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presented by the importer to an 

authorized inspector at the port of 

arrival, upon arrival of the birds, 

poultry, hatching eggs, or poultry meat 

and products at the port. 

PART 95—SANITARY CONTROL OF 

ANIMAL BYPRODUCTS (EXCEPT 

CASINGS), AND HAY AND STRAW, 

OFFERED FOR ENTRY INTO THE 

UNITED STATES 

23. The authority citation for part 95 

continues to read as follows: 

Authority: 7 U.S.C. 8301–8317; 21 U.S.C. 

136 and 136a; 31 U.S.C. 9701; 7 CFR 2.22, 

2.80, and 371.4. 

§ 95.5 [Amended] 

24. In § 95.5, paragraph (c) is 

amended by removing the words 

‘‘exotic’’ and ‘‘subtype H5N1’’. 

§ 95.6 [Amended] 

25. In § 95.6, paragraph (c) is 

amended by removing the word 

‘‘exotic’’. 

PART 104—PERMITS FOR 

BIOLOGICAL PRODUCTS 

26. The authority citation for part 104 

continues to read as follows: 

Authority: 21 U.S.C. 151–159; 7 CFR 2.22, 

2.80, and 371.4. 

§ 104.2 [Amended] 

27. In § 104.2, paragraph (b) is 

amended by removing the words ‘‘fowl 

pest (fowl plague)’’ and adding the 

words ‘‘highly pathogenic avian 

influenza’’ in their place. 

Done in Washington, DC, this 13th day of 

July 2011. 

Kevin Shea, 

Acting Administrator, Animal and Plant 

Health Inspection Service. 

[FR Doc. 2011–18108 Filed 7–18–11 8:45 am] 

BILLING CODE 3410–34–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2011–0717; Directorate 

Identifier 2010–NM–108–AD] 

RIN 2120–AA64 

Airworthiness Directives; Airbus Model 

A330–201, –202, –203, –223, –243, 

–301, –302, –303, –321, –322, –323, 

–341, –342, and –343 Airplanes; and 

Model A340–200 and –300 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 that would 

supersede an existing AD. 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: 

During A330 and A340 aeroplanes fatigue 

tests, cracks appeared on the right (RH) and 

left (LH) sides between the crossing area of 

the keel beam fitting and the front spar of the 

Centre Wing Box (CWB). This condition, if 

not corrected, could lead to keel beam 

rupture which would affect the area 

structural integrity. 

* * * * * 

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 September 2, 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— 

Airworthiness Office—EAL, 1 Rond 

Point Maurice Bellonte, 31707 Blagnac 

Cedex, France; telephone +33 5 61 93 36 

96; fax +33 5 61 93 45 80; e-mail 

airworthiness.A330–A340@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: 

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: 

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–2011–0717; Directorate Identifier 

2010–NM–108–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 

On July 24, 2007, we issued AD 2007– 

16–02, Amendment 39–15141 (72 FR 

44731, August 9, 2007). That AD 

required actions intended to address an 

unsafe condition on the products listed 

above. 

Since we issued AD 2007–16–02, the 

European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Community, has issued EASA 

Airworthiness Directive 2010–0024, 

dated February 12, 2010 (referred to 

after this as ‘‘the MCAI’’), to correct an 

unsafe condition for the specified 

products. The MCAI states: 

During A330 and A340 aeroplanes fatigue 

tests, cracks appeared on the right (RH) and 

left (LH) sides between the crossing area of 

the keel beam fitting and the front spar of the 

Centre Wing Box (CWB). This condition, if 

not corrected, could lead to keel beam 

rupture which would affect the area 

structural integrity. 

In order to maintain the structural integrity 

of the aeroplane, EASA AD 2006–0315R1 

required repetitive special detailed 


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inspections on the horizontal flange of the 

keel beam in the area of first fastener hole aft 

of FR40. 

This AD, which supersedes EASA AD 

2006–0315R1: 

—Retains the inspection requirements of 

EASA AD 2006–0315R1, 

—Extends the AD applicability to aeroplanes 

which have embodied Airbus modification 

49202, and 

—Modifies the inspection thresholds and 

intervals. 

You may obtain further information by 

examining the MCAI in the AD docket. 

