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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 manager of the ACO, send it to the attention of the person identified in the

Related Information section of this AD.

(2) Before using any approved AMOC, notify your appropriate principal inspector, or lacking a principal inspector, the manager of the local flight standards district office/ certificate holding district office.

(3) All AMOCs approved for AD 2004–21– 08 (69 FR 62396, October 26, 2004) are approved for this AD.

(l) Related Information

For more information about this AD, contact Gary Park, Aerospace Engineer, Wichita ACO, FAA, 1801 Airport Road, Wichita, KS 67209; phone: (316) 946–4123; fax: (316) 946–4107; email: gary.park@faa.gov

. (m) Material Incorporated by Reference

(1) The Director of the Federal Register approved the incorporation by reference (IBR) of the service information listed in this paragraph under 5 U.S.C. 552(a) and 1 CFR
part 51.

(2) You must use this service information as applicable to do the actions required by this AD, unless the AD specifies otherwise.

(i) Cessna Aircraft Company Single Engine Service Bulletin SEB04–1, Revision 1, dated October 3, 2012.

(ii) Reserved. (3) For Cessna Aircraft Company service information identified in this AD, contact Cessna Aircraft Company, Customer service, P.O. Box 7706, Wichita, KS 67277; telephone: (316) 517–5800; fax: (316) 517–7271; email:
customercare@cessna.textron.com; Internet: http://www.cessnasupport.com

.

(4) You may view this service information at FAA,, Small Airplane Directorate, 901 Locust, Kansas City, MO 64106. For information on the availability of this material at the FAA, call (816) 329–4148.

(5) You may view this 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/cfr/ibrlocations.html

.

Issued in Kansas City, Missouri, on March

14, 2013.
Earl Lawrence,
Manager, Small Airplane Directorate, Aircraft Certification Service.

[FR Doc. 2013–06589 Filed 4–3–13; 8:45 am]

**BILLING CODE 4910–13–P** 

### DEPARTMENT OF TRANSPORTATION

**Federal Aviation Administration**

**14 CFR Part 39**

**[Docket No. FAA–2012–0994; Directorate Identifier 2012–NM–119–AD; Amendment**  **39–17402; AD 2013–06–05]**

**RIN 2120–AA64**



### Airworthiness Directives; The Boeing **Company Airplanes**

**AGENCY** 

### : Federal Aviation Administration (FAA), DOT.

**ACTION** 

### : Final rule.

**SUMMARY** 

### : We are superseding an existing airworthiness directive (AD) for all The Boeing Company Model 737– 600, –700, –700C, –800, –900, and –900ER series airplanes. That AD currently requires repetitive inspections of the aft attach lugs of the elevator tab control mechanisms, and replacement of any discrepant elevator tab control mechanism. This new AD requires replacing the left and right elevator tab
control mechanisms with elevator tab
control mechanisms that have the modified attach lugs, which would terminate the existing requirements. This AD was prompted by reports of failure of the aft attach lugs on the elevator tab control mechanisms, which resulted in severe elevator vibration; and reports of gaps in elevator tab control mechanisms and analysis indicating that additional elevator tab control mechanisms might have bearings that will come loose. We are issuing this AD to prevent discrepancies in the aft attach lugs of the elevator tab control mechanism, which could result
in severe elevator and tab vibration. Consequent structural failure of the
elevator or horizontal stabilizer could result in loss of structural integrity and
aircraft control.

**DATES** 

### : This AD is effective May 9, 2013.

The Director of the Federal Register approved the incorporation by reference of a certain publication listed in the AD as of May 9, 2013.

The Director of the Federal Register approved the incorporation by reference of a certain other publication listed in this AD as of September 9, 2010 (75 FR 52242, August 25, 2010).

The Director of the Federal Register approved the incorporation by reference of a certain other publication listed in this AD as of April 29, 2010 (75 FR 21499, April 26, 2010).

**ADDRESSES** 

### : For service information identified in this AD, contact Boeing Commercial Airplanes, Attention: Data & Services Management, P.O. Box 3707, MC 2H–65, Seattle, WA 98124–2207; telephone 206–544–5000, extension 1; fax 206–766–5680; Internet https:// www.myboeingfleet.com. You may review copies of the referenced service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. 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 Management Facility between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this AD, the regulatory evaluation, any comments received, and
other information. The address for the Docket Office (phone: 800–647–5527) is Document Management Facility, U.S. Department of Transportation, Docket Operations, M–30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE., Washington,

DC 20590.

