34 Federal Register / Vol. 76, No. 1 / Monday, January 3, 2011 / Proposed Rules 

Installation 

(g) Within 60 months after the effective 

date of this AD, install double shielded fuel 

quantity indicating system (FQIS) wire 

bundles, install a new wire feed-through 

fitting, and ground the wire shields, as 

applicable, in accordance with Part 1 of the 

Accomplishment Instructions of Boeing 

Service Bulletin 727–28–0131, dated August 

18, 2010. 

Repetitive Inspections 

(h) At the applicable times specified in 

paragraphs (h)(1) or (h)(2) of this AD, do low 

frequency eddy current (LFEC) inspections 

for cracking of the fuselage skin, in 

accordance with Part 2 of the 

Accomplishment Instructions of Boeing 

Service Bulletin 727–28–0131, dated August 

18, 2010. 

(1) For Model 727, 727–100, 727–100C, 

and 727C series airplanes: Before the 

accumulation of 45,000 total flight cycles, or 

within 8,000 flight cycles after the effective 

date of this AD, whichever occurs later. 

Repeat the inspections thereafter at intervals 

not to exceed 8,000 flight cycles. 

(2) For Model 727–200 and 727–200F 

series airplanes: Before the accumulation of 

45,000 total flight cycles, or within 16,000 

flight cycles after the effective date of this 

AD, whichever occurs later. Repeat the 

inspections thereafter at intervals not to 

exceed 16,000 flight cycles. 

(i) If any cracking is found during any 

inspection required by paragraph (h) of this 

AD: Before further flight, repair the crack in 

accordance with a method approved by the 

Manager, Seattle Aircraft Certification Office 

(ACO), FAA. For a repair method to be 

approved, the repair must meet the 

certification basis of the airplane, and the 

approval must specifically refer to this AD. 

Maintenance Program Revision 

(j) Before or concurrently with doing the 

actions required by paragraph (g) of this AD, 

or within 30 days after the effective date of 

this AD, whichever occurs later: Revise the 

maintenance program by incorporating 

airworthiness limitations (AWL) No. 28– 

AWL–18 and 28–AWL–19 in Section D of 

Section 9 (‘‘AIRWORTHINESS 

LIMITATIONS—FUEL SYSTEMS’’) of the 

Boeing 727–100/200 Airworthiness 

Limitations (AWLs) Document, 

D6–8766–AWL, Revision August 2010. The 

initial compliance time for AWL No. 28– 

AWL–18 is within 10 years after the 

accomplishment of paragraph (g) of this AD, 

or within 10 years after the effective date of 

this AD, whichever occurs later. 

No Alternative Inspections, Inspection 

Intervals, or Critical Design Configuration 

Control Limitations (CDCCLs) 

(k) After accomplishing the action 

specified in paragraph (j) of this AD, no 

alternative inspections, inspection intervals, 

or CDCCLs may be used unless the 

inspections, intervals, or CDCCLs are 

approved as an Alternative Method of 

Compliance (AMOC) in accordance with the 

procedures specified in paragraph (l) of this 

AD. 

Alternative Methods of Compliance 

(AMOCs) 

(l)(1) The Manager, Seattle Aircraft 

Certification Office (ACO), 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 manager of the ACO, send it to the 

attention of the person identified in the 

Related Information section of this AD. 

Information may be e-mailed to: 9-ANMSeattle-ACO-AMOC-Requests@faa.gov. 

(2) Before using any approved AMOC, 

notify your Principal Maintenance Inspector 

or Principal Avionics Inspector, as 

appropriate, or lacking a principal inspector, 

your local Flight Standards District Office. 

Related Information 

(m) For more information about this AD, 

contact Louis Natsiopoulos, Aerospace 

Engineer, Systems and Equipment Branch, 

ANM–130S, FAA, Seattle Aircraft 

Certification Office, 1601 Lind Avenue, SW., 

Renton, Washington 98057–3356; telephone 

(425) 917–6478; fax (425) 917–6590; e-mail: 

elias.natsiopoulos@faa.gov. 