Relevant Service Information 

Airbus has issued the following 

service information. 

TABLE—SERVICE INFORMATION

Document Revision Date 

Airbus Mandatory Service Bulletin A330–57–3081, including Appendix 1 ................................... 03 ................................. July 31, 2009. 

Airbus Mandatory Service Bulletin A340–57–4089, including Appendix 1 ................................... 03 ................................. July 31, 2009. 

Airbus Service Bulletin A330–57–3090 ......................................................................................... Original ........................ March 27, 2006. 

Airbus Service Bulletin A330–57–3098, including Appendix 1 ..................................................... 01 ................................. July 31, 2009. 

Airbus Service Bulletin A340–57–4106, including Appendix 1 ..................................................... 01 ................................. July 31, 2009. 

Airbus Service Bulletin A340–57–4098 ......................................................................................... Original ........................ March 27, 2006. 

Airbus Mandatory Service Bulletins 

A330–57–3081, Revision 03, dated July 

31, 2009; and A340–57–4089, Revision 

03, dated July 31, 2009; reduce certain 

compliance times. The compliance time 

for the initial special detailed inspection 

ranges from 10,350 flight cycles or 

69,870 flight hours, to 21,180 flight 

cycles or 63,560 flight hours, depending 

on airplane configuration. The 

compliance times for the repetitive 

interval range from 7,780 flight cycles or 

52,510 flight hours, to 12,360 flight 

cycles or 37,080 flight hours, depending 

on airplane configuration. 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. 

Change to Existing AD 

This proposed AD would retain all 

requirements of AD 2007–16–02. Since 

AD 2007–16–02 was issued, the AD 

format has been revised, and certain 

paragraphs have been rearranged. As a 

result, the corresponding paragraph 

identifiers have changed in this 

proposed AD, as listed in the following 

table: 

REVISED PARAGRAPH IDENTIFIERS

Requirement in AD 

2007–16–02 

Corresponding 

requirement in this 

proposed AD 

paragraph (e)(1) paragraph (h) 

paragraph (e)(2) paragraph (i) 

paragraph (e)(3) paragraph (j) 

paragraph (e)(4) paragraph (k) 

paragraph (e)(5) paragraph (l) 

paragraph (e)(6) paragraph (m) 

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 35 products of U.S. registry. 

For the 9 airplanes affected by the 

existing AD, the actions that are 

required by AD 2007–16–02 and 

retained in this proposed AD take about 

41 work-hours per product, at an 

average labor rate of $85 per work hour. 

Required parts cost about $191 per 

product. Based on these figures, the 

estimated cost of the currently required 

actions is $3,676 per product. 

For the 26 additional airplanes added 

in this AD, we estimate the actions in 

this proposed AD would take about 41 

work-hours per product, at an average 

labor rate of $85 per work hour. 

Required parts would cost about $191 

per product. Based on these figures, the 

estimated cost of the proposed AD is 

$3,676 per product. 

In addition, because the proposed AD 

advises to contact the manufacturer for 

repair instructions, we cannot estimate 

the parts or labor costs for any necessary 

follow-on actions. We have no way of 

determining the number of products 

that may need these actions. 

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. 


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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 

removing Amendment 39–15141 (72 FR 

44731, August 9, 2007) and adding the 

following new AD: 

Airbus: Docket No. FAA–2011–0717; 

Directorate Identifier 2010–NM–108–AD. 

Comments Due Date 

(a) We must receive comments by 

September 2, 2011. 

Affected ADs 

(b) This AD supersedes AD 2007–16–02, 

Amendment 39–15141. 

Applicability 

(c) This AD applies to the airplanes 

identified in paragraphs (c)(1) and (c)(2) of 

this AD; certificated in any category; except 

as provided by paragraph (c)(3) of this AD. 

(1) Airbus Model A330–201, –202, –203, 

–223, –243, –301, –302, –303, –321, –322, 

–323, –341, –342, and –343 airplanes, all 

serial numbers, except those on which 

Airbus modification 55306 or 55792 has been 

embodied in production. 

(2) Airbus Model A340–211, –212, –213, 

–311, –312, and –313 airplanes, all serial 

numbers, except those on which Airbus 

modification 55306 or 55792 has been 

embodied in production. 

