14992 Federal Register / Vol. 79, No. 52 / Tuesday, March 18, 2014 / Rules and Regulations 

Instructions of Boeing Alert Service Bulletin 

757–27A0153, dated May 9, 2012, as revised 

by Boeing Alert Service Bulletin 757– 

27A0153, Revision 1, dated October 29, 2012. 

(ii) Install a new rudder pedal pushrod 

connecting bolt, washer, nut, and cotter pin, 

in accordance with the Accomplishment 

Instructions of Boeing Alert Service Bulletin 

757–27A0153, dated May 9, 2012, as revised 

by Boeing Alert Service Bulletin 757– 

27A0153, Revision 1, dated October 29, 2012. 

(3) If the diameters of both holes are greater 

than 0.3140 inch on the assembly, before 

further flight, do the actions specified in 

paragraphs (h)(3)(i) and (h)(3)(ii) of this AD. 

(i) Install a new rudder pedal assembly, or 

install two bushings in the two worn holes, 

in accordance with the Accomplishment 

Instructions of Boeing Alert Service Bulletin 

757–27A0153, dated May 9, 2012, as revised 

by Boeing Alert Service Bulletin 757– 

27A0153, Revision 1, dated October 29, 2012. 

(ii) Install a new rudder pedal pushrod 

connecting bolt, washer, nut, and cotter pin, 

in accordance with the Accomplishment 

Instructions of Boeing Alert Service Bulletin 

757–27A0153, dated May 9, 2012, as revised 

by Boeing Alert Service Bulletin 757– 

27A0153, Revision 1, dated October 29, 2012. 

(i) Parts Installation Prohibition 

As of the effective date of this AD, no 

person may install, in a rudder pedal 

assembly of any Boeing Model 757 airplane, 

a bolt having part number (P/N) 

BACB30NM5DK47. 

(j) Credit for Previous Actions 

This paragraph provides credit for the 

actions required by paragraphs (g) and (h) of 

this AD, if operators installed washers having 

P/N NAS1149D0516J, NAS1149D0532J, and 

NAS1149D0563J, and if those actions were 

performed before the effective date of this AD 

using Boeing Alert Service Bulletin 757– 

27A0153, dated May 9, 2012, as unmodified 

by Boeing Alert Service Bulletin 757– 

27A0153, Revision 1, dated October 29, 2012. 

(k) 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 (l)(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. 

(l) Related Information 

(1) For more information about this AD, 

contact Marie Hogestad, Aerospace Engineer, 

Systems and Equipment Branch, ANM–130S, 

Seattle Aircraft Certification Office, FAA, 

1601 Lind Avenue SW., Renton, WA 98057– 

3356; phone: 425–917–6418; fax: 425–917– 

6590; email: marie.hogestad@faa.gov. 

(2) Service information identified in this 

AD that is not incorporated by reference in 

this AD may be obtained at the address 

specified in paragraphs (m)(3) and (m)(4) of 

this AD. 

(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) Boeing Alert Service Bulletin 757– 

27A0153, dated May 9, 2012. 

(ii) Boeing Alert Service Bulletin 757– 

27A0153, Revision 1, dated October 29, 2012. 

(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, 1601 Lind Avenue SW., Renton, WA 

98057–3356. 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 February 

19, 2014. 

Jeffrey E. Duven, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2014–04843 Filed 3–17–14; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2013–0327; Directorate 

Identifier 2011–NM–161–AD; Amendment 

39–17794; AD 2014–05–21] 

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) 2008–11– 

04 for all The Boeing Company Model 

737–100, –200, –200C, –300, –400, and 

–500 series airplanes. AD 2008–11–04 

required repetitive inspections for 

cracking in and around the upper and 

lower hinge cutouts of the forward entry 

and forward galley service doorways, 

and corrective actions if necessary. This 

new AD reduces the inspection 

threshold for cracking in and around the 

galley service doorway hinge cutouts, 

adds inspections of certain repaired 

structure at the forward entry and galley 

service doorway upper and lower hinge 

cutouts, expands the inspection area at 

the forward entry and galley service 

doorway upper and lower hinge cutouts, 

and removes certain airplanes from the 

applicability. This AD was prompted by 

multiple reports of cracks in the skin 

and/or bear strap at the forward galley 

service doorway hinge cutouts, and 

multiple reports of cracking under the 

repairs installed at the hinge cutouts. 

