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 


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Federal Register / Vol. 76, No. 1 / Monday, January 3, 2011 / Proposed Rules 43 

required by paragraph (g) of AD 98–26– 

01. The required actions are as follows, 

depending on airplane configuration: 

• A defectoscope or rototest 

inspection to detect cracks in the area of 

frame 47 and frame 54, install new 

doublers, and repair if necessary. 

• Repetitive visual inspections to 

detect cracks on frame 46 between the 

left- and right-hand sides of stringers 21 

and 22 on the forward and aft faces, and 

repair if necessary. 

• Repetitive visual inspections to 

detect cracks at the T-section connecting 

frame 50A to the beam between the leftand right-hand sides of frames 50 and 

51, and modification if necessary. 

• Repetitive visual inspections to 

detect cracks in the lower milled side 

panel at the lap joint with the upper 

side panel at frame 47 and stringer 22, 

left- and right-hand sides, and repair if 

necessary. 

• An eddy current inspection to 

detect cracks on the upper integral part 

adjacent to the rear attach fittings on the 

horizontal stabilizer, modification of the 

horizontal stabilizer, and repair if 

necessary. 

• Repetitive high frequency eddy 

current rototest inspections for cracking 

of the doubler plate edge, rear spar area, 

and at specified fastener holes in the top 

skin chordwise splice along the contour 

of the steel doubler between ribs 3 and 

4 on the left- and right-hand center and 

side boxes on the horizontal stabilizer, 

installing new fasteners if no cracking is 

found, and repair if necessary. 

• Repetitive inspections, either an 

eddy current or visual inspection, to 

detect cracks on the left and right 

vertical posts, numbers 1 through 5 

inclusive, in the wing center box at 

frame 40/41, and modification if 

necessary. 

You may obtain further information 

by examining the MCAI in the AD 

docket. 

Other Relevant Rulemaking 

Certain paragraphs specified in AD 

98–26–01 are not restated and are 

addressed by the following ADs and 

NPRMs. 

• AD 2009–01–09, Amendment 39– 

15788 (74 FR 8728, February 26, 2009), 

addresses the actions specified in 

paragraph (a) of AD 98–26–01. 

• AD 2004–15–07, Amendment 39– 

13741 (69 FR 44592, July 27, 2004), 

addresses the actions specified in 

paragraph (k) of AD 98–26–01. 

• AD 2006–09–05, Amendment 39– 

14575 (71 FR 25921, May 3, 2006), 

addresses the actions specified in 

paragraph (o) of AD 98–26–01. 

• NPRM, Directorate Identifier 2010– 

NM–091–AD, addresses the actions 

specified in paragraphs (h), (i), (j), (m), 

(n), and (s) of AD 98–26–01. 

• NPRM, Directorate Identifier 2010– 

NM–090–AD, addresses the action 

specified in paragraphs (p) and (r) of AD 

98–26–01. 

• NPRM, Directorate Identifier 2010– 

NM–089–AD, addresses the action 

specified in paragraph (q) of AD 98–26– 

01. 

Relevant Service Information 

Airbus has issued Mandatory Service 

Bulletin A310–55–2004, Revision 05, 

including Appendix 01, dated October 

13, 2006; and Airbus Service Bulletin 

A310–53–2019, Revision 3, dated 

February 28, 1991. 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. 

The actions that are required by AD 

98–26–01 and retained in this proposed 

AD take about 1,087 work-hours per 

product, at an average labor rate of $85 

per work hour. Required parts cost 

about $81,973 per product. Based on 

these figures, the estimated cost of the 

currently required actions is $174,368 

per product. 

We estimate that it would take about 

3 work-hours per product to comply 

with the new 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 

$11,220, or $255 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. 


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

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 

removing Amendment 39–10942 (63 FR 

69179, December 16, 1998) and 

Amendment 39–7032 (56 FR 26602, 

June 10, 1991) and adding the following 

new AD: 

Airbus: Docket No. FAA–2010–1276; 

Directorate Identifier 2010–NM–092–AD. 

Comments Due Date 

(a) We must receive comments by February 

17, 2011. 

Affected ADs 

(b) This AD supersedes AD 98–26–01, 

Amendment 39–10942, and AD 91–13–01, 

Amendment 39–7032. 

