## 41653 Federal Register / Vol. 76, No. 136 / Friday, July 15, 2011 / Rules and Regulations

and could lead to the loss of the vertical stabilizer.
Compliance

(f) Comply with this AD within the compliance times specified, unless already done.
Inspections

(g) Within 4,500 flight cycles after the effective date of this AD, do a detailed inspection for distress in and existing repairs to the leading edge structure of the vertical stabilizer at the splice at Station Zfs=52.267, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin MD80–55A067, dated June 24, 2010.
Repetitive Inspections for Cracks, and Related Investigative and Corrective Actions

(h) Before further flight after doing the inspection required by paragraph (g) of this AD, inspect for cracks of the left and right vertical stabilizer front spar cap, in accordance with either Option 1 or Option 2 as specified in the Accomplishment Instructions of Boeing Alert Service Bulletin MD80–55A067, dated June 24, 2010. If any crack is found, before further flight, evaluate and verify to confirm all crack indications, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin MD80–55A067, dated June 24, 2010.

(1) If any cracking is confirmed, before further flight, repair using a method approved in accordance with the procedures specified in paragraph (l) of this AD.

(2) If no cracking is confirmed, repeat the inspection thereafter at intervals not to exceed the applicable interval specified in paragraph (h)(2)(i) or (h)(2)(ii) of this AD.

(i) If the most recent inspection was done using Option 1, the next inspection must be done within 4,400 flight cycles.

(ii) If the most recent inspection was done using Option 2, the next inspection must be done within 3,000 flight cycles.
Leading Edge Repair

(i) If leading edge distress is found during the detailed inspection required by paragraph (g) of this AD, before further flight and after accomplishing the inspection required by paragraph (h) of this AD, repair the leading edge, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin MD80–55A067, dated June 24, 2010. Inspection for Loose/Missing Fasteners

(j) For airplanes on which no cracking is confirmed during the initial inspection required by paragraph (h) of this AD: At the applicable time specified in paragraph (j)(1) or (j)(2) of this AD, do a detailed inspection for indications of loose and missing fasteners, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin MD80–55A067, dated June 24, 2010. If any loose or missing fastener is found, before further flight, repair the leading edge, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin MD80–55A067, dated June 24, 2010.

(1) If the inspection required by paragraph (h) was done using Option 1, do the inspection required by paragraph (j) of this AD within 4,400 flight cycles after accomplishing the inspection required by paragraph (h) of this AD.

(2) If inspection required by paragraph (h) was done using Option 2, do the inspection required by paragraph (j) of this AD within 3,000 flight cycles after accomplishing the inspection required by paragraph (h) of this AD.

(k) For airplanes on which no cracking is confirmed during the most recent inspection required by paragraph (h) of this AD: Repeat the inspection for loose and missing fasteners required by paragraph (j) of this AD thereafter at intervals not to exceed the applicable time specified in paragraph (k)(1) or (k)(2) of this AD.

(1) If the most recent inspection required by paragraph (h) was done using Option 1, the next inspection required by paragraph (j) of this AD must be done within 4,400 flight cycles after accomplishing the most recent inspection required by paragraph (j) of this AD.

(2) If the most recent inspection required by paragraph (h) was done using Option 2, the next inspection required by paragraph (j) of this AD must be done within 3,000 flight cycles after the most recent inspection required by paragraph (j) of this AD.
Alternative Methods of Compliance (AMOCs)

(l)(1) The Manager, Los Angeles 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.

(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.

(3) An AMOC that provides an acceptable level of safety may be used for any repair required by this AD if it is approved by the Boeing Commercial Airplanes Organization Designation Authorization (ODA) that has been authorized by the Manager, Los Angeles ACO to make those findings. For a repair method to be approved, the repair must meet the certification basis of the airplane and 14 CFR 25.571, Amendment 45, and the approval must specifically refer to this AD.

Related Information

(m) For more information about this AD, contact Roger Durbin, Aerospace Engineer, Airframe Branch, ANM–120L, Los Angeles Aircraft Certification Office, 3960 Paramount Boulevard, Lakewood, California 90712– 4137; phone: 562–627–5233; fax: 562–627– 5210; e-mail: Roger.Durbin@faa.gov.
Material Incorporated by Reference

(n) You must use Boeing Alert Service Bulletin MD80–55A067, dated June 24, 2010, 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 Boeing Commercial Airplanes, Attention: Data & Services Management, 3855 Lakewood Boulevard, MC D800–0019, Long Beach, California 90846– 0001; telephone 206–544–5000, extension 2; fax 206–766–5683; e-mail dse.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 July 1,
2011. Jeffrey E. Duven, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service.

