Federal Register / Vol. 80, No. 205 / Friday, October 23, 2015 / Proposed Rules 64373 

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 adding 

the following new airworthiness 

directive (AD): 

Airbus: Docket No. FAA–2015–4204; 

Directorate Identifier 2015–NM–001–AD. 

(a) Comments Due Date 

We must receive comments by December 7, 

2015. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to the Airbus airplanes 

specified in paragraphs (c)(1), (c)(2), (c)(3), 

and (c)(4) of this AD; certificated in any 

category; modified by Simmonds Precision 

Products, Inc., supplemental type certificate 

(STC) ST00092BO (http://rgl.faa.gov/

Regulatory_and_Guidance_Library/rgstc.nsf/

0/D41C5AE8E46B4901862v574900069E004

?OpenDocument&Highlight=st00092bo). 

(1) Model A300 B4–601, B4–603, B4–620, 

and B4–622 airplanes. 

(2) Model A300 B4–605R and B4–622R 

airplanes. 

(3) Model A300 F4–605R and F4–622R 

airplanes. 

(4) Model A300 C4–605R Variant F 

airplanes. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 28, Fuel. 

(e) Reason 

This AD was prompted by a report of 

chafing found on the overflow sensor harness 

of the surge tank, and subsequent contact 

between the electrical wiring and fuel tank 

structure. We are issuing this AD to prevent 

chafing of the harness and subsequent 

contact between the electrical wiring and fuel 

tank structure, which could result in 

electrical arcing and a fuel tank explosion. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) One-Time Inspection and Repair 

Within 12 months after the effective date 

of this AD: Do the actions required by 

paragraphs (g)(1), (g)(2), and (g)(3) of this AD, 

in accordance with the Accomplishment 

Instructions of UTC Aerospace Systems 

Service Bulletin 300723–28–03 (V–1577), 

Revision 01, dated July 20, 2015. 

(1) Perform a one-time general visual 

inspection for damage of the outer tank 

sensor harness, and if any damage is found 

on the expando sleeving, before further flight, 

do a detailed inspection of the underlying 

wires for exposed conductor wires. If any 

exposed conductor wire is found, before 

further flight, replace the outer wing harness 

assembly. 

(2) Install new brackets and re-route the 

surge tank overflow sensor harness. 

(3) Modify the harness protection. 

(h) Credit for Previous Actions 

This paragraph provides credit for actions 

required by paragraph (g) of this AD, if those 

actions were performed before the effective 

date of this AD using UTC Aerospace 

Systems Service Bulletin 300723–28–03 (V– 

1577), dated October 10, 2014. This service 

information is not incorporated by reference 

in this AD. 

(i) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Boston Aircraft 

Certification Office (ACO) ANE–150, 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 ACO, send it 

to the attention of the person identified in 

paragraph (j)(1) of this AD. 

(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 Marc Ronell, Aerospace Engineer, 

Boston ACO, FAA, 12 New England 

Executive Park, Burlington, MA 01803; 

phone: 781–238–7776; fax: 781–238–7170; 

email: marc.ronell@faa.gov. 

(2) For service information identified in 

this AD, contact Simmonds Precision 

Products, Inc., A UTC Aerospace Company, 

100 Panton Road, Vergennes, Vermont 05491; 

phone 802–877–2911; fax 802–877–4444; 

Internet http://www.utcaerospace

systems.com. You may view this referenced 

service information at the FAA, Transport 

Airplane Directorate, 1601 Lind Avenue SW., 

Renton, WA. For information on the 

availability of this material at the FAA, call 

425–227–1221. 

Issued in Renton, Washington, on October 

15, 2015. 

Jeffrey E. Duven, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2015–26691 Filed 10–22–15; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2015–3713; Directorate 

Identifier 2015–NE–23–AD] 

RIN 2120–AA64 

Airworthiness Directives; Engine 

Alliance Turbofan Engines 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to adopt a new 

airworthiness directive (AD) for certain 

Engine Alliance (EA) GP7270 turbofan 

engines. This proposed AD was 

prompted by reports of the installation 

of non-conforming honeycomb seals in 

the high-pressure compressor (HPC) 

adjacent to the HPC rotor stage 2 to 5 

spool and stage 7 to 9 spool. This 

proposed AD would require removal 

and replacement of the affected HPC 

rotor stage 2 to 5 and stage 7 to 9 spools. 

We are proposing this AD to prevent 

failure of the HPC rotor stage 2 to 5 and 

stage 7 to 9 spools, which could lead to 

uncontained engine failure and damage 

to the airplane. 