(n) For service information identified in 

this AD, contact Boeing Commercial 

Airplanes, Attention: Data & Services 

Management, P. O. Box 3707, MC 2H–65, 

Seattle, Washington 98124–2207; telephone 

206–544–5000, extension 1; fax 206–766– 

5680; e-mail me.boecom@boeing.com; 

Internet https://www.myboeingfleet.com. You 

may review copies of the referenced service 

information at the FAA, Transport Airplane 

Directorate, 1601 Lind Avenue, SW., Renton, 

Washington. For information on the 

availability of this material at the FAA, call 

425–227–1221. 

Issued in Renton, Washington, on 

December 17, 2010. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2010–33002 Filed 12–30–10; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2010–1275; Directorate 

Identifier 2010–NM–091–AD] 

RIN 2120–AA64 

Airworthiness Directives; Airbus Model 

A310 Series Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to adopt a new 

airworthiness directive (AD) for the 

products listed above. This proposed 

AD results from mandatory continuing 

airworthiness information (MCAI) 

originated by an aviation authority of 

another country to identify and correct 

an unsafe condition on an aviation 

product. The MCAI describes the unsafe 

condition as: 

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. The 

proposed AD would require actions that 

are intended to address the unsafe 

condition described in the MCAI. 

DATES: We must receive comments on 

this proposed AD by February 17, 2011. 

ADDRESSES: You may send comments by 

any of the following methods: 

• Federal eRulemaking Portal: Go to 

http://www.regulations.gov. Follow the 

instructions for submitting comments. 

• Fax: (202) 493–2251. 

• Mail: U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–140, 1200 New Jersey Avenue, SE., 

Washington, DC 20590. 

• Hand Delivery: U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–40, 1200 New Jersey Avenue, SE., 

Washington, DC, between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. 

For service information identified in 

this proposed AD, contact Airbus SAS— 

EAW (Airworthiness Office), 1 Rond 

Point Maurice Bellonte, 31707 Blagnac 

Cedex, France; telephone +33 5 61 93 36 

96; fax +33 5 61 93 44 51; e-mail 

account.airworth-eas@airbus.com; 

Internet http://www.airbus.com. You 

may review copies of the referenced 

service information at the FAA, 

Transport Airplane Directorate, 1601 

Lind Avenue, SW., Renton, Washington. 

For information on the availability of 

this material at the FAA, call 425–227– 

1221. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http:// 

www.regulations.gov; or in person at the 

Docket Operations office between 9 a.m. 

and 5 p.m., Monday through Friday, 

except Federal holidays. The AD docket 

contains this proposed AD, the 

regulatory evaluation, any comments 

received, and other information. The 


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Federal Register / Vol. 76, No. 1 / Monday, January 3, 2011 / Proposed Rules 35 

street address for the Docket Operations 

office (telephone (800) 647–5527) is in 

the ADDRESSES section. Comments will 

be available in the AD docket shortly 

after receipt. 

FOR FURTHER INFORMATION CONTACT: Dan 

Rodina, Aerospace Engineer, 

International Branch, ANM–116, 

Transport Airplane Directorate, FAA, 

1601 Lind Avenue, SW., Renton, 

Washington 98057–3356; telephone 

(425) 227–2125; fax (425) 227–1149. 

SUPPLEMENTARY INFORMATION: 

Comments Invited 

We invite you to send any written 

relevant data, views, or arguments about 

this proposed AD. Send your comments 

to an address listed under the 

ADDRESSES section. Include ‘‘Docket No. 

FAA–2010–1275; Directorate Identifier 

2010–NM–091–AD’’ at the beginning of 

your comments. We specifically invite 

comments on the overall regulatory, 

economic, environmental, and energy 

aspects of this proposed AD. We will 

consider all comments received by the 

closing date and may amend this 

proposed AD based on those comments. 