[FR Doc. 2011–17400 Filed 7–14–11; 8:45 am]

**BILLING CODE 4910–13–P**



### DEPARTMENT OF TRANSPORTATION

**Federal Aviation Administration**

**14 CFR Part 39**

**[Docket No. FAA–2010–1307; Directorate Identifier 2010–NM–049–AD; Amendment**  **39–16671; AD 2011–09–09]**

**RIN 2120–AA64**



### Airworthiness Directives; Bombardier, **Inc. Model CL–600–2A12 (CL–601) and CL–600–2B16 (CL–601–3A, CL–601–**  **3R, and CL–604 Variants) 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:

During flight-testing of a wing anti-ice piccolo tube containing a deliberate small breach, it was determined that the wing leading edge thermal switches were not detecting the consequent bleed leak at the design threshold. As a result, new


## 41654 Federal Register / Vol. 76, No. 136 / Friday, July 15, 2011 / Rules and Regulations

Airworthiness Limitation tasks, consisting of a functional test of the wing leading edge thermal switches and an inspection of the wing anti-ice duct piccolo tubes, have been introduced in order to limit exposure to dormant failure of the switches in the event of piccolo tube failure, which could potentially compromise the structural integrity of the wing leading edge and the effectiveness of the wing anti-ice system. 

### We are issuing this AD to require actions to correct the unsafe condition on these products.

**DATES** 

### : This AD becomes effective August 19, 2011.

The Director of the Federal Register approved the incorporation by reference of certain publications listed in this AD as of August 19, 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** 

### : Cesar Gomez, Aerospace Engineer, Airframe and Mechanical Systems Branch, ANE–171, FAA, New York Aircraft Certification Office, 1600 Stewart Avenue, Suite 410, Westbury, New York 11590; telephone (516) 228– 7318; fax (516) 794–5531.

**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 5, 2011 (76 FR 477). That NPRM proposed to correct an unsafe condition for the specified products. The MCAI states:

During flight-testing of a wing anti-ice piccolo tube containing a deliberate small breach, it was determined that the wing leading edge thermal switches were not detecting the consequent bleed leak at the design threshold. As a result, new Airworthiness Limitation tasks, consisting of a functional test of the wing leading edge thermal switches and an inspection of the wing anti-ice duct piccolo tubes, have been introduced in order to limit exposure to dormant failure of the switches in the event of piccolo tube failure, which could potentially compromise the structural integrity of the wing leading edge and the effectiveness of the wing anti-ice system. This directive mandates the revision of the approved maintenance schedule to include these new tasks, including phase-in schedules.

This revision clarifies the applicability of the directive for CL–600–2A12 aircraft, serial numbers 3001 through 3066, and for CL– 600–2B16 aircraft, serial numbers 5001 through 5194. The directive is only applicable to these aircraft if Bombardier Service Bulletin (SB) 601–0590 [Scheduled Maintenance Instructions (MSG–3) Derived— Qualification] has been incorporated. There is no change required to the approved maintenance schedule if SB 601–0590 has not been incorporated. 

### 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 103 products of U.S. registry. We alsoestimate that it will take about 1 workhour 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 $8,755, or $85 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 that 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 proposed 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.


## 41655 Federal Register / Vol. 76, No. 136 / Friday, July 15, 2011 / Rules and Regulations

**§ 39.13 [Amended]**

■ 

### 2. The FAA amends § 39.13 by adding the following new AD:

2011–09–09 Bombardier, Inc.: Amendment 39–16671. Docket No. FAA–2010–1307; Directorate Identifier 2010–NM–049–AD.

Effective Date

(a) This airworthiness directive (AD) becomes effective August 19, 2011.

Affected ADs

(b) None.
Applicability

(c) This AD applies to the airplanes identified in paragraphs (c)(1), (c)(2), (c)(3), and (c)(4) of this AD; certificated in any category.

(1) Bombardier, Inc. Model CL–600–2A12 (CL–601) airplanes, serial numbers 3001 through 3066 inclusive on which Bombardier Service Bulletin 601–0590 has been accomplished.

(2) Bombardier, Inc. CL–600–2B16 (CL– 601–3A and CL–601–3R Variants) airplanes, serial numbers 5001 through 5194 inclusive on which Bombardier Service Bulletin 601– 0590 has been accomplished. (3) Bombardier, Inc. CL–600–2B16 (CL–604 Variants) airplanes, serial numbers 5301 through 5665 inclusive.

