46 Federal Register / Vol. 76, No. 1 / Monday, January 3, 2011 / Proposed Rules 

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. 

(3) Reporting Requirements: For any 

reporting requirement in this AD, under the 

provisions of the Paperwork Reduction Act 

(44 U.S.C. 3501 et seq.), the Office of 

Management and Budget (OMB) has 

approved the information collection 

requirements and has assigned OMB Control 

Number 2120–0056. 

Related Information 

(r) Refer to MCAI EASA Airworthiness 

Directive 2007–0053R3, dated December 17, 

2009, and the service bulletins listed in Table 

1 of this AD, for related information. 

TABLE 1—RELATED SERVICE INFORMATION

Service bulletin Revision Date 

Airbus Mandatory Service Bulletin A310–55–2004 .................... 05 ............................................ October 13, 2006. 

Airbus Service Bulletin A310–53–2016 ...................................... 5 .............................................. December 7, 1992. 

Airbus Service Bulletin A310-53-2019 ........................................ 3 .............................................. February 28, 1991. 

Airbus Service Bulletin A310–53–2054 ...................................... 2 .............................................. May 22, 1990. 

Airbus Service Bulletin A310–53–2057 ...................................... 1 .............................................. April 30, 1992. 

Airbus Service Bulletin A310–53–2059 ...................................... 1 .............................................. January 4, 1996. 

Airbus Service Bulletin A310–55–2002 ...................................... 4 .............................................. April 28, 1989. 

Airbus Service Bulletin A310–57–2039 ...................................... Original .................................... September 24, 1990. 

Airbus Service Bulletin A310–57–2041 ...................................... Original .................................... September 24, 1990. 

Issued in Renton, Washington on 

December 17, 2010. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2010–32983 Filed 12–30–10; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2010–1273; Directorate 

Identifier 2010–NM–089–AD] 

RIN 2120–AA64 

Airworthiness Directives; Airbus Model 

A310–203, –204, –222, –304, –322, and 

–324 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: 

A specific area, the lower tail plane cut-out 

located in the tail cone is subject to an 

inspection programme [for cracking] * * *. 

* * * * * 

The unsafe condition is reduced 

structural integrity of the tail cone. 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 February 17, 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 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; 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: Dan 

Rodina, Aerospace Engineer, 

International Branch, ANM–116, 

Transport Airplane Directorate, FAA, 

1601 Lind Avenue, SW., Renton, 

Washington 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–2010–1273; Directorate Identifier 

2010–NM–089–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 2009–0058, 

dated March 13, 2009 (referred to after 

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

condition for the specified products. 

The MCAI states: 


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Federal Register / Vol. 76, No. 1 / Monday, January 3, 2011 / Proposed Rules 47 

A specific area, the lower tail plane cut-out 

located in the tail cone is subject to an 

inspection programme specified in the 

Airbus Service Bulletin (SB) A310–53–2074. 

EASA issued AD 2007–0053 [which 

superseded French AD 1992–106–132 R6; 

French AD 1992–106–132 corresponds to 

FAA AD 98–26–01] to require the 

accomplishment of this SB at Revision 03. 

Airbus has established that this SB needed 

to be revised in order to state correct 

threshold and intervals due to errors 

introduced at revision 03. Consequently, 

revision 04 of this SB has been issued, and 

opportunity was taken: 

—To clarify the inspection area and 

associated threshold and intervals 

—To take aeroplane utilisation into 

consideration, in accordance with the 

A310 life extension programme. 

For the reasons stated above, this EASA 

AD takes over the requirements of paragraph 

1.16 of EASA AD 2007–0053R1 [currently at 

R3], which has been revised accordingly, and 

requires accomplishment of the instructions 

contained in Airbus SB A310–53–2074 at 

Revision 04. 

