Federal Register / Vol. 80, No. 61 / Tuesday, March 31, 2015 / Proposed Rules 17003 

view this 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 March 

19, 2015. 

Jeffrey E. Duven, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2015–07172 Filed 3–30–15; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2015–0679; Directorate 

Identifier 2013–NM–182–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) 2012–13– 

06, for all Airbus Model A300 series 

airplanes and all Model A300 B4–600, 

B4–600R, and F4–600R series airplanes, 

and Model A300 C4–605R Variant F 

airplanes (collectively called Model 

A300–600 series airplanes). AD 2012– 

13–06 currently requires a one-time 

detailed inspection to determine the 

length of the fire shut-off valve (FSOV) 

bonding leads and for contact or chafing 

of the wires, and corrective actions if 

necessary. Since we issued AD 2012– 

13–06, a determination was made that 

the description of the inspection area 

specified in the service information was 

misleading; therefore, some operators 

might have inspected incorrect bonding 

leads. This proposed AD would instead 

require a new one-time detailed 

inspection of the FSOV bonding leads to 

ensure that the correct bonding leads are 

inspected, and corrective action if 

necessary. We are proposing this AD to 

detect and correct contact or chafing of 

wires and the bonding leads, which, if 

not detected, could be a source of sparks 

in the wing trailing edge, and could lead 

to an uncontrolled engine fire. May 5, 

2015. 

DATES: We must receive comments on 

this proposed AD by May 15, 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 service information identified in 

this proposed AD, contact Airbus SAS, 

Airworthiness Office—EAW, 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. 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–2015–0679; 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: Dan 

Rodina, Aerospace Engineer, 

International Branch, ANM–116, 

Transport Airplane Directorate, FAA, 

1601 Lind Avenue SW., Renton, WA 

98057–3356; telephone 425–227–2125; 

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–2015–0679; Directorate Identifier 

2013–NM–182–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://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 21, 2012, we issued AD 

2012–13–06, Amendment 39–17108 (77 

FR 40485, July 10, 2012). AD 2012–13– 

06 requires actions intended to address 

an unsafe condition on all Airbus Model 

A300 series airplanes and all Model 

A300 B4–600, B4–600R, and F4–600R 

series airplanes, and Model A300 C4– 

605R Variant F airplanes (collectively 

called Model A300–600 series 

airplanes). 

Since we issued AD 2012–13–06, the 

European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Union, has issued EASA Airworthiness 

Directive 2013–0204, dated September 

6, 2013 (referred to after this as the 

Mandatory Continuing Airworthiness 

Information, or ‘‘the MCAI’’), to correct 

an unsafe condition for the specified 

products. The MCAI states: 

During a scheduled maintenance check, 

one operator reported inoperative Fire Shut 

Off Valve (FSOV). Investigations showed 

damage at wire located between engine 2 

hydraulic FSOV and wing rear spar, in the 

zones 575/675, and at bonding lead, located 

between wing rib 7A and rib 8 below 

hydraulic pressure lines. 

Similar inspections on different aeroplanes 

have shown that one of the causes of damage 

is the contact between bonding lead and the 

harness, due to over length of the bonding 

lead. 

This condition, if not detected and 

corrected, could lead to either: 

—a potential explosive condition onground if the FSOV, that is installed in fuel 

vapor zone is commanded to close position, 

or 

—a temporary uncontrolled engine fire, if 

combined with a fire event in the nacelle fed 

by an hydraulic leakage and not controlled 

by the fire extinguishing system. 

As the affected wire is not powered during 

normal operation, no defect can be detected 

unless a test is performed on the FSOV 

during maintenance check. 

EASA issued AD 2011–0084 [http://ad.

easa.europa.eu/blob/easa_ad_2011_

0084.pdf/AD_2011–0084_Superseded] which 

required a one-time [detailed] inspection of 

the wires [for contact or chafing] located 

between [LH/RH] engines hydraulic FSOV 

and wing rear spar in the zones 575/675, and 

the bonding lead [for length] that is located 

between rib 7A and rib 8 below hydraulic 

pressure lines, and corrective actions [repair 

of wires or replacement of bonding leads] 

depending on findings. 

It appeared that the original issue of the 

Airbus inspection Service Bulletins (SB’s) as 


asabaliauskas on DSK5VPTVN1PROD with PROPOSALS
17004 Federal Register / Vol. 80, No. 61 / Tuesday, March 31, 2015 / Proposed Rules 

well as EASA AD 2011–0084 might have 

caused possible misunderstandings on the 

exact bonding leads and wires that are 

required to be inspected. 

For the reasons described above, this 

[EASA] AD retains the requirements of EASA 

AD 2011–0084, which is superseded, and 

requires additional work on aeroplanes that 

have already been inspected in accordance 

with the instructions of the original issue of 

the SB’s. 