(3) This AD is not applicable to Airbus 

Model A340–211, –212, –213, –311, –312, 

and –313 airplanes that have been repaired 

in accordance with Airbus Repair Drawing 

R57115053, R57115051, or R57115047 

(installation of titanium doubler on both 

sides). AD 2007–12–08, Amendment 39– 

15086 (72 FR 31171, June 6, 2007), applies 

to these airplanes. 

Subject 

(d) Air Transport Association (ATA) of 

America Code 57: Wings. 

Reason 

(e) The mandatory continuing 

airworthiness information (MCAI) states: 

During A330 and A340 aeroplanes fatigue 

tests, cracks appeared on the right (RH) and 

left (LH) sides between the crossing area of 

the keel beam fitting and the front spar of the 

Centre Wing Box (CWB). This condition, if 

not corrected, could lead to keel beam 

rupture which would affect the area 

structural integrity. 

* * * * * 

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. 

Restatement of Requirements of AD 2007– 

16–02, With Revised Service Information 

(g) For Model A330–201, –202, –203, –223, 

–243, –301, –321, –322, –323, –341, –342, 

and –343 airplanes, except those on which 

Airbus modification 49202 has been 

embodied in production, or Airbus Service 

Bulletin A330–57–3090 has been embodied 

in service, and Model A340–200 and –300 

series airplanes, except those on which 

Airbus modification 49202 has been 

embodied in production or Airbus Service 

Bulletin A340–57–4098 has been embodied 

in service, and except Model A340–211, 

–212, –213, –311, –312, and –313 airplanes 

that have been repaired in accordance with 

Airbus Repair Drawing R57115053, 

R57115051, or R57115047: Do the actions 

required by paragraphs (h), (l), and (m) of this 

AD. 

(h) For airplanes identified in paragraph (g) 

of this AD, within the mandatory threshold 

(flight cycles or flight hours) mentioned in 

the paragraph 1.E.(2) of Airbus Mandatory 

Service Bulletin A340–57–4089, Revision 02; 

or A330–57–3081, Revision 02; both dated 

January 24, 2006; depending on the 

configuration of the aircraft model; or within 

3 months after September 13, 2007 (the 

effective date of AD 2007–16–02); whichever 

occurs later: Carry out the NDT (nondestructive test) inspection of the hole(s) of 

the horizontal flange of the keel beam located 

on FR 40 datum on RH (right-hand) and/or 

LH (left-hand) side of the fuselage, in 

accordance with the instructions of the 

applicable service bulletin listed in table 1 of 

this AD. After the effective date of this AD, 

use only Airbus Mandatory Service Bulletin 

A330–57–3081, Revision 03, dated July 31, 

2009; or Airbus Mandatory Service Bulletin 

A340–57–4089, Revision 03, dated July 31, 

2009; as applicable. Inspection in accordance 

with Airbus A330/A340 200–300 Technical 

Disposition F57D03012810, Issue B, dated 

August 18, 2003; or 582.0651/2002, Issue A, 

dated October 17, 2002; satisfies the 

inspection requirements for the first rotating 

probe inspection which is specified at the 

inspection threshold of this AD. Doing the 

inspection required by paragraph (n) of this 

AD terminates the requirements of this 

paragraph of this AD. 

Note 1: In order to prevent large repairs or 

heavy maintenance, Airbus recommends to 

perform the above inspection according to 

recommended thresholds mentioned in 

paragraph 1.E.(2) of Airbus Mandatory 

Service Bulletin A340–57–4089, Revision 02; 

or Airbus Mandatory Service Bulletin A330– 

57–3081, Revision 02; both dated January 24, 

2006. 

TABLE 1—ACCEPTABLE SERVICE INFORMATION FOR CERTAIN REQUIREMENTS OF PARAGRAPH (H) 

Document Revision Date 

Airbus Mandatory Service Bulletin A330–57–3081 ..................................................................................... 02 January 24, 2006. 

Airbus Mandatory Service Bulletin A330–57–3081 ..................................................................................... 03 July 31, 2009. 

Airbus Mandatory Service Bulletin A340–57–4089 ..................................................................................... 02 January 24, 2006. 