**FOR FURTHER INFORMATION CONTACT** 

### : Kelly McGuckin, Aerospace Engineer, Systems and Equipment Branch, ANM– 130S, FAA, Seattle Aircraft Certification Office (ACO), 1601 Lind Avenue SW., Renton, Washington 98057–3356; phone: 425–917–6490; fax: 425–917– 6590; email: kelly.mcguckin@faa.gov

. **SUPPLEMENTARY INFORMATION** 

### :

Discussion

We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to supersede AD 2010–17–19, Amendment 39–16413 (75 FR 52242, August 25, 2010). (That AD superseded AD 2010–09–05, Amendment 39–16270 (75 FR 21499, April 26, 2010).) That AD applies to the specified products. The NPRM published in the Federal Register on September 20, 2012 (77 FR 58330). That NPRM proposed to continue to require repetitive inspections of the aft attach lugs of the elevator tab control mechanisms, and replacement of any discrepant elevator
tab control mechanism. That NPRM also proposed to require replacing the left and right elevator tab control
mechanisms with elevator tab control
mechanisms that have modified attach lugs, which would terminate the existing requirements.

Comments

We gave the public the opportunity to participate in developing this AD. The following presents the comments received on the proposal (77 FR 58330, September 20, 2012) and the FAA’s response to each comment. Aviation


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Partners Boeing stated that the installation of winglets per supplemental type certificate (STC) ST00830SE ( http://rgl.faa.gov/ Regulatory

_ and

_ Guidance

_Library/ rgstc.nsf/0/
408e012e008616a7862578880060456c/ $FILE/ST00830SE.pdf ) does not affect the accomplishment of the
manufacturer’s service instructions. United Airlines stated that it agrees with the proposal.

Request To Remove Parts Installation
Prohibition

Boeing requested that we remove paragraph (v) (‘‘New Parts Installation Prohibition’’) from the NPRM (77 FR 58330, September 20, 2012). Boeing
stated that we should allow installation of mechanisms having part number (P/ N) 251A2430–13, –14, –15, –16, –17, or –18 within the compliance time specified in the NPRM, and allow continued operations under the provisions of Boeing Alert Service Bulletin 737–27A1297, Revision 1, dated August 2, 2010; and AD 2010–17– 19, Amendment 39–16413 (75 FR 52242, August 25, 2010). Likewise, Boeing requested that we allow installation of mechanisms having P/N 251A2430–101, –102, –103, –104, –105, or –106 within the compliance time specified in the NPRM, and allow continued operations under the provisions of Boeing Alert Service Bulletin 737–27A1299, dated July 1, 2011; and Boeing Alert Service Bulletin 737–27A1299, Revision 1, dated April 16, 2012; which are approved as alternative methods of compliance (AMOCs) to AD 2010–17–19. The commenter stated that paragraph (v) of the NPRM (which would prohibit installing those parts as of the effective date of the AD) would reduce operator flexibility by prematurely forcing incorporation of Boeing Service Bulletin 737–27–1300, dated April 16, 2012,
before the end of the 60-month compliance period. The commenter added that this also would prevent incorporation of Boeing Alert Service Bulletin 737–27A1299, Revision 1, dated April 16, 2012, which Boeing plans to recommend that operators incorporate by April 2013 if they cannot complete terminating action by that
date.

We partially agree with the request. We agree to allow operators the continued flexibility of using the noted
mechanisms in accordance with the provisions of AD 2010–17–19, Amendment 39–16413 (75 FR 52242, August 25, 2010), or AMOCs specified in Boeing Alert Service Bulletin 737– 27A1299, dated July 1, 2011, and Boeing Alert Service Bulletin 737–27A1299, Revision 1, dated April 16, 2012, before the replacement specified in paragraph (u) of this AD. That replacement is required for airplanes with line numbers 1 through 3909 inclusive. This will provide flexibility and still maintain an adequate level of safety. We disagree, however, with deleting paragraph (v) of
this AD. The referenced mechanisms
have contributed to a known unsafe
condition and must not be used as a spare after the incorporation of paragraph (u) of this AD (which requires replacement of these mechanisms). We have changed paragraph (v) in this final rule to limit the prohibition against installing the referenced parts to a time after the requirements of paragraph (u) have been accomplished for airplanes with line numbers 1 through 3909 inclusive. For airplanes with line numbers 3910 and subsequent,
mechanisms with modified aft attach lugs have been installed in production; for these airplanes, the parts referenced in paragraph (v) of this AD are prohibited from installation as of the
effective date of this AD.

Request To Revise Identity of
Referenced Mechanisms

Boeing requested that we revise paragraph (t) of the NPRM (77 FR 58330, September 20, 2012) to limit the affected
mechanisms to mechanism P/Ns ‘‘251A2430–13, –14, –15, –16, –17, or –18.’’ Boeing stated that this paragraph should not apply to P/N 251A2430–23 and –24 mechanisms, because their installation is terminating action for the
NPRM. The commenter added that paragraph (t) of the NPRM also does not apply to the –101, –102, –103, –104, –105, or –106 mechanism, which have a minimum proposed repetitive inspection requirement of 800 flight hours (not 300 flight hours).

