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

2074, Revision 03, dated October 13, 2006, 

are considered acceptable for compliance 

with the corresponding action specified in 

this AD. 

FAA AD Differences 

Note 2: This AD differs from the MCAI 

and/or service information as follows: The 

MCAI and service information do not specify 

a corrective action if cracking is found and 

the radius of the rework is 20.0 mm (0.787 

inch) or more. Paragraph (g)(3)(i)(B) of this 

AD requires 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). 

Other FAA AD Provisions 

(k) 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. 

(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 

(l) Refer to MCAI EASA Airworthiness 

Directive 2009–0058, dated March 13, 2009; 

and Airbus Mandatory Service Bulletin 

A310–53–2074, Revision 04, dated October 

24, 2008; for related information. 

Issued in Renton, Washington, on 

December 17, 2010. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2010–32991 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–2010–1274; Directorate 

Identifier 2010–NM–090–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 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 

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–2010–1274; Directorate Identifier 

2010–NM–090–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 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Community, has issued EASA 

Airworthiness Directive 2009–0057, 

dated March 13, 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 


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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 

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. 

Other Relevant Rulemaking 

We are 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 

(p) and (r) of AD 98–26–01. Instead, 

certain requirements of paragraphs (p) 

and (r) of that AD are included in this 

NPRM, Directorate Identifier 2010–NM– 

090–AD. 

• Directorate Identifiers 2010–NM– 

089–AD and 2010–NM–091–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 that follows: 

TABLE—SERVICE INFORMATION

Service bulletin Revision Date 

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

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

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

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 137 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 

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

Authority for This Rulemaking 

Title 49 of the United States Code 

specifies the FAA’s authority to issue 

rules on aviation safety. Subtitle I, 

section 106, describes the authority of 

the FAA Administrator. ‘‘Subtitle VII: 

Aviation Programs,’’ describes in more 

detail the scope of the Agency’s 

authority. 

We are issuing this rulemaking under 

the authority described in ‘‘Subtitle VII, 

Part A, Subpart III, Section 44701: 

General requirements.’’ Under that 

section, Congress charges the FAA with 

promoting safe flight of civil aircraft in 

air commerce by prescribing regulations 

for practices, methods, and procedures 

the Administrator finds necessary for 

safety in air commerce. This regulation 

is within the scope of that authority 

because it addresses an unsafe condition 

that is likely to exist or develop on 

products identified in this rulemaking 

action. 

Regulatory Findings 

We determined that this 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 


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

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–2010–1274; 

Directorate Identifier 2010–NM–090–AD. 

Comments Due Date 

(a) We must receive comments by February 

17, 2011. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to Airbus Model A310– 

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

–325 airplanes, certificated in any category, 

all serial numbers. 

Subject 

(d) Air Transport Association (ATA) of 

America Code 57: Wings. 

Reason 

(e) The mandatory continuing 

airworthiness information (MCAI) states: 

DGAC [Direction Ge ́ne ́rale de l’Aviation 

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

* * * * * 

The unsafe condition is reduced structural 

integrity of the wings. 

Compliance 

(f) You are responsible for having the 

actions required by this AD performed within 

the compliance times specified, unless the 

actions have already been done. 

Cold Working of Trellis Boom Drainage 

Holes 

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

–322 and –324 airplanes, except airplanes 

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

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

specified in Table 1 of this AD, cold work the 

trellis boom drainage holes, in accordance 

with the Accomplishment Instructions of 

Airbus Mandatory Service Bulletin A310–57– 

2048, Revision 01, dated May 22, 2007. 

Certain compliance times specified in Table 

1 of this AD are applicable to short range use, 

average flight time (AFT) equal to or less than 

3.6 hours; or long range use, AFT exceeding 

3.6 hours. 

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

Airplanes, as identified in Airbus mandatory 

service bulletin A310–57–2048, revision 01, 

dated May 22, 2007 

Compliance time (whichever occurs later) 

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

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

Within 6 months after the effective date of this 

AD. 

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

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

Within 6 months after the effective date of this 

AD. 

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

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

Within 6 months after the effective date of this 

AD. 

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

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

Within 6 months after the effective date of this 

AD. 

(1) Airplanes on which Airbus 

modification 06130 was done in production. 

