82_FR_53620 82 FR 53400 - Special Conditions: General Electric Company, GE9X Engine Models; Endurance Test Special Conditions

82 FR 53400 - Special Conditions: General Electric Company, GE9X Engine Models; Endurance Test Special Conditions

DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration

Federal Register Volume 82, Issue 220 (November 16, 2017)

Page Range53400-53403
FR Document2017-24812

These special conditions are issued for the General Electric Company turbofan engine models GE9X-105B1A, -105B1A1, -105B1A2, - 105B1A3, -102B1A, -102B1A1, -102B1A2, -102B1A3, and -93B1A. In these special conditions, the engine models will be referred to as ``GE9X.'' The engines will have novel or unusual design features associated with the engine design. The applicable airworthiness regulations do not contain adequate or appropriate safety standards for these design features. 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.

Federal Register, Volume 82 Issue 220 (Thursday, November 16, 2017) 
[Federal Register Volume 82, Number 220 (Thursday, November 16, 2017)]
[Rules and Regulations]
[Pages 53400-53403]
From the Federal Register Online  [www.thefederalregister.org]
[FR Doc No: 2017-24812]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 33

[Docket No. FAA-2017-0537; Notice No. 33-17-02-SC]


Special Conditions: General Electric Company, GE9X Engine Models; 
Endurance Test Special Conditions

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final special conditions.

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SUMMARY: These special conditions are issued for the General Electric 
Company turbofan engine models GE9X-105B1A, -105B1A1, -105B1A2, -
105B1A3, -102B1A, -102B1A1, -102B1A2, -102B1A3, and -93B1A. In these 
special conditions, the engine models will be referred to as ``GE9X.'' 
The engines will have novel or unusual design features associated with 
the engine design. The applicable airworthiness regulations do not 
contain adequate or appropriate safety standards for these design 
features. 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 December 18, 2017.

FOR FURTHER INFORMATION CONTACT: Diane Cook, AIR-6A1, Engine and 
Propeller Standards Branch, Aircraft Certification Service, 1200 
District Avenue, Burlington, Massachusetts 01803-5213; telephone (781) 
238-7111; facsimile (781) 238-7199; email [email protected].

SUPPLEMENTARY INFORMATION:

Background

    On January 29, 2016, General Electric Company (GE) applied for a 
type certificate for their new GE9X turbofan engine models. The GE9X 
engine models are high-bypass-ratio engines that incorporate novel or 
unusual design features. The GE9X engine models incorporate new 
technologies such that the company cannot run the endurance test 
conditions prescribed in Sec.  33.87 without significant modifications 
making the test vehicle non-representative of the type design.

Discussion

    An alternative endurance test cycle has been developed that 
provides a level of safety equivalent with that intended by Sec.  
33.87. The alternate endurance test provides the test conditions that 
allow the engine to be run in type design configuration and demonstrate 
engine operability and durability as well as systems functionality to a 
level intended by the current Sec.  33.87 rule.
    These special conditions provide the necessary conditions for 
verification of engine-level and component-level effects as intended by 
the current Sec.  33.87 Endurance test. The test is run in engine type 
design configuration, with only limited test enabling modifications as 
needed. The special conditions include a demonstration for the oil, 
fuel, air bleed, and accessory drive systems as required in the current 
Sec.  33.87 Endurance test.
    The equivalent level of severity intended by the Sec.  33.87 
Endurance test is provided by an engine test demonstration at the gas 
path limiting temperature and at shaft speed redlines and at the most 
extreme shaft speeds as determined through a critical point analysis 
(CPA). In addition, times on condition and cycle counts were developed 
to allow additional challenges to the novel or unusual

[[Page 53401]]

design features that would not have been as challenged by the current 
Sec.  33.87 test schedule.
    The level of durability is equivalent with that intended by the 
rule, which considers the damage accumulated during the test for the 
limiting damage mechanisms for components and engine systems, up to and 
including the applicable limitations declared in the Type Certificate 
Data Sheets (TCDS). The alternate test schedule provides conditions in 
the engine for a sufficient amount of time to demonstrate that no 
potential safety issue will develop from the limiting damage mechanisms 
while operating in service.
    The special conditions for Sec. Sec.  33.4 and 33.29 are added to 
support an equivalent compliance by means of mandatory inspections 
prescribed in paragraph (b)(3) of the Sec.  33.87 special conditions. 
These special condition requirements maintain a level of safety 
equivalent to the level intended by the applicable airworthiness 
standards in effect on the date of application.

Type Certification Basis

    Under the provisions of Title 14, Code of Federal Regulations (14 
CFR) 21.17, GE must show that the GE9X engine models meet the 
applicable provisions of part 33, as amended by Amendments 33-1 through 
33-34. The FAA has determined that the applicable airworthiness 
regulations in part 33 do not contain adequate or appropriate safety 
standards for the GE9X engine models because of their novel or unusual 
engine design features. Therefore, these special conditions are 
prescribed under the provisions of 14 CFR 11.19 and 21.16, and will 
become part of the type certification basis for GE9X engine models in 
accordance with Sec.  21.17(a)(2).