Airbus Mandatory Service Bulletin A340–57–4089 ..................................................................................... 03 July 31, 2009. 

(i) In case of any crack finding during the 

inspection required by paragraph (h) of this 

AD, before further flight, contact Airbus in 

order to get repair instructions before next 

flight, and repair before further flight. 

(j) Should no crack be detected during the 

inspection required by paragraph (h) of this 

AD: 

(1) Before further flight: Follow up the 

actions indicated in the flow charts, Figure 

7, 8, or 9, of Airbus Mandatory Service 

Bulletin A340–57–4089, including Appendix 

01, Revision 02, dated January 24, 2006, or 

Revision 03, dated July 31, 2009; or Figure 

5, 6, or 7, of Airbus Mandatory Service 

Bulletin A330–57–3081, including Appendix 

01, Revision 02, dated January 24, 2006, or 

Revision 03, dated July 31, 2009; in 

accordance with the instructions of Airbus 

Mandatory Service Bulletin A340–57–4089, 

including Appendix 01, Revision 02, dated 

January 24, 2006, or Revision 03, dated July 

31, 2009; or Airbus Mandatory Service 

Bulletin A330–57–3081, including Appendix 

01, Revision 02, dated January 24, 2006, or 


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Revision 03, dated July 31, 2009; as 

applicable. 

(2) Within 30 days after September 13, 

2007, or within 30 days after doing the 

inspection required by paragraph (h) of this 

AD, whichever occurs later: Send the report 

of actions carried out in paragraph (j)(1) of 

this AD to Airbus. 

(3) Renew the inspection at mandatory 

intervals given in paragraph 1.E.(2) of Airbus 

Mandatory Service Bulletin A340–57–4089, 

Revision 02, dated January 24, 2006; or 

Airbus Mandatory Service Bulletin A330–57– 

3081, Revision 02, dated January 24, 2006; as 

applicable; in accordance with the 

instructions of Airbus Mandatory Service 

Bulletin A340–57–4089, Revision 02, dated 

January 24, 2006, or Revision 03, dated July 

31, 2009, or Airbus Mandatory Service 

Bulletin A330–57–3081, Revision 02, dated 

January 24, 2006, or Revision 03, dated July 

31, 2009; as applicable, and send the 

inspection results to Airbus. Doing the 

inspection required by paragraph (n) of this 

AD terminates the requirements of this 

paragraph of this AD. 

Note 2: In order to prevent large repairs or 

heavy maintenance, Airbus recommends to 

perform the above repetitive inspection 

according to recommended intervals 

mentioned in paragraph 1.E.(2) of Airbus 

Mandatory Service Bulletin A340–57–4089, 

Revision 02, dated January 24, 2006; or 

Airbus Mandatory Service Bulletin A330–57– 

3081, Revision 02, dated January 24, 2006. 

(k) Upon detection of a crack during a 

repetitive inspection required by paragraph 

(j)(3) of this AD, before further flight, contact 

Airbus to get repair instructions, and repair 

before further flight. 

(l) For airplanes identified in paragraph (g) 

of this AD: No additional work is required for 

compliance with paragraph (h) of this AD for 

aircraft inspected in accordance with the 

instructions of Airbus Service Bulletin A330– 

57–3081, dated October 30, 2003, or Revision 

01, dated May 18, 2004; or Airbus Service 

Bulletin A340–57–4089, dated October 30, 

2003, or Revision 01, dated March 2, 2004. 

Nevertheless, the operators must check that 

their inspection program is in accordance 

with paragraph 1.E.(2) of Airbus Mandatory 

Service Bulletin A340–57–4089, Revision 02, 

dated January 24, 2006; or Airbus Mandatory 

Service Bulletin A330–57–3081, Revision 02, 

dated January 24, 2006; as applicable; for the 

repetitive inspection. 

(m) For airplanes identified in paragraph 

(g) of this AD on which Airbus Modification 

41652 is not embodied: When the aircraft has 

been modified in accordance with Airbus 

Service Bulletin A330–57–3090, dated March 

27, 2006; or Airbus Service Bulletin A340– 

57–4098, dated March 27, 2006; as 

applicable; the repetitive inspections 

required by this AD are cancelled. In case of 

any crack finding during the modification: 

Where the applicable service bulletin 

specifies to contact Airbus, before further 

flight, contact Airbus to get repair 

instructions, and repair. 

