67044 Federal Register / Vol. 79, No. 218 / Wednesday, November 12, 2014 / Rules and Regulations 

request to your principal inspector or local 

Flight Standards District Office, as 

appropriate. If sending information directly 

to the International Branch, send it to ATTN: 

Sanjay Ralhan, Aerospace Engineer, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA, 1601 Lind 

Avenue SW., Renton, Washington 98057– 

3356; telephone 425–227–1405; fax 425–227– 

1149. Information may be emailed to: 9– 

ANM–116–AMOC–REQUESTS@faa.gov. 

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. The AMOC 

approval letter must specifically reference 

this AD. 

(2) Contacting the Manufacturer: For any 

requirement in this AD to obtain corrective 

actions from a manufacturer, the action must 

be accomplished using a method approved 

by the Manager, International Branch, ANM– 

116, Transport Airplane Directorate, FAA; or 

the European Aviation Safety Agency 

(EASA); or Airbus’s EASA Design 

Organization Approval (DOA). If approved by 

the DOA, the approval must include the 

DOA-authorized signature. 

(j) Related Information 

Refer to Mandatory Continuing 

Airworthiness Information (MCAI) European 

Aviation Safety Agency Airworthiness 

Directive 2013–0148, dated July 16, 2013, for 

related information. This MCAI may be 

found in the AD docket on the Internet at 

http://www.regulations.gov/

#!documentDetail;D=FAA-2014-0452-0002. 

(k) 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 this AD specifies otherwise. 

(i) Airbus A318/A319/A320/A321 

Airworthiness Limitations Section (ALS) Part 

3, Certification Maintenance Requirements 

(CMR), Revision 1, dated June 15, 2012. 

(ii) Reserved. 

(3) For service information identified in 

this AD, contact Airbus, Airworthiness 

Office—EIAS, 1 Rond Point Maurice 

Bellonte, 31707 Blagnac Cedex, France; 

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

93 44 51; email account.airworth-eas@

airbus.com; Internet http://www.airbus.com. 

(4) You may view this 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. 

(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 Renton, Washington, on October 

28, 2014. 

Jeffrey E. Duven, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2014–26436 Filed 11–10–14; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2013–0836; Directorate 

Identifier 2013–NM–126–AD; Amendment 

39–18011; AD 2014–22–06] 

RIN 2120–AA64 

Airworthiness Directives; the Boeing 

Company Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are superseding 

Airworthiness Directive (AD) 2005–07– 

12, which applies to certain the Boeing 

Company Model 737–100, –200, –200C, 

–300, –400, and –500 series airplanes. 

AD 2005–07–12 required detailed and 

eddy current inspections to detect 

cracking of the frame web around the 

cutout for the doorstop intercostal strap 

at the aft side of the station (STA) 291.5 

frame at stringer 16R, and corrective 

action if necessary. Since we issued AD 

2005–07–12, we received reports of new 

findings of cracking at various locations 

of the STA 277 to STA 291.5 frames and 

intercostals, including webs, chords, 

clips, and shear ties, between stringers 

7R and 17R. This new AD requires 

inspections for cracking at the forward 

galley door cutout, and corrective 

actions if necessary. This new AD also 

reduces a certain inspection threshold 

required by AD 2005–07–12. We are 

issuing this AD to detect and correct 

fatigue cracking of the aft frame and 

frame support structure of the forward 

galley door, which could result in a 

severed fuselage frame web, rapid 

decompression of the airplane, and 

possible loss of the forward galley door. 

DATES: This AD is effective December 

17, 2014. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of December 17, 2014. 

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 view 

copies of the referenced service 

information at the FAA, Transport 

Airplane Directorate, 1601 Lind Ave. 

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 by searching for 

and locating Docket No. FAA–2013– 

0836; 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 

Docket 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: 

Alan Pohl, Aerospace Engineer, 

Airframe Branch, ANM–120S, FAA, 

Seattle Aircraft Certification Office, 

1601 Lind Avenue SW., Renton, WA 

98057–3356; phone: 425–917–6450; fax: 

425–917–6590; email: alan.pohl@

faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to supersede AD 2005–07–12, 

