Federal Register / Vol. 76, No. 93 / Friday, May 13, 2011 / Rules and Regulations 27875 

(1) Within the next 10 hours time-inservice (TIS) after May 31, 2011 (the effective 

date of this AD) or within the next 10 days 

after May 31, 2011 (the effective date of this 

AD), whichever occurs first, cut off the 

rubber flap of the two flapper valves near 

frame 36, inspect the flapper valves, and do 

the functional test of the valves and fuselage 

drainage holes following Part A of PIAGGIO 

AERO INDUSTRIES S.p.A. Service Bulletin 

(Mandatory) N.: 80–0330, dated April 21, 

2011. 

(2) If in the inspection and functional test 

required in paragraph (f)(1) of this AD the 

valves and drain holes are found to not drain 

properly, before further flight, take corrective 

action following Part A of PIAGGIO AERO 

INDUSTRIES S.p.A. Service Bulletin 

(Mandatory) N.: 80–0330, dated April 21, 

2011. 

(3) Within the next 165 hours TIS after 

May 31, 2011 (the effective date of this AD) 

or within the next 90 days after May 31, 2011 

(the effective date of this AD), whichever 

occurs first, add drain holes on keel beam 

webs connecting the lateral bays to the center 

bays following Part B of PIAGGIO AERO 

INDUSTRIES S.p.A. Service Bulletin 

(Mandatory) N.: 80–0330, dated April 21, 

2011; or PIAGGIO AERO INDUSTRIES S.p.A. 

Service Bulletin (Mandatory) N.: 80–0291, 

dated November 29, 2010. 

(4) Within 10 days after complying with 

the actions required in paragraphs (f)(1), 

(f)(2), and (f)(3) of this AD or within 10 days 

after May 31, 2011 (the effective date of this 

AD), whichever occurs later, report the 

results (including no findings) using the 

Confirmation Slip attached to PIAGGIO 

AERO INDUSTRIES S.p.A. Service Bulletin 

(Mandatory) N.: 80–0330, dated April 21, 

2011. Send the report to Piaggio at one of the 

addresses (facsimile, email) referenced in the 

Related Information section, paragraph (i)(2) 

of this AD. 

FAA AD Differences 

Note: This AD differs from the MCAI and/ 

or service information as follows: No 

differences. 

Other FAA AD Provisions 

(g) The following provisions also apply to 

this AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, Standards Office, 

FAA, has the authority to approve AMOCs 

for this AD, if requested using the procedures 

found in 14 CFR 39.19. Send information to 

ATTN: Mike Kiesov, Aerospace Engineer, 

FAA, Small Airplane Directorate, 901 Locust, 

Room 301, Kansas City, Missouri 64106; 

telephone: (816) 329–4144; fax: (816) 329– 

4090. Before using any approved AMOC on 

any airplane to which the AMOC applies, 

notify your appropriate principal inspector 

(PI) in the FAA Flight Standards District 

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

FSDO. 

(2) Airworthy Product: For any requirement 

in this AD to obtain corrective actions from 

a manufacturer or other source, use these 

actions if they are FAA-approved. Corrective 

actions are considered 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: For the 

reporting requirement in this AD, a federal 

agency may not conduct or sponsor, and a 

person is not required to respond to, nor 

shall a person be subject to a penalty for 

failure to comply with a collection of 

information subject to the requirements of 

the Paperwork Reduction Act unless that 

collection of information displays a current 

valid OMB Control Number. The OMB 

Control Number for this information 

collection is 2120–0056. Public reporting for 

this collection of information is estimated to 

be approximately 5 minutes per response, 

including the time for reviewing instructions, 

completing and reviewing the collection of 

information. All responses to this collection 

of information are mandatory. Comments 

concerning the accuracy of this burden and 

suggestions for reducing the burden should 

be directed to the FAA at: 800 Independence 

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

Information Collection Clearance Officer, 

AES–200. 

