27246 Federal Register / Vol. 76, No. 91 / Wednesday, May 11, 2011 / Rules and Regulations 

after the effective date of this AD, modify the 

thrust reverser control system wiring to the 

FCU in the P252 and P253 thrust reverser 

relay panels, in accordance with the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 747–78A2184, Revision 1, 

dated December 23, 2010. 

(h) For Model 747–400, –400D, and –400F 

airplanes equipped with General Electric 

Model CF6–80C2 series engines: Within 36 

months after the effective date of this AD, 

modify the thrust reverser control system 

wiring to the FCU in the P414 and P415 

power distribution panels, in accordance 

with Boeing Special Attention Service 

Bulletin 747–78–2183, Revision 1, dated 

December 23, 2010. 

Credit for Actions Accomplished in 

Accordance With Previous Service 

Information 

(i) Modifying the thrust reverser control 

system wiring before the effective date of this 

AD, in accordance with Boeing Special 

Attention Service Bulletin 747–78–2183 or 

Boeing Alert Service Bulletin 747–78A2184, 

both dated January 12, 2010, as applicable, is 

acceptable for compliance with the 

corresponding modification required by 

paragraph (g) or (h) of this AD. 

Alternative Methods of Compliance 

(AMOCs) 

(j)(1) The Manager, Seattle Aircraft 

Certification Office (ACO), FAA, has the 

authority to approve AMOCs for this AD, if 

requested using the procedures found in 14 

CFR 39.19. In accordance with 14 CFR 39.19, 

send your request to your principal inspector 

or local Flight Standards District Office, as 

appropriate. If sending information directly 

to the manager of the ACO, send it to the 

attention of the person identified in the 

Related Information section of this AD. 

Information may be e-mailed to: 9-ANMSeattle-ACO-AMOC-Requests@faa.gov. 

(2) Before using any approved AMOC, 

notify your appropriate principal inspector, 

or lacking a principal inspector, the manager 

of the local flight standards district office/ 

certificate holding district office. 

Related Information 

(k) For more information about this AD, 

contact Tung Tran, Aerospace Engineer, 

Propulsion Branch, ANM–140S, FAA, Seattle 

Aircraft Certification Office, 1601 Lind 

Avenue, SW., Renton, Washington 98057– 

3356; phone: 425–917–6505; fax: 425–917– 

6590; e-mail: tung.tran@faa.gov. 

(l) For information about AMOCs, contact 

Tung Tran, Aerospace Engineer, Propulsion 

Branch, ANM–140S, FAA, Seattle Aircraft 

Certification Office, 1601 Lind Avenue, SW., 

Renton, Washington 98057–3356; phone: 

425–917–6505; fax: 425–917–6590; e-mail: 

tung.tran@faa.gov. 

Material Incorporated by Reference 

(m) You must use Boeing Special Attention 

Service Bulletin 747–78–2183, Revision 1, 

dated December 23, 2010; or Boeing Alert 

Service Bulletin 747–78A2184, Revision 1, 

dated December 23, 2010; as applicable; to do 

the actions required by this AD, unless the 

AD specifies otherwise. 

(1) The Director of the Federal Register 

approved the incorporation by reference of 

the service information under 5 U.S.C. 552(a) 

and 1 CFR part 51. 

(2) For service information identified in 

this 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. 

(3) You may review copies of the 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. 

(4) You may also review copies of the 

service information that is incorporated by 

reference at the National Archives and 

Records Administration (NARA). For 

information on the availability of this 

material at an NARA facility, call 202–741– 

6030, or go to http://www.archives.gov/ 

federal_register/code_of_federal_regulations/ 

ibr_locations.html. 

Issued in Renton, Washington, on April 20, 

2011. 

Kalene C. Yanamura, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2011–10692 Filed 5–10–11; 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; Amendment 

39–16686; AD 2011–10–05] 

RIN 2120–AA64 

Airworthiness Directives; Airbus Model 

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

–324 Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for the 

products listed above. This 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. We 

are issuing this AD to require actions to 

correct the unsafe condition on these 

products. 

DATES: This AD becomes effective June 

15, 2011. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of June 15, 2011. 

ADDRESSES: You may examine the AD 

docket on the Internet at http:// 

www.regulations.gov or in person at the 

U.S. Department of Transportation, 

Docket Operations, M–30, West 

Building Ground Floor, Room W12–140, 

1200 New Jersey Avenue, SE., 

Washington, DC. 

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: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to include an AD that would 

apply to the specified products. That 

NPRM was published in the Federal 

Register on January 3, 2011 (76 FR 46). 

That NPRM proposed to correct an 

unsafe condition for the specified 

products. The MCAI states: 

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: 


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• 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. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

received no comments on the NPRM or 

on the determination of the cost to the 

public. 

Conclusion 

We reviewed the available data and 

determined that air safety and the 

public interest require adopting the AD 

as proposed. 

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 required different 

actions in this AD from those in the 

MCAI in order to follow our FAA 

policies. Any such differences are 

highlighted in a NOTE within the AD. 

