## 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:


## 27247 Federal Register / Vol. 76, No. 91 / Wednesday, May 11, 2011 / Rules and Regulations

• 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


## 27248 Federal Register / Vol. 76, No. 91 / Wednesday, May 11, 2011 / Rules and Regulations

Mandatory Service Bulletin A310–53–2074, Revision 04, dated October 24, 2008. Certaincompliance 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—I NITIAL 

### C OMPLIANCE 

### T IME

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


## 27249 Federal Register / Vol. 76, No. 91 / Wednesday, May 11, 2011 / Rules and Regulations

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. Certaincompliance 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—R EPETITIVE 

### I NTERVAL FOR 

### A REAS 

### 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. Certaincompliance 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


## 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