(4) Bombardier, Inc. CL–600–2B16 (CL–604 Variants) airplanes, serial numbers 5701 and subsequent.

Note 1: This AD requires revisions to certain operator maintenance documents to include new inspections. Compliance with these inspections is required by 14 CFR 91.403(c). For airplanes that have been previously modified, altered, or repaired in the areas addressed by these inspections, the operator may not be able to accomplish the inspections described in the revisions. In this situation, to comply with 14 CFR 91.403(c), the operator must request approval for an alternative method of compliance according to paragraph (j) of this AD. The request should include a description of changes to the required inspections that will ensure the continued operational safety of the airplane.

Subject

(d) Air Transport Association (ATA) of America Codes 30 and 36: Ice and Rain Protection and Pneumatic, respectively.

Reason

(e) The mandatory continuing airworthiness information (MCAI) states: During flight-testing of a wing anti-ice piccolo tube containing a deliberate small breach, it was determined that the wing leading edge thermal switches were not detecting the consequent bleed leak at the design threshold. As a result, new Airworthiness Limitation tasks, consisting of a functional test of the wing leading edge thermal switches and an inspection of the wing anti-ice duct piccolo tubes, have been introduced in order to limit exposure to dormant failure of the switches in the event of piccolo tube failure, which could potentially compromise the structural integrity of the wing leading edge and the effectiveness of the wing anti-ice system.
Compliance

(f) You are responsible for having the actions required by this AD performed within the compliance times specified, unless the actions have already been done.

Actions

(g) Within 30 days after the effective date of this AD: Revise the Airworthiness Limitations Section of the Instructions for Continued Airworthiness by incorporating the applicable tasks identified in table 1 of this AD.



### T ABLE 

### 1—A IRWORTHINESS 

### L IMITATIONS 

### T ASKS

For Bombardier, Inc. model— Incorporate task(s)— Identified in—

CL-600-2A12 (CL-601) airplanes, serial numbers 3001 through 3066 inclusive on which Bombardier Service Bulletin 601-0590 has been accomplished. 30–11–00–101, Wing Anti-icing, and 30–11– 00–102, Wing Anti-icing. Bombardier Challenger 601 Time Limits/Maintenance Checks, PSP 601–5, Revision 38, dated June 19, 2009.

CL-600-2B16 (CL-601-3A and CL-601-3R

Variants) airplanes, serial numbers 5001 through 5194 inclusive on which BombardierService Bulletin 601–0590 has been accomplished. 30–11–00–101, Wing Anti-icing, and 30–11– 00–102, Wing Anti-icing. Bombardier Challenger 601 Time Limits/Maintenance Checks, PSP 601A–5, Revision 34, dated June 19, 2009.

CL–600–2B16 (CL–604 Variants) airplanes, serial numbers 5301 through 5665 inclusive. 30–11–00–101, Detailed Inspection of the Wing Anti-Ice Duct Piccolo-Tube, and36-21-00-101, Functional Test of the Leading Edge Thermal Switches. Bombardier Challenger 604 Time Limits/Maintenance Checks, CH 604 TLMC, Revision 13, dated August 12, 2009.

CL–600–2B16 (CL–604 Variants) airplanes, serial numbers 5701 and subsequent. 30–11–00–101, Detailed Inspection of the Wing Anti-Ice Duct Piccolo-Tube, and36-21-00-101, Functional Test of the Leading Edge Thermal Switches. Bombardier Challenger 605 Time Limits/Maintenance Checks, CH 605 TLMC, Revision 1, dated August 12, 2009.

(h) For all tasks identified in paragraph (g) of this AD, the initial compliance times for those tasks are within the applicable times specified in table 2 of this AD.



### T ABLE 

### 2—I NITIAL 

### C OMPLIANCE 

### T IMES FOR 

### A IRWORTHINESS 

### L IMITATIONS 

### T ASKS

Bombardier, Inc. model— Task(s)— Initial compliance time (whichever occurs later)—

CL-600-2A12 (CL-601) airplanes,

serial numbers 3001 through 3066 inclusive; and CL-600-2B16 (CL-601-3A and CL-601-3R Variants) airplanes, serial numbers 5001 through5194 inclusive; on which Bombardier Service Bulletin 601– 0590 has been accomplished. 30–11–00–101, Wing Anti-icing ... Prior to the accumulation of 4,800 total flight hours; or within 4,800 flight hours after accomplishing Task 30-11-06-204 in Section 5-20–15 of the applicable Time Limits/Maintenance Checks manual specified in table 1 of this AD; whichever occurs later. Within 240 flight hours after the effective date of this AD.