We are issuing this AD to detect and 

correct such cracking, which could 

result in rapid decompression of the 

airplane. 

DATES: This AD is effective April 22, 

2014. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of April 22, 2014. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain other publication listed in 

this AD as of June 25, 2008 (73 FR 

29421, May 21, 2008). 

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; 

phone: 206–544–5000, extension 1; fax: 

206–766–5680; Internet: https://

www.myboeingfleet.com. You may view 

this referenced service information at 

the FAA, Transport Airplane 


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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 by searching for 

and locating Docket No. FAA–2013– 

0327; 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, Seattle 

Aircraft Certification Office (ACO), 

FAA, 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 2008–11–04, 

Amendment 39–15526 (73 FR 29421, 

May 21, 2008). AD 2008–11–04 applied 

to all The Boeing Company Model 737– 

100, –200, –200C, –300, –400, and –500 

series airplanes. The NPRM published 

in the Federal Register on April 16, 

2013 (78 FR 22439). The NPRM was 

prompted by multiple reports of cracks 

in the skin and/or bear strap at the 

forward galley service doorway hinge 

cutouts, and multiple reports of 

cracking under the repairs installed at 

the hinge cutouts. The NPRM proposed 

to reduce the inspection threshold for 

cracking in and around the galley 

service doorway hinge cutouts, add 

inspections of certain repaired structure 

at the forward entry and galley service 

doorway upper and lower hinge cutouts, 

expand the inspection area at the 

forward entry and galley service 

doorway upper and lower hinge cutouts, 

and remove certain airplanes from the 

applicability. We are issuing this AD to 

detect and correct such cracking, which 

could result in rapid decompression of 

the airplane. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. The 

following presents the comments 

received on the proposal (78 FR 22439, 

April 16, 2013) and the FAA’s response 

to each comment. 

Request to Add Service Information 

Southwest Airlines (SWA) and Boeing 

requested we add a provision to the 

NPRM (78 FR 22439, April 16, 2013) to 

specify that performing a repair in 

accordance with ‘‘Boeing 737–300/ 

–400/–500 Structural Repair Manual 

(SRM) 53–10–01, Repair 14 and Repair 

15’’ is considered terminating action for 

the requirements of paragraph (j) of the 

NPRM for the repaired location. Boeing 

stated that the repairs are in the 

referenced SRM, and those repairs 

incorporate the procedures specified in 

Note 10 of paragraph 3.A., ‘‘General 

Information,’’ of the Accomplishment 

Instructions of Boeing Service Bulletin 

737–53A1200, Revision 2, dated 

September 12, 2012. 

We agree that certain SRM repairs 

meet the conditions specified in Note 10 

of paragraph 3.A., ‘‘General 

Information,’’ of the Accomplishment 

Instructions of Boeing Service Bulletin 

737–53A1200, Revision 2, dated 

September 12, 2012. However, to 

include SRM repairs in this final rule 

would unnecessarily delay issuance of 

the final rule. Boeing may apply for a 

global alternative method of compliance 

(AMOC) on behalf of the affected 

operators in accordance with the 

procedures specified in paragraph (p) of 

this final rule. We have not changed this 

final rule in this regard. 

Request to Allow Terminating Action 

for Inspections 

All Nippon Airways (ANA) stated that 

no further action should be necessary if 

the repair meets the conditions 

specified in Note 10 of paragraph 3.A., 

‘‘General Information,’’ of the 

Accomplishment Instructions of Boeing 

Service Bulletin 737–53A1200, Revision 

2, dated September 12, 2012, and that 

this should be addressed in paragraph 

(k)(3) of the NPRM (78 FR 22439, April 

16, 2013), which terminates paragraph 

(g) of the NPRM. 

