53400 Federal Register / Vol. 82, No. 220 / Thursday, November 16, 2017 / Rules and Regulations 

TABLE I—Continued 

Variety Regulation period Minimum grade 

Minimum 

diameter 

(inches) 

(1) (2) (3) (4) 

*******

(b) * * * 

TABLE II 

Variety Regulation period Minimum grade 

Minimum 

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

* * * * * * * 

* * * * * 

[Subpart Redesignated as Subpart E 

and Amended] 

■ 7. Redesignate ‘‘Subpart—Interpretive 

Rule’’ as subpart E and revise the 

heading to read as follows: 

Subpart E—Interpretations 

Dated: November 9, 2017. 

Bruce Summers, 

Acting Administrator, Agricultural Marketing 

Service. 

[FR Doc. 2017–24701 Filed 11–15–17; 8:45 am] 

BILLING CODE 3410–02–P 

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. 

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 

diane.cook@faa.gov. 

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 § 33.87 

without significant modifications 

making the test vehicle nonrepresentative of the type design. 

Discussion 

An alternative endurance test cycle 

has been developed that provides a level 

of safety equivalent with that intended 

by § 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 § 33.87 rule. 

These special conditions provide the 

necessary conditions for verification of 

engine-level and component-level 

effects as intended by the current 

§ 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 

§ 33.87 Endurance test. 

The equivalent level of severity 

intended by the § 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 


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Federal Register / Vol. 82, No. 220 / Thursday, November 16, 2017 / Rules and Regulations 53401 

design features that would not have 

been as challenged by the current 

§ 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 §§ 33.4 and 

33.29 are added to support an 

equivalent compliance by means of 

mandatory inspections prescribed in 

paragraph (b)(3) of the § 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 

§ 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 

§ 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 

■ 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 

§ 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. 

§ 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. 

§ 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 

§ 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 § 33.87(a)(1), (2), 

(4), and (6). 

(3) Requirements of § 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 § 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. 


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53402 Federal Register / Vol. 82, No. 220 / Thursday, November 16, 2017 / Rules and Regulations 

(5) Testing for engine fuel, oil, and 

hydraulic fluid pressure and oil 

temperature must be at least equal with 

the prescribed test required in 

§ 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 § 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 


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Federal Register / Vol. 82, No. 220 / Thursday, November 16, 2017 / Rules and Regulations 53403 

1Offer Caps in Markets Operated by Regional 

Transmission Organizations and Independent 

System Operators, 81 FR 87,770 (Dec. 5, 2016), 

FERC Stats. & Regs. ¶ 31,387 (2016) (Order No. 

831). 

2Order No. 831, FERC Stats. & Regs. ¶ 31,387 at 

PP 11–13. 

3 Id. P 1. 

4 Id. P 78. 

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 

DEPARTMENT OF ENERGY 

Federal Energy Regulatory 

Commission 

18 CFR Part 35 

[Docket No. RM16–5–001; Order No. 831– 

A] 

Offer Caps in Markets Operated by 

Regional Transmission Organizations 

and Independent System Operators 

AGENCY: Federal Energy Regulatory 

Commission, Department of Energy. 

ACTION: Order on rehearing and 

clarification. 

SUMMARY: The Federal Energy 

Regulatory Commission is granting in 

part and denying in part requests for 

rehearing and clarification of its 

determinations in Order No. 831, which 

amended its regulations to address 

incremental energy offer caps in markets 

operated by regional transmission 

organizations and independent system 

operators. 

DATES: This rule is effective January 16, 

2018. 

FOR FURTHER INFORMATION CONTACT: 

Emma Nicholson (Technical 

Information), Office of Energy Policy 

and Innovation, Federal Energy 

Regulatory Commission, 888 First 

Street NE., Washington, DC 20426, 

(202) 502–8846, emma.nicholson@

ferc.gov 

Pamela Quinlan (Technical 

Information), Office of Energy Market 

Regulation, Federal Energy Regulatory 

Commission, 888 First Street NE., 

Washington, DC 20426, (202) 502– 

6179, pamela.quinlan@ferc.gov 

Anne Marie Hirschberger (Legal 

Information), Office of the General 

Counsel, Federal Energy Regulatory 

Commission, 888 First Street NE., 

Washington, DC 20426, (202) 502– 

8387, annemarie.hirschberger@

ferc.gov 

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 

1. On November 17, 2016, the Federal 

Energy Regulatory Commission 

(Commission) issued Order No. 831.1

Order No. 831 addresses the 

incremental energy offer component of 

a resource’s supply offer, which is a 

financial component consisting of costs 

that vary with a resource’s output or 

level of demand reduction. Incremental 

energy offers are one of the components 

used to calculate locational marginal 

prices (LMPs). California Independent 

System Operator Corporation (CAISO), 

ISO New England Inc. (ISO–NE), 

Midcontinent Independent System 

Operator, Inc. (MISO), New York 

Independent System Operator, Inc. 

(NYISO), and Southwest Power Pool, 

Inc. (SPP) currently have a $1,000/MWh 

cap on incremental energy offers (offer 

cap), and PJM Interconnection, L.L.C. 

(PJM) currently has an offer cap of 

$2,000/MWh on cost-based offers.2

2. In Order No. 831, the Commission 

amended its regulations to require that 

each regional transmission organization 

and independent system operator (RTO/ 

ISO): (1) Cap each resource’s 

incremental energy offer at the higher of 

$1,000/MWh or that resource’s verified 

cost-based incremental energy offer; and 

(2) cap verified cost-based incremental 

energy offers at $2,000/MWh when 

calculating LMPs (hard cap).3 Resources 

with verified cost-based incremental 

energy offers above $2,000/MWh will be 

eligible to receive uplift.4 In response to 

comments on the Notice of Proposed 


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