27220 Federal Register / Vol. 76, No. 91 / Wednesday, May 11, 2011 / Rules and Regulations 

14; then north on State Route 14 to 

South Shore Road; then east on South 

Shore Road and continuing to the 

shoreline of Sodus Bay. 

Done in Washington, DC, this 4th day of 

May 2011. 

Kevin Shea, 

Acting Administrator, Animal and Plant 

Health Inspection Service. 

[FR Doc. 2011–11489 Filed 5–10–11; 8:45 am] 

BILLING CODE 3410–34–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2010–1275; Directorate 

Identifier 2010–NM–091–AD; Amendment 

39–16688; AD 2011–10–07] 

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 (MCA I) 

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 Airworthiness Directive (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 34). 

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 Airworthiness Directive (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 [FAA AD 

98–26–01 corresponds to DGAC AD 1992– 

106–132(B)R4, dated June 5, 1996]. 

Following the Extended Design Service 

Goal activities as part of the Structure Task 

Group for the Airbus A310 program, EASA 

issued AD 2007–0053 which replaced DGAC 

France AD F–1992–106–132R7. Since the 

issuance of that AD, the thresholds and the 

intervals of some Airbus Service Bulletins 

(SBs which address structure fatigue related 

areas on the wing parts), until now part of 

the requirements of AD 2007–0053, have 

been updated. 

For the reasons stated above, this new 

[EASA] AD requires the accomplishment of 

the structural fatigue-related corrective 

actions in accordance with the latest revision 

of these SBs which have been reviewed in 

the context of the A310 Extended Service 

Goal activities. Consequently, this new AD 

supersedes the requirements of paragraphs 

1.8, 1.9, 1.10, 1.13, 1.18 of EASA AD 2007– 

0053, which has been revised accordingly. 

The unsafe condition is reduced 

structural integrity of the wings. The 

required corrective actions are as 

follows, depending on airplane 

configuration: 

• For certain Model A310–203 and 

A310–222 airplanes: Repetitive detailed 

inspections for cracking of the leading 

edge access panels around the bolt 

holes, and repair if necessary. 

• For certain Model A310–203, 

A310–204, A310–222, A310–304, A310– 

322, A310–324, and A310–325 

airplanes: Repetitive eddy current 

inspections to detect cracks in the holes 

around the overwing refueling aperture 

at ribs 13–14, and repair if necessary. 

• For certain Model A310–203, 

A310–204, A310–222, A310–304, A310– 

322, A310–324, and A310–325 

airplanes: Repetitive external detailed 

inspections for cracking of the top skin 

at ribs 13–14, repetitive internal 

detailed inspections for cracking of 

stringer 7 and stringer 8 of the overwing 

refuel aperture, and repair if necessary. 

• For certain Model A310–203 and 

A310–222 airplanes: Repetitive detailed 

inspections for cracking around the 

bolts in the wing top skin upper surface 

of the front spar between rib 7 and rib 

28, and repair if necessary. 

• For certain Model A310–203 and 

A310–222 airplanes: Repetitive high 

frequency eddy current (HFEC) or X-ray 

inspections to detect cracking of the 

stringer runouts inboard and outboard 

of rib 14 at stringers 6, 7, 8, and 9, and 

repair if necessary. 

• For certain Model A310–203, 

A310–204, A310–222, A310–304, A310– 

322, and A310–324 airplanes: Repetitive 

ultrasonic inspections for cracking in 

certain bolt holes where the main 

landing gear forward pick-up fitting is 

attached to the rear spar, and repair if 

necessary. 

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. 

Explanation of Changes to This AD 

We have moved the parenthetical 

information from paragraphs (g), (i), (j), 

(o), and (q)(1), (q)(2), and (q)(3) of this 

AD. Instead, we have provided that 

information in Note 1, Note 3, Note 4, 

Note 6, and Note 8 of this AD. 

We have also revised tables 3 and 4 

of this AD to refer to Model ‘‘A310–322’’ 

instead of ‘‘A310A–322.’’ We 

inadvertently referred to ‘‘A310A–322’’ 

in the NPRM. 

Conclusion 

We reviewed the available data and 

determined that air safety and the 

public interest require adopting the AD 

with the changes described previously. 

We determined that these change will 

not 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 


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Federal Register / Vol. 76, No. 91 / Wednesday, May 11, 2011 / Rules and Regulations 27221 

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 97 workhours 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 $362,780, or $8,245 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: 

2011–10–07 Airbus: Amendment 39–16688. 

Docket No. FAA–2010–1275; Directorate 

Identifier 2010–NM–091–AD. 

Effective Date 

(a) This airworthiness directive (AD) 

becomes effective June 15, 2011. 

Affected ADs 

(b) This AD affects AD 90–19–07, 

Amendment 39–6731 (55 FR 37455, 

September 12, 1990); and AD 91–06–18, 

Amendment 39–6940 (56 FR 10796, March 

14, 1991). 

Applicability 

(c) This AD applies to Airbus Model A310– 

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

–325 airplanes, certificated in any category, 

all certified models, 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 Airworthiness Directive (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. 