New Requirements of This AD 

(n) At the applicable time in paragraph 

(n)(1) or (n)(2) of this AD: Do an NDT 

inspection of the hole(s) of the horizontal 

flange of the keel beam located on FR 40 

datum on RH and/or LH side of the fuselage, 

in accordance with the Accomplishment 

Instructions of Airbus Mandatory Service 

Bulletin A330–57–3081, Revision 03, dated 

July 31, 2009; or Airbus Mandatory Service 

Bulletin A340–57–4089, Revision 03, dated 

July 31, 2009; as applicable. Inspection in 

accordance with Airbus A330/A340 

Technical Disposition F57D03012810, Issue 

B, dated August 18, 2003; or 582.0651/2002, 

Issue A, dated October 17, 2002; is acceptable 

for compliance with the inspection 

requirements for the first rotating probe 

inspection required by this paragraph. Doing 

the inspection required by this paragraph 

terminates the requirements of paragraphs (h) 

and (j)(3) of this AD. 

(1) For airplanes on which an inspection 

required by paragraph (h) of this AD has not 

been done as of the effective date of this AD: 

At the applicable time specified in paragraph 

(n)(1)(i) or (n)(1)(ii) of this AD. 

(i) For all airplanes except those identified 

in paragraph (g) of this AD: Within the 

‘‘Mandatory Threshold’’ (flight cycles or 

flight hours) specified in table 1 of paragraph 

1.E.(2) of the Accomplishment Instructions of 

Airbus Mandatory Service Bulletin A330–57– 

3081, Revision 03, dated July 31, 2009; or 

Airbus Mandatory Service Bulletin A340–57– 

4089, Revision 03, dated July 31, 2009; as 

applicable; or within 3 months after the 

effective date of this AD; whichever occurs 

later. The compliance times for configuration 

02 through 06 specified in the ‘‘Mandatory 

Threshold’’ column in table 1 of paragraph 

1.E., ‘‘Compliance,’’ are total flight cycles and 

total flight hours. 

(ii) For airplanes identified in paragraph (g) 

of this AD: At the earlier of the times 

specified in paragraphs (n)(1)(ii)(A) and 

(n)(1)(ii)(B) of this AD. 

(A) Within the ‘‘Mandatory Threshold’’ 

(flight cycles or flight hours) specified in 

table 1 of paragraph 1.E.(2) of Airbus 

Mandatory Service Bulletin A340–57–4089, 

Revision 02, dated January 24, 2006; or 

Airbus Mandatory Service Bulletin A330–57– 

3081, Revision 02, dated January 24, 2006; 

depending on the configuration of the aircraft 

model; or within 3 months after September 

13, 2007; whichever occurs later. The 

compliance times for Model A330 post-mod. 

No. 41652 and pre-mod. No. 44360, postmod. No. 44360, and pre-mod. No. 49202 

(specified in Airbus Mandatory Service 

Bulletin A330–57–3081, Revision 02, dated 

January 24, 2006); and Model A340 postmod. No. 41652, post-mod. No. 43500 and 

pre-mod. No. 44360, post-mod. No. 44360 

and pre-mod. No. 49202, and Weight Variant 

027 (specified in Airbus Mandatory Service 

Bulletin A340–57–4089, Revision 02, dated 

January 24, 2006); specified in the 

‘‘Mandatory Threshold’’ column in table 1 of 

paragraph 1.E., ‘‘Compliance,’’ are total flight 

cycles and total flight hours. 

(B) Within the ‘‘Mandatory Threshold’’ 

(flight cycles or flight hours) specified in 

table 1 of paragraph 1.E.(2) of the 

Accomplishment Instructions of Airbus 

Mandatory Service Bulletin A330–57–3081, 

Revision 03, dated July 31, 2009; or Airbus 

Mandatory Service Bulletin A340–57–4089, 

Revision 03, dated July 31, 2009; as 

applicable; or within 3 months after the 

effective date of this AD; whichever occurs 

later. The compliance times for configuration 

02 through 06 specified in the ‘‘Mandatory 

Threshold’’ column in table 1 of paragraph 

1.E., ‘‘Compliance,’’ are total flight cycles and 

total flight hours. 