(2) Airplanes on which Airbus Mandatory 

Service Bulletin A310–57–2048 was done in 

service. 

(3) Airplanes on which rework of cracked 

drain holes was done in accordance with 

Airbus Mandatory Service Bulletin A310–57– 

2050. 

Inspection of Trellis Boom Drainage Holes 

(h) For all airplanes: Within the applicable 

intervals specified in Table 2 of this AD, 

perform a detailed or rotating probe 

inspection for cracking in the drain holes on 

the lower skin panel in the center wing box 

between frames 42 and 46, in accordance 

with the Accomplishment Instructions of 

Airbus Mandatory Service Bulletin A310–57– 

2050, Revision 02, dated August 27, 2009. 

Repeat the inspections thereafter at intervals 

not to exceed the applicable times specified 

in Table 3 of this AD. Certain compliance 

times specified in Tables 2 and 3 of this AD 

are applicable to short range use, average 

flight time (AFT) equal to or less than 3.6 

hours; or long range use, AFT exceeding 3.6 

hours. 

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

Airplanes, as identified in Airbus mandatory 

service bulletin A310–57–2050, revision 02, 

dated August 27, 2009 

Compliance time (whichever occurs later) 

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

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

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

whichever occurs first, after the effective 

date of this AD. 


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

Airplanes, as identified in Airbus mandatory 

service bulletin A310–57–2050, revision 02, 

dated August 27, 2009 

Compliance time (whichever occurs later) 

Configuration 02 airplanes on which Airbus 

Mandatory Service Bulletin A310–57–2048 

has been done within the ‘‘recommended’’ 

compliance times specified in paragraph 

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

2048, Revision 01, dated May 22, 2007.

Within 32,850 flight cycles or 65,700 flight 

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

A310–57–2048.

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

whichever occurs first, after the effective 

date of this AD. 

Configuration 02 airplanes on which Airbus 

Mandatory Service Bulletin A310–57–2048 

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

paragraph 1.E.(2), ‘‘Accomplishment 

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

22, 2007.

Within 8,600 flight cycles or 17,250 flight 

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

Airbus Mandatory Service Bulletin A310– 

57–2048; 

OR 

Within 11,400 flight cycles or 22,800 flight 

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

A310–57–2048.

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

whichever occurs first, after the effective 

date of this AD. 

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

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

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

whichever occurs first, after the effective 

date of this AD. 

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

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

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

whichever occurs first, after the effective 

date of this AD. 

Configuration 05 airplanes on which Airbus 

Mandatory Service Bulletin A310–57–2048 

has been done within the ‘‘recommended’’ 

compliance times specified in paragraph 

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

2048, Revision 01, dated May 22, 2007.

Prior to the accumulation of 40,000 total flight 

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

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

whichever occurs first, after the effective 

date of this AD. 

Configuration 05 airplanes on which Airbus 

Mandatory Service Bulletin A310–57–2048 

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

paragraph 1.E.(2), ‘‘Accomplishment 

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

22, 2007.

Within 10,600 flight cycles or 21,150 flight 

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

Airbus Mandatory Service Bulletin A310– 

57–2048; 

OR 

Within 13,900 flight cycles or 27,800 flight 

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

A310–57–2048.

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

whichever occurs first, after the effective 

date of this AD. 

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

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

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

whichever occurs first, after the effective 

date of this AD. 

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

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

Within 800 flight cycles or 4,000 flight hours, 

whichever occurs first, after the effective 

date of this AD. 

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

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

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

whichever occurs first, after the effective 

date of this AD. 

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

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

Within 800 flight cycles or 4,000 flight hours, 

whichever occurs first, after the effective 

date of this AD. 

Configuration 08 short range airplanes on 

which Airbus Mandatory Service Bulletin 

A310–57–2048 has been done within the 

‘‘recommended’’ compliance times specified 

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

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

22, 2007.

Prior to the accumulation of 30,950 total flight 

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

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

whichever occurs first, after the effective 

date of this AD. 


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

Airplanes, as identified in Airbus mandatory 

service bulletin A310–57–2050, revision 02, 

dated August 27, 2009 

Compliance time (whichever occurs later) 

Configuration 08 short range airplanes on 

which Airbus Mandatory Service Bulletin 

A310–57–2048 has not been done within the 

‘‘recommended’’ compliance times specified 

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

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

22, 2007.

