Federal Register / Vol. 76, No. 125 / Wednesday, June 29, 2011 / Proposed Rules 38069 

Manual, CSP A–012; and the service bulletins listed in table 6 of this AD; for 

related information. 

TABLE 6—RELATED SERVICE INFORMATION

Document Revision Date 

Bombardier Alert Service Bulletin A601R–29–029 .............................................. B ............................................................ May 11, 2010. 

Bombardier Alert Service Bulletin A601R–29–031 .............................................. A ............................................................ March 26, 2009. 

Bombardier Alert Service Bulletin A601R–32–103 .............................................. D ........................................................... May 11, 2010. 

Bombardier Service Bulletin 601R–29–032 ......................................................... A ............................................................ January 26, 2010. 

Bombardier Service Bulletin 601R–29–033 ......................................................... A ............................................................ May 11, 2010. 

Bombardier Service Bulletin 601R–29–035 ......................................................... A ............................................................ December 8, 2010. 

Bombardier Service Bulletin 601R–32–106 ......................................................... A ............................................................ May 11, 2010. 

Bombardier Service Bulletin 601R–32–107 ......................................................... B ............................................................ December 8, 2010. 

Issued in Renton, Washington, on June 16, 

2011. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2011–16365 Filed 6–28–11; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2011–0647; Directorate 

Identifier 2010–NM–193–AD] 

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 A310 

Series Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to adopt a new 

airworthiness directive (AD) for the 

products listed above. This proposed 

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 an Airbus A319 and an 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 A310 and A300–600 

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. 

* * * * * 

The proposed AD would require actions 

that are intended to address the unsafe 

condition described in the MCAI. 

DATES: We must receive comments on 

this proposed AD by August 15, 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 W12–40, 1200 New Jersey 

Avenue, SE., Washington, DC, between 

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

Friday, except Federal holidays. 

For service information identified in 

this proposed 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.airworth-eas@airbus.com; 

Internet http://www.airbus.com. You 

may review copies of the referenced 

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. 

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 proposed 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: 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: 

Comments Invited 

We invite you to send any written 

relevant data, views, or arguments about 

this proposed AD. Send your comments 

to an address listed under the 

ADDRESSES section. Include ‘‘Docket No. 

FAA–2011–0647; Directorate Identifier 

2010–NM–193–AD’’ at the beginning of 

your comments. We specifically invite 

comments on the overall regulatory, 

economic, environmental, and energy 

aspects of this proposed AD. We will 

consider all comments received by the 

closing date and may amend this 

proposed AD based on 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 proposed AD. 

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 2010–0144, 

dated July 16, 2010 (referred to after this 

as ‘‘the MCAI’’), to correct an unsafe 

condition for the specified products. 

The MCAI states: 

Surface defects were visually detected on 

the rudder of an Airbus A319 and an 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 


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38070 Federal Register / Vol. 76, No. 125 / Wednesday, June 29, 2011 / Proposed Rules 

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 A310 and A300–600 

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. 

To address this unsafe condition EASA 

issued AD 2010–0002 [which corresponds to 

FAA AD 2010–16–13, amendment 39– 

16390], superseding [EASA] AD 2009–0166, 

to require inspections of specific areas and, 

depending on findings, the application of 

corrective actions for those rudders where 

production reworks have been identified. 

This new [EASA] AD addresses the rudder 

population that has also been reworked in 

production, but not included in the 

applicability of EASA AD 2010–0002. 

The required actions, for certain 

rudders, include vacuum loss 

inspections and elasticity laminate 

checker inspections for defects 

including de-bonding between the skin 

and honeycomb core of the rudder. The 

corrective action is contacting the FAA 

or EASA for repair instructions if any 

defects are found. For certain other 

rudders, the required actions include 

replacing the rudder with a serviceable 

rudder. We are considering similar 

rulemaking action on Model A319 and 

A321 airplanes. You may obtain further 

information by examining the MCAI in 

the AD docket. 

Relevant Service Information 

Airbus has issued Mandatory Service 

Bulletins A310–55–2049 and A300–55– 

6048, both dated March 16, 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 Proposed 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 proposing this 

AD because we evaluated all pertinent 

information and determined an 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 also have proposed 

different actions in this AD from those 

in the MCAI in order to follow FAA 

policies. Any such differences are 

highlighted in a NOTE within the 

proposed AD. 

