27232 Federal Register / Vol. 76, No. 91 / Wednesday, May 11, 2011 / Rules and Regulations 

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. 

In accordance with 14 CFR 39.19, send your 

request to your principal inspector or local 

Flight Standards District Office, as 

appropriate, or if sending information 

directly to the International Branch, send it 

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. Information may be e-mailed to: 

9-ANM-116-AMOC-Requests@faa.gov. Before 

using any approved AMOC, notify your 

principal inspector, or lacking a principal 

inspector, the manager of the local flight 

standards district office/certificate holding 

district office. The AMOC approval letter 

must specifically reference this AD. 

(2) Airworthy Product: For any requirement 

in this AD to obtain corrective actions from 

a manufacturer or other source, use these 

actions if they are FAA-approved. Corrective 

actions are considered FAA-approved if they 

are approved by the State of Design Authority 

(or their delegated agent). You are required 

to assure the product is airworthy before it 

is returned to service. 

Related Information 

(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 A310–57–2050 ........................................................................................... 02 August 27, 2009. 

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

Material Incorporated by Reference 

(q) You must use the applicable service 

information contained in Table 7 of this AD 

to do the actions required by this AD, unless 

the AD specifies otherwise. 

TABLE 7—ALL MATERIAL INCORPORATED BY REFERENCE

Service Bulletin Revision Date 

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

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

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

(1) The Director of the Federal Register 

approved the incorporation by reference of 

the service information under 5 U.S.C. 552(a) 

and 1 CFR part 51. 

(2) For service information identified in 

this AD, contact Airbus SAS—EAW 

(Airworthiness Office), 1 Rond Point Maurice 

Bellonte, 31707 Blagnac Cedex, France; 

telephone +33 5 61 93 36 96; fax +33 5 61 

93 44 51; e-mail account.airwortheas@airbus.com; Internet http:// 

www.airbus.com. 

(3) You may review copies of the service 

information at the FAA, Transport Airplane 

Directorate, 1601 Lind Avenue, SW., Renton, 

Washington. For information on the 

availability of this material at the FAA, call 

425–227–1221. 

(4) You may also review copies of the 

service information that is incorporated by 

reference at the National Archives and 

Records Administration (NARA). For 

information on the availability of this 

material at NARA, call 202–741–6030, or go 

to: http://www.archives.gov/federal_register/ 

code_of_federal_regulations/ 

ibr_locations.html. 

Issued in Renton, Washington, on April 22, 

2011. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2011–10685 Filed 5–10–11; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2010–1276; Directorate 

Identifier 2010–NM–092–AD; Amendment 

39–16689; AD 2011–10–08] 

RIN 2120–AA64 

Airworthiness Directives; Airbus Model 

A310 Series Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for the 

products listed above that would 

supersede two existing ADs. This AD 

results from mandatory continuing 

airworthiness information (MCAI) 

originated by an aviation authority of 

another country to identify and correct 

an unsafe condition on an aviation 

product. The MCAI describes the unsafe 

condition as: 

DGAC [Direction Ge ́ne ́rale de l’Aviation 

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

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. We are issuing 

this AD to require actions to correct the 

unsafe condition on these products. 

DATES: This AD becomes effective June 

15, 2011. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of June 15, 2011. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain other publications listed in 

this AD as of January 20, 1999 (63 FR 

69179, December 16, 1998). 

ADDRESSES: You may examine the AD 

docket on the Internet at http:// 

www.regulations.gov or in person at the 

U.S. Department of Transportation, 

Docket Operations, M–30, West 

Building Ground Floor, Room W12–140, 

1200 New Jersey Avenue, SE., 

Washington, DC. 


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FOR FURTHER INFORMATION CONTACT: 

Dan Rodina, Aerospace Engineer, 

International Branch, ANM–116, 

Transport Airplane Directorate, FAA, 

1601 Lind Avenue, SW., Renton, 

Washington 98057–3356; telephone 

(425) 227–2125; fax (425) 227–1149. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to include an AD that would 

apply to the specified products. That 

NPRM was published in the Federal 

Register on January 3, 2011 (76 FR 42), 

and proposed to supersede AD 98–26– 

01, Amendment 39–10942 (63 FR 

69179, December 16, 1998), and AD 91– 

13–01, Amendment 39–7032 (56 FR 

26602, June 10, 1991). 

The NPRM proposed to correct an 

unsafe condition for the specified 

products. The MCAI states: 

DGAC [Direction Ge ́ne ́rale de l’Aviation 

Civile] France AD 1992–106–132(B) original 

issue up to revision 7 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 proposed to continue to 

require certain actions specified in AD 

98–26–01. 

The NPRM also proposed to expand 

the inspection area of the high 

frequency eddy current rototest 

inspection 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. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

received no comments on the NPRM or 

on the determination of the cost to the 

public. 