Novel or Unusual Design Features

    The GE9X engine models will incorporate the following novel or 
unusual design features: Technological advances that reduce noise and 
emissions while improving fuel efficiency and increasing thrust, when 
compared to previous similarly certificated GE engine models. The 
technological advances are incorporated into hardware design, 
materials, and engine operating characteristics. Introduction of 
complex cooling systems and film-cooled components cause metal 
temperatures to be significantly influenced by cooling air temperatures 
and air flows and are no longer in direct proportion to the gas path 
temperature which is a target of the current endurance test. 
Introduction of new materials, new design features, and operating 
conditions also introduced new failure modes that are not targeted by 
the current endurance test cycle. Some of the technological 
advancements were introduced in prior GE engine models and mitigated by 
modifications to the test engine.
    For past certifications, GE has shown that the engine design, as 
modified, still represented the durability and operating 
characteristics of the intended type design but the modifications 
needed to the GE9X engine model to run the Sec.  33.87 Endurance test 
cannot be reconciled and would affect the test outcome.

Discussion of Comments

    Notice of proposed special conditions No. 33-17-02-SC for the GE9X 
engine models was published in the Federal Register on 82 FR 28790. We 
received one comment from an anonymous commenter that acknowledged the 
need for special conditions as it concerns the GE9X engines models. We 
understand and acknowledge the comment we received, which is supportive 
of a special condition for the GE9X engine model. No further response 
is required.

Applicability

    As discussed above, the special conditions are applicable to the 
GE9X engine model(s). Should GE apply at a later date for a change to 
the type certificate to include another model on the same type 
certificate incorporating the same novel or unusual design feature, the 
special conditions would apply to that model as well.

Conclusion

    This action affects only certain novel or unusual design features 
on the GE9X turbofan engine models. It is not a rule of general 
applicability and applies only to GE, who requested FAA approval of 
this engine feature.

List of Subjects in 14 CFR Part 33

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

    The authority citation for these special conditions is as follows:

    Authority:  49 U.S.C. 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 the GE9X engine models: GE9X-105B1A, -
105B1A1, -105B1A2, -105B1A3, -102B1A, -102B1A1, 102B1A2, -102B1A3, and 
-93B1A.

PART 33--REQUIREMENTS


Sec.  33.4  Instructions for Continued Airworthiness

    The Airworthiness Limitations section must prescribe the mandatory 
post-flight inspections and maintenance actions associated with any 
exceedance required by the endurance test, paragraph (b)(3), of these 
special conditions.


Sec.  33.29  Instrument Connection

    The engine must have means, or provisions for means, to 
automatically record and alert maintenance personnel of each occurrence 
of any exceedance required by the endurance test paragraph (b)(3), of 
these special conditions.


Sec.  33.87  Endurance Test

    (a) General: The applicant must show that the endurance test 
schedule in combination with any prescribed mandatory actions provide 
an equivalent level of severity and demonstration of durability and 
operability as that intended by Sec.  33.87(a) and (b). When showing 
that the level of durability is equivalent with that intended by the 
rule, the applicant must consider the damage accumulated during the 
test for the limiting damage mechanisms for components and engine 
systems, up to and including the applicable limitations declared in the 
type certificate data sheets (TCDS). The test cycle content must create 
conditions in the engine for a sufficient amount of time to demonstrate 
no potential safety issue will develop from the limiting damage 
mechanisms while operating in service. The following minimum 
requirements apply:
    (1) Conduct the tests in paragraphs (b), (c), and (d) of these 
special conditions, for total cumulative and dwell time duration 
between ground idle and the takeoff thrust prescribed in these special 
conditions. The test cycle durations must include all maximums allowed 
in the TCDS and expected service operation.
    (2) Requirements of Sec.  33.87(a)(1), (2), (4), and (6).
    (3) Requirements of Sec.  33.87(a)(3) applicable to the temperature 
of external surfaces of the engine.
    (4) Testing for maximum air bleed must be at least equal with the 
prescribed test required in Sec.  33.87(a)(5). However, for these 
cycles, the thrust or the rotor shaft rotational speed may be less than 
100 percent of the value associated with the particular operation being 
tested if the FAA finds that the validity of the endurance test is not 
compromised.