Costs of Compliance 

We estimate that this AD will affect 

44 products of U.S. registry. We also 

estimate that it will take about 36 workhours per product to comply with the 

basic requirements of this AD. The 

average labor rate is $85 per work-hour. 

Based on these figures, we estimate the 

cost of this AD to the 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 

This AD will not have federalism 

implications under Executive Order 

13132. This AD will 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 AD: 

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 AD and placed it in the AD docket. 

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 the NPRM, 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. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety. 

Adoption of the Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA amends 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: 

2011–10–05 Airbus: Amendment 39–16686. 

Docket No. FAA–2010–1273; Directorate 

Identifier 2010–NM–089–AD. 

Effective Date 

(a) This airworthiness directive (AD) 

becomes effective June 15, 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 


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Mandatory Service Bulletin A310–53–2074, 

Revision 04, dated October 24, 2008. Certain 

compliance times are applicable to shortrange use (i.e., average flight time (AFT) 

equal to or less than 4 flight hours), or longrange use (i.e., AFT exceeding 4 flight hours). 

Inspection areas are specified in Airbus 

Mandatory Service Bulletin A310–53–2074, 

Revision 04, dated October 24, 2008. 

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 Airbus Mandatory Service 

Bulletin A310–53–2074, Revision 04, dated 

October 24, 2008. 

(i) If any corrosion is found, before further 

flight, repair in accordance with the 

Accomplishment Instructions of Airbus 

Mandatory Service Bulletin A310–53–2074, 

Revision 04, dated October 24, 2008. 

(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 Airbus 

Mandatory Service Bulletin A310–53–2074, 

Revision 04, dated October 24, 2008. 

(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 Airbus 

Mandatory Service Bulletin A310–53–2074, 

Revision 04, dated October 24, 2008. 

(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 Airbus 

Mandatory Service Bulletin A310–53–2074, 

Revision 04, dated October 24, 2008. If no 

cracking is found, before further flight, shot 

peen the reworked area, in accordance with 

the Accomplishment Instructions of Airbus 

Mandatory Service Bulletin A310–53–2074, 

Revision 04, dated October 24, 2008. 

(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 Airbus 

Mandatory Service Bulletin A310–53–2074, 

Revision 04, dated October 24, 2008. If no 

cracking is found, before further flight, shot 

peen the reworked area, in accordance with 

the Accomplishment Instructions of Airbus 

Mandatory Service Bulletin A310–53–2074, 

Revision 04, dated October 24, 2008. 

(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 Airbus 

Mandatory Service Bulletin A310–53–2074, 

Revision 04, dated October 24, 2008, 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) 

(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 

Airbus Mandatory Service Bulletin A310–53– 

2074, Revision 04, dated October 24, 2008; 

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 Airbus Mandatory Service 

Bulletin A310–53–2074, Revision 04, dated 

October 24, 2008. 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 Airbus 

Mandatory Service Bulletin A310–53–2074, 

Revision 04, dated October 24, 2008. 

(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 

Airbus Mandatory Service Bulletin A310–53– 

2074, Revision 04, dated October 24, 2008; 

except where this service bulletin specifies to 

contact Airbus if the fastener diameter does 

not meet specifications or if the distance 


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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 Airbus 

Mandatory Service Bulletin A310–53–2074, 

Revision 04, dated October 24, 2008. 

(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 Airbus Mandatory Service 

Bulletin A310–53–2074, Revision 04, dated 

October 24, 2008; except where this 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 Airbus 

Mandatory Service Bulletin A310–53–2074, 

Revision 04, dated October 24, 2008. 

(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 Airbus 

Mandatory Service Bulletin A310–53–2074, 

Revision 04, dated October 24, 2008. 

(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 

Airbus Mandatory Service Bulletin A310–53– 

2074, Revision 04, dated October 24, 2008. 

(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 Airbus Mandatory 

Service Bulletin A310–53–2074, Revision 04, 

dated October 24, 2008. 

(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 Airbus 

Mandatory Service Bulletin A310–53–2074, 

Revision 04, dated October 24, 2008. 

(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 

Airbus Mandatory Service Bulletin A310–53– 

2074, Revision 04, dated October 24, 2008. 

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 

Airbus Mandatory Service Bulletin A310–53– 

2074, Revision 04, dated October 24, 2008. 

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– 

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. 

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 


srobinson on DSKHWCL6B1PROD with RULES
27250 Federal Register / Vol. 76, No. 91 / Wednesday, May 11, 2011 / Rules and Regulations 

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, Washington 98057– 

3356; telephone (425) 227–2125; 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 

(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. 

Material Incorporated by Reference 

(m) You must use Airbus Mandatory 

Service Bulletin A310–53–2074, Revision 04, 

dated October 24, 2008, to do the actions 

required by this AD, unless the AD specifies 

otherwise. 

(1) The Director of the Federal Register 

approved the incorporation by reference of 

this service information under 5 U.S.C. 

552(a) and 1 CFR part 51. 

(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; e-mail account.airwortheas@airbus.com; Internet http:// 

www.airbus.com. 

(3) You may review copies of the 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. 

