## 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.



### T ABLE 

### 6—S ERVICE 

### I NFORMATION

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.



### T ABLE 

### 7—A LL 

### M ATERIAL 

### I NCORPORATED BY 

### R EFERENCE

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.


## 27233 Federal Register / Vol. 76, No. 91 / Wednesday, May 11, 2011 / Rules and Regulations

**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 connectingframe 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


## 27234 Federal Register / Vol. 76, No. 91 / Wednesday, May 11, 2011 / Rules and Regulations

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.


## 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.



### T ABLE 

### 1—R ELATED 

### I NFORMATION

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.



### T ABLE 

### 2—A LL 

### M ATERIAL 

### I NCORPORATED BY 

### R EFERENCE

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.



### T ABLE 

### 3—N EW 

### M ATERIAL 

### I NCORPORATED BY 

### R EFERENCE

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.


## 27237 Federal Register / Vol. 76, No. 91 / Wednesday, May 11, 2011 / Rules and Regulations

(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).



### T ABLE 

### 4—M ATERIAL 

### P REVIOUSLY 

### I NCORPORATED BY 

### R EFERENCE

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.