4260 Federal Register / Vol. 76, No. 16 / Tuesday, January 25, 2011 / Proposed Rules 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2011–0030; Directorate 

Identifier 2009–NM–183–AD] 

RIN 2120–AA64 

Airworthiness Directives; Airbus Model 

A300 and A310 Series Airplanes, and 

Model A300 B4–600, B4–600R, and F4– 

600R Series Airplanes, and Model C4– 

605R Variant F Airplanes (Collectively 

Called A300–600 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 three existing ADs. 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: 

The airworthiness limitations applicable to 

the Damage Tolerant Airworthiness 

Limitation Items (DT ALI) are currently listed 

in Airbus ALI Documents, which are 

referenced in the A300, A310, and A300–600 

Airworthiness Limitations Section (ALS) Part 

2. Airbus has recently revised the ALI 

Documents, which have been approved by 

the European Aviation Safety Agency 

(EASA). 

* * * * * 

The actions contained in these revised 

documents, which introduce more restrictive 

maintenance requirements and/or 

airworthiness limitations, have been 

identified as mandatory actions for continued 

airworthiness. * * * 

The unsafe condition is fatigue cracking, 

damage, or corrosion in principal 

structural elements, which could result 

in reduced structural integrity of the 

airplane. 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 March 11, 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, FAA, 

Transport Airplane Directorate, 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–2011–0030; Directorate Identifier 

2009–NM–183–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 February 6, 2007, we issued AD 

2007–04–11, Amendment 39–14943 (72 

FR 8604, February 27, 2007). That AD 

required actions intended to address an 

unsafe condition on Airbus Model A300 

B2 and B4 series airplanes. 

On September 19, 2007, we issued AD 

2007–20–03, Amendment 39–15213 (72 

FR 54536, September 26, 2007). That 

AD required actions intended to address 

an unsafe condition on Airbus Model 

A300–600 series airplanes. 

On November 23, 2007, we issued AD 

2007–25–02, Amendment 39–15283 (72 

FR 69612, December 10, 2007). That AD 

required actions intended to address an 

unsafe condition on Airbus Model A310 

series airplanes. 

Since we issued ADs 2007–04–11, 

2007–20–03, and 2007–25–02, we have 

determined that the airworthiness 

limitations for these airplanes must be 

updated in order to adequately address 

the unsafe condition. The European 

Aviation Safety Agency (EASA), which 

is the Technical Agent for the Member 

States of the European Community, has 

issued EASA Airworthiness Directive 

2009–0155, dated July 17, 2009 (referred 

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

an unsafe condition for the specified 

products. The MCAI states: 

The airworthiness limitations applicable to 

the Damage Tolerant Airworthiness 

Limitation Items (DT ALI) are currently listed 

in Airbus ALI Documents, which are 

referenced in the A300, A310, and A300–600 

Airworthiness Limitations Section (ALS) Part 

2. Airbus has recently revised the ALI 

Documents, which have been approved by 

the European Aviation Safety Agency 

(EASA). 

—Airbus A300 ALI Document issue 04. 

—Airbus A310 ALI Document issue 07 and 

—Airbus A300–600 ALI Document issue 12 

The actions contained in these revised 

documents, which introduce more restrictive 

maintenance requirements and/or 

airworthiness limitations, have been 

identified as mandatory actions for continued 

airworthiness. EASA issued ADs 2006–0071, 

2006–0260, and 2006–0374 [which 

correspond to FAA ADs 2007–04–11, 2007– 

25–02, and 2007–20–03] to require 

compliance with the maintenance 

requirements and associated airworthiness 

limitations defined in previous issues of 

these Airbus ALI documents. 

For the reason described above, [the] EASA 

AD supersedes existing ADs 2006–0071, 

2006–0260, and 2006–0374 and requires an 

update to the approved aircraft maintenance 


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programme and compliance with the 

maintenance requirements and associated 

airworthiness limitations defined in the 

Airbus ALI Documents listed above. 

The unsafe condition is fatigue cracking, 

damage, or corrosion in principal 

structural elements, which could result 

in reduced structural integrity of the 

airplane. The required actions include 

revising the Airworthiness Limitations 

section of the Instructions for Continued 

Airworthiness to incorporate new and 

revised structural inspections and 

inspection intervals. You may obtain 

further information by examining the 

MCAI in the AD docket. 

Relevant Service Information 

Airbus has issued A300–600 

Airworthiness Limitation Items (ALI) 

Document AI/SE–M2/95A.1310/07, 

Issue 12, dated June 2008; A300 ALI 

Document AI/SE–M2/95A.1308/07, 

Issue 4, dated June 2008; and A310 ALI 

Document, AI/SE–M2/95A.1309/07, 

Issue 7, dated June 2008. 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 206 products of U.S. 

registry. 