The unsafe condition is reduced 

structural integrity of the tail cone. The 

required actions include repetitive and 

one-time inspections, depending on the 

area, of the lower tail plane cut-out, and 

corrective actions if necessary. The 

inspections include the following: 

• Detailed inspections in areas 1, 2, 

and 3 for cracking and corrosion of the 

lower horizontal stabilizer cutout 

longeron, the corner fitting, the skin 

strap, and the skin. 

• Detailed inspections in areas 1, 2, 

and 3 for damaged sealant. 

• Eddy current inspections in area 1 

for cracking. 

• Eddy current inspections in area 2 

for cracking. 

• Rotating probe inspection for 

cracking of specified fastener holes in 

Area 3. 

The corrective actions, depending on 

the conditions found, include the 

following: 

• Repairing corrosion. 

• Contacting Airbus for repair 

instructions. 

• Replacing damaged sealant. 

• Removing cracking. 

• Doing an eddy current inspection 

for cracking of the reworked area. 

• Installing a new corner fitting. 

• Doing a rotating probe inspection 

for cracking of fastener holes. 

• Doing an eddy current inspection of 

the longeron and outer skin. 

• Drilling or reaming fastener holes. 

You may obtain further information 

by examining the MCAI in the AD 

docket. 

Other Relevant Rulemaking 

We are considering issuing three other 

NPRMs related to this NPRM: 

• Directorate Identifier 2010–NM– 

092–AD. That NPRM proposes to 

supersede AD 98–26–01, amendment 

39–10942 (63 FR 69179, December 16, 

1998), to continue to require certain 

actions specified in that AD. However, 

that NPRM does not restate paragraph 

(q) of AD 98–26–01. Instead, certain 

requirements of paragraph (q) of that AD 

are included in this NPRM, Directorate 

Identifier 2010–NM–089–AD. 

• Directorate Identifiers 2010–NM– 

090–AD and 2010–NM–091–AD. Both of 

these NPRMs include the requirements 

of certain other paragraphs of AD 98– 

26–01. 

Relevant Service Information 

Airbus has issued Mandatory Service 

Bulletin A310–53–2074, Revision 04, 

dated October 24, 2008. 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. 

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 44 products of U.S. registry. 

We also estimate that it would take 

about 36 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 

$134,640, or $3,060 per product. 

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: 


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48 Federal Register / Vol. 76, No. 1 / Monday, January 3, 2011 / Proposed Rules 

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–2010–1273; 

Directorate Identifier 2010–NM–089–AD. 

Comments Due Date 

(a) We must receive comments by February 

17, 2011. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to Model A310–203, 

–204, –222, –304, –322, and –324 airplanes, 

certificated in any category, all serial 

numbers, except airplanes on which Airbus 

modification 06146 has been done in 

production. 

Subject 

(d) Air Transport Association (ATA) of 

America Code 53: Fuselage. 

Reason 

(e) The mandatory continuing 

airworthiness information (MCAI) states: 

A specific area, the lower tail plane cut-out 

located in the tail cone is subject to an 

inspection programme [for cracking] * * *. 

* * * * * 

The unsafe condition is reduced structural 

integrity of the tail cone. 

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. 

Initial Inspections of the Lower Tail Plane 

Cut-Out Area and Corrective Actions 

(g) Within the applicable time specified in 

Table 1 of this AD, do the inspections of the 

lower tail plane cut-out area in the tail cone 

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

(g)(4), (g)(5), and (g)(6) of this AD, as 

applicable, in accordance with the 

Accomplishment Instructions of Airbus 

Mandatory Service Bulletin A310–53–2074, 

Revision 04, dated October 24, 2008 (‘‘the 

service bulletin’’). Certain compliance times 

are applicable to short-range use (i.e., average 

flight time (AFT) equal to or less than 4 flight 

hours), or long-range use (i.e., AFT exceeding 

4 flight hours). Inspection areas are specified 

in the service bulletin. 

