Federal Register / Vol. 83, No. 247 / Thursday, December 27, 2018 / Rules and Regulations 66609 

hazardous loads on the airplane, nor 

create hazardous deviations in the flight 

path. This applies to both fault-free 

operation and in the event of a 

malfunction, and assumes the pilot 

begins corrective action within a 

reasonable period of time. 

(h) When the flight guidance system 

is in use, a means must be provided to 

avoid excursions beyond an acceptable 

margin from the speed range of the 

normal flight envelope. If the airplane 

experiences an excursion outside this 

range, a means must be provided to 

prevent the flight guidance system from 

providing guidance or control to an 

unsafe speed. 

(i) The flight guidance system 

functions, controls, indications, and 

alerts must be designed to minimize 

flight crew errors and confusion 

concerning the behavior and operation 

of the flight guidance system. Means 

must be provided to indicate the current 

mode of operation, including any armed 

modes, transitions, and reversions. 

Selector switch position is not an 

acceptable means of indication. The 

controls and indications must be 

grouped and presented in a logical and 

consistent manner. The indications 

must be visible to each pilot under all 

expected lighting conditions. 

(j) Following disengagement of the 

autothrust function, a caution (visual 

and auditory) must be provided to each 

pilot. 

(k) During autothrust operation, it 

must be possible for the flightcrew to 

move the thrust levers without requiring 

excessive force. The autothrust may not 

create a potential hazard when the 

flightcrew applies an override force to 

the thrust levers. 

(l) For purposes of this section, a 

transient is a disturbance in the control 

or flight path of the airplane that is not 

consistent with response to flight crew 

inputs or environmental conditions. 

(1) A minor transient would not 

significantly reduce safety margins and 

would involve flightcrew actions that 

are well within their capabilities. A 

minor transient may involve a slight 

increase in flight crew workload or 

some physical discomfort to passengers 

or cabin crew. 

(2) A significant transient may lead to 

a significant reduction in safety 

margins, an increase in flight crew 

workload, discomfort to the flightcrew, 

or physical distress to the passengers or 

cabin crew, possibly including non-fatal 

injuries. Significant transients do not 

require, in order to remain within or 

recover to the normal flight envelope, 

any of the following: 

(i) Exceptional piloting skill, 

alertness, or strength. 

(ii) Forces applied by the pilot that are 

greater than those specified in 

§ 23.143(c). 

(iii) Accelerations or attitudes in the 

airplane that might result in further 

hazard to secured or non-secured 

occupants. 

Issued in Kansas City, Missouri on 

December 17, 2018. 

Pat Mullen, 

Manager, Small Airplane Standards Branch, 

Aircraft Certification Service. 

[FR Doc. 2018–28116 Filed 12–26–18; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2018–0938; Product 

Identifier 2018–NE–36–AD; Amendment 39– 

19480; AD 2018–22–07] 

RIN 2120–AA64 

Airworthiness Directives; Engine 

Alliance Turbofan Engines 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule; request for 

comments. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for all 

Engine Alliance (EA) GP7270, GP7272, 

and GP7277 model turbofan engines. 

This AD requires inspection of the stage 

6 seal ring for correct installation and 

inspection of the high-pressure 

compressor (HPC) stages 2–5 spool for 

cracks. This AD also requires 

replacement of the HPC stages 2–5 spool 

if the stage 6 seal ring is incorrectly 

installed or if the HPC stages 2–5 spool 

is found cracked. This AD was 

prompted by a shop finding of axial 

cracks in the interstage 5–6 seal teeth of 

the HPC stages 2–5 spool spacer arm, 

due to an incorrectly installed stage 6 

seal ring. We are issuing this AD to 

address the unsafe condition on these 

products. 

DATES: This AD is effective January 11, 

2019. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of January 11, 2019. 

We must receive comments on this 

AD by February 11, 2019. 

