39248 Federal Register / Vol. 76, No. 129 / Wednesday, July 6, 2011 / Rules and Regulations 

OTS REGULATIONS THAT WILL BE ENFORCED BY THE FDIC—TITLE 12 

Part or section Chapter V—Office of Thrift Supervision, Department of the Treasury 

Part 507 (except 507.3(b)) ................................. Restrictions on Post-Employment Activities of Senior Examiners. 

Part 508 .............................................................. Removals, Suspensions and Prohibitions where a Crime is Charged. 

Part 509 (except 509.1(e)(3), 509.100(b), 

509.103(b)(2), and Subparts C and D).

Rules of Practice and Procedure in Adjudicatory Proceedings. 

Part 512 .............................................................. Rules for Investigative Proceedings and Formal Examination Proceedings. 

Part 513 .............................................................. Practice Before the Office. 

Part 516 (except 516.45(a)(3), and 516.290(b)) Application Processing Procedure. 

Part 528 .............................................................. Nondiscrimination Requirements. 

Part 533 (except 533.1(b)(2) and 533.10) .......... Disclosure and Reporting of CRA-related Agreements. 

Part 536 .............................................................. Consumer Protection in Sales of Insurance. 

Part 550 (only 550.10(b)) ................................... Fiduciary Powers of Savings Associations. 

Part 551 .............................................................. Recordkeeping for Securities Transactions. 

Part 555 (only Subpart B, except 555.310(b)) ... Electronic Operations. 

Part 557 (only Subpart C) .................................. Deposits. 

Part 558 .............................................................. Possession by Conservators and Receivers for Federal and State Savings Associations. 

Part 559 (only Subpart B) ................................... Subordinate Organizations. 

Part 560 (only 560.1, 560.3 and Subpart B) ...... Lending and Investment. 

Part 561 (except 561.18(b) and 561.34) ............ Definitions for Regulations Affecting All Savings Associations. 

Part 562 (except 562.4(b)(2)) ............................. Regulatory Reporting Standards. 

Part 563 12 (except 563.161 as to service corporations, 563.172(b)(1), 563.180(d)(4), 

563.555 (definition of ‘‘Troubled condition’’ 

(2)).

Savings Associations—Operations. 

Part 563b ............................................................ Conversions from Mutual to Stock Form. 

Part 563c ............................................................ Accounting Requirements. 

Part 563d (except 563d.2) .................................. Securities of Savings Associations. 

Part 563e ............................................................ Community Reinvestment. 

Part 563f (except 563f.2(o)(1)) ........................... Management Official Interlocks. 

Part 563g ............................................................ Securities Offerings. 

Part 564 .............................................................. Appraisals. 

Part 565 (except 565.5(h)) ................................. Prompt Corrective Action. 

Part 567 .............................................................. Capital. 

Part 568 .............................................................. Security Procedures. 

Part 569 .............................................................. Proxies. 

Part 570 .............................................................. Safety and Soundness Guidelines Establishing Standards for Safety and Soundness. 

Part 57113 (except 571.30(a)(1)(iii), (iv), and (v)) Fair Credit Reporting. 

Part 572 .............................................................. Loans in Areas Having Special Flood Hazards. 

Part 573 14 ........................................................... Privacy of Consumer Information. 

Part 574 (except provisions applicable to 

SLHCs).

Acquisition of Control of Savings Associations. 

Part 590 .............................................................. Preemption of State Usury Laws. 

Part 591 .............................................................. Preemption of Due-on-Sale Laws. 

Dated: June 15, 2011. 

John Walsh, 

Acting Comptroller of the Currency. 

By order of the Board of Directors. 

Dated at Washington, DC, this 14th day of 

June, 2011. 

Federal Deposit Insurance Corporation. 

Robert E. Feldman, 

Executive Secretary. 

