63270 Federal Register / Vol. 77, No. 200 / Tuesday, October 16, 2012 / Proposed Rules 

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. 

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–2012–1071; 

Directorate Identifier 2012–NM–070–AD. 

(a) Comments Due Date 

We must receive comments by November 

30, 2012. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to all Airbus Model A310– 

203 airplanes, certificated in any category. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 71; Powerplant. 

(e) Reason 

This AD was prompted by a report of an 

analysis that demonstrated a reduced fatigue 

life for the side link bolts, center sway link 

bolts, and thrust link bolts on the forward 

engine mounts. We are issuing this AD to 

prevent deterioration of the structural 

integrity of the bolts, which could result in 

possible damage to an engine or wing. 

(f) Compliance 

You are responsible for having the actions 

required by this AD performed within the 

compliance times specified, unless the 

actions have already been done. 

(g) Actions 

Within 18 months after the effective date 

of this AD, replace all side link bolts on left 

hand (LH) and right hand (RH) side of the 

engines, and all center sway link bolts and 

thrust link bolts of both engines, having any 

part number (P/N) identified in paragraphs 

(g)(1) through (g)(6) of this AD, with new 

bolts having the same part number, in 

accordance with the Accomplishment 

Instructions of Airbus Mandatory Service 

Bulletin A310–71–2037, including 

Appendices 01 and 02, dated September 30, 

2011. Repeat the bolt replacements thereafter 

at intervals not exceeding 134 months. 

(1) P/N 9021M88P01 

(2) P/N 9021M88P02 

(3) P/N 9205M81P01 

(4) P/N 9021M88P03 

(5) P/N 9021M88P04 

(6) P/N 9205M82P01 

(h) 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– 

1147. 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) 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. 

(i) Related Information 

(1) Refer to MCAI European Aviation 

Safety Agency (EASA) Airworthiness 

Directive 2012–0056, dated April 3, 2012; 

and Airbus Mandatory Service Bulletin 

A310–71–2037, including Appendices 01 

and 02, dated September 30, 2011; for related 

information. 

(2) For service information identified in 

this AD, contact Airbus SAS—EAW 

(Airworthiness Office), 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.airwortheas@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, WA. For 

information on the availability of this 

material at the FAA, call 425–227–1221. 

Issued in Renton, Washington, on October 

4, 2012. 

Dionne Palermo, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2012–25458 Filed 10–15–12; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2012–1076; Directorate 

Identifier 2011–NM–274–AD] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to adopt a new 

airworthiness directive (AD) for certain 

Airbus Model A320–214, –232 and 

–233; and Model A321–211, –213, and 

–231 airplanes. This proposed AD was 

prompted by a report of a missing 

fastener between certain stringers of the 

fuselage frame which connects the 

frame to a tee. This proposed AD would 

require a rototest inspection and 

modification or repair of the fuselage 

frame at the affected area. We are 

proposing this AD to detect and correct 

cracking in the fuselage that could result 

in reduced structural integrity of the 

airplane. 

DATES: We must receive comments on 

this proposed AD by November 30, 

2012. 

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, 

Airworthiness Office—EAS, 1 Rond 

Point Maurice Bellonte, 31707 Blagnac 

Cedex, France; telephone +33 5 61 93 36 


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Federal Register / Vol. 77, No. 200 / Tuesday, October 16, 2012 / Proposed Rules 63271 

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

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, 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; 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, 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–2012–1076; Directorate Identifier 

2011–NM–274–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 aviation authority 

for the Member States of the European 

Community, has issued EASA 

Airworthiness Directive 2011–0229, 

dated December 6, 2011 (referred to 

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

unsafe condition for the specified 

products. The MCAI states: 

During a quality check in production of an 

A320 family aeroplane, it was discovered 

that a fastener was missing at [frame] FR 24 

between stringer (STRG) 25 and STRG 26 on 

the right-hand (RH) side. The purpose of the 

missing fastener, a 4 [millimeter] mm 

diameter aluminum rivet, Part Number (P/N) 

ASNA2050DXJ040, is to connect the FR 24 to 

the FR 24 Tee. The hole where the fastener 

was missing was not drilled. 

Further investigations revealed that the 

drilling was missing on the milling grid used 

for frame assembly of a limited group of 

aeroplanes. 

This condition, if not corrected, could impair 

the structural integrity of the affected 

aeroplanes. 

For the reasons described above, this [EASA] 

AD requires a special detailed inspection 

(SDI) [rototest inspection for cracking] of the 

affected area, and the accomplishment of the 

associated corrective actions [modification 

and/or repair]. 

You may obtain further information by 

examining the MCAI in the AD docket. 

Relevant Service Information 

Airbus has issued Service Bulletin 

A320–53–1247, including Appendix 01, 

dated July 15, 2011. 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 

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. 

Costs of Compliance 

Based on the service information, we 

estimate that this proposed AD would 

affect about 111 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 

$56,610, or $510 per product. 