Related Information 

(h) Refer to EASA AD No.: 2011–0074–E, 

dated April 22, 2011; PIAGGIO AERO 

INDUSTRIES S.p.A. Service Bulletin 

(Mandatory) N.: 80–0330, dated April 21, 

2011; and PIAGGIO AERO INDUSTRIES 

S.p.A. Service Bulletin (Mandatory) N.: 80– 

0291, dated November 29, 2010 for related 

information. 

Material Incorporated by Reference 

(i) You must use PIAGGIO AERO 

INDUSTRIES S.p.A. Service Bulletin 

(Mandatory) N.: 80–0330, dated April 21, 

2011; and PIAGGIO AERO INDUSTRIES 

S.p.A. Service Bulletin (Mandatory) N.: 80– 

0291, dated November 29, 2010, to do the 

actions required by this AD, unless the AD 

specifies otherwise. 

(1) The Director of the Federal Register 

approved the incorporation by reference of 

this service information under 5 U.S.C. 

552(a) and 1 CFR part 51. 

(2) For service information identified in 

this AD, contact Piaggio Aero Industries 

S.p.A–Airworthiness Office; Via Luigi 

Cibrario, 4—16154 Genova—Italy; telephone: 

+39 010 6481353; fax: +39 010 6481881; 

E-mail: airworthiness@piaggioaero.it. 

(3) You may review copies of the 

referenced service information at the FAA, 

Small Airplane Directorate, 901 Locust, 

Kansas City, Missouri 64106. For information 

on the availability of this material at the 

FAA, call (816) 329–4148. 

(4) You may also review copies of the 

service information incorporated by reference 

for this AD at the National Archives and 

Records Administration (NARA). For 

information on the availability of this 

material at NARA, call (202) 741–6030, or go 

to: http://www.archives.gov/federal_register/ 

code_of_federal_regulations/ 

ibr_locations.html. 

Issued in Kansas City, Missouri, on May 4, 

2011. 

Earl Lawrence, 

Manager, Small Airplane Directorate, Aircraft 

Certification Service. 

[FR Doc. 2011–11330 Filed 5–12–11; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2011–0030; Directorate 

Identifier 2009–NM–183–AD; Amendment 

39–16698; AD 2011–10–17] 

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), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are superseding three 

existing airworthiness directives (ADs) 

that apply to the products listed above. 

This AD results from mandatory 

continuing airworthiness information 

(MCAI) originated by an aviation 

authority of another country to identify 

and correct an unsafe condition on an 

aviation product. The MCAI describes 

the unsafe condition as: 

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. We are issuing 

this AD to require actions to correct the 

unsafe condition on these products. 

DATES: This AD becomes effective June 

17, 2011. 

The Director of the Federal Register 

approved the incorporation by reference 

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of certain publications listed in this AD 

as of June 17, 2011. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain other publications listed in 

this AD as of January 14, 2008 (72 FR 

69612, December 10, 2007). 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain other publication listed in 

this AD as of October 31, 2007 (72 FR 

54536, September 26, 2007). 

The Director of the Federal Register 

approved the incorporation by reference 

of certain other publications listed in 

this AD as of April 3, 2007 (72 FR 8604, 

February 27, 2007). 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain other publication listed in 

this AD as of August 9, 1996 (61 FR 

35122, July 5, 1996). 

ADDRESSES: You may examine the AD 

docket on the Internet at http:// 

www.regulations.gov or in person at the 

U.S. Department of Transportation, 

Docket Operations, M–30, West 

Building Ground Floor, Room W12–140, 

1200 New Jersey Avenue, SE., 

Washington, DC. 

FOR FURTHER INFORMATION CONTACT: Dan 

Rodina, Aerospace Engineer, 

International Branch, ANM–116, FAA, 

Transport Airplane Directorate, 1601 

Lind Avenue, SW., Renton, Washington 

98057–3356; telephone (425) 227–2125; 

fax (425) 227–1149. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to include an AD that would 

apply to the specified products. That 

NPRM was published in the Federal 

Register on January 25, 2011 (76 FR 

4260), and proposed to supersede AD 

2007–04–11, Amendment 39–14943 (72 

FR 8604, February 27, 2007); AD 2007– 

20–03, Amendment 39–15213 (72 FR 

54536, September 26, 2007); and AD 

2007–25–02, Amendment 39–15283 (72 

FR 69612, December 10, 2007). That 

NPRM proposed 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 

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. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

received no comments on the NPRM or 

on the determination of the cost to the 

public. 