[[Page 53402]]

    (5) Testing for engine fuel, oil, and hydraulic fluid pressure and 
oil temperature must be at least equal with the prescribed test 
required in Sec.  33.87(a)(7).
    (6) If the number of occurrences of either transient rotor shaft 
overspeed or transient gas over temperature is not limited, at least 
155 accelerations must be made at the limiting overspeed or over 
temperature. If the number of occurrences is limited, that number of 
accelerations must be made at the limiting overspeed or over 
temperature.
    (7) One hundred starts must be made, of which:
    (i) Twenty-five starts must be preceded by at least a two-hour 
engine shutdown.
    (ii) Ten false engine starts must be accomplished, pausing for the 
applicant's specified minimum fuel drainage time, before attempting a 
normal start.
    (iii) Ten normal restarts must be accomplished with not longer than 
15 minutes since engine shutdown.
    The remaining starts may be made after completing the endurance 
testing prescribed by these special conditions.
    (8) Unless otherwise specified (i.e. (d)(2) of these special 
conditions), for accelerations from ground idle to takeoff, the 
throttle must be moved in not more than one second, except that, if 
different regimes of control operations are incorporated necessitating 
scheduling of the thrust-control lever motion in going from one extreme 
position to the other, a longer period of time is acceptable, but not 
more than two seconds.
    (i) When operating with max oil temperatures the throttle movement 
may be `stair-stepped' to allow for oil temperature stabilization for 
durations greater than two seconds.
    (9) The applicant must validate any analytical methods used for 
compliance with these special conditions. Validation includes the 
ability to accurately predict an outcome applicable to the engine being 
tested.
    (10) The applicant must perform the endurance test on an engine 
that substantially conforms to its type design. Modifications may be 
made as needed to achieve test conditions and/or engine operating 
conditions representative of the type design.
    (b) Conduct the endurance test at or above the declared shaft 
speeds and gas temperatures limits, and at or above conditions 
representative of critical points (speeds, temperatures, rated thrust) 
in the operating envelope.
    (1) Conduct the endurance test at or above the rated takeoff thrust 
and rated maximum continuous thrust and with the associated limits for 
rotor speeds and gas temperature (redlines), as follows:
    (i) Either rotor speed or gas temperature, or concurrent rotor 
speed and gas temperature, if analysis indicates a combination of 
redline operational conditions is possible to occur in service, must be 
at least 100 percent of the values associated with the engine rating 
being tested.
    (ii) The cumulative test time duration and number of cycles must be 
representative of the rotor speed and gas temperature excursions to 
redlines that can be expected to occur in between overhauls.
    (iii) The time durations for each takeoff or maximum continuous 
segment must include all maximums allowed in the TCDS and expected 
service operation and must include the following cycles:
    (A) At least one (1) takeoff cycle of 5-minutes time duration at 
the low pressure rotor speed limit and gas temperature limit 
(redlines).
    (B) At least one (1) takeoff cycle of 5-minutes time duration at 
the high pressure rotor speed limit and gas temperature limit 
(redlines).
    (C) In lieu of the separate cycles specified in paragraphs (A) and 
(B) of this section, the applicant may run the low pressure and high 