(2) For airplanes on which an inspection 

required by paragraph (h) of this AD has been 

done as of the effective date of this AD: At 

the earlier of the times specified in 

paragraphs (n)(2)(i) and (n)(2)(ii) of this AD. 

(i) Within the ‘‘Mandatory Intervals’’ given 

in table 1 of paragraph 1.E.(2) of Airbus 

Mandatory Service Bulletin A340–57–4089, 

Revision 02, dated January 24, 2006; or 

Airbus Mandatory Service Bulletin A330–57– 

3081, Revision 02, dated January 24, 2006; as 

applicable. 

(ii) Within the applicable ‘‘Mandatory 

Interval’’ specified in table 1 of Paragraph 

1.E.(2). of Airbus Mandatory Service Bulletin 

A330–57–3081, Revision 03, dated July 31, 

2009; or Airbus Mandatory Service Bulletin 

A340–57–4089, Revision 03, dated July 31, 

2009; as applicable; or within 3 months after 

the effective date of this AD; whichever 

occurs later. 

Note 3: To prevent large repairs or heavy 

maintenance, Airbus recommends to perform 

the above inspection according to 

recommended thresholds specified in 

paragraph 1.E.(2) of Airbus Mandatory 

Service Bulletin A330–57–3081, Revision 03, 

dated July 31, 2009; or Airbus Mandatory 

Service Bulletin A340–57–4089, Revision 03, 

dated July 31, 2009; as applicable. 

(o) If any cracking is found during any 

inspection required by paragraph (n) of this 

AD, before further flight, repair in accordance 

with a method approved by the International 

Branch, ANM–116, Transport Airplane 

Directorate, FAA, or EASA (or its delegated 

agent). 

(p) If no cracking is found during any 

inspection required by paragraph (n) of this 

AD, do the actions required by paragraphs 

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

(1) Before further flight: Install new or 

oversized fastener, as applicable; seal the 

fastener; and do all other applicable actions; 

in accordance with the Accomplishment 

Instructions of Airbus Mandatory Service 

Bulletin A330–57–3081, Revision 03, dated 

July 31, 2009; or Airbus Mandatory Service 

Bulletin A340–57–4089, Revision 03, dated 

July 31, 2009; as applicable. 

(2) Repeat the inspection required by 

paragraph (n) of this AD thereafter at 

intervals not to exceed the mandatory 

intervals specified in Paragraph 1.E.(2). of 

Airbus Mandatory Service Bulletin A330–57– 

3081, Revision 03, dated July 31, 2009; or 

Airbus Mandatory Service Bulletin A340–57– 

4089, Revision 03, dated July 31, 2009; as 

applicable. 

Note 4: To prevent large repairs or heavy 

maintenance, Airbus recommends to perform 

the above repetitive inspection according to 

recommended intervals mentioned in 

paragraph 1.E.(2) of Airbus Mandatory 

Service Bulletin A330–57–3081, Revision 03, 

dated July 31, 2009; or Airbus Mandatory 

Service Bulletin A340–57–4089, Revision 03, 

dated July 31, 2009; as applicable. 


srobinson on DSK4SPTVN1PROD with PROPOSALS
42606 Federal Register / Vol. 76, No. 138 / Tuesday, July 19, 2011 / Proposed Rules 

Credit for Actions Accomplished in 

Accordance With Previous Service 

Information 

(q) Inspections done before the effective 

date of this AD in accordance with the 

service information specified in table 2 of 

this AD are acceptable for compliance with 

the corresponding inspection required by 

paragraph (n) of this AD. 

TABLE 2—CREDIT SERVICE INFORMATION FOR CERTAIN ACTIONS

Document Revision Date 

Airbus Mandatory Service Bulletin A330–57–3081 ....................................................................... 02 ................................. January 24, 2006. 

Airbus Mandatory Service Bulletin A340–57–4089 ....................................................................... 02 ................................. January 24, 2006. 

Airbus Service Bulletin A330–57–3081 ......................................................................................... Original ........................ October 30, 2003. 

