36724 Federal Register / Vol. 83, No. 147 / Tuesday, July 31, 2018 / Rules and Regulations 

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, or should any other 

model already included on the same 

type certificate be modified to 

incorporate the same novel or unusual 

design feature, these special conditions 

would also apply to the other model 

under § 21.101. 

In addition to the applicable 

airworthiness regulations and special 

conditions, the Bombardier Model BD– 

700–2A12 and BD–700–2A13 series 

airplanes must comply with the fuelvent and exhaust-emission requirements 

of 14 CFR part 34, and the noisecertification requirements of 14 CFR 

part 36. 

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 

§ 21.101. 

Novel or Unusual Design Features 

The Model BD–700–2A12 and BD– 

700–2A13 series airplanes will 

incorporate the following novel or 

unusual design features: 

Fly-by-wire EFCS that will limit pitch 

and roll functions to prevent the 

airplane from attaining certain pitch 

attitudes and roll angles greater than 

plus or minus 65 degrees, and introduce 

positive spiral stability introduced for 

roll angles greater than 30 degrees at 

speeds below VMO/MMO. This system 

generates the actual surface commands 

that provide for stability augmentation 

and flight control for all three airplane 

axes (longitudinal, lateral, and 

directional). 

Discussion 

Part 25 of title 14 of the CFR does not 

specifically relate to flight 

characteristics associated with fixed 

attitude limits. Bombardier proposes to 

implement on the airplanes pitch and 

roll attitude-limiting functions via the 

EFCS normal mode. This will prevent 

the airplane from attaining certain pitch 

attitudes and roll angles greater than 

plus or minus 65 degrees. In addition, 

positive spiral stability, introduced for 

roll angles greater than 30 degrees at 

speeds below VMO/MMO, and spiral 

stability characteristics, must not 

require excessive pilot strength to 

achieve bank angles up to the bankangle limit. 

Bombardier requested this 

amendment, in order to be performancebased rather than prescriptive and to 

more closely follow the language 

developed in the Aviation Rulemaking 

Advisory Committee (ARAC) Flight Test 

Harmonization Working Group 

(FTHWG). The FAA concurs with this 

request. 

The basic envelope protection 

requirement, historically applied, is to 

not unduly limit the maneuver 

capability of the airplane, or interfere 

with its ability to perform maneuvers 

required for normal and emergency 

operations. Since the design details 

used to meet this requirement vary from 

airplane to airplane, this amendment 

recognizes and adopts that philosophy 

for this specific design implementation. 

The substance of the special conditions 

is unchanged, in that, for this specific 

design, the design details support the 

objective of not unduly limiting the 

maneuver capability, while also 

protecting the airplane from adverse 

attitudes. 

These special conditions are in 

addition to the requirements of § 25.143. 

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 Model 

BD–700–2A12 and BD–700–2A13 series 

airplanes. Should Bombardier 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 one model 

series of airplanes. It is not a rule of 

general applicability. 

List of Subjects in 14 CFR Part 25 

Aircraft, Aviation safety, Reporting 

and recordkeeping requirements. 

Authority Citation 

The authority citation for these 

special conditions is as follows: 

Authority: 49 U.S.C. 106(f), 106(g), 40113, 

44701, 44702, 44704. 

The Special Conditions 

■ Accordingly, pursuant to the authority 

delegated to me by the Administrator, 

the following special conditions are 

issued as part of the type certification 

basis for Bombardier Model BD–700– 

2A12 and BD–700–2A13 series 

airplanes: 

In addition to § 25.143, the following 

requirements apply to the electronic 

flight-control system (EFCS) pitch- and 

roll-limiting functions: 

1. The pitch-limiting function must 

not impede normal maneuvering for 

pitch angles up to the maximum 

required for normal maneuvering, 

including a normal, all-enginesoperating takeoff, plus a suitable margin 

to allow for satisfactory speed control. 

2. The pitch- and roll-limiting 

functions must not restrict or prevent 

attaining pitch attitudes necessary for 

emergency maneuvering, or roll angles 

up to 65 degrees. Spiral stability, which 

is introduced above 30 degrees of roll 

angle, must not require excessive pilot 

strength to achieve these roll angles. 

Other protections, which further limit 

the roll capability under certain extreme 

angle-of-attack, attitude, or high-speed 

conditions, are acceptable, as long as the 

airplane is able to perform coordinated 

turns as per § 25.143(h). A roll attitude 

limit of approximately 45 degrees at 

high angle-of-attack conditions is 

acceptable. 