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 Codes 53: Fuselage, 55: Stabilizers, 

and 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 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. 

Compliance 

(f) You are responsible for having the 

actions required by this AD performed within 

the compliance times specified, unless the 

actions have already been done. 

Restatement of Certain Requirements of 

AD 98–26–01 

Actions for Service Bulletin 

A310–53–2016—No Changes 

(g) For airplanes listed in Airbus Service 

Bulletin A310–53–2016, Revision 5, dated 

December 7, 1992: 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), whichever 

occurs later, perform a defectoscope or 

rototest inspection to detect cracks in the 

area of frame 47 and frame 54, and install 

new doublers, in accordance with Airbus 

Service Bulletin A310–53–2016, Revision 5, 

dated December 7, 1992. Except as provided 

by paragraph (m) of this AD, if any 

discrepancy is found, prior to further flight, 

perform follow-on corrective actions, as 

applicable, in accordance with Airbus 

Service Bulletin A310–53–2016, Revision 5, 

dated December 7, 1992. 

Note 1: Airplanes on which Airbus 

Modification 04980 is done in production are 

not affected by paragraph (g) of this AD. 

Actions for Service Bulletin 

A310–53–2054, With Latest Optional 

Modification 

(h) For airplanes listed in Airbus Service 

Bulletin A310–53–2054, Revision 2, dated 

May 22, 1990: Prior to the accumulation of 

12,000 total flight cycles, or within 1,000 

flight cycles after January 20, 1999, 

whichever occurs later, and thereafter at 

intervals not to exceed 3,000 flight cycles, 

perform a visual inspection to detect cracks 

on frame 46 between the left- and right-hand 

sides of stringers 21 and 22 on the forward 

and aft faces, in accordance with Airbus 

Service Bulletin A310–53–2054, Revision 2, 

dated May 22, 1990. If any crack is found, 

prior to further flight, repair in accordance 

with Airbus Service Bulletin A310–53–2054, 

Revision 2, dated May 22, 1990. 

Note 2: Airplanes on which Airbus 

modification 05254 is done in production; or 

on which Airbus Service Bulletin A310–53– 

2019, Revision 2, dated May 22, 1990, or 

Revision 3, dated February 28, 1991, is done 

in service; are not affected by paragraph (h) 

of this AD. 

(1) Prior to the effective date of this AD: 

Accomplishment of the repair required by 

paragraph (h) of this AD; or modification of 

the reinforcement angle runout in accordance 

with Airbus Service Bulletin A310–53–2019, 

Revision 2, dated May 22, 1990, or Revision 

3, dated February 28, 1991; terminates the 

repetitive inspection requirements of 

paragraph (h) of this AD. 

(2) On or after the effective date of this AD: 

Accomplishment of the repair required by 

paragraph (h) of this AD; or modification of 

the reinforcement angle runout in accordance 

with Airbus Service Bulletin A310–53–2019, 

Revision 3, dated February 28, 1991; 

terminates the repetitive inspection 

requirements of paragraph (h) of this AD. 

Actions for Service Bulletin 

A310–53–2057—No Changes 

(i) For airplanes listed in Airbus Service 

Bulletin A310–53–2057, Revision 1, dated 

April 30, 1992: Perform a visual inspection 

to detect cracks at the T-section connecting 

frame 50A to the beam between the left- and 

right-hand sides of frames 50 and 51, in 

accordance with Airbus Service Bulletin 

A310–53–2057, Revision 1, dated April 30, 

1992. Perform the inspection at the time 

specified in paragraph (i)(1) or (i)(2) of this 

AD, as applicable. If any crack is found, prior 

to further flight, accomplish Airbus 

Modifications No. 4853 and No. 5273, in 

accordance with Airbus Service Bulletin 

A310–53–2057, Revision 1, dated April 30, 

1992. Accomplishment of these 

modifications terminates the requirements of 

this paragraph. 

Note 3: Airplanes on which Airbus 

modification 4853 is done are affected by 

paragraph (i) of this AD, except those 

airplanes on which Airbus Modification 5273 

has been done or on which Airbus Service 

Bulletin A310–53–2011 has been done in 

service. 