We have received no definitive data 

that would enable us to provide cost 

estimates for the on-condition actions 

specified in this proposed AD. 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. 

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. 


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63272 Federal Register / Vol. 77, No. 200 / Tuesday, October 16, 2012 / Proposed Rules 

§ 39.13 [Amended] 

2. The FAA amends § 39.13 by adding 

the following new AD: 

Airbus: Docket No. FAA–2012–1076; 

Directorate Identifier 2011–NM–274–AD. 

(a) Comments Due Date 

We must receive comments by November 

30, 2012. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to Airbus Model A320– 

214, –232, and –233; and Model A321–211, 

–213, and –231 airplanes; certificated in any 

category; manufacturer serial numbers 4338, 

4371, 4374, 4375, 4377, 4381 through 4384 

inclusive, 4386, 4387, 4388, 4390 through 

4402 inclusive, 4404 through 4409 inclusive, 

4411 through 4417 inclusive, 4419, 4420, 

4421, 4423, 4424, 4426, 4429 through 4436 

inclusive, 4438 through 4443 inclusive, 4445 

through 4450 inclusive, 4453, 4454, 4456 

through 4469 inclusive, 4471, 4472, 4474 

through 4481 inclusive, 4483 through 4498 

inclusive, 4500, 4504, 4505, 4506, and 4509. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 53, Fuselage. 

(e) Reason 

This AD was prompted by a report of a 

missing fastener between certain stringers of 

the fuselage frame which connects the frame 

to a tee. We are issuing this AD to detect and 

correct cracking in the fuselage that could 

result in reduced structural integrity of the 

airplane. 

(f) Compliance 

You are responsible for having the actions 

required by this AD performed within the 

compliance times specified, unless the 

actions have already been done. 

(g) Inspection 

Before the accumulation of 24,000 total 

flight cycles since first flight of the airplane, 

or within 30 days after the effective date of 

this AD, whichever occurs later: Do a rototest 

inspection for cracking of the two adjacent 

fastener holes at fuselage frame (FR) 24 

between stringer 25 and stringer 26 righthand side, in accordance with the 

Accomplishment Instructions of Airbus 

Service Bulletin A320–53–1247, excluding 

Appendix 01, dated July 15, 2011. 

(1) If, during the rototest inspection 

required by paragraph (g) of this AD, any 

crack is found, 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). 

(2) If, during the rototest inspection 

required by paragraph (g) of this AD, no crack 

is found, before the accumulation of 24,000 

total flight cycles since first flight of the 

airplane, or within 30 days after the effective 

date of this AD, whichever occurs later, 

modify fuselage frame FR 24 between stringer 

25 and stringer 26 right-hand side, in 

accordance with the Accomplishment 

Instructions of Airbus Service Bulletin A320– 

53–1247, excluding Appendix 01, dated July 

15, 2011. 

(h) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, International 

Branch, ANM–116, 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, WA 98057–3356; 

telephone (425) 227–1405; 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) 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. 

(i) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) EASA 

Airworthiness Directive 2011–0229, dated 

December 6, 2011; and Airbus Service 

Bulletin A320–53–1247, excluding Appendix 

01, dated July 15, 2011. 

(2) For service information identified in 

this 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; email 

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, WA. For 

information on the availability of this 

material at the FAA, call 425–227–1221. 

Issued in Renton, Washington, on October 

5, 2012. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2012–25461 Filed 10–15–12; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2012–1077; Directorate 

Identifier 2012–NM–146–AD] 

RIN 2120–AA64 

Airworthiness Directives; Embraer S.A. 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to adopt a new 

airworthiness directive (AD) for certain 

Embraer S.A. Model ERJ 170 and ERJ 

190 airplanes. This proposed AD was 

prompted by a report that high rate 

discharge (HRD) bottle explosive 

cartridges of a cargo compartment fire 

extinguisher system were swapped 

between the forward and aft cargo 

compartments. Additional investigation 

also revealed the possibility of 

swapping between the electrical 

connectors of the HRD and low rate 

discharge (LRD) bottles, and a rotated 

installation of the HRD bottle. Improper 

assembly of the fire extinguishing bottle 

might cause the extinguishing agent to 

be discharged toward the unselected 

cargo compartment rather than toward 

the cargo compartment with fire. This 

proposed AD would require an 

inspection of the HRD bottle for correct 

installation and to determine if the 

pressure switch is in the correct 

position, and re-installation if 

necessary; an inspection of the HRD and 

LRD bottle discharge heads to determine 

the part number and replacement if 

necessary; and, for certain airplanes, an 

inspection to determine the part 

numbers of the HRD and LRD electrical 

connectors, and relocation if necessary. 

We are proposing this AD to prevent the 

inability of the fire extinguishing system 

to suppress fire. 

DATES: We must receive comments on 

this proposed AD by November 30, 

2012. 

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– 


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