Federal Register / Vol. 76, No. 91 / Wednesday, May 11, 2011 / Rules and Regulations 27227 

TABLE 9—MATERIAL PREVIOUSLY INCORPORATED BY REFERENCE

Service Bulletin Revision Date 

Airbus Service Bulletin A310–57–2038 ....................................................................................................... 2 ................... January 4, 1996. 

Airbus Service Bulletin A310–57–2046 ....................................................................................................... 4 ................... October 16, 1996. 

Airbus Service Bulletin A310–57–2046, Change Notice 4A ....................................................................... Original ......... October 16, 1996. 

(3) 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. 

(4) 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. 

(5) 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 April 22, 

2011. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2011–10684 Filed 5–10–11; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2010–1274; Directorate 

Identifier 2010–NM–090–AD; Amendment 

39–16687; AD 2011–10–06] 

RIN 2120–AA64 

Airworthiness Directives; Airbus Model 

A310 Series Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for the 

products listed above. This AD results 

from mandatory continuing 

airworthiness information (MCAI) 

originated by an aviation authority of 

another country to identify and correct 

an unsafe condition on an aviation 

product. The MCAI describes the unsafe 

condition as: 

DGAC [Direction Ge ́ne ́rale de l’Aviation 

Civile] France AD 1992–106–132(B) * * * 

was issued to require a set of inspection and 

modification tasks which addressed JAR/FAR 

[Joint Aviation Regulation/Federal Aviation 

Regulation] 25–571 requirements related to 

damage-tolerance and fatigue evaluation of 

structure. 

* * * * * 

The unsafe condition is reduced 

structural integrity of the wings. We are 

issuing this AD to require actions to 

correct the unsafe condition on these 

products. 

DATES: This AD becomes effective June 

15, 2011. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of June 15, 2011. 

ADDRESSES: You may examine the AD 

docket on the Internet at http:// 

www.regulations.gov or in person at the 

U.S. Department of Transportation, 

Docket Operations, M–30, West 

Building Ground Floor, Room W12–140, 

1200 New Jersey Avenue, SE., 

Washington, DC. 

FOR FURTHER INFORMATION CONTACT: 

Dan Rodina, Aerospace Engineer, 

International Branch, ANM–116, 

Transport Airplane Directorate, FAA, 

1601 Lind Avenue, SW., Renton, 

Washington 98057–3356; telephone 

(425) 227–2125; fax (425) 227–1149. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to include an AD that would 

apply to the specified products. That 

NPRM was published in the Federal 

Register on January 3, 2011 (76 FR 50). 

That NPRM proposed to correct an 

unsafe condition for the specified 

products. The MCAI states: 

DGAC [Direction Ge ́ne ́rale de l’Aviation 

Civile] France AD 1992–106–132(B) original 

issue up to revision 7 was issued to require 

a set of inspection and modification tasks 

which addressed JAR/FAR [Joint Aviation 

Regulation/Federal Aviation Regulation] 25– 

571 requirements related to damage-tolerance 

and fatigue evaluation of structure. 

Following the Extended Design Service 

Goal activities as part of the Structure Task 

Group for the Airbus A310 program, EASA 

[European Aviation Safety Agency] 

published AD 2007–0053, which replaced 

DGAC France AD F–1992–106–132R7. 

Since the issuance of AD 2007–0053R1, the 

thresholds and the intervals of Airbus 

Service Bulletins (SB) A310–57–2050 and 

A310–57–2064 have been updated. 

Consequently, this new [EASA] AD takes 

over the requirements of paragraphs 1.15 and 

1.17 of EASA AD 2007–0053R1, which has 

been revised accordingly * * * and requires 

the accomplishment of Airbus SB A310–57– 

2048 at revision 01. 

The unsafe condition is reduced 

structural integrity of the wings. The 

required actions are as follows, 

depending on airplane configuration: 

• Cold working of trellis boom 

drainage holes. 

• Repetitive detailed or rotating probe 

inspections for cracking in the drain 

holes on the lower skin panel in the 

center wing box between frames 42 and 

46 and corrective actions if necessary. 