(1) For the airplane having manufacturer’s 

serial number (MSN) 191: Prior to the 

accumulation of 24,000 total flight cycles, or 

within 1,000 flight cycles after January 20, 

1999, whichever occurs later; and thereafter 

at intervals not to exceed 6,000 flight cycles. 

(2) For airplanes other than the airplane 

identified in paragraph (i)(1) of this AD: Prior 

to the accumulation of 12,000 total flight 

cycles, or within 1,000 flight cycles after 

January 20, 1999, whichever occurs later; and 

thereafter at intervals not to exceed 6,000 

flight cycles. 

Actions for Service Bulletin 

A310–53–2059—No Changes 

(j) For airplanes listed in Airbus Service 

Bulletin A310–53–2059, Revision 1, dated 

January 4, 1996: Perform a visual inspection 

to detect cracks in the lower milled side 

panel at the lap joint with the upper side 

panel at frame 47 and stringer 22, left- and 

right-hand sides, in accordance with Airbus 

Service Bulletin A310–53–2059, Revision 1, 

dated January 4, 1996. Perform the inspection 

at the time specified in paragraph (j)(1) or 

(j)(2) of this AD, as applicable. Except as 

provided by paragraph (m) of this AD, if any 

crack is found, prior to further flight, repair 

in accordance with Airbus Service Bulletin 

A310–53–2059, Revision 1, dated January 4, 

1996. Thereafter, repeat the inspections at 

intervals not to exceed 9,000 flight cycles, or 

accomplish Airbus Modification 5997 

(Airbus Service Bulletin A310–53–2058). 

Accomplishment of either the repair or 

Airbus Modification 5997 constitutes 

terminating action for the repetitive 

inspections required by this paragraph. 

Note 4: Airplanes on which Airbus 

Modification 5997 has been done completely 

in production, or on which Airbus Service 

Bulletin A310–53–2058 has been done in 

service, are not affected by the actions in 

paragraph (j) of this AD. 

(1) For Model A310–200 series airplanes, 

accomplish the inspection at the time 

specified in paragraph (j)(1)(i) or (j)(1)(ii) of 

this AD, as applicable. 

(i) For airplanes that have accumulated less 

than 20,000 total flight cycles as of January 

20, 1999: Prior to the accumulation of 18,000 

total flight cycles, or within 2,000 flight 

cycles after January 20, 1999, whichever 

occurs later. 

(ii) For airplanes that have accumulated 

20,000 or more total flight cycles as of 

January 20, 1999: Within 1,000 flight cycles 

after January 20, 1999. 

(2) For Model A310–300 series airplanes, 

accomplish the inspection at the time 


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Federal Register / Vol. 76, No. 1 / Monday, January 3, 2011 / Proposed Rules 45 

specified in paragraph (j)(2)(i) or (j)(2)(ii) of 

this AD, as applicable. 

(i) For airplanes that have accumulated less 

than 19,700 total flight cycles as of January 

20, 1999: Prior to the accumulation of 18,000 

total flight cycles, or within 1,700 flight 

cycles after January 20, 1999, whichever 

occurs later. 

(ii) For airplanes that have accumulated 

19,700 or more total flight cycles as of 

January 20, 1999: Within 850 flight cycles 

after January 20, 1999. 

Actions for Service Bulletin 

A310–55–2002—No Changes 

(k) For airplanes listed in Airbus Service 

Bulletin A310–55–2002, Revision 4, dated 

April 28, 1989: Prior to the accumulation of 

12,000 total flight cycles, or within 1,000 

flight cycles after January 20, 1999, 

whichever occurs later, perform an eddy 

current inspection to detect cracks on the 

upper integral part adjacent to the rear attach 

fittings on the horizontal stabilizer, and 

modify the horizontal stabilizer, in 

accordance with Airbus Service Bulletin 

A310–55–2002, Revision 4, dated April 28, 

1989. Except as provided by paragraph (m) of 

this AD, if any discrepancy is found, prior to 

further flight, perform follow-on corrective 

actions, as applicable, in accordance with 

Airbus Service Bulletin A310–55–2002, 

Revision 4, dated April 28, 1989. 