DATES: We must receive comments on 

this proposed AD by December 22, 

2015. 

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 proposed AD, contact Engine 

Alliance, 400 Main St., East Hartford, 

CT 06108, M/S 169–10, phone: 800– 

565–0140; email: help24@pw.utc.com; 

mstockstill on DSK4VPTVN1PROD with PROPOSALS

64374 Federal Register / Vol. 80, No. 205 / Friday, October 23, 2015 / Proposed Rules 

Web site: 

www.engineallianceportal.com. You 

may view this service information at the 

FAA, Engine & Propeller Directorate, 12 

New England Executive Park, 

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– 

3713; 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: 

Martin Adler, Aerospace Engineer, 

Engine & Propeller Directorate, FAA, 12 

New England Executive Park, 

Burlington, MA 01803; phone: 781– 

238–7157; fax: 781–238–7199; email: 

martin.adler@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Comments Invited 

We invite you to send any written 

relevant data, views, or arguments about 

this proposal. Send your comments to 

an address listed under the ADDRESSES

section. Include ‘‘Docket No. FAA– 

2015–3713; Directorate Identifier 2015– 

NE–23–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 

We learned from the manufacturer 

that non-conforming honeycomb seals 

were installed in the affected HPCs 

adjacent to the HPC rotor stage 2 to 5 

spools and stage 7 to 9 spools. The 

honeycomb seals in the HPC were 

machined to an incorrect radial height 

which resulted in reduced clearances 

between the honeycomb and the 

rotating spools. This error could lead to 

cracks on the spools prior to reaching 

their full life. This condition, if not 

corrected, could result in failure of the 

HPC rotor stage 2 to 5 and stage 7 to 9 

spools, which could lead to 

uncontained engine failure, and damage 

to the airplane. 

Relevant Service Information Under 1 

CFR Part 51 

Engine Alliance has issued EA 

Service Bulletin (SB) No. EAGP7–72– 

327, dated July 21, 2015; and SB No. 

EAGP7–72–328, dated July 21, 2015. 

The SBs describe procedures for 

removal and replacement of HPC rotor 

stage 2 to 5 spools and HPC rotor stage 

7 to 9 spools, respectively. 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 of this 

document. 

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 require 

removal and replacement of the affected 

HPC rotor stage 2 to 5 and stage 7 to 9 

spools. 

Costs of Compliance 

We estimate that this proposed AD 

affects zero engines installed on 

airplanes of U.S. registry. The average 

labor rate is $85 per hour. Based on 

these figures, we estimate the cost of 

this proposed AD on U.S. operators to 

be $0. 

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 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 this 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 adding 

the following new airworthiness 

directive (AD): 

Engine Alliance: Docket No. FAA–2015– 

3713; Directorate Identifier 2015–NE– 

23–AD. 

(a) Comments Due Date 

We must receive comments by December 

22, 2015. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to Engine Alliance (EA) 

GP7270 turbofan engines with one or both of 

the following installed: 

mstockstill on DSK4VPTVN1PROD with PROPOSALS

Federal Register / Vol. 80, No. 205 / Friday, October 23, 2015 / Proposed Rules 64375 

(1) A high-pressure compressor (HPC) rotor 

stage 2 to 5 spool, part number (P/N) 382– 

104–807–0, with a serial number (S/N) listed 

in EA Service Bulletin (SB) No. EAGP7–72– 

327, dated July 21, 2015; or 

(2) an HPC rotor stage 7 to 9 spool, P/N 

2031M90G04, 2031M90G05, or 2031M90G07, 

with an S/N listed in EA SB No. EAGP7–72– 

328, dated July 21, 2015. 

(d) Unsafe Condition 

This AD was prompted by reports of the 

installation of non-conforming honeycomb 

seals in the HPC adjacent to the HPC rotor 

stage 2 to 5 spool and stage 7 to 9 spool. We 

are issuing this AD to prevent failure of the 

HPC rotor stage 2 to 5 spools and stage 7 to 

9 spools, which could lead to uncontained 

engine failure and damage to the airplane. 

(e) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. Within 30 days after the effective date 

of this AD or before accumulating 2,100 

engine cycles since the last disassembly of 

the compressor module of the engine, 

whichever occurs later: 

(1) For engines with an HPC rotor stage 2 

to 5 spool, P/N 382–104–807–0, installed 

with a S/N listed in EA SB No. EAGP7–72– 

327, dated July 21, 2015, do the following: 

(i) Remove the HPC rotor stage 2 to 5 spool 

from service and replace with a part eligible 

for installation. 