You may examine the MCAI in the 

AD docket on the Internet at http://

www.regulations.gov by searching for 

and locating Docket No. FAA–2015– 

0679. 

Related Service Information Under 1 

CFR Part 51 

Airbus has issued Service Bulletin 

A300–24–0106, Revision 01, including 

Appendices 01, 02, 03, and 04, dated 

March 26, 2013 (for Model A300 series 

airplanes); and Service Bulletin A300– 

24–6108, Revision 01, including 

Appendices 01, 02, 03, and 04, dated 

March 26, 2013 (for Model A300–600 

series airplanes. The actions described 

in this service information are intended 

to correct the unsafe condition 

identified in the MCAI. This service 

information is reasonably available; see 

ADDRESSES for ways to access this 

service information. 

FAA’s Determination and Requirements 

of This Proposed AD 

This product has been approved by 

the aviation authority of another 

country, and is approved for operation 

in the United States. Pursuant to our 

bilateral agreement with the State of 

Design Authority, we have been notified 

of the unsafe condition described in the 

MCAI and service information 

referenced above. We are proposing this 

AD because we evaluated all pertinent 

information and determined an unsafe 

condition exists and is likely to exist or 

develop on other products of these same 

type designs. 

Costs of Compliance 

We estimate that this proposed AD 

affects 123 airplanes of U.S. registry. 

We estimate that it would take about 

8 work-hours per product to comply 

with the basic requirements of this 

proposed AD. The average labor rate is 

$85 per work-hour. Required parts 

would cost about $500 per product. 

Based on these figures, we estimate the 

cost of this proposed AD on U.S. 

operators to be $145,140, or $1,180 per 

product. 

In addition, we estimate that any 

necessary follow-on actions would take 

about 1 work-hour and require parts 

costing $50, for a cost of $135 per 

product. We have no way of 

determining the number of products 

that may need these actions. 

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; 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) 

2012–13–06, Amendment 39–17108 (77 

FR 40485, July 10, 2012), and adding the 

following new AD: 

Airbus: Docket No. FAA–2015–0679; 

Directorate Identifier 2013–NM–182–AD. 

(a) Comments Due Date 

We must receive comments by May 15, 

2015. 

(b) Affected ADs 

This AD replaces AD 2012–13–06, 

Amendment 39–17108 (77 FR 40485, July 10, 

2012). 

(c) Applicability 

This AD applies to the airplanes specified 

in paragraphs (c)(1), (c)(2), and (c)(3) of this 

AD, certificated in any category, all 

certificated models; all manufacturer serial 

numbers. 

(1) Airbus Model A300 B2–1A, B2–1C, 

B2K–3C, B2–203, B4–2C, B4–103, and B4– 

203 airplanes. 

(2) Airbus Model A300 B4–601, B4–603, 

B4–620, B4–622, B4–605R, B4–622R, F4– 

605R, and F4–622R airplanes. 

(3) Airbus Model A300 C4–605R Variant F 

airplanes. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 24, Electrical Power. 

(e) Reason 

This AD was prompted by a determination 

that the description of the inspection area 

specified in the service information was 

misleading; therefore, some operators might 

have inspected incorrect bonding leads. We 

are issuing this AD to detect and correct 

contact or chafing of wires and the bonding 

leads, which, if not detected, could be a 

source of sparks in the wing trailing edge, 

and could lead to an uncontrolled engine 

fire. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Inspection of the Fire Shut-off Valve 

(FSOV) Bonding Leads 

At the applicable time specified in 

paragraph (g)(1) or (g)(2) of this AD: Do a onetime detailed inspection to determine the 

length of the FSOV bonding leads, and to 

detect contact or chafing of the wires located 

on the left-hand (LH) and right-hand (RH) 

sides of the wing rear spar, in accordance 

with the Accomplishment Instructions of 

Airbus Service Bulletin A300–24–0106, 

Revision 01, including Appendices 01, 02, 

03, and 04, dated March 26, 2013 (for Model 

A300 series airplanes); or Airbus Service 

Bulletin A300–24–6108, Revision 01, 

including Appendices 01, 02, 03, and 04, 

dated March 26, 2013 (for Model A300–600 

series airplanes); as applicable. 

(1) For airplanes on which the inspection 

required by paragraph (g) of AD 2012–13–06, 


asabaliauskas on DSK5VPTVN1PROD with PROPOSALS
Federal Register / Vol. 80, No. 61 / Tuesday, March 31, 2015 / Proposed Rules 17005 

Amendment 39–17108 (77 FR 40485, July 10, 

2012), has not been done as of the effective 

date of this AD: Inspect within 4,500 flight 

hours or 30 months after August 14, 2012 

(the effective date of AD 2012–13–06), 

whichever occurs first. 