Corrective actions include repairing 

cracking and contacting the FAA or 

EASA for repair and doing the repair. 

• Repetitive eddy current inspections 

for cracking of the upper corner angle 

fitting and the vertical tee fitting at left 

and right frame 40, and corrective 

actions if necessary. Corrective actions 

include repairing, replacing the internal 

angle fitting, and contacting the FAA or 

EASA for repair and doing the repair. 

You may obtain further information 

by examining the MCAI in the AD 

docket. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

considered the comment received. 

Request To Revise Paragraph Header 

An anonymous commenter requested 

that the paragraph reference in the 

paragraph header between table 5 and 

paragraph (k) of the NPRM be revised 

from ‘‘paragraph (h)’’ to ‘‘paragraph (j)’’. 

The commenter believed the intent was 

to reference paragraph (j) of the NPRM. 

We agree with the commenter’s 

request. We have revised the paragraph 

header between table 5 and paragraph 

(k) of this AD. 

Conclusion 

We reviewed the available data, 

including the comment received, and 

determined that air safety and the 

public interest require adopting the AD 

with the change described previously. 

We determined that this change will not 


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27228 Federal Register / Vol. 76, No. 91 / Wednesday, May 11, 2011 / Rules and Regulations 

increase the economic burden on any 

operator or increase the scope of the AD. 

Differences Between This AD and the 

MCAI or Service Information 

We have reviewed the MCAI and 

related service information and, in 

general, agree with their substance. But 

we might have found it necessary to use 

different words from those in the MCAI 

to ensure the AD is clear for U.S. 

operators and is enforceable. In making 

these changes, we do not intend to differ 

substantively from the information 

provided in the MCAI and related 

service information. 

We might also have required different 

actions in this AD from those in the 

MCAI in order to follow our FAA 

policies. Any such differences are 

highlighted in a Note within the AD. 

Costs of Compliance 

We estimate that this AD will affect 

44 products of U.S. registry. We also 

estimate that it will take about 137 

work-hours per product to comply with 

the basic requirements of this AD. The 

average labor rate is $85 per work-hour. 

Based on these figures, we estimate the 

cost of this AD to the U.S. operators to 

be $512,380, or $11,645 per product. 

Authority for This Rulemaking 

Title 49 of the United States Code 

specifies the FAA’s authority to issue 

rules on aviation safety. Subtitle I, 

section 106, describes the authority of 

the FAA Administrator. ‘‘Subtitle VII: 

Aviation Programs,’’ describes in more 

detail the scope of the Agency’s 

authority. 

We are issuing this rulemaking under 

the authority described in ‘‘Subtitle VII, 

Part A, Subpart III, Section 44701: 

General requirements.’’ Under that 

section, Congress charges the FAA with 

promoting safe flight of civil aircraft in 

air commerce by prescribing regulations 

for practices, methods, and procedures 

the Administrator finds necessary for 

safety in air commerce. This regulation 

is within the scope of that authority 

because it addresses an unsafe condition 

that is likely to exist or develop on 

products identified in this rulemaking 

action. 

Regulatory Findings 

We determined that this AD will not 

have federalism implications under 

Executive Order 13132. This AD will 

not have a substantial direct effect on 

the States, on the relationship between 

the national government and the States, 

or on the distribution of power and 

responsibilities among the various 

levels of government. 

For the reasons discussed above, I 

certify this AD: 

1. Is not a ‘‘significant regulatory 

action’’ under Executive Order 12866; 

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

DOT Regulatory Policies and Procedures 

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

3. Will not have a significant 

economic impact, positive or negative, 

on a substantial number of small entities 

under the criteria of the Regulatory 

Flexibility Act. 

We prepared a regulatory evaluation 

of the estimated costs to comply with 

this AD and placed it in the AD docket. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http:// 

www.regulations.gov; or in person at the 

Docket Operations office between 9 a.m. 

and 5 p.m., Monday through Friday, 

except Federal holidays. The AD docket 

contains the NPRM, the regulatory 

evaluation, any comments received, and 

other information. The street address for 

the Docket Operations office (telephone 

(800) 647–5527) is in the ADDRESSES

section. Comments will be available in 

the AD docket shortly after receipt. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety. 