We do not agree to incorporate the requested changes in the final rule. Paragraph (t) of the AD restates the requirements of paragraph (t) of AD 2010–17–19, Amendment 39–16413 (75 FR 52242, August 25, 2010). The replacement required by paragraph (u)
of this new AD terminates the requirements of AD 2010–17–19, including paragraph (t). The FAA approved an AMOC to AD 2010–17–19 for Boeing Alert Service Bulletin 737– 27A1299, dated July 1, 2011; and Boeing Alert Service Bulletin 737–27A1299, Revision 1, dated April 16, 2012; for the requirements of paragraph (t) for the –101, –102, –103, –104, –105, and –106 mechanisms; as specified in paragraph (x)(4) of this AD, that AMOC still applies. We have not changed the final rule regarding this issue. Request To Remove Compliance Time

Restriction

Boeing requested that we revise the NPRM (77 FR 58330, September 20, 2012) to delete ‘‘and until the effective
date of this new AD’’ from the second sentence of paragraph (t) of the proposed AD. The commenter stated that operators should be allowed to install P/N 251A2430–13, –14, –15, –16, –17, or –18 mechanisms within the compliance period specified in the NPRM and continue operations under the provisions of Boeing Alert Service Bulletin 737–27A1297, Revision 1, dated August 2, 2010; and AD 2010–17– 19, Amendment 39–16413 (75 FR 52242, August 25, 2010).

We agree with the request and have revised paragraph (t) accordingly in this final rule. We are also clarifying the requirements of paragraph (t) in this
final rule for line numbers 3910 and subsequent, which are produced with part numbers that terminate the requirements of AD 2010–17–19, Amendment 39–16413 (75 FR 52242, August 25, 2010).

Request To Revise Cost Estimate

Delta requested that we revise the estimated costs in the NPRM (77 FR 58330, September 20, 2012). Delta stated that the cost information provided in
the NPRM does not reflect the most current information available in Boeing
Service Bulletin 737–27–1300 Information Notice (IN) 01, dated April 19, 2012, which gives a total of 16 task hours for each installed mechanism (32 hours per airplane) and 10 hours for each modified component (20 hours per airplane).

We agree, and have revised the cost estimate accordingly in this final rule.

Request To Extend Compliance Time
for Related AMOC

Delta, American, and Boeing requested that we revise the NPRM (77 FR 58330, September 20, 2012) to extend the compliance time for the AMOC associated with AD 2010–17–19, Amendment 39–16413 (75 FR 52242, August 25, 2010). American and Delta
stated that we should allow that AMOC
to remain valid until the accomplishment of the actions specified in paragraph (u) of the NPRM to allow the fullest benefit of the clip installation. Boeing stated that paragraph (v) of the NPRM conflicts with paragraph (x)(3) of the NPRM regarding the AMOC. Delta stated that Boeing Alert Service Bulletin 737– 27A1299, Revision 1, dated April 16, 2012, notes that the AMOC was
intended as interim action and has an


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expiration date of June 30, 2016; Delta concluded that AMOC approval would therefore expire before the 60-month compliance time specified in the NPRM for the replacement in paragraph (u) of
the NPRM.

We agree with the requests, for the reasons provided by the commenters. We have changed paragraph (x)(4) in this final rule to extend the expiration
of the referenced AMOCs.

Request To Clarify Reporting Requirement

Delta requested that we revise the NPRM (77 FR 58330, September 20, 2012) to clarify the required methods and requirements for reporting completion of the retrofit. Delta noted that paragraph (u) of the NPRM specifies to replace the elevator tab control
mechanism in accordance with the Accomplishment Instructions of Boeing Service Bulletin 737–27–1300, dated April 16, 2012. Delta stated that the last step of those instructions specifies reporting retrofit completions to Boeing using the service request application on MyBoeingFleet.com. Delta noted that the NPRM does not specifically identify any requirement to report the tab mechanism retrofit completions.

We agree to clarify the reporting requirements: Although Boeing Service Bulletin 737–27–1300, dated April 16, 2012, specifies submitting a report, there is no new reporting requirement to report completion of the replacement required by paragraph (u) of this AD. We have changed paragraph (u) in this
final rule to state that there is no reporting requirement as part of the replacement.

Request To Revise Applicability

American requested that we revise paragraph (c) (‘‘Applicability’’) of the NPRM (77 FR 58330, September 20, 2012) to match the applicability of paragraph (u) (mechanism replacement) of the NPRM (which applied to line numbers 1 through 3909 inclusive). American stated that Boeing Alert Service Bulletin 737–27A1297, Revision 2, dated April 16, 2012; and Boeing Alert Service Bulletin 737–27A1299, Revision 1, dated April 16, 2012; have been revised to limit the effectivity of
this issue.

We disagree with the request to revise the applicability. The applicability of this final rule includes the effectivity of
those service bulletins. But the applicability of this AD extends to all Model 737–600, -700, -700C, -800, -900, and -900ER series airplanes to account for spares that might also be installed on those airplanes, as specified in paragraph (v) (‘‘New Parts Installation Prohibition’’) in this final rule. We have
not revised the final rule further regarding this issue.