3. A reduced roll attitude limit is 

acceptable at extreme nose down pitch 

attitudes and beyond the overspeed 

warning to provide protection against 

high-speed combined pitch and roll 

upsets. The airplane should be able to 

perform operational turns at these 

speeds. A roll attitude limit of 

approximately 30 degrees at Vdf/Mdf is 

considered acceptable. 

Issued in Des Moines, Washington. 

Victor Wicklund, 

Manager, Transport Standards Branch, Policy 

and Innovation Division, Aircraft 

Certification Service. 

[FR Doc. 2018–16360 Filed 7–30–18; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2018–0630; Product 

Identifier 2018–NE–25–AD; Amendment 39– 

19347; AD 2018–16–07] 

RIN 2120–AA64 

Airworthiness Directives; General 

Electric Company Turbofan Engines 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule; request for 

comments. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for certain 

General Electric Company (GE) GEnx– 

1B54, –1B58, –1B64, –1B67, –1B70, 

–1B54/P1, –1B58/P1, –1B64/P1, –1B67/ 


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Federal Register / Vol. 83, No. 147 / Tuesday, July 31, 2018 / Rules and Regulations 36725 

P1, –1B70/P1, –1B54/P2, –1B58/P2, 

–1B64/P2, –1B67/P2, –1B70/P2, 

–1B70C/P1, –1B70/72/P1, –1B70/75/P1, 

–1B74/75/P1, –1B75/P1, –1B70C/P2, 

–1B70/72/P2, –1B70/75/P2, –1B74/75/ 

P2, –1B75/P2, –1B76/P2, –1B76A/P2, 

–1B78/P2, –2B67, –2B67B, and 

–2B67/P turbofan engines. This AD 

requires removal of affected highpressure turbine (HPT) stator cases (HPT 

cases) from service and their 

replacement with a part eligible for 

installation. This AD was prompted by 

the discovery of a quality escape at a 

manufacturing facility. We are issuing 

this AD to address the unsafe condition 

on these products. 

DATES: This AD is effective August 15, 

2018. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of August 15, 2018. 

We must receive comments on this 

AD by September 14, 2018. 

ADDRESSES: You may send comments, 

using the procedures found in 14 CFR 

11.43 and 11.45, by any of the following 

methods: 

• Federal eRulemaking Portal: Go to 

http://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 final rule, contact General Electric 

Company, GE Aviation, Room 285, 1 

Neumann Way, Cincinnati, OH 45215; 

phone: 513–552–3272; email: 

aviation.fleetsupport@ge.com. You may 

view this service information at the 

FAA, Engine and Propeller Standards 

Branch, 1200 District Avenue, 

Burlington, MA. For information on the 

availability of this material at the FAA, 

call 781–238–7759. It is also available 

on the internet at http://

www.regulations.gov by searching for 

and locating Docket No. FAA–2018– 

0630. 

Examining the AD Docket 

You may examine the AD docket on 

the internet at http://

www.regulations.gov by searching for 

and locating Docket No. FAA–2018– 

0630; 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 final rule, 

the regulatory evaluation, any 

comments received, and other 

information. The street address for the 

Docket Operations (phone: 800–647– 

5527) is listed above. Comments will be 

available in the AD docket shortly after 

receipt. 

FOR FURTHER INFORMATION CONTACT: 

Herman Mak, Aerospace Engineer, ECO 

Branch, FAA, 1200 District Avenue, 

Burlington, MA 01803; phone: 781– 

238–7147; fax: 781–238–7199; email: 

herman.mak@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We learned from GE of a quality 

escape at one of their suppliers. This 

supplier was performing welds on 

newly-manufactured components to 

correct errors introduced in their 

manufacturing process. These welds 

were not reviewed or approved by either 

GE or the FAA. GE’s review of 

manufacturing records determined that 

these parts include HPT cases installed 

on GEnx engines. These HPT cases are 

life limited. The unapproved repairs 

reduced the material capability of these 

cases which requires their removal prior 

to reaching their published 

Airworthiness Limitation Section life 

limit. This condition, if not addressed, 

could result in failure of the HPT case, 

engine fire, and damage to the airplane. 

We are issuing this AD to address the 

unsafe condition on these products. 