Costs of Compliance 

Based on the service information, we 

estimate that this proposed AD would 

affect about 215 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 proposed AD. The average labor 

rate is $85 per work-hour. Based on 

these figures, we estimate the cost of the 

proposed AD on U.S. operators to be 

$73,100, 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 proposed AD 

would not have federalism implications 

under Executive Order 13132. This 

proposed AD would 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 proposed regulation: 

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. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety. 

The Proposed Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA proposes to amend 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: 

Airbus: Docket No. FAA–2011–0647; 

Directorate Identifier 2010–NM–193–AD. 

Comments Due Date 

(a) We must receive comments by August 

15, 2011. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to Airbus Model A300 

B4–601, B4–603, B4–620, B4–622, B4–605R, 

B4–622R, F4–605R, F4–622R, and C4–605R 

Variant F airplanes; and Model A310–203, 

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

airplanes; certificated in any category; 

equipped with carbon fiber reinforced plastic 

rudders having any part number and serial 

number listed in Table 1, 2, 3, or 4 of this 

AD. 

TABLE 1—RUDDER INFORMATION

Rudder part No. 

Affected 

rudder 

serial No. 

A554–71710–000–00 ................... TS–2010 

A554–71710–000–00 ................... TS–2027 

A554–71710–000–00 ................... TS–2030 

A554–71710–002–00 ................... TS–2043 

A554–71710–004–00 ................... TS–2048 


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Federal Register / Vol. 76, No. 125 / Wednesday, June 29, 2011 / Proposed Rules 38071 

TABLE 2—RUDDER INFORMATION

Rudder part No. 

Affected 

rudder 

serial No. 

MSN—scrapped ........................... TS–1362 

A554–71710–000–00 ................... TS–2006 

A554–71710–000–00 ................... TS–2008 

A554–71710–002–00 ................... TS–2033 

A554–71710–004–00 ................... TS–2054 

A554–71710–004–00 ................... TS–2061 

A554–71710–004–00 ................... TS–2071 

A554–71710–004–00 ................... TS–2072 

A554–71710–004–00 ................... TS–2073 

A554–71730–000–00–0000 ......... TS–2082 

A554–71730–000–00–0000 ......... TS–2084 

A554–71730–000–00–0000 ......... TS–2085 

A554–71730–000–00–0000 ......... TS–2086 

A554–71730–000–00–0000 ......... TS–2087 

TABLE 3—RUDDER INFORMATION

Rudder part No. 

Affected 

rudder 

serial No. 

A554–71500–016–30 ................... HF–1254 

A554–71710–004–00 ................... TS–2049 

A554–71710–004–00 ................... TS–2055 

A554–71710–004–00 ................... TS–2059 

TABLE 4—RUDDER INFORMATION

Rudder part No. 

Affected 

rudder 

serial No. 

A554–71500–016–91 ................... HF–1044 

A554–71500–014–00 ................... HF–1116 

A554–71500–016–00 ................... HF–1183 

A554–71500–016–00 ................... HF–1184 

A554–71500–026–00 ................... TS–1402 

Subject 

(d) Air Transport Association (ATA) of 

America Code 55: Stabilizers. 

Reason 

(e) The mandatory continuing 

airworthiness information (MCAI) states: 

Surface defects were visually detected on 

the rudder of an Airbus A319 and an 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 A310 and A300–600 

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. 

* * * * * 

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. 

Inspections and Corrective Actions for 

Rudders Identified in Tables 1, 2, and 3 

(g) For rudders identified in Table 1 or 

Table 2 of this AD: Do the actions specified 

in paragraph (g)(1) or (g)(2) of this AD, as 

applicable, and paragraphs (g)(3) and (g)(4) of 

this AD, at the time specified. Do the actions 

in accordance with the Accomplishment 

Instructions of Airbus Mandatory Service 

Bulletin A310–55–2049 (for Model A310 

series airplanes) or A300–55–6048 (for Model 

A300–600 series airplanes), both dated 

March 16, 2010. 

(1) For rudders identified in Table 1 of this 

AD: Within 8 months after the effective date 

of this AD, perform a vacuum loss inspection 

in the ‘‘area 1’’ location defined in Airbus 

Mandatory Service Bulletin A310–55–2049 

or A300–55–6048, both dated March 16, 

2010, as applicable, to detect defects, 

including de-bonding. 

(2) For rudders identified in Table 2 of this 

AD: Within 24 months after the effective date 

of this AD, perform a vacuum loss inspection 

in the ‘‘area 1’’ location defined in Airbus 

Mandatory Service Bulletin A310–55–2049 

or A300–55–6048, both dated March 16, 

2010, as applicable, to detect defects, 

including de-bonding. 