The actions that are required by AD 

2007–04–11, AD 2007–20–03, and AD 

2007–25–02, and retained in this 

proposed AD, take about 1 work hour 

per product. The average labor rate is 

$85 per work-hour. Based on these 

figures, we estimate the cost of those 

actions on U.S. operators to be $85 per 

product. 

We estimate that it would take about 

1 work-hour per product to comply with 

the new 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 $17,510, or $85 per 

product. 

Authority for This Rulemaking 

Title 49 of the United States Code 

specifies the FAA’s authority to issue 

rules on aviation safety. Subtitle I, 

section 106, describes the authority of 

the FAA Administrator. ‘‘Subtitle VII: 

Aviation Programs,’’ describes in more 

detail the scope of the Agency’s 

authority. 

We are issuing this rulemaking under 

the authority described in ‘‘Subtitle VII, 

Part A, Subpart III, Section 44701: 

General requirements.’’ Under that 

section, Congress charges the FAA with 

promoting safe flight of civil aircraft in 

air commerce by prescribing regulations 

for practices, methods, and procedures 

the Administrator finds necessary for 

safety in air commerce. This regulation 

is within the scope of that authority 

because it addresses an unsafe condition 

that is likely to exist or develop on 

products identified in this rulemaking 

action. 

Regulatory Findings 

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 

removing Amendment 39–14943 (72 FR 

8604, February 27, 2007); Amendment 

39–15213 (72 FR 54536, September 26, 

2007); and Amendment 39–15283 (72 

FR 69612, December 10, 2007); and 

adding the following new AD: 

Airbus: Docket No. FAA–2011–0030; 

Directorate Identifier 2009–NM–183–AD. 

Comments Due Date 

(a) We must receive comments by March 

11, 2011. 

Affected ADs 

(b) This AD supersedes AD 2007–04–11, 

Amendment 39–14943; AD 2007–20–03, 

Amendment 39–15213; and AD 2007–25–02, 

Amendment 39–15283. 

Applicability 

(c) This AD applies to all Airbus model 

airplanes identified in paragraphs (c)(1), 

(c)(2), and (c)(3) of this AD, certificated in 

any category. 

(1) Model A300 B2–1A, B2–1C, B4–2C, 

B2K–3C, B4–103, B2–203, and B4–203 

airplanes. 

(2) Model A310–203, –204, –221, –222, 

–304, –322, –324, and –325 airplanes. 

(3) Models A300 B4–601, B4–603, B4–620, 

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

F4–622R airplanes, and Model A300 C4– 

605R Variant F airplanes. 

Note 1: This AD requires revisions to 

certain operator maintenance documents to 

include new inspections. Compliance with 

these inspections is required by 14 CFR 

91.403(c). For airplanes that have been 

previously modified, altered, or repaired in 

the areas addressed by these inspections, the 

operator may not be able to accomplish the 

inspections described in the revisions. In this 

situation, to comply with 14 CFR 91.403(c), 

the operator must request approval for an 

alternative method of compliance according 


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to paragraph (t)(1) of this AD. The request 

should include a description of changes to 

the required inspections that will ensure the 

continued damage tolerance of the affected 

structure. The FAA has provided guidance 

for this determination in Advisory Circular 

(AC) 25–1529–1. 

Subject 

(d) Air Transport Association (ATA) of 

America Codes 52: Doors; 53: Fuselage; 54: 

Nacelles/pylons; 55: Stabilizers; 57: Wings; 

and 71: Powerplant (for Model A300–600 

only). 

Reason 

(e) The mandatory continuing 

airworthiness information (MCAI) states: 

The airworthiness limitations applicable to 

the Damage Tolerant Airworthiness 

Limitation Items (DT ALI) are currently listed 

in Airbus ALI Documents, which are 

referenced in the A300, A310, and A300–600 

Airworthiness Limitations Section (ALS) Part 

2. Airbus has recently revised the ALI 

Documents, which have been approved by 

the European Aviation Safety Agency 

(EASA). 

* * * * * 

The actions contained in these revised 

documents, which introduce more restrictive 

maintenance requirements and/or 

airworthiness limitations, have been 

identified as mandatory actions for continued 

airworthiness. * * * 

The unsafe condition is fatigue cracking, 

damage, or corrosion in principal structural 

elements, which could result in reduced 

structural integrity of the airplane. 