Explanation of Change Made to This

AD

We have added paragraph (x)(3) in this final rule to specify that an AMOC that provides an acceptable level of safety may be used for any repair required by this AD if that repair is approved by the Boeing Commercial Airplanes Organizational Designation Authorization (ODA) that has been authorized by the Manager of the Seattle
Aircraft Certification Office to make those findings.

Conclusion

We reviewed the relevant data, considered the comments received, and determined that air safety and the public interest require adopting the AD with the changes described previously and minor editorial changes. We have determined that these minor changes:

• Are consistent with the intent that was proposed in the NPRM (77 FR 58330, September 20, 2012) for correcting the unsafe condition; and

• Do not add any additional burden upon the public than was already proposed in the NPRM (77 FR 58330, September 20, 2012).

We also determined that these changes will not increase the economic burden on any operator or increase the scope of the AD.

Costs of Compliance

We estimate that this AD affects 1,096 airplanes of U.S. registry. We estimate the following costs to comply with this

AD:



### E STIMATED 

### C OSTS

Action Labor cost Parts cost Cost per product

Retained actions ................................ 7 work-hours × $85 per hour = $595 per inspection cycle. $0 ..................................................... $595 per inspection cycle.

Mechanism replacement (one option

for terminating action). 32 work-hours × $85 per hour = $2,720. $58,579 1 $1,140 (installation kit) ..... $62,439 per airplane.

Mechanism modification and replacement (one option for terminating action). 52 work-hours × $85 per hour = $4,420. $5,858 (for the modification) $1,140 (installation kit) $2,145 (tooling 2 ). $13,563 per airplane.

1 This is the estimated cost for both a left and right mechanism. Boeing is planning a seed/exchange program so operators are not forced to purchase a new mechanism.

2 Per the Boeing service information, tooling is available from Boeing for $90 per day.



### 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 have determined that this AD will not have federalism implications under Executive Order 13132. This AD will
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 that this AD:

(1) Is not a ‘‘significant regulatory action’’ under Executive Order 12866,

(2) Is not a ‘‘significant rule’’ under DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979),


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(3) Will not affect intrastate aviation in Alaska, and

(4) 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.

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 airworthiness directive (AD) 2010–17–19, Amendment 39–16413 (75 FR 52242, August 25, 2010), and adding the following new AD:

2013–06–05 The Boeing Company: Amendment 39–17402; Docket No. FAA–2012–0994; Directorate Identifier

2012–NM–119–AD.

(a) Effective Date

This AD is effective May 9, 2013.

(b) Affected ADs

This AD supersedes AD 2010–17–19, Amendment 39–16413 (75 FR 52242, August 25, 2010).

(c) Applicability

This AD applies to all The Boeing Company Model 737–600, –700, –700C, –800, –900, and –900ER series airplanes, certificated in any category.

(d) Subject

Joint Aircraft System Component (JASC)/ Air Transport Association (ATA) of America Code 27, Flight Controls.

(e) Unsafe Condition

This AD was prompted by reports of failure of the aft attach lugs on the elevator tab control mechanisms, which resulted in
severe elevator vibration. This AD also results from reports of gaps in elevator tab control mechanisms and analysis that
additional elevator tab control mechanisms might have bearings that will come loose. We are issuing this AD to prevent discrepancies in the aft attach lugs of the elevator tab control mechanism, which could result in severe elevator and tab vibration. Consequent
structural failure of the elevator or horizontal
stabilizer could result in loss of structural integrity and aircraft control. (f) Compliance
Comply with this AD within the compliance times specified, unless already
done.

(g) Retained Repetitive Inspections for Group 1 Airplanes

This paragraph restates the requirements of paragraph (g) of AD 2010–17–19, Amendment 39–16413 (75 FR 52242, August 25, 2010). For Group 1 airplanes, as identified in Boeing Alert Service Bulletin 737–27A1297, dated April 16, 2010: Except as required by paragraph (h) of this AD, within 12 days after April 29, 2010 (the effective date of AD 2010–09–05, Amendment 39–16270 (75 FR 21499, April 26, 2010)), do a detailed inspection for discrepancies of the inboard and outboard aft attach lugs of the left and right elevator tab control mechanisms, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 737–27A1297, dated April 16, 2010. Repeat the inspection thereafter at intervals not to exceed 300 flight hours. Doing the replacement specified in paragraph (l) of this AD before September 9, 2010 (the effective date of AD 2010–17–19), terminates the requirements of this paragraph. Doing the inspection required by paragraph (n) of this AD terminates the requirements of this paragraph.

(h) Retained Extended Twin Operations (ETOPS) Flight Provisions

This paragraph restates the requirements of paragraph (h) of AD 2010–17–19, Amendment 39–16413 (75 FR 52242, August 25, 2010). For Group 1 airplanes as identified in Boeing Alert Service Bulletin 737– 27A1297, dated April 16, 2010: Beginning 7 days after April 29, 2010 (the effective date of AD 2010–09–05, Amendment 39–21499 (75 FR 21499, April 26, 2010)), no person may operate an airplane on an ETOPS flight unless the initial inspection required by paragraph (g) of this AD has been accomplished. Doing the inspection required by paragraph (n) of this AD terminates the requirements of this paragraph.

