This section of the FEDERAL REGISTER

contains notices to the public of the proposed

issuance of rules and regulations. The

purpose of these notices is to give interested

persons an opportunity to participate in the

rule making prior to the adoption of the final

rules.

Proposed Rules Federal Register

39863 

Vol. 75, No. 133 

Tuesday, July 13, 2010 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2010–0680; Directorate 

Identifier 2008–NM–195–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 an existing AD. 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: Analysis 

performed in the frame of the Extended 

Service Goal has led Airbus to modify 

the inspection programme [modification 

of thresholds, intervals and associated 

configurations] which is currently 

required by DGAC (Direction Ge ́ne ́rale 

de l’Aviation Civile) France AD F– 

2005–001. This modified inspection 

programme is necessary to detect and 

prevent damage associated with a 

structural fatigue phenomenon of the 

rear spar internal angle and the tee 

fitting located in the centre wing box. 

This condition, if not corrected, could 

affect the structural integrity of the 

centre wing box. 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 August 27, 2010. 

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, FAA, 

Transport Airplane Directorate, 1601 

Lind Avenue, SW., Renton, Washington 

98055–4056; 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–2010–0680; Directorate Identifier 

2008–NM–195–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 have lengthened the 30-day 

comment period for proposed ADs that 

address MCAI originated by aviation 

authorities of other countries to provide 

adequate time for interested parties to 

submit comments. The comment period 

for these proposed ADs is now typically 

45 days, which is consistent with the 

comment period for domestic transport 

ADs. 

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 April 20, 2006, we issued AD 

2006–09–05, Amendment 39–14575 (71 

FR 25921, May 3, 2006). That AD 

required actions intended to address an 

unsafe condition on the products listed 

above. 

Since we issued AD 2006–09–05, the 

manufacturer has modified the 

inspection program currently required 

by AD 2006–09–05 by reducing certain 

compliance times. The European 

Aviation Safety Agency (EASA), which 

is the Technical Agent for the Member 

States of the European Community, has 

issued EASA Airworthiness Directive 

2008–0187, dated October 10, 2008 

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

correct an unsafe condition for the 

specified products. The MCAI states: 

Analysis performed in the frame of the 

Extended Service Goal has led Airbus to 

modify the inspection programme 

[modification of thresholds, intervals and 

associated configurations] which is currently 

required by DGAC (Direction Ge ́ne ́rale de 

l’Aviation Civile) France AD F–2005–001 

[which corresponds to FAA AD 2006–09–05]. 

This modified inspection programme is 

necessary to detect and prevent damage 

associated with a structural fatigue 

phenomenon of the rear spar internal angle 

and the tee fitting located in the centre wing 

box. This condition, if not corrected, could 

affect the structural integrity of the centre 

wing box. 


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For the reason stated above, this new 

EASA AD retains the requirements of DGAC 

France AD F–2005–001, which is 

superseded, and refers to the latest revision 

of Airbus Service Bulletin (SB) A310–57– 

2047. 

The unsafe condition is reduced 

structural integrity of the wings. This 

AD retains the requirements of AD 

2006–09–05, but with certain reduced 

compliance times. The required actions 

include doing repetitive rotating probe 

inspections for any crack of the rear spar 

internal angle and the left and right 

sides of the tee fitting, and doing related 

investigative/corrective actions if 

necessary. The actions also include 

modifying the holes in the internal 

angle and tee fitting by cold expansion. 

You may obtain further information by 

examining the MCAI in the AD docket. 

Relevant Service Information 

Airbus has issued Service Bulletin 

A310–57–2047, Revision 08, dated July 

2, 2009; and Mandatory Service Bulletin 

A310–57–2035, Revision 10, dated 

March 25, 2008. 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 66 products of U.S. registry. 

The actions that are required by AD 

2006–09–05 and retained in this 

proposed AD take up to 600 work-hours 

per product, at an average labor rate of 

$85 per work hour. Required parts cost 

up to $38,900 per product. Based on 

these figures, the estimated cost of the 

currently required actions is up to 

$89,900 per product. 