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 Certain Requirements of AD 

2007–04–11 

(g) Within one year after August 9, 1996 

(the effective date of AD 96–13–11), replace 

the revision of the maintenance program with 

the inspections, inspection intervals, repairs, 

and replacements defined in ‘‘Airbus 

Industrie A300 Supplemental Structural 

Inspection Document’’ (SSID), Revision 2, 

dated June 1994 (‘‘Revision 2 of the SSID’’). 

Accomplish the actions specified in the 

service bulletins identified in Section 6, ‘‘SB 

Reference List,’’ Revision 2 of the SSID, at the 

times specified in those service bulletins. 

The actions are to be accomplished in 

accordance with those service bulletins. 

Accomplishing the initial ALI tasks required 

by paragraph(s) of this AD terminates the 

actions required by this paragraph. 

(1) For airplanes that have exceeded the 

threshold specified in any of the service 

bulletins identified in Section 6, ‘‘SB 

Reference List,’’ Revision 2 of the SSID: 

Accomplish the actions specified in those 

service bulletins within the grace period 

specified in that service bulletin. The grace 

period is to be measured from August 9, 

1996. 

(2) For airplanes that have exceeded the 

threshold specified in any of the service 

bulletins identified in Section 6, ‘‘SB 

Reference List,’’ Revision 2 of the SSID, and 

a grace period is not specified in that service 

bulletin: Accomplish the actions specified in 

that service bulletin within 1,500 flight 

cycles after August 9, 1996. 

Revision of the Maintenance Inspection 

Program 

(h) For airplanes identified in paragraph 

(c)(1) of this AD: Within 12 months after 

April 3, 2007 (the effective date of AD 2007– 

04–11), replace the revision of the 

maintenance program required by paragraph 

(g) of this AD with the supplemental 

structural inspections, inspection intervals, 

and repairs defined in Airbus A300 

Airworthiness Limitation Items (ALI) 

Document SEM2/95A.1090/05, Issue 3, dated 

September 2005, as revised by Airbus A300 

Temporary Revision (TR) 3.1, dated April 

2006 (‘‘Issue 3 of the ALI’’). Accomplish the 

actions specified in Issue 3 of the ALI at the 

times specified in that ALI, except as 

provided by paragraph (i) of this AD. The 

actions must be accomplished in accordance 

with Issue 3 of the ALI. Accomplishing the 

initial ALI tasks required by paragraph (s) of 

this AD terminates the actions required by 

this paragraph. 

(i) For airplanes identified in paragraph 

(c)(1) of this AD that have exceeded the 

threshold or intervals specified in the Airbus 

A300 Airworthiness Limitation Items 

Document SEM2/95A.1090/05, Issue 3, dated 

September 2005 (‘‘Issue 3 of the ALI’’), for 

the application tolerance on the first interval 

for new and revised requirements and have 

exceeded 50 percent of the intervals specified 

in sections D and E of Issue 3 of the ALI: Do 

the actions within 6 months after April 3, 

2007. 

Corrective Actions 

(j) Damaged, cracked, or corroded structure 

detected during any inspection done in 

accordance with the Airbus 

A300Airworthiness Limitation Items 

Document SEM2/95A.1090/05, Issue 3, dated 

September 2005 (‘‘Issue 3 of the ALI’’), must 

be repaired, before further flight, in 

accordance with Issue 3 of the ALI, except as 

provided by paragraph (k) of this AD; or 

other data meeting the certification basis of 

the airplane which is approved by the 

Manager, International Branch, ANM–116; or 

by the European Aviation Safety Agency 

(EASA) (or its delegated agent). 

(k) Where the Airbus A300Airworthiness 

Limitation Items Document SEM2/95A.1090/ 

05, Issue 3, dated September 2005, specifies 

contacting Airbus for appropriate action: 

Before further flight, repair the damaged, 

cracked, or corroded structure using a 

method approved by either the Manager, 

International Branch, ANM–116; or the 

EASA (or its delegated agent). 

No Fleet Sampling 

(l) Although Airbus A300 Airworthiness 

Limitation Items Document SEM2/95A.1090/ 

05, Issue 3, dated September 2005, specifies 

to do a ‘‘Sampling Concept’’ in section B, this 

AD prohibits the use of such a sampling 

program and requires all affected airplanes of 

the fleet to be inspected. 

No Reporting 

(m) Although Airbus A300 Airworthiness 

Limitation Items Document SEM2/95A.1090/ 

05, Issue 3, dated September 2005, specifies 

to submit certain information to the 

manufacturer, this AD does not include that 

requirement. 

