22316 Federal Register / Vol. 76, No. 77 / Thursday, April 21, 2011 / Rules and Regulations 

the compliance times specified, unless the 

actions have already been done. 

Initial Inspections 

(g) At the later of the times specified in 

paragraphs (g)(1) and (g)(2) of this AD: Do 

eddy current inspections to detect cracking of 

the center wing upper and lower rainbow 

fittings on the left and right side of the 

airplane. Do the actions in accordance with 

the Accomplishment Instructions of 

Lockheed Service Bulletin 382–57–82, 

Revision 4, including Appendixes A and B, 

dated May 20, 2009. If any crack is found 

during the inspections required by paragraph 

(g) of this AD, before further flight, do the 

actions required by paragraph (k) of this AD. 

(1) Before the accumulation of 15,000 total 

flight hours on the rainbow fitting. 

(2) Within 365 days or 600 flight hours on 

the rainbow fitting after the effective date of 

this AD, whichever occurs first. 

Repetitive Inspection Schedule 

(h) Repeat the inspection required by 

paragraph (g) of this AD at intervals not to 

exceed 3,600 flight hours on the center wing, 

until the rainbow fitting has accumulated 

30,000 total flight hours. If any crack is found 

during the inspections required by paragraph 

(h) of this AD, before further flight, do the 

actions required by paragraph (k) of this AD. 

Rainbow Fitting Replacements 

(i) Before the accumulation of 30,000 flight 

hours on the rainbow fitting, or within 600 

flight hours after the effective date of this AD, 

whichever occurs later: Replace the rainbow 

fitting, do all related investigative actions, 

and do all applicable corrective actions, in 

accordance with paragraph 2.C. of the 

Accomplishment Instructions of Lockheed 

Service Bulletin 382–57–82, Revision 4, 

including Appendix C, dated May 20, 2009, 

except as required by paragraph (l) of this 

AD. Replace the rainbow fitting thereafter at 

intervals not to exceed 30,000 flight hours. 

Post-Replacement Repetitive Inspections 

(j) For upper and lower rainbow fittings 

replaced in accordance with paragraph (i) or 

(k) of this AD: Do the eddy current 

inspections specified in paragraph (g) of this 

AD within 15,000 flight hours after doing the 

replacement and repeat the eddy current 

inspections specified in paragraph (h) of this 

AD thereafter at intervals not to exceed 3,600 

flight hours until the rainbow fittings are 

replaced in accordance with paragraph (i) or 

(k) of this AD. 

Replacement, Related Investigative Actions, 

and Corrective Actions 

(k) If, during any inspection required by 

paragraph (g) or (h) of this AD, any crack is 

detected in the rainbow fitting, before further 

flight, replace the rainbow fitting, do all 

related investigative actions, and do all 

applicable corrective actions, in accordance 

with Paragraph 2.C. of the Accomplishment 

Instructions of Lockheed Service Bulletin 

382–57–82, Revision 4, including Appendix 

C, dated May 20, 2009, except as provided by 

paragraph (l) of this AD. 

Exceptions to Service Bulletin 

(l) Where Lockheed Service Bulletin 382– 

57–82, Revision 4, including Appendixes A, 

B, and C, dated May 20, 2009, specifies to 

contact the manufacturer for disposition of 

certain repair conditions or does not specify 

corrective actions if certain conditions are 

found, this AD requires repairing those 

conditions using a method approved by the 

Manager, Atlanta Aircraft Certification Office 

(ACO), FAA. For a repair method to be 

approved by the Manager, Atlanta ACO, as 

required by this paragraph, the Manager’s 

approval letter must specifically refer to this 

AD. 

Credit for Actions Accomplished in 

Accordance With Previous Service 

Information 

(m) Actions accomplished before the 

effective date of this AD in accordance with 

Lockheed Service Bulletin 382–57–82, 

Revision 3, including Appendixes A, B, and 

C, dated April 25, 2008, are acceptable for 

compliance with the corresponding 

requirements of this AD. 

Alternative Methods of Compliance 

(AMOCs) 

(n)(1) The Manager, Atlanta ACO, FAA, 

has the authority to approve AMOCs for this 

AD, if requested using the procedures found 

in 14 CFR 39.19. Send information to Attn: 

Carl Gray, Aerospace Engineer, Airframe 

Branch, ACE–117A, FAA, Atlanta Aircraft 

Certification Office, 1701 Columbia Avenue, 

College Park, Georgia 30337; telephone (404) 

474–5554; fax (404 474–5606. 