pressure rotor speeds and gas temperature limits (redlines) in the same 
cycle. However, in this case, the applicant must run at least 2 cycles 
of 5 minutes' time duration each.
    (2) Conduct the endurance test at or above the rated takeoff thrust 
and the rated maximum continuous thrust with rotor speeds at or above 
those determined by a critical point analysis (CPA) and with gas 
temperature redline conditions as follows:
    (i) The applicant must determine through a CPA the highest rotor 
shaft rotational speeds (CPA speeds) expected to occur for each rotor 
shaft system within the declared operating envelope. The CPA must be 
conducted for the takeoff and maximum continuous rated thrust and must 
consider the declared operating envelope, engine deterioration, engine-
to-engine variability, and any other applicable variables that can 
cause the engine to operate at the extremes of its performance ratings.
    (ii) Except as provided in paragraph (b)(3)(ii) of these special 
conditions, conduct a cyclic test between ground idle and combined 
takeoff and maximum continuous thrust ratings, as follows:
    (A) Eighteen hours and forty-five minutes (18.75 hours) cumulated 
time duration at or above the rated takeoff thrust, the gas temperature 
limit for takeoff (redline), and the CPA rotor speeds for takeoff 
determined per paragraph (b)(2)(i) of these special conditions.
    (B) Forty-five (45) hours cumulated time duration at or above the 
rated maximum continuous thrust, the gas temperature limit for maximum 
continuous (redline), and the CPA rotor speeds for maximum continuous 
determined per paragraph (b)(2)(i) of these special conditions.
    (C) The time durations for each takeoff or maximum continuous 
segments must include all maximums allowed in the TCDS and expected 
service operation, and must include at least one maximum continuous 
cycle of 30 minutes run continuously.
    (3) If the cyclic shaft speed excursions specified in paragraphs 
(b)(1) or (b)(2) of these special conditions cannot be demonstrated in 
the test, then an alternative equivalent with the rule intent must be 
provided. Alternatives may include alternate means of test 
demonstration, mandatory actions, or other means found acceptable to 
the FAA. The applicant must prescribe a mandatory action plan for 
engine operation between the shaft speeds demonstrated for a minimum of 
cumulated 18.75 hours at or above rated takeoff and 45 hours at or 
above rated maximum continuous, respectively, and the declared speed 
limits (redlines), as follows:
    (i) Prescribe post-event actions or operating limitations 
acceptable to the FAA for operation below the declared speed limits 
(redlines) and above the CPA speeds.
    (ii) If the test required by (b)(2)(ii) of these special conditions 
can only be accomplished at a rotor shaft speed lower than the CPA 
speed, prescribe post-event actions or operating limitations acceptable 
to the FAA for operation below that CPA speed and above the value 
demonstrated during the test.
    (c) Conduct the endurance test at the incremental cruise thrust 
that must be at least equal with the prescribed test required in Sec.  
33.87(b)(4). The 25 incremental test cycles must be uniformly 
distributed throughout the entire endurance test.
    (d) Conduct at least 300 cycles between ground idle and combined 
rated takeoff and rated maximum continuous thrust, as follows:
    (1) Each cycle to include acceleration to or above rated takeoff 
thrust, deceleration from takeoff to ground idle, followed by 5 to 15 
seconds at ground idle, acceleration to or above rated