(3) Within 24 months after the effective 

date of this AD: Do an elasticity laminate 

checker inspection to detect defects, 

including de-bonding, in the trailing edge 

location. 

(4) Repeat the inspection required by 

paragraph (g)(3) of this AD two times at 

intervals not to exceed 4,500 flight cycles, 

but not fewer than 4,000 flight cycles from 

the most recent inspection. 

(h) For rudders identified in Table 3 of this 

AD: Do the actions specified in paragraphs 

(h)(1) and (h)(2) of this AD at the time 

specified. Do the actions in accordance with 

the Accomplishment Instructions of Airbus 

Mandatory Service Bulletin A310–55–2049 

(for Model A310 series airplanes) or A300– 

55–6048 (for Model A300–600 series 

airplanes), both dated March 16, 2010. 

(1) Within 4,500 flight cycles after the 

effective date of this AD, but not fewer than 

4,000 flight cycles from the most recent 

elasticity laminate checker inspection: Do an 

elasticity laminate checker inspection to 

detect defects, including de-bonding, in the 

trailing edge location. 

(2) Repeat the inspection required by 

paragraph (h)(1) of this AD one time within 

4,500 flight cycles, but not fewer than 4,000 

flight cycles from the last inspection. 

(i) If any defect is found during any 

inspection required by paragraphs (g) and (h) 

of this AD, before further flight, repair in 

accordance with a method approved by the 

Manager, International Branch, ANM–116, 

Transport Airplane Directorate, FAA, or the 

European Aviation Safety Agency (EASA) (or 

its delegated agent). 

(j) If no defect is found during the 

inspections required by paragraphs (g)(1) and 

(g)(2) of this AD, before further flight, restore 

the vacuum loss holes with the temporary 

restoration with self adhesive tape, 

temporary restoration with resin, or 

permanent restoration with resin and surface 

protection. Do the applicable actions 

specified in paragraph (j)(1) or (j)(2) of this 

AD. 

(1) For airplanes on which a temporary 

restoration with self-adhesive disks or tapes 

is done, within 4 months after doing the 

restoration, do a detailed inspection for loose 

or missing self-adhesive disks or tapes and 

repeat the inspection thereafter at intervals 

not to exceed 4 months until the permanent 

restoration is done, in accordance with the 

Accomplishment Instructions of Airbus 

Mandatory Service Bulletin A310–55–2049 

(for Model A310 series airplanes) or A300– 

55–6048 (for Model A300–600 series 

airplanes), both dated March 16, 2010. If any 

loose or missing self-adhesive disks or tapes 

are found during any inspection required by 

this AD, before further flight, close the holes, 

in accordance with the Accomplishment 

Instructions of Airbus Mandatory Service 

Bulletin A310–55–2049 or A300–55–6048, 

both dated March 16, 2010, as applicable. Do 

the permanent restoration within 4,500 flight 

cycles after doing the temporary restoration, 

in accordance with the Accomplishment 

Instructions of Airbus Mandatory Service 

Bulletin A310–55–2049 or A300–55–6048, 

both dated March 16, 2010, as applicable. 

(2) For airplanes on which a temporary 

restoration with resin is done: Within 4,500 

flight cycles after doing the temporary 

restoration do the permanent restoration, in 

accordance with the Accomplishment 

Instructions of Airbus Mandatory Service 

Bulletin A310–55–2049 (for Model A310 

series airplanes) or A300–55–6048 (for Model 

A300–600 series airplanes), both dated 

March 16, 2010. 

Reporting 

(k) At the applicable time specified in 

paragraph (k)(1) or (k)(2) of this AD: Report 

the results of each inspection required by 

paragraphs (g) and (h) of this AD, including 

no findings, to Airbus, as specified in Airbus 

Mandatory Service Bulletin A310–55–2049 

(for Model A310 series airplanes) or A300– 

55–6048 (for Model A300–600 series 

airplanes), both dated March 16, 2010. 

(1) Inspections done before the effective 

date of this AD: Within 30 days after the 

effective date of this AD. 

(2) Inspections done on or after the 

effective date of this AD: Within 30 days after 

accomplishment of the inspection. 

Replacement for Rudders Identified in 

Table 4 

(l) For rudders identified in Table 4 of this 

AD: Within 8 months after the effective date 

of this AD, replace the affected rudder with 

a serviceable unit, in accordance with a 

method approved by the Manager, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA, or the EASA (or 

its delegated agent). 