(2) Before using any approved AMOC, 

notify your appropriate principal inspector, 

the manager of the local flight standards 

district office/certificate holding district 

office. 

Material Incorporated by Reference 

(o) You must use Lockheed Service 

Bulletin 382–57–82, Revision 4, including 

Appendixes A, B, and C, dated May 20, 2009, 

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 Lockheed Martin 

Corporation/Lockheed Martin Aeronautics 

Company, Airworthiness Office, Dept. 6A0M, 

Zone 0252, Column P–58, 86 S. Cobb Drive, 

Marietta, Georgia 30063; telephone 770–494– 

5444; fax 770–494–5445; e-mail 

ams.portal@lmco.com; Internet http:// 

www.lockheedmartin.com/ams/tools/ 

TechPubs.html. 

(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 12, 

2011. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2011–9285 Filed 4–20–11; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2011–0379; Directorate 

Identifier 2011–CE–007–AD; Amendment 

39–16670; AD 2011–09–08] 

RIN 2120–AA64 

Airworthiness Directives; Pacific 

Aerospace Limited Model 750XL 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), 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) 

issued by the aviation authority of 

another country to identify and correct 

an unsafe condition on an aviation 

product. The MCAI describes the unsafe 

condition as: 

This AD is prompted by a report from the 

manufacturer of finding cracks in rudder 

pedal assemblies at the quadrant attachment 

weld on early 750 XL aircraft. 

This AD requires actions that are 

intended to address the unsafe 

condition described in the MCAI. 

DATES: This AD becomes effective May 

2, 2011. 

On May 2, 2011, the Director of the 

Federal Register approved the 

incorporation by reference of certain 

publications listed in this AD. 

We must receive comments on this 

AD by June 6, 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 

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Federal Register / Vol. 76, No. 77 / Thursday, April 21, 2011 / Rules and Regulations 22317 

Avenue, SE., Washington, DC 20590, 

between 9 a.m. and 5 p.m., Monday 

through Friday, except Federal holidays. 

For service information identified in 

this AD, contact Pacific Aerospace 

Limited, Hamilton Airport, Private Bag 

3027 Hamilton 3240, New Zealand; 

telephone: +64 7 843 6144; fax: +64 7 

843 6134; e-mail: 

pacific@aerospace.co.nz; Internet: 

http://www.aerospace.co.nz/. You may 

review copies of the referenced service 

information at the FAA, Small Airplane 

Directorate, 901 Locust, Kansas City, 

Missouri 64106. For information on the 

availability of this material at the FAA, 

call 816–329–4148. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http:// 

www.regulations.gov; or in person at the 

Docket Management Facility 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 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: Karl 

Schletzbaum, Aerospace Engineer, FAA, 

Small Airplane Directorate, 901 Locust, 

Room 301, Kansas City, Missouri 64106; 

telephone: (816) 329–4146; fax: (816) 

329–4090. 

SUPPLEMENTARY INFORMATION: 

Discussion 

The Civil Aviation Authority (CAA), 

which is the airworthiness authority for 

New Zealand, has issued AD DCA/ 

750XL/14, dated March 31, 2011, 

(referred to after this as ‘‘the MCAI’’), to 

correct an unsafe condition for the 

specified products. The MCAI states: 

This AD is prompted by a report from the 

manufacturer of finding cracks in rudder 

pedal assemblies at the quadrant attachment 

weld on early 750 XL aircraft. 

The MCAI requires inspecting the lefthand and right-hand rudder pedal 

assemblies for cracks and incorporating 

a modification repair scheme if any 

cracks are found. You may obtain 

further information by examining the 

MCAI in the AD docket. 

Relevant Service Information 

Pacific Aerospace Limited has issued 

Mandatory Service Bulletin PACSB/XL/ 

050, Issue 1, dated December 15, 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 the 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 this State of 

Design Authority, they have notified us 

of the unsafe condition described in the 

MCAI and service information 

referenced above. We are issuing this 

AD because we evaluated all 

information provided by the State of 

Design Authority and determined the 

unsafe condition exists and is likely to 

exist or develop on other products of the 

same type design. 

Differences Between This AD and the 

MCAI or Service Information 

We have reviewed the MCAI and 

related service information and, in 

general, agree with their substance. But 

we might have found it necessary to use 

different words from those in the MCAI 

to ensure the AD is clear for U.S. 

operators and is enforceable. In making 

these changes, we do not intend to differ 

substantively from the information 

provided in the MCAI and related 

service information. 