Conclusion 

We reviewed the available data and 

determined that air safety and the 

public interest require adopting the AD 

as proposed. 

Differences Between This AD and the 

MCAI or Service Information 

We have reviewed the MCAI and 

related service information and, in 

general, agree with their substance. But 

we might have found it necessary to use 

different words from those in the MCAI 

to ensure the AD is clear for U.S. 

operators and is enforceable. In making 

these changes, we do not intend to differ 

substantively from the information 

provided in the MCAI and related 

service information. 

We might also have required different 

actions in this AD from those in the 

MCAI in order to follow our FAA 

policies. Any such differences are 

highlighted in a NOTE within the AD. 

Costs of Compliance 

We estimate that this AD will 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 will take about 1 

work-hour per product to comply with 

the new basic requirements of this AD. 

The average labor rate is $85 per workhour. Based on these figures, we 

estimate the cost of this AD to the 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 AD will not 

have federalism implications under 

Executive Order 13132. This AD will 

not have a substantial direct effect on 

the States, on the relationship between 

the national government and the States, 

or on the distribution of power and 

responsibilities among the various 

levels of government. 

For the reasons discussed above, I 

certify this AD: 

1. Is not a ‘‘significant regulatory 

action′′ under Executive Order 12866; 

2. Is not a ‘‘significant rule′′ under the 

DOT Regulatory Policies and Procedures 

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

3. Will not have a significant 

economic impact, positive or negative, 

on a substantial number of small entities 

under the criteria of the Regulatory 

Flexibility Act. 

We prepared a regulatory evaluation 

of the estimated costs to comply with 

this AD and placed it in the AD docket. 

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Federal Register / Vol. 76, No. 93 / Friday, May 13, 2011 / Rules and Regulations 27877 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http:// 

www.regulations.gov; or in person at the 

Docket Operations office between 9 a.m. 

and 5 p.m., Monday through Friday, 

except Federal holidays. The AD docket 

contains the NPRM, the regulatory 

evaluation, any comments received, and 

other information. The street address for 

the Docket Operations office (telephone 

(800) 647–5527) is in the ADDRESSES

section. Comments will be available in 

the AD docket shortly after receipt. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety. 

Adoption of the Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA amends 14 CFR part 39 as 

follows: 

PART 39—AIRWORTHINESS 

DIRECTIVES 

■ 1. The authority citation for part 39 

continues to read as follows: 

Authority: 49 U.S.C. 106(g), 40113, 44701. 

§ 39.13 [Amended] 

■ 2. The FAA amends § 39.13 by 

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: 

2011–10–17 Airbus: Amendment 39–16698. 

Docket No. FAA–2011–0030; Directorate 

Identifier 2009–NM–183–AD. 

Effective Date 

(a) This airworthiness directive (AD) 

becomes effective June 17, 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 

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, Revision 2, dated June 1994. 

Accomplish the actions specified in the 

service bulletins identified in Section 6, ‘‘SB 

Reference List,′′ in Airbus Industrie A300 

Supplemental Structural Inspection 

Document, Revision 2, dated June 1994, 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,′′ in Airbus Industrie A300 

Supplemental Structural Inspection 

Document, Revision 2, dated June 1994: 

Accomplish the actions specified in those 

service bulletins within the grace period 

specified in those service bulletins. 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,′′ in Airbus Industrie A300 

Supplemental Structural Inspection 

Document, Revision 2, dated June 1994, 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 Document 

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

2005, as revised by Airbus A300 Temporary 

Revision (TR) 3.1, dated April 2006. 