This new AD adds no new costs to 

affected operators; the manufacturer has 

modified the inspection program 

currently required by AD 2006–09–05, 

this proposed AD reduces the 

compliance times required by the 

existing AD. 

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 

removing Amendment 39–14575 (71 FR 

25921, May 3, 2006) and adding the 

following new AD: 

Airbus: Docket No. FAA–2010–0680; 

Directorate Identifier 2008–NM–195–AD. 

Comments Due Date 

(a) We must receive comments by August 

27, 2010. 

Affected ADs 

(b) This AD supersedes AD 2006–09–05, 

Amendment 39–14575. This AD also affects 

certain requirements of AD 98–26–01, 

Amendment 39–10942. 

Applicability 

(c) This AD applies to all Airbus Model 

A310–203, –204, –221, –222, –304, –322, 

–324, and –325 airplanes, certificated in any 

category. 

Subject 

(d) Air Transport Association (ATA) of 

America Code 57: Wings. 

Reason 

(e) The mandatory continuing 

airworthiness information (MCAI) states: 

Analysis performed in the frame of the 

Extended Service Goal has led Airbus to 

modify the inspection programme 

[modification of thresholds, intervals and 

associated configurations] which is currently 

required by DGAC (Direction Ge ́ne ́rale de 

l’Aviation Civile) France AD F–2005–001 

[which corresponds to FAA AD 2006–09–05]. 

This modified inspection programme is 

necessary to detect and prevent damage 

associated with a structural fatigue 

phenomenon of the rear spar internal angle 

and the tee fitting located in the centre wing 

box. This condition, if not corrected, could 

affect the structural integrity of the centre 

wing box. 

The unsafe condition is reduced structural 

integrity of the wings. 


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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 2006–09–05 

MODIFICATION 

(g) For all airplanes except those that are 

modified by Airbus Modifications 

06672S6812, 06673S6813, and 07387S7974 

in production: Within 60 months after June 

7, 2006 (the effective date of AD 2006–09– 

05), modify the holes in the internal angle 

and tee fitting and do all applicable related 

investigative and corrective actions by 

accomplishing all the actions specified in the 

Accomplishment Instructions of Airbus 

Service Bulletin A310–57–2035, Revision 08, 

dated September 19, 2005; or Airbus 

Mandatory Service Bulletin A310–57–2035, 

Revision 10, dated March 25, 2008; except as 

required by paragraph (h) of this AD. Do all 

applicable related investigative and 

corrective actions before further flight. As of 

the effective date of this AD, use only Airbus 

Mandatory Service Bulletin A310–57–2035, 

Revision 10, dated March 25, 2008. 

Contact the FAA 

(h) Where the service information specified 

in Table 1 of this AD specifies to contact the 

manufacturer if certain cracks are found, 

before further flight, repair those conditions 

according to a method approved by either the 

Manager, International Branch, ANM–116, 

Transport Airplane Directorate, FAA; or the 

Direction Ge ́ne ́rale de l’Aviation Civile 

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

its delegated agent). 

TABLE 1—SERVICE INFORMATION

Document Revision Date 

Airbus Mandatory Service Bulletin A310–57–2035 ......................................................................................... 10 March 25, 2008. 

Airbus Service Bulletin A310–57–2035 ........................................................................................................... 08 September 19, 2005. 

Actions Accomplished According to 

Previous Issues of Airbus Service Bulletin 

A310–57–2035 

(i) Actions accomplished before June 7, 

2006, in accordance with the service 

information specified in Table 2 of this AD, 

are considered acceptable for compliance 

with the corresponding actions specified in 

paragraph (g) of this AD. 

TABLE 2—PREVIOUS ISSUES OF SERVICE BULLETIN A310–57–2035 

Document Revision Date 

Airbus Service Bulletin A310–57–2035 ........................................................................................................... 1 October 13, 1989. 

Airbus Service Bulletin A310–57–2035 ........................................................................................................... 2 February 26, 1990. 

Airbus Service Bulletin A310–57–2035 ........................................................................................................... 3 May 23, 1990. 