Amendment 39–14036 (70 FR 17596, 

April 7, 2005). AD 2005–07–12 applied 

to certain The Boeing Company Model 

737–100, –200, –300, –400, and –500 

series airplanes. The NPRM published 

in the Federal Register on October 2, 

2013 (78 FR 60804). The NPRM was 

prompted by reports of new findings of 

cracking at various locations of the STA 

277 to STA 291.5 frames and 

intercostals, including webs, chords, 

clips, and shear ties, between stringers 

7R and 17R. The NPRM proposed to 

continue to require detailed and eddy 

current inspections to detect cracking of 

the frame web around the cutout for the 

doorstop intercostal strap at the aft side 

of the STA 291.5 frame at stringer 16R, 

and corrective action if necessary. The 

NPRM also proposed to require new 

inspections for cracking at the forward 

galley door cutout, and corrective 

actions if necessary. In addition, the 

NPRM also proposed to reduce a certain 

inspection threshold required by AD 

2005–07–12. We are issuing this AD to 


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detect and correct fatigue cracking of the 

aft frame and frame support structure of 

the forward galley door, which could 

result in a severed fuselage frame web, 

rapid decompression of the airplane, 

and possible loss of the forward galley 

door. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. The 

following presents the comments 

received on the NPRM (78 FR 60804, 

October 2, 2013), and the FAA’s 

response to each comment. 

Boeing stated that it concurs with the 

contents of the NPRM (78 FR 60804, 

October 2, 2013). 

Effect of Winglets on AD 

Aviation Partners Boeing stated that 

accomplishing the installation of 

winglets per supplemental type 

certificate (STC) ST01219SE (http://

rgl.faa.gov/Regulatory_and_Guidance_

Library/rgstc.nsf/0/

082838ee177dbf62862576a4005cdfc0/

$FILE/ST01219SE.pdf) does not affect 

the actions specified in the NPRM (78 

FR 60804, October 2, 2013). 

We concur with the commenter. We 

have redesignated paragraph (c) of the 

NPRM (78 FR 60804, October 2, 2013) 

as (c)(1) in this AD and added new 

paragraph (c)(2) to this AD to state that 

installation of STC ST01219SE (http://

rgl.faa.gov/Regulatory_and_Guidance_

Library/rgstc.nsf/0/

082838ee177dbf62862576a4005cdfc0/

$FILE/ST01219SE.pdf) does not affect 

the ability to accomplish the actions 

required by this final rule. Therefore, for 

airplanes on which STC ST01219SE is 

installed, a ‘‘change in product’’ 

alternative method of compliance 

(AMOC) approval request is not 

necessary to comply with the 

requirements of 14 CFR 39.17. 

Request To Clarify That Certain 

Inspections Are Not Required for Areas 

With Existing Repairs 

Southwest Airlines (SWA) requested 

that paragraph (h)(1) of the NPRM (78 

FR 60804, October 2, 2013), be revised 

to include language stating that when 

operators are accomplishing Steps 2 and 

6 in Part 2 of Paragraph 3.B., ‘‘Work 

Instructions,’’ of the Accomplishment 

Instructions of Boeing Alert Service 

Bulletin 737–53A1241, Revision 1, 

dated June 11, 2013, they do not need 

to do inspections in areas that are 

common to repairs that were previously 

approved by Boeing via FAA Form 

8100–9, ‘‘Statement of Compliance with 

Airworthiness Standards.’’ We infer that 

the basis for SWA’s request is that the 

existing repairs have inspections 

included in the engineering for those 

repairs, so the inspections included in 

the service information are not needed. 

SWA also requested that the NPRM 

(78 FR 60804, October 2, 2013), be 

revised to clarify that inspections are 

not required in areas that are common 

to existing repairs that were installed 

using a certain repair in the applicable 

Boeing Model 737 structural repair 

manual (SRM). SWA noted that Step 6 

in Part 2 of Paragraph 3.B., ‘‘Work 

Instructions,’’ of the Accomplishment 

Instructions of Boeing Alert Service 

Bulletin 737–53A1241, Revision 1, 

dated June 11, 2013, only addresses 

repetitive inspections when a new SRM 

repair is installed. We infer that SWA is 

suggesting that the service information 

should have also addressed repetitive 

inspections for areas with a certain 

existing SRM repair installed. 

We agree with the commenter. The 

inspections required by paragraph (h)(1) 

of this AD include detailed and surface 

eddy current inspections that cannot be 

accomplished with certain repairs 

installed. Repairs 1, 15, and 16, of 

Chapter 53 of the applicable Boeing 737 

SRM, are referenced in the 

Accomplishment Instructions of Boeing 

Alert Service Bulletin 737–53A1241, 

Revision 1, dated June 11, 2013, and are 

considered corrective actions for 

cracking found during the inspections 

required by paragraph (h)(1) of this AD. 

These SRM repairs can also be used as 

a preventive modification. 