[FR Doc. 2011–16875 Filed 7–5–11; 8:45 am] 

BILLING CODE 4810–33–P; 6714–01–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2010–1197; Directorate 

Identifier 2010–NM–044–AD; Amendment 

39–16736; AD 2011–14–01] 

RIN 2120–AA64 

Airworthiness Directives; Airbus Model 

A300 B4–600, B4–600R, and F4–600R 

Series Airplanes, and Model C4–605R 

Variant F Airplanes (Collectively Called 

A300–600 Series Airplanes); and Model 

A310 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: 

An operator of an A300–600 aeroplane 

reported finding a cracked pylon fuel drain 

pipe on engine #1. * * * 

* * * The pipe drains the double wall of 

the wing-to-pylon junction in the event of 

fuel leakage. 

After investigation, it was concluded that 

the damage of the pylon fuel drain pipe had 

been caused by chafing of the pipe against 

over-length screws that had been installed in 

accordance with the Illustrated Parts 

Catalogue (IPC) during a maintenance phase 

of the Lower Aft Pylon Fairing (LAPF). 

This condition, if not detected and 

corrected, could, in combination with fuel 

leakage in the pylon, lead to an accumulation 

of fuel in the lowest point of the LAPF. As 

high temperatures are present within the 

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Federal Register / Vol. 76, No. 129 / Wednesday, July 6, 2011 / Rules and Regulations 39249 

LAPF, and without ventilation, this could 

result in fuel (vapour) ignition and 

consequent fire. 

* * * * * 

We are issuing this AD to require 

actions to correct the unsafe condition 

on these products. 

DATES: This AD becomes effective 

August 10, 2011. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of August 10, 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 December 10, 2010 (75 FR 

76926). That NPRM proposed to correct 

an unsafe condition for the specified 

products. The MCAI states: 

An operator of an A300–600 aeroplane 

reported finding a cracked pylon fuel drain 

pipe on engine #1.The pipe, Part Number 

(P/N) A71715020, had separated and the end 

was found 5.5 inches from the pylon aft 

bulkhead. A similar case was also reported 

on an A300F4–608ST aeroplane. 

The affected pylon fuel drain pipe runs 

from the top of the pylon primary structure 

to the aft part of the pylon rear secondary 

structure and is partly attached under the 

pylon lower spar. The pipe drains the double 

wall of the wing-to-pylon junction in the 

event of fuel leakage. 

After investigation, it was concluded that 

the damage of the pylon fuel drain pipe had 

been caused by chafing of the pipe against 

over-length screws that had been installed in 

accordance with the Illustrated Parts 

Catalogue (IPC) during a maintenance phase 

of the Lower Aft Pylon Fairing (LAPF). 

This condition, if not detected and 

corrected, could, in combination with fuel 

leakage in the pylon, lead to an accumulation 

of fuel in the lowest point of the LAPF. As 

high temperatures are present within the 

LAPF, and without ventilation, this could 

result in fuel (vapour) ignition and 

consequent fire. 

To address and correct this unsafe 

condition, EASA * * * required an 

inspection [for missing pipes, or distortions 

or holes] of the pylon fuel drain pipe and the 

attachment screws and, depending on 

findings, the necessary corrective actions. In 

case over-length screws are found to be 

installed, depending on location and 

aeroplane configuration, these must be 

replaced. 

* * * * * 

Required actions also include visually 

inspecting to determine the length and 

part number of the drain pipe 

attachment screws on the LAPF on the 

left- and right-hand pylons. Corrective 

actions include replacing or repairing 

the pipe, or replacing screws with 

incorrect part numbers with new 

screws. 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 

considered the comments received. 

