This section of the FEDERAL REGISTER

contains notices to the public of the proposed

issuance of rules and regulations. The

purpose of these notices is to give interested

persons an opportunity to participate in the

rule making prior to the adoption of the final

rules.

Proposed Rules Federal Register

91880 

Vol. 81, No. 243 

Monday, December 19, 2016 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2015–7491; Directorate 

Identifier 2015–NE–39–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) 2016–13– 

05, which applies to all General Electric 

Company (GE) GE90–76B, GE90–77B, 

GE90–85B, GE90–90B, and GE90–94B 

turbofan engines. AD 2016–13–05 

requires eddy current inspection (ECI) 

of the high-pressure compressor (HPC) 

stage 8–10 spool at each shop visit for 

all affected engines and ECI or 

ultrasonic inspection (USI) for certain 

affected engines. Since we issued AD 

2016–13–05, we determined that the 

risk of the failure of an HPC stage 8–10 

spool was excessive without repetitive 

USI prior to shop visit. This proposed 

AD would require initial and repetitive 

on-wing USIs of the HPC stage 8–10 

spool for certain engines prior to shop 

visit and ECI of all affected engines at 

each shop visit. We are proposing this 

AD to correct the unsafe condition on 

these products. 

DATES: We must receive comments on 

this proposed AD by February 2, 2017. 

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, GE-Aviation, Room 285, 1 

Neumann Way, Cincinnati, OH 45215, 

phone: 513–552–3272; fax: 513–552– 

3329; email: geae.aoc@ge.com. You may 

view this service information at the 

FAA, Engine & Propeller Directorate, 

1200 District Avenue, Burlington, MA. 

For information on the availability of 

this material at the FAA, call 781–238– 

7125. 

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–2015– 

7491; or in person at the Docket 

Management Facility between 9 a.m. 

and 5 p.m., Monday through Friday, 

except Federal holidays. The AD docket 

contains this proposed AD, the 

regulatory evaluation, any comments 

received, and other information. The 

street address for the Docket Office 

(phone: 800–647–5527) is in the 

ADDRESSES section. Comments will be 

available in the AD docket shortly after 

receipt. 

FOR FURTHER INFORMATION CONTACT: John 

Frost, Aerospace Engineer, Engine 

Certification Office, FAA, Engine & 

Propeller Directorate, 1200 District 

Avenue, Burlington, MA 01803; phone: 

781–238–7756; fax: 781–238–7199; 

email: john.frost@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–2015–7491; Directorate Identifier 

2015–NE–39–AD’’ at the beginning of 

your comments. We specifically invite 

comments on the overall regulatory, 

economic, environmental, and energy 

aspects of this proposed AD. We will 

consider all comments received by the 

closing date and may amend this 

proposed AD 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 

On June 15, 2016, we issued AD 

2016–13–05, Amendment 39–18569 (81 

FR 41208, June 24, 2016; corrected 81 

FR 42475, June 30, 2016) (‘‘AD 2016– 

13–05’’), for GE GE90–76B, GE90–77B, 

GE90–85B, GE90–90B, and GE90–94B 

turbofan engines. AD 2016–13–05 

requires an ECI or USI of the HPC stage 

8–10 spool and removing from service 

those parts that fail inspection. AD 

2016–13–05 resulted from an 

uncontained failure of the HPC stage 8– 

10 spool, leading to an airplane fire. We 

issued AD 2016–13–05 to prevent 

failure of the HPC stage 8–10 spool, 

uncontained rotor release, damage to the 

engine, and damage to the airplane. 

Actions Since AD 2016–13–05 Was 

Issued 

We issued AD 2016–13–05 without 

including the repetitive USI prior to 

shop visit to expedite introduction of 

the corrective actions to the fleet. Since 

we issued AD 2016–13–05, we 

determined that a repetitive USI is 

required based on analysis that the risk 

of the failure of an HPC stage 8–10 spool 

is excessive without this inspection. 

Related Service Information 

We reviewed GE GE90 Service 

Bulletin (SB) SB 72–1151 R00, dated 

June 10, 2016. This SB describes 

procedures for an on-wing USI of the 

stage 8 web of the stage 8–10 spool. 

We also reviewed Chapter 72–31–08, 

Special Procedures 003; and Chapter 

72–00–31, Special Procedures 006, in 

the GE GE90 Engine Manual, 

GEK100700, Revision 68, dated 

September 1, 2016. These procedures 

describe how to perform ECI of the stage 

8 aft web of the stage 8–10 spool. 

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. 


sradovich on DSK3GMQ082PROD with PROPOSALS
Federal Register / Vol. 81, No. 243 / Monday, December 19, 2016 / Proposed Rules 91881 

Proposed AD Requirements 

This proposed AD would retain all 

the requirements of AD 2016–13–05. 