Actions for Service Bulletin 

A310–57–2039—No Changes 

(l) For airplanes listed in Airbus Service 

Bulletin A310–57–2039, dated September 24, 

1990: Perform either an eddy current or 

visual inspection to detect cracks on the left 

and right vertical posts, numbers 1 through 

5 inclusive, in the wing center box at frame 

40/41, in accordance with Airbus Service 

Bulletin A310–57–2039, dated September 24, 

1990. Perform the inspection at the time 

specified in paragraph (l)(1) or (l)(2) of this 

AD, as applicable. Except as provided by 

paragraph (m) of this AD, if any crack is 

found, prior to further flight, accomplish the 

modification specified in Airbus Service 

Bulletin A310–57–2041, dated September 24, 

1990, in accordance with Airbus Service 

Bulletin A310–57–2039, dated September 24, 

1990. 

Note 5: Airplanes on which Airbus 

Modification 04977 has been done in 

production are not affected by the actions 

specified in paragraph (l) of this AD. 

(1) For airplanes on which Airbus 

Modification 7541/S7973 (reference Airbus 

Service Bulletin A310–57–2041) has not been 

accomplished: Inspect prior to the 

accumulation of 21,000 total flight cycles, or 

within 1,000 flight cycles after January 20, 

1999, whichever occurs later; and thereafter 

at intervals not to exceed 4,200 flight cycles 

(for a visual inspection), or 7,500 flight cycles 

(for an eddy current inspection). 

(2) For airplanes on which Airbus 

Modification 7541/S7973 (reference Airbus 

Service Bulletin A310–57–2041) has been 

accomplished: Inspect at the time specified 

in the graph contained in NOTE 1 of 

paragraph 1.A.(2) of Airbus Service Bulletin 

A310–57–2039, dated September 24, 1990, or 

within 1,000 flight cycles after January 20, 

1999, whichever occurs later; and thereafter 

at intervals not to exceed 5,000 flight cycles 

(for a visual inspection), or 8,600 flight cycles 

(for an eddy current inspection). 

Exception to Certain Service Bulletin 

Repairs 

(m) If any crack is found during any 

inspection required by paragraph (g), (j), (k), 

or (l) of this AD, and the applicable service 

bulletin specifies to contact Airbus for an 

appropriate action: Prior to further flight, 

repair in accordance with a method approved 

by either the Manager, International Branch, 

ANM–116, or the DGAC (or its delegated 

agent), or EASA (or its delegated agent). 

New Requirements of This AD: Actions 

Actions for Service Bulletin A310–55–2004 

(n) For airplanes listed in Airbus 

Mandatory Service Bulletin A310–55–2004, 

Revision 05, dated October 13, 2006: At the 

applicable time specified in paragraph (n)(1) 

or (n)(2) of this AD, do a high frequency eddy 

current inspection for cracking of the doubler 

plate edge, the rear spar area, and specified 

fastener holes in the top skin chordwise 

splice along the contour of the steel doubler 

between ribs 3 and 4 on the left- and righthand center and side boxes on the horizontal 

stabilizer, in accordance with the 

Accomplishment Instructions of Airbus 

Mandatory Service Bulletin A310–55–2004, 

Revision 05, dated October 13, 2006. If any 

cracking is found, before further flight, repair 

in accordance with the Accomplishment 

Instructions of Airbus Mandatory Service 

Bulletin A310–55–2004, Revision 05, dated 

October 13, 2006; except where this 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, or 

EASA (or its delegated agent). Thereafter, 

repeat the inspections at intervals not to 

exceed 9,700 flight cycles or 19,500 flight 

hours, whichever occurs first; except as 

required by paragraph (o) of this AD for the 

rear spar area. 

Note 6: Airplanes on which Airbus 

Modification 06070 has been done in 

production are not affected by the actions 

specified in paragraph (l) of this AD. 

(1) For airplanes on which Airbus Service 

Bulletin A310–55–2002 was accomplished 

prior to the accumulation of 6,000 total flight 

cycles on the airplane; and for airplanes 

having MSN 311 through 400 inclusive on 

which Airbus Modification 4933 was 

accomplished during production: Do the 

inspection at the later of the compliance 

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

(l)(1)(ii) of this AD. 

(i) Prior to the accumulation of 14,400 total 

flight cycles or 28,500 total flight hours, 

whichever occurs first. 