We revised paragraph (h)(1) in this 

AD to state that ‘‘Accomplishment of a 

repair specified in Steps 1.a., 2.a., 6.a., 

or 6.b. of Part 2 of the Accomplishment 

Instructions of Boeing Alert Service 

Bulletin 737–53A1241, Revision 1, 

dated June 11, 2013, as applicable, and 

except as required by paragraph (k)(1) of 

this AD, terminates the inspections 

required by this paragraph for the 

repaired area(s) only.’’ 

Request To Address Notes 11 and 13 in 

the Service Information Regarding 

Existing Repairs and Existing Repairs 

at Certain Body Stations 

SWA requested clarification regarding 

existing repairs common to the 

inspection areas addressed in Part 2 of 

Paragraph 3.B., ‘‘Work Instructions,’’ of 

the Accomplishment Instructions of 

Boeing Alert Service Bulletin 737– 

53A1241, Revision 1, dated June 11, 

2013. SWA observed that Notes 11 and 

13 in Paragraph 3.A., ‘‘General 

Information,’’ of that service bulletin 

include provisions for omitting 

inspections in areas covered by repairs 

that were previously approved by 

Boeing via FAA Form 8100–9, 

‘‘Statement of Compliance with 

Airworthiness Standards,’’ but those 

notes are not included or referenced in 

Part 2 of Paragraph 3.B., ‘‘Work 

Instructions.’’ 

SWA also requested approval for 

existing repairs common to the body 

station (BS) 291.5 frame at locations 

from stringer (STR) 8R to STR 15R that 

were previously approved by Boeing via 

FAA Form 8100–9, ‘‘Statement of 

Compliance with Airworthiness 

Standards,’’ as terminating action for the 

inspection requirements in paragraph 

(h)(1) of the NPRM (78 FR 60804, 

October 2, 2013), for the repaired area 

only. 

Furthermore, SWA requested 

approval for existing repairs common to 

the BS 277 frame and shear ties between 

STR 7R and STR 17R that were 

previously approved by Boeing via FAA 

Form 8100–9, ‘‘Statement of 

Compliance with Airworthiness 

Standards,’’ or that were installed using 

certain repairs in the applicable Boeing 

737 SRM as terminating action for the 

inspection requirements of paragraph 

(h)(1) of the NPRM (78 FR 60804, 

October 2, 2013), for the repaired areas 

only. 

We agree that the existing repairs 

mentioned by the commenter can be 

used as terminating action for the 

inspection requirements of paragraph 

(h)(1) of this AD. Several SRM repairs 

are referenced in Steps 6.a. and 6.b. of 

Part 2 of the Accomplishment 

Instructions of Boeing Alert Service 

Bulletin 737–53A1241, Revision 1, 

dated June 11, 2013, and are considered 

corrective actions for cracking found 

during the inspections required by 

paragraph (h)(1) of this AD. The notes 

to Steps 6.a. and 6.b. state that the SRM 

repairs terminate the repetitive 

inspections. As stated previously, 

paragraph (h)(1) of this AD was revised 

accordingly. 

We have also added a new paragraph 

(i), Terminating Action, to this AD and 

redesignated subsequent paragraphs 

accordingly. Paragraph (i) of this AD 

states ‘‘The inspections required by 

paragraph (h)(1) of this AD may be 

terminated at areas with repairs 

installed prior to the effective date of 

this AD, provided the repairs meet the 

conditions specified in note 11 or note 

13 of paragraph 3.A., ‘‘General 

Information,’’ of the Accomplishment 

Instructions of Boeing Alert Service 

Bulletin 737–53A1241, Revision 1, 

dated June 11, 2013.’’ 

Request To Include Exception to the 

Service Information Specifications 

SWA requested that the NPRM (78 FR 

60804, October 2, 2013) address a 

typographical error that appears in the 


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title to figure 5 of Boeing Alert Service 

Bulletin 737–53A1241, Revision 1, 

dated June 11, 2013. SWA noted that the 

title refers to STR 16R, however, the 

inspection location is STR 14R. 

We agree to address this 

typographical error in Boeing Alert 

Service Bulletin 737–53A1241, Revision 

1, dated June 11, 2013, and have added 

a new paragraph (k)(3) to this AD to 

notify operators that the title to figure 5 

should reference STR 14R. 

Clarification of Affected Airplanes 

We have added ‘‘certificated in any 

category’’ to the applicability specified 

in paragraph (c)(1) of this AD to clarify 

the affected airplanes. 