Restatement of Certain Requirements of AD 

98–26–01, Amendment 39–10942 (63 FR 

69179, December 16, 1998), With Reduced 

Compliance Times 

Leading Edge Access Panels Landing— 

Lower Skin—Inspection for Cracks at Bolt 

Holes 

(g) For Model A310–203 and A310–222 

airplanes listed in Airbus Service Bulletin 

A310–57–2002, Revision 2, dated January 4, 

1996, except airplanes on which Airbus 

modification No. 05101 has been embodied 

in production, or on which Airbus Service 

Bulletin A310–57–2003 has been embodied 

in service before the accumulation of 9,400 

total flight cycles and 18,800 total flight 

hours: At the times specified in paragraph (h) 

of this AD, perform a detailed visual 

inspection to detect cracks in the external 

surface of the wing lower skin around the 

landing access panel holes of the leading 

edge, in accordance with the Airbus Service 

Bulletin A310–57–2002, Revision 1, dated 

July 2, 1992; Airbus Service Bulletin A310– 

57–2002, Revision 2, dated January 4, 1996; 

or Airbus Mandatory Service Bulletin A310– 

57–2002, Revision 03, dated November 28, 

2006. If any discrepancy is found, prior to 

further flight, repair in accordance with a 

method approved by either the Manager, 

International Branch, ANM–116, FAA, 

Transport Airplane Directorate, or the 

Direction Ge ́ne ́rale de l’Aviation Civile 

(DGAC) (or its delegated agent) or EASA (or 

its delegated agent). Except as required by 

paragraph (n) of this AD, repeat the detailed 

inspection specified in this paragraph at the 

earlier of the times specified in paragraphs 

(g)(1) and (g)(2) of this AD; and thereafter at 

intervals not to exceed 2,300 flight cycles or 

4,700 flight hours, whichever occurs first. As 

of the effective date of this AD, use only 

Airbus Mandatory Service Bulletin A310–57– 

2002, Revision 03, dated November 28, 2006. 

Accomplishment of Airbus Modification 

05101 before the effective date of this AD 

terminates the repetitive inspection 

requirements of this paragraph; however, 

airplanes identified in paragraph (n) of this 

AD are applicable to the new inspections 

required by paragraph (n) of this AD. As of 

the effective date of this AD: 

Accomplishment of Airbus Modification 

05101 before the accumulation of 9,400 total 

flight cycles and 18,800 total flight hours 

terminates the repetitive inspection 

requirements of this paragraph. 

Note 1: Airbus Service Bulletin A310–57– 

2003, Revision 03, dated October 16, 2006, is 


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an additional source of guidance for 

accomplishing Airbus Modification 05101. 

Note 2: As of the effective date of this AD, 

if Airbus Service Bulletin A310–57–2003 is 

done on or after the accumulation of 9,400 

total flight cycles or on or after the 

accumulation of 18,800 total flight hours, the 

actions specified in paragraph (g) of this AD 

are still required. 

(1) Within 3,000 flight cycles after doing 

the detailed inspection specified in 

paragraph (g) of this AD. 

(2) At the later of the times specified in 

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

(i) Within 2,300 flight cycles or 4,700 flight 

hours, whichever occurs first, after doing the 

detailed inspection required by paragraph (g) 

of this AD. 

(ii) Within 1,500 flight cycles or 3,000 

flight hours, whichever occurs first, after the 

effective date of this AD. 

(h) For Model A310–203 and A310–222 

airplanes listed in Airbus Service Bulletin 

A310–57–2002, Revision 2, dated January 4, 

1996, except airplanes on which Airbus 

modification No. 05101 has been embodied 

in production, or on which Airbus Service 

Bulletin A310–57–2003 has been embodied 

in service before the accumulation of 9,400 

total flight cycles and 18,800 total flight 

hours: At the earlier of the times specified in 

paragraphs (h)(1) and (h)(2) of this AD, do the 

detailed inspection required by paragraph (g) 

of this AD. 

(1) Prior to the accumulation of 12,000 

total flight cycles, or within 1,000 flight 

cycles after January 20, 1999 (the effective 

date of AD 98–26–01, amendment 39–10942), 

whichever occurs later. 

(2) At the later of the times specified in 

paragraph (h)(2)(i) and (h)(2)(ii) of this AD. 

(i) Prior to the accumulation of 9,400 total 

flight cycles or 18,800 total flight hours, 

whichever occurs first. 

(ii) Within 1,500 flight cycles or 3,000 

flight hours, whichever occurs first, after the 

effective date of this AD. 

