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as insufficient electrical bonding of the wing lightning protection panels. The FAA is issuing this AD to address the unsafe condition on these products. DATES: This AD is effective September 14, 2020. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in the AD as of September 14, 2020. SUMMARY: jbell on DSKJLSW7X2PROD with RULES 52043 VerDate Sep<11>2014 15:48 Aug 21, 2020 Jkt 250001 You may examine the AD docket on the internet at https:// www.regulations.gov by searching for and locating Docket No. FAA–2020– 0769; or in person at Docket Operations between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this AD, the regulatory evaluation, any comments received, and other information. The street address for Docket Operations is in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt. FOR FURTHER INFORMATION CONTACT: Mike Kiesov, Aerospace Engineer, FAA, General Aviation & Rotorcraft Section, International Validation Branch, 901 Locust, Room 301, Kansas City, Missouri 64106; telephone: (816) 329– 4144; fax: (816) 329–4090; email: mike.kiesov@faa.gov. SUPPLEMENTARY INFORMATION: Discussion The Civil Aviation Authority of New Zealand (CAA) has issued AD DCA/ 750XL/21, dated December 15, 2017 PO 00000 Frm 00019 Fmt 4700 Sfmt 4700 This [CAA] AD with effective date 22 December 2017 mandates an electrical bonding inspection of the wing lightning protection panels per the requirements in Pacific Aerospace Mandatory Service Bulletin (MSB) PACSB/XL/092 issue 2, dated 15 December 2017, or later approved revision. The [CAA] AD is prompted by the possibility that there may be insufficient electrical bonding between the lightning protection panels and the airframe. Due to a report of an airplane with wing lightning strike panels that were not bonded to the airframe and without information confirming whether the bonding was performed properly during the assembly process, a check of all airplanes in operation is necessary. In addition to the inspection of the electrical bonding on the wing lightning protection panels, the MCAI also requires repair of any insufficient electrical bonding found during the inspection. You may examine the MCAI on the internet at https:// www.regulations.gov by searching for and locating Docket No. FAA–2020– 0769. Differences Between This AD and the MCAI The MCAI requires compliance before further flight for aircraft operating under instrument flight rules (IFR) and before February 15, 2018, for aircraft operating under visual flight rules. The FAA’s engineering assessment determined an emergency AD was not warranted. Therefore, this AD requires compliance within 30 days for aircraft approved to E:\FR\FM\24AUR1.SGM 24AUR1

Agencies

[Federal Register Volume 85, Number 164 (Monday, August 24, 2020)]
[Rules and Regulations]
[Pages 52041-52043]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2020-18614]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 33

[Docket No FAA-2020-0816; Special Conditions No. 33-20-01-SC]


Special Conditions: Safran Helicopter Engines, S.A., Arrano 1A 
Turboshaft Engine Model; 30-Minute All Engines Operating Power Rating

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final special conditions; request for comments.

-----------------------------------------------------------------------

SUMMARY: These special conditions are issued for the Safran Helicopter 
Engines, S.A. (Safran Helicopter Engines), Arrano 1A turboshaft engine 
model. This engine model will have a novel or unusual design feature 
when compared to the state of technology envisioned in the 
airworthiness standards for aircraft engines. This design feature is a 
30-minute All Engines Operating (AEO) power rating. 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: This action is effective on Safran Helicopter Engines on August 
24, 2020. Send comments on or before October 8, 2020.

ADDRESSES: Send comments identified by docket number FAA-2020-0816 
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.
     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://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 the 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: Tara Fitzgerald, FAA, AIR-6A2, Engine 
and Propeller Standards Branch, Aircraft Certification Service, 1200 
District Avenue, Burlington, Massachusetts, 01803-5213; telephone (781) 
238-7130; facsimile (781) 238-7199; email [email protected].

SUPPLEMENTARY INFORMATION: The FAA has determined, in accordance with 5 
U.S. Code 553(b)(3)(B) and 553(d)(3), that notice and opportunity for 
prior public comment are unnecessary because substantially identical 
special conditions have been previously subject to the public comment 
process in several prior instances such that the FAA is satisfied that 
new comments are unlikely. For the same reason, the FAA finds that good 
cause exists for adopting these special conditions upon issuance. The 
FAA is requesting comments to allow interested persons to submit views 
that may not have been submitted in response to the prior opportunities 
for comment.