We will post all comments we 

receive, without change, to http:// 

www.regulations.gov, including any 

personal information you provide. We 

will also post a report summarizing each 

substantive verbal contact we receive 

about this proposed AD. 

Discussion 

On December 8, 1998, we issued AD 

98–26–01, Amendment 39–10942 (63 

FR 69179, December 16, 1998). That AD 

required actions intended to address an 

unsafe condition on the products listed 

above. 

Since we issued AD 98–26–01, we 

have determined that certain 

compliance times need to be reduced in 

order to adequately address the 

identified unsafe condition. Therefore, 

certain requirements of paragraphs (h), 

(i), (j), (m), (n), and (s) of that AD are 

included in this NPRM. The European 

Aviation Safety Agency (EASA), which 

is the Technical Agent for the Member 

States of the European Community, has 

issued EASA Airworthiness Directive 

2007–0242, dated September 4, 2007 

(referred to after this as ‘‘the MCAI’’), 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 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, 

A310A–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. 

Other Relevant Rulemaking 

On September 5, 1990, we issued AD 

90–19–07, Amendment 39–6731 (55 FR 

37455), for certain Airbus Model A310– 

200 series airplanes, to require 

repetitive X-ray inspections of stringers 

6, 7, 8, and 9 run-outs inboard and 

outboard of rib 14, and repair if 

necessary. Accomplishing an inspection 

in accordance with paragraph (l) of this 

AD would terminate the requirements of 

paragraph (a) of AD 90–19–07. 

On March 6, 1991, we issued AD 91– 

06–18, amendment 39–6940 (56 FR 

10796), for all Airbus Model A310–200 

series airplanes, to require repetitive 

high frequency eddy current (HFEC) 

rototest inspections to detect cracks in 

the wing rear spar at certain bolt holes 

where the main landing gear (MLG) 

forward pick-up fittings are attached to 

the rear spar, and repair, if necessary. 

Accomplishing an inspection in 

accordance with paragraph (q) of this 

AD would terminate the requirements of 

AD 91–06–18, amendment 39–6940. 

We are also considering issuing three 

other NPRMs related to this NPRM: 

• Directorate Identifier 2010–NM– 

092–AD. That NPRM proposes to 

supersede AD 98–26–01, amendment 

39–10942 (63 FR 69179, December 16, 

1998), to continue to require certain 

actions specified in that AD. However, 

that NPRM does not restate paragraphs 

(h), (i), (j), (m), (n), and (s) of AD 98– 

26–01. Instead, certain requirements of 

paragraphs (h), (i), (j), (m), (n), and (s) 

of that AD are included in this NPRM, 

Directorate Identifier 2010–NM–091– 

AD. 

• Directorate Identifiers 2010–NM– 

089–AD and 2010–NM–090–AD. Both of 

these NPRMs include the requirements 

of certain other paragraphs of AD 98– 

26–01. 

Relevant Service Information 

Airbus has issued the service 

bulletins listed in the table below. 


srobinson on DSKHWCL6B1PROD with PROPOSALS
36 Federal Register / Vol. 76, No. 1 / Monday, January 3, 2011 / Proposed Rules 

TABLE—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. 

The actions described in this service 

information are intended to correct the 

unsafe condition identified in the 

MCAI. 

FAA’s Determination and Requirements 

of This Proposed AD 

This product has been approved by 

the aviation authority of another 

country, and is approved for operation 

in the United States. Pursuant to our 

bilateral agreement with the State of 

Design Authority, we have been notified 

of the unsafe condition described in the 

MCAI and service information 

referenced above. We are proposing this 

AD because we evaluated all pertinent 

information and determined an unsafe 

condition exists and is likely to exist or 

develop on other products of the same 

type design. 

Differences Between This AD and the 

MCAI or Service Information 

We have reviewed the MCAI and 

related service information and, in 

general, agree with their substance. But 

we might have found it necessary to use 

different words from those in the MCAI 

to ensure the AD is clear for U.S. 

operators and is enforceable. In making 

these changes, we do not intend to differ 

substantively from the information 

provided in the MCAI and related 

service information. 