(i) Retained One-Time Inspection for Group 2, Configuration 1, Airplanes

This paragraph restates the requirements of paragraph (i) of AD 2010–17–19, Amendment 39–16413 (75 FR 52242, August 25, 2010). For Group 2, Configuration 1, airplanes as identified in Boeing Alert Service Bulletin 737–27A1297, dated April 16, 2010: Within 30 days after April 29, 2010 (the effective date of AD 2010–09–05, Amendment 39– 16270 (75 FR 21499, April 26, 2010)), do a one-time detailed inspection for discrepancies of the inboard and outboard aft attach lugs of the left and right elevator tab control mechanisms, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 737–27A1297, dated April 16, 2010. Doing the inspection required by paragraph (n) of this AD terminates the requirements of this paragraph.

(j) Corrective Actions for Paragraphs (g), (i), and (k) of This AD

This paragraph restates the requirements of paragraph (j) of AD 2010–17–19, Amendment 39–16413 (75 FR 52242, August 25, 2010). If, during any inspection required by paragraph (g), (i), or (k) of this AD, any discrepancy is found, before further flight, replace the elevator tab control mechanism by doing the actions specified in paragraphs (j)(1) and (j)(2) of this AD.

(1) Do a detailed inspection for discrepancies of the replacement elevator tab control mechanism; and, if no discrepancy is found, install the replacement elevator tab control mechanism; in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 737–27A1297, dated April 16, 2010. If any discrepancy is found, then
that elevator tab control mechanism cannot be installed and the actions specified in this paragraph must be done before further flight on another replacement elevator tab control
mechanism.

(2) Re-inspect the installed elevator tab control mechanism using the inspection procedure specified in paragraph (i) of this

AD.

(k) Retained Repetitive Inspections for Certain Group 2, Configuration 1, Airplanes

This paragraph restates the requirements of paragraph (k) of AD 2010–17–19, Amendment 39–16413 (75 FR 52242, August 25, 2010). For Group 2, Configuration 1, airplanes as identified in Boeing Alert Service Bulletin 737–27A1297, dated April 16, 2010, on which the elevator tab control mechanism is replaced with a mechanism other than a new, Boeing-built mechanism: Within 300 flight hours after doing the replacement, do a detailed inspection for discrepancies of the inboard and outboard aft attach lugs of the left and right elevator tab control mechanisms, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 737–27A1297, dated April 16, 2010. Repeat the inspection thereafter at intervals not to exceed 300 flight hours. Doing the replacement specified in paragraph (l) of this AD before September 9, 2010 (the effective date of AD 2010–17–19, Amendment 39–16413 (75 FR 52242, August 25, 2010)), is terminating action for this paragraph. Doing the inspection required by paragraph (n) of this AD terminates the requirements of this paragraph.

(l) Terminating Action Credit for Paragraphs (g), (i), and (k) of This AD

This paragraph restates the requirements of paragraph (l) of AD 2010–17–19, Amendment 39–16413 (75 FR 52242, August 25, 2010). Replacing an elevator tab control mechanism with a new, Boeing-built mechanism before September 9, 2010 (the effective date of AD 2010–17–19), as specified in paragraphs (l)(1) and (l)(2) of this AD, terminates the inspections required by paragraphs (g), (i), and (k) of this AD. Replacement of the
elevator tab control mechanism on or after September 9, 2010 (the effective date of AD 2010–17–19), does not terminate the inspections required by paragraphs (g), (i), and (k) of this AD.

Note 1 to paragraph (l) of this AD: Additional guidance can be found in paragraphs 3.B.7.b.(1)(a)(1) and 3.B.7.b.(1)(a)(2) of the Accomplishment Instructions of Boeing Alert Service Bulletin


## 20233 Federal Register / Vol. 78, No. 65 / Thursday, April 4, 2013 / Rules and Regulations

737–27A1297, dated April 16, 2010, for establishing whether the mechanism is Boeing built.

(1) Do a detailed inspection for discrepancies of the new, Boeing-built replacement elevator tab control mechanism; and, if no discrepancy is found, install the replacement elevator tab control mechanism; in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 737–27A1297, dated April 16, 2010. If any discrepancy is found, then that elevator tab
control mechanism cannot be installed and the actions specified in this paragraph must be done on another new, Boeing-built replacement elevator tab control mechanism.

(2) Re-inspect the installed elevator tab control mechanism using the inspection procedure specified in paragraph (i) of this

AD.