Note 1: To establish the average flight time, 

take the accumulated flight time (counted 

from the take-off up to the landing) and 

divide by the number of accumulated flight 

cycles. This gives the average flight time per 

flight cycle. 

TABLE 1—INITIAL COMPLIANCE TIME

Airplanes Inspection 

areas 

Compliance time (whichever occurs later) 

Model A310–203, A310–204, and A310– 

222 airplanes.

1 and 2 ......... Prior to the accumulation of 18,000 total 

flight cycles or 36,000 total flight 

hours, whichever occurs first.

Within 1,500 flight cycles or 3,000 flight 

hours, whichever occurs first, after the 

effective date of this AD. 

Model A310–203, A310–204, and A310– 

222 airplanes.

3 ................... Prior to the accumulation of 24,000 total 

flight cycles or 48,000 total flight 

hours, whichever occurs first.

Within 1,500 flight cycles or 3,000 flight 

hours, whichever occurs first, after the 

effective date of this AD. 

Model A310–304, A310–322, and A310– 

324 short range airplanes.

1 and 2 ......... Prior to the accumulation of 12,000 total 

flight cycles or 33,750 total flight 

hours, whichever occurs first.

Within 1,200 flight cycles or 3,300 flight 

hours, whichever occurs first, after the 

effective date of this AD. 

Model A310–304, A310–322, and A310– 

324 short range airplanes.

3 ................... Prior to the accumulation of 18,000 total 

flight cycles or 50,500 total flight 

hours, whichever occurs first.

Within 1,200 flight cycles or 3,300 flight 

hours, whichever occurs first, after the 

effective date of this AD. 

Model A310–304, A310–322, and A310– 

324 long range airplanes.

1 and 2 ......... Prior to the accumulation of 7,500 total 

flight cycles or 37,500 total flight 

hours, whichever occurs first.

Within 750 flight cycles or 3,750 flight 

hours, whichever occurs first, after the 

effective date of this AD. 

Model A310–304, A310–322, and A310– 

324 long range airplanes.

3 ................... Prior to the accumulation of 11,250 total 

flight cycles or 56,000 total flight 

hours, whichever occurs first.

Within 750 flight cycles or 3,750 flight 

hours, whichever occurs first, after the 

effective date of this AD. 

(1) For areas 1, 2, and 3: Do a detailed 

inspection for cracking and corrosion of the 

lower horizontal stabilizer cutout longeron, 

the corner fitting, the skin strap, and the skin, 

in accordance with the Accomplishment 

Instructions of the service bulletin. 

(i) If any corrosion is found, before further 

flight, repair in accordance with the 

Accomplishment Instructions of the service 

bulletin. 

(ii) If any cracking is found, before further 

flight, contact Airbus for repair instructions 

and do the repair. 

(2) For areas 1, 2, and 3 on which cracking 

is not found during the inspection required 

by paragraph (g)(1) of this AD: Do a detailed 

inspection for damaged sealant; and, if any 

damaged sealant is found, before further 

flight, replace the sealant; in accordance with 

the Accomplishment Instructions of the 

service bulletin. 

(3) For area 1: Do an eddy current 

inspection for cracking in area 1; and, if no 

cracking is found, before further flight, apply 

sealant and corrosion compound, as 

applicable; in accordance with the 

Accomplishment Instructions of the service 

bulletin. 

(i) If cracking is equal to or less than 2.0 

mm (0.079 inch) long and not more than 2 

cracks with a minimum distance of 50.0 mm 

(1.969 inch) between the cracks: Before 

further flight, remove any cracking and do an 

eddy current inspection for cracking of the 

reworked area, in accordance with the 

Accomplishment Instructions of the service 

bulletin. If no cracking is found, before 

further flight, shot peen the reworked area, in 

accordance with the Accomplishment 

Instructions of the service bulletin. 