Parts Installation 

(m) As of the effective date of this AD, no 

person may install any rudder identified in 

Table 1, 2, or 3 of this AD on any airplane, 

unless the rudder has been inspected and all 

applicable corrective actions have been done 

in accordance with paragraphs (g), (h), and (i) 

of this AD, as applicable. 


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38072 Federal Register / Vol. 76, No. 125 / Wednesday, June 29, 2011 / Proposed Rules 

(n) As of the effective date of this AD, no 

person may install any rudder identified in 

Table 4 of this AD on any airplane. 

FAA AD Differences 

Note 1: This AD differs from the MCAI 

and/or service information as follows: No 

differences. 

Other FAA AD Provisions 

(o) The following provisions also apply to 

this AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, International 

Branch, ANM–116, 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. Information may be e-mailed to: 

9-ANM-116-AMOC-REQUESTS@faa.gov. 

Before using any approved AMOC, notify 

your appropriate principal inspector, or 

lacking a principal inspector, the manager of 

the local flight standards district office/ 

certificate holding district office. The AMOC 

approval letter must specifically reference 

this AD. 

(2) Airworthy Product: For any requirement 

in this AD to obtain corrective actions from 

a manufacturer or other source, use these 

actions if they are FAA-approved. Corrective 

actions are considered FAA-approved if they 

are approved by the State of Design Authority 

(or their delegated agent). You are required 

to assure the product is airworthy before it 

is returned to service. 

(3) Reporting Requirements: 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 

(p) Refer to MCAI EASA Airworthiness 

Directive 2010–0144, dated July 16, 2010; 

and Airbus Mandatory Service Bulletins 

A310–55–2049 and A300–55–6048, both 

dated March 16, 2010; for related 

information. 

Issued in Renton, Washington, on June 16, 

2011. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2011–16367 Filed 6–28–11; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2011–0644; Directorate 

Identifier 2010–NM–265–AD] 

RIN 2120–AA64 

Airworthiness Directives; The Boeing 

Company Model 777 Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to adopt a new 

airworthiness directive (AD) for the 

products listed above. This proposed 

AD would require repetitive detailed 

inspection and high frequency eddy 

current (HFEC) inspections for cracks of 

the wing center section (WCS) spanwise 

beams, and repair if necessary. This 

proposed AD was prompted by reports 

of cracks found in the web pockets of 

the WCS spanwise beams. We are 

proposing this AD to detect and correct 

cracking in the WCS spanwise beams, 

which could result in reduced structural 

integrity of the wings. 

DATES: We must receive comments on 

this proposed AD by August 15, 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: Deliver to Mail 

address above between 9 a.m. and 

5 p.m., Monday through Friday, except 

Federal holidays. 

For service information identified in 

this proposed AD, contact Boeing 

Commercial Airplanes, Attention: Data 

& Services Management, P.O. Box 3707, 

MC 2H–65, Seattle, Washington 98124– 

2207; telephone 206–544–5000, 

extension 1; fax 206–766–5680; e-mail 

me.boecom@boeing.com; Internet 

https://www.myboeingfleet.com. You 

may review copies of the referenced 

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. 

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 proposed AD, the 

regulatory evaluation, any comments 

received, and other information. The 

street address for the Docket Office 

(phone: 800–647–5527) is in the 

ADDRESSES section. Comments will be 

available in the AD docket shortly after 

receipt. 

FOR FURTHER INFORMATION CONTACT: 

Duong Tran, Aerospace Engineer, 

Airframe Branch, ANM–120S, FAA, 

Seattle Aircraft Certification Office, 

1601 Lind Avenue, SW., Renton, 

Washington 98057–3356; phone: (425) 

917–6452; Fax: (425) 917–6590; e-mail: 

duong.tran@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Comments Invited 

We invite you to send any written 

relevant data, views, or arguments about 

this proposal. Send your comments to 

an address listed under the ADDRESSES

section. Include ‘‘Docket No. FAA– 

2011–0644; Directorate Identifier 2010– 

NM–265–AD’’ at the beginning of your 

comments. We specifically invite 

comments on the overall regulatory, 

economic, environmental, and energy 

aspects of this proposed AD. We will 

consider all comments received by the 

closing date and may amend this 

proposed 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 proposed AD. 

Discussion 

We have received reports of cracking 

in the wing center section (WSC) 

spanwise beams. Two operators 

reported finding a crack in the web 

pockets of WCS spanwise beams on two 

airplanes. In the first report, 

metallurgical testing showed the cracks 

were the result of fatigue from reverse 

bending (diagonal tension buckling). 

If cracking at multiple locations 

occurs in multiple spanwise beams, the 

WCS spanwise beams might not be able 


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