We agree with the commenter’s 

request. The conditions provided in 

Note 10 of paragraph 3.A., ‘‘General 

Information,’’ of the Accomplishment 

Instructions of Boeing Service Bulletin 

737–53A1200, Revision 2, dated 

September 12, 2012, ensure that the 

non-SRM repairs were developed to 

preclude further cracking. 

We note that there is no paragraph 

(k)(3) in the NPRM (78 FR 22439, April 

16, 2013), and infer that ANA meant to 

request that a new paragraph (k)(3) be 

added to this final rule. Instead, we 

have added new paragraph (n) to this 

final rule and redesignated subsequent 

paragraphs accordingly. New paragraph 

(n) of this final rule states that the 

inspections required by paragraph (j) of 

this final rule may be terminated at 

areas with repairs installed prior to the 

effective date of this final rule if those 

repairs meet the conditions specified in 

Note 10 of paragraph 3.A., ‘‘General 

Information,’’ of the Accomplishment 

Instructions of Boeing Service Bulletin 

737–53A1200, Revision 2, dated 

September 12, 2012. 

Request to Include AMOC Approval 

Boeing requested that we modify 

paragraph (o)(4) of the NPRM (78 FR 

22439, April 16, 2013) (paragraph (p)(4) 

in this final rule) to include the 

additional conditions shown in Note 10 

of paragraph 3.A., ‘‘General 

Information,’’ of the Accomplishment 

Instructions of Boeing Service Bulletin 

737–53A1200, Revision 2, dated 

September 12, 2012. Boeing stated that 

the paragraph should state that AMOCs 

approved previously for paragraphs (f) 

and (i) of AD 2008–11–04, Amendment 

39–15526 (73 FR 29421, May 21, 2008), 

are approved as AMOCs for the 

corresponding provisions of paragraphs 

(g) and (i) of the NPRM, provided that 

the repairs meet the criteria of Note 10 

of paragraph 3.A., ‘‘General 

Information,’’ of the Accomplishment 

Instructions of Boeing Service Bulletin 

737–53A1200, Revision 2, dated 

September 12, 2012. Boeing stated that 

the conditions provided in Note 10 of 

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

of the Accomplishment Instructions of 

Boeing Service Bulletin 737–53A1200, 

Revision 2, dated September 12, 2012, 

ensure that the repairs were developed 

to preclude post-modification cracking. 

We do not agree with the commenter’s 

request. The commenter’s concerns are 

adequately addressed in paragraph 

(k)(2) of this final rule, which requires 

additional actions when repairs do not 

meet the conditions specified in Note 10 

of paragraph 3.A., ‘‘General 

Information,’’ of the Accomplishment 

Instructions of Boeing Service Bulletin 

737–53A1200, Revision 2, dated 

September 12, 2012, whether or not the 

repair was approved previously as an 

AMOC for AD 2008–11–04, Amendment 

39–15526 (73 FR 29421, May 21, 2008). 

We have not changed this final rule in 

this regard. 


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Request to Add AMOC Approval for 

Paragraph (g) of the NPRM (78 FR 

22439, April 16, 2013) 

ANA requested that we add a new 

paragraph (o)(5) to the NPRM (78 FR 

22439, April 16, 2013) to clarify that 

AMOCs approved previously for the 

requirements of paragraph (f) of AD 

2008–11–04, Amendment 39–15526 (73 

FR 29421, May 21, 2008), are approved 

as AMOCs for paragraph (g) of the 

NPRM. ANA stated that if the repair 

meets the criteria specified in Note 10 

of paragraph 3.A., ‘‘General 

Information,’’ of the Accomplishment 

Instructions of Boeing Service Bulletin 

737–53A1200, Revision 2, dated 

September 12, 2012, then the inspection 

required by paragraph (g) of the NPRM 

should be terminated even if an AMOC 

statement in FAA Form 8100–9 

(Statement of Compliance with 

Airworthiness Standards) is not the 

same as paragraph (o)(4) of the NPRM. 

ANA asserted that a new AMOC to the 

NPRM will be necessary if the AMOC 

statement only refers to paragraph (f) of 

AD 2008–11–04, Amendment 39–15526 

(73 FR 29421, May 21, 2008). 