(m) Retained Reporting for Paragraphs (g), (i), and (k) of This AD

This paragraph restates the requirements of paragraph (m) of AD 2010–17–19, Amendment 39–16413 (75 FR 52242, August 25, 2010). For airplanes identified in Boeing Alert Service Bulletin 737–27A1297, dated April 16, 2010: At the applicable time specified in paragraph (m)(1) or (m)(2) of this AD, submit a report of any findings (positive and negative) of the first inspection required by paragraphs (g), (i), and (k) of this AD, and any positive findings from the repetitive inspections required by paragraphs (g) and (k) of this AD, to Boeing Commercial Airplanes Group, Attention: Manager, Airline Support, email: rse.boecom@boeing.com . The report must include the inspection results including a description of any discrepancies found, the airplane line number, and the total number of flight cycles and flight hours accumulated on the airplane.

(1) If the inspection was done on or after April 29, 2010 (the effective date of AD 2010–09–05, Amendment 39–16270 (75 FR 21499, April 26, 2010)): Submit the report within 10 days after the inspection.

(2) If the inspection was done before April 29, 2010 (the effective date of AD 2010–09– 05, Amendment 39–16270 (75 FR 21499, April 26, 2010)): Submit the report within 10 days after April 29, 2010 (the effective date of AD 2010–09–05).

(n) Retained Repetitive Inspections

This paragraph restates the requirements of paragraph (n) of AD 2010–17–19, Amendment 39–16413 (75 FR 52242, August 25, 2010). For airplanes having line numbers 1 through 3909 inclusive: At the applicable time specified in paragraph (n)(1), (n)(2), or (n)(3) of this AD, do a detailed inspection for discrepancies of the inboard and outboard aft attach lugs of the left and right elevator tab control mechanisms, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 737–27A1297, Revision 1, dated August 2, 2010. For Groups 1 and 2 airplanes identified in Boeing Alert Service Bulletin 737–27A1297, Revision 1, dated August 2, 2010, repeat the inspection thereafter at intervals not to exceed 300 flight hours, except as provided by paragraph (t)(2) of this AD. For Group 3 airplanes identified in Boeing Alert Service Bulletin 737– 27A1297, Revision 1, dated August 2, 2010, repeat the inspection thereafter at intervals not to exceed 1,800 flight hours, except as required by paragraphs (p) and (t)(2) of this AD. Doing the inspection specified in this paragraph terminates the requirements of paragraphs (g), (h), (i), and (k) of this AD.

(1) For Group 1 airplanes identified in Boeing Alert Service Bulletin 737–27A1297, Revision 1, dated August 2, 2010: Within 300 flight hours after doing an inspection in accordance with Boeing Alert Service Bulletin 737–27A1297, dated April 16, 2010, or within 30 days after September 9, 2010 (the effective date of AD 2010–17–19, Amendment 39–16413 (75 FR 52242, August 25, 2010)), whichever occurs later.

(2) For Group 2 airplanes identified in Boeing Alert Service Bulletin 737–27A1297, Revision 1, dated August 2, 2010: At the later of the times specified in paragraphs (n)(2)(i) and (n)(2)(ii) of this AD.

(i) Before the accumulation of 2,000 total flight cycles or 4,000 total flight hours,
whichever occurs first.

(ii) Within 14 days after September 9, 2010 (the effective date of AD 2010–17–19, Amendment 39–16413 (75 FR 52242, August 25, 2010)).

(3) For Group 3 airplanes identified in Boeing Alert Service Bulletin 737–27A1297, Revision 1, dated August 2, 2010: Within 180 days or 1,800 flight hours after September 9, 2010 (the effective date of AD 2010–17–19, Amendment 39–16413 (75 FR 52242, August 25, 2010)), whichever occurs first.

(o) Retained Corrective Actions for Paragraphs (n) and (p) of This AD

This paragraph restates the requirements of paragraph (o) of AD 2010–17–19, Amendment 39–16413 (75 FR 52242, August 25, 2010). If, during any inspection required by paragraph (n) or (p) of this AD, any discrepancy is found, before further flight, replace the elevator tab control mechanism by doing the actions specified in paragraphs (o)(1) and (o)(2) of this AD.

(1) Do a detailed inspection for discrepancies of the replacement elevator tab control mechanism; and, if no discrepancy is found, install the replacement elevator tab control mechanism; in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 737–27A1297, Revision 1, dated August 2, 2010. If any discrepancy is found, then that elevator tab control
mechanism cannot be installed and the actions specified in this paragraph must be done before further flight on another replacement elevator tab control mechanism.

(2) Re-inspect the installed elevator tab control mechanism using the inspection procedure specified in paragraph (n) of this

AD.

(p) Retained Reduced Repetitive Inspection Interval for Group 3 Airplanes

This paragraph restates the requirements of paragraph (p) of AD 2010–17–19, Amendment 39–16413 (75 FR 52242, August 25, 2010). For Group 3 airplanes as identified in Boeing Alert Service Bulletin 737– 27A1297, Revision 1, dated August 2, 2010,
on which the elevator tab control mechanism is replaced during the actions required by paragraph (o) of this AD: Within 300 flight hours after doing the replacement, do a detailed inspection for discrepancies of the inboard and outboard aft attach lugs of the replaced elevator tab control mechanism, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 737–27A1297, Revision 1, dated August 2, 2010. Repeat the inspection of the replaced
elevator tab control mechanism thereafter at intervals not to exceed 300 flight hours, except as provided by paragraph (t)(2) of this

AD.