Inspect Area around Overwing Refueling 

Aperture at Ribs 13–14 

(i) For Model A310–203, A310–204, A310– 

222, A310–304, A310–322, A310–324, and 

A310–325 airplanes that are listed in Airbus 

Service Bulletin A310–57–2006, Revision 3, 

dated May 2, 1996, and are identified as 

Configuration 1 in Airbus Mandatory Service 

Bulletin A310–57–2006, Revision 04, dated 

May 21, 2007: Prior to the accumulation of 

6,000 total flight cycles, or within 1,000 flight 

cycles after January 20, 1999, whichever 

occurs later, perform an eddy current 

inspection to detect cracks in the holes 

around the overwing refueling aperture at 

ribs 13–14, in accordance with Airbus 

Service Bulletin A310–57–2006, Revision 3, 

dated May 2, 1996; or Airbus Mandatory 

Service Bulletin A310–57–2006, Revision 04, 

dated May 21, 2007. If any discrepancy is 

found, prior to further flight, perform followon corrective actions, as applicable, in 

accordance with Airbus Service Bulletin 

A310–57–2006, Revision 3, dated May 2, 

1996; or Airbus Mandatory Service Bulletin 

A310–57–2006, Revision 04, dated May 21, 

2007; except where the service bulletin 

specifies to contact Airbus for repair, before 

further flight, repair in accordance with a 

method approved by either the Manager, 

International Branch, ANM–116, FAA, 

Transport Airplane Directorate, or the DGAC 

(or its delegated agent) or EASA (or its 

delegated agent). Repeat the inspection 

specified in this paragraph at the earlier of 

the times specified in paragraphs (i)(1) and 

(i)(2) of this AD, and thereafter at intervals 

not to exceed 2,300 flight cycles or 4,600 

flight hours, whichever occurs first. As of the 

effective date of this AD, use only Airbus 

Mandatory Service Bulletin A310–57–2006, 

Revision 04, dated May 21, 2007. 

Accomplishment of Airbus Modification 

05891H5128 terminates the repetitive 

inspections required by this paragraph. 

(1) Within 3,000 flight cycles after doing 

the last inspection required by paragraph (i) 

of this AD. 

(2) At the later of the times specified in 

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

(i) Within 2,300 flight cycles or 4,600 flight 

hours, whichever occurs first, after doing the 

most recent inspection required by paragraph 

(i) of this AD. 

(ii) Within 380 flight cycles or 770 flight 

hours, whichever occurs first, after the 

effective date of this AD. 

Note 3: Airbus Service Bulletin A310–57– 

2020, Revision 07, dated June 5, 2006, is an 

additional source of guidance for 

accomplishing Airbus Modification 

05891H5128. 

Upper Skin Forward of Front Spar— 

Inspection for Cracks 

(j) For Model A310–203 and A310–222 

airplanes listed in Airbus Service Bulletin 

A310–57–2032, Revision 3, dated January 4, 

1996, except airplanes on which Airbus 

modification 05026 has been embodied in 

production, or on which Airbus Service 

Bulletin A310–57–2005 has been done in 

service before the accumulation of 10,500 

total flight cycles and 21,000 total flight 

hours: At the times specified in paragraph (k) 

of this AD, perform a detailed visual 

inspection to detect cracks around the bolts 

in the wing top skin upper surface of the 

front spar between rib 7 and rib 28, in 

accordance with the Accomplishment 

Instructions of Airbus Service Bulletin A310– 

57–2032, Revision 3, dated January 4, 1996; 

or Airbus Mandatory Service Bulletin A310– 

57–2032, Revision 04, dated December 1, 

2006. If any discrepancy is found, prior to 

further flight, repair in accordance with a 

method approved by either the Manager, 

International Branch, ANM–116, FAA, 

Transport Airplane Directorate, or DGAC (or 

its delegated agent) or EASA (or its delegated 

agent). Except as required by paragraph (p) of 

this AD, repeat the detailed inspection 

specified in this paragraph at the earlier of 

the times specified in paragraphs (j)(1) and 

(j)(2) of this AD, and thereafter at intervals 

not to exceed 3,900 flight cycles or 7,900 

flight hours, whichever occurs first. As of the 

effective date of this AD, use only Airbus 

Mandatory Service Bulletin A310–57–2032, 

Revision 04, dated December 1, 2006. 

Accomplishment of Airbus Modification 

05026H0878 before the effective date of this 

AD terminates the repetitive inspection 

requirements of this paragraph; however, 

airplanes identified in paragraph (p) of this 

AD are applicable to the new inspections 

required by paragraph (p) of this AD. As of 

the effective date of this AD: 

Accomplishment of Airbus Modification 

05026H0878 before the accumulation of 

10,500 total flight cycles and 21,000 total 

flight hours terminates the repetitive 

inspection requirements of this paragraph. 

(1) Within 4,500 flight cycles after doing 

the last inspection required by paragraph (j) 

of this AD. 

(2) At the later of the times specified in 

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

(i) Within 3,900 flight cycles or 7,900 flight 

hours, whichever occurs first, after doing the 

most recent inspection required by paragraph 

(j) of this AD. 

(ii) Within 850 flight cycles or 1,700 flight 

hours, whichever occurs first, after the 

effective date of this AD. 

Note 4: Airbus Service Bulletin A310–57– 

2005, Revision 03, dated October 2, 2006, is 

an additional source of guidance for 

accomplishing Airbus Modification 

05026H0878. 

Note 5: As of the effective date of this AD, 

if Airbus Service Bulletin A310–57–2005 is 

done on or after the accumulation of 10,500 

total flight cycles or on or after the 

accumulation of 21,000 total flight hours, the 

actions specified in paragraph (j) of this AD 

are still required. 