This proposed AD would also require 

repetitive USI of the HPC 8–10 spool. 

Interim Action 

We consider this proposed AD 

interim action. GE is determining the 

root cause for the unsafe condition 

identified in this proposed AD. Once a 

root cause is identified, we will 

consider additional rulemaking. 

Costs of Compliance 

We estimate that this proposed AD 

affects 54 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 

Inspection ......... 7 work-hours × $85 per hour = 

$595 per inspection cycle.

$0 $595 per inspection cycle ............. $32,130 per inspection cycle. 

We estimate the following costs to do 

any necessary replacements that would 

be required based on the results of the 

proposed inspection. We have no way of 

determining the number of engines that 

might need this replacement: 

ON-CONDITION COSTS

Action Labor cost Parts cost Cost per 

product 

Replacement of spool ................................................... 0 work-hours × $85 per hour = $0 ............................... $780,000 $780,000 

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. 

Regulatory Findings 

We have determined that this 

proposed AD would not have federalism 

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 to the extent that it justifies 

making a regulatory distinction, 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) 

2016–13–05, Amendment 39–18569 (81 

FR 41208, June 24, 2016; corrected 81 

FR 42475, June 30, 2016), and adding 

the following new AD: 

General Electric Company: Docket No. FAA– 

2015–7491; Directorate Identifier 2015– 

NE–39–AD. 

(a) Comments Due Date 

The FAA must receive comments on this 

AD action by February 2, 2017. 

(b) Affected ADs 

This AD replaces AD 2016–13–05, 

Amendment 39–18569 (81 FR 41208, June 

24, 2016; corrected 81 FR 42475, June 30, 

2016). 

(c) Applicability 

This AD applies to General Electric 

Company (GE) GE90–76B, GE90–77B, GE90– 

85B, GE90–90B, and GE90–94B turbofan 

engines with a high-pressure compressor 

(HPC) stage 8–10 spool, part numbers (P/Ns) 

1694M80G04, 1844M90G01, or 1844M90G02, 

installed. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 72, Engine General. 

(e) Unsafe Condition 

This AD was prompted by an uncontained 

failure of the HPC stage 8–10 spool. We are 

issuing this AD to prevent failure of the HPC 

stage 8–10 spool, uncontained rotor release, 

damage to the engine, and damage to the 

airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(1) For HPC stage 8–10 spool, P/N 

1694M80G04, all serial numbers (S/Ns), or 

HPC stage 8–10 spool, P/N 1844M90G01 or 

1844M90G02, with a S/N listed in Figure 1 

to paragraph (f) of this AD; perform an onwing ultrasonic inspection (USI) of the stage 

8 aft web upper face as follows: 

(i) Perform an initial USI after reaching 

8,000 cycles since new (CSN), but, before 

exceeding 9,000 CSN, or within 500 cycles in 


sradovich on DSK3GMQ082PROD with PROPOSALS
91882 Federal Register / Vol. 81, No. 243 / Monday, December 19, 2016 / Proposed Rules 

service after July 29, 2016, whichever occurs 

later. 

(ii) Thereafter, perform a USI of the stage 

8 aft web upper face every 500 cycles since 

last inspection. 

(iii) Compliance with paragraph (f)(2)(i) of 

this AD is terminating action for the initial 

and repetitive USIs specified by paragraphs 

(f)(1)(i) and (f)(1)(ii) of this AD. 

FIGURE 1 TO PARAGRAPH (f)—HPC STAGE 8–10 SPOOL S/NS

Part Nos. Serial Nos. 

1844M90G01 ...................................................................... GWN005MF GWNBK753 GWNBS077 GWNBS497 GWNBS724 

GWN005MG GWNBK754 GWNBS078 GWNBS499 GWNBS794 

GWN0087M GWNBK841 GWNBS079 GWNBS500 GWNBS810 

GWN0087N GWNBK842 GWNBS080 GWNBS501 GWNBS811 

GWN00DGK GWNBK843 GWNBS081 GWNBS502 GWNBS812 

GWN00DGL GWNBK844 GWNBS157 GWNBS609 GWNBS813 

GWNBJ992 GWNBK952 GWNBS158 GWNBS610 GWNBS814 

GWNBK667 GWNBK953 GWNBS159 GWNBS611 GWNBS910 

GWNBK674 GWNBK954 GWNBS160 GWNBS612 GWNBS911 

GWNBK675 GWNBK955 GWNBS266 GWNBS613 GWNBS912 

GWNBK743 GWNBK956 GWNBS267 GWNBS614 GWNBS914 

GWNBK744 GWNBK957 GWNBS268 GWNBS721 GWNBS915 

GWNBK751 GWNBK958 GWNBS269 GWNBS722 GWNBS982 

GWNBK752 GWNBK959 GWNBS270 GWNBS723 GWNBS983 

1844M90G02 ...................................................................... GWN00C2T GWN01C5N GWN02N8D GWN03RTM GWN04E21 