Airbus Service Bulletin A330–57–3081 ......................................................................................... 01 ................................. May 18, 2004. 

Airbus Service Bulletin A340–57–4089 ......................................................................................... Original ........................ October 30, 2003. 

Airbus Service Bulletin A340–57–4089 ......................................................................................... 01 ................................. March 2, 2004. 

(r) Modifying the fasteners installation in 

the junction keel beam fitting at FR 40, in 

accordance with Airbus Service Bulletin 

A330–57–3098, dated August 30, 2007; or 

Airbus Service Bulletin A340–57–4106, 

dated August 30, 2007; as applicable; before 

the effective date of this AD terminates the 

requirements of this AD; except for airplanes 

on which a crack was detected at hole 5 

before oversizing of the keel beam (in 

accordance with step 3.B.(1)(b)3 of the 

Accomplishment Instructions of Airbus 

Service Bulletin A330–57–3098 or Airbus 

Service Bulletin A340–57–4106), before 

further flight, repair in accordance with a 

method approved by the International 

Branch, ANM–116, Transport Airplane 

Directorate, FAA, or EASA (or its delegated 

agent). 

(s) Modifying the fasteners installation in 

the junction keel beam fitting at FR 40, in 

accordance with Airbus Service Bulletin 

A330–57–3098, Revision 01, dated July 31, 

2009; or Airbus Service Bulletin A340–57– 

4106, Revision 01, dated July 31, 2009; as 

applicable; terminates the requirements of 

this AD. 

(t) Modifying the fasteners installation in 

the junction keel beam fitting at FR 40, in 

accordance with Airbus Service Bulletin 

A330–57–3090, dated March 27, 2006; or 

Airbus Service Bulletin A340–57–4098, 

dated March 27, 2006; as applicable; 

terminates the requirements of this AD. 

(u) In case of any crack finding during any 

modification specified paragraphs (r), (s), and 

(t) of this AD: Where the applicable service 

bulletin specifies to contact Airbus, before 

further flight, repair in accordance with a 

method approved by the International 

Branch, FAA, or EASA (or its delegated 

agent). 

FAA AD Differences 

Note 5: This AD differs from the MCAI 

and/or service information as follows: No 

differences. 

Other FAA AD Provisions 

(v) The following provisions also apply to 

this AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, International 

Branch, 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: 

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. Information may be e-mailed to: 

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

Before using any approved AMOC, notify 

your appropriate principal inspector, or 

lacking a principal inspector, the manager of 

the local flight standards district office/ 

certificate holding district office. The AMOC 

approval letter must specifically reference 

this AD. 

(2) Airworthy Product: For any requirement 

in this AD to obtain corrective actions from 

a manufacturer or other source, use these 

actions if they are FAA-approved. Corrective 

actions are considered FAA-approved if they 

are approved by the State of Design Authority 

(or their delegated agent). You are required 

to assure the product is airworthy before it 

is returned to service. 

Related Information 

(w) Refer to MCAI European Aviation 

Safety Agency Airworthiness Directive 2010– 

0024, dated February 12, 2010, and the 

applicable service information specified/ 

identified in table 3 of this AD, for related 

information. 

TABLE 3—RELATED SERVICE INFORMATION

Document Revision Date 

Airbus Mandatory Service Bulletin A330–57–3081 ....................................................................... 02 ................................. January 24, 2006. 

Airbus Mandatory Service Bulletin A330–57–3081 ....................................................................... 03 ................................. July 31, 2009. 

Airbus Mandatory Service Bulletin A340–57–4089 ....................................................................... 02 ................................. January 24, 2006. 

Airbus Mandatory Service Bulletin A340–57–4089 ....................................................................... 03 ................................. July 31, 2009. 

Airbus Service Bulletin A330–57–3090 ......................................................................................... Original ........................ March 27, 2006. 

Airbus Service Bulletin A330–57–3098 ......................................................................................... 01 ................................. July 31, 2009. 

Airbus Service Bulletin A340–57–4106 ......................................................................................... 01 ................................. July 31, 2009. 

Airbus Service Bulletin A340–57–4098 ......................................................................................... Original ........................ March 27, 2006. 

Airbus A330/A340 200–300 Technical Disposition F57D03012810 ............................................. Issue B ........................ August 18, 2003. 