Adoption of the Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA amends 14 CFR part 39 as 

follows: 

PART 39—AIRWORTHINESS 

DIRECTIVES 

■ 1. The authority citation for part 39 

continues to read as follows: 

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

§ 39.13 [Amended] 

■ 2. The FAA amends § 39.13 by adding 

the following new AD: 

2011–10–06 Airbus: Amendment 39–16687. 

Docket No. FAA–2010–1274; Directorate 

Identifier 2010–NM–090–AD. 

Effective Date 

(a) This airworthiness directive (AD) 

becomes effective June 15, 2011. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to Airbus Model A310– 

203, –204, –221, –222, –304, –322, –324, and 

–325 airplanes, certificated in any category, 

all serial numbers. 

Subject 

(d) Air Transport Association (ATA) of 

America Code 57: Wings. 

Reason 

(e) The mandatory continuing 

airworthiness information (MCAI) states: 

DGAC [Direction Ge ́ne ́rale de l’Aviation 

Civile] France AD 1992–106–132(B) * * * 

was issued to require a set of inspection and 

modification tasks which addressed JAR/FAR 

[Joint Aviation Regulation/Federal Aviation 

Regulation] 25–571 requirements related to 

damage-tolerance and fatigue evaluation of 

structure. 

* * * * * 

The unsafe condition is reduced structural 

integrity of the wings. 

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. 

Cold Working of Trellis Boom Drainage 

Holes 

(g) For Model A310–203, –204, –222, –304, 

–322 and –324 airplanes, except airplanes 

identified in paragraphs (g)(1), (g)(2), and 

(g)(3) of this AD: Within the applicable time 

specified in Table 1 of this AD, cold work the 

trellis boom drainage holes, in accordance 

with the Accomplishment Instructions of 

Airbus Mandatory Service Bulletin A310–57– 

2048, Revision 01, dated May 22, 2007. 

Certain compliance times specified in Table 

1 of this AD are applicable to short range use, 

average flight time (AFT) equal to or less than 

3.6 hours; or long range use, AFT exceeding 

3.6 hours. 

TABLE 1—COMPLIANCE TIMES FOR PARAGRAPH (g) OF THIS AD 

Airplanes, as identified in Airbus Mandatory 

Service Bulletin A310–57–2048, Revision 

01, dated May 22, 2007 

Compliance time (whichever occurs later) 

Configuration 01 airplanes ................................. Prior to the accumulation of 31,800 total flight 

cycles or 63,600 total flight hours, whichever occurs first.

Within 6 months after the effective date of this 

AD. 


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TABLE 1—COMPLIANCE TIMES FOR PARAGRAPH (g) OF THIS AD—Continued 

Configuration 02 airplanes ................................. Prior to the accumulation of 40,000 total flight 

cycles or 80,000 total flight hours, whichever occurs first.

Within 6 months after the effective date of this 

AD. 

Configuration 03 short range airplanes .............. Prior to the accumulation of 30,950 total flight 

cycles or 86,750 total flight hours, whichever occurs first.

Within 6 months after the effective date of this 

AD. 

Configuration 03 long range airplanes ............... Prior to the accumulation of 24,100 total flight 

cycles or 120,600 total flight hours, whichever occurs first.

Within 6 months after the effective date of this 

AD. 

(1) Airplanes on which Airbus 

modification 06130 was done in production. 

(2) Airplanes on which Airbus Mandatory 

Service Bulletin A310–57–2048 was done in 

service. 

(3) Airplanes on which rework of cracked 

drain holes was done in accordance with 

Airbus Mandatory Service Bulletin A310–57– 

2050. 

Inspection of Trellis Boom Drainage Holes 

(h) For all airplanes: Within the applicable 

intervals specified in Table 2 of this AD, 

perform a detailed or rotating probe 

inspection for cracking in the drain holes on 

the lower skin panel in the center wing box 

between frames 42 and 46, in accordance 

with the Accomplishment Instructions of 

Airbus Mandatory Service Bulletin A310–57– 

2050, Revision 02, dated August 27, 2009. 