Conclusion 

We reviewed the available data and 

determined that air safety and the 

public interest require adopting the AD 

as proposed. 

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 required different 

actions in this AD from those in the 

MCAI in order to follow our FAA 

policies. Any such differences are 

highlighted in a NOTE within the AD. 

Costs of Compliance 

We estimate that this AD will affect 

44 products of U.S. registry. The actions 

that are required by AD 98–26–01 and 

are retained in this 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 also estimate that it will take 

about 3 work-hours per product to 

comply with the basic requirements of 

this AD. The average labor rate is $85 

per work-hour. Based on these figures, 

we estimate the cost of this AD to the 

U.S. operators to be $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 AD will not 

have federalism implications under 

Executive Order 13132. This AD will 

not have a substantial direct effect on 


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the States, on the relationship between 

the national government and the States, 

or on the distribution of power and 

responsibilities among the various 

levels of government. 

For the reasons discussed above, I 

certify this AD: 

1. Is not a ’’significant regulatory 

action’’ under Executive Order 12866; 

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

DOT Regulatory Policies and Procedures 

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

3. Will not have a significant 

economic impact, positive or negative, 

on a substantial number of small entities 

under the criteria of the Regulatory 

Flexibility Act. 

We prepared a regulatory evaluation 

of the estimated costs to comply with 

this AD and placed it in the AD docket. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http:// 

www.regulations.gov; or in person at the 

Docket Operations office between 9 a.m. 

and 5 p.m., Monday through Friday, 

except Federal holidays. The AD docket 

contains the NPRM, the regulatory 

evaluation, any comments received, and 

other information. The street address for 

the Docket Operations office (telephone 

(800) 647–5527) is in the ADDRESSES

section. Comments will be available in 

the AD docket shortly after receipt. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety. 

Adoption of the Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA amends 14 CFR part 39 as 

follows: 

PART 39—AIRWORTHINESS 

DIRECTIVES 

■ 1. The authority citation for part 39 

continues to read as follows: 

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

§ 39.13 [Amended] 

■ 2. The FAA amends § 39.13 by 

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: 

2011–10–08 Airbus: Amendment 39–16689. 

Docket No. FAA–2010–1276; Directorate 

Identifier 2010–NM–092–AD. 

Effective Date 

(a) This airworthiness directive (AD) 

becomes effective June 15, 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) * * * 

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. 


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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 

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 European Aviation Safety Agency 

(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 paragraph (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. 


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27236 Federal Register / Vol. 76, No. 91 / Wednesday, May 11, 2011 / Rules and Regulations 

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. 

In accordance with 14 CFR 39.19, send your 

request to your principal inspector or local 

Flight Standards District Office, as 

appropriate. If sending information directly 

to the International Branch, send it to ATTN: 

Dan Rodina, Aerospace Engineer, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA, 1601 Lind 

Avenue, SW., Renton, Washington 98057– 

3356; telephone (425) 227–2125; fax (425) 

227–1149. Information may be e-mailed to: 

9-ANM-116-AMOC-Requests@faa.gov. Before 

using any approved AMOC, notify your 

principal inspector or lacking a principal 

inspector, the manager of the local flight 

standards district office/certificate holding 

district office. The AMOC approval letter 

must specifically reference this AD. AMOCs 

approved previously in accordance with AD 

98–26–01, amendment 39–10942, are 

approved as AMOCs for the corresponding 

provisions of this AD. 

(2) Airworthy Product: For any requirement 

in this AD to obtain corrective actions from 

a manufacturer or other source, use these 

actions if they are FAA-approved. Corrective 

actions are considered FAA-approved if they 

are approved by the State of Design Authority 

(or their delegated agent). You are required 

to assure the product is airworthy before it 

is returned to service. 

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 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. 

Material Incorporated by Reference 

(s) You must use the applicable service 

bulletins contained in Table 2 of this AD, to 

do the actions required by this AD, unless the 

AD specifies otherwise. 

TABLE 2—ALL MATERIAL INCORPORATED BY REFERENCE

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. 

Note 8: Only pages 1 and 6 of Airbus 

Service Bulletin A310–53–2019, Revision 3, 

dated February 28, 1991, show revision level 

3 and issue date February 28, 1991. All other 

pages of this document show the original 

issue date of February 8, 1985. 

(1) The Director of the Federal Register 

approved the incorporation by reference of 

the service information contained in Table 3 

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

part 51. 

TABLE 3—NEW MATERIAL INCORPORATED BY REFERENCE

Service Bulletin Revision Date 

Airbus Mandatory Service Bulletin A310–55–2004, excluding Appendix 01 .................................. 05 .............................. October 13, 2006. 