We do not agree. Paragraph (p)(4) of 

this final rule (which was designated as 

paragraph (o)(4) of the NPRM (78 FR 

22439, April 16, 2013)), as currently 

worded, addresses ANA’s concern. A 

repair which has an AMOC for only 

paragraph (f) of AD 2008–11–04, 

Amendment 39–15526 (73 FR 29421, 

May 21, 2008), would be approved as an 

AMOC for the corresponding provisions 

of paragraph (g) of this final rule. 

Further, we understand ANA to mean 

that this particular repair satisfies the 

conditions specified in Note 10 of 

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

of the Accomplishment Instructions of 

Boeing Service Bulletin 737–53A1200, 

Revision 2, dated September 12, 2012. If 

this is the case, then new paragraph (n) 

of this final rule, discussed previously, 

means that this repair satisfies the 

requirements of paragraph (j) of this 

final rule, which would terminate the 

inspection requirements of paragraph (f) 

of AD 2008–11–04, Amendment 39– 

15526 (73 FR 29421, May 21, 2008) in 

the repaired area. We have not changed 

this final rule in this regard. 

Request to Change Optional 

Terminating Action Paragraph (i) of the 

NPRM (78 FR 22439, April 16, 2013) 

SWA requested that we delete Note 1 

to paragraph (i) of the NPRM (78 FR 

22439, April 16, 2013), which states that 

‘‘Guidance on repairs can be found in 

Boeing 737–100/–200 SRM 53–30–1, 

Figure 20, 21, 31, or 32; or Boeing 737– 

300/–400/–500 SRM 53–10–01, Repair 

5, 6, or 8; as applicable.’’ SWA noted 

that Boeing 737–300/–500 SRM 53–10– 

01, Repairs 5, 6, and 8 have been 

removed as they are no longer 

applicable. SWA stated that the NPRM 

(78 FR 22439, April 16, 2013) is in error 

when it states that guidance on repairs 

can be found in these locations. 

We agree with SWA’s request. 

Subsequent to the issuance of AD 2008– 

11–04, Amendment 39–15526 (73 FR 

29421, May 21, 2008), Boeing removed 

the noted SRM repairs from the 737– 

300/–400/–500 SRMs. For the Boeing 

737–100/200 SRM, the noted repairs 

were not removed, but each page was 

watermarked OBSOLETE. For clarity, 

we have deleted Note 1 to paragraph (i) 

of this final rule. 

Boeing requested that we not retain 

paragraph (i) from AD 2008–11–04, 

Amendment 39–15526 (73 FR 29421, 

May 21, 2008). Boeing asserted that 

paragraph (i) of AD 2008–11–04 

provides terminating actions for 

airplanes on which areas were repaired 

in accordance with ‘‘Boeing 737–100/ 

–200 SRM 53–30–1, Figures 20, 21, 31, 

or 32; or Boeing 737–300/–400/–500 

SRM 53–10–01, Repair 5, 6, or 8.’’ 

Boeing stated that allowing the repairs 

listed in paragraph (i) of the NPRM (78 

FR 22439, April 16, 2013) as terminating 

action would conflict with Boeing 

Service Bulletin 737–53A1200, Revision 

2, dated September 12, 2012, and 

paragraph (k) of the NPRM. Boeing 

added that Boeing Service Bulletin 737– 

53A1200, Revision 2, dated September 

12, 2012, requires follow-on inspections 

for SRM repairs, which are required 

based on fleet reports showing crack 

susceptibility after the repair has been 

installed. Boeing stated that new repairs 

are now provided in the SRM. 

We disagree with the commenter’s 

request. Paragraph (i) of AD 2008–11– 

04, Amendment 39–15526 (73 FR 

29421, May 21, 2008), is not retained as 

written in AD 2008–11–04, but rather it 

is retained ‘‘. . . with revised method of 

compliance language. . . .’’ Paragraph 

(i) states, ‘‘The inspections specified in 

paragraph (g) of this AD may be 

terminated at areas repaired using a 

method approved in accordance with 

the procedures specified in paragraph 

(p) [AMOC] of this AD.’’ Thus, operators 

cannot continue to install the noted 

obsolete/removed repairs specified 

previously in AD 2008–11–04. Boeing 

has addressed repairs installed 

previously by providing inspections for 

them in Boeing Service Bulletin 737– 

53A1200, Revision 2, dated September 

12, 2012. These inspections are 

mandated by paragraph (k) of this final 

rule. We have not changed this final 

rule in this regard. 