Request To Extend the Compliance 

Time 

UPS requested that we extend the 

compliance time from 30 days to 30 

months after the effective date of the 

AD. Per the commenter, the NPRM 

stated that the over-length screws 

installed on the affected aircraft were 

installed in accordance with the 

illustrated parts catalog (IPC), and that 

the correct attachment screws are 

clearly identified in the UPS A300–600 

IPC, so there is a minimal probability of 

installing an over-length screw. The 

commenter stated that the compliance 

time of 30 days is too restrictive and 

believes that extending the threshold to 

30 months for those operators whose 

IPC does not list an over-length fastener 

would provide an equivalent level of 

safety and better fit within an operator’s 

routine maintenance program and 

eliminate any undue burden associated 

with a restrictive timetable. 

We do not agree to extend the 

compliance time. The FAA received 

information confirming that over-length 

screws could have been introduced in 

production due to some erroneous 

drawings. Further, before 2007, not all 

IPCs were correct. Some of the IPCs for 

aircraft fitted with Pratt & Whitney 

engines were corrected in 2007. All IPCs 

were checked in 2010, and remaining 

erroneous IPCs were corrected. 

Although UPS may have the correct IPC, 

since some over-length screws could 

have been installed during production, 

a fleet inspection is needed to address 

the identified unsafe condition. 

However, under the provisions of 

paragraph (k) of this AD, we will 

consider requests for approval of an 

extension of the compliance time if 

sufficient data are submitted to 

substantiate that the new compliance 

time would provide an acceptable level 

of safety. We have not changed the AD 

in this regard. 

Request To Use Thicker Washer as 

Advised in Service Information Letter 

UPS requested FAA concurrence that 

using an alternative washer, P/N 

NSA5149–3, as recommended by Airbus 

in Service Information Letter 54–035, 

Revision 01, dated July 9, 2010, will not 

have an impact on the AD. This washer 

would be used in lieu of P/N NSA5149– 

4 under the head of the attachment 

screws, to prevent cracking of the LAPF. 

We partially agree with the 

commenter’s request. The alternative 

washer is a recommended improvement, 

but not a modification addressing an 

unsafe condition/airworthiness issue. 

As the Service Information Letter 

mentions, both washers are fully 

interchangeable; the last IPC update 

(2010) also reflects this 

interchangeability. Therefore, we 

confirm that use of either washer is 

adequate. In this regard, and to avoid 

the need for an alternative method of 

compliance (AMOC) on this issue in the 

future, we have added the washer 

having P/N NSA5149–3 to paragraphs 

(g)(1) and (g)(2) of this AD. 

Conclusion 

We reviewed the available data, 

including the comments received, and 

determined that air safety and the 

public interest require adopting the AD 

with the change described previously. 

We determined that this change will not 

increase the economic burden on any 

operator or increase the scope of the AD. 

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 

168 products of U.S. registry. We also 

estimate that it will take about 4 workmstockstill on DSK4VPTVN1PROD with RULES

39250 Federal Register / Vol. 76, No. 129 / Wednesday, July 6, 2011 / Rules and Regulations 

hours 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 $57,120, or $340 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 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: 

2011–14–01 Airbus: Amendment 39–16736. 

Docket No. FAA–2010–1197; Directorate 

Identifier 2010–NM–044–AD. 

Effective Date 

(a) This airworthiness directive (AD) 

becomes effective August 10, 2011. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to Airbus Model A300 

B4–601, B4–603, B4–620, and B4–622 

airplanes; Model A300 B4–605R and B4– 

622R airplanes; Model A300 F4–605R and 

F4–622R airplanes; Model A300 C4–605R 

Variant F airplanes; and Model A310–203, 

–204, –221, –222, –304, –322, –324, and –325 

airplanes; certificated in any category; all 

serial numbers. 

Subject 

(d) Air Transport Association (ATA) of 

America Code 54: Nacelles/pylons. 

Reason 

(e) The mandatory continuing 

airworthiness information (MCAI) states: 

An operator of an A300–600 aeroplane 

reported finding a cracked pylon fuel drain 

pipe on engine #1. * * * 

* * * The pipe drains the double wall of 

the wing-to-pylon junction in the event of 

fuel leakage. 