Repeat the inspections thereafter at intervals 

not to exceed the applicable times specified 

in Table 3 of this AD. Certain compliance 

times specified in Tables 2 and 3 of this AD 

are applicable to short range use, average 

flight time (AFT) equal to or less than 3.6 

hours; or long range use, AFT exceeding 3.6 

hours. 

TABLE 2—COMPLIANCE TIMES FOR PARAGRAPH (h) OF THIS AD 

Airplanes, as identified in Airbus Mandatory 

Service Bulletin A310–57–2050, Revision 

02, dated August 27, 2009 

Compliance time (whichever occurs later) 

Configuration 01 airplanes ................................. Prior to the accumulation of 17,800 total flight 

cycles or 35,600 total flight hours, whichever occurs first.

Within 1,000 flight cycles or 2,000 flight hours, 

whichever occurs first, after the effective 

date of this AD. 

Configuration 02 airplanes on which Airbus 

Mandatory Service Bulletin A310–57–2048 

has been done within the ‘‘recommended’’ 

compliance times specified in paragraph 

1.E.(2), ‘‘Accomplishment Timescale,’’ of Airbus Mandatory Service Bulletin A310–57– 

2048, Revision 01, dated May 22, 2007.

Within 32,850 flight cycles or 65,700 flight 

hours, whichever occurs first, after accomplishing Airbus Mandatory Service Bulletin 

A310–57–2048.

Within 1,000 flight cycles or 2,000 flight hours, 

whichever occurs first, after the effective 

date of this AD. 

Configuration 02 airplanes on which Airbus 

Mandatory Service Bulletin A310–57–2048 

has not been done within the ‘‘recommended’’ compliance times specified in 

paragraph 1.E.(2), ‘‘Accomplishment 

Timescale,’’ of Airbus Mandatory Service Bulletin A310–57–2048, Revision 01, dated May 

22, 2007.

Within 8,600 flight cycles or 17,250 flight 

hours, whichever occurs first, after accomplishing the detailed inspection specified in 

Airbus Mandatory Service Bulletin A310– 

57–2048; 

OR 

Within 11,400 flight cycles or 22,800 flight 

hours, whichever occurs first, after accomplishing the rotating probe inspection specified in Airbus Mandatory Service Bulletin 

A310–57–2048.

Within 1,000 flight cycles or 2,000 flight hours, 

whichever occurs first, after the effective 

date of this AD. 

Configuration 03 airplanes ................................. Prior to the accumulation of 22,300 total flight 

cycles or 44,550 total flight hours, whichever occurs first.

Within 1,000 flight cycles or 2,000 flight hours, 

whichever occurs first, after the effective 

date of this AD. 

Configuration 04 airplanes ................................. Prior to the accumulation of 41,550 total flight 

cycles or 83,100 total flight hours, whichever occurs first.

Within 1,000 flight cycles or 2,000 flight hours, 

whichever occurs first, after the effective 

date of this AD. 

Configuration 05 airplanes on which Airbus 

Mandatory Service Bulletin A310–57–2048 

has been done within the ‘‘recommended’’ 

compliance times specified in paragraph 

1.E.(2), ‘‘Accomplishment Timescale,’’ of Airbus Mandatory Service Bulletin A310–57– 

2048, Revision 01, dated May 22, 2007.

Prior to the accumulation of 40,000 total flight 

cycles or 80,000 total flight hours, whichever occurs first.

Within 1,000 flight cycles or 2,000 flight hours, 

whichever occurs first, after the effective 

date of this AD. 

Configuration 05 airplanes on which Airbus 

Mandatory Service Bulletin A310–57–2048 

has not been done within the ‘‘recommended’’ compliance times specified in 

paragraph 1.E.(2), ‘‘Accomplishment 

Timescale,’’ of Airbus Mandatory Service Bulletin A310–57–2048, Revision 01, dated May 

22, 2007.