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 

22439, April 16, 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 22439, 

April 16, 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 547 

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 [actions retained 

from AD 2008-11-04, 

Amendment 39-15526 (73 

FR 29421, May 21, 2008)].

Up to 73 work-hours × $85 

per hour = $6,205 per inspection cycle.

$0 Up to $6,205 per inspection 

cycle.

Up to $3,394,135 per inspection cycle. 

Inspection [new action] .......... Up to 34 work-hours × $85 

per hour = $2,890 per inspection cycle.

0 Up to $2,890 per inspection 

cycle.

Up to $1,580,830 per inspection cycle. 


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We have received no definitive data 

that would enable us to provide cost 

estimates for the on-condition actions 

specified in this AD. 

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 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) 

2008–11–04, Amendment 39–15526 (73 

FR 29421, May 21, 2008), and adding 

the following new AD: 

2014–05–21 The Boeing Company: 

Amendment 39–17794; Docket No. 

FAA–2013–0327; Directorate Identifier 

2011–NM–161–AD. 

(a) Effective Date 

This AD is effective April 22, 2014. 

(b) Affected ADs 

This AD supersedes AD 2008–11–04, 

Amendment 39–15526 (73 FR 29421, May 21, 

2008). 

(c) Applicability 

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 Service 

Bulletin 737–53A1200, Revision 2, dated 

September 12, 2012. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 53, Fuselage. 

(e) Unsafe Condition 

This AD was prompted by multiple reports 

of cracks in the skin and/or bear strap at the 

forward galley service doorway hinge 

cutouts, and multiple reports of cracking 

under the repairs installed at the hinge 

cutouts. We are issuing this AD to detect and 

correct such cracking, which could result in 

rapid decompression of the airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Retained Repetitive Inspections 

This paragraph restates the requirements of 

paragraph (f) of AD 2008–11–04, Amendment 

39–15526 (73 FR 29421, May 21, 2008). 

Except as provided by paragraph (h)(1) of this 

AD, at the applicable times specified in 

paragraph 1.E. ‘‘Compliance,’’ of Boeing Alert 

Service Bulletin 737–53A1200, dated April 

13, 2006, do external detailed, low frequency 

eddy current (LFEC), high frequency eddy 

current (HFEC), and HFEC rotary probe 

inspections, as applicable, for cracks in and 

around the upper and lower hinge cutouts of 

the forward entry and forward galley service 

doorways, in accordance with the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 737–53A1200, dated April 

13, 2006, except as provided by paragraphs 

(h)(2) and (i) of this AD. Do not exceed the 

applicable repetitive interval for the previous 

inspection, as specified in Boeing Alert 

Service Bulletin 737–53A1200, dated April 

13, 2006, as Option A or Option B. Repair 

any crack before further flight using a method 

approved in accordance with the procedures 

specified in paragraph (p) of this AD. 

Accomplishment of the actions required by 

paragraph (j) of this AD terminates the 

requirements of this paragraph. 

(h) Retained Exceptions to Service Bulletin 

Specifications 

This paragraph restates the requirements of 

paragraphs (g) and (h) of AD 2008–11–04, 

Amendment 39–15526 (73 FR 29421, May 21, 

2008). 

(1) Where Boeing Alert Service Bulletin 

737–53A1200, dated April 13, 2006, specifies 

a compliance time after the release date of 

that service bulletin, this AD requires 

compliance within the specified compliance 

time after June 25, 2008 (the effective date of 

AD 2008–11–04, Amendment 39–15526 (73 

FR 29421, May 21, 2008)). 

(2) Although Boeing Alert Service Bulletin 

737–53A1200, dated April 13, 2006, specifies 

contacting Boeing for information about 

installing an optional preventive 

modification that would terminate the 

repetitive inspections specified in paragraph 

(g) of this AD, this AD requires that any 

terminating action be done by using a 

method approved in accordance with the 

procedures specified in paragraph (p) of this 

AD. 