After investigation, it was concluded that 

the damage of the pylon fuel drain pipe had 

been caused by chafing of the pipe against 

over-length screws that had been installed in 

accordance with the Illustrated Parts 

Catalogue (IPC) during a maintenance phase 

of the Lower Aft Pylon Fairing (LAPF). 

This condition, if not detected and 

corrected, could, in combination with fuel 

leakage in the pylon, lead to an accumulation 

of fuel in the lowest point of the LAPF. As 

high temperatures are present within the 

LAPF, and without ventilation, this could 

result in fuel (vapour) ignition and 

consequent fire. 

* * * * * 

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. 

Inspection and Corrective Actions 

(g) Within 30 days after the effective date 

of this AD, do a general visual inspection for 

missing pipes, or distortions or holes, of the 

fuel drain pipes of the LAPF, and if no 

missing pipes, distortions, and holes are 

found, do a general visual inspection to 

determine the length and part number of the 

drain pipe attachment screws on the LAPF 

on the left-hand and right-hand pylons, in 

accordance with the Accomplishment 

Instructions of Airbus Mandatory Service 

Bulletin A300–54A6039, Revision 01, dated 

March 11, 2010 (for Model A300–600 series 

airplanes); or A310–54A2040, Revision 02, 

dated June 10, 2010 (for Model A310 series 

airplanes). 

(1) If missing pipes, distortions, or holes of 

the fuel drain pipes are detected during any 

inspection required by paragraph (g) of this 

AD, before further flight, replace the drain 

pipe, in accordance with the 

Accomplishment Instructions of Airbus 

Mandatory Service Bulletin A300–54A6039, 

Revision 01, dated March 11, 2010 (for Model 

A300–600 series airplanes); or A310– 

54A2040, Revision 02, dated June 10, 2010 

(for Model A310 series airplanes); or contact 

Airbus for repair instructions and do the 

repair; except where the applicable service 

bulletin specifies using washers having part 

number (P/N) NSA5149–4, washers having 

P/N NSA5149–3 may alternatively be used. 

(2) If screw length is outside the 

measurement specified in the 

Accomplishment Instructions of Airbus 

Mandatory Service Bulletin A300–54A6039, 

Revision 01, dated March 11, 2010 (for Model 

A300–600 series airplanes); or A310– 

54A2040, Revision 02, dated June 10, 2010 

(for Model A310 series airplanes); or screws 

having incorrect part numbers are found 

during any inspection required by paragraph 

(g) of this AD, before further flight, replace 

the screws with screws having P/N 

NAS1102E3–10, NAS1102E3–12, or 

NAS560HK3–2, as applicable to location and 

airplane (engine) configuration, in 

accordance with the Accomplishment 

Instructions of Airbus Mandatory Service 

Bulletin A300–54A6039, Revision 01, dated 

March 11, 2010 (for Model A300–600 series 

airplanes); or A310–54A2040, Revision 02, 

dated June 10, 2010 (for Model A310 series 

airplanes); except where the applicable 

service bulletin specifies using washers 

having P/N NSA5149–4, washers having P/N 

NSA5149–3 may alternatively be used. 

(h) As of the effective date of this AD, do 

not install screws on the LAPF, other than 

screws having P/N NAS1102E3–10, 

NAS1102E3–12, or NAS560HK3–2, as 

applicable to location and airplane (engine) 

configuration, in accordance with the 

Accomplishment Instructions of Airbus 

Mandatory Service Bulletin A300–54A6039, 

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Federal Register / Vol. 76, No. 129 / Wednesday, July 6, 2011 / Rules and Regulations 39251 

Revision 01, dated March 11, 2010 (for Model 

A300–600 series airplanes); or A310– 

54A2040, Revision 02, dated June 10, 2010 

(for Model A310 series airplanes). 