Related Service Information Under 1 

CFR Part 51 

We reviewed GE Service Bulletin (SB) 

GEnx–1B S/B 72–0424, Revision 03, 

dated June 29, 2018 and GEnx–2B S/B 

72–0360, Revision 03, dated June 29, 

2018. The SBs describe procedures for 

removing the affected HPT cases from 

the engine. GE SB GEnx–1B S/B 72– 

0424 is effective for GEnx–1B engines 

with the serial numbers of HPT cases 

listed in that SB. GE SB GEnx–2B S/B 

72–0360 is effective for GEnx-2B 

engines with the serial numbers of HPT 

cases listed in that SB. 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. 

Other Related Service Information 

We reviewed Inspection 001, Subtask 

72–52–01–230–001 of GEnx–1B 

Cleaning, Inspection, and Repair 

Manual GEK112862, Rev 27, dated April 

30, 2018, and GEnx–2B Cleaning, 

Inspection, and Repair Manual 

GEK114120, Rev 20, dated April 30, 

2018. These manuals provide guidance 

for conducting Class A fluorescent 

penetrant inspections. 

FAA’s Determination 

We are issuing this AD because we 

evaluated all the relevant information 

and determined the unsafe condition 

described previously is likely to exist or 

develop in other products of the same 

type design. 

AD Requirements 

This AD requires removal of the 

affected HPT cases from service and 

their replacement with a part eligible for 

installation. 

FAA’s Justification and Determination 

of the Effective Date 

An unsafe condition exists that 

requires the immediate adoption of this 

AD without providing an opportunity 

for public comments prior to adoption. 

The FAA has found that the risk to the 

flying public justifies waiving notice 

and comment prior to adoption of this 

rule because the compliance time for the 

required action is shorter than the time 

necessary for the public to comment and 

for us to publish the final rule. 

Therefore, we find good cause that 

notice and opportunity for prior public 

comment are impracticable. In addition, 

for the reason stated above, we find that 

good cause exists for making this 

amendment effective in less than 30 

days. 

Comments Invited 

This AD is a final rule that involves 

requirements affecting flight safety and 

was not preceded by notice and an 

opportunity for public comment. 

However, we invite you to send any 

written data, views, or arguments about 

this final rule. Send your comments to 

an address listed under the ADDRESSES

section. Include the docket number 

FAA–2018–0630 and Product Identifier 

2018–NE–25–AD at the beginning of 

your comments. We specifically invite 

comments on the overall regulatory, 

economic, environmental, and energy 

aspects of this final rule. We will 

consider all comments received by the 

closing date and may amend this final 

rule because of those comments. 

We will post all comments we 

receive, without change, to http://

www.regulations.gov, including any 

personal information you provide. We 

will also post a report summarizing each 

substantive verbal contact we receive 

about this final rule. 


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Costs of Compliance 

We estimate that this AD affects 13 

engines installed on airplanes of U.S. 

registry. 

We estimate the following costs to 

comply with this AD: 

ESTIMATED COSTS

Action Labor cost Parts cost Cost per 

product 

Cost on U.S. 

operators 

Replacement of HPT case .............................. 0 work-hours × $85 per hour = $0 ................. $362,400 $362,400 $4,711,200 

Authority for This Rulemaking 

Title 49 of the United States Code 

specifies the FAA’s authority to issue 

rules on aviation safety. Subtitle I, 

section 106, describes the authority of 

the FAA Administrator. ‘‘Subtitle VII: 

Aviation Programs’’ describes in more 

detail the scope of the Agency’s 

authority. 

We are issuing this rulemaking under 

the authority described in Subtitle VII, 

Part A, Subpart III, Section 44701: 

‘‘General requirements.’’ Under that 

section, Congress charges the FAA with 

promoting safe flight of civil aircraft in 

air commerce by prescribing regulations 

for practices, methods, and procedures 

the Administrator finds necessary for 

safety in air commerce. This regulation 

is within the scope of that authority 

because it addresses an unsafe condition 

that is likely to exist or develop on 

products identified in this rulemaking 

action. 

This AD is issued in accordance with 

authority delegated by the Executive 

Director, Aircraft Certification Service, 

as authorized by FAA Order 8000.51C. 

In accordance with that order, issuance 

of ADs is normally a function of the 

Compliance and Airworthiness 

Division, but during this transition 

period, the Executive Director has 

delegated the authority to issue ADs 

applicable to engines, propellers, and 

associated appliances to the Manager, 

Engine and Propeller Standards Branch, 

Policy and Innovation Division. 