[[Page 53403]]

maximum continuous thrust, and deceleration to ground idle.
    (2) The throttle movement from ground idle to rated takeoff or 
maximum continuous thrust and from rated takeoff thrust to ground idle 
should be not more than one (1) second, except that, if different 
regimes of control operations are incorporated necessitating scheduling 
of the thrust-control lever motion in going from one extreme position 
to the other, a longer period of time is acceptable, but not more than 
two (2) seconds. The throttle movement from rated maximum continuous 
thrust to ground idle should not be more than five (5) seconds.
    (3) The time durations for each cycle associated with either 
takeoff or maximum continuous thrust segments must include all maximums 
allowed in the TCDS and expected service operation, and must include 
the following cycles:
    (i) Three (3) cycles of 5 minutes each and one (1) cycle of 10 
minutes at the takeoff thrust.
    (ii) Three (3) cycles of 30 minutes each at the maximum continuous 
thrust.

    Issued in Burlington, Massachusetts, on November 8, 2017.
Robert J. Ganley,
Manager, Engine and Propeller Standards Branch, Aircraft Certification 
Service.
[FR Doc. 2017-24812 Filed 11-15-17; 8:45 am]
 BILLING CODE 4910-13-P

53400 Federal Register / Vol. 82, No. 220 / Thursday, November 16, 2017 / Rules and Regulations TABLE I—Continued Minimum Variety Regulation period Minimum grade diameter (inches) (1) (2) (3) (4) * * * * * * * (b) * * * TABLE II Minimum Variety Regulation period Minimum grade diameter (inches) (1) (2) (3) (4) Oranges Early and midseason ............................... 01/29/90–08/19/90 .................................. U.S. No. 1 Golden ................................... 24⁄16 On and after 08/20/90 ............................. U.S. No. 1 ............................................... 24⁄16 Navel ................................................. On and after 11/24/89 ............................. U.S. No. 1 Golden ................................... 24⁄16 Temple .............................................. On and after 11/24/89 ............................. U.S. No. 1 ............................................... 24⁄16 Valencia and other late type ............. March 23, 1992–9/27/92 ......................... U.S. No. 1 ............................................... 24⁄16 On and after 9/28/92 ............................... U.S. No. 1 ............................................... 24⁄16 * * * * * * * * * * * * –102B1A, –102B1A1, –102B1A2, without significant modifications –102B1A3, and –93B1A. In these special making the test vehicle non- [Subpart Redesignated as Subpart E conditions, the engine models will be representative of the type design. and Amended] referred to as ‘‘GE9X.’’ The engines will Discussion ■ 7. Redesignate ‘‘Subpart—Interpretive have novel or unusual design features Rule’’ as subpart E and revise the associated with the engine design. The An alternative endurance test cycle heading to read as follows: applicable airworthiness regulations do has been developed that provides a level not contain adequate or appropriate of safety equivalent with that intended Subpart E—Interpretations safety standards for these design by § 33.87. The alternate endurance test features. These special conditions provides the test conditions that allow Dated: November 9, 2017. contain the additional safety standards the engine to be run in type design Bruce Summers, that the Administrator considers configuration and demonstrate engine Acting Administrator, Agricultural Marketing necessary to establish a level of safety operability and durability as well as Service. equivalent to that established by the systems functionality to a level intended [FR Doc. 2017–24701 Filed 11–15–17; 8:45 am] existing airworthiness standards. by the current § 33.87 rule. These special conditions provide the BILLING CODE 3410–02–P DATES: Effective December 18, 2017. necessary conditions for verification of FOR FURTHER INFORMATION CONTACT: engine-level and component-level Diane Cook, AIR–6A1, Engine and effects as intended by the current DEPARTMENT OF TRANSPORTATION Propeller Standards Branch, Aircraft § 33.87 Endurance test. The test is run Certification Service, 1200 District in engine type design configuration, Federal Aviation Administration Avenue, Burlington, Massachusetts with only limited test enabling 01803–5213; telephone (781) 238–7111; modifications as needed. The special 14 CFR Part 33 facsimile (781) 238–7199; email conditions include a demonstration for [Docket No. FAA–2017–0537; Notice No. 33– diane.cook@faa.gov. the oil, fuel, air bleed, and accessory 17–02–SC] SUPPLEMENTARY INFORMATION: drive systems as required in the current Special Conditions: General Electric § 33.87 Endurance test. Background The equivalent level of severity Company, GE9X Engine Models; On January 29, 2016, General Electric intended by the § 33.87 Endurance test Endurance Test Special Conditions Company (GE) applied for a type is provided by an engine test AGENCY: Federal Aviation certificate for their new GE9X turbofan demonstration at the gas path limiting nshattuck on DSK9F9SC42PROD with RULES Administration (FAA), DOT. engine models. The GE9X engine temperature and at shaft speed redlines ACTION: Final special conditions. models are high-bypass-ratio engines and at the most extreme shaft speeds as that incorporate novel or unusual design determined through a critical point SUMMARY: These special conditions are features. The GE9X engine models analysis (CPA). In addition, times on issued for the General Electric Company incorporate new technologies such that condition and cycle counts were turbofan engine models GE9X–105B1A, the company cannot run the endurance developed to allow additional –105B1A1, –105B1A2, –105B1A3, test conditions prescribed in § 33.87 challenges to the novel or unusual VerDate Sep<11>2014 14:33 Nov 15, 2017 Jkt 244001 PO 00000 Frm 00004 Fmt 4700 Sfmt 4700 E:\FR\FM\16NOR1.SGM 16NOR1

