29474 Federal Register / Vol. 83, No. 122 / Monday, June 25, 2018 / Proposed Rules 

requirements. Ultramagic’s change 

application applied the language in the 

EASA proposed special condition for CS 

31HA.14(c), ‘‘Occupant mass,’’ CS 

31HA.43(d), ‘‘Fitting factor,’’ CS 

31HA.561(a) and (b)(1), ‘‘Emergency 

landing conditions—General,’’ and CS 

31HA.785(a), (c), and (d), ‘‘Seats and 

seat belts’’ to the CV–08 basket. The 

FAA finds that these standards are 

appropriate for a seated, restrained 

occupant. 

Applicability 

As discussed above, these special 

conditions are applicable to the Model 

M–56, M–56C, M–65, M–65C, M–77, M– 

77C, M–90, M–105, M–120, M–130, M– 

145, M–160, N–180, N–210, N–250, N– 

300, N–355, N–425, S–70, S–90, S–105, 

S–130, S–160, T–150, T–180, T–210, V– 

56, V–65, V–77, V–90, and V–105 

balloons. Should Ultramagic apply at a 

later date for a change to the type 

certificate to include another model 

incorporating the same novel or unusual 

design feature, the FAA would apply 

these special conditions to that model as 

well. 

Conclusion 

This action affects only certain novel 

or unusual design features on the 

balloon models specified in these 

special conditions. It is not a rule of 

general applicability and it affects only 

the applicant who applied to the FAA 

for approval of these features on the 

airplane. These proposed special 

conditions are identical in intent to the 

EASA special conditions, although the 

formatting has been altered to meet 

these special condition requirements. 

List of Subjects in 14 CFR Part 23 

Aircraft, Aviation safety. 

The authority citation for these 

special conditions is as follows: 

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

44702, 44704. 

The Proposed Special Conditions 

Accordingly, the FAA proposes the 

following special conditions as part of 

the type certification basis for 

Ultramagic S.A. Model M–56, M–56C, 

M–65, M–65C, M–77, M–77C, M–90, M– 

105, M–120, M–130, M–145, M–160, N– 

180, N–210, N–250, N–300, N–355, N– 

425, S–70, S–90, S–105, S–130, S–160, 

T–150, T–180, T–210, V–56, V–65, V– 

77, V–90, and V–105 balloons with a 

basket Model no. CV–08. 

1. Hot Air Balloon Crashworthiness 

Requirements for Seat Installations and 

Restraints for Seated and Restrained 

Occupants 

a. Occupant Mass 

For calculation purposes, it should be 

assumed the mass of an occupant is at 

least 86 kilograms (190 pounds). 

b. Seats, Safety Belts, and Harnesses 

Factor of Safety 

For each seat, safety belt, and harness, 

its attachment to the structure must be 

shown, by analysis, tests, or both, to be 

able to withstand the inertia forces 

prescribed in paragraph (c) of these 

special conditions multiplied by a 

fitting factor of 1.33. 

c. Emergency Landing Conditions— 

General 

The balloon—although it may be 

damaged under emergency landing 

conditions—must be designed to give 

each occupant every reasonable chance 

of avoiding serious injury in a crash 

landing—when seat belts provided for 

in the design are properly used—and 

the occupant is subject to the following 

ultimate inertia forces acting relative to 

the surrounding structure as well as 

independently of each other. 

(1) Forward 6g 

(2) Sideways 6g 

(3) Downward 6g 

d. Seats and Seatbelts 

(1) Each seat and its supporting 

structure must be designed for an 

occupant mass in accordance paragraph 

(a) of these special conditions and for 

the maximum load factors 

corresponding to the specified flight and 

ground load conditions, including the 

emergency landing conditions 

prescribed in paragraph (c) of these 

special conditions. 

(2) Each seat or berth shall be fitted 

with an individual approved seat belt or 

harness. 