Credit for Actions Accomplished in 

Accordance With Previous Service 

Information 

(i) Actions accomplished before the 

effective date of this AD in accordance with 

the service bulletins identified in table 1 of 

this AD are considered acceptable for 

compliance with the corresponding actions 

specified in this AD. 

TABLE 1—CREDIT SERVICE BULLETINS

For model— Airbus Mandatory Service Bulletin— Revision— Dated— 

A300–600 series airplanes ................................... A300–54A6039 .................................................... Original .................. January 19, 2010. 

A310 series airplanes ........................................... A310–54A2040 .................................................... Original .................. January 19, 2010. 

A310 series airplanes ........................................... A310–54A2040 .................................................... 01 ........................... March 11, 2010. 

No Reporting 

(j) Although Airbus Mandatory Service 

Bulletins A300–54A6039, Revision 01, dated 

March 11, 2010; and A310–54A2040, 

Revision 02, dated June 10, 2010; specify to 

submit certain information to the 

manufacturer, this AD does not include that 

requirement. 

FAA AD Differences 

Note 1: This AD differs from the MCAI 

and/or service information as follows: 

Although the MCAI or service information 

tells you to submit information to the 

manufacturer, paragraph (j) of this AD does 

not require that information. 

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 

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. Before using any approved AMOC 

on any airplane to which the AMOC applies, 

notify your principal maintenance inspector 

(PMI) or principal avionics inspector (PAI), 

as appropriate, or lacking a principal 

inspector, your local Flight Standards District 

Office. The AMOC approval letter must 

specifically reference this AD. 

(2) Airworthy Product: For any requirement 

in this AD to obtain corrective actions from 

a manufacturer or other source, use these 

actions if they are FAA-approved. Corrective 

actions are considered FAA-approved if they 

are approved by the State of Design Authority 

(or their delegated agent). You are required 

to assure the product is airworthy before it 

is returned to service. 

Related Information 

(l) Refer to MCAI European Aviation Safety 

Agency Airworthiness Directive 2010–0085, 

dated May 3, 2010; Airbus Mandatory 

Service Bulletin A300–54A6039, Revision 01, 

dated March 11, 2010; and Airbus Mandatory 

Service Bulletin A310–54A2040, Revision 02, 

dated June 10, 2010; for related information. 

Material Incorporated by Reference 

(m) You must use Airbus Mandatory 

Service Bulletin A300–54A6039, Revision 01, 

excluding Appendix 01 and including 

Appendices 02 and 03, dated March 11, 

2010; or Airbus Mandatory Service Bulletin 

A310–54A2040, Revision 02, excluding 

Appendix 01 and including Appendices 02 

and 03, dated June 10, 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 

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 June 16, 

2011. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2011–15991 Filed 7–5–11; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2010–1203; Directorate 

Identifier 2010–NM–168–AD; Amendment 

39–16738; AD 2011–14–03] 

RIN 2120–AA64 

Airworthiness Directives; The Boeing 

Company Model DC–9–81 (MD–81), 

DC–9–82 (MD–82), DC–9–83 (MD–83), 

DC–9–87 (MD–87), and MD–88 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for the 

products listed above. This AD requires 

repetitive inspections for cracking of the 

left and right upper center skin panels 

of the horizontal stabilizer, and 

corrective action if necessary. This AD 

was prompted by a report of a crack 

found in the upper center skin panel at 

the aft inboard corner of a right 

horizontal stabilizer. We are issuing this 

AD to detect and correct cracks in the 

horizontal stabilizer upper center skin 

panel. Uncorrected cracks might 

ultimately lead to the loss of overall 

structural integrity of the horizontal 

stabilizer. 

DATES: This AD is effective August 10, 

2011. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in the AD 

as of August 10, 2011. 

ADDRESSES: 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; 

phone: 206–544–5000, extension 2; fax: 

206–766–5683; e-mail: 

dse.boecom@boeing.com; Internet 

https://www.myboeingfleet.com. You 

may review copies of the referenced 

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