(A) If cracking is found and the radius of 

the rework is less than 20.0 mm (0.787 inch), 

before further flight, increase the radius and 

do an eddy current inspection for cracking of 

the reworked area, in accordance with the 

Accomplishment Instructions of the service 

bulletin. If no cracking is found, before 

further flight, shot peen the reworked area, in 

accordance with the Accomplishment 

Instructions of the service bulletin. 

(1) If any cracking is found in the outer 

skin, before further flight, contact Airbus for 

repair instructions and do the repair. 

(2) If any cracking is found in the corner 

fitting and area 3 has not been cold 

expanded, before further flight, install new 

corner fitting, in accordance with the 

Accomplishment Instructions of the service 

bulletin, and do the rotating probe inspection 

in area 3 specified in paragraph (g)(5) of this 

AD. 

(3) If any cracking is found in the corner 

fitting and area 3 has been cold expanded, 

before further flight, do the eddy current 

inspection of the longeron and outer skin 

specified in paragraph (g)(6) of this AD. 

(B) If cracking is found and the radius of 

the rework is 20.0 mm (0.787 inch) or more, 

before further flight, repair in accordance 

with a method approved by either the 

Manager, International Branch, ANM–116, 

FAA, Transport Airplane Directorate, or the 

European Aviation Safety Agency (EASA) (or 

its delegated agent). 


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(ii) If cracking is greater than 2.0 mm 

(0.079 inch) long or there are more than 2 

cracks; or if there are more than 2 cracks with 

less than a minimum distance of 50.0 mm 

(1.969 inch) between the cracks: Before 

further flight, remove the corner fitting, and 

do the applicable actions specified in 

paragraph (g)(3)(ii)(A) or (g)(3)(ii)(B) of this 

AD. 

(A) If any cracking is found and area 3 has 

not been cold expanded, before further flight, 

install a new corner fitting, in accordance 

with the Accomplishment Instructions of the 

service bulletin; and do the rotating probe 

inspection in area 3 specified in paragraph 

(g)(5) of this AD. 

(B) If any cracking is found and area 3 has 

been cold expanded, before further flight, do 

the eddy current inspection of the longeron 

and outer skin specified in paragraph (g)(6) 

of this AD. 

(4) For area 2: Do an eddy current 

inspection for cracking of area 2, in 

accordance with the Accomplishment 

Instructions of the service bulletin. If any 

cracking is found, before further flight, 

contact Airbus for repair instructions and do 

the repair. 

(5) For area 3: Do a rotating probe 

inspection for cracking of specified fastener 

holes in area 3, in accordance with the 

Accomplishment Instructions of the service 

bulletin. 

(i) If no cracking is found, before further 

flight, drill or ream fastener holes, cold 

expand the fastener holes and countersinks, 

and wet install with sealant, in accordance 

with the Accomplishment Instructions of the 

service bulletin; except where the service 

bulletin specifies to contact Airbus if the 

fastener diameter does not meet 

specifications or if the distance between the 

hole center and material edge is less than 

specifications, before further flight, contact 

Airbus for repair instructions and do the 

repair. 

(ii) If cracking is found, before further 

flight, drill or ream fastener holes, and do a 

rotating probe inspection for cracking of the 

fastener holes in accordance with the 

Accomplishment Instructions of the service 

bulletin. 

(A) If no cracking is found, cold expand the 

fastener holes and countersinks, drill or ream 

fastener holes, and wet install with sealant, 

in accordance with the Accomplishment 

Instructions of the service bulletin; except 

where the service bulletin specifies to contact 

Airbus if the fastener diameter does not meet 

specifications or if the distance between the 

hole center and material edge is less than the 

specifications, before further flight, contact 

Airbus for repair instructions and do the 

repair. 

(B) If cracking is found, before further 

flight, contact Airbus for repair instructions 

and do the repair. 

(6) For airplanes on which cracking is 

found in the corner fitting during any 

inspection required by paragraph (g)(3) of 

this AD and area 3 is cold-expanded: Do an 

eddy current inspection for cracking of the 

longeron and outer skin, in accordance with 

the Accomplishment Instructions of the 

service bulletin. 

