Federal Register / Vol. 78, No. 65 / Thursday, April 4, 2013 / Rules and Regulations 20229 

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: 

ESTIMATED COSTS

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.

$58,5791 $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 (tooling2).

$13,563 per airplane. 

1This 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. 2Per 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 


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

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. 


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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 


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