GWN00C2V GWN01GE2 GWN02T3R GWN03RTP GWN04GHT 

GWN00G2N GWN01GE3 GWN02WGM GWN040RL GWN04GHW 

GWN00G2P GWN01GE4 GWN0311K GWN040RM GWN04GJ0 

GWN00PFP GWN01GE6 GWN035PP GWN040RN GWN04JW6 

GWN00PFR GWN01WH1 GWN038TD GWN040RP GWN04JW7 

GWN00T2N GWN02688 GWN039TG GWN04202 GWN04JW8 

GWN00YHV GWN02689 GWN03G2R GWN0435W GWN04L7K 

GWN0125G GWN0268A GWN03G2W GWN04360 GWN04L7L 

GWN0125H GWN02DP2 GWN03G30 GWN04361 GWN04MT7 

GWN0166K GWN02DP3 GWN03JPC GWN04362 GWN04MT8 

GWN01C5K GWN02F9F GWN03JPD GWN04ATG GWNBS984 

GWN01C5L GWN02F9G GWN03N8P GWN04ATH 

GWN01C5M GWN02L9T GWN03N8R GWN04E20 

(2) For all HPC stage 8–10 spools, P/N 

1694M80G04, 1844M90G01, or 1844M90G02, 

perform an eddy current inspection (ECI) of 

the stage 8 aft upper face as follows: 

(i) Perform an initial ECI of the stage 8 aft 

web upper face at the next shop visit after the 

effective date of this AD. 

(ii) Thereafter, perform an ECI of the stage 

8 aft web upper face at each subsequent shop 

visit. 

(3) Remove from service any HPC stage 8– 

10 spool that fails the inspection required by 

paragraphs (f)(1) or (f)(2) of this AD, and 

replace with a spool eligible for installation. 

(g) Definition 

For the purpose of this AD, an engine shop 

visit is the induction of an engine into the 

shop for maintenance during which the 

compressor discharge pressure seal face is 

exposed. 

(h) Alternative Methods of Compliance 

(AMOCs) 

The Manager, Engine Certification Office, 

FAA, may approve AMOCs for this AD. Use 

the procedures found in 14 CFR 39.19 to 

make your request. You may email your 

request to: ANE-AD-AMOC@faa.gov. 

(i) Related Information 

(1) For more information about this AD, 

contact John Frost, Aerospace Engineer, 

Engine Certification Office, FAA, 1200 

District Avenue, Burlington, MA 01803; 

phone: 781–238–7756; fax: 781–238–7199; 

email: john.frost@faa.gov. 

(2) GE GE90 Service Bulletin (SB) SB 72– 

1151 R00, dated June 10, 2016, and Chapter 

72–31–08, Special Procedures 003, and 

Chapter 72–00–31, Special Procedures 006, 

in GE GE90 Engine Manual, GEK100700, 

Revision 68, dated September 1, 2016, can be 

obtained from GE using the contact 

information in paragraph (i)(3) of this AD. 

This SB describes procedures for an on-wing 

USI of the stage 8 web of the stage 8–10 

spool. These engine manual procedures 

describe how to perform ECI of the stage 8 

aft web of the stage 8–10 spool. 

(3) For service information identified in 

this proposed AD, contact General Electric 

Company, GE-Aviation, Room 285, 1 

Neumann Way, Cincinnati, OH 45215, 

phone: 513–552–3272; fax: 513–552–3329; 

email: geae.aoc@ge.com. 

(4) You may view this service information 

at the FAA, Engine & Propeller Directorate, 

1200 District Avenue, Burlington, MA. For 

information on the availability of this 

material at the FAA, call 781–238–7125. 

(j) Material Incorporated by Reference 

None. 

Issued in Burlington, Massachusetts, on 

November 29, 2016. 

Colleen M. D’Alessandro, 

Manager, Engine & Propeller Directorate, 

Aircraft Certification Service. 

[FR Doc. 2016–29679 Filed 12–16–16; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2016–9393; Directorate 

Identifier 2014–NM–199–AD] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to supersede 

Airworthiness Directive (AD) 2013–13– 

16, which applies to all Airbus Model 

A330–200, A330–200 Freighter, A330– 

300 series airplanes, and all Airbus 

Model A340–200, –300, –500, and –600 

series airplanes. AD 2013–13–16 

currently requires repetitive inspections 

for discrepancies of the ball-screw 

assembly of the trimmable horizontal 

stabilizer actuator (THSA), repetitive 

greasing of the THSA ball-nut, and 

replacement of the THSA if necessary; 

and modification or replacement (as 

applicable) of the ball-nut assembly, 


sradovich on DSK3GMQ082PROD with PROPOSALS