Restatement of Requirements of AD 2007– 

20–03 

Actions and Compliance 

(n) For airplanes identified in paragraph 

(c)(3) of this AD: Within 3 months after 

October 31, 2007 (the effective date AD 

2007–20–03), revise the ALS of the 

Instructions for Continued Airworthiness to 

incorporate Airbus A300–600 Airworthiness 

Limitation Items (ALI) Document AI/SE–M2/ 

95A.0502/06, Issue 11, dated April 2006 

(‘‘Issue 11 of the ALI’’). The tolerance (grace 

period) for compliance (specified in 

paragraph 2 of Section B—Program Rules) 

with Issue 11 of the ALI is within 2,000 flight 

cycles after October 31, 2007, provided that 

none of the following is exceeded. 

Accomplishing the initial ALI tasks required 

by paragraph (s) of this AD terminates the 

actions required by this paragraph. 

(1) Thresholds or intervals in the operator’s 

current approved maintenance schedule that 

are taken from a previous ALI issue, if 

existing, and are higher than or equal to those 

given in Issue 11 of the ALI. 

(2) 8 months after October 31, 2007. 

(3) 50 percent of the intervals given in 

Issue 11 of the ALI. 

(4) Any application tolerance given in the 

task description of Issue 11 of the ALI. 

Restatement of Requirements of AD 2007– 

25–02 

Revision of the Airworthiness Limitations 

Section (ALS) of the Instructions for 

Continued Airworthiness (ICA) 

(o) For airplanes identified in paragraph 

(c)(2) of this AD: Within 3 months after 

January 14, 2008 (the effective date of AD 

2007–25–02), do the actions specified in 

paragraphs (o)(1) and (o)(2) of this AD. 

Accomplishing the initial ALI tasks required 

by paragraph (s) of this AD terminates the 

actions required by this paragraph. 

(1) Revise the ALS of the ICA to 

incorporate the structural inspections and 

inspection intervals defined in Airbus A310 

Airworthiness Limitations Items (ALI) 

Document, AI/SE–M2/95A.0263/06, Issue 6, 

dated April 2006 (approved by the European 

Aviation Safety Agency (EASA) on May 31, 

2006). Accomplish the actions specified in 

Issue 6 of the ALI at the times specified in 

that ALI, except as provided by paragraph (p) 

of this AD. Thereafter, except as provided by 

paragraphs (o)(2) and (t)(1) of this AD, no 

alternative structural inspection intervals 

may be approved. The actions specified in 

Issue 6 of the ALI must be accomplished in 

accordance with Issue 6 of the ALI. 

(2) Revise the ALS of the ICA to 

incorporate the new and revised structural 

inspections and inspection intervals defined 

in Airbus Temporary Revision (TR) 6.1, dated 

November 2006 (approved by the EASA on 

December 12, 2006), to Issue 6 of the ALI. 

Thereafter, except as provided by paragraph 


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(t)(1) of this AD, no alternative structural 

inspection intervals may be approved. 

Exception to Issue 6 of the ALI 

(p) The tolerance (grace period) for 

compliance with Airbus A310 Airworthiness 

Limitations Items (ALI) Document, AI/SE– 

M2/95A.0263/06, Issue 6, dated April 2006 

(‘‘Issue 6 of the ALI’’), is within 1,500 flight 

cycles after January 14, 2008, provided that 

none of the following is exceeded. 

(1) Thresholds or intervals in the operator’s 

current approved maintenance schedule that 

are taken from a previous ALI issue, if 

existing, and are higher than or equal to those 

given in Issue 6 of the ALI. 

(2) 18 months after January 14, 2008. 

(3) 50 percent of the intervals given in 

Issue 6 of the ALI. 

(4) Any application tolerance specified in 

Section D of Issue 6 of the ALI. 

Corrective Actions 

(q) Damaged, cracked, or corroded 

structure detected during any inspection 

done in accordance with Airbus A310 

Airworthiness Limitation Items (ALI) 

Document, AI/SE–M2/95A.0263/06, Issue 6, 

dated April 2006 (‘‘Issue 6 of the ALI’’), must 

be repaired, before further flight, in 

accordance with Issue 6 of the ALI; or in 

accordance with other data meeting the 

certification basis of the airplane that has 

been approved by either the Manager, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA, or the EASA (or 

its delegated agent). Where Issue 6 of the ALI 

specifies to contact Airbus for appropriate 

action: Before further flight, repair the 

damaged, cracked, or corroded structure 

using a method approved by either the 

Manager, International Branch, ANM–116, or 

the EASA (or its delegated agent). 