Federal Register / Vol. 82, No. 220 / Thursday, November 16, 2017 / Rules and Regulations 53401 design features that would not have operating conditions also introduced PART 33—REQUIREMENTS been as challenged by the current new failure modes that are not targeted § 33.87 test schedule. by the current endurance test cycle. § 33.4 Instructions for Continued The level of durability is equivalent Some of the technological Airworthiness with that intended by the rule, which advancements were introduced in prior The Airworthiness Limitations considers the damage accumulated GE engine models and mitigated by section must prescribe the mandatory during the test for the limiting damage modifications to the test engine. post-flight inspections and maintenance mechanisms for components and engine For past certifications, GE has shown actions associated with any exceedance systems, up to and including the that the engine design, as modified, still required by the endurance test, applicable limitations declared in the represented the durability and operating paragraph (b)(3), of these special Type Certificate Data Sheets (TCDS). characteristics of the intended type conditions. The alternate test schedule provides design but the modifications needed to § 33.29 Instrument Connection conditions in the engine for a sufficient the GE9X engine model to run the amount of time to demonstrate that no The engine must have means, or § 33.87 Endurance test cannot be potential safety issue will develop from provisions for means, to automatically reconciled and would affect the test the limiting damage mechanisms while record and alert maintenance personnel outcome. operating in service. of each occurrence of any exceedance The special conditions for §§ 33.4 and Discussion of Comments required by the endurance test 33.29 are added to support an Notice of proposed special conditions paragraph (b)(3), of these special equivalent compliance by means of No. 33–17–02–SC for the GE9X engine conditions. mandatory inspections prescribed in models was published in the Federal § 33.87 Endurance Test paragraph (b)(3) of the § 33.87 special Register on 82 FR 28790. We received conditions. These special condition (a) General: The applicant must show one comment from an anonymous that the endurance test schedule in requirements maintain a level of safety commenter that acknowledged the need equivalent to the level intended by the combination with any prescribed for special conditions as it concerns the mandatory actions provide an applicable airworthiness standards in GE9X engines models. We understand effect on the date of application. equivalent level of severity and and acknowledge the comment we demonstration of durability and Type Certification Basis received, which is supportive of a operability as that intended by special condition for the GE9X engine § 33.87(a) and (b). When showing that Under the provisions of Title 14, Code model. No further response is required. the level of durability is equivalent with of Federal Regulations (14 CFR) 21.17, GE must show that the GE9X engine Applicability that intended by the rule, the applicant models meet the applicable provisions must consider the damage accumulated As discussed above, the special of part 33, as amended by Amendments during the test for the limiting damage conditions are applicable to the GE9X 33–1 through 33–34. The FAA has mechanisms for components and engine engine model(s). Should GE apply at a determined that the applicable systems, up to and including the later date for a change to the type airworthiness regulations in part 33 do applicable limitations declared in the certificate to include another model on not contain adequate or appropriate type certificate data sheets (TCDS). The the same type certificate incorporating safety standards for the GE9X engine test cycle content must create the same novel or unusual design models because of their novel or conditions in the engine for a sufficient feature, the special conditions would unusual engine design features. amount of time to demonstrate no apply to that model as well. Therefore, these special conditions are potential safety issue will develop from prescribed under the provisions of 14 Conclusion the limiting damage mechanisms while CFR 11.19 and 21.16, and will become This action affects only certain novel operating in service. The following part of the type certification basis for or unusual design features on the GE9X minimum requirements apply: GE9X engine models in accordance with turbofan engine models. It is not a rule (1) Conduct the tests in paragraphs § 21.17(a)(2). of general applicability and applies only (b), (c), and (d) of these special to GE, who requested FAA approval of conditions, for total cumulative and Novel or Unusual Design Features dwell time duration between ground this engine feature. The GE9X engine models will idle and the takeoff thrust prescribed in incorporate the following novel or List of Subjects in 14 CFR Part 33 these special conditions. The test cycle unusual design features: Technological Aircraft, Engines, Aviation safety, durations must include all maximums advances that reduce noise and Reporting and recordkeeping allowed in the TCDS and expected emissions while improving fuel requirements. service operation. efficiency and increasing thrust, when (2) Requirements of § 33.87(a)(1), (2), compared to previous similarly The authority citation for these (4), and (6). certificated GE engine models. The special conditions is as follows: (3) Requirements of § 33.87(a)(3) technological advances are incorporated Authority: 49 U.S.C. 106(g), 40113, 44701, applicable to the temperature of external into hardware design, materials, and 44702, 44704. surfaces of the engine. engine operating characteristics. The Special Conditions (4) Testing for maximum air bleed Introduction of complex cooling must be at least equal with the systems and film-cooled components ■ Accordingly, pursuant to the authority prescribed test required in § 33.87(a)(5). nshattuck on DSK9F9SC42PROD with RULES cause metal temperatures to be delegated to me by the Administrator, However, for these cycles, the thrust or significantly influenced by cooling air the following special conditions are the rotor shaft rotational speed may be temperatures and air flows and are no issued as part of the type certification less than 100 percent of the value longer in direct proportion to the gas basis for the GE9X engine models: associated with the particular operation path temperature which is a target of the GE9X–105B1A, –105B1A1, –105B1A2, being tested if the FAA finds that the current endurance test. Introduction of –105B1A3, –102B1A, –102B1A1, validity of the endurance test is not new materials, new design features, and 102B1A2, –102B1A3, and –93B1A. compromised. VerDate Sep<11>2014 16:43 Nov 15, 2017 Jkt 244001 PO 00000 Frm 00005 Fmt 4700 Sfmt 4700 E:\FR\FM\16NOR1.SGM 16NOR1