Accomplish the actions specified in Airbus 

A300 Airworthiness Limitation Items 

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

September 2005, as revised by Airbus A300 

TR 3.1, dated April 2006, at the times 

specified in that ALI, except as provided by 

paragraph (i) of this AD. The actions must be 

accomplished in accordance with Airbus 

A300 Airworthiness Limitation Items 

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

September 2005, as revised by Airbus A300 

TR 3.1, dated April 2006. 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, 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 Airbus A300 Airworthiness Limitation 

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

dated September 2005: 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 A300 

Airworthiness Limitation Items Document 

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

2005, must be repaired, before further flight, 

in accordance with Airbus A300 

Airworthiness Limitation Items Document 

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

2005, as revised by Airbus A300 TR 3.1, 

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dated April 2006, 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, Transport 

Airplane Directorate, FAA; or by the 

European Aviation Safety Agency (EASA) (or 

its delegated agent). 

(k) Where the Airbus A300 Airworthiness 

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 Document AI/SE–M2/ 

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

tolerance (grace period) for compliance 

(specified in paragraph 2 of Section B— 

Program Rules) with Airbus A300–600 

Airworthiness Limitation Items Document 

AI/SE–M2/95A.0502/06, Issue 11, dated 

April 2006, 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 Airbus A300–600 Airworthiness 

Limitation Items Document AI/SE–M2/ 

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

(2) 8 months after October 31, 2007. 

(3) 50 percent of the intervals given in 

Airbus A300–600 Airworthiness Limitation 

Items Document AI/SE–M2/95A.0502/06, 

Issue 11, dated April 2006. 

(4) Any application tolerance given in the 

task description of Airbus A300–600 

Airworthiness Limitation Items Document 

AI/SE–M2/95A.0502/06, Issue 11, dated 

April 2006. 

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 Document, 

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

2006 (approved by the EASA on May 31, 

2006). Accomplish the actions specified in 

Airbus A310 Airworthiness Limitations Items 

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

dated April 2006, at the times specified in 

Airbus A310 Airworthiness Limitations Items 

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

dated April 2006, 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 Airbus A310 Airworthiness 

Limitations Items Document, AI/SE–M2/ 

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

be accomplished in accordance with Airbus 

A310 Airworthiness Limitations Items 

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

dated April 2006. 

(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 Airbus A310 

Airworthiness Limitations Items Document, 

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

2006. Thereafter, except as provided by 

paragraph (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 Document, AI/SE–M2/ 

95A.0263/06, Issue 6, dated April 2006, 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 Airbus A310 Airworthiness 

Limitations Items Document, AI/SE–M2/ 

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

(2) 18 months after January 14, 2008. 

(3) 50 percent of the intervals given in 

Airbus A310 Airworthiness Limitations Items 

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

dated April 2006. 

(4) Any application tolerance specified in 

Section D of Airbus A310 Airworthiness 

Limitations Items Document, AI/SE–M2/ 

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

Corrective Actions 

(q) Damaged, cracked, or corroded 

structure detected during any inspection 

done in accordance with Airbus A310 

Airworthiness Limitations Items Document, 

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

2006, must be repaired, before further flight, 

in accordance with Airbus A310 

Airworthiness Limitations Items Document, 

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

2006; 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, or 

the EASA (or its delegated agent). Where 

Airbus A310 Airworthiness Limitations Items 

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

dated April 2006, 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 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 maintenance program 

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. 

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Federal Register / Vol. 76, No. 93 / Friday, May 13, 2011 / Rules and Regulations 27879 

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 this 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. 

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, FAA, 

Transport Airplane Directorate, 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. 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 FAAapproved if they are approved by the State 

of Design Authority (or their delegated 

agent). You are required to assure the product 

is airworthy before it is returned to service. 