We might have also required different 

actions in this AD from those in the 

MCAI in order to follow FAA policies. 

Any such differences are described in a 

separate paragraph of the AD. These 

requirements take precedence over 

those copied from the MCAI. 

FAA’s Determination of the Effective 

Date 

An unsafe condition exists that 

requires the immediate adoption of this 

AD. The FAA has found that the risk to 

the flying public justifies waiving notice 

and comment prior to adoption of this 

rule because cracks in the rudder pedal 

assemblies could cause the rudder pedal 

assembly to fail, which could result in 

loss of control. Therefore, we 

determined that notice and opportunity 

for public comment before issuing this 

AD are impracticable and that good 

cause exists for making this amendment 

effective in fewer than 30 days. 

Comments Invited 

This AD is a final rule that involves 

requirements affecting flight safety, and 

we did not precede it by notice and 

opportunity for public comment. We 

invite you to send any written relevant 

data, views, or arguments about this AD. 

Send your comments to an address 

listed under the ADDRESSES section. 

Include ‘‘Docket No. FAA–2011–0379; 

Directorate Identifier 2011–CE–007–AD’’ 

at the beginning of your comments. We 

specifically invite comments on the 

overall regulatory, economic, 

environmental, and energy aspects of 

this AD. We will consider all comments 

received by the closing date and may 

amend this AD because of those 

comments. 

We will post all comments we 

receive, without change, to http:// 

www.regulations.gov, including any 

personal information you provide. We 

will also post a report summarizing each 

substantive verbal contact we receive 

about this AD. 

Costs of Compliance 

We estimate that this AD will affect 

15 products of U.S. registry. We also 

estimate that it would take about 4 

work-hours per product to comply with 

the basic requirements of this AD. The 

average labor rate is $85 per work-hour. 

Required parts would cost about $1,269 

per product. 

Based on these figures, we estimate 

the cost of the AD on U.S. operators to 

be $24,135 or $1,609 per product. 

Authority for This Rulemaking 

Title 49 of the United States Code 

specifies the FAA’s authority to issue 

rules on aviation safety. Subtitle I, 

section 106, describes the authority of 

the FAA Administrator. ‘‘Subtitle VII: 

Aviation Programs,’’ describes in more 

detail the scope of the Agency’s 

authority. 

We are issuing this rulemaking under 

the authority described in ‘‘Subtitle VII, 

Part A, Subpart III, Section 44701: 

General requirements.’’ Under that 

section, Congress charges the FAA with 

promoting safe flight of civil aircraft in 

air commerce by prescribing regulations 

for practices, methods, and procedures 

the Administrator finds necessary for 

safety in air commerce. This regulation 

is within the scope of that authority 

because it addresses an unsafe condition 

that is likely to exist or develop on 

products identified in this rulemaking 

action. 

Regulatory Findings 

We determined that this 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 

DOT Regulatory Policies and Procedures 

(44 FR 11034, February 26, 1979); and 

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22318 Federal Register / Vol. 76, No. 77 / Thursday, April 21, 2011 / Rules and Regulations 

(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. 

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: 

2011–09–08 Pacific Aerospace Limited: 

Amendment 39–16670; Docket No. 

FAA–2011–0379; Directorate Identifier 

2011–CE–007–AD. 

Effective Date 

(a) This airworthiness directive (AD) 

becomes effective May 2, 2011. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to Pacific Aerospace 

Limited Model 750XL airplanes, all serial 

numbers through 111, certificated in any 

category. 

Subject 

(d) Air Transport Association of America 

(ATA) Code 27: Flight Controls. 

Reason 

(e) The mandatory continuing 

airworthiness information (MCAI) states: 

This AD is prompted by a report from the 

manufacturer of finding cracks in rudder 

pedal assemblies at the quadrant attachment 

weld on early 750 XL aircraft. 

The MCAI requires inspecting the left-hand 

(LH) and right-hand (RH) rudder pedal 

assemblies for cracks and incorporating a 

modification repair scheme if any cracks are 

found. You may obtain further information 

by examining the MCAI in the AD docket. 