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 Engine Alliance, 

411 Silver Lane, East Hartford, CT 

06118; phone: 800–565–0140; email: 

help24@pw.utc.com; website: 

www.engineallianceportal.com. You 

may view this service information at the 

FAA, Engine and Propeller Standards 

Branch, 1200 District Avenue, 

Burlington, MA 01803. 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– 

0938. 

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– 

0938; 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: 

Matthew Smith, Aerospace Engineer, 

ECO Branch, FAA, 1200 District 

Avenue, Burlington, MA 01803; phone: 

781–238–7735; fax: 781–238–7199; 

email: Matthew.C.Smith@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We were informed about the 

discovery of axial cracks in the 

interstage 5–6 seal teeth of the HPC 

stages 2–5 spool spacer arm, due to an 

incorrectly installed stage 6 seal ring, in 

a GP7270 model turbofan engine. The 

incorrect installation of the stage 6 seal 

ring created a leakage path from the aft 

cavity to the forward cavity of the HPC 

stage 6 disk. This leakage elevated the 


khammond on DSK30JT082PROD with RULES
66610 Federal Register / Vol. 83, No. 247 / Thursday, December 27, 2018 / Rules and Regulations 

temperature in the cavity and adversely 

affected the material properties of the 

HPC stages 2–5 spool. This condition, if 

not addressed, could result in failure of 

the HPC stages 2–5 spool, an 

uncontained HPC stages 2–5 spool 

release, damage to the engine, 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 EA Alert Service 

Bulletin (ASB) EAGP7–A72–395, 

Revision No. 2, dated August 2, 2018. 

The SB describes procedures for 

performing a borescope inspection of 

the installed HPC stages 2–5 spool for 

cracks, visual inspection of the stage 6 

seal ring for correct installation, visual 

inspection of the interstage 5–6 seal 

teeth for damage, and removal and 

replacement of parts if damage or 

defects are found that are outside 

serviceable limits, within the identified 

cycles. 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. 

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 inspection of the 

stage 6 seal ring for correct installation 

and inspection of the HPC stages 2–5 

spool for cracks. This AD also requires 

removal and replacement of the HPC 

stages 2–5 spool if the stage 6 seal ring 

is incorrectly installed or the interstage 

5–6 seal teeth are found cracked. 

FAA’s Justification and Determination 

of the Effective Date 

No domestic operators use this 

product. Therefore, we find good cause 

that notice and opportunity for prior 

public comment are unnecessary. 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–2018–0938 and Product Identifier 

2018–NE–36–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. 

Costs of Compliance 

We estimate that this AD affects zero 

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 

Borescope inspection of stage 6 seal ring 

and interstage 5–6 seal teeth forward and 

aft faces only.

4 work-hours × $85 per hour = $340 ............. $0 $340 $0 

We estimate the following costs to do 

any necessary replacements that would 

be required based on the results of the 

inspection. We have no way of 

determining the number of aircraft that 

might need these replacements: 

ON-CONDITION COSTS

Action Labor cost Parts cost Cost per 

product 

Replacement of HPC stages 2 to 5 spool ................... 8 work-hours × $85 per hour = $680 ........................... $346,540 $347,220 

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 


khammond on DSK30JT082PROD with RULES
Federal Register / Vol. 83, No. 247 / Thursday, December 27, 2018 / Rules and Regulations 66611 

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): 

AD 2018–22–07 Engine Alliance: 

Amendment 39–19480; Docket No. 

FAA–2018–0938; Product Identifier 

2018–NE–36–AD. 

(a) Effective Date 

This AD is effective January 11, 2019. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to all Engine Alliance (EA) 

GP7270, GP7272, and GP7277 model 

turbofan engines. 

(d) Subject 

Joint Aircraft System Component (JASC) 

Code 7230, Turbine Engine Compressor 

Section. 