Regulatory Findings 

This AD will not have federalism 

implications under Executive Order 

13132. This AD will not have a 

substantial direct effect on the States, on 

the relationship between the national 

government and the States, or on the 

distribution of power and 

responsibilities among the various 

levels of government. 

For the reasons discussed above, I 

certify that this AD: 

(1) Is not a ‘‘significant regulatory 

action’’ under Executive Order 12866, 

(2) Is not a ‘‘significant rule’’ under 

DOT Regulatory Policies and Procedures 

(44 FR 11034, February 26, 1979), 

(3) Will not affect intrastate aviation 

in Alaska, and 

(4) Will not have a significant 

economic impact, positive or negative, 

on a substantial number of small entities 

under the criteria of the Regulatory 

Flexibility Act. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety. 

Adoption of the Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA amends 14 CFR part 39 as 

follows: 

PART 39—AIRWORTHINESS 

DIRECTIVES 

■ 1. The authority citation for part 39 

continues to read as follows: 

Authority: 49 U.S.C. 106(g), 40113, 44701. 

§ 39.13 [Amended] 

■ 2. The FAA amends § 39.13 by adding 

the following new airworthiness 

directive (AD): 

2018–16–07 General Electric Company: 

Amendment 39–19347; Docket No. 

FAA–2018–0630; Product Identifier 

2018–NE–25–AD. 

(a) Effective Date 

This AD is effective August 15, 2018. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to General Electric 

Company (GE) GEnx–1B54, –1B58, –1B64, 

–1B67, –1B70, –1B54/P1, –1B58/P1, –1B64/ 

P1, –1B67/P1, –1B70/P1, –1B54/P2, –1B58/ 

P2, –1B64/P2, –1B67/P2, –1B70/P2, –1B70C/ 

P1, –1B70/72/P1, –1B70/75/P1, –1B74/75/P1, 

–1B75/P1, –1B70C/P2, –1B70/72/P2, –1B70/ 

75/P2, –1B74/75/P2, –1B75/P2, –1B76/P2, 

–1B76A/P2, –1B78/P2, –2B67, –2B67B, and 

–2B67/P turbofan engines with a highpressure turbine (HPT) stator case (HPT 

case), part number (P/N) 2302M90G04 

installed, and with any serial number (S/N) 

listed in Table 1, 2, or 3, in the Planning 

Information section of GE Service Bulletin 

(SB) GEnx–2B S/B 72–0360, Revision 03, 

dated June 29, 2018, or GEnx–1B S/B 72– 

0424, Revision 03, dated June 29, 2018, 

installed. 

(d) Subject 

Joint Aircraft System Component (JASC) 

Code 7250, Turbine Section. 

(e) Unsafe Condition 

This AD was prompted by the discovery of 

a quality escape at a manufacturing facility 

involving unapproved welds on HPT cases. 

We are issuing this AD to prevent failure of 

the HPT case. The unsafe condition, if not 

addressed, could result in engine fire and 

damage to the airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Required Actions 

(1) For HPT cases listed in Planning 

Information, Table 1 or 2, of GE SBs GEnx– 

2B S/B 72–0360, Revision 03, dated June 29, 

2018 and GEnx–1B S/B 72–0424, Revision 

03, dated June 29, 2018, determine the lesser 

of the following: Cycles since new (CSN) or 

cycles since Class A fluorescent penetrant 

inspection (CSFPI) of the entire HPT case. 

(2) Using the determination made in 

paragraph (g)(1) of this AD, remove from 

service the HPT case after the effective date 

of this AD as specified in Table 1 to 

paragraph (g) of this AD. Replace the 

removed HPT case with a part eligible for 

installation. 


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Federal Register / Vol. 83, No. 147 / Tuesday, July 31, 2018 / Rules and Regulations 36727 

(3) Remove from service HPT cases listed 

in Planning Information, Table 3, of GE SBs 

GEnx–2B S/B 72–0360, Revision 03, dated 

June 29, 2018 or GEnx–1B S/B 72–0424, 

Revision 03, dated June 29, 2018, prior to 

exceeding 10 cycles after the effective date of 

this AD or exceeding the CSN limits listed in 

Table 3, whichever comes later. Replace the 

removed HPT case with a part eligible for 

installation. 

(h) Installation Prohibition 

(1) After the effective date of this AD, do 

not install any affected HPT case onto any 

engine. 