Airbus Service Bulletin A310–57–2035 ........................................................................................................... 4 April 15, 1992. 

Airbus Service Bulletin A310–57–2035 ........................................................................................................... 5 May 27, 1992. 

Airbus Service Bulletin A310–57–2035 ........................................................................................................... 6 March 8, 1994. 

Airbus Service Bulletin A310–57–2035 ........................................................................................................... 7 April 17, 1996. 

NEW REQUIREMENTS OF THIS AD— 

REVISED COMPLIANCE TIMES FOR 

INSPECTIONS REQUIRED BY AD 2006–09– 

05 

Initial and Repetitive Inspections of the Rear 

Spar Internal Angle 

(j) For airplanes on which an inspection of 

the rear spar internal angle has not been done 

in accordance with Airbus Service Bulletin 

A310–57–2047 as of the effective date of this 

AD: At the later of the times specified in 

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

rotating probe inspection for any crack of the 

rear spar internal angle located in the center 

wing box and do all applicable related 

investigative and corrective actions, in 

accordance with the Accomplishment 

Instructions of Airbus Service Bulletin A310– 

57–2047, Revision 08, dated July 2, 2009; 

except as required by paragraphs (n) and (o) 

of this AD. Do all applicable related 

investigative and corrective actions before 

further flight. Repeat the inspection 

thereafter at the applicable time specified in 

Table 4 of this AD. Certain compliance times 

are applicable to short range use, average 

flight time (AFT) equal to or less than 4 

hours, or long range use, AFT exceeding 4 

hours. 

Note 1: To establish the AFT, divide the 

accumulated flight time (counted from the 

take-off up to the landing) by the number of 

accumulated flight cycles. This gives the 

average flight time per flight cycle. 

(1) Within the applicable time specified in 

Table 3 of this AD. 

(2) Within the applicable time specified in 

paragraph (j)(2)(i), (j)(2)(ii), or (j)(2)(iii) of this 

AD: 

(i) For A310–203, –204, –221, and –222 

airplanes: Within 700 flight cycles or 1,500 

flight hours after the effective date of this AD, 

whichever occurs first. 

(ii) For A310–304, –322, –324, and –325 

short range airplanes: Within 700 flight 

cycles or 1,900 flight hours after the effective 

date of this AD, whichever occurs first. 

(iii) For A310–304, –322, –324, and –325 

long range airplanes: Within 500 flight cycles 

or 2,500 flight hours after the effective date 

of this AD, whichever occurs first. 

TABLE 3—INITIAL INSPECTION INTERNAL ANGLE

Model and configuration Compliance time (whichever occurs first) 

A310–203, –204, –221, and –222 airplanes on 

which Mod 6672S6812 and Mod 7387S7974 

are not done.

Before the accumulation of 9,200 total flight 

cycles.

Before the accumulation of 18,500 total flight 

hours. 

A310–203, –204, –221, and –222 airplanes on 

which Mod 6672S6812 and Mod 7387S7974 

are done in production.

Before the accumulation of 19,800 total flight 

cycles.

Before the accumulation of 39,600 total flight 

hours. 


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TABLE 3—INITIAL INSPECTION INTERNAL ANGLE—Continued 

A310–203, –204, –221, and –222 airplanes on 

which Mod 6672S6812 and Mod 7387S7974 

are done in accordance with Airbus Service 

Bulletin A310–57–2035 and before the accumulation of 6,200 total flight cycles and 

12,500 total flight hours.

Within 19,800 flight cycles after the effective 

date of this AD.

Within 39,600 flight hours after the effective 

date of this AD. 

A310–203, –204, –221, and –222 airplanes on 

which Mod 6672S6812 and Mod 7387S7974 

are done in accordance with Airbus Service 

Bulletin A310–57–2035 and are not done before the accumulation of 6,200 total flight cycles and 12,500 total flight hours.

Within 8,200 flight cycles after the effective 

date of this AD.

Within 16,400 flight hours after the effective 

date of this AD. 