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

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

Note 9: Only pages 1 and 6 of Airbus 

Service Bulletin A310–53–2019, Revision 3, 

dated February 28, 1991, show revision level 

3 and issue date February 28, 1991. All other 

pages of this document show the original 

issue date of February 8, 1985. 


srobinson on DSKHWCL6B1PROD with RULES
Federal Register / Vol. 76, No. 91 / Wednesday, May 11, 2011 / Rules and Regulations 27237 

(2) The Director of the Federal Register 

previously approved the incorporation by 

reference of the service information 

contained in Table 4 of this AD on January 

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

TABLE 4—MATERIAL PREVIOUSLY INCORPORATED BY REFERENCE

Service Bulletin Revision Date 

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

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. 

(3) For service information identified in 

this AD, contact Airbus SAS—EAW 

(Airworthiness Office), 1 Rond Point Maurice 

Bellonte, 31707 Blagnac Cedex, France; 

telephone +33 5 61 93 36 96; fax +33 5 61 

93 44 51; e-mail account.airwortheas@airbus.com; Internet http:// 

www.airbus.com. 

(4) You may review copies of the service 

information at the FAA, Transport Airplane 

Directorate, 1601 Lind Avenue, SW., Renton, 

Washington. For information on the 

availability of this material at the FAA, call 

425–227–1221. 

(5) You may also review copies of the 

service information that is incorporated by 

reference at the National Archives and 

Records Administration (NARA). For 

information on the availability of this 

material at NARA, call 202–741–6030, or go 

to: http://www.archives.gov/federal_register/ 

code_of_federal_regulations/ 

ibr_locations.html. 

Issued in Renton, Washington, on April 22, 

2011. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2011–10687 Filed 5–10–11; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2011–0038; Directorate 

Identifier 2010–NM–153–AD; Amendment 

39–16684; AD 2011–10–03] 

RIN 2120–AA64 

Airworthiness Directives; Empresa 

Brasileira de Aeronautica S.A. 

(EMBRAER) Model ERJ 170 Airplanes; 

and Model ERJ 190–100 STD, ERJ 190– 

100 LR, ERJ 190–100 IGW, ERJ 190– 

200 STD, ERJ 190–200 LR, and ERJ 

190–200 IGW Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for the 

products listed above. This AD results 

from mandatory continuing 

airworthiness information (MCAI) 

originated by an aviation authority of 

another country to identify and correct 

an unsafe condition on an aviation 

product. The MCAI describes the unsafe 

condition as: 

[T]he occurrence of drill marks [has been 

found] at the lower ring region of the rear 

pressure bulkhead between [the] 

circumferential splice joint and rear skin 

located between stringers 12 and 13. These 

marks may result in formation of fatigue 

cracks accelerated by corrosion reducing the 

structural strength of the rear pressure 

bulkhead, which may cause a sudden 

decompression of the passenger cabin. 

* * * * * 

We are issuing this AD to require 

actions to correct the unsafe condition 

on these products. 

DATES: This AD becomes effective June 

15, 2011. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of June 15, 2011. 

ADDRESSES: You may examine the AD 

docket on the Internet at http:// 

www.regulations.gov or in person at the 

U.S. Department of Transportation, 

Docket Operations, M–30, West 

Building Ground Floor, Room W12–140, 

1200 New Jersey Avenue, SE., 

Washington, DC. 

FOR FURTHER INFORMATION CONTACT: 

Cindy Ashforth, Aerospace Engineer, 

International Branch, ANM–116, 

Transport Airplane Directorate, FAA, 

1601 Lind Avenue, SW., Renton, 

Washington 98057–3356; telephone 

425–227–2768; fax 425–227–1149. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to include an AD that would 

apply to the specified products. That 

NPRM was published in the Federal 

Register on February 10, 2011 (76 FR 

7511). That NPRM proposed to correct 

an unsafe condition for the specified 

products. The MCAI states: 

[T]he occurrence of drill marks [has been 

found] at the lower ring region of the rear 

pressure bulkhead between [the] 

circumferential splice joint and rear skin 

located between stringers 12 and 13. These 

marks may result in formation of fatigue 

cracks accelerated by corrosion reducing the 

structural strength of the rear pressure 

bulkhead, which may cause a sudden 

decompression of the passenger cabin. 

* * * * * 

The required actions include doing a 

detailed inspection for signs of drill 

marks and repairing if necessary. You 

may obtain further information by 

examining the MCAI in the AD docket. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

received no comments on the NPRM or 

on the determination of the cost to the 

public. 

Conclusion 

We reviewed the available data and 

determined that air safety and the 

public interest require adopting the AD 

as proposed. 

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 required different 

actions in this AD from those in the 

MCAI in order to follow our FAA 

policies. Any such differences are 

highlighted in a NOTE within the AD. 


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