(3) Reporting Requirements: 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 Document AI/SE–M2/95A.0502/06, 

Issue 11, dated April 2006; Airbus A300–600 

Airworthiness Limitation Items Document 

AI/SE–M2/95A.1310/07, Issue 12, dated June 

2008; Airbus A300 Airworthiness Limitation 

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

dated September 2005, as revised by Airbus 

A300 Temporary Revision 3.1, dated April 

2006; Airbus A300 Airworthiness Limitation 

Items Document AI/SE–M2/95A.1308/07, 

Issue 4, dated June 2008; Airbus A310 

Airworthiness Limitations Items Document, 

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

2006; Airbus Temporary Revision 6.1, dated 

November 2006; Airbus A310 Airworthiness 

Limitation Items Document, AI/SE–M2/ 

95A.1309/07, Issue 7, dated June 2008; and 

Airbus Industrie A300 Structural Inspection 

Document, Revision 2, dated June 1994; for 

related information. 

Material Incorporated by Reference 

(v) You must use the service information 

contained in Table 2 of this AD to do the 

actions required by this AD, as applicable, 

unless the AD specifies otherwise. 

TABLE 2—ALL MATERIAL INCORPORATED BY REFERENCE

Document Issue/revision Date 

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

Airbus A300 Airworthiness Limitation Items Document SEM2/95A.1090/05, as revised by Airbus 

A300 TR 3.1, dated April 2006.

3 .................................. September 2005. 

Airbus A300 Airworthiness Limitation Items, Document SEM2/95A.1090/05, Temporary Revision 

3.1, including attachment, dated April 2006, and including attachments dated September 2005.

Original ........................ April 2006. 

Airbus Temporary Revision 6.1, including pages 1 and 2 of Section D and page 1 of Section E, 

dated November 2006, to Airbus A310 Airworthiness Limitations Items Document, AI/SE–M2/ 

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

Original ........................ November 2006. 

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

Airbus A310 Airworthiness Limitations Items Document AI/SE-M2/95A.0263/06 ............................ 6 .................................. April 2006. 

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

Airbus A300–600 Airworthiness Limitation Items Document AI/SE-M2/95A.0502/06 ...................... 11 ................................ April 2006. 

Airbus Industrie A300 Structural Inspection Document .................................................................... 2 .................................. June 1994. 

(1) The Director of the Federal Register 

approved the incorporation by reference of 

the service information contained in Table 3 

of this AD under 5 U.S.C. 552(a) and 1 CFR 

part 51. 

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27880 Federal Register / Vol. 76, No. 93 / Friday, May 13, 2011 / Rules and Regulations 

TABLE 3—NEW MATERIAL INCORPORATED BY REFERENCE

Document Issue Date 

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

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

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

(2) The Director of the Federal Register 

previously approved the incorporation by 

reference of Airbus A310 Airworthiness 

Limitations Items Document, AI/SE–M2/ 

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

Airbus Temporary Revision 6.1, including 

pages 1 and 2 of Section D and page 1 of 

Section E, dated November 2006, to Airbus 

A310 Airworthiness Limitations Items 

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

dated April 2006; on January 14, 2008 (72 FR 

69612, December 10, 2007). 

(3) The Director of the Federal Register 

previously approved the incorporation by 

reference of Airbus A300–600 Airworthiness 

Limitation Items Document AI/SE–M2/ 

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

October 31, 2007 (72 FR 54536, September 

26, 2007). 

(4) The Director of the Federal Register 

previously approved the incorporation by 

reference of Airbus A300 Airworthiness 

Limitations Items Document SEM2/ 

95A.1090/05, Issue 3, dated September 2005, 

as revised by Airbus A300 Airworthiness 

Limitation Items Document SEM2/95A.1090/ 

05, Temporary Revision 3.1, including 

attachment, dated April 2006, and including 

attachments, dated September 2005, on April 

3, 2007 (72 FR 8604, February 27, 2007). 

(5) The Director of the Federal Register 

previously approved the incorporation by 

reference of Airbus Industrie A300 

Supplemental Structural Inspection 

Document, Revision 2, dated June 1994, on 

August 9, 1996 (61 FR 35122, July 5, 1996). 

(6) For service information identified in 

this AD, contact Airbus SAS–EAW 

(Airworthiness Office), 1 Rond Point Maurice 

Bellonte, 31707 Blagnac Cedex, France; 

telephone +33 5 61 93 36 96; fax +33 5 61 

93 44 51; e-mail account.airwortheas@airbus.com; Internet http:// 

www.airbus.com. 