## 41656 Federal Register / Vol. 76, No. 136 / Friday, July 15, 2011 / Rules and Regulations

T ABLE 

### 2—I NITIAL 

### C OMPLIANCE 

### T IMES FOR 

### A IRWORTHINESS 

### L IMITATIONS 

### T ASKS 

### —Continued

Bombardier, Inc. model— Task(s)— Initial compliance time (whichever occurs later)—

CL-600-2A12 (CL-601) airplanes,

serial numbers 3001 through 3066 inclusive; and CL-600-2B16 (CL-601-3A and CL-601-3R Variants) airplanes, serial numbers 5001 through5194 inclusive; on which Bombardier Service Bulletin 601– 0590 has been accomplished. 30–11–00–102, Wing Anti-icing ... Prior to the accumulation of 4,800 total flight hours; or within 4,800 flight hours after accomplishing Task 30-13-00-205 in Section 5-20–15 of the applicable Time Limits/Maintenance Checks manual specified in table 1 of this AD; whichever occurs later. Within 240 flight hours after the effective date of this AD.

CL–600–2B16 (CL–604 Variants)

airplanes, serial numbers 5301 through 5665 inclusive. 30–11–00–101, Detailed Inspection of the Wing Anti-Ice Duct Piccolo-Tube, and 36-21-00-101, Functional Test of the Leading Edge Thermal Switches. Prior to the accumulation of 6,400total flight hours; except for airplanes having 6,400 total flighthours or more as of the effective date of this AD on whichthe task has not been accomplished: prior to the next scheduled 6,400 flight hour task inspection or prior to the next scheduled accomplishment ofTask 57-10-00–208 in the applicable Time Limits/Maintenance Checks manual specified in table 1 of this AD, whichever occurs first. Within 320 flight hours after the effective date of this AD.

CL–600–2B16 (CL–604 Variants)

airplanes, serial numbers 5701 and subsequent. 30–11–00–101, Detailed Inspection of the Wing Anti-Ice Duct Piccolo-Tube, and 36-21-00-101, Functional Test of the Leading Edge Thermal Switches. Prior to the accumulation of 6,400 total flight hours. Within 320 flight hours after the effective date of this AD.

(i) After accomplishing the actions required by paragraph (g) of this AD, no alternative tasks or task intervals may be used unless the tasks or task intervals are approved as an alternative method of compliance (AMOC) in accordance with the procedures specified in paragraph (j)(1) of this AD.

FAA AD Differences

Note 2: This AD differs from the MCAI and/or service information as follows: No differences.

Other FAA AD Provisions

(j) The following provisions also apply to this AD:

(1) Alternative Methods of Compliance (AMOCs): The Manager, New York Aircraft Certification Office (ACO), ANE–170, 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 ACO, send it to ATTN: Program Manager, Continuing Operational Safety, FAA, New York ACO, 1600 Stewart Avenue, Suite 410, Westbury, New York 11590; telephone 516–228–7300; fax 516– 794–5531. 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 FAAapproved 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

(k) Refer to MCAI Canadian Airworthiness Directive CF–2009–49R1, dated January 21, 2010, and the service information specified in Table 1 of this AD, for related information.
Material Incorporated by Reference

(l) You must use the applicable service information contained in table 3 of this AD to do the actions required by this AD, unless the AD specifies otherwise.



### T ABLE 

### 3—M ATERIAL 

### I NCORPORATED BY 

### R EFERENCE

Document Revision Date

Tasks 30–11–00–101, Wing Anti-icing, and 30–11–00–102, Wing Anti-icing, of the Bombardier Challenger 601 Time Limits/Maintenance Checks, PSP 601–5. 38 June 19, 2009.

Tasks 30–11–00–101, Wing Anti-icing, and 30–11–00–102, Wing Anti-icing, of the Bombardier Challenger 601 Time Limits/Maintenance Checks, PSP 601A–5. 34 June 19, 2009.

Tasks 30–11–00–101, Detailed Inspection of the Wing Anti-Ice Duct Piccolo-Tube, and 36–21–00–101,

Functional Test of the Leading Edge Thermal Switches, of the Bombardier Challenger 604 Time Limits/ Maintenance Checks, CH 604 TLMC. 13 August 12, 2009.