(k) For Model A310–203 and A310–222 

airplanes listed in Airbus Service Bulletin 

A310–57–2032, Revision 3, dated January 4, 

1996, except airplanes on which Airbus 

modification 05026 has been embodied in 

production, or on which Airbus Service 

Bulletin A310–57–2005 has been done in 

service before the accumulation of 10,500 

total flight cycles and 21,000 total flight 

hours: At the earlier of the times specified in 

paragraphs (k)(1) and (k)(2) of this AD, do the 

detailed inspection required by paragraph (j) 

of this AD. 

(1) Prior to the accumulation of 12,000 

total flight cycles, or within 1,000 flight 

cycles after January 20, 1999, whichever 

occurs later. 

(2) At the later of the times specified in 

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

(i) Prior to the accumulation of 10,500 total 

flight cycles or 21,000 total flight hours, 

whichever occurs first. 

(ii) Within 850 flight cycles or 1,700 flight 

hours, whichever occurs first, after the 

effective date of this AD. 

Stringer Flanges at Rib 14 Wing Bottom 

Skin—Inspect for Cracks 

(l) For Model A310–203 and A310–222 

airplanes listed in Airbus Service Bulletin 

A310–57–2038, Revision 2, dated January 4, 

1996, except airplanes on which Airbus 

modification 04987 has been done in 

production: At the compliance time specified 

in paragraph (m) of this AD, perform a high 

frequency eddy current (HFEC) or X-ray 

inspection to detect cracking of the stringer 

runouts inboard and outboard of rib 14 at 

stringers 6, 7, 8, and 9, in accordance with 

the Accomplishment Instructions of Airbus 

Service Bulletin A310–57–2038, Revision 2, 

dated January 4, 1996; or Airbus Mandatory 


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Service Bulletin A310–57–2038, Revision 04, 

dated October 19, 2006. Do the next 

inspection at the earlier of the times specified 

in paragraph (l)(1) and (l)(2) of this AD, and 

repeat the inspection thereafter at intervals 

not to exceed the applicable times specified 

in table 1 of this AD. If any crack is detected, 

prior to further flight, repair in accordance 

with a method approved by either the 

Manager, International Branch, ANM–116, 

FAA, Transport Airplane Directorate, or 

DGAC (or its delegated agent) or EASA (or its 

delegated agent). As of the effective date of 

this AD, use only Airbus Mandatory Service 

Bulletin A310–57–2038, Revision 04, dated 

October 19, 2006. 

(1) Within the applicable interval specified 

in paragraph 1.B.(5) of Airbus Service 

Bulletin A310–57–2038, Revision 2, dated 

January 4, 1996. 

(2) At the later of the times specified in 

paragraph (l)(2)(i) and (l)(2)(ii) of this AD. 

(i) Within the applicable interval specified 

in table 1 of this AD after doing the most 

recent inspection specified in paragraph (l) of 

this AD. 

(ii) Within 1,100 flight cycles or 2,300 

flight hours, whichever occurs first, after the 

effective date of this AD. 

TABLE 1—REPETITIVE INTERVALS, 

DEPENDING ON INSPECTION TYPE

Type of 

inspection 

Repetitive interval 

(not to exceed) 

X-Ray ............. 7,200 flight cycles or 14,500 

flight hours, whichever occurs first. 

HFEC ............. 9,400 flight cycles or 18,800 

flight hours, whichever occurs first. 

(m) For Model A310–203 and A310–222 

airplanes listed in Airbus Service Bulletin 

A310–57–2038, Revision 2, dated January 4, 

1996, except airplanes on which Airbus 

modification 04987 has been done in 

production: At the earlier of the times 

specified in paragraphs (m)(1) and (m)(2) of 

this AD, perform an inspection required by 

paragraph (l) of this AD. 

(1) Prior to the accumulation of 12,000 

total flight cycles, or within 1,500 flight 

cycles after January 20, 1999, whichever 

occurs later. 

(2) At the later of the times specified in 

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

(i) Prior to the accumulation of 12,000 total 

flight cycles or 24,000 total flight hours, 

whichever occurs first. 

(ii) Within 1,100 flight cycles or 2,300 

flight hours after the effective date of this AD, 

whichever occurs first. 

New Requirements of This AD 

Leading Edge Access Panels Landing— 

Lower Skin—Inspection for Cracks at Bolt 

Holes—Additional Inspections for Certain 

Airplanes 

(n) For Model A310–203 and A310–222 

airplanes, on which Airbus Service Bulletin 

A310–57–2003 has been done in service on 

or after the accumulation of 9,400 total flight 

cycles or on or after the accumulation of 

18,800 total flight hours: Do the inspection 

required by paragraph (g) of this AD at the 

later of the times specified in paragraphs 

(n)(1) and (n)(2) of this AD. Repeat the 

inspection required by paragraph (g) of this 

AD thereafter at intervals not to exceed 2,300 

flight cycles or 4,700 flight hours, whichever 

occurs first. 

(1) Within 2,300 flight cycles or 4,700 

flight hours, whichever occurs first, after 

doing the most recent detailed inspection 

required by paragraph (g) of this AD. 

(2) Within 1,500 flight cycles or 3,000 

flight hours, after the effective date of this 

AD, whichever occurs first. 