------------------------------------------------------------------------
      Special  conditions  number               Company and model
------------------------------------------------------------------------
No. 33-021-SC \1\.....................  Light Helicopter Turbine Engine
                                         Company CTS800-4AT Turboshaft
                                         Engine.
No. 33-010-SC \2\.....................  Pratt and Whitney Canada, Inc.
                                         PT6C-67E Turboshaft Engine.
No. 33-009-SC \3\.....................  Pratt and Whitney Canada Corp.
                                         PW210S Turboshaft Engine.
------------------------------------------------------------------------
\1\ 82 FR 60854, December 26, 2017.
\2\ 76 FR 56097, September 12, 2011.
\3\ 76 FR 40594, July 11, 2011.

Comments Invited

    The FAA invites 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.
    The FAA will consider all comments received by the closing date for 
comments. The FAA may change these special conditions based on the 
comments received.

Background

    On August 30, 2019, Safran Helicopter Engines applied for a type 
certificate for the Arrano 1A turboshaft engine model. The Arrano 1A 
turboshaft engine model has an annular inlet integrating inlet guide 
vanes, a two-stage centrifugal compressor driven by a single-stage high 
pressure turbine, a reverse flow combustion chamber and a single-stage 
low pressure turbine (power turbine) driving a reduction gearbox 
located at the front of the engine and an exhaust pipe. The Arrano 1A 
turboshaft engine model will incorporate a novel or unusual design 
feature, which is a 30-minute AEO power rating. Regulations pertaining 
to a 30-minute AEO power rating have not been incorporated into part 
33. These special conditions provide the requirements for the 30-minute 
AEO power rating for the Arrano 1A turboshaft engine model. Safran 
Helicopter Engines has requested this 30-minute AEO power rating to 
support helicopter search and rescue missions that require hover 
operations at high power. The use of the 30-minute AEO power rating 
will require special conditions to address the use of this 30-minute 
AEO power rating and its effects on the Arrano 1A engine model.

Type Certification Basis

    Under the provisions of title 14, Code of Federal Regulations (14 
CFR) 21.17, Safran Helicopter Engines must show that the Arrano 1A 
turboshaft engine model meets the applicable provisions of 14 CFR part 
33, dated February 1,

[[Page 52042]]

1965, as amended by amendments 33-1 through 33-34.
    If the Administrator finds that the applicable airworthiness 
regulations (e.g., 14 CFR part 33) do not contain adequate or 
appropriate safety standards for the Safran Helicopter Engines, Arrano 
1A turboshaft engine model because of a novel or unusual design 
feature, special conditions are prescribed under the provisions of 
Sec.  21.16.
    Special conditions are initially applicable to the model for which 
they are issued. Should the type certificate for that model be amended 
later to include any other model that incorporates the same novel or 
unusual design feature, 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.  21.17(a)(2).

Novel or Unusual Design Features

    The Arrano 1A turboshaft engine model will incorporate a novel or 
unusual design feature, which is a 30-minute AEO power rating. This 
rating will be used to support helicopter search and rescue missions 
that require hover operations at high power.

Discussion

    The type certification basis for the Arrano 1A turboshaft engine 
model does not contain adequate airworthiness standards for a 30-minute 
AEO power rating. Therefore, special conditions are necessary to 
provide additional safety standards for rating definition, instructions 
for continued airworthiness (ICA), and endurance testing.
    The 30-minute AEO power rating is generally intended to be used for 
hovering at increased power for search and rescue missions at power 
levels higher than the maximum continuous rating, up to rated takeoff 
power. These special conditions address the effects on the engine 
during the use of the 30-minute AEO power for up to 30 minutes. The 30-
minute AEO power rating time limitation applies to each instance the 
30-minute AEO power rating is used. There is no limit to the number of 
times the 30-minute AEO power rating can be used during any one flight 
and there is no cumulative time limitation.
    In accordance with Sec.  33.4, the applicant must prepare ICAs. 
Those ICAs must include instructions to address the unknown usage of 
the 30-minute AEO power rating and its effect on engine deterioration 
for the Arrano 1A turboshaft engine model. Safran Helicopter Engines 
must assess the usage and publish ICAs with airworthiness limitations 
section limits in accordance with the usage to prevent excessive engine 
deterioration. Because the Arrano 1A turboshaft engine model has a 
continuous one engine inoperative (OEI) rating and associated 
limitations equal to or higher than the 30-minute AEO rating, the test 
time performed at the continuous OEI rating may be credited toward the 
25 hours of operation endurance test requirement set forth in these 
SCs. However, test times spent at other rating elements of the Sec.  
33.87 endurance test, such as takeoff or other OEI ratings (that may be 
equal to or higher), may not be counted toward the required 25 hours 
endurance test set forth in these SCs. Therefore, special conditions 
are issued under the provisions of 14 CFR 11.19, 21.16, and 21.17. 
Safran Helicopter Engines must demonstrate compliance to the safety 
standards specified in the special conditions.
    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.