(ii) Within 1,500 flight cycles or 18 months 

after the effective date of this AD, whichever 

occurs first. 

(2) For airplanes on which Airbus Service 

Bulletin A310–55–2002 was accomplished 

on or after the accumulation of 6,000 total 

flight cycles: Do the inspection at the later of 

the times specified in paragraphs (l)(2)(i) and 

(l)(2)(ii) of this AD. 

(i) Within 9,700 flight cycles or 19,500 

flight hours after accomplishing the 

modification, whichever occurs first. 

(ii) Within 1,500 flight cycles or 18 months 

after the effective date of this AD, whichever 

occurs first. 

(o) For airplanes on which the initial 

inspection required by paragraph (n) of this 

AD has been done and on which a repair was 

installed at fastener position A in accordance 

with Airbus Service Bulletin A310–55–2002: 

At the later of the times specified in 

paragraphs (o)(1) and (o)(2) of this AD, do a 

high frequency eddy current inspection for 

cracking of the rear spar area as specified in 

paragraph (n) of this AD, and repeat the high 

frequency eddy current inspection of the rear 

spar area thereafter at intervals not to exceed 

4,800 flight cycles or 9,700 flight hours, 

whichever occurs first. 

(1) Within 4,800 flight cycles or 9,700 

flight hours, whichever occurs first, after 

doing the repair in accordance with Airbus 

Service Bulletin A310–55–2002. 

(2) Within 400 flight cycles or 800 flight 

hours, whichever occurs first, after the 

effective date of this AD. 

Credit for Actions Accomplished in 

Accordance With Previous Service 

Information 

(p) Actions accomplished before the 

effective date of this AD in accordance with 

Airbus Service Bulletin A310–55–2004, 

Revision 2, dated February 7, 1991; Revision 

3, dated April 16, 1997; and Revision 04, 

dated April 17, 2001; are acceptable for 

compliance with the corresponding actions 

specified in paragraph (n) of this AD. 

FAA AD Differences 

Note 7: This AD differs from the MCAI 

and/or service information as follows: No 

Differences. 

Other FAA AD Provisions 

(q) 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 


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

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 

(r) Refer to MCAI EASA Airworthiness 

Directive 2007–0053R3, dated December 17, 

2009, and the service bulletins listed in Table 

1 of this AD, for related information. 

TABLE 1—RELATED SERVICE INFORMATION

Service bulletin Revision Date 

Airbus Mandatory Service Bulletin A310–55–2004 .................... 05 ............................................ October 13, 2006. 

Airbus Service Bulletin A310–53–2016 ...................................... 5 .............................................. December 7, 1992. 

Airbus Service Bulletin A310-53-2019 ........................................ 3 .............................................. February 28, 1991. 

Airbus Service Bulletin A310–53–2054 ...................................... 2 .............................................. May 22, 1990. 

Airbus Service Bulletin A310–53–2057 ...................................... 1 .............................................. April 30, 1992. 

Airbus Service Bulletin A310–53–2059 ...................................... 1 .............................................. January 4, 1996. 

Airbus Service Bulletin A310–55–2002 ...................................... 4 .............................................. April 28, 1989. 

Airbus Service Bulletin A310–57–2039 ...................................... Original .................................... September 24, 1990. 

Airbus Service Bulletin A310–57–2041 ...................................... Original .................................... September 24, 1990. 

Issued in Renton, Washington on 

December 17, 2010. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2010–32983 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–2010–1273; Directorate 

Identifier 2010–NM–089–AD] 

RIN 2120–AA64 

Airworthiness Directives; Airbus Model 

A310–203, –204, –222, –304, –322, and 

–324 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: 

A specific area, the lower tail plane cut-out 

located in the tail cone is subject to an 

inspection programme [for cracking] * * *. 

* * * * * 

The unsafe condition is reduced 

structural integrity of the tail cone. 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–2010–1273; Directorate Identifier 

2010–NM–089–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 2009–0058, 

dated March 13, 2009 (referred to after 

this as ‘‘the MCAI’’), to correct an unsafe 

condition for the specified products. 

The MCAI states: 


srobinson on DSKHWCL6B1PROD with PROPOSALS