(q) Retained Credit for Previous Action

This paragraph restates the provisions specified in paragraph (q) of AD 2010–17–19, Amendment 39–16413 (75 FR 52242, August 25, 2010). For Group 1 airplanes as identified in Boeing Alert Service Bulletin 737– 27A1297, Revision 1, dated August 2, 2010: Inspections done in accordance with Boeing Alert Service Bulletin 737–27A1297, dated April 16, 2010, are acceptable for compliance with only the initial inspection required by paragraph (n) of this AD.

(r) Retained Reporting for Paragraphs (n) and (p) of This AD

This paragraph restates the requirements of paragraph (r) of AD 2010–17–19, Amendment 39–16413 (75 FR 52242, August 25, 2010). For airplanes having line numbers 1 through 3909 inclusive: At the applicable time specified in paragraph (r)(1) or (r)(2) of this AD, submit a report of any findings (positive and negative) of the first inspection required by paragraphs (n) and (p) of this AD, except for airplanes on which a report required by paragraph (m) of this AD has been submitted, only submit positive findings; and submit a report of any positive findings from the repetitive inspections required by paragraphs (n) and (p) of this AD; to Boeing Commercial Airplanes Group, Attention: Manager, Airline Support, email: rse.boecom@boeing.com . The report must include the inspection results including a description of any discrepancies found, the airplane line number, and the total number of flight cycles and flight hours accumulated on the airplane.

(1) If the inspection was done on or after September 9, 2010 (the effective date of AD 2010–17–19, Amendment 39–16413 (75 FR 52242, August 25, 2010)): Submit the report within 10 days after the inspection.

(2) If the inspection was done before September 9, 2010 (the effective date of AD 2010–17–19, Amendment 39–16413 (75 FR 52242, August 25, 2010)): Submit the report within 10 days after September 9, 2010 (the effective date of AD 2010–17–19).

(s) Retained Provision Regarding Not Returning Parts

This paragraph restates the provision specified in paragraph (s) of AD 2010–17–19, Amendment 39–16413 (75 FR 52242, August 25, 2010). Although Boeing Alert Service Bulletin 737–27A1297, dated April 16, 2010; and Boeing Alert Service Bulletin 737– 27A1297, Revision 1, dated August 2, 2010; specify to return the affected elevator tab control mechanism to the manufacturer, this AD does not require the return of the part to
the manufacturer.


## 20234 Federal Register / Vol. 78, No. 65 / Thursday, April 4, 2013 / Rules and Regulations

(t) Retained Parts Installation Limitations

This paragraph restates the requirements of paragraph (t) of AD 2010–17–19, Amendment 39–16413 (75 FR 52242, August 25, 2010), with revised limitations. As of September 9, 2010 (the effective date of AD 2010–17–19), and until the replacement required by paragraph (u) of this AD for airplanes with line numbers 1 through 3909 inclusive, or
until the effective date of this new AD for airplanes with line numbers 3910 and subsequent, as applicable: Comply with the conditions specified in paragraphs (t)(1) and (t)(2) of this AD.

(1) No person may install an elevator tab control mechanism, part number (P/N) 251A2430-(), on any airplane, unless the mechanism has been inspected before and after installation using the inspection procedures specified in paragraphs (o)(1) and (o)(2) of this AD, and no discrepancies have
been found.

(2) An elevator tab control mechanism, P/ N 251A2430-(), may be installed, provided that the inspection specified in paragraph (n) of this AD is done within 300 flight hours after doing the installation, and that the inspection specified in paragraph (n) of this AD is repeated thereafter at intervals not to exceed 300 flight hours.

(u) New Replacement

For airplanes having line numbers 1 through 3909 inclusive: Within 60 months after the effective date of this AD, replace the left and right elevator tab control
mechanisms with elevator tab control
mechanisms that have new machined aft attach lugs, in accordance with the Accomplishment Instructions of Boeing Service Bulletin 737–27–1300, dated April 16, 2012. This replacement terminates the requirements of paragraphs (g) through (t) of this AD. Although Boeing Service Bulletin 737–27–1300, dated April 16, 2012, specifies submitting a report, there is no requirement to report completion of the replacement required by paragraph (u) of this AD.

(v) New Parts Installation Prohibition

As of the effective date of this AD, no person may install, on any airplane identified in paragraph (v)(1) or (v)(2) of this AD, an elevator tab control mechanism having P/N
251A2430–13, –14, –15, –16, –17, –18, –101,
–102, –103, –104, –105, or –106.