Reporting Requirement 

(r) If any damage that exceeds the 

allowable limits specified in Airbus A310 

Airworthiness Limitations Items (ALI) 

Document, AI/SE–M2/95A.0263/06, Issue 6, 

dated April 2006, is detected during any 

inspection required by this AD: At the 

applicable time specified in paragraph (r)(1) 

or (r)(2) of this AD, submit a report of the 

finding to Airbus, Customer Service 

Directorate, Attn: Department Manager 

Maintenance Engineering, 1 Rond Point 

Maurice Bellonte, 31707 Blagnac Cedex, 

France; e-mail: sched.maint@airbus.com. The 

report must include the ALI task reference, 

airplane serial number, the number of flight 

cycles and flight hours on the airplane, 

identification of the affected structure, 

location and description of the finding 

including its size and orientation, and the 

circumstance of detection and inspection 

method used. 

(1) If the inspection was done after January 

14, 2008: Submit the report within 30 days 

after the inspection. 

(2) If the inspection was accomplished 

prior to January 14, 2008: Submit the report 

within 30 days after January 14, 2008. 

New Requirements of This AD 

Revision of the ALS of the Instructions for 

ICA 

(s) Within 3 months after the effective date 

of this AD: Revise the ALS of the ICA to 

incorporate the structural inspections and 

inspection intervals defined in the applicable 

ALI document listed in Table 1 of this AD. 

Thereafter, except as provided by paragraph 

(t)(1) of this AD, no alternative structural 

inspections and inspection intervals may be 

approved. The actions must be accomplished 

in accordance with the applicable issue of 

the ALI. The initial ALI tasks must be done 

at the times specified in the applicable ALI 

document listed in Table 1 of this AD. 

Accomplishing the applicable initial ALI 

tasks constitutes terminating action for the 

requirements of paragraphs (g) through (r) of 

this AD for that airplane only. 

TABLE 1—AIRWORTHINESS LIMITATIONS ITEMS DOCUMENT

Model Document Issue Date 

A300 ....................................... Airbus A300 Airworthiness Limitation Items Document AI/SE–M2/95A.1308/07 ................ 4 June 2008. 

A310 ....................................... Airbus A310 Airworthiness Limitation Items Document AI/SE-M2/95A.1309/07 ................. 7 June 2008. 

A300–600 ............................... Airbus A300–600 Airworthiness Limitation Items Document AI/SE-M2/95A.1310/07 ......... 12 June 2008. 

FAA AD Differences 

Note 2: This AD differs from the MCAI 

and/or service information as follows: 

Where the MCAI includes a compliance 

time of ‘‘from the effective date of this AD,’’ 

we have determined that a compliance time 

of ‘‘within 3 months after the effective date 

of the AD’’ is appropriate. The manufacturer 

and EASA agree with this difference in 

compliance time. 

Other FAA AD Provisions 

(t) 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. 

Send information to Attn: Dan Rodina, 

Aerospace Engineer, International Branch, 

ANM–116, FAA, Transport Airplane 

Directorate, 1601 Lind Avenue, SW., Renton, 

Washington 98057–3356; telephone (425) 

227–2125; fax (425) 227–1149. 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. AMOCs 

approved previously in accordance with AD 

2007–04–11, Amendment 39–14943; AD 

2007–20–03, Amendment 39–15213; and AD 

2007–25–02, Amendment 39–15283; as 

applicable; are approved as AMOCs for the 

corresponding provisions of 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 

(u) Refer to MCAI EASA Airworthiness 

Directive 2009–0155, dated July 17, 2009; 

Airbus A300–600 Airworthiness Limitation 

Items (ALI) Document AI/SE–M2/95A.0502/ 

06, Issue 11, dated April 2006; Airbus A300– 

600 ALI Document AI/SE–M2/95A.1310/07, 

Issue 12, dated June 2008; Airbus A300 ALI 

Document SEM2/95A.1090/05, Issue 3, dated 

September 2005, as revised by Airbus A300 

Temporary Revision (TR) 3.1, dated April 

2006; Airbus A300 ALI Document AI/SE– 

M2/95A.1308/07, Issue 4, dated June 2008; 

Airbus A310 ALI Document, AI/SE–M2/ 

95A.0263/06, Issue 6, dated April 2006; 

Airbus TR 6.1, dated November 2006; Airbus 

A310 ALI Document, AI/SE–M2/95A.1309/ 

07, Issue 7, dated June 2008; and Airbus 

Industrie A300 Structural Inspection 

Document’’ (SSID), Revision 2, dated June 

1994; for related information. 

Issued in Renton, Washington, on January 

13, 2011. 

Jeffrey E. Duven, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2011–1439 Filed 1–24–11; 8:45 am] 

BILLING CODE 4910–13–P 


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