Within 8,200 flight cycles or 23,000 flight 

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

Airbus Mandatory Service Bulletin A310– 

57–2048; 

OR 

Within 10,800 flight cycles or 30,300 flight 

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

A310–57–2048.

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

whichever occurs first, after the effective 

date of this AD. 

Configuration 08 long range airplanes on which 

Airbus Mandatory Service Bulletin A310–57– 

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

paragraph 1.E.(2), ‘‘Accomplishment 

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

22, 2007.

Prior to the accumulation of 24,100 total flight 

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

Within 800 flight cycles or 4,000 flight hours, 

whichever occurs first, after the effective 

date of this AD. 

Configuration 08 long range airplanes on which 

Airbus Mandatory Service Bulletin A310–57– 

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

paragraph 1.E.(2), ‘‘Accomplishment 

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

22, 2007.

Within 6,400 flight cycles or 31,950 flight 

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

Airbus Mandatory Service Bulletin A310– 

57–2048; 

OR 

Within 8,400 flight cycles or 42,150 flight 

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

A310–57–2048.

Within 800 flight cycles or 4,000 flight hours, 

whichever occurs first, after the effective 

date of this AD. 

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

Airplanes, as identified in Airbus 

mandatory service bulletin A310–57–2050, 

revision 02, dated August 27, 2009 

Type of inspection done during 

most recent inspection 

Repetitive interval 

(not to exceed) 

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

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

first. 

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

first. 

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

first. 

Configurations 06, 07, and 08 short range 

airplanes.

Detailed inspection ....................... 8,200 flight cycles or 23,000 flight hours, whichever occurs first. 

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

first. 

Configurations 06, 07, and 08 long range 

airplanes.

Detailed inspection ....................... 6,400 flight cycles or 31,950 flight hours, whichever occurs first. 

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

Corrective Actions for Paragraph (h) of This 

AD 

(i) If any cracking is found during any 

inspection required by paragraph (h) of this 

AD, before further flight, do all applicable 

corrective actions, in accordance with the 

Accomplishment Instructions of Airbus 

Mandatory Service Bulletin A310–57–2050, 

Revision 02, dated August 27, 2009; except 

where the service bulletin specifies to contact 

Airbus, before further flight, repair in 

accordance with a method approved by 

either the Manager, International Branch, 

ANM–116, FAA, Transport Airplane 

Directorate, or EASA (or its delegated agent). 

Inspection of Fuselage Frame 40 Upper 

Corner Fitting 

(j) For all airplanes: Within the applicable 

time specified in Table 4 of this AD, perform 

an eddy current inspection for cracking of the 

upper corner fitting at left and right frame 40, 

in accordance with the Accomplishment 

Instructions of Airbus Mandatory Service 

Bulletin A310–57–2064, Revision 02, dated 

December 21, 2007. Repeat the inspections 

thereafter at intervals not to exceed the 

applicable times specified in Table 5 of this 

AD. Certain compliance times specified in 

Tables 4 and 5 of this AD are applicable to 

short range use, average flight time (AFT) 

equal to or less than 3.23 hours; or long range 

use, AFT exceeding 3.23 hours. 


srobinson on DSKHWCL6B1PROD with PROPOSALS
Federal Register / Vol. 76, No. 1 / Monday, January 3, 2011 / Proposed Rules 55 

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

Airplane configurations identified in Airbus 

mandatory service bulletin A310–57–2064, 

revision 02, dated December 21, 2007 

Compliance time (whichever occurs later) 

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

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

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

whichever occurs first, after the effective 

date of this AD. 

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

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

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

whichever occurs first, after the effective 

date of this AD. 

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

range airplanes identified as Configuration 01.

Prior to the accumulation of 14,700 total flight 

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

Within 600 flight cycles or 1,800 flight hours, 

whichever occurs first, after the effective 

date of this AD. 

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

range airplanes identified as Configurations 

02 and 03.

Prior to the accumulation of 20,700 total flight 

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

Within 600 flight cycles or 1,800 flight hours, 

whichever occurs first, after the effective 

date of this AD. 