Within 10,600 flight cycles or 21,150 flight 

hours, whichever occurs first, after accomplishing the detailed inspection specified in 

Airbus Mandatory Service Bulletin A310– 

57–2048; 

OR 

Within 13,900 flight cycles or 27,800 flight 

hours, whichever occurs first, after accomplishing the rotating probe inspection specified in Airbus Mandatory Service Bulletin 

A310–57–2048.

Within 1,000 flight cycles or 2,000 flight hours, 

whichever occurs first, after the effective 

date of this AD. 


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TABLE 2—COMPLIANCE TIMES FOR PARAGRAPH (h) OF THIS AD—Continued 

Configuration 06 short range airplanes .............. Prior to the accumulation of 17,250 total flight 

cycles or 48,400 total flight hours, whichever occurs first.

Within 1,000 flight cycles or 2,800 flight hours, 

whichever occurs first, after the effective 

date of this AD. 

Configuration 06 long range airplanes ............... Prior to the accumulation of 13,450 total flight 

cycles or 67,250 total flight hours, whichever occurs first.

Within 800 flight cycles or 4,000 flight hours, 

whichever occurs first, after the effective 

date of this AD. 

Configuration 07 short range airplanes .............. Prior to the accumulation of 32,150 total flight 

cycles or 90,050 total flight hours, whichever occurs first.

Within 1,000 flight cycles or 2,800 flight hours, 

whichever occurs first, after the effective 

date of this AD. 

Configuration 07 long range airplanes ............... Prior to the accumulation of 25,050 total flight 

cycles or 125,150 total flight hours, whichever occurs first.

Within 800 flight cycles or 4,000 flight hours, 

whichever occurs first, after the effective 

date of this AD. 

Configuration 08 short range airplanes on 

which Airbus Mandatory Service Bulletin 

A310–57–2048 has been done within the 

‘‘recommended’’ compliance times specified 

in paragraph 1.E.(2), ‘‘Accomplishment 

Timescale,’’ of Airbus Mandatory Service Bulletin A310–57–2048, Revision 01, dated May 

22, 2007.

Prior to the accumulation of 30,950 total flight 

cycles or 86,750 total flight hours, whichever occurs first.

Within 1,000 flight cycles or 2,800 flight hours, 

whichever occurs first, after the effective 

date of this AD. 

Configuration 08 short range airplanes on 

which Airbus Mandatory Service Bulletin 

A310–57–2048 has not been done within the 

‘‘recommended’’ compliance times specified 

in paragraph 1.E.(2), ‘‘Accomplishment 

Timescale,’’ of Airbus Mandatory Service Bulletin A310–57–2048, Revision 01, dated May 

22, 2007.

Within 8,200 flight cycles or 23,000 flight 

hours, whichever occurs first, after accomplishing the detailed inspection specified in 

Airbus Mandatory Service Bulletin A310– 

57–2048; 

OR 

Within 10,800 flight cycles or 30,300 flight 

hours, whichever occurs first, after accomplishing the rotating probe inspection specified in Airbus Mandatory Service Bulletin 

A310–57–2048.

Within 1,000 flight cycles or 2,800 flight hours, 

whichever occurs first, after the effective 

date of this AD. 

Configuration 08 long range airplanes on which 

Airbus Mandatory Service Bulletin A310–57– 

2048 has been done within the ‘‘recommended’’ compliance times specified in 

paragraph 1.E.(2), ‘‘Accomplishment 

Timescale,’’ of Airbus Mandatory Service Bulletin A310–57–2048, Revision 01, dated May 

22, 2007.

Prior to the accumulation of 24,100 total flight 

cycles or 120,600 total flight hours, whichever occurs first.

Within 800 flight cycles or 4,000 flight hours, 

whichever occurs first, after the effective 

date of this AD. 

Configuration 08 long range airplanes on which 

Airbus Mandatory Service Bulletin A310–57– 

2048 has not been done within the ‘‘recommended’’ compliance times specified in 

paragraph 1.E.(2), ‘‘Accomplishment 

Timescale,’’ of Airbus Mandatory Service Bulletin A310–57–2048, Revision 01, dated May 

22, 2007.