Conclusion 

We reviewed the relevant data, 

considered the comments received, and 

determined that air safety and the 

public interest require adopting this 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 (78 FR 

60804, October 2, 2013) for correcting 

the unsafe condition; and 

• Do not add any additional burden 

upon the public than was already 

proposed in the NPRM (78 FR 60804, 

October 2, 2013). 

We also determined that these 

changes will not increase the economic 

burden on any operator or increase the 

scope of this AD. 

Costs of Compliance 

We estimate that this AD affects 419 

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 Cost on U.S. operators 

Inspections [retained from AD 

2005–07–12, Amendment 

39 14036 (70 FR 17596, 

April 7, 2005)].

2 work-hours × $85 per hour 

= $170 per inspection cycle.

None ........... $170 per inspection cycle ...... $71,230 per inspection cycle. 

Inspections [new proposed action].40 work-hours × $85 per hour 

= $3,400 per inspection 

cycle.

None ........... $3,400 per inspection cycle ... $1,424,600 per inspection 

cycle. 

We have received no definitive data 

that would enable us to provide a cost 

estimate for the on-condition actions 

specified in the service information. 

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), 

(3) Will not affect intrastate aviation 

in, 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) 

2005–07–12, Amendment 39–14036 (70 

FR 17596, April 7, 2005), and adding 

the following new AD: 

2014–22–06 The Boeing Company: 

Amendment 39–18011 ; Docket No. 

FAA–2013–0836; Directorate Identifier 

2013–NM–126–AD. 

(a) Effective Date 

This AD is effective December 17, 2014. 

(b) Affected ADs 

This AD replaces AD 2005–07–12, 

Amendment 39–14036 (70 FR 17596, April 7, 

2005). 

(c) Applicability 

(1) This AD applies to The Boeing 

Company Model 737–100, –200, –200C, 

–300, –400, and –500 series airplanes, 

certificated in any category, as identified in 

Boeing Alert Service Bulletin 737–53A1241, 

Revision 1, dated June 11, 2013. 

(2) Installation of Supplemental Type 

Certificate (STC) ST01219SE (http://

rgl.faa.gov/Regulatory_and_Guidance_

Library/rgstc.nsf/0/

082838ee177dbf62862576a4005cdfc0/$FILE/

ST01219SE.pdf) does not affect the ability to 

accomplish the actions required by this AD. 

Therefore, for airplanes on which STC 

ST01219SE is installed, a ‘‘change in 

product’’ alternative method of compliance 

(AMOC) approval request is not necessary to 

comply with the requirements of 14 CFR 

39.17. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 53, Fuselage. 

(e) Unsafe Condition 

This AD was prompted by reports of new 

findings of cracking at various locations of 

the stations (STA) 277 to STA 291.5 frames 

and intercostals, including webs, chords, 

clips, and shear ties, between stringers 7R 

and 17R. We are issuing this AD to detect 


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and correct fatigue cracking of the aft frame 

and frame support structure of the forward 

galley door, which could result in a severed 

fuselage frame web, rapid decompression of 

the airplane, and possible loss of the forward 

galley door. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Group 1 Airplanes: Inspections and 

Corrective Actions 

For airplanes identified as Group 1 in 

Boeing Alert Service Bulletin 737–53A1241, 

Revision 1, dated June 11, 2013: Within 120 

days after the effective date of this AD, do 

inspections for cracking from STA 277 to 

STA 328, stringer 7R to 17R of the forward 

galley door cutout, using a method approved 

in accordance with the procedures specified 

in paragraph (m) of this AD. Do all applicable 

corrective actions before further flight using 

a method approved in accordance with the 

procedures specified in paragraph (m) of this 

AD. 

(h) Group 2 and Group 3 Airplanes: 

Inspections and Corrective Actions 

(1) For airplanes identified as Group 2 and 

Group 3 in Boeing Alert Service Bulletin 

737–53A1241, Revision 1, dated June 11, 

2013: Except as provided by paragraph (k)(2) 

of this AD, at the applicable times specified 

in tables 1 and 2 in paragraph 1.E, 

‘‘Compliance,’’ of Boeing Alert Service 

Bulletin 737–53A1241, Revision 1, dated 

June 11, 2013, do detailed and surface high 

frequency eddy current (HFEC) inspections, 

as applicable, for cracking in the forward 

galley door cutout, in accordance with Part 

2 of the Accomplishment Instructions of 

Boeing Alert Service Bulletin 737–53A1241, 

Revision 1, dated June 11, 2013. Repeat the 

detailed and surface HFEC inspections 

thereafter at the applicable intervals specified 

in tables 1 and 2 in paragraph 1.E, 

‘‘Compliance,’’ of Boeing Alert Service 

Bulletin 737–53A1241, Revision 1, dated 

June 11, 2013. If any crack is found, before 

further flight, do all applicable corrective 

actions in accordance with Part 2 of the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 737–53A1241, Revision 1, 