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

airplanes on which Mod 6672S6812 and Mod 

7387S7974 are not done.

Before the accumulation of 7,500 total flight 

cycles.

Before the accumulation of 21,100 total flight 

hours. 

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

airplanes on which Mod 6672S6812 and Mod 

7387S7974 are not done.

Before the accumulation of 5,300 total flight 

cycles.

Before the accumulation of 26,900 total flight 

hours. 

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

airplanes on which Mod 6672S6812 and Mod 

7387S7974 are done.

Before the accumulation of 15,900 total flight 

cycles.

Before the accumulation of 44,700 total flight 

hours. 

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

airplanes on which Mod 6672S6812 and Mod 

7387S7974 are done in production.

Before the accumulation of 11,300 total flight 

cycles.

Before the accumulation of 56,900 total flight 

hours. 

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

airplanes on which Mod 6672S6812 and Mod 

7387S7974 are done in accordance with Airbus Service Bulletin A310–57–2035 and before the accumulation of 4,700 total flight cycles and 13,100 total flight hours.

Within 15,900 flight cycles after the effective 

date of this AD.

Within 44,700 flight hours after the effective 

date of this AD. 

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

airplanes on which Mod 6672S6812 and Mod 

7387S7974 are done in accordance with Airbus Service Bulletin A310–57–2035 and not 

done before the accumulation of 4,700 total 

flight cycles and 13,100 total flight hours.

Within 8,500 flight cycles after the effective 

date of this AD.

Within 23,800 flight hours after the effective 

date of this AD. 

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

airplanes on which Mod 6672S6812 and Mod 

7387S7974 are done in accordance with Airbus Service Bulletin A310–57–2035 before 

the accumulation of 3,300 total flight cycles 

and 16,700 total flight hours.

Within 11,300 flight cycles after the effective 

date of this AD.

Within 56,900 flight hours after the effective 

date of this AD. 

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

airplanes on which Mod 6672S6812 and Mod 

7387S7974 are done in accordance with Airbus Service Bulletin A310–57–2035 and not 

done before the accumulation of 3,300 total 

flight cycles and 16,700 total flight hours.

Within 6,000 flight cycles after the effective 

date of this AD.

Within 30,300 flight hours after the effective 

date of this AD. 

TABLE 4—REPETITIVE INTERVALS

Model and configuration Interval (not to exceed) 

A310–203, –204, –221, and –222 airplanes ............................ Within 7,200 flight cycles or 14,400 flight hours, whichever occurs first. 

A310–304, –322, –324, and –325 short range airplanes ........ Within 6,800 flight cycles or 19,100 flight hours, whichever occurs first. 

A310–304, –322, –324, and –325 long range airplanes ......... Within 4,800 flight cycles or 24,300 flight hours, whichever occurs first. 

(k) For airplanes on which an inspection of 

the rear spar internal angle has been done in 

accordance with Airbus Service Bulletin 

A310–57–2047 as of the effective date of this 

AD: At the applicable time specified in 

paragraphs (k)(1), (k)(2), and (k)(3) of this AD, 

do a rotating probe inspection for any crack 

of the rear spar internal angle located in the 

center wing box and do all applicable related 

investigative and corrective actions, in 

accordance with the Accomplishment 

Instructions of Airbus Service Bulletin A310– 

57–2047, Revision 08, dated July 2, 2009; 

except as required by paragraphs (n) and (o) 

of this AD. Do all applicable related 

investigative and corrective actions before 

further flight. Repeat the inspection 

thereafter at the applicable time specified in 

Table 4 of this AD. Certain compliance times 

are applicable to short range use, AFT equal 

to or less than 4 hours, or long range use, 

AFT exceeding 4 hours. 

(1) For A310–203, –204, –221, and –222 

airplanes: At the earlier of the times specified 

in paragraphs (k)(1)(i) and (k)(1)(ii) of this 

AD. 

(i) Within 7,940 flight cycles or 15,880 

flight hours after the most recent inspection, 

whichever occurs first. 

(ii) At the later of the times specified in 

paragraphs (k)(1)(ii)(A) and (k)(1)(ii)(B) of 

this AD. 