Within 6,400 flight cycles or 31,950 flight 

hours, whichever occurs first, after accomplishing the detailed inspection specified in 

Airbus Mandatory Service Bulletin A310– 

57–2048; 

OR 

Within 8,400 flight cycles or 42,150 flight 

hours, whichever occurs first, after accomplishing the rotating probe inspection specified in Airbus Mandatory Service Bulletin 

A310–57–2048.

Within 800 flight cycles or 4,000 flight hours, 

whichever occurs first, after the effective 

date of this AD. 

TABLE 3—REPETITIVE INTERVALS FOR PARAGRAPH (h) OF THIS AD, DEPENDING ON MOST RECENT INSPECTION TYPE

Airplanes, as identified in Airbus Mandatory Service Bulletin A310–57–2050, Revision 02, dated August 27, 

2009 

Type of inspection done 

during most recent 

inspection 

Repetitive interval 

(not to exceed) 

Configuration 01 and 02 airplanes ................................... Detailed inspection ............. 8,600 flight cycles or 17,250 flight hours, whichever occurs first. 

Rotating probe inspection .. 11,400 flight cycles or 22,800 flight hours, whichever 

occurs first. 

Configurations 03, 04, and 05 airplanes .......................... Detailed inspection ............. 10,600 flight cycles or 21,150 flight hours, whichever 

occurs first. 

Rotating probe inspection .. 13,900 flight cycles or 27,800 flight hours, whichever 

occurs first. 

Configurations 06, 07, and 08 short range airplanes ....... Detailed inspection ............. 8,200 flight cycles or 23,000 flight hours, whichever occurs first. 

Rotating probe inspection .. 10,800 flight cycles or 30,300 flight hours, whichever 

occurs first. 

Configurations 06, 07, and 08 long range airplanes ........ Detailed inspection ............. 6,400 flight cycles or 31,950 flight hours, whichever occurs first. 


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TABLE 3—REPETITIVE INTERVALS FOR PARAGRAPH (h) OF THIS AD, DEPENDING ON MOST RECENT INSPECTION TYPE— 

Continued 

Airplanes, as identified in Airbus Mandatory Service Bulletin A310–57–2050, Revision 02, dated August 27, 

2009 

Type of inspection done 

during most recent 

inspection 

Repetitive interval 

(not to exceed) 

Rotating probe inspection .. 8,400 flight cycles or 42,150 flight hours, whichever occurs first. 

Corrective Actions for Paragraph (h) of This 

AD 

(i) If any cracking is found during any 

inspection required by paragraph (h) of this 

AD, before further flight, do all applicable 

corrective actions, in accordance with the 

Accomplishment Instructions of Airbus 

Mandatory Service Bulletin A310–57–2050, 

Revision 02, dated August 27, 2009; except 

where the service bulletin specifies to contact 

Airbus, before further flight, repair in 

accordance with a method approved by 

either the Manager, International Branch, 

ANM–116, FAA, Transport Airplane 

Directorate, or European Aviation Safety 

Agency (EASA) (or its delegated agent). 

Inspection of Fuselage Frame 40 Upper 

Corner Fitting 

(j) For all airplanes: Within the applicable 

time specified in Table 4 of this AD, perform 

an eddy current inspection for cracking of the 

upper corner fitting at left and right frame 40, 

in accordance with the Accomplishment 

Instructions of Airbus Mandatory Service 

Bulletin A310–57–2064, Revision 02, dated 

December 21, 2007. Repeat the inspections 

thereafter at intervals not to exceed the 

applicable times specified in Table 5 of this 

AD. Certain compliance times specified in 

Tables 4 and 5 of this AD are applicable to 

short range use, average flight time (AFT) 

equal to or less than 3.23 hours; or long range 

use, AFT exceeding 3.23 hours. 

TABLE 4—COMPLIANCE TIMES FOR PARAGRAPH (j) OF THIS AD 

Airplane configurations identified in Airbus 

Mandatory Service Bulletin A310–57–2064, 

Revision 02, dated December 21, 2007 

Compliance time 

(whichever occurs later) 

Model A310–203, –204, –221, and –222 airplanes identified as Configuration 01.Prior to the accumulation of 15,100 total flight 

cycles or 30,300 total flight hours, whichever occurs first.