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

range airplanes identified as Configuration 01.

Prior to the accumulation of 12,800 total flight 

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

Within 500 flight cycles or 2,650 flight hours, 

whichever occurs first, after the effective 

date of this AD. 

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

range airplanes identified as Configurations 

02 and 03.

Prior to the accumulation of 18,000 total flight 

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

Within 500 flight cycles or 2,650 flight hours, 

whichever occurs first, after the effective 

date of this AD. 

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

Airplanes Repetitive interval 

(not to exceed) 

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

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

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

Corrective Actions for Paragraph (h) of This 

AD 

(k) If, during any inspection required by 

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

prior to further flight, do all applicable 

corrective actions, in accordance with the 

Accomplishment Instructions of Airbus 

Mandatory Service Bulletin A310–57–2064, 

Revision 02, dated December 21, 2007; 

except where the service bulletin specifies to 

contact Airbus, before further flight, repair in 

accordance with a method approved by 

either the Manager, International Branch, 

ANM–116, FAA, Transport Airplane 

Directorate, or EASA (or its delegated agent). 

Credit for Actions Accomplished in 

Accordance With Previous Service 

Information 

(l) Actions accomplished before the 

effective date of this AD in accordance with 

Airbus Service Bulletin A310–57–2048, 

dated April 23, 1990, are considered 

acceptable for compliance with the 

corresponding action specified in paragraph 

(g) of this AD. 

(m) Actions accomplished before the 

effective date of this AD in accordance with 

Airbus Service Bulletin A310–57–2050, 

dated April 23, 1990; or Airbus Mandatory 

Service Bulletin A310–57–2050, Revision 01, 

dated May 22, 2007; are considered 

acceptable for compliance with the 

corresponding actions specified in 

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

(n) Actions done before the effective date 

of this AD in accordance with Airbus Service 

Bulletin A310–57–2064, dated August 24, 

1995; or Revision 01, dated January 5, 2001; 

are acceptable for compliance with the 

corresponding actions specified in 

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

FAA AD Differences 

Note 1: This AD differs from the MCAI 

and/or service information as follows: No 

Differences. 

Other FAA AD Provisions 

(o) The following provisions also apply to 

this AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, International 

Branch, ANM–116, Transport Airplane 

Directorate, FAA, has the authority to 

approve AMOCs for this AD, if requested 

using the procedures found in 14 CFR 39.19. 

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. 

(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 

(p) Refer to MCAI EASA Airworthiness 

Directive 2009–0057, dated March 13, 2009, 

and the service bulletins listed in Table 6 of 

this AD, for related information. 

TABLE 6—SERVICE INFORMATION

Service bulletin Revision Date 

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

Airbus Mandatory Service Bulletin A31–57–2050 ........................................................ 02 ................................................. August 27, 2009. 


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

TABLE 6—SERVICE INFORMATION—Continued 

Service bulletin Revision Date 

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

Issued in Renton, Washington on 

December 17, 2010. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2010–32992 Filed 12–30–10; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF DEFENSE 

Office of the Secretary 

[Docket ID: DOD–2010–OS–0183] 

32 CFR Part 311 

Privacy Act; Implementation 

AGENCY: Office of the Secretary, DoD. 

ACTION: Proposed rule. 

SUMMARY: The Office of the Secretary of 

Defense is exempting those records 

contained in DMDC 15 DoD, entitled 

‘‘Armed Services Military Accession 

Testing’’ when the record includes the 

specific answers submitted and the 

answer key. Releasing this information 

to the individual will compromise the 

objectivity or fairness of the test if the 

correct or incorrect answers are 

released. 

DATES: Comments must be received on 

or before March 4, 2011 to be 

considered by this agency. 

ADDRESSES: You may submit comments, 

identified by docket number and/or RIN 

number and title, by any of the 

following methods: 

• Federal Rulemaking Portal: http:// 

www.regulations.gov. Follow the 

instructions for submitting comments. 

• Mail: Federal Docket Management 

System Office, Room 3C843, 1160 

Defense Pentagon, Washington, DC 

20301–1160. 