(2) For airplanes on which the inspection 

required by paragraph (g) of AD 2012–13–06, 

Amendment 39–17108 (77 FR 40485, July 10, 

2012), has been done as of the effective date 

of this AD: Inspect within 4,500 flight hours 

or 30 months after the effective date of this 

AD, whichever occurs first. 

(h) Corrective Action for FSOV Bonding 

Leads 

If, during the inspection required by 

paragraph (g) of this AD, the length of the 

bonding lead(s) is more than 80 millimeters 

(mm) (3.15 inches): Before further flight, 

replace the bonding lead(s) with a new 

bonding lead having a length equal to 80 mm 

± 2 mm (3.15 inches) ± 0.08 inch, in 

accordance with the Accomplishment 

Instructions of the applicable service 

information identified in paragraph (g) of this 

AD. 

(i) Repair of the Wires of the LH and RH 

Sides 

If, during the inspection required by 

paragraph (g) of this AD, any contact or 

chafing of the wires is found, repair the wires 

before further flight, in accordance with the 

Accomplishment Instructions of the 

applicable service information identified in 

paragraph (g) of this AD. 

(j) Parts Installation Prohibition 

As of August 14, 2012 (the effective date 

of AD 2012–13–06, Amendment 39–17108 

(77 FR 40485, July 10, 2012), no person may 

install any bonding lead longer than 80 mm 

± 2 mm (3.15 inches) ± 0.08 inch, located 

between the LH/RH engine hydraulic FSOV 

and wing rear spar in zones 575/675 on any 

airplane. 

(k) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, International 

Branch, ANM–116, Transport Airplane 

Directorate, 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 International Branch, send it to ATTN: 

Dan Rodina, Aerospace Engineer, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA, 1601 Lind 

Avenue SW., Renton, WA 98057–3356; 

telephone 425–227–2125; fax 425–227–1149. 

Information may be emailed to: 9-ANM-116- 

AMOC-REQUESTS@faa.gov. 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. The AMOC approval letter 

must specifically reference this AD. 

(2) Contacting the Manufacturer: As of the 

effective date of this AD, for any requirement 

in this AD to obtain corrective actions from 

a manufacturer, the action must be 

accomplished using a method approved by 

the Manager, International Branch, ANM– 

116, Transport Airplane Directorate, FAA; or 

the European Aviation Safety Agency 

(EASA); or Airbus’s EASA Design 

Organization Approval (DOA). If approved by 

the DOA, the approval must include the 

DOA-authorized signature. 

(l) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) EASA 

Airworthiness Directive 2013–0204, dated 

September 6, 2013, for related information. 

This MCAI may be found in the AD docket 

on the Internet at http://www.regulations.gov 

by searching for and locating Docket No. 

FAA–2015–0679. 

(2) For service information identified in 

this AD, contact Airbus SAS, Airworthiness 

Office—EAW, 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. 

You may view this 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 March 

24, 2015. 

Michael Kaszycki, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2015–07280 Filed 3–30–15; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2015–0677; Directorate 

Identifier 2013–NM–244–AD] 

RIN 2120–AA64 

Airworthiness Directives; Gulfstream 

Aerospace Corporation Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to adopt a new 

airworthiness directive (AD) for all 

Gulfstream Aerospace Corporation 

Model GVI airplanes. This proposed AD 

was prompted by reports of corrosion on 

in-service air non-return valves. This 

proposed AD would require a revision 

to the Emergency Procedures section of 

the airplane flight manual (AFM). This 

proposed AD would also require a 

revision to the maintenance or 

inspection program, as applicable, to 

incorporate airworthiness limitations for 

the high pressure (HP) Stage 5 air nonreturn valves. We are proposing this AD 

to ensure the flightcrew is provided 

with procedures to mitigate the risks 

associated with failure of the HP Stage 

5 air non-return valve. Failure of the HP 

Stage 5 air non-return valve in the open 

position could result in engine 

instability and uncommanded in-flight 

shutdown. 

DATES: We must receive comments on 

this proposed AD by May 15, 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 Gulfstream 

Aerospace Corporation, Technical 

Publications Dept., P.O. Box 2206, 

Savannah, GA 31402–2206; telephone 

800–810–4853; fax 912–965–3520; email 

pubs@gulfstream.com; Internet http://

www.gulfstream.com/product_support/

technical_pubs/pubs/index.htm. You 

may view this 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– 

0677; 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: Eric 

Potter, Aerospace Engineer, Propulsion 

and Services Branch, ACE–118A, 

Atlanta Aircraft Certification Office, 

FAA, 1701 Columbia Avenue, College 

Park, GA 30337; phone: 404–474–5583; 


asabaliauskas on DSK5VPTVN1PROD with PROPOSALS