(3) Seat belts installed on the balloon 

must not fail under flight or ground load 

conditions or emergency landing 

conditions in accordance with 

paragraph (c) of these special 

conditions, taking into account the 

geometrical arrangement of the belt 

attachment and the seat. 

Issued in Kansas City, Missouri, on June 

15, 2018. 

Pat Mullen, 

Manager, Small Airplane Standards Branch, 

Aircraft Certification Service. 

[FR Doc. 2018–13499 Filed 6–22–18; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2018–0406; Product 

Identifier 2013–NE–30–AD] 

RIN 2120–AA64 

Airworthiness Directives; General 

Electric Company Turbofan Engines 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to supersede 

Airworthiness Directive (AD) 2017–07– 

04, which applies to General Electric 

Company (GE) GE90–110B1 and GE90– 

115B turbofan engines with certain 

high-pressure compressor (HPC) rotor 

stage 2–5 spools installed. AD 2017–07– 

04 resulted from reports of cracks in 

HPC rotor stage 2–5 spool aft spacer 

arms. Since we issued AD 2017–07–04, 

GE released a new service bulletin (SB) 

that increases the number of affected 

HPC rotor stage 2–5 spools. 

Additionally, we learned that we 

inadvertently omitted certain HPC rotor 

stage 2–5 spools from the applicability 

of AD 2017–07–04. This proposed AD 

would require removing certain HPC 

rotor stage 2–5 spools from service 

before reaching the new reduced life 

limit and replacing them with parts 

eligible for installation. We are 

proposing this AD to correct the unsafe 

condition on these products. 

DATES: We must receive comments on 

this proposed AD by August 9, 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: Deliver to Mail 

address above between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. 

For service information identified in 

this NPRM, contact General Electric 

Company, One Neumann Way, Room 

285, Cincinnati, OH; phone: 513–552– 

3272; email: geae.aoc@ge.com. You may 

view this service information at the 

FAA, Engine and Propeller Standards 

Branch, 1200 District Avenue, 


amozie on DSK3GDR082PROD with PROPOSALS1
Federal Register / Vol. 83, No. 122 / Monday, June 25, 2018 / Proposed Rules 29475 

Burlington, MA 01803. For information 

on the availability of this material at the 

FAA, call 781–238–7759. 

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– 

0406; 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 NPRM, the 

regulatory evaluation, any comments 

received, and other information. The 

street address for Docket Operations 

(phone: 800–647–5527) is listed above. 

Comments will be available in the AD 

docket shortly after receipt. 

FOR FURTHER INFORMATION CONTACT: 

David Bethka, Aerospace Engineer, ECO 

Branch, FAA, 1200 District Avenue, 

Burlington, MA 01803; phone: 781– 

238–7129; fax: 781–238–7199; email: 

david.bethka@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Comments Invited 

We invite you to send any written 

relevant data, views, or arguments about 

this proposed AD. Send your comments 

to an address listed under the 

ADDRESSES section. Include ‘‘Docket No. 

FAA–2018–0406; Product Identifier 

2013–NE–30–AD’’ at the beginning of 

your comments. We specifically invite 

comments on the overall regulatory, 

economic, environmental, and energy 

aspects of this NPRM. We will consider 

all comments received by the closing 

date and may amend this NPRM 

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 proposed AD. 

Discussion 

We issued AD 2017–07–04, 

Amendment 39–18842 (82 FR 16728, 

April 6, 2017), (‘‘AD 2017–07–04’’), for 

GE GE90–110B1 and GE90–115B 

turbofan engines with certain HPC rotor 

stage 2–5 spools installed. AD 2017–07– 

04 requires removing these spools from 

service at times determined by a 

drawdown plan. AD 2017–07–04 

resulted from reports of cracks in HPC 

rotor stage 2–5 spool aft spacer arms. 

We issued AD 2017–07–04 to prevent 

failure of a critical life-limited rotating 

engine part, which could result in an 

uncontained engine failure and damage 

to the airplane. 