Actions and Compliance 

(f) Unless already done, do the following 

actions: 

(1) Inspect the quadrant welds in the LH 

rudder pedal assembly, part number (P/N) 

11–45711–1, and the RH rudder pedal 

assembly, P/N 11–45713–1, for cracks at the 

following times following Pacific Aerospace 

Limited Mandatory Service Bulletin PACSB/ 

XL/050, Issue 1, dated December 15, 2010: 

(i) Initially before further flight after the 

effective date of this AD. 

(ii) Repetitively thereafter at intervals not 

to exceed 300 hours time-in-service (TIS) 

until the modification repair scheme required 

in paragraph (f)(2) of this AD is incorporated. 

(2) Incorporate modification repair scheme 

Pacific Aerospace Drawing Number 11– 

03221/22, dated December 3, 2010, as 

specified in Pacific Aerospace Limited 

Mandatory Service Bulletin PACSB/XL/050, 

Issue 1, dated December 15, 2010, at the 

following time: 

(i) Before further flight after any inspection 

required in paragraphs (f)(1)(i) or (f)(1)(ii) of 

this AD if any cracks are found. 

(ii) Within the next 1,200 hours TIS after 

the effective date of this AD or within the 

next 12 months after the effective date of this 

AD, whichever occurs first, if no cracks are 

found during any inspection required in 

paragraphs (f)(1)(i) or (f)(1)(ii) of this AD. 

Incorporating modification repair scheme 

Pacific Aerospace Drawing Number 11– 

03221/22, dated December 3, 2010, 

terminates the repetitive inspections required 

in paragraph (f)(1)(ii) of this AD. 

(3) You may incorporate modification 

repair scheme Pacific Aerospace Drawing 

Number 11–03221/22, dated December 3, 

2010, at any time after the initial inspection 

required in paragraph (f)(1)(i) of this AD but 

no later than the compliance time specified 

in paragraph (f)(2)(ii) of this AD as long as 

no cracks were found. As required in 

paragraph (f)(2)(i) of this AD, the 

modification repair scheme must be 

incorporated before further flight if cracks are 

found. 

FAA AD Differences 

Note: This AD differs from the MCAI and/ 

or service information as follows: The MCAI 

Civil Aviation Authority (CAA) AD DCA/ 

750XL/14, dated March 31, 2011, and the 

applicable service bulletin specifies repair of 

the rudder pedal assembly if cracks are found 

exceeding certain limits and allows 

continued flight for a specified time if cracks 

are found in the rudder pedal assembly that 

do not exceed certain limits. This AD does 

not allow continued flight if any crack is 

found. The FAA policy is to disallow 

airplane operation when known cracks exist 

in primary structure, unless the ability to 

sustain ultimate load with these cracks is 

proven. The rudder pedal assembly is 

considered primary structure, and the FAA 

has not received any analysis to prove that 

ultimate load can be sustained with cracks in 

this area. 

Other FAA AD Provisions 

(g) The following provisions also apply to 

this AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, Standards Office, 

FAA, has the authority to approve AMOCs 

for this AD, if requested using the procedures 

found in 14 CFR 39.19. Send information to 

Attn: Karl Schletzbaum, Aerospace Engineer, 

FAA, Small Airplane Directorate, 901 Locust, 

Room 301, Kansas City, Missouri 64106; 

telephone: (816) 329–4146; fax: (816) 329– 

4090. Before using any approved AMOC on 

any airplane to which the AMOC applies, 

notify your appropriate principal inspector 

(PI) in the FAA Flight Standards District 

Office (FSDO), or lacking a PI, your local 

FSDO. 

(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. 

(3) Reporting Requirements: For any 

reporting requirement in this AD, a federal 

agency may not conduct or sponsor, and a 

person is not required to respond to, nor 

shall a person be subject to a penalty for 

failure to comply with a collection of 

information subject to the requirements of 

the Paperwork Reduction Act unless that 

collection of information displays a current 

valid OMB Control Number. The OMB 

Control Number for this information 

collection is 2120–0056. Public reporting for 

this collection of information is estimated to 

be approximately 5 minutes per response, 

including the time for reviewing instructions, 

completing and reviewing the collection of 

information. All responses to this collection 

of information are mandatory. Comments 

concerning the accuracy of this burden and 

suggestions for reducing the burden should 

be directed to the FAA at: 800 Independence 

Ave., SW., Washington, DC 20591, Attn: 

Information Collection Clearance Officer, 

AES–200. 

Related Information 

(h) Refer to MCAI Civil Aviation Authority 

(CAA) AD DCA/750XL/14, dated March 31, 

2011, and Pacific Aerospace Limited 

Mandatory Service Bulletin PACSB/XL/050, 

Issue 1, dated December 15, 2010, for related 

information. 