Tasks 30–11–00–101, Detailed Inspection of the Wing Anti-Ice Duct Piccolo-Tube, and 36–21–00–101,

Functional Test of the Leading Edge Thermal Switches, of the Bombardier Challenger 605 Time Limits/ Maintenance Checks, CH 605 TLMC. 1 August 12, 2009.


## 41657 Federal Register / Vol. 76, No. 136 / Friday, July 15, 2011 / Rules and Regulations

The title pages of these documents do not indicate the revision level or issue date of the documents. Only the Record of Revisions of these documents contains the revision level of these documents.

(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 Bombardier, Inc., 400 Co ˆ teVertu Road West, Dorval, Que  ́ bec H4S 1Y9, Canada; telephone 514–855–5000; fax 514– 855–7401; e-mail thd.crj@aero.bombardier.com ; Internet http:// www.bombardier.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 13,
2011. Ali Bahrami, Manager,Transport Airplane Directorate,Aircraft Certification Service.

[FR Doc. 2011–17402 Filed 7–14–11; 8:45 am]

**BILLING CODE 4910–13–P**



### DEPARTMENT OF TRANSPORTATION

**Federal Aviation Administration**

**14 CFR Part 39**

**[Docket No. FAA–2011–0653; Directorate Identifier 2010–NM–249–AD; Amendment**  **39–16745; AD 2011–14–10]**

**RIN 2120–AA64**



### Airworthiness Directives; Airbus Model **A330–342 Airplanes**

**AGENCY** 

### : Federal Aviation Administration (FAA), Department of Transportation (DOT).

**ACTION** 

### : Final rule; request for
comments.

**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:

* * * * *

Following a query from an operator, investigations revealed that some MSN [manufacturer serial number], for which Airbus modification 40391 was indicated as fully embodied inside the Aircraft Inspection Report (AIR), did not have Modification Proposal (MP–S10437) which is part of this modification embodied in production.

As a result, ALI [Airworthiness Limitation Item] task 533105–01–02 has not been performed on the MSN listed in the applicability section of this AD, which constitutes an unsafe condition.


### * * * * * The unsafe condition is fatigue cracking of the internal structure of the fuselage, which could adversely affect the structural integrity of the airplane. This AD requires actions that are intended to address the unsafe condition described in the MCAI.

**DATES** 

### : This AD becomes effective August 1, 2011.

The Director of the Federal Register approved the incorporation by reference of a certain publication listed in the AD as of August 1, 2011.

We must receive comments on this AD by August 29, 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 W12–140, 1200 New Jersey Avenue, SE., Washington, DC, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. 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 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** 

### : Vladimir Ulyanov, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue, SW., Renton, Washington 98057–3356; telephone (425) 227–1138; fax (425) 227–1149.

**SUPPLEMENTARY INFORMATION** 

### : 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 2010–0173, dated August 17, 2010 (referred to after this as ‘‘the MCAI’’), to correct an unsafe condition for the specified products. The MCAI states:

Airworthiness Limitation Item (ALI) task 533105–01–02 is applicable to aeroplanes on which Airbus modification 40391 has not been embodied in production. The requirements associated to this task are applicable to aeroplanes on which Modification Proposal (MP–S10437) has not been embodied.

Following a query from an operator, investigations revealed that some MSN [manufacturer serial numbers], for which Airbus modification 40391 was indicated as fully embodied inside the Aircraft Inspection Report (AIR), did not have Modification Proposal (MP–S10437) which is part of this modification embodied in production.

As a result, ALI task 533105–01–02 has not been performed on the MSN listed in the applicability section of this AD, which constitutes an unsafe condition.

For the reasons described above, this AD requires repetitive special detailed inspections [for fatigue cracking of the internal structure of the fuselage] corresponding to ALI task 533105–01–02 and the accomplishment of the associated corrective actions. 

### The unsafe condition is fatigue cracking of the internal structure of the fuselage, which could adversely affect the structural integrity of the airplane. The special detailed inspection is defined as an ultrasonic inspection in this AD. The corrective action is repairing any cracks in accordance with a method approved by the FAA or EASA (or its delegated agent). You may obtain further information by examining the MCAI in the AD docket.

Relevant Service Information

Airbus has issued Mandatory Service Bulletin A330–53–3185, including Appendices 01 and 02, dated May 20, 2010. The actions described in this service information are intended to correct the unsafe condition identified in the MCAI. FAA’s Determination and Requirements of This 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 issuing this