53402 Federal Register / Vol. 82, No. 220 / Thursday, November 16, 2017 / Rules and Regulations (5) Testing for engine fuel, oil, and the associated limits for rotor speeds duration at or above the rated takeoff hydraulic fluid pressure and oil and gas temperature (redlines), as thrust, the gas temperature limit for temperature must be at least equal with follows: takeoff (redline), and the CPA rotor the prescribed test required in (i) Either rotor speed or gas speeds for takeoff determined per § 33.87(a)(7). temperature, or concurrent rotor speed paragraph (b)(2)(i) of these special (6) If the number of occurrences of and gas temperature, if analysis conditions. either transient rotor shaft overspeed or indicates a combination of redline (B) Forty-five (45) hours cumulated transient gas over temperature is not operational conditions is possible to time duration at or above the rated limited, at least 155 accelerations must occur in service, must be at least 100 maximum continuous thrust, the gas be made at the limiting overspeed or percent of the values associated with the temperature limit for maximum over temperature. If the number of engine rating being tested. continuous (redline), and the CPA rotor occurrences is limited, that number of (ii) The cumulative test time duration speeds for maximum continuous accelerations must be made at the and number of cycles must be determined per paragraph (b)(2)(i) of limiting overspeed or over temperature. representative of the rotor speed and gas these special conditions. (7) One hundred starts must be made, temperature excursions to redlines that (C) The time durations for each of which: can be expected to occur in between takeoff or maximum continuous (i) Twenty-five starts must be overhauls. segments must include all maximums preceded by at least a two-hour engine (iii) The time durations for each allowed in the TCDS and expected shutdown. takeoff or maximum continuous service operation, and must include at (ii) Ten false engine starts must be segment must include all maximums least one maximum continuous cycle of accomplished, pausing for the allowed in the TCDS and expected 30 minutes run continuously. applicant’s specified minimum fuel service operation and must include the (3) If the cyclic shaft speed excursions drainage time, before attempting a following cycles: specified in paragraphs (b)(1) or (b)(2) of normal start. (A) At least one (1) takeoff cycle of these special conditions cannot be (iii) Ten normal restarts must be 5-minutes time duration at the low demonstrated in the test, then an accomplished with not longer than 15 pressure rotor speed limit and gas alternative equivalent with the rule minutes since engine shutdown. temperature limit (redlines). intent must be provided. Alternatives The remaining starts may be made (B) At least one (1) takeoff cycle of may include alternate means of test after completing the endurance testing 5-minutes time duration at the high demonstration, mandatory actions, or prescribed by these special conditions. pressure rotor speed limit and gas other means found acceptable to the (8) Unless otherwise specified (i.e. temperature limit (redlines). FAA. The applicant must prescribe a (d)(2) of these special conditions), for (C) In lieu of the separate cycles mandatory action plan for engine accelerations from ground idle to specified in paragraphs (A) and (B) of operation between the shaft speeds takeoff, the throttle must be moved in this section, the applicant may run the demonstrated for a minimum of not more than one second, except that, low pressure and high pressure rotor cumulated 18.75 hours at or above rated if different regimes of control operations speeds and gas temperature limits takeoff and 45 hours at or above rated are incorporated necessitating (redlines) in the same cycle. However, maximum continuous, respectively, and scheduling of the thrust-control lever in this case, the applicant must run at the declared speed limits (redlines), as motion in going from one extreme least 2 cycles of 5 minutes’ time follows: position to the other, a longer period of duration each. (i) Prescribe post-event actions or time is acceptable, but not more than (2) Conduct the endurance test at or operating limitations acceptable to the two seconds. above the rated takeoff thrust and the FAA for operation below the declared (i) When operating with max oil rated maximum continuous thrust with speed limits (redlines) and above the temperatures the throttle movement rotor speeds at or above those CPA speeds. may be ‘stair-stepped’ to allow for oil determined by a critical point analysis (ii) If the test required by (b)(2)(ii) of temperature stabilization for durations (CPA) and with gas temperature redline these special conditions can only be greater than two seconds. conditions as follows: accomplished at a rotor shaft speed (9) The applicant must validate any (i) The applicant must determine lower than the CPA speed, prescribe analytical methods used for compliance through a CPA the highest rotor shaft post-event actions or operating with these special conditions. rotational speeds (CPA speeds) expected limitations acceptable to the FAA for Validation includes the ability to to occur for each rotor shaft system operation below that CPA speed and accurately predict an outcome within the declared operating envelope. above the value demonstrated during applicable to the engine being tested. The CPA must be conducted for the the test. (10) The applicant must perform the takeoff and maximum continuous rated (c) Conduct the endurance test at the endurance test on an engine that thrust and must consider the declared incremental cruise thrust that must be at substantially conforms to its type operating envelope, engine least equal with the prescribed test design. Modifications may be made as deterioration, engine-to-engine required in § 33.87(b)(4). The 25 needed to achieve test conditions and/ variability, and any other applicable incremental test cycles must be or engine operating conditions variables that can cause the engine to uniformly distributed throughout the representative of the type design. operate at the extremes of its entire endurance test. (b) Conduct the endurance test at or performance ratings. (d) Conduct at least 300 cycles above the declared shaft speeds and gas (ii) Except as provided in paragraph between ground idle and combined nshattuck on DSK9F9SC42PROD with RULES temperatures limits, and at or above (b)(3)(ii) of these special conditions, rated takeoff and rated maximum conditions representative of critical conduct a cyclic test between ground continuous thrust, as follows: points (speeds, temperatures, rated idle and combined takeoff and (1) Each cycle to include acceleration thrust) in the operating envelope. maximum continuous thrust ratings, as to or above rated takeoff thrust, (1) Conduct the endurance test at or follows: deceleration from takeoff to ground idle, above the rated takeoff thrust and rated (A) Eighteen hours and forty-five followed by 5 to 15 seconds at ground maximum continuous thrust and with minutes (18.75 hours) cumulated time idle, acceleration to or above rated VerDate Sep<11>2014 14:33 Nov 15, 2017 Jkt 244001 PO 00000 Frm 00006 Fmt 4700 Sfmt 4700 E:\FR\FM\16NOR1.SGM 16NOR1