Material Incorporated by Reference 

(i) You must use Pacific Aerospace Limited 

Mandatory Service Bulletin PACSB/XL/050, 

Issue 1, dated December 15, 2010, and Pacific 

Aerospace Drawing Number 11–03221/22, 

dated December 3, 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 Pacific Aerospace Limited, 

Hamilton Airport, Private Bag HN3027 

Hamilton, New Zealand; telephone: 0064 7 

843 6144; fax: 0064 7 843 6134; Internet: 

http://www.aerospace.co.nz/. 

(3) You may review copies of the 

referenced service information at the FAA, 

Small Airplane Directorate, 901 Locust, 

Kansas City, Missouri 64106. For information 

on the availability of this material at the 

FAA, call 816–329–4148. 

(4) You may also review copies of the 

service information incorporated by reference 

for this AD at the National Archives and 

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Federal Register / Vol. 76, No. 77 / Thursday, April 21, 2011 / Rules and Regulations 22319 

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 Kansas City, Missouri on April 

13, 2011. 

Earl Lawrence, 

Manager, Small Airplane Directorate, Aircraft 

Certification Service. 

[FR Doc. 2011–9429 Filed 4–20–11; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2010–1309; Directorate 

Identifier 2010–NM–060–AD; Amendment 

39–16662; AD 2011–08–12] 

RIN 2120–AA64 

Airworthiness Directives; Airbus Model 

A330–300, A340–200, and A340–300 

Series 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: 

Surface defects were visually detected on 

the rudder of one Airbus A319 and one A321 

in-service aeroplane. Investigation has 

determined that the defects reported on both 

rudders corresponded to areas that had been 

reworked in production. The investigation 

confirmed that the defects were the result of 

de-bonding between the skin and honeycomb 

core. Such reworks were also performed on 

some rudders fitted on A330–300 and A340– 

200/–300 aeroplanes. 

An extended de-bonding, if not detected 

and corrected, may degrade the structural 

integrity of the rudder. The loss of the rudder 

leads to degradation of the handling qualities 

and reduces the controllability of the 

aeroplane. 

* * * * * 

We are issuing this AD to require 

actions to correct the unsafe condition 

on these products. 

DATES: This AD becomes effective May 

26, 2011. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of May 26, 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: 

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 

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 13, 2011 (76 FR 

2284). That NPRM proposed to correct 

an unsafe condition for the specified 

products. The MCAI states: 

Surface defects were visually detected on 

the rudder of one Airbus A319 and one A321 

in-service aeroplane. Investigation has 

determined that the defects reported on both 

rudders corresponded to areas that had been 

reworked in production. The investigation 

confirmed that the defects were the result of 

de-bonding between the skin and honeycomb 

core. Such reworks were also performed on 

some rudders fitted on A330–300 and A340– 

200/–300 aeroplanes. 

An extended de-bonding, if not detected 

and corrected, may degrade the structural 

integrity of the rudder. The loss of the rudder 

leads to degradation of the handling qualities 

and reduces the controllability of the 

aeroplane. 

EASA AD 2009–0156 required inspections 

of specific areas and, depending on findings, 

the application of corrective actions for those 

rudders where production reworks have been 

identified. 

This AD retains the requirements of EASA 

AD 2009–0156, which is superseded, and in 

addition requires for the vacuum loss hole 

restoration: 

—A local ultrasonic inspection for reinforced 

area instead of the local thermography 

inspection, which is maintained for nonreinforced areas, and 

—An additional work for aeroplanes on 

which this thermography inspection has 

been performed in the reinforced area. 

The inspections include vacuum loss 

inspections and repetitive elasticity 

laminate checker inspections for defects 

including de-bonding between the skin 

and honeycomb core of the rudder, and 

ultrasonic inspections for defects on 

rudders on which temporary restoration 

with resin or permanent vacuum loss 

hole restoration has been performed. 

The corrective action is repair, if 

necessary. 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 

Currently, there are no affected 

airplanes on the U.S. Register. However, 

if an affected airplane is imported and 

placed on the U.S. Register in the future, 

the required actions would take about 

21 work hours, at an average labor rate 

of $85 per work hour. Based on these 

figures, we estimate the cost of this AD 

to be $1,785 per airplane. 

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 

WReier-Aviles on DSKGBLS3C1PROD with RULES