(A) Within the applicable interval specified 

in Table 4 of this AD. 

(B) Within 740 flight cycles or 1,480 flight 

hours after the effective date of this AD, 

whichever occurs first. 

(2) For A310–304, –322, –324, and –325 

short range airplanes: At the later of the times 


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specified in paragraphs (k)(2)(i) and (k)(2)(ii) 

of this AD. 

(i) Within the applicable interval specified 

in Table 4 of this AD. 

(ii) Within 700 flight cycles or 1,900 flight 

hours after the effective date of this AD, 

whichever occurs first. 

(3) For A310–304, –322, –324, and –325 

long range airplanes: At the later of the times 

specified in paragraphs (k)(3)(i) and (k)(3)(ii) 

of this AD. 

(i) Within the applicable interval specified 

in Table 4 of this AD. 

(ii) Within 500 flight cycles or 2,500 flight 

hours after the effective date of this AD, 

whichever occurs first. 

Initial and Repetitive Inspections of the Tee 

Fitting 

(l) For airplanes on which an inspection of 

the left and right sides of the tee fitting has 

not been done in accordance with Airbus 

Service Bulletin A310–57–2047 as of the 

effective date of this AD: At the later of the 

times specified in paragraphs (l)(1) and (l)(2) 

of this AD, do a rotating probe inspection for 

any crack of the left and right sides of the tee 

fitting, and do all applicable related 

investigative and corrective actions, in 

accordance with the Accomplishment 

Instructions of Airbus Service Bulletin A310– 

57–2047, Revision 08, dated July 2, 2009; 

except as required by paragraphs (n) and (o) 

of this AD. Do all applicable related 

investigative and corrective actions before 

further flight. Repeat the inspection 

thereafter at the applicable time specified in 

Table 6 of this AD. Certain compliance times 

are applicable to short range use, AFT equal 

to or less than 4 hours, or long range use, 

AFT exceeding 4 hours. 

(1) Within the applicable time specified in 

Table 5 of this AD. 

(2) Within the applicable time in paragraph 

(l)(2)(i), (l)(2)(ii), or (l)(2)(iii) of this AD. 

(i) For A310–203, –204, –221, and –222 

airplanes: Within 800 flight cycles or 1,600 

flight hours, whichever occurs first. 

(ii) For A310–304, –322, –324, and –325 

short range airplanes: Within 800 flight 

cycles or 2,200 flight hours, whichever 

occurs first. 

(iii) For A310–304, –322, –324, and –325 

long range airplanes: Within 600 flight cycles 

or 3,100 flight hours, whichever occurs first. 

TABLE 5—INITIAL INSPECTION TEE FITTING

Model and configuration Compliance time (whichever occurs first) 

A310–203, –204, –221, and –222 airplanes on 

which Mod 6673S6813 is not done.

Before the accumulation of 14,300 flight cycles.Within 28,700 flight hours after the effective 

date of this AD. 

A310–203, –204, –221, and –222 airplanes on 

which Mod 6673S6813 is done in production.

Before the accumulation of 17,500 total flight 

cycles.

Before the accumulation of 35,000 total flight 

hours. 

A310–203, –204, –221, and –222 airplanes on 

which Mod 6673S6813 is done in accordance 

with Airbus Service Bulletin A310–57–2035 

and before the accumulation of 8,100 total 

flight cycles and 16,200 total flight hours.

Within 17,500 flight cycles after the effective 

date of this AD.

Within 35,000 flight hours after the effective 

date of this AD. 

A310–203, –204, –221, and –222 airplanes on 

which Mod 6673S6813 is done in accordance 

with Airbus Service Bulletin A310–57–2035 

and not before the accumulation of 8,100 

total flight cycles and 16,200 total flight hours.

Within 9,600 flight cycles after the effective 

date of this AD.

Within 19,200 flight hours after the effective 

date of this AD. 

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

airplanes on which Mod 6673S6813 is not 

done.

Within 10,800 flight cycles after the effective 

date of this AD.