(i) If no cracking is found, before further 

flight, install a new corner fitting and do a 

rotating probe inspection for cracking of the 

fastener holes, in accordance with the 

Accomplishment Instructions of the service 

bulletin. 

(A) If no cracking is found, before further 

flight, drill or ream fastener holes, cold 

expand the fastener holes and countersinks, 

and wet install with sealant, in accordance 

with the Accomplishment Instructions of the 

service bulletin. 

(B) If cracking is found and the hole 

diameter is less than the maximum oversize 

specification, before further flight, drill or 

ream holes and do a rotating probe 

inspection for cracking of the fastener holes, 

in accordance with the service bulletin. 

(1) If no cracking is found, cold expand the 

fastener holes and countersinks, and wet 

install with sealant, in accordance with the 

Accomplishment Instructions of the service 

bulletin. 

(2) If cracking is found, before further 

flight, contact Airbus for repair instructions 

and do the repair. 

(C) If cracking is found and the hole 

diameter is equal to or greater than the 

maximum oversize specification, before 

further flight, contact Airbus for repair 

instructions and do the repair. 

(ii) If cracking is found, before further 

flight, contact Airbus for repair instructions 

and do the repair. 

Repetitive Inspections of the Lower Tail 

Plane Cut-Out Area 

(h) Repeat the inspections for area 1 

required by paragraphs (g)(1) and (g)(3) of 

this AD thereafter at the applicable intervals 

specified in Table 2 of this AD. Certain 

compliance times are applicable to shortrange use (AFT equal to or less than 4 flight 

hours), or long-range use (AFT exceeding 4 

flight hours). Inspection areas are specified in 

the service bulletin. 

TABLE 2—REPETITIVE INTERVAL FOR AREAS 1 AND 2 

Affected airplanes Interval (not to exceed) 

(1) Model A310–203, A310–204, and A310–222 airplanes that have accumulated less than 30,000 total flight cycles and 60,000 total flight 

hours, as of the effective date of this AD.

6,000 flight cycles or 12,000 flight hours, whichever occurs first, until 

the airplane accumulates 30,000 total flight cycles or 60,000 total 

flight hours; then perform the inspections within the interval specified 

in paragraph (h)(2) of this AD. 

(2) Model A310–203, A310–204, and A310–222 airplanes that have accumulated 30,000 total flight cycles or more or 60,000 total flight 

hours or more, as of the effective date of this AD.

3,900 flight cycles or 7,800 flight hours, whichever occurs first. 

(3) Model A310–304, A310–322 and A310–324 short range airplanes 

that have accumulated less than 24,000 total flight cycles and 67,500 

total flight hours, as of the effective date of this AD.

4,800 flight cycles or 13,500 flight hours, whichever occurs first, until 

the airplane accumulates 24,000 total flight cycles or 67,500 total 

flight hours; then perform the inspections within the interval specified 

in paragraph (h)(4) of this AD. 

(4) Model A310–304, A310–322 and A310–324 short range airplanes 

that have accumulated 24,000 total flight cycles or more or 67,500 

total flight hours or more, as of the effective date of this AD.

3,100 flight cycles or 8,750 flight hours, whichever occurs first. 

(5) Model A310–304, A310–322 and A310–324 long range airplanes 

that have accumulated less than 15,000 total flight cycles and 75,000 

total flight hours, as of the effective date of this AD.

3,000 flight cycles or 15,000 flight hours, whichever occurs first, until 

the airplane accumulates 15,000 total flight cycles or 75,000 total 

flight hours; then perform the inspections within the interval specified 

in paragraph (h)(6) of this AD. 

(6) Model A310–304, A310–322 and A310–324 long range airplanes 

that have accumulated 15,000 total flight cycles or more or 75,000 

total flight hours or more, as of the effective date of this AD.