Applicability

    As discussed above, these special conditions are applicable to the 
Safran Helicopter Engines, Arrano 1A turboshaft engine model. Should 
Safran Helicopter Engines apply at a later date for a change to the 
type certificate to include another model incorporating the same novel 
or unusual design feature, these special conditions would apply to that 
model as well.

Conclusion

    This action affects only certain novel or unusual design features 
on the Arrano 1A turboshaft engine model. It is not a rule of general 
applicability.

List of Subjects in 14 CFR Part 33

    Aircraft, Engines, Aviation Safety, Reporting and recordkeeping 
requirements.

Authority Citation

    The authority citation for these special conditions is as follows:

    Authority:  49 U.S.C. 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 Safran Helicopter Engines, Arrano 
1A turboshaft engine model.
    In addition to the general definitions in Sec.  1.1, the following 
definition applies to these special conditions: ``Rated 30-minute All 
Engines Operating (AEO) power'' means the approved brake horsepower 
developed under static conditions at the specified altitude and 
temperature, and within the operating limitations under part 33, and 
limited in use to periods not exceeding 30 minutes.
    In addition to the airworthiness standards in 14 CFR part 33, the 
following special conditions apply:
    (a) Section 33.1, Applicability, and Section 33.3, General. As 
applicable, all documentation, testing and analysis required to comply 
with the part 33 type certification basis must account for the 30-
minute AEO rating, limits, and usage.
    (b) Section 33.4, Instructions for Continued Airworthiness. In 
addition to the requirements of Sec.  33.4, the instructions for 
continued airworthiness must:
    (1) Include instructions to ensure that in-service engine 
deterioration due to the rated 30-minute AEO power usage will not 
exceed that assumed for establishing the engine maintenance program and 
all other approved ratings, including one engine inoperative (OEI), are 
available (within associated limits and assumed usage) for every 
flight.
    (2) Validate the adequacy of the maintenance actions required under 
paragraph (b)(1) of these special conditions.
    (3) Include in the airworthiness limitations section any mandatory 
inspections and serviceability limits related to the use of the 30-
minute AEO power rating.
    (c) Section 33.7, Engine ratings and operating limitations. In 
addition to the ratings and operating limitations required to be 
established by Sec.  33.7(a) and (c), a rated 30-minute AEO power and 
operating limitations must be established relating to the following:
    (1) Horsepower, torque, shaft speed (r.p.m.) and gas temperature.
    (2) The rated 30-minute AEO power and associated limitations must 
not exceed the rated takeoff power and associated limitations.
    (d) Section 33.29, Instrument connection. If dependence is placed 
on instrumentation needed to monitor the rating's use, the applicant 
must make provision for the installation of that instrumentation, 
specify the provisions for instrumentation in the engine installation 
instructions, and declare them mandatory in the engine approval 
documentation.

[[Page 52043]]

    (e) Section 33.87, Endurance Test. In addition to the requirements 
of Sec.  33.87(a) and (d), the overall test run must include a minimum 
of 25 hours of operation at rated 30-minute AEO power and limits, 
divided into periods of not less than 30 minutes, but not more than 60 
minutes at rated 30-minute AEO power, and alternate periods at maximum 
continuous power or less.
    (1) Each Sec.  33.87(d) continuous OEI rating test period of 60 
minutes duration, run at power and limits equal to or higher than the 
30-minute AEO power rating, may be credited toward this requirement. 
Note that the test time required for the takeoff or other OEI ratings 
may not be counted toward the 25 hours of testing required at the 30-
minute AEO power rating.

    Issued in Burlington, Massachusetts, on August 20, 2020.
Robert J. Ganley,
Manager, Engine and Propeller Standards Branch, Aircraft Certification 
Service.
[FR Doc. 2020-18614 Filed 8-20-20; 11:15 am]
BILLING CODE 4910-13-P
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