Within 1,300 flight cycles or 2,700 flight hours, 

whichever occurs first, after the effective 

date of this AD. 

Model A310–203, –204, –221, and –222 airplanes identified as Configurations 02 and 03.Prior to the accumulation of 21,400 total flight 

cycles or 42,800 total flight hours, whichever occurs first.

Within 1,300 flight cycles or 2,700 flight hours, 

whichever occurs first, after the effective 

date of this AD. 

Model A310–304, –322, –324, and –325 short 

range airplanes identified as Configuration 01.

Prior to the accumulation of 14,700 total flight 

cycles or 41,300 total flight hours, whichever occurs first.

Within 600 flight cycles or 1,800 flight hours, 

whichever occurs first, after the effective 

date of this AD. 

Model A310–304, –322, –324, and –325 short 

range airplanes identified as Configurations 

02 and 03.

Prior to the accumulation of 20,700 total flight 

cycles or 58,300 total flight hours, whichever occurs first.

Within 600 flight cycles or 1,800 flight hours, 

whichever occurs first, after the effective 

date of this AD. 

Model A310–304, –322, –324, and –325 long 

range airplanes identified as Configuration 01.

Prior to the accumulation of 12,800 total flight 

cycles or 64,000 total flight hours, whichever occurs first.

Within 500 flight cycles or 2,650 flight hours, 

whichever occurs first, after the effective 

date of this AD. 

Model A310–304, –322, –324, and –325 long 

range airplanes identified as Configurations 

02 and 03.

Prior to the accumulation of 18,000 total flight 

cycles or 90,400 total flight hours, whichever occurs first.

Within 500 flight cycles or 2,650 flight hours, 

whichever occurs first, after the effective 

date of this AD. 

TABLE 5—REPETITIVE INTERVALS FOR PARAGRAPH (j) OF THIS AD 

Airplanes Repetitive interval 

(not to exceed) 

Model A310–203, –204, –221, and –222 airplanes ................................. 8,750 flight cycles or 17,550 flight hours, whichever occurs first. 

Model A310–304, –322, –324, and –325 short range airplanes ............. 5,800 flight cycles or 16,300 flight hours, whichever occurs first. 

Model A310–304, –322, –324, and –325 long range airplanes .............. 4,800 flight cycles or 24,050 flight hours, whichever occurs first. 

Corrective Actions for Paragraph (j) of This 

AD 

(k) If, during any inspection required by 

paragraph (j) of this AD, any crack is found, 

prior to further flight, do all applicable 

corrective actions, in accordance with the 

Accomplishment Instructions of Airbus 

Mandatory Service Bulletin A310–57–2064, 

Revision 02, dated December 21, 2007; 

except where the service bulletin specifies to 

contact Airbus, before further flight, repair in 

accordance with a method approved by 

either the Manager, International Branch, 

ANM–116, FAA, Transport Airplane 

Directorate, or EASA (or its delegated agent). 

Credit for Actions Accomplished in 

Accordance With Previous Service 

Information 

(l) Actions accomplished before the 

effective date of this AD in accordance with 

Airbus Service Bulletin A310–57–2048, 

dated April 23, 1990, are considered 

acceptable for compliance with the 

corresponding action specified in paragraph 

(g) of this AD. 

(m) Actions accomplished before the 

effective date of this AD in accordance with 

Airbus Service Bulletin A310–57–2050, 

dated April 23, 1990; or Airbus Mandatory 

Service Bulletin A310–57–2050, Revision 01, 

dated May 22, 2007; are considered 

acceptable for compliance with the 

corresponding actions specified in 

paragraphs (h) and (i) of this AD. 