(i) Retained Optional Terminating Action 

This paragraph restates the optional 

terminating action specified paragraph (i) of 

AD 2008–11–04, Amendment 39–15526 (73 

FR 29421, May 21, 2008), with revised 

method of compliance language and removal 

of note 1 to paragraph (i) of this AD. The 

inspections specified in paragraph (g) of this 

AD may be terminated at areas repaired using 

a method approved in accordance with the 

procedures specified in paragraph (p) of this 

AD. 

(j) New Repetitive Inspections and Repair 

Except as required by paragraph (l)(1) of 

this AD, at the applicable times specified in 

Paragraph 1.E., ‘‘Compliance,’’ of Boeing 

Service Bulletin 737–53A1200, Revision 2, 

dated September 12, 2012: Do an external 

and internal detailed inspection, HFEC 

inspection, and HFEC hole probe inspection, 

at the forward entry and galley service 

doorway upper and lower hinge cutouts for 

cracking in the skin, bonded doubler, 

bearstrap, and frame outer chord, in 

accordance with the Accomplishment 

Instructions of Boeing Service Bulletin 737– 

53A1200, Revision 2, dated September 12, 

2012, except as required by paragraph (m) of 

this AD. Options provided in Boeing Service 

Bulletin 737–53A1200, Revision 2, dated 

September 12, 2012, for accomplishing the 

inspections are acceptable for compliance 

with the corresponding requirements of this 

paragraph. Repeat the applicable inspections 

thereafter at the applicable times specified in 

paragraph 1.E., ‘‘Compliance,’’ of Boeing 

Service Bulletin 737–53A1200, Revision 2, 

dated September 12, 2012. If any crack is 

found, before further flight, repair using a 

method approved in accordance with the 

procedures specified in paragraph (p) of this 

AD. Accomplishment of the initial 


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14996 Federal Register / Vol. 79, No. 52 / Tuesday, March 18, 2014 / Rules and Regulations 

inspections terminates the requirements of 

paragraph (g) of this AD. 

(k) New Actions for Airplanes With Certain 

Repairs Installed 

(1) For airplanes with any structural repair 

manual (SRM) repair specified in paragraphs 

(k)(1)(i) through (k)(1)(vii) of this AD 

installed, at the applicable times specified in 

paragraph 1.E., ‘‘Compliance,’’ of Boeing 

Service Bulletin 737–53A1200, Revision 2, 

dated September 12, 2012: Do an external 

and internal detailed inspection, HFEC 

inspection, and LFEC inspection, at the 

forward entry and galley service doorway 

upper and lower hinge cutouts for cracking 

in the skin, bearstrap, and frame outer chord, 

in accordance with the Accomplishment 

Instructions of Boeing Service Bulletin 737– 

53A1200, Revision 2, dated September 12, 

2012, except as required by paragraph (l)(2) 

of this AD. Repeat the inspection thereafter 

at the applicable times specified in paragraph 

1.E., ‘‘Compliance,’’ of Boeing Service 

Bulletin 737–53A1200, Revision 2, dated 

September 12, 2012. If any crack is found, 

before further flight, repair using a method 

approved in accordance with the procedures 

specified in paragraph (p) of this AD. 

(i) Repair specified in Boeing 737–100/ 

–200 SRM 53–30–03, Figure 21. 

(ii) Repair specified in Boeing 737–100/200 

SRM 53–30–03, Figure 31. 

(iii) Repair 5 specified in Boeing 737–300 

SRM 53–10–01; Repair 5 specified in Boeing 

737–400 SRM 53–10–01; or Repair 5 

specified in Boeing 737–500 SRM 53–10–01; 

installed at the upper or lower hinge cutout. 

(iv) Repair specified in Boeing 737–100/

200 SRM 53–30–03, Figure 20. 

(v) Repair 6 specified in Boeing 737–300 

SRM 53–10–01; Repair 6 specified in Boeing 

737–400 SRM 53–10–01; or Repair 6 

specified in Boeing 737–500 SRM 53–10–01. 