Actions Since AD 2017–07–04 Was 

Issued 

Since we issued AD 2017–07–04, GE 

released GE SB GE90–100 SB 72–0714 

R01, dated February 16, 2018, for the 

HPC rotor stage 2–5 spools, which 

increases the number of affected parts. 

Additionally, GE and Boeing provided 

comments on AD–2017–07–04 that 

some HPC rotor stage 2–5 spools listed 

in AD 2013–24–17 (superseded by AD 

2017–07–04), were omitted from AD 

2017–07–04. 

Related Service Information Under 1 

CFR Part 51 

We reviewed GE SB GE90–100 SB 72– 

0499 R01, dated February 5, 2014; GE 

SB GE90–100 SB 72–0659 R01, dated 

February 18, 2016; and GE SB GE90–100 

SB 72–0714 R01, dated February 16, 

2018. 

GE SB GE90–100 SB 72–0499 R01 

describes procedures for identification 

and removal from service of HPC rotor 

stage 2–5 spools that use the original 

seal tooth coating process. GE SB GE90– 

100 SB 72–0659 R01 describes 

procedures for identification and 

removal from service of HPC rotor stage 

2–5 spools that use a modified seal 

tooth coating process. GE SB GE90–100 

SB 72–0714 R01 describes procedures 

for identification and removal from 

service of HPC rotor stage 2–5 spools 

that use the modified seal tooth coating 

process, without coating between the 

seal teeth. 

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 proposing 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. 

Proposed AD Requirements 

This proposed AD would retain all 

requirements of AD 2017–07–04. This 

proposed AD would require removing 

certain HPC rotor stage 2–5 spools from 

service at times specified in the required 

actions section. 

Costs of Compliance 

We estimate that this proposed AD 

affects 85 engines installed on airplanes 

of U.S. registry. 

We estimate the following costs to 

comply with this proposed AD: 

ESTIMATED COSTS

Action Labor cost Parts cost Cost per 

product 

Cost on U.S. 

operators 

Paragraph (g)(1) Spools Replacement ........... 0 work-hours × $85 per hour = $0 ................. $229,737 $229,737 $5,054,214 

Paragraph (g)(2) Spools Replacement ........... 0 work-hours × $85 per hour = $0 ................. 39,048 39,048 2,460,024 

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 

We have determined that this 

proposed AD would not have federalism 


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29476 Federal Register / Vol. 83, No. 122 / Monday, June 25, 2018 / Proposed Rules 

implications under Executive Order 

13132. This proposed AD would 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 the proposed regulation: 

(1) Is not a ‘‘significant regulatory 

action’’ under Executive Order 12866, 

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

the 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. 

The Proposed Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA proposes to amend 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 

removing Airworthiness Directive (AD) 

2017–07–04, Amendment 39–18842 (82 

FR 16728, April 6, 2017), and adding 

the following new AD: 

General Electric Company: Docket No. 

FAA–2018–0406; Product Identifier 2013– 

NE–30–AD. 

(a) Comments Due Date 

The FAA must receive comments on this 

AD action by August 9, 2018. 

(b) Affected ADs 

This AD replaces AD 2017–07–04, 

Amendment 39–18842 (82 FR 16728, April 6, 

2017) (‘‘AD 2017–07–04’’). 

(c) Applicability 

This AD applies to General Electric 

Company (GE) GE90–110B1 and GE90–115B 

turbofan engines with HPC rotor stage 2–5 

spools, with: 

(1) A serial number listed in either, 

paragraph 4, Appendix A of GE Service 

Bulletin (SB) No. GE90–100 SB 72–0499 R01, 

dated February 5, 2014, in paragraph 4, 

Appendix A of GE SB GE90–100 SB 72–0659 

R01, dated February 18, 2016, or in 

paragraph 4, Appendix A, of GE SB GE90– 

100 SB 72–0714 R01, dated February 16, 

2018. 