We might also have proposed 

different actions in this AD from those 

in the MCAI in order to follow FAA 

policies. Any such differences are 

highlighted in a NOTE within the 

proposed AD. 

Costs of Compliance 

Based on the service information, we 

estimate that this proposed AD would 

affect about 44 products of U.S. registry. 

We also estimate that it would take 

about 97 work-hours per product to 

comply with the basic requirements of 

this proposed AD. The average labor 

rate is $85 per work-hour. Based on 

these figures, we estimate the cost of the 

proposed AD on U.S. operators to be 

$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 proposed AD 

would not have federalism implications 

under Executive Order 13132. This 

proposed AD would not have a 

substantial direct effect on the States, on 

the relationship between the national 

government and the States, or on the 

distribution of power and 

responsibilities among the various 

levels of government. 

For the reasons discussed above, I 

certify this proposed regulation: 

1. Is not a ‘‘significant regulatory 

action’’ under Executive Order 12866; 

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

DOT Regulatory Policies and Procedures 

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

3. Will not have a significant 

economic impact, positive or negative, 

on a substantial number of small entities 

under the criteria of the Regulatory 

Flexibility Act. 

We prepared a regulatory evaluation 

of the estimated costs to comply with 

this proposed AD and placed it in the 

AD docket. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety. 

The Proposed Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA proposes to amend 14 CFR part 

39 as follows: 

PART 39—AIRWORTHINESS 

DIRECTIVES 

1. The authority citation for part 39 

continues to read as follows: 

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

§ 39.13 [Amended] 

2. The FAA amends § 39.13 by adding 

the following new AD: 

Airbus: Docket No. FAA–2010–1275; 

Directorate Identifier 2010–NM–091–AD. 

Comments Due Date 

(a) We must receive comments by February 

17, 2011. 

Affected ADs 

(b) This AD affects AD 90–19–07, 

Amendment 39–6731; and AD 91–06–18, 

Amendment 39–6940. 

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. 


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Federal Register / Vol. 76, No. 1 / Monday, January 3, 2011 / Proposed Rules 37 

Restatement of Certain Requirements of AD 

98–26–01, Amendment 39–10942, 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 (Airbus Service Bulletin A310–57– 

2003) 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 (Airbus Service Bulletin A310–57– 

2003) 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: 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 Refuelling 

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 

5891H5128 (Airbus Service Bulletin A310– 

57–2020) 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. 

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 

5026H0878 (Airbus Service Bulletin A310– 

57–2005) 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 

5026H0878 (Airbus Service Bulletin A310– 

57–2005) 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 2: As of the effective date of this AD, 

if Airbus Service Bulletin A310–57–2005 is 


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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 

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, whichever occurs first, after the 

effective date of this AD. 

Inspect Area Around Overwing Refuelling 

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 

(Airbus Service Bulletin A310–57–2020) 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 (Airbus 

Service Bulletin A310–57–2020) 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. 

(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. 


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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. 

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, A310A–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 3: For Model A310–304, A310A–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 (Airbus Service 

Bulletin A310–57–2049) and Modification 

11578H5436 (Airbus Service Bulletin A310– 

57–2074) 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 (Airbus 

Service Bulletin A310–57–2049) or 

11578H5436 (Airbus Service Bulletin A310– 

57–2074) has been done. After doing Airbus 

Modification 07925H1113 (Airbus Service 

Bulletin A310–57–2049) or 11578H5436 

(Airbus Service Bulletin A310–57–2074) 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. 

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. 


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

Model A310–304, A310A–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, A310A–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 (Airbus Service 

Bulletin A310–57–2049) 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. 

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, A310A–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, A310A–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 (Airbus Service 

Bulletin A310–57–2074) 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 (Airbus 

Service Bulletin A310–57–2074) 

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, A310A–322, and 

A310–324 short range airplanes.