Within 30,400 flight hours after the effective 

date of this AD. 

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

airplanes on which Mod 6673S6813 is not 

done.

Before the accumulation of 8,500 total flight 

cycles.

Before the accumulation of 42,800 total flight 

hours. 

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

airplanes on which Mod 6673S6813 is done 

in production.

Before the accumulation of 13,100 total flight 

cycles.

Before the accumulation of 36,700 total flight 

hours. 

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

airplanes on which Mod 6673S6813 is done 

in production.

Before the accumulation of 10,300 total flight 

cycles.

Before the accumulation of 51,600 total flight 

hours. 

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

airplanes on which Mod 6673S6813 is done 

in accordance with Airbus Service Bulletin 

A310–57–2035 and before the accumulation 

of 5,800 total flight cycles and 16,400 total 

flight hours.

Within 13,100 flight cycles after the effective 

date of this AD.

Within 36,700 flight hours after the effective 

date of this AD. 

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

airplanes on which Mod 6673S6813 is done 

in accordance with Airbus Service Bulletin 

A310–57–2035 and not before the accumulation of 5,800 total flight cycles and 16,400 

total flight hours.

Within 7,400 flight cycles after the effective 

date of this AD.

Within 20,900 flight hours after the effective 

date of this AD. 

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

airplanes on which Mod 6673S6813 is done 

in accordance with Airbus Service Bulletin 

A310–57–2035 and before the accumulation 

of 4,600 total flight cycles and 23,100 total 

flight hours.

Within 10,300 flight cycles after the effective 

date of this AD.

Within 51,600 flight hours after the effective 

date of this AD. 

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

airplanes on which Mod 6673S6813 is done 

in accordance with Airbus Service Bulletin 

A310–57–2035 and not before the accumulation of 4,600 total flight cycles and 23,100 

total flight hours.

Within 6,000 flight cycles after the effective 

date of this AD.

Within 30,300 flight hours after the effective 

date of this AD. 


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39868 Federal Register / Vol. 75, No. 133 / Tuesday, July 13, 2010 / Proposed Rules 

TABLE 6—REPETITIVE INTERVALS

Model and configuration Interval (not to exceed) 

A310–203, –204, –221, and –222 airplanes ............................................ 9,100 flight cycles or 18,300 flight hours, whichever occurs first. 

A310–304, –322, –324, and –325 short range airplanes ........................ 7,300 flight cycles or 20,400 flight hours, whichever occurs first. 

A310–304, –322, –324, and –325 long range airplanes ......................... 5,900 flight cycles or 29,600 flight hours, whichever occurs first 

(m) For airplanes on which an inspection 

of the rear left and right sides of the tee 

fitting has been done in accordance with 

Airbus Service Bulletin A310–57–2047 as of 

the effective date of this AD: At the 

applicable time specified in paragraphs 

(m)(1) or (m)(2) of this AD, do a rotating 

probe inspection for any crack of the left and 

right sides of the tee fitting, and do all 

applicable related investigative and 

corrective actions, in accordance with the 

Accomplishment Instructions of Airbus 

Service Bulletin A310–57–2047, Revision 08, 

dated July 2, 2009; except as required by 

paragraphs (n) and (o) of this AD. Do all 

applicable related investigative and 

corrective actions before further flight. 

Repeat the inspection thereafter at the 

applicable time specified in Table 6 of this 

AD. Certain compliance times are applicable 

to short range use, AFT equal to or less than 

4 hours, or long range use, AFT exceeding 4 

hours. 

(1) For A310–203, –204, –221, and –222 

airplanes: At the earlier of the times specified 

in paragraphs (m)(1)(i) and (m)(1)(ii) of this 

AD. 

(i) Within 10,800 flight cycles or 17,400 

flight hours after the most recent inspection, 

whichever occurs first. 

(ii) At the later of the times specified in 

paragraphs (m)(1)(ii)(A) and (m)(1)(ii)(B) of 

this AD. 

(A) Within the applicable interval specified 

in Table 6 of this AD. 