Inspect Area Around Overwing Refueling 

Aperture at Ribs 13–14 for Additional 

Airplanes 

(o) For Model A310–203, A310–204, A310– 

222, A310–304, A310–322, A310–324, and 

A310–325 airplanes, except for airplanes 

identified in paragraph (i) of this AD on 

which Airbus Modification 05891H5128 has 

not been done: At the applicable compliance 

time specified in table 2 of this AD, do the 

applicable actions specified in paragraph 

(o)(1) or (o)(2) of this AD, in accordance with 

the Accomplishment Instructions of Airbus 

Mandatory Service Bulletin A310–57–2006, 

Revision 04, dated May 21, 2007. If any 

cracking is found, before further flight, repair 

in accordance with the Accomplishment 

Instructions of Airbus Mandatory Service 

Bulletin A310–57–2006, Revision 04, dated 

May 21, 2007; except where this service 

bulletin specifies to contact Airbus for repair, 

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). Repeat the 

inspections thereafter at the applicable 

interval specified in table 2 of this AD. 

Certain compliance times specified in table 2 

of this AD are applicable to short range use, 

average flight time (AFT) equal to or less than 

4.0 hours, or long range use, AFT exceeding 

4.0 hours. For airplanes identified as 

Configuration 01 in Airbus Mandatory 

Service Bulletin A310–57–2006, Revision 04, 

dated May 21, 2007, accomplishment of 

Airbus Modification 05891H5128 terminates 

the repetitive inspections required by this 

paragraph for Configuration 01 airplanes; 

thereafter do the applicable actions specified 

in paragraph (o)(2) of this AD at the times 

specified in table 2 of this AD. 

Note 6: Airbus Service Bulletin A310–57– 

2020, Revision 07, dated June 5, 2006, is an 

additional source of guidance for 

accomplishing Airbus Modification 

05891H5128. 

(1) For Configuration 01 airplanes, as 

identified in Airbus Mandatory Service 

Bulletin A310–57–2006, Revision 04, dated 

May 21, 2007: Do a rotating probe eddy 

current inspection for cracking in the holes 

around the overwing refueling aperture at 

ribs 13–14. 

(2) For Configuration 02 through 06 

airplanes, as identified in Airbus Mandatory 

Service Bulletin A310–57–2006, Revision 04, 

dated May 21, 2007: Do an external detailed 

inspection for cracking of the top skin at ribs 

13–14, and an internal detailed inspection for 

cracking of string 7 and string 8 of the 

overwing refuel aperture. 

TABLE 2—COMPLIANCE TIMES FOR CONFIGURATION 01 THROUGH 06 AIRPLANES

Airplanes as Identified in Airbus 

Mandatory Service Bulletin 

A310–57–2006, revision 04, 

dated May 21, 2007 

Compliance time (whichever occurs later) Repetitive interval (not to exceed) 

Configuration 01 airplanes ............. Prior to the accumulation of 6,000 

total flight cycles.

Within 380 flight cycles or 770 

flight hours, whichever occurs 

first, after the effective date of 

this AD.

2,300 flight cycles or 4,600 flight 

hours, whichever occurs first. 

Configuration 02 airplanes ............. Within 30,900 flight cycles or 

61,900 flight hours, whichever 

occurs first, after accomplishing 

Airbus Service Bulletin A310– 

57–2020.

Within 1,500 flight cycles or 18 

months, whichever occurs first, 

after the effective date of this 

AD.

11,300 flight cycles or 22,600 

flight hours, whichever occurs 

first. 

Configuration 03 airplanes ............. Within 30,900 flight cycles or 

61,900 flight hours, whichever 

occurs first, after Airbus Modification 05891H5128 is done or 

Airbus Service Bulletin A310– 

57–2020 is accomplished.

Within 1,500 flight cycles or 18 

months, whichever occurs first, 

after the effective date of this 

AD.

12,000 flight cycles or 24,000 

flight hours, whichever occurs 

first. 


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TABLE 2—COMPLIANCE TIMES FOR CONFIGURATION 01 THROUGH 06 AIRPLANES—Continued 

Configuration 04 and 05 short 

range airplanes.

Before the accumulation of 

25,900 total flight cycles or 

72,500 total flight hours, whichever occurs first.

Within 1,500 flight cycles or 18 

months, whichever occurs first, 

after the effective date of this 

AD.

12,000 flight cycles or 33,600 

flight hours, whichever occurs 

first. 

Configuration 04 and 05 long 

range airplanes.

Before the accumulation of 

18,800 total flight cycles or 

94,200 total flight hours, whichever occurs first.

Within 1,500 flight cycles or 18 

months, whichever occurs first, 

after the effective date of this 

AD.

9,400 flight cycles or 47,200 flight 

hours, whichever occurs first. 

Configuration 06 ............................ Before the accumulation of 

30,900 total flight cycles or 

61,900 total flight hours, whichever occurs first.

Within 1,500 flight cycles or 18 

months, whichever occurs first, 

after the effective date of this 

AD.

12,000 flight cycles or 24,000 

flight hours, whichever occurs 

first. 