1,950 flight cycles or 9,750 flight hours, whichever occurs first. 

(i) Repeat the inspections for area 2 

required by paragraphs (g)(1) and (g)(4) of 

this AD thereafter at the applicable intervals 

specified in Table 2 of this AD. Certain 

compliance times are applicable to shortrange use (AFT equal to or less than 4 flight 

hours), or long-range use (AFT exceeding 4 

flight hours). Inspection areas are specified in 

the service bulletin. 

Credit for Actions Accomplished in 

Accordance With Previous Service 

Information 

(j) Inspections accomplished before the 

effective date of this AD in accordance with 

Airbus Mandatory Service Bulletin A310–53– 


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50 Federal Register / Vol. 76, No. 1 / Monday, January 3, 2011 / Proposed Rules 

2074, Revision 03, dated October 13, 2006, 

are considered acceptable for compliance 

with the corresponding action specified in 

this AD. 

FAA AD Differences 

Note 2: This AD differs from the MCAI 

and/or service information as follows: The 

MCAI and service information do not specify 

a corrective action if cracking is found and 

the radius of the rework is 20.0 mm (0.787 

inch) or more. Paragraph (g)(3)(i)(B) of this 

AD requires repair in accordance with a 

method approved by either the Manager, 

International Branch, ANM–116, FAA, 

Transport Airplane Directorate, or EASA (or 

its delegated agent). 

Other FAA AD Provisions 

(k) 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. 

Send information to ATTN: Dan Rodina, 

Aerospace Engineer, International Branch, 

ANM–116, Transport Airplane Directorate, 

FAA, 1601 Lind Avenue, SW., Renton, 

Washington 98057–3356; telephone (425) 

227–2125; fax (425) 227–1149. Before using 

any approved AMOC on any airplane to 

which the AMOC applies, notify your 

principal maintenance inspector (PMI) or 

principal avionics inspector (PAI), as 

appropriate, or lacking a principal inspector, 

your local Flight Standards 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. 

(3) Reporting Requirements: For any 

reporting requirement in this AD, under the 

provisions of the Paperwork Reduction Act 

(44 U.S.C. 3501 et seq.), the Office of 

Management and Budget (OMB) has 

approved the information collection 

requirements and has assigned OMB Control 

Number 2120–0056. 

Related Information 

(l) Refer to MCAI EASA Airworthiness 

Directive 2009–0058, dated March 13, 2009; 

and Airbus Mandatory Service Bulletin 

A310–53–2074, Revision 04, dated October 

24, 2008; for related information. 

Issued in Renton, Washington, on 

December 17, 2010. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2010–32991 Filed 12–30–10; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2010–1274; Directorate 

Identifier 2010–NM–090–AD] 

RIN 2120–AA64 

Airworthiness Directives; Airbus Model 

A310 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 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: 

DGAC [Direction Ge ́ne ́rale de l’Aviation 

Civile] France AD 1992–106–132(B) * * * 

was issued to require a set of inspection and 

modification tasks which addressed JAR/FAR 

[Joint Aviation Regulation/Federal Aviation 

Regulation] 25–571 requirements related to 

damage-tolerance and fatigue evaluation of 

structure. * * * 

* * * * * 

The unsafe condition is reduced 

structural integrity of the wings. 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 February 17, 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 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; 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: Dan 

Rodina, Aerospace Engineer, 

International Branch, ANM–116, 

Transport Airplane Directorate, FAA, 

1601 Lind Avenue, SW., Renton, 

Washington 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–2010–1274; Directorate Identifier 

2010–NM–090–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 2009–0057, 

dated March 13, 2009 (referred to after 

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

condition for the specified products. 

The MCAI states: 

DGAC [Direction Ge ́ne ́rale de l’Aviation 

Civile] France AD 1992–106–132(B) original 


srobinson on DSKHWCL6B1PROD with PROPOSALS