(2) After the effective date of this AD, HPT 

cases listed in Planning Information, Table 3, 

in GE SB GEnx–2B S/B 72–0360, Revision 03, 

dated June 29, 2018 or GEnx–1B S/B 72– 

0424, Revision 03, dated June 29, 2018, and 

any higher level assemblies with these parts 

installed, may not be removed from a GEnx– 

2B engine and installed on a GEnx–1B engine 

or removed from a GEnx–1B engine and 

installed on a GEnx–2B engine. 

(i) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, ECO Branch, FAA, has 

the authority to approve AMOCs for this AD, 

if requested using the procedures found in 14 

CFR 39.19. In accordance with 14 CFR 39.19, 

send your request to your principal inspector 

or local Flight Standards District Office, as 

appropriate. If sending information directly 

to the manager of the certification office, 

send it to the attention of the person 

identified in paragraph (j) of this AD. You 

may email your request to: ANE-AD-AMOC@

faa.gov. 

(2) Before using any approved AMOC, 

notify your appropriate principal inspector, 

or lacking a principal inspector, the manager 

of the local flight standards district office/ 

certificate holding district office. 

(j) Related Information 

For more information about this AD, 

contact Herman Mak, Aerospace Engineer, 

ECO Branch, FAA, 1200 District Avenue, 

Burlington, MA 01803; phone: 781–238– 

7147; fax: 781–238–7199; email: 

herman.mak@faa.gov. 

(k) Material Incorporated by Reference 

(1) The Director of the Federal Register 

approved the incorporation by reference 

(IBR) of the service information listed in this 

paragraph under 5 U.S.C. 552(a) and 1 CFR 

part 51. 

(2) You must use this service information 

as applicable to do the actions required by 

this AD, unless the AD specifies otherwise. 

(i) General Electric Company (GE) Service 

Bulletin (SB) GEnx–2B S/B 72–0360, 

Revision 03, dated June 29, 2018. 

(ii) GE SB GEnx–1B S/B 72–0424, Revision 

03, dated June 29, 2018. 

(3) For GE service information identified in 

this AD, contact General Electric Company, 

GE Aviation, Room 285, 1 Neumann Way, 

Cincinnati, OH 45215; phone: 513–552–3272; 

email: aviation.fleetsupport@ge.com. 

(4) You may view this service information 

at FAA, Engine and Propeller Standards 

Branch, 1200 District Avenue, Burlington, 

MA. For information on the availability of 

this material at the FAA, call 781–238–7759. 

(5) You may view this service information 

that is incorporated by reference at the 

National Archives and Records 

Administration (NARA). For information on 

the availability of this material at NARA, call 

202–741–6030, or go to: http://

www.archives.gov/federal-register/cfr/ibrlocations.html. 

Issued in Burlington, Massachusetts, on 

July 25, 2018. 

Karen M. Grant, 

Acting Manager, Engine & Propeller 

Standards Branch, Aircraft Certification 

Service. 

[FR Doc. 2018–16309 Filed 7–30–18; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF ENERGY 

Federal Energy Regulatory 

Commission 

18 CFR Part 40 

[Docket No. RM18–2–000; Order No. 848] 

Cyber Security Incident Reporting 

Reliability Standards 

AGENCY: Federal Energy Regulatory 

Commission. 

ACTION: Final rule. 

SUMMARY: The Federal Energy 

Regulatory Commission (Commission) 

directs the North American Electric 

Reliability Corporation (NERC) to 

develop and submit modifications to the 

NERC Reliability Standards to augment 

the mandatory reporting of Cyber 

Security Incidents, including incidents 

that might facilitate subsequent efforts 

to harm the reliable operation of the 

bulk electric system (BES). 

DATES: This rule will become effective 

October 1, 2018. 

FOR FURTHER INFORMATION CONTACT: 

Margaret Steiner (Technical 

Information), Office of Electric 

Reliability, Federal Energy Regulatory 

Commission, 888 First Street NE, 

Washington, DC 20426, (202) 502–6704, 

Margaret.Steiner@ferc.gov. 

Kevin Ryan (Legal Information), 

Office of the General Counsel, Federal 

Energy Regulatory Commission, 888 

First Street NE, Washington, DC 20426, 

(202) 502–6840, Kevin.Ryan@ferc.gov. 

SUPPLEMENTARY INFORMATION: 

Order No. 848—Final Rule (Issued July 

19, 2018) 

1. Pursuant to section 215(d)(5) of the 

Federal Power Act (FPA), the 

Commission directs the North American 

Electric Reliability Corporation (NERC) 

to develop and submit modifications to 


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