Within 24,200 flight cycles or 

67,900 flight hours, whichever 

occurs first, after Airbus Modification 11578H5436 (Airbus 

Service Bulletin A310–57–2074) 

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, A310A–322, and 

A310–324 long range airplanes.

Within 19,300 flight cycles or 

96,800 flight hours, whichever 

occurs first, after Airbus Modification 11578H5436 (Airbus 

Service Bulletin A310–57–2074) 

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. 


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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, Amendment 39–6731 

(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, Amendment 

39–6731. 

Note 4: 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, 

Amendment 39–6940 

(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, 

amendment 39–6940. 

Note 5: 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 6: 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. 

Send information 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. Before using 

any approved AMOC on any airplane to 

which the AMOC applies, notify your 

principal maintenance inspector (PMI) or 

principal avionics inspector (PAI), as 

appropriate, or lacking a principal inspector, 

your local Flight Standards District Office. 

The AMOC approval letter must specifically 

reference this AD. AMOCs approved 

previously in accordance with AD 98–26–01, 

amendment 39–10942, are approved as 

AMOCs for the corresponding provisions of 

this AD. 

(2) Airworthy Product: For any requirement 

in this AD to obtain corrective actions from 

a manufacturer or other source, use these 

actions if they are FAA-approved. Corrective 

actions are considered FAA-approved if they 

are approved by the State of Design Authority 

(or their delegated agent). You are required 

to assure the product is airworthy before it 

is returned to service. 

(3) Reporting Requirements: For any 

reporting requirement in this AD, under the 

provisions of the Paperwork Reduction Act 

(44 U.S.C. 3501 et seq.), the Office of 

Management and Budget (OMB) has 

approved the information collection 

requirements and has assigned OMB Control 

Number 2120–0056. 

Related Information 

(w) Refer to MCAI EASA Airworthiness 

Directive 2007–0242, dated September 4, 

2007; and 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 A310–57–2032 .................................................................................................... 3 ....................... January 4, 1996. 

Airbus Service Bulletin A310–57–2002 .................................................................................................... 2 ....................... January 4, 1996. 

Airbus Service Bulletin A310–57–2006 .................................................................................................... 3 ....................... May 2, 1996. 

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. 


srobinson on DSKHWCL6B1PROD with PROPOSALS
42 Federal Register / Vol. 76, No. 1 / Monday, January 3, 2011 / Proposed Rules 

Issued in Renton, Washington, on 

December 17, 2010. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2010–32989 Filed 12–30–10; 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] 

RIN 2120–AA64 

Airworthiness Directives; Airbus Model 

A310 Series Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to adopt a new 

airworthiness directive (AD) for the 

products listed above that would 

supersede two existing ADs. This 

proposed AD results from mandatory 

continuing airworthiness information 

(MCAI) originated by an aviation 

authority of another country to identify 

and correct an unsafe condition on an 

aviation product. The MCAI describes 

the unsafe condition as: 

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. The proposed 

AD would require actions that are 

intended to address the unsafe 

condition described in the MCAI. 

DATES: We must receive comments on 

this proposed AD by February 17, 2011. 

ADDRESSES: You may send comments by 

any of the following methods: 

• Federal eRulemaking Portal: Go to 

http://www.regulations.gov. Follow the 

instructions for submitting comments. 

• Fax: (202) 493–2251. 

• Mail: U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–140, 1200 New Jersey Avenue, SE., 

Washington, DC 20590. 

• Hand Delivery: U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–40, 1200 New Jersey Avenue, SE., 

Washington, DC, between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. 

For service information identified in 

this proposed AD, contact Airbus SAS– 

EAW (Airworthiness Office), 1 Rond 

Point Maurice Bellonte, 31707 Blagnac 

Cedex, France; telephone +33 5 61 93 36 

96; fax +33 5 61 93 44 51; e-mail 

account.airworth-eas@airbus.com; 

Internet http://www.airbus.com. You 

may review copies of the referenced 

service information at the FAA, 

Transport Airplane Directorate, 1601 

Lind Avenue, SW., Renton, Washington. 