Airbus A330/A340 Technical Disposition 582.0651/2002 ............................................................. Issue A ........................ October 17, 2002. 


srobinson on DSK4SPTVN1PROD with PROPOSALS
Federal Register / Vol. 76, No. 138 / Tuesday, July 19, 2011 / Proposed Rules 42607 

Issued in Renton, Washington, on July 7, 

2011. 

Kalene C. Yanamura, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2011–18131 Filed 7–18–11; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2011–0719; Directorate 

Identifier 2010–NM–087–AD] 

RIN 2120–AA64 

Airworthiness Directives; The Boeing 

Company Model 767–200, –300, and 

–400ER Series Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to supersede an 

existing airworthiness directive (AD) 

that applies to the products listed above. 

The existing AD currently requires 

replacing the separation link assembly 

on the applicable entry and service 

doors with an improved separation link 

assembly, and doing related 

investigative and corrective actions if 

necessary. Since we issued that AD, we 

have received a report that an additional 

airplane is subject to the unsafe 

condition. This proposed AD would add 

that airplane to the applicability and 

also remove certain other airplanes from 

the applicability. We are proposing this 

AD to prevent failure of an entry or 

service door to open fully in the event 

of an emergency evacuation, which 

could impede exit from the airplane. 

This condition could result in injury to 

passengers or crewmembers. 

DATES: We must receive comments on 

this proposed AD by September 2, 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 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: 

Stephen Styskal, Aerospace Engineer, 

Cabin Safety and Environmental 

Systems Branch, ANM–150S, FAA, 

Seattle Aircraft Certification Office, 

1601 Lind Avenue, SW., Renton, 

Washington 98057–3356; phone: (425) 

917–6439; fax: (425) 917–6590; e-mail: 

stephen.styskal@faa.gov. 

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–2011–0719; Directorate Identifier 

2010–NM–087–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 

On January 22, 2009, we issued AD 

2009–04–12, Amendment 39–15818 (74 

FR 8717, February 26, 2009), for certain 

Model 767–200, –300, and –400ER 

series airplanes. That AD requires 

replacing the separation link assembly 

on the applicable entry and service 

doors with an improved separation link 

assembly, and doing related 

investigative and corrective actions if 

necessary. That AD resulted from 

reports that entry and service doors did 

not open fully during deployment of 

emergency escape slides, and additional 

reports of missing snap rings. We issued 

that AD to prevent failure of an entry or 

service door to open fully in the event 

of an emergency evacuation, which 

could impede exit from the airplane. 

This condition could result in injury to 

passengers or crewmembers. 

Actions Since Existing AD Was Issued 

Since we issued AD 2009–04–12, we 

have received a report indicating that an 

additional airplane is subject to the 

unsafe condition. In addition, four 

airplanes were converted to freighter 

configurations without the affected 

slides, and, therefore, are no longer 

subject to the unsafe condition. 

Relevant Service Information 

We reviewed Boeing Special 

Attention Service Bulletin 767–25– 

0428, Revision 3, dated October 21, 

2010. This service bulletin describes the 

same procedures that are described in 

Boeing Special Attention Service 

Bulletin 767–25–0428, Revision 1, dated 

May 8, 2008 (which was referenced in 

AD 2009–04–12 as the appropriate 

source of service information). Revision 

3 of Boeing Special Attention Service 

Bulletin 767–25–0428 adds a step to the 

entry/service door bustle installation 

process, and contains information on 

airplanes identified in the revised 

Effectivity section and a changed part 

number for a cap screw. 

Boeing Special Attention Service 

Bulletin 767–25–0428, Revision 2, dated 

February 4, 2010, included an 

additional airplane in the Effectivity 

section and removed four airplanes from 

the Effectivity section. 

FAA’s Determination 

We are proposing this AD because we 

evaluated all the relevant information 

and determined the unsafe condition 

described previously is likely to exist or 

develop in other products of the same 

type design. 

Proposed AD Requirements 

This proposed AD would retain all 

the requirements of AD 2009–04–12 

using the revised service information 

described previously. This proposed AD 

would add an airplane to the 


srobinson on DSK4SPTVN1PROD with PROPOSALS