(2) A part number (P/N) 351–103–109–0, P/ 

N 351–103–110–0, P/N 351–103–147–0 or P/ 

N 351–103–152–0, with any serial number. 

(d) Subject 

Joint Aircraft System Component (JASC) 

Code 7230, Turbine Engine Compressor 

Section. 

(e) Unsafe Condition 

This AD was prompted by reports of cracks 

in HPC rotor stage 2–5 spool aft spacer arms. 

We are issuing this AD to prevent failure of 

the HPC rotor stage 2–5 spools. The unsafe 

condition, if not addressed, could result in 

uncontained spool release, 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) Remove from service HPC rotor stage 2– 

5 spools with serial numbers listed in 

paragraph 4, Appendix A, of GE SB GE90– 

100 SB 72–0659 R01, dated February 18, 

2016, as follows, or before further flight, 

whichever occurs later: 

(i) For spools with fewer than 4,500 flight 

CSN as of April 21, 2017, remove before 

exceeding 5,000 CSN. 

(ii) For spools with 4,500 CSN or more but 

fewer than 5,200 CSN as of April 21, 2017, 

remove within 500 CIS but not to exceed 

5,500 CSN. 

(iii) For spools with 5,200 CSN or more but 

fewer than 5,600 CSN as of April 21, 2017, 

remove within 300 CIS but not to exceed 

5,800 CSN. 

(iv) For spools with 5,600 CSN or more but 

fewer than 5,800 CSN as of April 21, 2017, 

remove within 200 CIS but not to exceed 

5,850 CSN. 

(v) For spools with 5,800 CSN or more but 

fewer than 6,000 CSN as of April 21, 2017, 

remove within 50 CIS but not to exceed 6,000 

CSN. 

(vi) For spools with 6,000 CSN or more as 

of April 21, 2017, remove before the next 

flight. 

(2) Remove from service HPC rotor stage 2– 

5 spools listed in paragraph (c)(2) of this AD 

and HPC rotor stage 2–5 spools with serial 

numbers listed in paragraph 4, Appendix A, 

of GE SB GE90–100 SB 72–0714 R01, dated 

February 16, 2018, before exceeding 8,200 

CSN, or before further flight, whichever 

occurs later. 

(h) Installation Prohibition 

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

not install or reinstall onto any engine, any 

HPC rotor stage 2–5 spool with a serial 

number listed in paragraph 4, Appendix A, 

of GE SB No. GE90–100 SB 72–0499 R01, 

dated February 5, 2014, or paragraph 4, 

Appendix A, of GE SB GE90–100 SB72–0659 

R01, dated February 18, 2016, that exceeds 

5,000 CSN. 

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

not install or reinstall onto any engine, any 

HPC rotor stage 2–5 spool listed in paragraph 

(c)(2) of this AD, or HPC rotor stage 2–5 spool 

with a serial number listed in paragraph 4, 

Appendix A, of GE SB GE90–100 SB 72–0714 

R01, dated February 16, 2018, that exceeds 

8,200 CSN. 

(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)(1) 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 

(1) For more information about this AD, 

contact David Bethka, Aerospace Engineer, 

ECO Branch, FAA, 1200 District Avenue, 

Burlington, MA 01803; phone: 781–238– 

7129; fax: 781–238–7199; email: 

david.bethka@faa.gov. 

(2) For service information identified in 

this AD, contact General Electric Company, 

One Neumann Way, Room 285, Cincinnati, 

OH; phone: 513–552–3272; email: geae.aoc@

ge.com. You may view this referenced 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. 

Issued in Burlington, Massachusetts, on 

June 19, 2018. 

Robert J. Ganley, 

Manager, Engine and Propeller Standards 

Branch, Aircraft Certification Service. 

[FR Doc. 2018–13444 Filed 6–22–18; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2018–0552; Product 

Identifier 2018–NM–049–AD] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

Defense and Space S.A. (Formerly 

Known as Construcciones 

Aeronauticas, S.A. (CASA)) Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 


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