For information on the availability of 

this material at the FAA, call 425–227– 

1221. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http:// 

www.regulations.gov; or in person at the 

Docket Operations office between 9 a.m. 

and 5 p.m., Monday through Friday, 

except Federal holidays. The AD docket 

contains this proposed AD, the 

regulatory evaluation, any comments 

received, and other information. The 

street address for the Docket Operations 

office (telephone (800) 647–5527) is in 

the ADDRESSES section. Comments will 

be available in the AD docket shortly 

after receipt. 

FOR FURTHER INFORMATION CONTACT: Dan 

Rodina, Aerospace Engineer, 

International Branch, ANM–116, 

Transport Airplane Directorate, FAA, 

1601 Lind Avenue, SW., Renton, 

Washington 98057–3356; telephone 

(425) 227–2125; fax (425) 227–1149. 

SUPPLEMENTARY INFORMATION: 

Comments Invited 

We invite you to send any written 

relevant data, views, or arguments about 

this proposed AD. Send your comments 

to an address listed under the 

ADDRESSES section. Include ‘‘Docket No. 

FAA–2010–1276; Directorate Identifier 

2010–NM–092–AD’’ at the beginning of 

your comments. We specifically invite 

comments on the overall regulatory, 

economic, environmental, and energy 

aspects of this proposed AD. We will 

consider all comments received by the 

closing date and may amend this 

proposed AD based on those comments. 

We will post all comments we 

receive, without change, to http:// 

www.regulations.gov, including any 

personal information you provide. We 

will also post a report summarizing each 

substantive verbal contact we receive 

about this proposed AD. 

Discussion 

On December 8, 1998, we issued AD 

98–26–01, Amendment 39–10942 (63 

FR 69179, December 16, 1998); and on 

May 30, 1991, we issued AD 91–13–01, 

Amendment 39–7032 (56 FR 26602, 

June 10, 1991). Those ADs required 

actions intended to address an unsafe 

condition on the products listed above. 

Since we issued ADs 98–26–01 and 

91–13–01, we have determined that 

certain compliance times need to be 

reduced in order to adequately address 

the identified unsafe condition. The 

European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Community, has issued EASA 

Airworthiness Directive 2007–0053R3, 

dated December 17, 2009 (referred to 

after this as ‘‘the MCAI’’), 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 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 [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 part of the Structure Task 

Group for the A310 program, EASA AD 

2007–0053 superseded DGAC France AD F– 

1992–106–132R7 in order to take into 

account the publication of Airbus Service 

Bulletins (SB) A310–55–2004 at Revision 5 

and Airbus SB A310–53–2074 at Revision 3, 

whose inspection thresholds and/or intervals 

had been reduced. 

Revision 1 of this AD was issued to remove 

the mandatory requirements related to the 

wings (i.e. § 1.8, 1.9, 1.10, 1.13, and 1.18) 

from the Compliance section, which have 

been transferred to EASA AD 2007–0242. 

Revision 2 of this AD has been issued to 

remove the mandatory requirements of 

paragraph 1.15, 1.16 and 1.17 which have 

now been transferred to EASA AD 2009–0057 

(§ 1.15 and 1.17) and 2009–0058 (§ 1.16) 

respectively. 

Revision 3 of this AD is issued to add a 

Note to the Applicability and amend the 

Required Action(s) and Compliance Time(s) 

section of this AD to clarify the allowed use 

of the referenced SBs by operators. In 

addition, a note has been added to paragraph 

1.7 and the notes associated to paragraphs 

1.1, 1.2, 1.3, 1.4, 1.5 and 1.12 have been 

clarified. 

The unsafe condition is reduced 

structural integrity of the wings, 

fuselage, and stabilizers. This NPRM 

proposes to continue to require certain 

actions specified in AD 98–26–01. This 

proposed AD also expands the 

inspection area of the high frequency 

eddy current rototest inspection 


srobinson on DSKHWCL6B1PROD with PROPOSALS