Federal Register / Vol. 76, No. 193 / Wednesday, October 5, 2011 / Proposed Rules 61641 

Certification Maintenance Requirements 

Document TM–CMR–010793–ALL, Revision 

13, dated April 30, 2007; and 328 Support 

Services Dornier 328JET Certification 

Maintenance Requirements Document TM– 

CMR–010599–ALL, Revision 2, dated May 1, 

2007; for related information. 

Issued in Renton, Washington, on 

September 22, 2011. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2011–25580 Filed 10–4–11; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2011–0998; Directorate 

Identifier 2011–NM–046–AD] 

RIN 2120–AA64 

Airworthiness Directives; Airbus Model 

A319–111, –112, and –132 Airplanes; 

Model A320–111, –211, –212, –214 and 

–232 Airplanes; and Model A321–111, 

–211, –212, and –231 Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to adopt a new 

airworthiness directive (AD) for the 

products listed above. This proposed 

AD results from mandatory continuing 

airworthiness information (MCAI) 

originated by an aviation authority of 

another country to identify and correct 

an unsafe condition on an aviation 

product. The MCAI describes the unsafe 

condition as: 

Cases of corrosion findings have been 

reported on the overwing refueling aperture 

(used to fill the fuel tank by gravity) on the 

wing top skin. * * * 

* * * * * 

This condition, if not corrected, could, in 

combination with a lightning strike in this 

area, create a source of ignition in a fuel tank, 

possibly resulting in a fire or explosion and 

consequent loss of the aeroplane. 

* * * * * 

The proposed AD would require actions 

that are intended to address the unsafe 

condition described in the MCAI. 

DATES: We must receive comments on 

this proposed AD by November 21, 

2011. 

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 W12–40, 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, 

Airworthiness Office—EAS, 1 Rond 

Point Maurice Bellonte, 31707 Blagnac 

Cedex, France; telephone +33 5 61 93 36 

96; fax +33 5 61 93 44 51; e-mail: 

account.airworth-eas@airbus.com; 

Internet http://www.airbus.com. You 

may review copies of the referenced 

service information at the FAA, 

Transport Airplane Directorate, 1601 

Lind Avenue, SW., Renton, Washington. 

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; or in person at the 

Docket Operations office 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, 

Washington 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–2011–0998; Directorate Identifier 

2011–NM–046–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 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Community, has issued EASA 

Airworthiness Directive 2011–0034, 

dated March 2, 2011 (referred to after 

this as ‘‘the MCAI’’), to correct an unsafe 

condition for the specified products. 

The MCAI states: 

Cases of corrosion findings have been 

reported on the overwing refueling aperture 

(used to fill the fuel tank by gravity) on the 

wing top skin. The reported corrosion was on 

the mating surface of the aperture flange, 

underneath the refuel adaptor. Corrosion 

findings have been repaired on a case by case 

basis in accordance with approved data. 

For certain aeroplanes (identified by MSN 

in the applicability section of this AD), the 

provided repair contained instructions to 

apply primer coating on the mating surface. 

Since doing those repairs, it has been found 

that this primer coating may prevent proper 

electrical bonding provision between the 

overwing refuelling cap adaptor and the wing 

skin. 

This condition, if not corrected, could, in 

combination with a lightning strike in this 

area, create a source of ignition in a fuel tank, 

possibly resulting in a fire or explosion and 

consequent loss of the aeroplane. 

For the reasons described above, this AD 

requires a one-time electrical bonding check 

between the gravity fill re-fuel adaptor and 

the top skin panels on the affected aeroplanes 

and, in case of findings [a general visual 

inspection for corrosion of the component 

interface and adjacent area], the application 

of the associated corrective actions [i.e. 

repair]. 

You may obtain further information by 

examining the MCAI in the AD docket. 

Relevant Service Information 

Airbus has issued Service Bulletin 

A320–57–1152, dated June 14, 2010. 

The actions described in this service 

information are intended to correct the 

unsafe condition identified in the 

MCAI. 

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 


jlentini on DSK4TPTVN1PROD with PROPOSALS
61642 Federal Register / Vol. 76, No. 193 / Wednesday, October 5, 2011 / Proposed Rules 

AD because we evaluated all pertinent 

information and determined an unsafe 

condition exists and is likely to exist or 

develop on other products of the same 

type design. 