(1) Airplanes on which the replacement in paragraph (u) of this AD has been accomplished.

(2) Airplanes with line numbers 3910 and subsequent.

(w) Paperwork Reduction Act Burden

Statement

A federal agency may not conduct or sponsor, and a person is not required to respond to, nor shall a person be subject to a penalty for failure to comply with a collection of information subject to the requirements of the Paperwork Reduction
Act unless that collection of information displays a current valid OMB Control
Number. The OMB Control Number for this
information collection is 2120–0056. Public reporting for this collection of information is estimated to be approximately 5 minutes per response, including the time for reviewing instructions, completing and reviewing the collection of information. All responses to this collection of information are mandatory. Comments concerning the accuracy of this burden and suggestions for reducing the
burden should be directed to the FAA at: 800 Independence Ave. SW., Washington, DC 20591, Attn: Information Collection Clearance Officer, AES–200.

(x) Alternative Methods of Compliance (AMOCs)

(1) The Manager, Seattle Aircraft Certification Office (ACO), 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 manager of the ACO, send it to the attention of the person identified in the
Related Information section of this AD. Information may be emailed to 9-ANMSeattle-ACO-AMOC-Requests@faa.gov

.

(2) Before using any approved AMOC, notify your appropriate principal inspector, or lacking a principal inspector, the manager of the local flight standards district office/ certificate holding district office.

(3) An AMOC that provides an acceptable level of safety may be used for any repair required by this AD if it is approved by the Boeing Commercial Airplanes Organization Designation Authorization (ODA) that has been authorized by the Manager, Seattle ACO, to make those findings. For a repair method to be approved, the repair must meet the certification basis of the airplane, and the approval must specifically refer to this AD.

(4) AMOCs approved for AD 2010–17–19, Amendment 39–16413 (75 FR 52242, August 25, 2010), are approved as AMOCs for the corresponding provisions of this AD. The expiration of the AMOCS to AD 2010–17–19, as specified in the service information identified in paragraphs (x)(4)(i) and (x)(4)(ii) of this AD, is extended to remain valid until accomplishment of the requirements of paragraph (u) of this AD.

(i) Boeing Alert Service Bulletin 737– 27A1299, dated July 1, 2011 (which is not incorporated by reference in this AD).

(ii) Boeing Alert Service Bulletin 737– 27A1299, Revision 1, dated April 16, 2012 (which is not incorporated by reference in this AD).

(y) Related Information

For more information about this AD, contact Kelly McGuckin, Aerospace Engineer, Systems and Equipment Branch, ANM–130S, FAA, Seattle Aircraft Certification Office (ACO), 1601 Lind Avenue SW., Renton, Washington 98057–3356; phone: 425–917–6490; fax: 425–917–6590;
email: kelly.mcguckin@faa.gov

. (z) Material Incorporated by Reference

(1) The Director of the Federal Register approved the incorporation by reference (IBR) of the service information listed in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51. (2) You must use this service information as applicable to do the actions required by this AD, unless the AD specifies otherwise.

(3) The following service information was approved for IBR on May 9, 2013.

(i) Boeing Service Bulletin 737–27–1300, dated April 16, 2012.

(ii) Reserved. (4) The following service information was approved for IBR on September 9, 2010 (75 FR 52242, August 25, 2010).

(i) Boeing Alert Service Bulletin 737– 27A1297, Revision 1, dated August 2, 2010.

(ii) Reserved. (5) The following service information was approved for IBR on April 29, 2010 (75 FR 21499, April 26, 2010).

(i) Boeing Alert Service Bulletin 737– 27A1297, dated April 16, 2010.

(ii) Reserved. (6) For service information identified in this AD, contact Boeing Commercial Airplanes, Attention: Data & Services Management, P.O. Box 3707, MC 2H–65, Seattle, WA 98124–2207; telephone 206– 544–5000, extension 1; fax 206–766–5680;

Internet https://www.myboeingfleet.com

.

(7) You may view this service information at FAA, You may review copies of the referenced service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425–227–1221.

(8) You may view this 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/cfr/ibrlocations.html

.

Issued in Renton, Washington, on March

20, 2013. Jeffrey E. Duven, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service.

[FR Doc. 2013–07209 Filed 4–3–13; 8:45 am]

**BILLING CODE 4910–13–P**



### DEPARTMENT OF TRANSPORTATION

**Federal Aviation Administration**

**14 CFR Part 39**

**[Docket No. FAA–2012–1014; Directorate Identifier 2010–SW–058–AD; Amendment**  **39–17404; AD 2013–06–07]**

**RIN 2120–AA64**



### Airworthiness Directives; Eurocopter **France Helicopters**

**AGENCY** 

### : Federal Aviation Administration (FAA), DOT.

**ACTION** 

### : Final rule.

**SUMMARY** 

### : We are adopting a new airworthiness directive (AD) for Eurocopter France (Eurocopter) Model SA–365N1, AS–365N2, and AS 365 N3