(B) Within 700 flight cycles or 1,500 flight 

hours after the effective date of this AD, 

whichever occurs first. 

(2) For A310–304, –322, –324, and –325 

airplanes: At the later of the times specified 

in paragraphs (m)(2)(i) and (m)(2)(ii) of this 

AD. 

(i) Within the applicable interval specified 

in Table 6 of this AD. 

(ii) Within 700 flight cycles or 1,900 flight 

hours after the effective date of this AD, 

whichever occurs first. 

Contact the FAA 

(n) Where Airbus Service Bulletin A310– 

57–2047, Revision 08, dated July 2, 2009, 

specifies to contact the manufacturer if 

certain cracks are found, before further flight, 

repair those conditions according to a 

method approved by either the Manager, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA; or EASA (or its 

delegated agent). 

No Reporting Required 

(o) Although Airbus Service Bulletin 

A310–57–2047, Revision 06, dated July 13, 

2004; and Revision 08, dated July 2, 2009; 

specify to submit certain information to the 

manufacturer, this AD does not include that 

requirement. 

(p) Actions accomplished before the 

effective date of this AD in accordance with 

Airbus Mandatory Service Bulletin A310–57– 

2035, Revision 09, dated September 27, 2007, 

are considered acceptable for compliance 

with the corresponding actions specified in 

paragraph (g) of this AD. 

(q) Actions accomplished before the 

effective date of this AD in accordance with 

the service information specified in Table 7 

of this AD, are considered acceptable for 

compliance with the corresponding actions 

specified in paragraphs (j) through (m) of this 

AD. 

TABLE 7—PREVIOUS ISSUES OF SERVICE BULLETIN A310–57–2047 

Document Revision Date 

Airbus Service Bulletin A310-57-2047 ......................................................................................................... 03 November 26, 1997. 

Airbus Service Bulletin A310–57–2047 ....................................................................................................... 04 March 5, 1999. 

Airbus Service Bulletin A310–57–2047 ....................................................................................................... 05 August 3, 2000. 

Airbus Service Bulletin A310–57–2047 ....................................................................................................... 06 July 13, 2004. 

Airbus Service Bulletin A310–57–2047 ....................................................................................................... 07 March 14, 2008. 

Related AD 

(r) Accomplishing a rotating probe 

inspection of the rear spar internal angle and 

the tee fitting in accordance with Airbus 

Service Bulletin A310–57–2047, Revision 08, 

dated July 2, 2009, or a service bulletin listed 

in Table 7 of this AD, terminates the 

requirements specified in paragraph (o) of 

AD 98–26–01. 

FAA AD Differences 

Note 2: This AD differs from the MCAI 

and/or service information as follows: 

Although the MCAI or service information 

tells you to contact the manufacturer for 

repair information, paragraph (n) of this AD 

requires that you contact the FAA or EASA 

(or its delegated agent) instead. Although the 

MCAI or service information tells you to 

submit information to the manufacturer, 

paragraph (o) of this AD specifies that such 

submittal is not required. 

Other FAA AD Provisions 

(s) 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, FAA, Transport Airplane 

Directorate, 1601 Lind Avenue, SW., Renton, 

Washington 98055–4056; 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) AMOCs approved previously in 

accordance with AD 2006–09–05, 

Amendment 39–14575, are approved as 

AMOCs for the corresponding provisions of 

this AD. 

(3) 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 FAAapproved if they are approved by the State 

of Design Authority (or their delegated 

agent). You are required to assure the product 

is airworthy before it is returned to service. 

Related Information 

(t) Refer to MCAI EASA Airworthiness 

Directive 2008–0187, dated October 10, 2008; 

and Airbus Service Bulletins A310–57–2047, 

Revision 08, dated July 2, 2009; and Airbus 

Mandatory Service Bulletin A310–57–2035, 

Revision 10, dated March 25, 2008; for 

related information. 

Issued in Renton, Washington, on June 30, 

2010. 

Todd G. Dixon, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2010–17061 Filed 7–12–10; 8:45 am] 

BILLING CODE 4910–13–P 


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