Differences Between This AD and the 

MCAI or Service Information 

We have reviewed the MCAI and 

related service information and, in 

general, agree with their substance. But 

we might have found it necessary to use 

different words from those in the MCAI 

to ensure the AD is clear for U.S. 

operators and is enforceable. In making 

these changes, we do not intend to differ 

substantively from the information 

provided in the MCAI and related 

service information. 

We might also have proposed 

different actions in this AD from those 

in the MCAI in order to follow FAA 

policies. Any such differences are 

highlighted in a NOTE within the 

proposed AD. 

Costs of Compliance 

Based on the service information, we 

estimate that this proposed AD would 

affect about 67 products of U.S. registry. 

We also estimate that it would take 

about 6 work-hours per product to 

comply with the basic requirements of 

this proposed AD. The average labor 

rate is $85 per work-hour. Based on 

these figures, we estimate the cost of the 

proposed AD on U.S. operators to be 

$34,170 or $510 per product. 

In addition, we estimate that any 

necessary follow-on actions would take 

about 6 work-hours and require parts 

costing $0, for a cost of $510 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); and 

3. 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. 

We prepared a regulatory evaluation 

of the estimated costs to comply with 

this proposed AD and placed it in the 

AD docket. 

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 AD: 

Airbus: Docket No. FAA–2011–0998; 

Directorate Identifier 2011–NM–046–AD. 

Comments Due Date 

(a) We must receive comments by 

November 21, 2011. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to Airbus Model A319– 

111, –112, and –132 airplanes; Model A320– 

111, –211, –212, –214 and –232 airplanes; 

and Model A321–111, –211, –212, and –231 

airplanes; certificated in any category; having 

manufacturer serial numbers 0039, 0078, 

0109, 0118, 0120, 0153, 0174, 0187, 0203, 

0215, 0218, 0226, 0227, 0228, 0236, 0237, 

0269, 0270, 0278, 0285, 0286, 0287, 0288, 

0294, 0301, 0337, 0377, 0462, 0463, 0464, 

0465, 0520, 0523, 0528, 0876, 0888, 0921, 

0935, 0974, 1014, 1102, 1130, 1160, 1162, 

1177, 1215, 1250, 1287, 1336, 1388, 1404, 

1444, 1449, 1476, 1505, 1524, 1564, 1605, 

1616, 1622, 1640, 1645, 1658, 1677, 1691, 

1729, and 1905. 

Subject 

(d) Air Transport Association (ATA) of 

America Code 57: Wings. 

Reason 

(e) The mandatory continuing 

airworthiness information (MCAI) states: 

Cases of corrosion findings have been 

reported on the overwing refueling aperture 

(used to fill the fuel tank by gravity) on the 

wing top skin. * * * 

* * * * * 

This condition, if not corrected, could, in 

combination with a lightning strike in this 

area, create a source of ignition in a fuel tank, 

possibly resulting in a fire or explosion and 

consequent loss of the aeroplane. 

* * * * * 

Compliance 

(f) You are responsible for having the 

actions required by this AD performed within 

the compliance times specified, unless the 

actions have already been done. 

Actions 

(g) Within 24 months after the effective 

date of this AD, do an electrical bonding test 

to check for bonding between the re-fuel 

adaptor of the gravity fill and the top skin 

panels on the left-hand and right-hand wings, 

in accordance with the Accomplishment 

Instructions of Airbus Service Bulletin A320– 

57–1152, dated June 14, 2010. 

(1) If the resistance value is 10 milliOhms 

or less at the left-hand and right-hand wing, 

no further action is required. 

(2) If the resistance value is greater than 10 

milliOhms at the left-hand or right-hand 

wing, before further flight do a general visual 

inspection for corrosion of the component 

interface and adjacent area, in accordance 

with the Accomplishment Instructions of 

Airbus Service Bulletin A320–57–1152, 

dated June 14, 2010. If any corrosion is found 

during the inspection, before further flight 

repair the gravity fuel adaptor, in accordance 

with the Accomplishment Instructions of 

Airbus Service Bulletin A320–57–1152, 

dated June 14, 2010; except where Airbus 

Service Bulletin A320–57–1152, dated June 

14, 2010, specifies to contact Airbus before 

further flight, repair using a method 

approved by the Manager, International 

Branch, ANM–116, Transport Airplane 

Directorate, FAA; or the European Aviation 

Safety Agency (EASA) (or its delegated 

agent). 