Upper Skin Forward of Front Spar— 

Inspection for Cracks—Additional 

Inspections for Certain Airplanes 

(p) For Model A310–203 and A310–222 

airplanes on which Airbus Service Bulletin 

A310–57–2005 has been done in service on 

or after the accumulation of 10,500 total 

flight cycles or on or after 21,000 total flight 

hours: Do the inspection required by 

paragraph (j) of this AD at the later of the 

times specified in paragraphs (p)(1) and 

(p)(2) of this AD. Repeat the inspection 

specified in paragraph (j) of this AD 

thereafter at intervals not to exceed 3,900 

flight cycles or 7,900 flight hours, whichever 

occurs first. 

(1) Within 3,900 flight cycles or 7,900 

flight hours, whichever occurs first, after 

doing the most recent inspection required by 

paragraph (j) of this AD. 

(2) Within 850 flight cycles or 1,700 flight 

hours, whichever occurs first, after the 

effective date of this AD. 

Inspection of Rear Spar at Selected Bolt 

Locations for Attachment of Main landing 

Gear Forward Pick-Up Fitting 

(q) For Model A310–203, A310–204, A310– 

222, A310–304, A310–322, and A310–324 

airplanes, except airplanes on which Airbus 

modification 07601 has been done in 

production: Do the applicable actions 

specified in paragraphs (q)(1), (q)(2), and 

(q)(3) of this AD. If any cracking is found 

during any inspection, 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). 

Note 7: For Model A310–304, A310–322, 

and A310–324 airplanes on which Airbus 

modification 07601 has been done, guidance 

for post-modification inspections can be 

found in Structure Significant Item (SSI) 

57.21.16 of the Maintenance Review Board 

Document (MRBD). 

(1) For airplanes on which Airbus 

Modification 07925H1113 and Modification 

11578H5436 have not been done: At the 

applicable time specified in table 3 of this 

AD, perform an ultrasonic inspection for 

cracking in certain bolt holes where the main 

landing gear forward pick-up fitting is 

attached to the rear spar, in accordance with 

the Accomplishment Instructions of Airbus 

Mandatory Service Bulletin A310–57–2046, 

Revision 08, dated December 1, 2006. Repeat 

the inspection thereafter at the applicable 

interval specified in table 3 of this AD until 

Airbus Modification 07925H1113 or 

11578H5436 has been done. After doing 

Airbus Modification 07925H1113 or 

11578H5436 do the applicable actions 

specified in paragraph (q)(2) or (q)(3) of this 

AD at the times specified in paragraph (q)(2) 

or (q)(3) of this AD, as applicable. Certain 

compliance times specified in table 3 of this 

AD are applicable to short range use, average 

flight time (AFT) equal to or less than 4.0 

hours, or long range use, AFT exceeding 4.0 

hours. 

Note 8: Airbus Service Bulletin A310–57– 

2049, Revision 6, dated November 26, 1997, 

is an additional source of guidance for 

accomplishing Airbus Modification 

07925H1113. Airbus Service Bulletin A310– 

57–2074, Revision 03, dated July 3, 2006, is 

an additional source of guidance for 

accomplishing Airbus Modification 

11578H5436. 

TABLE 3—COMPLIANCE TIMES FOR AIRPLANES PRE-MOD 07925 AND PRE-MOD 11578 

Airplanes Compliance time (whichever occurs later) Repetitive interval (not to exceed) 

Model A310–203, A310–204, and 

A310–222 airplanes.

Prior to the accumulation of 9,800 

total flight cycles or 19,600 total 

flight hours, whichever occurs 

first.

Within 750 flight cycles or 1,500 

flight hours, whichever occurs 

first, after the effective date of 

this AD.

2,800 flight cycles or 5,700 flight 

hours, whichever occurs first. 

Model A310–304, A310–322, and 

A310–324 short range airplanes.

Prior to the accumulation of 7,100 

total flight cycles or 20,100 total 

flight hours, whichever occurs 

first.

Within 750 flight cycles or 1,500 

flight hours, whichever occurs 

first, after the effective date of 

this AD.

2,400 flight cycles or 6,900 flight 

hours, whichever occurs first. 

Model A310–304, A310–322, and 

A310–324 long range airplanes.

Prior to the accumulation of 5,700 

total flight cycles or 28,600 total 

flight hours, whichever occurs 

first.

Within 750 flight cycles or 1,500 

flight hours, whichever occurs 

first, after the effective date of 

this AD.

1,900 flight cycles or 9,800 flight 

hours, whichever occurs first. 

(2) For airplanes on which Airbus 

Modification 07925H1113 has been done: At 

the applicable time specified in table 4 of this 

AD, perform an ultrasonic inspection for 

cracking in certain bolt holes where the main 

landing gear forward pick-up fitting is 

attached to the rear spar, in accordance with 

the Accomplishment Instructions of Airbus 

Mandatory Service Bulletin A310–57–2046, 

Revision 08, dated December 1, 2006. Repeat 

the inspection thereafter at the applicable 

interval specified in table 4 of this AD. 

Certain compliance times specified in table 4 

of this AD are applicable to short range use, 

AFT equal to or less than 4.0 hours, or long 

range use, AFT exceeding 4.0 hours. 