(e) Unsafe Condition 

This AD was prompted by a shop finding 

of axial cracks in the interstage 5–6 seal teeth 

of the high-pressure compressor (HPC) stages 

2–5 spool spacer arm, due to an incorrectly 

installed stage 6 seal ring. We are issuing this 

AD to prevent failure of the HPC stage 5–6 

seal teeth and uncontained HPC stages 2–5 

spool release. The unsafe condition, if not 

addressed, could result in an uncontained 

failure of the HPC stages 2–5 spool, damage 

to the engine, and damage to the airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Required Actions 

(1) Borescope inspect the stage 6 seal ring 

location in accordance with the 

Accomplishment Instructions, paragraph 1.F, 

in EA Alert Service Bulletin (ASB) EAGP7– 

A72–395, Revision No. 2, dated August 2, 

2018, and within the compliance times 

specified in Table 1 to paragraph (g) of this 

AD. If the stage 6 seal ring is incorrectly 

installed, remove the HPC stages 2–5 spool 

from service within 50 cycles and replace 

with a part eligible for installation. 

(2) Borescope inspect the interstage 5–6 

seal tooth aft face and interstage 5–6 forward 

face for cracks and missing coating in 

accordance with the Accomplishment 

Instructions, paragraphs 2.C and 2.E, in EA 

ASB EAGP7–A72–395, Revision No. 2, dated 

August 2, 2018, and within the compliance 

times specified in Table 1 to paragraph (g) of 

this AD. 

(i) If coating is missing on the interstage 5– 

6 seal tooth forward or aft faces, repeat the 

borescope inspection required by paragraph 

(g)(2) of this AD for cracks every 150 cycles. 

(ii) If cracks are found in the interstage 5– 

6 seal tooth forward or aft faces, remove the 

HPC stages 2–5 spool from service and 

replace with a part eligible for installation 

before further flight. 

(h) 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 (i) 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. 

(i) Related Information 

For more information about this AD, 

contact Matthew Smith, Aerospace Engineer, 

ECO Branch, FAA, 1200 District Avenue, 

Burlington, MA 01803; phone: 781–238– 

7735; fax: 781–238–7199; email: 

Matthew.C.Smith@faa.gov. 

(j) 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) Engine Alliance (EA) Alert Service 

Bulletin EAGP7–A72–395, Revision No. 2, 

dated August 2, 2018. 

(ii) [Reserved] 


khammond on DSK30JT082PROD with RULESER27DE18.041</GPH>
66612 Federal Register / Vol. 83, No. 247 / Thursday, December 27, 2018 / Rules and Regulations 

(3) For EA service information identified in 

this AD, contact Engine Alliance, 411 Silver 

Lane, East Hartford, CT 06118; phone: 800– 

565–0140; email: help24@pw.utc.com; 

website: www.engineallianceportal.com. 

(4) You may view this service information 

at FAA, Engine and Propeller Standards 

Branch, 1200 District Avenue, Burlington, 

MA 01803. 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 

December 19, 2018. 

Robert J. Ganley, 

Manager, Engine and Propeller Standards 

Branch, Aircraft Certification Service. 

[FR Doc. 2018–27926 Filed 12–26–18; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2018–0711; Product 

Identifier 2018–NM–062–AD; Amendment 

39–19533; AD 2018–26–03] 

RIN 2120–AA64 

Airworthiness Directives; The Boeing 

Company Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for all The 

Boeing Company Model 757–200 series 

airplanes. This AD was prompted by 

reports of uncommanded movement of 

the captain’s and first officer’s seats. 

This AD requires, for the captain’s and 

first officer’s seats, repetitive horizontal 

actuator identifications, repetitive 

checks of the horizontal movement 

system (HMS), a detailed inspection of 

the HMS, as applicable, and applicable 

on-condition actions. This AD also 

requires a general visual inspection to 

determine the seat part numbers of the 

captain’s and first officer’s seats, a cable 

adjustment check on seats with certain 

seat part numbers, and applicable oncondition actions. We are issuing this 

AD to address the unsafe condition on 

these products. 

DATES: This AD is effective January 31, 

2019. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of January 31, 2019. 