FAA AD Differences 

Note 1: This AD differs from the MCAI 

and/or service information as follows: No 

differences. 

Other FAA AD Provisions 

(h) The following provisions also apply to 

this AD: 


jlentini on DSK4TPTVN1PROD with PROPOSALS
Federal Register / Vol. 76, No. 193 / Wednesday, October 5, 2011 / Proposed Rules 61643 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, International 

Branch, ANM–116, 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: 

Sanjay Ralhan, Aerospace Engineer, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA, 1601 Lind 

Avenue, SW., Renton, Washington 98057– 

3356; telephone (425) 227–1405; fax (425) 

227–1149. Information may be e-mailed 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) Airworthy Product: For any requirement 

in this AD to obtain corrective actions from 

a manufacturer or other source, use these 

actions if they are FAA-approved. Corrective 

actions are considered FAA-approved if they 

are approved by the State of Design Authority 

(or their delegated agent). You are required 

to assure the product is airworthy before it 

is returned to service. 

Related Information 

(i) Refer to MCAI EASA Airworthiness 

Directive 2011–0034, dated March 2, 2011; 

and Airbus Service Bulletin A320–57–1152, 

dated June 14, 2010; for related information. 

Issued in Renton, Washington, on 

September 22, 2011. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2011–25569 Filed 10–4–11; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2011–0996; Directorate 

Identifier 2011–NM–068–AD] 

RIN 2120–AA64 

Airworthiness Directives; The Boeing 

Company Model 737–600, –700, –700C, 

–800, –900, and –900ER Series 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to adopt a new 

airworthiness directive (AD) for the 

products listed above. This proposed 

AD would require replacement of the 

thumbnail fairing edge seals on both 

sides of the engines with Nitronic 60 

stainless steel alloy seals. This proposed 

AD was prompted by reports of 

excessive in-service wear damage of the 

thumbnail fairing edge seal and the fan 

cowl panel rub strip and fan cowl skin 

assembly. We are proposing this AD to 

prevent failure of the fire seal, which 

could allow a fire in the fan 

compartment to spread beyond the 

firewall and reach the flammable fluid 

leakage zones, resulting in an 

uncontrolled fire. 

DATES: We must receive comments on 

this proposed AD by November 21, 

2011. 

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: 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 Boeing 

Commercial Airplanes, Attention: Data 

& Services Management, P.O. Box 3707, 

MC 2H–65, Seattle, Washington 98124– 

2207; telephone 206–544–5000, 

extension 1; fax 206–766–5680; e-mail 

me.boecom@boeing.com; Internet 

https://www.myboeingfleet.com. You 

may review copies of the referenced 

service information at the FAA, 

Transport Airplane Directorate, 1601 

Lind Avenue, SW., Renton, Washington. 

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; 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: 

Chris Parker, Aerospace Engineer, 

Propulsion Branch, ANM–140S, FAA, 

Seattle Aircraft Certification Office 

(ACO), 1601 Lind Avenue, SW., Renton, 

Washington 98057–3356; phone: 425– 

917–6496; fax: 425–917–6590; e-mail: 

chris.r.parker@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– 

2011–0996; Directorate Identifier 2011– 

NM–068–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 received reports of repetitive 

occurrences of excessive in-service wear 

damage of the thumbnail fairing edge 

seal and of the fan cowl panel rub strip 

and fan cowl skin assembly. Identical 

abrasion damage was also reported at 

the location where the thumbnail fairing 

edge seal rests against the top surface of 

the hinge beam forward firewall. This 

condition, if not corrected, could result 

in failure of the fire seal, which could 

allow a fire in the fan compartment to 

spread beyond the firewall and reach 

the flammable fluid leakage zones, 

resulting in an uncontrolled fire. 

Relevant Service Information 

We reviewed Boeing Special 

Attention Service Bulletin 737–54– 

1046, dated February 16, 2011. That 

service bulletin describes procedures for 

replacing the thumbnail fairing edge 

seals on both the left side and the right 

side of both engine 1 and engine 2 with 

new Nitronic 60 stainless steel alloy 

seals. 

FAA’s Determination and Proposed AD 

Requirements 

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 these same 

type designs. This proposed AD would 

require accomplishing the actions 

specified in the service information 

described previously. 


jlentini on DSK4TPTVN1PROD with PROPOSALS