(vi) Repair 8 specified in Boeing 737–300 

SRM 53–10–01; Repair 8 specified in Boeing 

737–400 SRM 53–10–01; or Repair 8 

specified in Boeing 737–500 SRM 53–10–01. 

(vii) Repair specified in Boeing 737–100/

200 SRM 53–30–03, Figure 32. 

(2) For airplanes with any repair installed 

at the forward entry doorway or forward 

galley doorway, upper or lower hinge cutout, 

that does not meet the conditions specified 

in Note 10 of paragraph 3.A., ‘‘General 

Information,’’ of the Accomplishment 

Instructions of Boeing Service Bulletin 737– 

53A1200, Revision 2, dated September 12, 

2012: Except as required by paragraph (l) of 

this AD, at the applicable times specified in 

paragraph 1.E., ‘‘Compliance,’’ of Boeing 

Service Bulletin 737–53A1200, Revision 2, 

dated September 12, 2012, contact the 

Manager, Seattle ACO, FAA, for instructions, 

using the procedures specified in paragraph 

(p) of this AD, and do the actions required 

by the FAA. 

(l) New Exception to Service Bulletin 

Specifications 

(1) Where Boeing Service Bulletin 737– 

53A1200, Revision 2, dated September 12, 

2012, specifies a compliance time after the 

issue date of Boeing Service Bulletin 737– 

53A1200, Revision 1, dated July 7, 2011, this 

AD requires compliance within the specified 

compliance time after the effective date of 

this AD. 

(2) Where Boeing Service Bulletin 737– 

53A1200, Revision 2, dated September 12, 

2012, specifies to contact Boeing for further 

instructions, this AD requires contacting the 

Manager, Seattle Aircraft Certification Office 

(ACO), FAA, for instructions and doing the 

actions required by the FAA, using the 

procedures specified in paragraph (p) of this 

AD. 

(m) Exception for Group 5 Airplanes 

For Group 5 airplanes identified in Boeing 

Service Bulletin 737–53A1200, Revision 2, 

dated September 12, 2012: Before further 

flight, contact the Manager, Seattle ACO, 

FAA, for instructions, using the procedures 

specified in paragraph (p) of this AD, and do 

the actions required by the FAA. 

(n) Terminating Actions 

The inspections required by paragraph (j) 

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 10 of paragraph 

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

Accomplishment Instructions of Boeing 

Service Bulletin 737–53A1200, Revision 2, 

dated September 12, 2012. 

(o) Credit for Previous Actions 

This paragraph provides credit for the 

actions required by paragraphs (j) and (k) of 

this AD, if those actions were performed 

before the effective date of this AD using 

Boeing Alert Service Bulletin 737–53A1200, 

Revision 1, dated July 7, 2011, which is not 

incorporated by reference in this AD. 

(p) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Seattle 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 (q)(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 previously for 

paragraphs (f) and (i) of AD 2008–11–04, 

Amendment 39–15526 (73 FR 29421, May 21, 

2008), are approved as AMOCs for the 

corresponding provisions of paragraphs (g) 

and (i) of this AD. 

(q) Related Information 

(1) For more information about this AD, 

contact Alan Pohl, Aerospace Engineer, 

Airframe Branch, ANM–120S, Seattle 

Aircraft Certification Office (ACO), FAA, 

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 may 

be obtained at the addresses specified in 

paragraphs (r)(5) and (r)(6) of this AD. 

(r) 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 April 22, 2014. 

(i) Boeing Service Bulletin 737–53A1200, 

Revision 2, dated September 12, 2012. 

(ii) Reserved. 

(4) The following service information was 

approved for IBR on June 25, 2008 (73 FR 

29421, May 21, 2008). 

(i) Boeing Alert Service Bulletin 737– 

53A1200, dated April 13, 2006. 

(ii) Reserved. 

(5) 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; phone: 206–544– 

5000, extension 1; fax: 206–766–5680; 

Internet: https://www.myboeingfleet.com. 

(6) 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. 

(7) 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 February 

19, 2014. 

Jeffrey E. Duven, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2014–04838 Filed 3–17–14; 8:45 am] 

BILLING CODE 4910–13–P 


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