Instructions: All submissions received 

must include the agency name and 

docket number or Regulatory 

Information Number (RIN) for this 

Federal Register document. The general 

policy for comments and other 

submissions from members of the public 

is to make these submissions available 

for public viewing on the Internet at 

http://www.regulations.gov as they are 

received without change, including any 

personal identifiers or contact 

information. 

FOR FURTHER INFORMATION CONTACT: Mrs. 

Cindy Allard at (703) 588–6830. 

SUPPLEMENTARY INFORMATION: 

Executive Order 12866, ‘‘Regulatory 

Planning and Review’’ 

It has been determined that Privacy 

Act rules for the Department of Defense 

are not significant rules. The rules do 

not (1) Have an annual effect on the 

economy of $100 million or more or 

adversely affect in a material way the 

economy; a sector of the economy; 

productivity; competition; jobs; the 

environment; public health or safety; or 

State, local, or Tribal governments or 

communities; (2) Create a serious 

inconsistency or otherwise interfere 

with an action taken or planned by 

another Agency; (3) Materially alter the 

budgetary impact of entitlements, 

grants, user fees, or loan programs, or 

the rights and obligations of recipients 

thereof; or (4) Raise novel legal or policy 

issues arising out of legal mandates, the 

President’s priorities, or the principles 

set forth in this Executive order. 

Public Law 96–354, ‘‘Regulatory 

Flexibility Act’’ (5 U.S.C. Chapter 6) 

It has been determined that this 

Privacy Act rule for the Department of 

Defense does not have significant 

economic impact on a substantial 

number of small entities because it is 

concerned only with the administration 

of Privacy Act systems of records within 

the Department of Defense. 

Public Law 95–511, ‘‘Paperwork 

Reduction Act’’ (44 U.S.C. Chapter 35) 

It has been determined that this 

Privacy Act rule for the Department of 

Defense imposes no information 

requirements beyond the Department of 

Defense and that the information 

collected within the Department of 

Defense is necessary and consistent 

with 5 U.S.C. 552a, known as the 

Privacy Act of 1974. 

Section 202, Public Law 104–4, 

‘‘Unfunded Mandates Reform Act’’ 

It has been determined that this 

Privacy Act rulemaking for the 

Department of Defense does not involve 

a Federal mandate that may result in the 

expenditure by State, local and Tribal 

governments, in the aggregate, or by the 

private sector, of $100 million or more 

and that such rulemaking will not 

significantly or uniquely affect small 

governments. 

Executive Order 13132, ‘‘Federalism’’ 

It has been determined that the 

Privacy Act rules for the Department of 

Defense do not have federalism 

implications. The rule does not have 

substantial direct effects 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. 

List of Subjects in 32 CFR Part 311 

Privacy. 

Accordingly, 32 CFR part 311 is 

proposed to be amended to read as 

follows: 

PART 311—OFFICE OF THE 

SECRETARY OF DEFENSE AND JOINT 

STAFF PRIVACY PROGRAM 

1. The authority citation for 32 CFR 

part 311 continues to read as follows: 

Authority: Pub. L. 93–579, 88 Stat. 1986 (5 

U.S.C. 522a). 

2. Section 311.8 is amended by 

adding paragraph (c)(16) to read as 

follows: 

§ 311.8 Procedures for exemptions. 

* * * * * 

(c) * * * 

(16) System identifier and name: 

DMDC 15 DoD, Armed Services Military 

Accession Testing. 

(i) Exemption: Testing or examination 

material used solely to determine 

individual qualifications for 

appointment or promotion in the 

Federal service or military service may 

be exempt pursuant to 5 U.S.C. 552a 

(k)(6), if the disclosure would 

compromise the objectivity or fairness 

of the test or examination process. 

Therefore, portions of the system of 

records may be exempt pursuant to 5 

U.S.C. 552a(d). 

(ii) 

Authority: 5 U.S.C. 552a(k)(6). 

(iii) Reasons: (A) An exemption is 

required for those portions of the Skill 

Qualification Test system pertaining to 

individual item responses and scoring 

keys to preclude compromise of the test 

and to ensure fairness and objectivity of 

the evaluation system. 

(B) From subsection (d)(1) when 

access to those portions of the Skill 

Qualification Test records would reveal 

the individual item responses and 


srobinson on DSKHWCL6B1PROD with PROPOSALS