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TABLE 4—COMPLIANCE TIMES FOR AIRPLANES POST-MOD 07925 

Airplanes Compliance time (whichever occurs later) Repetitive interval (not to exceed) 

Model A310–203, A310–204, and 

A310–222 airplanes.

Prior to the accumulation of 

14,700 total flight cycles or 

29,400 total flight hours, whichever occurs first.

Within 750 flight cycles or 1,500 

flight hours, whichever occurs 

first, after the effective date of 

this AD.

9,400 flight cycles or 18,900 flight 

hours, whichever occurs first. 

Model A310–304, A310–322, and 

A310–324 short range airplanes.

Prior to the accumulation of 

11,900 total flight cycles or 

33,500 total flight hours, whichever occurs first.

Within 750 flight cycles or 1,500 

flight hours, whichever occurs 

first, after the effective date of 

this AD.

5,000 flight cycles or 14,000 flight 

hours, whichever occurs first. 

Model A310–304, A310–322, and 

A310–324 long range airplanes.

Prior to the accumulation of 9,500 

total flight cycles or 47,700 total 

flight hours, whichever occurs 

first.

Within 750 flight cycles or 1,500 

flight hours, whichever occurs 

first, after the effective date of 

this AD.

4,000 flight cycles or 20,000 flight 

hours, whichever occurs first. 

(3) For airplanes on which Airbus 

Modification 11578H5436 has been done: At 

the applicable time specified in table 5 of this 

AD, perform an ultrasonic inspection for 

cracking in certain bolt holes where the main 

landing gear forward pick-up fitting is 

attached to the rear spar, in accordance with 

the Accomplishment Instructions of Airbus 

Mandatory Service Bulletin A310–57–2046, 

Revision 08, dated December 1, 2006. Repeat 

the inspection thereafter at the applicable 

interval specified in table 5 of this AD. 

Certain compliance times specified in table 5 

of this AD are applicable to short range use, 

average flight time (AFT) equal to or less than 

4.0 hours, or long range use, AFT exceeding 

4.0 hours. 

TABLE 5—COMPLIANCE TIMES FOR AIRPLANES POST-MOD 11578 

Airplanes Compliance time (whichever occurs later) Repetitive interval (not to exceed) 

Model A310–203, A310–204, and 

A310–222 airplanes.

Within 29,600 flight cycles or 

59,200 flight hours, whichever 

occurs first, after Airbus Modification 11578H5436 has been 

done.

Within 750 flight cycles or 1,500 

flight hours, whichever occurs 

first, after the effective date of 

this AD.

9,400 flight cycles or 18,900 flight 

hours, whichever occurs first. 

Model A310–304, A310–322, and 

A310–324 short range airplanes.

Within 24,200 flight cycles or 

67,900 flight hours, whichever 

occurs first, after Airbus Modification 11578H5436 has been 

done.

Within 750 flight cycles or 1,500 

flight hours, whichever occurs 

first, after the effective date of 

this AD.

5,000 flight cycles or 14,000 flight 

hours, whichever occurs first. 

Model A310–304, A310–322, and 

A310–324 long range airplanes.

Within 19,300 flight cycles or 

96,800 flight hours, whichever 

occurs first, after Airbus Modification 11578H5436 has been 

done.

Within 750 flight cycles or 1,500 

flight hours, whichever occurs 

first, after the effective date of 

this AD.

4,000 flight cycles or 20,000 flight 

hours, whichever occurs first. 

Credit for Actions Accomplished in 

Accordance With Previous Service 

Information 

(r) Actions done before the effective date of 

this AD in accordance with Airbus Service 

Bulletin A310–57–2038, Revision 03, dated 

September 4, 1998, are acceptable for 

compliance with the corresponding actions 

specified in paragraph (l) of this AD. 

(s) Actions done before the effective date 

of this AD in accordance with Airbus Service 

Bulletin A310–57–2046, Revision 07, dated 

April 2, 1999, are acceptable for compliance 

with the corresponding actions specified in 

paragraph (q) of this AD. 

Terminating Action for Paragraph (a) of AD 

90–19–07 

(t) Accomplishing an inspection in 

accordance with Airbus Service Bulletin 

A310–57–2038, Revision 2, dated January 4, 

1996, or Revision 03, dated September 4, 

1998; or Airbus Mandatory Service Bulletin 

A310–57–2038, Revision 04, dated October 

19, 2006; terminates the requirements of 

paragraph (a) of AD 90–19–07. 

Note 9: Airbus Service Bulletin A310–57– 

2038, Revision 2, dated January 4, 1996; and 

Airbus Mandatory Service Bulletin A310–57– 

2038, Revision 04, dated October 19, 2006; 

are referred to in paragraph (l) of this AD. 

Airbus Service Bulletin A310–57–2038, 

Revision 03, dated September 4, 1998, is 

referred to in paragraph (r) of this AD. 