(4) You may also review copies of the 

service information that is incorporated by 

reference at the National Archives and 

Records Administration (NARA). For 

information on the availability of this 

material at NARA, call 202–741–6030, or go 

to: http://www.archives.gov/federal_register/ 

code_of_federal_regulations/ 

ibr_locations.html. 

Issued in Renton, Washington, on April 22, 

2011. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2011–10688 Filed 5–10–11; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF HOMELAND 

SECURITY 

Coast Guard 

33 CFR Part 117 

[Docket No. USCG–2011–0330] 

Drawbridge Operation Regulations; 

Hackensack River, Jersey City, NJ 

AGENCY: Coast Guard, DHS. 

ACTION: Notice of temporary deviation 

from regulations. 

SUMMARY: The Commander, First Coast 

Guard District, has issued a temporary 

deviation from the regulation governing 

the operation of the Lower Hack Bridge 

across the Hackensack River, mile 3.4, at 

Jersey City, New Jersey. The deviation is 

necessary to repair structural steel 

members on the lift span. This deviation 

allows the bridge to remain in the 

closed position to facilitate the above 

repairs. 

DATES: This deviation is effective from 

10 p.m. on May 26, 2011 through 5 a.m. 

on May 27, 2011. 

ADDRESSES: Documents mentioned in 

this preamble as being available in the 

docket are part of docket USCG–2011– 

0330 and are available online at 

http://www.regulations.gov, inserting 

USCG–2011–0330 in the ‘‘Keyword’’ and 

then clicking ‘‘Search.’’ They are also 

available for inspection or copying at 

the Docket Management Facility (M–30), 

U.S. Department of Transportation, 

West Building Ground Floor, Room 

W12–140, 1200 New Jersey Avenue, SE., 

Washington, DC 20590, between 9 a.m. 

and 5 p.m., Monday through Friday, 

except Federal holidays. 

FOR FURTHER INFORMATION CONTACT: If 

you have questions on this rule, call or 

e-mail Mr. Joe Arca, Project Officer, 

First Coast Guard District, 

joe.m.arca@uscg.mil, telephone (212) 

668–7165. If you have questions on 

viewing the docket, call Renee V. 

Wright, Program Manager, Docket 

Operations, telephone 202–366–9826. 

SUPPLEMENTARY INFORMATION: The Lower 

Hack Bridge, across the Hackensack 

River at mile 3.4, has a vertical 

clearance in the closed position of 40 

feet at mean high water and 45 feet at 

mean low water. The existing 

drawbridge operation regulations are 

listed at 33 CFR 117.723(b). 

The waterway accommodates both 

commercial and recreational vessels of 

various sizes. Recreational navigation 

passes under the bridge without 

requiring any drawbridge openings. 

The owner of the bridge, New Jersey 

Transit, requested a temporary deviation 

to facilitate necessary structural steel 

repairs at the bridge. 

Under this temporary deviation the 

Lower Hack Bridge, across the 

Hackensack River at mile 3.4, may 

remain in the closed position from 

10 p.m. on May 26, 2011 through 5 a.m. 

on May 27, 2011. Vessels that can pass 

under the bridge without a bridge 

opening may do so at all times. 

In accordance with 33 CFR 117.35(e), 

the bridge must return to its regular 

operating schedule immediately at the 

end of the designated time period. This 

deviation from the operating regulations 

is authorized under 33 CFR 117.35. 

Dated: May 2, 2011. 

Gary Kassof, 

Bridge Program Manager, First Coast Guard 

District. 

[FR Doc. 2011–11545 Filed 5–10–11; 8:45 am] 

BILLING CODE 9110–04–P 

DEPARTMENT OF HOMELAND 

SECURITY 

Coast Guard 

33 CFR Part 117 

[Docket No. USCG–2011–0291] 

Drawbridge Operation Regulation; 

Atlantic Intracoastal Waterway, 

Albemarle and Chesapeake Canal, 

Chesapeake, VA 

AGENCY: Coast Guard, DHS. 

ACTION: Notice of temporary deviation 

from regulations. 

SUMMARY: The Commander, Fifth Coast 

Guard District, has issued a temporary 

deviation from the regulations 

governing the operation of the SR170 

Centerville Turnpike Bridge across the 

Atlantic Intracoastal Waterway, 

Albemarle and Chesapeake Canal, mile 

15.2, at Chesapeake, VA. The deviation 

is necessary to facilitate urgent 

mechanical structural repairs to the 

swing span. Under this deviation, the 

drawbridge will be allowed to operate 

on a limited schedule for the extent of 

the effective period, specifically 

affecting four specific dates during the 

effective time-period: May 14, 2011; 

May 15, 2011; June 4, 2011; and June 5, 

2011. 

DATES: This deviation is effective from 

8 a.m. on May 14, 2011 to 8 p.m. on 

June 5, 2011. 

ADDRESSES: Documents mentioned in 

this preamble as being available in the 

docket USCG–2011–0291 and are 

available online by going to http:// 

www.regulations.gov, inserting USCG– 

2011–0291 in the ‘‘Keyword’’ box, and 


srobinson on DSKHWCL6B1PROD with RULES