(7) You may review copies of the service 

information at the FAA, Transport Airplane 

Directorate, 1601 Lind Avenue SW., Renton, 

Washington. For information on the 

availability of this material at the FAA, call 

425–227–1221. 

(8) You may also review copies of the 

service information that is incorporated by 

reference at the National Archives and 

Records Administration (NARA). For 

information on the availability of this 

material at NARA, call 202–741–6030, or go 

to: http://www.archives.gov/federal_register/ 

code_of_federal_regulations/ 

ibr_locations.html. 

Issued in Renton, Washington, on May 2, 

2011. 

Kalene C. Yanamura, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2011–11333 Filed 5–12–11; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2011–0042; Directorate 

Identifier 2010–NM–267–AD; Amendment 

39–16695; AD 2011–10–14] 

RIN 2120–AA64 

Airworthiness Directives; DASSAULT 

AVIATION Model MYSTERE–FALCON 

50 Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are superseding an 

existing airworthiness directive (AD) 

that applies to the products listed above. 

This AD results from mandatory 

continuing airworthiness information 

(MCAI) originated by an aviation 

authority of another country to identify 

and correct an unsafe condition on an 

aviation product. The MCAI describes 

the unsafe condition as: 

On two occurrences on Myste`re-Falcon 50 

aeroplanes in service, it was detected that 

two pipes of the emergency brake system #2 

located near the nose landing gear bearing 

were swapped. 

The swapping of these two pipes implies 

that when the Left Hand (LH) brake pedal is 

depressed, the Right Hand (RH) brake unit is 

activated, and conversely, when the RH brake 

pedal is depressed, the LH brake unit is 

actuated. This constitutes an unsafe 

condition, which may go unnoticed as the 

condition is latent until the emergency brake 

system #2 is used. This condition, if not 

corrected, could ultimately lead to a runway 

excursion of the aeroplane. 

* * * * * 

We are issuing this AD to require 

actions to correct the unsafe condition 

on these products. 

DATES: This AD becomes effective June 

17, 2011. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of December 9, 2010 (75 FR 71530, 

November 24, 2010). 

ADDRESSES: You may examine the AD 

docket on the Internet at http:// 

www.regulations.gov or in person at the 

U.S. Department of Transportation, 

Docket Operations, M–30, West 

Building Ground Floor, Room W12–140, 

1200 New Jersey Avenue, SE., 

Washington, DC. 

FOR FURTHER INFORMATION CONTACT: Tom 

Rodriguez, Aerospace Engineer, 

International Branch, ANM–116, 

Transport Airplane Directorate, FAA, 

1601 Lind Avenue, SW., Renton, 

Washington 98057–3356; telephone 

(425) 227–1137; fax (425) 227–1149. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to include an AD that would 

apply to the specified products. That 

NPRM was published in the Federal 

Register on February 16, 2011 (76 FR 

8919), and proposed to supersede AD 

2010–24–08, Amendment 39–16527 (75 

FR 71530, November 24, 2010). That 

NPRM proposed to correct an unsafe 

condition for the specified products. 

The MCAI states: 

In AD 2010–24–08, we pointed out 

that the corresponding EASA AD, AD 

2010–0208–E, dated October 12, 2010, 

requires painting the pipes end of the 

emergency brake system number 2 and 

related unions within 7 months after the 

effective date of that AD. We explained 

that AD 2010–24–08 did not require that 

action, and that we might consider 

additional rulemaking to require this 

action in the future. We have 

determined that further rulemaking is 

indeed necessary to require that action, 

and this AD follows from that 

determination. 

You may obtain further information 

by examining the MCAI in the AD 

docket. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

received no comments on the NPRM or 

on the determination of the cost to the 

public. 

Conclusion 

We reviewed the available data and 

determined that air safety and the 

public interest require adopting the AD 

as proposed. 

WReier-Aviles on DSKGBLS3C1PROD with RULES