Terminating Action for AD 91–06–18 

(u) Accomplishing an inspection in 

accordance with Airbus Service Bulletin 

A310–57–2046, Revision 4, dated October 16, 

1996, as revised by Airbus Service Bulletin 

Change Notice 4A, dated October 16, 1996; 

Airbus Service Bulletin A310–57–2046, 

Revision 07, dated April 2, 1999; or Airbus 

Mandatory Service Bulletin A310–57–2046, 

Revision 08, dated December 1, 2006; 

terminates the requirements of AD 91–06–18. 

Note 10: Airbus Mandatory Service 

Bulletin A310–57–2046, Revision 08, dated 

December 1, 2006, is referred to in paragraph 

(q) of this AD. Airbus Service Bulletin A310– 

57–2046, Revision 07, dated April 2, 1999, is 

referred to in paragraph (s) of this AD. Airbus 

Service Bulletin A310–57–2046, Revision 4, 

dated October 16, 1996, as revised by Airbus 

Service Bulletin Change Notice 4A, dated 

October 16, 1996, is referred to in paragraph 

(n) of AD 98–26–01. 

FAA AD Differences 

Note 11: This AD differs from the MCAI 

and/or service information as follows: 

Although the MCAI or service information 

allows further flight after cracks are found 

during compliance with the required action, 

paragraph (j) of this AD requires that you 

repair the crack(s) before further flight. 

Other FAA AD Provisions 

(v) 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, Transport 


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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. 

AMOCs approved previously in accordance 

with AD 98–26–01, 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. 

Related Information 

(w) Refer to MCAI EASA Airworthiness 

Directive 2007–0242, dated September 4, 

2007, and the Airbus service bulletins listed 

in table 6 of this AD for related information. 

TABLE 6—RELATED SERVICE INFORMATION

Service Bulletin Revision Date 

Airbus Mandatory Service Bulletin A310–57–2002 ..................................................................................... 03 ................. November 28, 2006. 

Airbus Mandatory Service Bulletin A310–57–2006 ..................................................................................... 04 ................. May 21, 2007. 

Airbus Mandatory Service Bulletin A310–57–2032 ..................................................................................... 04 ................. December 1, 2006. 

Airbus Mandatory Service Bulletin A310–57–2038 ..................................................................................... 04 ................. October 19, 2006. 

Airbus Mandatory Service Bulletin A310–57–2046 ..................................................................................... 08 ................. December 1, 2006. 

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

Airbus Service Bulletin A310–57–2038 ....................................................................................................... 03 ................. September 4, 1998 

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

Airbus Service Bulletin A310–57–2046 ....................................................................................................... 07 ................. April 2, 1999. 

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

Material Incorporated by Reference 

(x) You must use the service bulletins 

contained in table 7 of this AD to do the 

actions required by this AD, unless the AD 

specifies otherwise. If you accomplish the 

optional terminating actions specified by this 

AD, you must use the service information 

contained in table 7 of this AD to perform 

those actions unless the AD specifies 

otherwise. 

TABLE 7—ALL MATERIAL INCORPORATED BY REFERENCE

Service Bulletin Revision Date Required/optional action 

Airbus Mandatory Service Bulletin A310–57–2002 ......... 03 ................. November 28, 2006 .............................. Required. 

Airbus Mandatory Service Bulletin A310–57–2006 ......... 04 ................. May 21, 2007 ........................................ Required. 

Airbus Mandatory Service Bulletin A310–57–2032 ......... 04 ................. December 1, 2006 ................................ Required. 

Airbus Mandatory Service Bulletin A310–57–2038 ......... 04 ................. October 19, 2006 .................................. Required and optional. 

Airbus Mandatory Service Bulletin A310–57–2046 ......... 08 ................. December 1, 2006 ................................ Required and optional. 

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

Airbus Service Bulletin A310–57–2038 ............................ 03 ................. September 4, 1998 ............................... Optional. 

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

Airbus Service Bulletin A310–57–2046 ............................ 07 ................. April 2, 1999 ......................................... Optional. 

Airbus Service Bulletin A310–57–2046, Change Notice 

4A.

Original ......... October 16, 1996 .................................. Optional. 

(1) The Director of the Federal Register 

approved the incorporation by reference of 

the service information contained in table 8 

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

part 51. 

TABLE 8—NEW MATERIAL INCORPORATED BY REFERENCE

Service Bulletin Revision Date 

Airbus Mandatory Service Bulletin A310–57–2002 ................................................................................... 03 November 28, 2006. 

Airbus Mandatory Service Bulletin A310–57–2006 ................................................................................... 04 May 21, 2007. 

Airbus Mandatory Service Bulletin A310–57–2032 ................................................................................... 04 December 1, 2006. 

Airbus Mandatory Service Bulletin A310–57–2038 ................................................................................... 04 October 19, 2006. 

Airbus Mandatory Service Bulletin A310–57–2046 ................................................................................... 08 December 1, 2006. 

Airbus Service Bulletin A310–57–2038 ..................................................................................................... 03 September 4, 1998. 

Airbus Service Bulletin A310–57–2046 ..................................................................................................... 07 April 2, 1999. 

(2) The Director of the Federal Register 

previously approved the incorporation by 

reference of the service information 

contained in table 9 of this AD on January 

20, 1999 (63 FR 69179, December 16, 1998). 


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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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