ADDRESSES: For service information 

identified in this final rule, contact 

Boeing Commercial Airplanes, 

Attention: Contractual & Data Services 

(C&DS), 2600 Westminster Blvd., MC 

110–SK57, Seal Beach, CA 90740–5600; 

telephone 562–797–1717; internet 

https://www.myboeingfleet.com. You 

may view this service information at the 

FAA, Transport Standards Branch, 2200 

South 216th St., Des Moines, WA. For 

information on the availability of this 

material at the FAA, call 206–231–3195. 

It is also available on the internet at 

http://www.regulations.gov by searching 

for and locating Docket No. FAA–2018– 

0711. 

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– 

0711; 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 address for Docket 

Operations (phone: 800–647–5527) is 

U.S. Department of Transportation, 

Docket Operations, M–30, West 

Building Ground Floor, Room W12–140, 

1200 New Jersey Avenue SE, 

Washington, DC 20590. 

FOR FURTHER INFORMATION CONTACT: 

Myra Kuck, Aerospace Engineer, Cabin 

Safety and Environmental Systems 

Section, FAA, Los Angeles ACO Branch, 

3960 Paramount Boulevard, Lakewood, 

CA 90712–4137; phone: 562–627–5316; 

fax: 562–627–5210; email: myra.j.kuck@

faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 by adding an AD that would 

apply to all The Boeing Company Model 

757–200 series airplanes. The NPRM 

published in the Federal Register on 

August 16, 2018 (83 FR 40710). The 

NPRM was prompted by reports of 

uncommanded movement of the 

captain’s and first officer’s seats. The 

NPRM proposed to require, for the 

captain’s and first officer’s seats, 

repetitive horizontal actuator 

identifications, repetitive checks of the 

HMS, a detailed inspection of the HMS, 

as applicable, and applicable oncondition actions. The NPRM also 

proposed to require a general visual 

inspection to determine seat part 

numbers of the captain’s and first 

officer’s seats, a cable adjustment check 

on seats with certain seat part numbers, 

and applicable on-condition actions. 

Comments 

We gave the public the opportunity to 

participate in developing this final rule. 

The following presents the comments 

received on the NPRM and the FAA’s 

response to each comment. 

Support for the NPRM 

Air Line Pilots Association, 

International (ALPA) stated its support 

for the NPRM. United Airlines stated 

that it has no technical objections to the 

NPRM. 

Effect of Winglets on Accomplishment 

of the Proposed Actions 

Aviation Partners Boeing (APB) stated 

that the installation of winglets per 

Supplemental Type Certificate (STC) 

ST01518SE does not affect the 

accomplishment of the manufacturer’s 

service instructions. 

We agree with APB that STC 

ST01518SE does not affect the 

accomplishment of the manufacturer’s 

service instructions. Therefore, the 

installation of STC ST01518SE does not 

affect the ability to accomplish the 

actions required by this AD. We have 

not changed this AD in this regard. 

Request To Add Airplane Models to 

Applicability 

Delta Air Lines (DAL) requested that 

the FAA consider expanding the 

applicability of the proposed AD to 

address all affected fleets that share the 

identified unsafe condition, or consider 

requiring effectivity at the manufacturer 

part number. DAL reasoned that 

expanding the applicability of the 

proposed AD to include all affected 

airplane models or affected 

manufacturer part numbers would ease 

the burden on operators by allowing 

them to forgo commenting on multiple 

proposed fleet ADs and processing 

separate AD-related service information 

by individual fleet type. DAL pointed 

out that this would greatly assist 

operators with implementation for 

operators that share the same affected 

part number among different affected 

fleets. 

We disagree with the commenter’s 

request. Not all of the service 

information for all affected airplane 

models is available, and we do not agree 

to delay issuance of this AD until new 

service information is released. 

Moreover, adding airplanes to the 

applicability would necessitate (under 

the provisions of the Administrative 

Procedure Act) reissuing the notice, 


khammond on DSK30JT082PROD with RULES