(ii) Remove and replace the honeycomb 

seals on the HPC stage 5 vanes. 

(2) For engines with an HPC rotor stage 7 

to 9 spool, P/N 2031M90G04, 2031M90G05, 

or 2031M90G07 installed with an S/N listed 

in EA SB No. EAGP7–72–328, dated July 21, 

2015, do the following: 

(i) Remove the HPC rotor stage 7 to 9 spool 

from service and replace with a part eligible 

for installation. 

(ii) Remove and replace the honeycomb 

seals on the HPC stage 6, stage 7, and stage 

8 vanes. 

(f) Alternative Methods of Compliance 

(AMOCs) 

The Manager, Engine Certification Office, 

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. 

(g) Related Information 

(1) For more information about this AD, 

contact Martin Adler, Aerospace Engineer, 

Engine & Propeller Directorate, FAA, 12 New 

England Executive Park, Burlington, MA 

01803; phone: 781–238–7157; fax: 781–238– 

7199; email: martin.adler@faa.gov. 

(2) EA SBs No. EAGP7–72–327, dated July 

21, 2015; and No. EAGP7–72–328, dated July 

21, 2015 can be obtained from EA using the 

contact information in paragraph (g)(3) of this 

proposed AD. 

(3) For service information identified in 

this AD, contact Engine Alliance, 400 Main 

St., East Hartford, CT 06108, M/S 169–10, 

phone: 800–565–0140; email: help24@

pw.utc.com; Web site: 

www.engineallianceportal.com. 

(4) You may view this service information 

at the FAA, Engine & Propeller Directorate, 

12 New England Executive Park, Burlington, 

MA. For information on the availability of 

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

Issued in Burlington, Massachusetts, on 

October 16, 2015. 

Colleen M. D’Alessandro, 

Directorate Manager, Engine & Propeller 

Directorate, Aircraft Certification Service. 

[FR Doc. 2015–26755 Filed 10–22–15; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2015–4202; Directorate 

Identifier 2014–NM–016–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) 2012–18– 

12, for certain Airbus Model A318, 

A319, and A320 series airplanes. AD 

2012–18–12 currently requires 

modifying the off-wing escape slide 

(OWS) enclosures on the left-hand (LH) 

side and right-hand (RH) side of the 

fuselage. Since we issued AD 2012–18– 

12, we have received reports that 

additional OWS part numbers have been 

affected. This proposed AD would 

retain the requirements of AD 2012–18– 

12 and expand the applicability to all 

Airbus Model A318, A319, and A320 

series airplanes. We are proposing this 

AD to prevent off-wing exits on the LH 

and RH sides of the fuselage from 

becoming inoperative, which, during an 

emergency, could impair the safe 

evacuation of occupants, possibly 

resulting in personal injuries. 

DATES: We must receive comments on 

this proposed AD by December 7, 2015. 

ADDRESSES: You may send comments 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, between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. 

For Airbus service information 

identified in this proposed AD, contact 

Airbus, Airworthiness Office—EIAS, 1 

Rond Point Maurice Bellonte, 31707 

Blagnac Cedex, France; telephone +33 5 

61 93 36 96; fax +33 5 61 93 44 51; email 

account.airworth-eas@airbus.com; 

Internet http://www.airbus.com. For Air 

Cruisers service information identified 

in this proposed AD, contact Air 

Cruisers Company, Cage Code 70167, 

1747 State Route 34, Wall Township, NJ 

07727–3935; telephone 732–681–3527; 

fax 732–681–9163; Internet http://www.

zodiacaerospace.com/en/our-activities/

aerosafety/zodiac-evacuation-systems. 

You may view this referenced service 

information at the FAA, Transport 

Airplane Directorate, 1601 Lind Avenue 

SW., Renton, WA. For information on 

the availability of this material at the 

FAA, call 425–227–1221. 

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– 

4202; 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 Operations 

office (telephone 800–647–5527) is in 

the ADDRESSES section. Comments will 

be available in the AD docket shortly 

after receipt. 

FOR FURTHER INFORMATION CONTACT: 

Sanjay Ralhan, Aerospace Engineer, 

International Branch, ANM–116, 

Transport Airplane Directorate, FAA, 

1601 Lind Avenue SW., Renton, WA 

98057–3356; telephone 425–227–1405; 

fax 425–227–1149. 

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–2015–4202; Directorate Identifier 

2014–NM–016–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 based on those comments. 

We will post all comments we 

receive, without change, to http://

mstockstill on DSK4VPTVN1PROD with PROPOSALS