Federal Register / Vol. 82, No. 220 / Thursday, November 16, 2017 / Rules and Regulations 53403 maximum continuous thrust, and Issued in Burlington, Massachusetts, on determinations in Order No. 831, which deceleration to ground idle. November 8, 2017. amended its regulations to address Robert J. Ganley, incremental energy offer caps in markets (2) The throttle movement from ground idle to rated takeoff or maximum Manager, Engine and Propeller Standards operated by regional transmission Branch, Aircraft Certification Service. organizations and independent system continuous thrust and from rated takeoff thrust to ground idle should be not more [FR Doc. 2017–24812 Filed 11–15–17; 8:45 am] operators. BILLING CODE 4910–13–P DATES: This rule is effective January 16, than one (1) second, except that, if different regimes of control operations 2018. are incorporated necessitating FOR FURTHER INFORMATION CONTACT: scheduling of the thrust-control lever DEPARTMENT OF ENERGY Emma Nicholson (Technical motion in going from one extreme Information), Office of Energy Policy Federal Energy Regulatory and Innovation, Federal Energy position to the other, a longer period of Commission Regulatory Commission, 888 First time is acceptable, but not more than two (2) seconds. The throttle movement Street NE., Washington, DC 20426, 18 CFR Part 35 (202) 502–8846, emma.nicholson@ from rated maximum continuous thrust to ground idle should not be more than [Docket No. RM16–5–001; Order No. 831– ferc.gov five (5) seconds. A] Pamela Quinlan (Technical Information), Office of Energy Market (3) The time durations for each cycle Offer Caps in Markets Operated by Regulation, Federal Energy Regulatory associated with either takeoff or Regional Transmission Organizations Commission, 888 First Street NE., maximum continuous thrust segments and Independent System Operators Washington, DC 20426, (202) 502– must include all maximums allowed in 6179, pamela.quinlan@ferc.gov the TCDS and expected service AGENCY: Federal Energy Regulatory Anne Marie Hirschberger (Legal operation, and must include the Commission, Department of Energy. Information), Office of the General following cycles: ACTION: Order on rehearing and Counsel, Federal Energy Regulatory (i) Three (3) cycles of 5 minutes each clarification. Commission, 888 First Street NE., and one (1) cycle of 10 minutes at the SUMMARY: The Federal Energy Washington, DC 20426, (202) 502– takeoff thrust. Regulatory Commission is granting in 8387, annemarie.hirschberger@ (ii) Three (3) cycles of 30 minutes part and denying in part requests for ferc.gov each at the maximum continuous thrust. rehearing and clarification of its SUPPLEMENTARY INFORMATION: TABLE OF CONTENTS Paragraph Nos. I. Introduction ............................................................................................................................................................................... 1 II. Discussion ................................................................................................................................................................................ 5 A. Offer Cap Structure .......................................................................................................................................................... 5 1. Hard Cap Level .......................................................................................................................................................... 6 2. Implementation of the Hard Cap .............................................................................................................................. 13 B. Verification Requirement ................................................................................................................................................. 18 1. Expected Costs ........................................................................................................................................................... 19 2. Verification of Imports .............................................................................................................................................. 30 C. Costs Included in Cost-Based Incremental Energy Offers .............................................................................................. 34 1. Requests for Rehearing/Clarification ........................................................................................................................ 34 2. Determination ............................................................................................................................................................. 37 III. Information Collection Statement .......................................................................................................................................... 41 IV. Regulatory Flexibility Act Certification ................................................................................................................................ 44 V. Document Availability ............................................................................................................................................................ 45 VI. Effective Date .......................................................................................................................................................................... 48 I. Introduction prices (LMPs). California Independent and independent system operator (RTO/ 1. On November 17, 2016, the Federal System Operator Corporation (CAISO), ISO): (1) Cap each resource’s Energy Regulatory Commission ISO New England Inc. (ISO–NE), incremental energy offer at the higher of (Commission) issued Order No. 831.1 Midcontinent Independent System $1,000/MWh or that resource’s verified Order No. 831 addresses the Operator, Inc. (MISO), New York cost-based incremental energy offer; and Independent System Operator, Inc. (2) cap verified cost-based incremental incremental energy offer component of (NYISO), and Southwest Power Pool, energy offers at $2,000/MWh when a resource’s supply offer, which is a Inc. (SPP) currently have a $1,000/MWh calculating LMPs (hard cap).3 Resources financial component consisting of costs cap on incremental energy offers (offer with verified cost-based incremental that vary with a resource’s output or cap), and PJM Interconnection, L.L.C. level of demand reduction. Incremental energy offers above $2,000/MWh will be (PJM) currently has an offer cap of nshattuck on DSK9F9SC42PROD with RULES energy offers are one of the components eligible to receive uplift.4 In response to $2,000/MWh on cost-based offers.2 used to calculate locational marginal 2. In Order No. 831, the Commission comments on the Notice of Proposed 1 Offer Caps in Markets Operated by Regional amended its regulations to require that Transmission Organizations and Independent each regional transmission organization System Operators, 81 FR 87,770 (Dec. 5, 2016), 3 Id. P 1. FERC Stats. & Regs. ¶ 31,387 (2016) (Order No. 2 Order No. 831, FERC Stats. & Regs. ¶ 31,387 at 831). PP 11–13. 4 Id. P 78. VerDate Sep<11>2014 14:33 Nov 15, 2017 Jkt 244001 PO 00000 Frm 00007 Fmt 4700 Sfmt 4700 E:\FR\FM\16NOR1.SGM 16NOR1


Document Created: 2017-11-16 03:53:35
Document Modified: 2017-11-16 03:53:35
CategoryRegulatory Information
CollectionFederal Register
sudoc ClassAE 2.7:
GS 4.107:
AE 2.106:
PublisherOffice of the Federal Register, National Archives and Records Administration
SectionRules and Regulations
ActionFinal special conditions.
DatesEffective December 18, 2017.
ContactDiane Cook, AIR-6A1, Engine and Propeller Standards Branch, Aircraft Certification Service, 1200 District Avenue, Burlington, Massachusetts 01803-5213; telephone (781) 238-7111; facsimile (781) 238-7199; email [email protected]
FR Citation82 FR 53400 
CFR AssociatedAircraft; Engines; Aviation Safety and Reporting and Recordkeeping Requirements
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