dated June 11, 2013, except as required by 

paragraph (k)(1) of this AD. Accomplishment 

of a repair specified in Steps 1.a., 2.a., 6.a., 

or 6.b. of Part 2, of the Accomplishment 

Instructions of Boeing Alert Service Bulletin 

737–53A1241, Revision 1, dated June 11, 

2013, as applicable, and except as required 

by paragraph (k)(1) of this AD, terminates the 

inspections required by this paragraph for the 

repaired area(s) only. 

(2) Removal and replacement of a cracked 

part, in accordance with Part 2 of the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 737–53A1241, Revision 1, 

dated June 11, 2013, does not terminate the 

repetitive inspections required by paragraph 

(h)(1) of this AD. 

(i) Terminating Action 

The inspections required by paragraph 

(h)(1) of this AD may be terminated at areas 

with repairs installed prior to the effective 

date of this AD, provided the repairs meet the 

conditions specified in note 11 or note 13 of 

paragraph 3.A., ‘‘General Information,’’ of the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 737–53A1241, Revision 1, 

dated June 11, 2013. 

(j) Optional Terminating Action 

Accomplishment of the preventive 

modification on the STA 291.5 frame web, in 

accordance with Part 2 of the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 737–53A1241, Revision 1, 

dated June 11, 2013, terminates the 

inspections required by paragraph (h)(1) of 

this AD for the area that is common to the 

preventive modification. 

(k) Exceptions to the Service Information 

(1) Where Boeing Alert Service Bulletin 

737–53A1241, Revision 1, dated June 11, 

2013, specifies to contact Boeing for a 

corrective action: Before further flight, do the 

applicable action using a method approved 

in accordance with the procedures specified 

in paragraph (m) of this AD. 

(2) Where paragraph 1.E., ‘‘Compliance,’’ of 

Boeing Alert Service Bulletin 737–53A1241, 

Revision 1, dated June 11, 2013, specifies a 

compliance time ‘‘after the date on Revision 

1 of this service bulletin,’’ this AD requires 

compliance within the specified compliance 

time after the effective date of this AD. 

(3) The title to each page of figure 5 of 

Boeing Alert Service Bulletin 737–53A1241, 

Revision 1, dated June 11, 2013, is incorrect 

and refers to ‘‘Stringer 16R’’ when it should 

refer to ‘‘Stringer 14R.’’ 

(l) Credit for Previous Actions 

This paragraph provides credit for the 

actions specified in paragraph (h)(1) of this 

AD, if those actions were performed before 

the effective date of this AD using Boeing 

Alert Service Bulletin 737–53A1241, dated 

June 13, 2002, which is not incorporated by 

reference in this AD. 

(m) 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 

paragraph (n)(1) of this AD. Information may 

be emailed to: 9-ANM-Seattle-ACO-AMOCRequests@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 the actions 

specified in AD 2005–07–12, Amendment 

39–14036 (70 FR 17596, April 7, 2005), are 

approved as AMOCs for the corresponding 

provisions of this AD. 

(n) Related Information 

(1) For more information about this AD, 

contact Alan Pohl, Aerospace Engineer, 

Airframe Branch, ANM–120S, FAA Seattle 

Aircraft Certification Office, 1601 Lind 

Avenue SW., Renton, WA 98057–3356; 

phone: 425–917–6450; fax: 425–917–6590; 

email: alan.pohl@faa.gov. 

(2) Service information identified in this 

AD that is not incorporated by reference is 

available at the addresses specified in 

paragraphs (o)(3) and (o)(4) of this AD. 

(o) 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) Boeing Alert Service Bulletin 737– 

53A1241, Revision 1, dated June 11, 2013. (ii) 

Reserved. 

(3) For Boeing 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. 

(4) You may view this service information 

at FAA, Transport Airplane Directorate, 1601 

Lind Ave. SW., Renton, WA. For information 

on the availability of this material at the 

FAA, call 425–227–1221. 

(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 Renton, Washington, on October 

28, 2014. 

Jeffrey E. Duven, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2014–26434 Filed 11–10–14; 8:45 am] 

BILLING CODE 4910–13–P 


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