(n) Actions done before the effective date 

of this AD in accordance with Airbus Service 

Bulletin A310–57–2064, dated August 24, 

1995; or, Airbus Mandatory Service Bulletin 

A310–57–2064, Revision 01, dated January 5, 

2001; are acceptable for compliance with the 

corresponding actions specified in 

paragraphs (j) and (k) of this AD. 


srobinson on DSKHWCL6B1PROD with RULES
27232 Federal Register / Vol. 76, No. 91 / Wednesday, May 11, 2011 / Rules and Regulations 

FAA AD Differences 

Note 1: This AD differs from the MCAI 

and/or service information as follows: No 

Differences. 

Other FAA AD Provisions 

(o) The following provisions also apply to 

this AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, International 

Branch, ANM–116, 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, or if sending information 

directly to the International Branch, send it 

to ATTN: Dan Rodina, Aerospace Engineer, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA, 1601 Lind 

Avenue, SW., Renton, Washington 98057– 

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

227–1149. Information may be e-mailed to: 

9-ANM-116-AMOC-Requests@faa.gov. Before 

using any approved AMOC, notify your 

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 

(p) Refer to MCAI EASA Airworthiness 

Directive 2009–0057, dated March 13, 2009, 

and the service bulletins listed in Table 6 of 

this AD, for related information. 

TABLE 6—SERVICE INFORMATION

Service Bulletin Revision Date 

Airbus Mandatory Service Bulletin A310–57–2048 ........................................................................................... 01 May 22, 2007. 

Airbus Mandatory Service Bulletin A310–57–2050 ........................................................................................... 02 August 27, 2009. 

Airbus Mandatory Service Bulletin A310–57–2064 ........................................................................................... 02 December 21, 2007. 

Material Incorporated by Reference 

(q) You must use the applicable service 

information contained in Table 7 of this AD 

to do the actions required by this AD, unless 

the AD specifies otherwise. 

TABLE 7—ALL MATERIAL INCORPORATED BY REFERENCE

Service Bulletin Revision Date 

Airbus Mandatory Service Bulletin A310–57–2048 ........................................................................................... 01 May 22, 2007. 

Airbus Mandatory Service Bulletin A310–57–2050, excluding Appendix 01 .................................................... 02 August 27, 2009. 

Airbus Mandatory Service Bulletin A310–57–2064, excluding Appendix 1 ...................................................... 02 December 21, 2007. 

(1) The Director of the Federal Register 

approved the incorporation by reference of 

the service information under 5 U.S.C. 552(a) 

and 1 CFR part 51. 

(2) For service information identified in 

this AD, contact Airbus SAS—EAW 

(Airworthiness Office), 1 Rond Point Maurice 

Bellonte, 31707 Blagnac Cedex, France; 

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

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

www.airbus.com. 

(3) You may review copies of the service 

information at the FAA, Transport Airplane 

Directorate, 1601 Lind Avenue, SW., Renton, 

Washington. For information on the 

availability of this material at the FAA, call 

425–227–1221. 

(4) You may also review copies of the 

service information that is incorporated by 

reference at the National Archives and 

Records Administration (NARA). For 

information on the availability of this 

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

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

code_of_federal_regulations/ 

ibr_locations.html. 

Issued in Renton, Washington, on April 22, 

2011. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2011–10685 Filed 5–10–11; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2010–1276; Directorate 

Identifier 2010–NM–092–AD; Amendment 

39–16689; AD 2011–10–08] 

RIN 2120–AA64 

Airworthiness Directives; Airbus Model 

A310 Series Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for the 

products listed above that would 

supersede two existing ADs. 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: 

DGAC [Direction Ge ́ne ́rale de l’Aviation 

Civile] France AD 1992–106–132(B) * * * 

has been issued in order to mandate a set of 

inspections/modifications which address 

JAR/FAR [Joint Aviation Regulation/Federal 

Aviation Regulation] 25–571 requirements 

related to damage-tolerance and fatigue 

evaluation of structure. 

* * * * * 

The unsafe condition is reduced 

structural integrity of the wings, 

fuselage, and stabilizers. We are issuing 

this AD to require actions to correct the 

unsafe condition on these products. 

DATES: This AD becomes effective June 

15, 2011. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of June 15, 2011. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain other publications listed in 

this AD as of January 20, 1999 (63 FR 

69179, December 16, 1998). 

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. 


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